Choose timezone
Your profile timezone:
2023 Clean Space Industry Days
→
Europe/Paris
ESTEC
ESTEC
Keplerlaan 1, 2201 AZ Noordwijk, The Netherlands
Description
The European Space Agency (ESA) is organising the 2023 Clean Space Industry Days. The event will take place from 16th to 20th October 2023 at ESTEC, The Netherlands.
The Clean Space Industry Days (CSID) 2023 is a must-attend event for all space professionals and enthusiasts working on designing and building sustainable space missions!
The five-day event will focus on the progress made in the fields of
- eco-design for space,
- end-of-life management,
- active debris removal and in-orbit servicing
Furthermore, the CSID will explore ways to consolidate the ESA Zero Debris approach.
ESA Zero Debris approach
The ESA Zero Debris approach was put forward at the ESA Council at the Ministerial level in 2022 and received great support from Member States. The new goal forms a key element to succeed in the implementation of ESA’s Agenda 2025 and the new PROTECT accelerator – working towards timely and accurate warnings of threats alongside measures to deal with them. The Zero Debris Approach expands ESA’s efforts within the Space Safety Programme and its related Clean Space initiative. Both are managed at ESA’s Directorate of Operations and aim at protecting life and infrastructure on Earth and in orbit.
Zero Debris outlines a series of actions and initiatives aimed at helping ESA in taking a strategic and proactive approach to safeguarding our space environment for future generations. The world leading Zero Debris approach will not only help to protect the functioning of satellites and the safety of human life on Earth, but also ensure that the benefits of space activities are enjoyed by all nations for many years to come.
The Zero Debris approach relies on the work performed in the frame of End-of-life Management and ADRIOS (Active Debris Removal and In-Orbit Servicing). Therefore, both clean space branches will be covered during the event, and an overview of the Zero Debris approach will be presented. Workshops will also be organised to allow the participants to give feedback to ESA on how to further implement and consolidate the approach.
End-of-life management
ESA’s clean space initiative has been developing technologies to prevent the creation of future debris and has been implementing system activities to promote their integration in future missions, thus feeding the Zero Debris approach.
The event will give the opportunity to present and discuss the latest outcomes on the following fundamental topics to comply with and anticipate the current and future space debris mitigation requirements:
- technologies for Design for demise
- technologies for Design for Removal
- technologies for Passivation
- technologies for Deorbiting
Abstracts related to these topics will be much appreciated.
Active Debris Removal and In-Orbit Servicing
During the Clean Space Industry, ESA encourages abstracts across various topics in the frame of Active Debris Removal and In-Orbit Servicing
Active Debris Removal
ESA is working together with ClearSpace on the implementation of an active debris removal (ADR) mission, ClearSpace-1. This mission will remove an existing debris, the VESPA upper part, which has been on-orbit since 2013. During the Clean Space Industry Days there will be an update on this mission, together with other ADR and inspection missions under implementation and in preparation by both ESA and European industry.
Commercial In-Orbit Servicing
Globally significant progress has been made in both the technical and commercial validation of in-orbit servicing activities such as debris removal, AOCS takeover for life extension, asset relocation, refuelling and in-orbit inspection. Looking forward, ESA aims to contribute to the creation of the demand for In-Orbit Servicing (IOS) in Europe by fostering both the service-offering side and to stimulate and enable the demand side of the developing IOS market. Recent IOS related activities conducted under ESA contracts highlighted the strong interest from commercial operators for life extension through Attitude and Orbit Control System (AOCS) takeover in Geostationary (GEO) orbit. At the Council Meeting at Ministerial Level in November 2022 (CM22), States participating to the Space Safety Programme (S2P) demonstrated strong support and ambitions for commercial In-Orbit Servicing (IOS). During the Clean Space Industry Days, ESA will present the latest regarding In-Orbit Servicing Mission Developments involving both service providers and commercial customers of IOS applications and welcomes abstracts in this area.
Circular Economy
In the long-term, IOS should enable the concept of a circular economy, with services such as in-orbit assembling, refueling, manufacturing and recycling and, even in space manufacturing and recycling. Therefore, abstracts related to circular economy in space will be also welcome, on top of in-orbit services and debris removal related matters.
Technology Development
Preparation is key for future In-Orbit Servicing Missions, in particular the derisking activities performed in technology developments. Abstracts on the latest state-of-the-art for GNC, capture systems, propulsion systems and avionics relevant for ADR and IOS are encouraged.
Close Proximity Operations
Increasing worldwide interest in the execution of rendezvous, proximity and capture operations for in-orbit servicing such as repair, refuelling, and tugging has highlighted the lack of clear and widely accepted technical and safety standards for uncrewed vehicles. There will be a dedicated session to cover standards and guidelines that enable commercial in-orbit servicing which are fundamental for building a common understanding between Agencies, insurers, integrators, equipment providers and licensing authorities.
Eco-design for space
ESA Director General reiterated in the Agenda 2025 that making ESA “a greener organisation” is a priority. This entails developing cleaner space missions and thus requires assessing and understanding their environmental footprint from the design phase to their end-of-life. A comprehensive understanding of the environmental footprint of space missions is paramount in order to:
- foster the application of ecodesign practices from early phases,
- comply with the expectations of European citizens in terms of environmental management,
- mitigate the risks of supply chain disruption from the early stages of the design because of stringent environmental regulations,
- prepare industry and decision makers for future challenges while remaining competitive,
- prepare roadmaps to develop greener technologies which can reduce the impacts of space missions
ESA Clean Space office has been working for more than a decade to achieve that goals and will take advantage of the 2023 CSID edition to further share the knowledge acquired, the latest developments and achievements as well as the challenges encountered. The clean space team is expecting the same from the professionals joining the event and is looking forward discussing any ways forward to enforce the European space sector’s position towards a greener space.
Abstracts related to the above listed topics are welcome.
Registration
Participation is free of charge. However, a registration is required. If you wish to attend the event, please register here.
Call for abstract
Submit your abstract for the CSID2023 here. If your abstract is selected, we will only ask you to give a presentation during the clean space industry days 2023 (no paper needed).
Please note the following deadlines:
- 10 September 2023: Abstract submission deadline has been extended!
- 18 September 2023: Announcement of the abstracts selected
- 8 October 2023: Registration deadline
- 16-19 October 2023: Presentations at CSID2023
Contact
-
-
14:00
→
14:30
Welcome & Opening: Welcome & Opening by Holger Krag Erasmus: High Bay
Erasmus: High Bay
-
14:30
→
15:00
Welcome & Opening: Pioneering the Way: Clean Space Initiatives Spotlight by Luisa Innocenti Erasmus: High Bay
Erasmus: High Bay
-
15:00
→
15:30
Refreshment break 30m
-
15:30
→
16:30
Welcome & Opening: Panel "Towards a cleaner and safer space" Erasmus: High Bay
Erasmus: High Bay
-
16:30
→
17:00
Welcome & Opening: Legal framework for Space Debris Mitigation and Removal by Alexander Soucek Erasmus: High Bay
Erasmus: High Bay
-
14:00
→
14:30
-
-
09:30
→
11:00
Ecodesign for Space: ESA's Ecodesign and Sustainability Spotlight
-
09:30
Opening of the Ecodesign sessions by Dietmar Pilz, ESA Director of Technology, Engineering and Quality 10m
- 09:40
-
10:10
Building bridges between organizational GHG assessment and environmental footprint at system level: the ESA Green Agenda 20m
ESA strives for being the role model for a modern global space agency fully committed to improve the sustainability and social responsibility of space activities by:
Increasing the contribution of its projects to the sustainable development of society (Agenda 2025: “(…) ensure that ESA and European space programmes can support the implementation of the Paris Agreement and the European Green Deal to the fullest extent.”)
Ensuring the socially & environmentally responsible management of its activities (Agenda 2025: “The Agency will improve its own environmental responsibility, to contribute to the climate neutrality of Europe. By 2030, ESA’s greenhouse gas emissions will be decreased by 46.2% for Scope 1, 2 and 28% for Scope 3 if compared to 2019.”)
To implement this vision, the Agency has adopted an ESA Green Agenda (EGA) along five high-level objectives and is updating its organizational carbon footprint on a yearly basis.
The main objective of the presentation is to demonstrate how LCA and Ecodesign activities contributes and are considered essential to reach the ESA Green Agenda targets.
In particular, LCA knowledge is essential to:
(1) Lower the uncertainty of calculation of the GHG assessment Scope 3 emissions categories so called “Purchase of goods and services “ and “Use of sold products” (GHG Protocol standard denomination),
(2) Identify the rights levers at corporate levels and,
(3) Put into lights environmental impacts knowledge gaps.
Therefore, the presentation will focus on the complementarity of the two approaches and the ESA wide approach towards environmental impact reduction of space systems and ESA Green Agenda success.
A specific focus will be given on the methodological development associated to GHG assessment Scope 3 emissions categories so called “Purchase of goods and services “ and “Use of sold products”. Strengths and weak points of the methodology will also be discussed as well as potential future improvement through upcoming case studies.
In addition, relevance of the methodology towards more robust calculation of Scope 3 and in particular in anticipation to European Corporate Sustainability Reporting Directive (CSRD) for the Space Industry will be addressed.
Finally, as part of the methodology, other positive effects on the environment and on the sustainable development of society at large, such as contribution to the European Green Deal objectives and UN Sustainable Development Goals, will also be addressed.
Speakers: Aurélie Gallice-Tanguy (ESA), Marta Caterina Salieri Lopez -
10:30
Environmental Regulations and their Impact on the European Space Sector 20m
In the course of implementation of the Green Deal, the EU's regulatory framework expanded significantly. RoHS directive, REACH and CLP regulations are undergoing revision process addressing EUs Chemical's Strategy for Sustainability, while new initiatives such as Sustainable Product Initiative (SPI) and relevant delegated acts adressing European Circular Economy Plan are piling up. This presentation will summarise relevant environmental regulations, focusing in particular on REACH-regulated susbtance list ammendments for specific chemicals (lead metal, BPA and PFAS), and reflect on new regulatory constraints from Sustainability and Ecodesign side.
Speaker: Mr Premysl Janik (REACH Officer at European Space Agency)
-
09:30
-
09:30
→
11:00
End-of-Life Management & Zero Debris: Plenary: Zero Debris Policy evolution
-
09:30
Introducing the Zero Debris approach 30mSpeaker: Tiago Soares (ESA)
- 10:00
-
10:15
ESA Space Debris Mitigation Standard 2023 30mSpeaker: Francesca Letizia (ESA)
-
10:45
Evolution of the LOS (Loi relatives aux Operations Spatiales/ French law on space operations) 15mSpeaker: Pierre Omaly (CNES)
-
09:30
-
11:00
→
11:30
Refreshment break 30m
-
11:30
→
13:00
Ecodesign for Space: LCA in Projects Key Takeaways
-
11:30
“Overview of Life Cycle Assessment and EcoDesign Activities for Large Space Missions at Thales Alenia Space” 30m
A comprehensive overview of Thales Alenia Space's (TAS) initiatives in Life Cycle Assessment (LCA) and EcoDesign for large space missions is provided. Large space missions present unique challenges and opportunities in terms of environmental impact and sustainability assessment, due to their complexity in terms of Product Tree and Organization Breakdown structure as well as largeness of the associated supply chains and the elaborate nature of the MAIT campaign. TAS has been actively involved as Prime Contractor in various projects spanning different development phases, from A/B1 to B2/C and C, thus this paper delves into the specifics of each project, highlighting the commonalities of the implemented approach at TAS to run LCA, but also identifying the methodology adaptation with respect to different development phases, driven by dissimilar levels of information as input to LCA Model generation.
The general approach at TAS to lead LCA adheres to applicable requirements and guidelines from the European Space Agency (ESA), first of all tailoring the handbook ESSB-HB-U-005 “Space system Life Cycle Assessment (LCA) guidelines” with respect to the peculiarities of each Large Mission as well as the phase in which the LCA study is conducted. Subsequently, the TAS methodology to LCA involves the development of a proprietary Life Cycle Inventory (LCI) Data Collection Questionnaire, aimed at a comprehensive Life Cycle Inventory (LCI) data collection carried out through workshops with subcontractors and internal stakeholders within the company; the process also employs the HSE TAS-I Tools and Databases to assess energy and water consumption throughout the entire product life cycle. TAS Steering LCA consultants and prioritizing Equipment datasets based on cost and mass criteria are crucial steps in the applied LCA methodology, and the paper provides insights into these processes. Furthermore, practical examples of LCA outcomes are presented to illustrate the impact of these assessments on large space missions.
LCA is one of the steps of the EcoDesign approach to give levers for the engineering work when the design is enough mature; nevertheless, EcoDesign is a fundamental aspect to address the design of TAS's product lines and projects, even at early stages: it encompasses the use of Thales simplified tools for carbon footprint and Ecodesign orientation (CLOE Matrix, PETER tool), as well as consolidated Company’s process to address the environmental impact reduction of new developments; a brief overview of these additional supports is also provided.
The paper concludes with lessons learned from TAS's LCA and EcoDesign endeavors and outlines future optimization activities, in line with TAS's commitment to sustainability and environmental responsibility, to drive innovation and improvements in LCA and EcoDesign practices as Large Space System Integrator.
This paper serves as a valuable resource for space industry professionals, environmentalists, and researchers interested in the intersection of space technology and sustainability.Speaker: Marco Giuliani (Thales Alenia Space Italia S.p.A.) -
12:00
Key learnings when applying an iterative LCA approach during the different development phases of a space mission 30m
VITO has performed LCA studies for space missions over consecutive phases of development (from A, B1, B2 over C/D). The CO2M mission is one example where we started assessing the environmental impact already during the early stages of development and continuously update the environmental profiles in different iterations to improve the quality of the results and conclusions.
This presentation will build on the experiences with this iterative approach to illustrate how the LCA process follows the space mission development phases, to share key learnings on how to perform this process as efficiently as possible and how this changes the results. We will discuss for example data quality, data gaps and data quality assessment and focus on how to make the data collection and LCA model improvement more effective. Also the hot spot identification and role of ecodesign will be discussed. We will relate, where relevant, to different initiatives from ESA to support LCA for space missions, such as the update of the ESA database and the harmonization of the data questionnaire.
Speakers: An Vercalsteren (VITO), Stefanie De Smet (VITO) -
12:30
ESA Space Segment LCA Studies by Airbus DS: Challenges and Insights 30m
Airbus DS will share its the experience as prime leading LCA studies of the space segment for ESA missions, under different contexts. In particular, prime data collection compilation process will be presented, together with the equipment suppliers data collection strategy and LCA modelling philosophy of different ongoing projects (CRISTAL, LSTM, G2G, FORUM). An overview of the challenges faced and potential improvement opportunities will be shared with the clean space community, anticipating formalized lessons learnt, which shall be formulated upon projects delivery in 2024.
Speaker: Catarina Val
-
11:30
-
11:30
→
13:00
In-Orbit Servicing & Debris Removal: Plenary: Removal services
-
11:30
GNC for rendezvous, dynamic capture and stabilization of spinning non-cooperative target 20m
ClearSpace-1 Mission is part of ESA’s active debris removal/in-orbit servicing programme. Its objective is to rendezvous, capture and de-orbit a VESPA upper stage. The technology developed in this mission will set the ground for a recurrent commercial service for removal of space debris, as well as other in-orbit servicing capabilities.
Deimos is the full responsible for the GNC subsystem, in a close co-engineering approach with system level activities of Clearspace. The uncertainty around the true state of the target, as well as realistic constraints in the S/C configuration, pose a significant challenge for its capture. Recent developments in the mission have demonstrated the feasibility of solutions for the capture of VESPA and, in general, non-cooperative targets.
In this presentation, we demonstrate the several capabilities developed for the capture of space debris. The aspects to be presented are:
- Overall GNC architecture adopted for tackling the several approach phases;
- High fidelity functional engineering simulation facility for verification and validation of the developed solutions;
- Capability for on-line capture of the target, namely with dynamic computation of approach trajectory, vision-based navigation solution and control with performance robustness in the presence of system uncertainties;
- Demonstration of very close proximity safety operations;
Speaker: Mr Baltazar Parreira (Deimos Engenharia) -
11:50
e.Inspector phase B: 12U CubeSat for debris target multispectral close inspection 20m
e.Inspector ESA mission is focused on performing close proximity maneuvering around a debris (nominally a VESPA adapter) to get VIS-IR images of the target and support its status, shape, dynamics reconstruction in aid of capture and removal. The mission, currently in its phase B, is largely focused on designing, implementing and breadboarding the VIS-IR imaging chain, exploited on board for relative navigation and guidance. COTS cameras are adopted, both VIS and IR already flown. The test campaign has been defined and the Processor In the Loop is being set up with breadboards of the proposed boards, which will be augmented by including EM of the imaging cameras to assess the IP-based GNC proposed architecture with Hardware in the Loop as well. To ensure the needed authority in the center of mass control, the platform is equipped with a low thrust, iodine based thruster, currently under endurance tests. The mission analysis, in fact, shall be robust to possible debris target changes, launcher's release initial state vector, new more stringent disposal regulations. Challenges and mission status will be discussed with focus on the e.Inspector key technologies and plans towards flight.
Speaker: Prof. Michelle Lavagna (Politecnico di Milano) -
12:10
COSMIC, UK’s first Active Debris Removal mission and Europe’s latest gem to the In-Orbit Servicing ecosystem 20m
Since the beginning of the space era, the number of debris generated in low Earth orbit (LEO) has been increasing. ESA statistics show there are an estimated 130 million objects in the 1 mm to 1 cm size classed as lethal non-trackable debris (with the potential to damage key infrastructure) and more than 2,700 non-functioning satellites. Analysis has shown that stabilising the space debris population can only be achieved by maintaining high PMD (post mission disposal) rates on future constellation satellites, plus removing a set number of defunct satellites per year from orbit, termed Active Debris Removal (ADR).
After a successful phase A study, the United Kingdom Space Agency (UKSA) committed in 2022 to continue funding towards a mission to remove two defunct pieces of UK-owned debris with a multi-client removal servicer. The mission, due for launch in 2026, needs to capture and remove unprepared debris (satellites with no existing preparation, docking plate or servicing interface). Astroscale was selected by the UKSA to continue its work up to PDR, which shall be concluded by end of 2023. The paper focuses on Astroscale’s mission — named COSMIC (Cleaning Outer Space Mission through Innovative Capture). Astroscale’s consortium includes 10 partner organisations including MDA, Thales Alenia Space, Nammo, GMV, Raytheon, among others, responsible for different parts of the space, ground and launch segments.
COSMIC is a variant of Astroscale’s ELSA-M mission, which has been in development for 5 years under the ESA Sunrise programme, under prime OneWeb. While ELSA-M is developed to enable magnetic servicing to prepared clients, COSMIC will enable robotic servicing to unprepared clients. The mission requires adaptations to several areas, notably the capture mechanism (inclusion of a robotic arm), GNC (guidance, navigation and control) and flight software. The paper will explore the way in which heritage and best operational practice can be leveraged from ELSA-M (and our precursor demonstration mission, ELSA-d) and will address the mission design, concept of operations (ConOps), additional mission functionalities/necessary adaptations, the resulting roles of partners in the consortium and the anticipated commercialisation axes. Indeed, the innovative ADR offer permitted by the “COSMIC” mission shall allow Astroscale to capitalise on the company-wide products catalogue and extend its set of end-to-end Space Sustainability services.
COSMIC promises to be the first UK funded debris removal mission in space, one of the cornerstone ADR missions in Europe and will be a worldwide breakthrough mission in the field of IOS as well. The development, production and integration of the innovative robotics solutions (and the associated Close Proximity flight and ground software assets) proposed in the COSMIC mission represents for Europe the steppingstone towards more advanced IOS services. To cite but a few, In-Orbit Refuelling, On-Demand Space Situational Awareness as well as In-orbit Repair/Upgrade or In-Orbit Manufacturing/Assembly of LEO assets would be facilitated by the innovations permitted by the COSMIC mission. In order to increase versatility of our service set, the COSMIC spacecraft is designed with refuellability in mind. Internal and external prospects (both European and Non-European) highlighted already the criticality of these servicers to have the capacity of being refuelled as well as refuelling client spacecraft. COSMIC is an enabler for the future space circular economy and the ever-increasing demand in space logistics.
Keywords: Active Debris Removal, ELSA-M, ELSA-D, COSMIC, Close Proximity Operations, In-Orbit Servicing
Speaker: Maxime Valencon (Astroscale) -
12:30
CAT-IOD: PHASE 0 FOR AN IN-ORBIT DEMONSTRATION MISSION FOR ACTIVE DEBRIS REMOVAL 18m
In the last years GMV, in collaboration with AVS and under ESA contracts, has been, and is still, designing and developing multiple technologies for ADR. Among those MICE, currently under validation phase, and CAT, currently in BreadBoard phase.
In line with the ESA strategy of zero-debris, goal of CAT-IOD is to perform an In-Orbit Demonstration (IOD) of an Active Debris Removal (ADR) mission using both mechanical devices, MICE and CAT, but not only.
The ongoing Pre-phase A study aims to perform a conceptual design of a potential mission towards the ADR of a small target satellite, the AVS LUR-1. The study will preliminarily evaluate the technical feasibility, cost, and risks of the mission, as well as the scalability and representativeness of the proposed mission concept and key technologies towards larger scale missions like the next generation of COPERNICUS which will be nominally provided with a MICE device.
CAT-IOD will size a servicer satellite to fulfil ADR mission objectives. It will also serve the purpose to identify potential needs on the client side and derive feasible inputs that could be eventually implemented at the target side and/or ground segments for an efficient service.Speaker: Fernando Gandia (GMV)
-
11:30
-
13:00
→
14:00
Lunch break 1h
-
14:00
→
15:30
Ecodesign for Space: Navigating the ESA LCA Database: A User's Guide
-
14:00
Introduction to ESA's LCA Database 30mSpeakers: Estefania Padilla Gutierrez (ESA (ESOC)), Sara Morales Serrano (ESA)
-
14:30
ESA LCA DB End-User Experience 1h
This presentation relates to the activities of the ESA LCA Database project as part of ESA Clean Space Initiative. The main purpose of the project is to build, consolidate and maintain a fully operational and up-to-date environmental LCA database and provide support services to the ESA LCA Database end-users. The presentation will focus on the main development in the project activities in the past year, impacting the users: ESA LCA database updates, new datasets collection, new LCIA methods, preparation of documentation (including requirements for datasets integration), identification of gaps in the DB, development of the Converter Tool (data conversion tool between main LCA software solutions), distribution and foreseen updates. One of the highlights of the presentation will be the guided tour of the ESA LCA DB updates (including the newly implemented LCIA methods), showcasing the background data updates, the structure changes and inclusion of new datasets, explaining the reasoning behind and impact on the user and next steps needed to obtain a robust and consistent database. On another front, the Converter Tool capabilities will be showcased, along with introduction of the need to find common ground in modelling in the different LCA software used in space projects, and the possible limitations triggered by non-compliance.
An invitation is extended to current end-users and conference participants in the consolidation process of the existent database through workshops, end user feedback and dataset wish lists, in order to focus efforts to address priority needs of the industry. Overall, this presentation addresses the steps taken from theory to practice in defining an operational environmental LCA database, emphasizing the advantages that the database can offer to users while also providing them with clear instructions on how to contribute to it, ensuring at the same time compliance with data quality requirements.Speakers: ELENA ROCCO (Rina Consulting), Mr Ionut Grozea (SC DEIMOS SPACE SRL)
-
14:00
-
14:00
→
15:30
End-of-Life Management & Zero Debris: Lessons Learnt End-of-Life
-
14:00
Aeolus re-entry paving the way to mitigate on Ground casualty risk 18m
Following ESA’s decision to set up a working group on Aeolus reentry at the Aladin workshop in February 2022, Airbus was involved in this working group aiming at defining the best strategy for Aeolus reentry in the evolving context of Space debris mitigation regulations.
This paper presents the overall contribution on this subject over the last 2 years, and covers the definition of a assisted re-entry scenario for Aeolus in terms of flight dynamics and overall scenario and covers the following main aspects:
- Major design elements, trade-offs and sizing approach
- Uncertainties and variability assumptions
- Performance campaigns
Airbus demonstrates that the casualty risk can be reduced by a sensible factor compared to uncontrolled reentry, through a combination of lowering the perigee down to 120 km, controlling the magnitude of the last maneuver based on the last orbit determination data, and phasing the descent with the Earth’s rotation so as to target a nominal reentry in the Atlantic corridor.
This consolidates the possibility for Aeolus to retroactively ensure compliance with the current space safety regulations, even though the mission was not subject to the 10-4 rule during development.Speaker: Kristen Lagadec (Airbus) -
14:18
Aeolus assisted reentry: a successful story 18m
At the end of its mission lifetime, Aeolus was designed to reenter in an uncontrolled approach. Aeolus did not have to comply to ESA’s Space Debris Mitigation Policy, since its SRR was held before the entry into force of such Policy.
A Working Group was set up by ESA, involving ESA and industry experts, with the objective to explore alternative ways to reenter and reduce the casualty risk, which was known to be above the current policy threshold (i.e. 1 over 10,000)The Working Group recommended a solution based on an assisted approach which was adopted by ESA executive and by its delegation bodies. The satellite reentered successfully on the 28th of July @18:46 UTC.
The objective of this presentation is to present the outcome of the reentry, the main challenges faced during the assisted reentry and the solutions adopted.
Speaker: Mr Tommaso Parrinello (ESA) -
14:36
CHEOPS: from reentry in 25 years to 5 months 18m
CHEOPS (Characterizing ExOPlanet Satellite) is the first small class ESA mission dedicated to characterizing exoplanets known to be orbiting nearby bright stars. CHEOPS telescope allows for high precision observations using the transient method, enabling the scientific community to determine the planets’ size and density accurately and to derive their structure and composition. CHEOPS is in a dawn-dusk Sun-synchronous orbit at an altitude of 700 km.
CHEOPS Mission Operations Center is located at Instituto Nacional de Técnica Aeroespacial in Torrejón de Ardoz, Spain, from which full operations since launch until decommissioning phases are held. End-of-life operations will be executed from this center in order to assure a safe reentry while complying with ESA space debris mitigation standards.
CHEOPS was initially designed to comply with ESA’s disposal policy by decreasing the perigee to an altitude of 490 km in order to re-enter within 25 years. During the preparation activities for the Mission Extension Operations Review held in late 2021, the assessment of the fuel budget, taking into account the collision avoidance and orbit maintenance maneuvers required for the extended period, showed high margin in the remaining fuel for disposal operations.
Consequently, a new detailed disposal plan was proposed to decrease the orbit altitude and further reduce the re-entry time below the initial approach. For the new strategy, the fuel budget and AOCS constraints determined feasible to lower the orbit down to a circular one with an altitude of 350 km, diminishing the re-entry to approximately five months. Crossing of critical orbits, such as the ISS orbit, was considered when designing the new strategy.
In the light of the above, a shortening in the time required for the re-entry, along with the reduced space debris population in such low orbits, will imply a risk reduction of both collision and fragmentation. The new strategy contributes to a more sustainable space environment by avoiding additional space debris generation.
Speaker: David Modrego Contreras (Isdefe) -
14:54
Rocket body reentry trends 18m
Of the record 180 rocket launches in 2022, 129 resulted in a rocket body being abandoned in orbit to eventually reenter the atmosphere days, weeks or years later. These uncontrolled reentries create a risk of casualty to people on the ground, at sea and in aircraft. Also in 2022, numerous pieces of large rocket debris from major launchers – including SpaceX Falcon-9 and Chinese Long-March rockets – crash landed near populated areas. These risky reentries can be prevented using existing technologies and mission designs: controlled reentries can direct the rocket bodies into a remote area of the ocean and effectively eliminate the risk of casualty.
Here we provide an overview of the recent trends concerning uncontrolled and controlled reentries of rocket bodies. We look at which rockets – and states – utilize either type of reentry, and in which type of launches (LEO, GTO etc.) these are used. Finally, we present the trends in recent years: while the absolute number of controlled reentries has increased (driven by SpaceX Starlink launches), the proportion of controlled reentries has stayed level, resulting in an increased number of uncontrolled reentries and therefore a greater casualty risk. Against this context we provide recommendations to industry and government to mitigate this risk.
Speaker: Ewan Wright (UBC) -
15:12
Ariane 6 - Space debris limitation 18m
Ariane 6 is the future large European Launcher launched from the Guiana Space Center (CSG). Besides, Ariane 6 launcher program corresponds to the first full application of the French Space Operations Act (FSOA) from the beginning of an European Launch System development. ESA Space Debris Mitigations Policy is also applicable to Ariane 6 development program.
The presentation will summarize the mitigations that have been implemented in the Ariane 6 Launcher System to support space debris limitation required both by French Space Operations Act and ESA Space Debris Mitigations Policy. It will present hardware systems as well as software solutions, together with studies that have been performed to assess the compliance with space debris limitation requirements. It will cover all solutions implemented on Ariane 6 launcher system and on its mission definition in order to mitigate space debris generation.
The presentation will address Ariane 6 Upper Stage de-orbitation, tanks passivation and the evaluation of remaining space debris generation risks. It will also highlight concerns raised during the development phase with regards to space debris matters.Speaker: Nathalie DIAS (ArianeGroup)
-
14:00
-
14:00
→
15:30
In-Orbit Servicing & Debris Removal: Mission Implementation: IOS
-
14:00
D-Orbit's In-Orbit Servicing: A Customer-Driven Development Approach 20m
As a response to the increasing market need for In-Orbit Services, D-Orbit is developing an offer able to provide AOCS takeover and relocation of satellites, particularly in geostationary orbit. D-Orbit has analysed several alternatives for a system that can tackle such market segment. Considerations on the design choices advanced by established and emerging competitors, the variability in targets and mission scenarios, and the specific needs for expandability and futureproofing, led to the definition of the modular architecture that now characterizes the D-Orbit General Expansion Architecture (GEA) programme. GEA proposes a highly modular approach leading to a spacecraft where the centre of attention moves away from the system and focuses on the modules that compose it. This allows D-Orbit to adapt the final spacecraft to serve a particular IOS mission depending on the final service schedule that is derived for such mission and maximises value for the customer..
Making up any GEA spacecraft, is a set of modules sharing standardized mechanical and electrical interfaces. The selection and the configuration of these modules depend on each spacecraft class mission and sizing point, with a physical architecture that allows a spacecraft configuration to be rapidly assembled from pre-manufactured modules, significantly increasing the mission responsiveness. Furthermore, such far-reaching modularity of the overall architecture allows the GEA spacecraft to be serviceable once already in space, adding or swapping modules, by means of services provided by other GEA spacecraft. With this approach, a true In-Orbit Servicing and Logistics infrastructure is deployed, moving beyond custom-made, single-mission designs towards truly adaptable and scalable solutions and creating a live ecosystem in orbit that can in turn feed off itself.
Developing such a service has challenges beyond the technical realm, including tackling the regulatory difficulties of involving multiple licensing authorities, the legal intricacies of service-based contracts, and the commercial hurdles of establishing a new market. D-Orbit aims to replicate its success in the LEO transportation market by providing an end-to-end regular and recurrent service with minimal barriers for customer acquisition at a very competitive price-point.Speakers: Diego Garces de Marcilla (D-Orbit UK Ltd), Mr Stefano Antonetti (D-Orbit S.p.A.) -
14:20
Regulatory Frameworks for a Thriving Circular Space Economy 20m
Growing congestion and increasing collision risk in low Earth orbit call for the development of a more circular space economy. Ensuring orbits can be safely used now and in the future requires the availability of in-orbit services to remove legacy derelict objects and better manage the end-of-life of satellites. The ability to service spacecraft, to refuel, repair, upgrade, repurpose, and ultimately recycle them not only offers the promise of a more sustainable space economy but also opens new possibilities and promises to reduce the cost and improve the reliability of space infrastructure.
There is increasing interest in the development of a stronger approach to space debris mitigation and remediation through policies and the implementation of debris removal missions. There are also several ongoing and upcoming missions trailblazing the development of in-orbit servicing. These public and private endeavours to develop in-space services, assembly, and manufacturing (ISAM) capabilities move us towards a more circular space economy. One such undertaking is ClearSpace’s ENCORE program, which will extend the life of geostationary (GEO) communications satellites.
A long-term vision of an interconnected and sustainable space ecosystem can only materialize if national regulatory frameworks enable and encourage transnational cooperation. The provision of services in orbit and the development of novel activities that bring us closer to a circular space economy will require (1) interoperable technical standards, (2) compatible regulatory frameworks, and (3) clear and predictable mission authorization pathways. Of paramount importance are the questions of responsibility and liability among actors engaged in joint servicing activities in space, which becomes critical when such actors are based in different jurisdictions. Governments and regulators have an important role to play in clarifying the rules and setting up the frameworks under which transnational in-orbit servicing activities can responsively and efficiently take place.
Speaker: Mr Romain Buchs (ClearSpace SA) -
14:40
Beyond ELSA-M – Developing Sustainable In-Orbit Commercial Services 20m
Space traffic is growing rapidly, and with it, the need for in-orbit servicing (IOS) solutions. Large constellations in low Earth orbit (LEO) are providing essential services, but are also increasing the number of objects, and therefore de-bris, in space and the risk of key orbits becoming unusable. Strategic and proactive approaches to safeguarding our space environment for future generations are championed through programmes such as ESA’s Zero Debris initiative, which not only considers services for post-mission disposal, but also encourages the development of enabling technologies and policies to maintain the safe use of LEO orbits for the benefit of humankind. Astroscale is preparing to conduct the world’s first prepared satellite debris removal mission, with a full-sized representative constellation customer in OneWeb, while working in parallel to develop in-orbit capabilities which underpin commercial in-orbit services and are essential to the concept of a circular space economy.
Building on the success of ELSA-d, an in-orbit demonstration of core Rendezvous and Proximity Operation (RPO) capabilities necessary to achieve debris removal, Astroscale is developing ELSA-M, a servicer which can remove multiple clients. ELSA-M will dock with a prepared client, lower their orbit, and drop them off for uncontrolled re-entry before moving on to the next client. Developed with prime OneWeb as part of the ESA Sunrise programme, the ELSA-M in-orbit demonstration is planned to launch in the 2025 timeframe and the team are currently working to-wards CDR. This paper will give an overview of the critical technical developments, both in the space segment and ground segment, that Astroscale have been advancing to mature from ELSA-d to the ELSA-M commercial servicer.
The ELSA-M in-orbit demonstration is the next step towards Astroscale realising a commercial removal service, after which Astroscale is preparing for high-volume production. This paper will highlight how Astroscale’s services fit within the European ecosystem, emphasising a commercial roadmap which shows the value proposition of the services and benefits to prospective customers. The need for end-of-life (EOL) services is under-stood by commercial operators and institutions, but companies proposing such services must overcome perceived customer sensitivities including cost, risk, and service flexibility. Additionally, many of the technologies at the core of debris removal, such as in-orbit inspection and close proximity operations (CPO), have wider applications in commercial in-orbit servicing.
Astroscale is working with clients to prepare their satellite for removal through docking plates, building a common understanding on behavioural norms and safety standards for complex operations such as CPOs, and utilising state-of-the-art technologies to prepare for future services such as refuelling and in-orbit assembly. Within this paper, the author will provide an overview of Astroscale’s docking plate solution, a simple, low-cost, ‘bolt-on’ solution with the potential to mitigate higher costs at EOL, highlight Astroscale’s involvement in initiatives to develop guidelines for RPO, including work with CONFERS and Japanese counterparts in preparation for the ADRAS-J mission, and demonstrate the inherent links between ADR and EOL in unlocking the future of space sustainability.
Speaker: Ms Zaria Serfontein (Astroscale) -
15:00
IOSHEX AND SPACERIDER INTEROPERABILITY TOWARDS ACTIVE DEBRIS REMOVAL AND RECYCLING 20m
In recent years, the issue of space debris has become a growing concern for the global space community. Currently, there are more than 9,000 tons of space debris orbiting Earth, posing significant challenges to future space missions. As space activities continue to increase, there is a pressing need for effective and sustainable debris mitigation and removal strategies. As the space industry advances and in-orbit manufacturing technologies mature, the possibility of recycling and repurposing space debris becomes ever more feasible. By leveraging the capabilities of In-Orbit Manufacturing (IOM), this space debris can be transformed into valuable resources for future exploration and infrastructure. With the same technology, parts of active spacecraft can be refurbished or replaced directly in orbit thanks to IOM together with an innovative robotic system capable of manipulating, mounting and dismounting hardware in the space environment.
This presentation explores the potential of utilizing IOM techniques and robotics to recycle old fairings, space stations, and large spacecraft, as well as extending the life or repairing faults on active satellites. This would open up a new era of sustainable space activities and it would be rendered possible by cooperation and interoperability between In-Orbit Servicer IOSHEX and the Space Rider platform.The IOSHEX system, equipped with advanced capture, cut, and weld technologies, plays a pivotal role in efficiently extracting valuable materials from space debris. These recovered materials can serve as feedstock for the 3D printing capabilities integrated onboard the Space Rider. By processing scrap material into usable resources, we open up new possibilities for in-space manufacturing and infrastructure assembly.
Our collaborative approach aims to maximize the utilization of space debris, transforming it into essential building blocks for constructing new spacecraft components for refurbishment or even large structures, reducing the need for Earth-to-space transport and minimizing the environmental footprint of space missions. Moreover, through a closed-loop recycling process, we can further enhance the sustainability of space activities, significantly reducing the generation of new debris.
During the presentation, we will delve into the technical aspects of the IOSHEX system, showcasing its capabilities for efficiently capturing, processing, and delivering materials for 3D printing on the Space Rider. We will also discuss the advantages of utilizing in-space manufacturing techniques to produce complex and customized components, minimizing the reliance on Earth-based manufacturing and fostering greater autonomy for future space missions.The presence of the Space Rider in the operative chain is crucial. Serving as an ideal host for the additive manufacturing machine utilized by IOSHEX, the Space Rider enables the efficient processing of materials extracted from space debris. The key advantage of the Space Rider lies in its capability to return safely to Earth, allowing for multiple instances of reuse of the manufacturing equipment in subsequent missions, fostering the sustainability aspect of the chain. Moreover, the Space Rider's safe reentry capacity opens up new possibilities for the recycling of space debris. This concept involves bringing salvaged debris containing rare materials back to Earth for use in various applications. This unique ability adds an extra dimension to the sustainability of space activities, contributing to the efficient utilization of resources and further reducing the environmental impact of space missions.
Other than the IOM capabilities and the advanced robotics, the cooperation between the two systems is another critical part of the concept presented. The ability of IOSHEX and Space Rider to interact, exchanging material and hardware in and out the cargo bay, is already a matter of study in a collaboration between SAB and ESA under the Future Launch Preparatory Programme (FLPP).
This collaborative effort showcases the potential of space agencies, private enterprises, and international organizations working together to address the pressing challenges posed by space debris, while also paving the way for a sustainable and thriving space industry. Together, Space Rider and IOSHEX demonstrate the promising future of in-orbit manufacturing and debris management, enabling us to unlock the full potential of space exploration and utilization.Speaker: Mr Marco Mariani (SAB Launch Services)
-
14:00
-
15:30
→
16:00
Refreshment break 30m
-
16:00
→
17:30
Ecodesign for Space: Improving Ecodesign Methodologies
-
16:00
Evaluation of current DQ Methodology 20mSpeaker: Floor Bagchus
-
16:20
A Consensus-Based Single-Score for Life Cycle Assessment of Space Missions 20m
With a continuously growing number of satellites in orbit, it becomes increasingly important to assess their impacts on the Earth's environment in a standardised manner. While interest in Life Cycle Assessment (LCA) for space missions has gained in strength in the past few years - particularly in Europe - no consensus has yet been reached on a single-score LCA system. In parallel however, scoring systems for other sustainability aspects have been defined and are increasingly being used in the industry.
A notable example is that of the Swiss-based Space Sustainability Rating (SSR) non-profit organization. It aims to incentivise sustainable behaviors in space through a quantitative and qualitative assessment of the sustainability level of a mission. Several criteria are considered for this such as collision avoidance, post-mission disposal strategy, compliance to existing space debris mitigation standards, detectability and trackability, data sharing, and readiness level to active removal.
This presentation shows the results of a consensus-based feasibility study for creating a LCA single-score to be used for both the LCA module of the SSR, as well as for general space mission ecodesign. The focus of the study lies in the identification of the initial inputs and the methodology to assess them, as well as the weighting method to reach a single-score. A global survey, with a European focus, has been conducted for this study and its conclusions are used to provide an initial discussion on the weighting method to be used.
Overall, this paper highlights the importance of an easy-to-understand LCA tool for space systems. It shows the necessity for a tool that is implementable during the design phase of the mission, to incentivise space actors to opt for more sustainable materials and designs, and to reassess their logistics. To that effect, this presentation explores consensus-based weights for a single score, highlights perceived benefits and drawbacks of doing a space LCA, investigates new weights for SSR, shows an initial application on the Delfi-n3Xt cubesat mission and underlines the main aspects which still need further development and investigation.
Speaker: Marnix Verkammen (TU Delft & eSpace EPFL) -
16:40
Uncertainty in Environmental Life Cycle Assessments of Launch Vehicles 20m
Life Cycle Assessments (LCA) are becoming an essential tool within the space transportation sector. These can support policy makers and designers in understanding the ecological footprint by quantifying environmental impacts, identifying hotspots throughout all phases in the launch mission, and designing environmentally sustainable systems though eco-design. Nevertheless, significant uncertainties remain, particularly in the launch event itself, which currently limits our understanding of the full spectrum of life-cycle environmental costs and increases the complexity of eco-design. It is therefore fundamental to derive a methodology to handle these uncertainty to guide uncertainty reduction strategies, guaranteeing a robust eco-design process with design choices.
In this study, several RLV technologies which have been proposed by different space actors are assessed with the Strathclyde Space System Database (SSSD) to identify their different life-cycle footprints including a preliminary estimation of atmospheric impacts with different climate metrics. This is followed by a sensitivity assessment which would allow us to take some first steps to fully understand the major sources of uncertainties affecting the LCA indicators.
These will support upcoming work to improve LCA's of generic space systems by including launch event and disposal related impacts and advanced uncertainty quantification formalisms, eventually enabling the robust eco-design of space missions.Speaker: Guillermo Joaquin Dominguez Calabuig (University of Strathclyde) -
17:00
The impact of re-entering satellites on atmospheric chemistry and Earth’s climate 20m
This presentation covers the first results of a study on the atmospheric effects of re-entering satellites in the mesosphere (40 – 100 km). Currently, the disposal method of choice for most LEO satellites is an atmospheric re-entry. However, in recent years a number of concerns have been raised about the amount of man-made material projected to burn up in the Earth’s atmosphere in the coming decades as well as the chemical products created during the burn-up and their impact on the atmosphere and our planet’s climate. It is present believe that there are three main emissions from re-entering satellite components which potentially can alter ozone concentrations and the radiative budget in the middle atmosphere, namely: black carbon (aerosols), aluminium alloys, and thermal nitric oxide (NO).
OHB and IAP Kühlungsborn took the initiative to investigate the potentially harmful substances produced during re-entry of space objects, their influence on the atmosphere and methods to models and detect them. In particular it was considered that the number of re-entering satellites will increase dramatically in the near future. This is driven by trends for mega constellations and cheaper access to space. Two aspects were studied and will be presented at the workshop: Based on the Chemistry-Transport Model at the Leibniz Institute of Atmospheric Physics (CTM-IAP) the effects of thermal NO on ozone in the upper stratosphere-mesosphere-mesopause region were computed. In addition, the impact of the increased mass of black carbon and aluminium on the radiative balance of the middle atmosphere has been discussed.
Initial results show no criticalities. NOx-driven ozone depletion on the middle atmosphere by re-entering satellite components show only negligible effects even with larger projected total masses re-entering. However, the picture is not complete. The presentation will conclude with an overview of the open questions and next steps as well as an appeal to collaborate on this important question and share outcomes as they become available.Speaker: Laura Schumacher (OHB System AG)
-
16:00
-
16:00
→
17:30
End-of-Life Management & Zero Debris: Space Surveillance and Tracking
-
16:00
Objects characterisation with on-ground SST measurements in support of space debris removal operations 20m
The growing population of objects in orbit and the accumulation of space debris over the past decades make it necessary to develop activities and initiatives focused on space debris removal. The first and most fundamental role of Space Surveillance & Tracking (SST) in those space debris removal activities is evident, enabling knowledge and prediction of object orbits and their associated uncertainty through cataloguing methodologies, leveraging SST measurements from networks of sensors (telescopes, radars and laser ranging stations). However, to extend the support to those activities, it is imperative not only to know the orbits, but also multiple aspects related to the characterisation of the objects to be removed such as their size, shape, rotation and attitude. Therefore, advanced techniques further exploiting those SST measurements beyond traditional orbit estimation and prediction methods are essential to achieve a fully comprehensive understanding of the objects. The presentation aims to describe object characterisation methodologies developed at GMV, including size and shape estimation, rotation determination and attitude characterization and estimation, with the objective of enhancing the effectiveness of space debris removal.
The methodologies developed make use of SST sensor data that complement the typical SST measurements (range, range-rate, azimuth, elevation, right-ascension, declination…), such as light-curves (i.e. apparent magnitude) in the case of optical sensors, and Radar Cross Section (RCS) measurements in the case of radars. Additionally, they can also be combined with initial estimates of size, shape, materials, and even attitude, which some other sensor technologies are able to provide.
Our first method involves classifying objects based on their rotational state, distinguishing between tumbling objects and stabilized objects. This is achieved through Machine Learning techniques that use RCS measurements and light-curves as input. The results of this method have been highly successful, surpassing a 90% accuracy rate, particularly when both types of measurements are combined.
Following that, another method involves determining the apparent rotation period of rotating objects using Lomb-Scargle periodograms and epoch folding techniques. This algorithm has been validated with objects of known rotation, yielding errors lower than 1%.
However, the most promising method by far is the attitude estimation based on light-curves. Our implementation relies on an LSM filter that aims to minimize the residuals between the real light-curves provided and those computed from the estimated attitude. To accomplish this, the development of a light-curve simulator, called GRIAL, has been necessary. GRIAL uses OpenGL to model the object and considers many aspects related to light reflection, such as shape, size, materials, solar panels, or the shadows that occur between different parts of the object. This simulator has been successfully validated with known real light-curves of well-known objects such as the SMOS and ESA’s Sentinel satellites. The attitude estimation method can be combined with input data about the object (size, shape, estimated attitude, etc.), whether they are known or estimated, to be used as an initial solution during the estimation process. These data can be provided by external sources, or be outputs of the previous algorithms. The method allows to estimate the objects attitude mode, the refinement of the initial attitude, the determination of the rotation axis and the fine-tuning of the rotation rate of rotating objects. In addition, it is possible to include a scale factor, allowing to deal with uncertainties in the size or reflection coefficient of the materials. The results obtained vary depending on the initial level of knowledge about the object. For example,. when there is good initial knowledge and enough amount of data, the orientation calculation accuracy reaches errors below 15º, although on the other side, the algorithm even diverges in cases with very limited initial knowledge (e.g., no initial information about shape, size, or attitude) or when there is few data available.
Furthermore, the development of the simulator is currently ongoing to expand its capabilities to simulate RCS measurements. This will allow to perform attitude estimation based on this type of measurement as well.
In addition, to deal with cases where no prior information is known about the object, a simple auxiliary method has been recently added that allows a reasonable estimation of the object size using light-curves and RCS. While it is only an approximation, it provides an initial starting point when no further data is available.As mentioned earlier, successful space debris removal operations need to have knowledge of the orbits of the objects for the effective initial approaches. But in addition, these missions typically demand a detailed understanding of the object characterisation, particularly in aspects such as attitude, rotation, size and shape, to conduct the activity in an efficient and safe manner. Therefore, a combined integration of our methods can be extremely useful for these activities, facilitating the necessary prior knowledge of the object before taking action.
The presentation gives more details on the methodologies indicated and on the results obtained, and presents some practical cases of application. For example, information is provided on the training process and results of the Machine Learning method; it is detailed how we use the periodograms to obtain an initial estimate of the rotation based on light-curves and RCS, and then epoch folding process for fine-tuning; it explains how GRIAL works as a light-curve simulator using OpenGL and 3D modelling, and gives some real validation examples; and it also shows the implementation of the LSM filter for attitude estimation and how GRIAL is integrated in this method, detailing the main results obtained in the different cases tested. Finally, the level of maturity achieved with these methods is analysed, as well as their current limitations.
In conclusion, this presentation serves to show the development and performance of characterisation methodologies that are useful in supporting activities aimed at maintaining a clean and sustainable space environment, also highlighting the main challenges and expectations for the future in this field.
Speakers: Angel Gallego Torrego (GMV), Adrián de Andrés Tirado (GMV), Carlos Paulete Periañez (GMV), Marc Torras Ribell (GMV), Javier Carro (GMV) -
16:20
CNN4NEOOD - CONVOLUTIONAL NEURAL NETWORK FOR NEAR EARTH OBJECT OBSERVATION AND DETECTION 20m
** CNN4NEOOD Abstract Proposal for Clean Space Industry Days**
Application of Artificial Intelligence in space domains is gaining prominent interest due the increasing demand for services and in-orbit satellites number, with a consequent increasing number of proximity operations and the need to mitigate the risks posed by space debris, and non-cooperative targets. The goal is to provide a complete solution that integrates image-based Meta Reinforcement Learning to actively recognize and track non-cooperative spacecrafts and space debris. This signifies the potential to revolutionize object detection and tracking in space, safeguarding critical space assets and ensuring enhanced safety in future space missions.
CONVOLUTIONAL NEURAL NETWORK FOR NEAR EARTH OBJECT OBSERVATION AND DETECTION, CNN4NEOOD Proposal, aims to create a robust and flexible AI algorithm able to work in different lighting conditions, damaged targets, occlusions, and other effects that might interfere with the data quality in order to simulate an In-Space environment for detection. The algorithm will use Meta Reinforcement Learning based on how human beings learn to be trained by relating to past experiences via sequential observation, in particular with videos, and the method applied is active with humans in the loop. Convolutional Neural Networks (CNN) are used for processing the acquired images and extracting relevant features. Recurrent Neural Networks (RNN) are capable of mapping temporal relationships in a sequence of inputs to the output, this property makes RNN suitable to be used within the Meta RL framework.
Observation method
Equipped with low technology readiness camera sensors, optical or multispectral, the simulated environment uses datasets and videos available to train the algorithm. Stereo photoclinometry and Stereophotogrammetry are executed with mixed input sourcing, optical and multispectral, to obtain a 3D from imagery. Thus, 3D reconstruction techniques are used to enhance the understanding of the environment.
Principle applied
Partially Observable Markov Decision Process (POMDP)
Every Reinforcement learning problem is a Markov Decision Process, depending on whether it satisfies Markov’s property. In scenarios where the state cannot be directly observed or is affected by noise, the Markov Decision Process (MDP) transforms into a Partially Observable Markov Decision Process (POMDP). In a POMDP, the underlying state of the environment becomes hidden, and the agent receives observations through an observation function that provides indirect information about the underlying state.
In the context of image-based RL, the observations contain embedded information about the state, but the agent does not have access to the actual state. Instead, it relies on these observations to make decisions. For example, in space debris tracking using images, the agent (a satellite) receives images from its onboard camera, but the true state of the debris (its exact position and velocity) remains unknown. Deep reinforcement learning with recurrent neural networks RNNs, can be employed to tackle the challenges of partial observability and make effective decisions in such environments.
State: The system employs computer vision techniques to estimate the state of the tracked object, including its position, velocity, and possibly other relevant attributes. This estimated state information is fed into the PPO framework to make decisions.
Action: At each time step, the actor network selects an action based on the current state, and the tracking platform executes the chosen action to update its viewpoint or trajectory.
Reward Function: The reward function es the learning process effectively. The reward function is likely to encourage the tracking system to follow the object accurately, maintain proximity to the object, and penalize with a penalty weight for deviations from the object's predicted trajectory.
Meta Reinforcement Learning (Meta RL)
Traditional reinforcement learning, the agent interacts with the environment and collects data (observations, actions, and rewards) to update its policy during training. The agent learns a policy that maps states to actions in order to maximize cumulative rewards over time. CNN is used for feature extraction. In our case we also employ an RNN to capture temporal dependencies in the image data, which can be crucial for successfully positioning the current state.
An actor-critic framework, in which two deep neural networks run in parallel to update the policy. The actor network is responsible for selecting actions (adjusting camera angles or the trajectory) based on the input data and its internal state. The critic network evaluates the actions performance and provides feedback to the actor to improve decisions.
Training Methods
Meta-RL involves training an agent (deep neural network) to learn how to learn more effectively in a reinforcement learning setting. Meta-RL takes this one step further by introducing an additional level of learning. Instead of directly learning a policy for the object detection task, the agent learns how to adapt or learn new policies more efficiently and effectively when faced with new, unseen object detection tasks. This is achieved by exposing the agent to a set of object detection training tasks during a meta-training phase. During the meta-testing phase, the agent is evaluated on its ability to perform well on new, unseen object detection tasks that were not encountered during the meta-training phase. By leveraging meta-learning, the agent can become better at learning from limited data, which is particularly crucial in Space applications, where acquiring large amounts of labeled dataset is challenging.
Proximal Policy Optimization PPO is employed as the reinforcement learning algorithm which is the state-of-the-art algorithm designed to perform well on on-policy optimization problems where you do not have an explicit model.
Simulation environment will simulate image acquisition from onboard cameras. Visual data will be captured from sensors mounted on a moving platform, such as a satellite or robotic arm. The goal is to actively track these objects in real time to estimate their state and improve tracking accuracy. The concept of Extended Simultaneous Localization and Mapping (ESLAM) is applied. An agent estimates a point of reference based on his own position and returns a map of the environment around itself reconstructed, in this case, via visual in-space observation and with particular attention to incoming objects.
Conclusions
Our project proposal CNN4NEOOD holds significant importance in the space industry due to the increasing demand for space surveillance use of the growing number of in-orbit satellites leads to a higher risk for space debris and non-cooperative targets. This means considerable challenge for space missions, as accurate detection and tracking of objects are essential for ensuring the safety of spacecraft, and efficiency of space operations. Therefore, signifying the importance of robust AI algorithm capable of real-time object detection and tracking. By integrating image-based Meta RL, the algorithm will actively improve learning, recognition and track non-cooperative space objects, even under varying lighting conditions, and uncertainties such as unknown observations, as is often the case with space debris tracking.
Speakers: Ms Aiswarya Unni (Tr2 srls), mauro venanzi (UrbyetOrbit srls) -
16:40
Dark & Quiet Skies 20mSpeaker: Andrew Williams
-
16:00
-
16:00
→
17:30
In-Orbit Servicing & Debris Removal: Mission Implementation: IOS
-
16:00
EROSS IOD - Mission Progress Status 20m
EROSS IOD (European Robotic Orbital Support Services - In Orbit Demonstration) is an EU-funded project within the Horizon Europe programme, aiming at demonstrating in orbit the European solutions for the Servicers and the Serviced LEO/GEO satellites, enabling a large range of efficient and safe orbital support services. EROSS IOD will showcase a mission design that will provide both life extension and life enhancement to future space systems, therefore answering both short-term customer needs and anticipating future new business perspectives.
The IOD phase of the EROSS project is the fourth part of the R&D partnership developed with the support of the European Commission. So far, the project allowed to increase the Technology Readiness Level of several key building blocks, in particular autonomous rendezvous and robotics.
The demonstration mission concept includes the complete orbital rendezvous phase of a Servicer satellite with a collaborative Client satellite prepared for On-Orbit Servicing that shall be followed by the capture and then servicing operations. The whole idea is to validate the capability of carrying out in-orbit operations of this type for future missions.
The project started in January 2023 after the SRR. It will last 27 months up to the CDR, with the in-orbit demonstration targeted by 2026.. The proposed presentation aims at giving a status on the progress of this development, 4 months ahead of the PDR.Speaker: Pierre Dandré -
16:20
Orbit Fab Podracer mission: an on-orbit testbed proving out the building blocks of sustainable orbital refueling 20m
The Orbit Fab Podracer mission, focused on rendezvous and proximity operations (RPO) in a sun-synchronous orbit, is the next step towards the first commercial satellite refueling. Refueling is one of the building blocks of a circular economy in space. The mission is an opportunity to promote sustainable in-space operations, and engage in open dialogue in on-orbit servicing. The mission, scheduled to launch in early 2024, will de-risk complex technologies required for a successful refueling. These include the RAFTI fueling port, a suite of sensors, an RPO-capable propulsion system, and proximity operations algorithms and relative navigation. Furthermore, it acts as a risk reduction for operations of an RPO-capable small satellite. In order to uphold a responsible, zero-debris approach to in orbit servicing development, the mission takes a stepwise approach in its deployment of select technologies to be proven on orbit. Later missions will build on Podracer, which is not a docking spacecraft, by performing closer approaches, docking, and refueling. The mission is designed to be rapid, low-cost, and collaborative. Learnings will be documented and shared in order to maintain an open dialogue with other in-space servicing companies and the public. It is an RPO testbed on orbit, which not only takes the next step towards on orbit refueling, but offers the opportunity to set the standard for collaboration across in orbit servicing companies and other stakeholders. For example, the spacecraft includes an Astroscale docking plate, which could be used for active deorbit at end-of-life. Agreements are being developed to collaborate with potential proximity operations clients, and plans are in place to provide public announcements of satellite proximity operations activity, similar to aviation “notices to air missions” (NOTAMs). The Orbit Fab Podracer mission strives to be an example that upholds clean space standards, including a zero-debris approach and responsible end-of-life management, and moves towards a more circular in-space economy. This underscores the possibility of achieving the dual objectives of technological advancement and sustainability in space operations, moving towards a future of responsible, cooperative, and economically viable space exploration.
Speaker: Connor Geiman (Orbit Fab) -
16:40
SENER's perspective on Active Debris Removal 20m
It is well-known that nowadays economy and society are highly dependent on the use of space and space applications: climate monitoring, weather forecast, transportation, communications, financial exchanges, etc. It is also known that, since the beginning of the space era the number of objects in orbit has continuously increased, with the orbital debris (abandoned stages, fragments from collisions and explosions, defunct satellites,…) outnumbering the operational satellites and hindering their missions. Moreover, in the last years, with the decrease in the cost of the access to space and the deployment of the so-called mega-constellations, the launches have increased to a rate never seen before.
The situation is such that, as stated in the last “ESA’s Annual Space Environment Report”, “Even in case of no further launches into orbit, it is expected that collisions among the space debris objects already present will lead to a further growth in space debris population. Based on these findings, among others, there is a growing consensus that stricter space debris mitigation and practices need to be implemented globally, and, eventually, remediation might need to be considered”.
In a nutshell: On top of mitigating the creation of new debris and improving the tracking and characterisation of the existing ones, there might be a need to remove the debris already in-orbit. Several approaches are possible, ranging from the remove of a sensitive number of small pieces of debris between 1cm and 10cm using various technologies, to the controlled / uncontrolled re-entry of the most dangerous large debris objects in orbit. Each approach has its own pros and cons and should be deeply analysed and considered, and probably a combination of several would be the right solution.
SENER Aerospace & Defence, as a pioneer engineering company in the design of satellites technology and equipment for the space exploration, is committed to contribute to the long-term sustainability of the space environment, not only for the success of the industry, but as a moral responsibility to preserve the space environment for ensuring the exploration, science and innovation in benefit of the future generations.
Therefore, with the aspiration to contribute to the fulfilment of the UN Long Term Sustainability Guidelines (e.g., B.8 and D.2) by governments and international institutions and keeping in mind the Space Debris Mitigation Guidelines (e.g., limit the long-term presence of spacecraft and launch vehicle orbital stages in LEO and GEO), SENER considers that a viable option to contribute to the remediation of space debris would be the development of a reusable “Cleaning Vehicle” attached to a container provided with several grasping mechanisms and de-orbiting devices. The “Cleaning Vehicle” would be able to manoeuvre to different orbits within the LEO region, identifying and capturing large debris objects by means of the grasping mechanisms, attached to them a de-orbiting device, release the object and manoeuvre to the next target. Once the container has depleted the grasping and de-orbiting mechanisms, it would de-orbit itself and a new container can be launched and docked to the “Cleaning Vehicle” to continue its mission.SENER is a leading company in the development of mechanism for space, as well as in GNC. Therefore, several projects run at SENER would be relevant for the development of the concept. In the next paragraphs, grouped by element of the “Cleaning Vehicle” and the container, these projects are summarised:
1. Rendezvous and capture GNC:
- SENER has been exploiting its capabilities to develop rendezvous and docking GNC systems, applied and further developed in the frame of the In-Orbit Logistics Proof Of Concept 1 ESA programme (POC1). The SENER rendezvous GNC is based on the use of onboard optimized guidance built on the SENER convex optimization toolbox (SOTB), and on in house developed collaborative visual navigation algorithms. Internal R&D activities are in progress to test in a robotic facility the rendezvous guidance and navigation and further mature the GNC algorithms in preparation of forthcoming POC1 phases. The rendezvous GNC has been designed in co-engineering with SIROM mechanical experts (see bullet 2), to ensure compliance with capture requirements, and provide inputs for SIROM evolution taking into account GNC needs and limitations. This concept could be used by the “Cleaning Vehicle” in case of collaborative targets (i.e. satellites designed with SIROM interfaces on-board)
- Under an ESA contract part of the Studies, Technology and Evolution Preparation Programme for the ISS, the Automatic Servicing Vehicle for ISS Surveilling (ASVIS) system was conceived as an unmanned vehicle operating outside ISS from an external Base Platform located on one of the platforms available for external payloads. ASVIS is an operative system for providing services to ISS such as: inspection at different ranges (both periodical and on-demand) and support for EVA.Figure 1. ASVIS System Concept
- SMART-OLEV was based on a purpose designed and built spacecraft to mechanically dock with a client satellite’s zenith face using its liquid apogee engine nozzle and launch vehicle interface ring. Neither electrical nor any other connections (e.g. fluid) connections are necessary to perform the on-orbit servicing except the mechanical link through the nozzle. SMART-OLEV would take-over attitude and orbit control functions for the client satellite allowing the client to continue to operate the other functions on the communication satellite as normal. In this way valuable geostationary hardware and orbital slots can be maintained and secured in a very cost-effective manner SMART-OLEV will be controlled before and during docking from a dedicated Operations Control Centre (OCC). After docking, SMART-OLEV control may be transferred to the client’s OCC if desired. Within SMART-OLEV SENER was responsible for some of the main subsystems and tasks like the GNC subsystem, the RCS subsystem and the camera image processing that would be relevant for the rendevouz phase of the “Cleaning Vehicle” and could be used in the case of non-collaborative target (i.e. no dedicated interface for the capturing/docking available)Figure 2. SMART-OLEV in docked configuration
2. Grasping of the object and attachment of the de-orbit mechanism:
- ADR clamping system, SENER was responsible for concept of a clamping system for the active debris removal (ADR) missions in frame of e.Deorbit activity led by Airbus. The clamping mechanism is responsible for catching a satellite to be removed from the orbit in order to allow to do so.
For the activity, various clamping scenarios were studied, aiming defining the suitable area (Interface) at a spacecraft to be caught by the clamping system. Final decision considered clamping on the Launch Adapter Ring (LAR) as the most suitable choice.
The mechanism is composed by the clamp driven by a motor with a gear. The motor is also coupled with a brake to maintain the position and force of the clamps. In addition, there is also a spindle driven rotational degree of freedom allowing adjustment of the mechanism in respect to the LAR.
- SIROM, already mentioned in the previous bullet, is a robotic interface that can be used both in orbital and planetary applications. As a robotic interface, SIROM integrates four different functionalities in a single mechanism: mechanical, data, electrical and fluids.
SIROM is one of the key “building blocks” developed for the European Union in the frame of PERASPERA, a project aiming to deliver enabling technologies and demonstrate autonomous robotic systems for on-orbit satellite servicing and planetary exploration.
SIROM was developed in the first Call of PERASPERA (2016-2019) by a project consortium coordinated by Sener Aeroespacial.
SIROM was successfully tested in a final orbital scenario by means of robotic devices, performing several test maneuvers, in AIRBUS DS (Bremen) and DLR.
In EROSS, project of the second Call of PERASPERA (2019-2021), Sener Aeroespacial has developed an integrated SIROM product combining the mechanics and flight compatible electronics, resulting in a simple and compact mechanism. SIROM is also being applied in other projects such as: MIRROR (ESA project), PERIOD (third PERASPERA Call) and currently in EROSS IOD (late PERASPERA call).
In addition, SENER Aeroespacial is coordinating a new Horizon Europe project, called ORUBOAS where SIROM is applied to a new concert of smart ORU (Orbital Replacement Unit).
SIROM videos:
https://youtu.be/uwpm_SOnYE8
https://youtu.be/fO-iVjy4voA
3. De-orbiting device: E.T.PACK-Fly is an EIC Project funded by the European Innovation Council with 2.5 M€. The main goal of E.T.PACK-F is to prepare a Ready-to-Fly (TRL 8) deorbit device based on ElectroDynamic Tether (EDT) technology. ETPACK-Fly will deploy 500 meters of thin aluminum tape in space and circulate up to 500mA of current collecting electrons from the earth plasma. Thanks to Lorentz drag the 24kg spacecraft will deorbit from 600 km altitude orbit in less than 100 days without using propellant. The E.T.PACK-Fly mission has been selected in the frame of the CASSINI IOD/IOV program to fly in 2025. The team of the project includes Universidad Carlos III de Madrid, the University of Padova, the Technical University of Dresden and Rocket Factory Augsburg.
Of course, all these development would be applicable also to other ADR concepts than the “Cleaning Vehicle” and SENER is open to collaborate in other visions/misions to ensure the long-term sustainability of the orbital environment.Speaker: María Antonia Ramos Prada
-
16:00
-
09:30
→
11:00
-
-
09:30
→
11:00
Ecodesign for Space: Exploring Environmental Hotspot Allocation: An Interactive SessionConveners: Estefania Padilla Gutierrez (ESA (ESOC)), Maarten Cauwe (imec-Cmst), Sara Morales Serrano (ESA)
-
09:30
→
11:00
End-of-Life Management & Zero Debris: How to reach Zero Debris WS: Successful Disposal and Orbital clearance
-
09:30
→
11:00
In-Orbit Servicing & Debris Removal: Policy and Close-Proximity Operations
-
09:30
Verification and Validation of Rendezvous and CPO Safety 30m
We will present the preliminary results of the ESA study "Verification and Validation of Rendezvous and CPO Safety", namely the derivation of CPO guidelines for cooperative and non-cooperative clients (starting from the critical review of the ESA CPO guidelines Issue2.0), and the subsequent definition of the V&V approaches, methodologies and numerical tools corresponding to each guideline.
Speaker: Anthea Comellini (Thales Alenia Space) -
10:00
Navigating the Stars Responsibly: Ethics in Mission Implementation for Active Debris Removal and In-Orbit Servicing 30m
As humanity expands its presence in space, the challenges posed by space debris and the need for in-orbit servicing become increasingly pressing. While we venture into these frontiers, it is essential to address the ethical considerations associated with these prospective and immerging missions. In this talk, Jane Davies (MSc) will explore the importance of ethics in mission implementation for active debris removal and in-orbit servicing.
With numerous satellites and defunct spacecraft cluttering Earth's orbit, proactive measures are required to mitigate the risks of collisions and safeguard critical space assets. Davies will delve into the ethical dimensions of active debris removal missions, discussing the importance of minimizing space debris generation, the equitable distribution of responsibilities, as well as the preservation of celestial environments. Additionally, although the rapidly advancing field of in-orbit servicing has the transformative potential for satellite maintenance and repair; it is essential to critically examine this emerging technology. This includes the need for transparency and accountability for in-orbit activities, equitable access to services, and the potential impact on space sustainability.
Drawing on insights from space law, policy, and ethical frameworks, this talk will propose guidelines and practices for mission designers, operators, and policymakers to navigate the ethical challenges of active debris removal and in-orbit servicing. In integrating ethical considerations into mission planning, implementation, and regulation, we can ensure the responsible and sustainable development of space activities, thereby protecting our orbital environment (and beyond) for future generations.Speakers: Jane Davies (know.space), jane davies -
10:30
ESA Close-Proximity Operations activities 30mSpeaker: Adina Cotuna (ESA\ESTEC)
-
09:30
-
11:00
→
11:30
Refreshment break 30m
-
11:30
→
13:00
Ecodesign for Space: Tools and Strategies for ecodesign in space
-
11:30
The Ecobox project - developing a toolbox for Ecodesign 15m
As many other actors in the sector, Airbus Defence and Space (ADS) is facing increasing internal and external requests for environmental evaluations and improvements of products in terms of sustainability. The needs are diverse, ranging from fast alternative assessments to external declarations. The resources, methods & tools to reply to these needs can be as various as the needs themselves. Up to now, ADS is not equipped with any clear unique framework or guidelines specifying which resources and methods are the ones to be used to reply to the needs.
The global objective of the project is to create a consolidated toolbox - the Ecobox - for products environmental evaluations and ecodesign guidelines. Trainings, evaluation tools, sustainability databases, processes or even network of identified Points of contacts are all the more means that will be consolidated in the toolbox.
The Ecobox will be a methodological platform, enabling the whole community of engineers to efficiently work on the question of products' environmental footprint and sustainability. This is seen as a first essential step into the engineering sustainability journey, providing solid foundation to the consideration of the topic and allowing it to grow bigger in the future. Value management is now a must in the innovation process, Design to Sustainability will then be a clear objective of the next developments.In 2023, the first step has been to better identify and understand the business needs, expectations and objectives regarding sustainability considerations for the products, systems and solutions developed by ADS. Interviews have been conducted to directly collect inputs and contributions from various teams across ADS engineering community and other parts of the company.
Our presentation would focus on the presentation of the Ecobox project and its first outcomes. A particular focus will be made on the SEEDS tool, a Simplified Ecodesign Evaluation for new Development in Space currently being developed by the ADS mechanical & thermal & robotics advanced project engineering team in the frame of an ADS-CNES contract.
Speakers: Ariane Bouilly (AirbusDS), Perrine Cau -
11:45
Ecodesign criteria for R&T and technology assessment in Airbus Defence and Space 15m
The maturation and maturity assessment of new technologies is essential for the success of new projects and programs. In some cases such processes require multi-years planning and significant investments before those technologies can be embedded in products for the benefit of our customers. It is therefore necessary to timely implement criteria for the assessment and the performance monitoring of the performance of such technologies also in terms of sustainability, and to harmonize such criteria with the ecodesign criteria implementation approach at product level. With this presentation we intend to provide a general description of the methodology and tools that are being introduced in Airbus Defence and Space for the successful implementation of sustainable criteria in the assessment of R&T projects.
Speaker: Luca Briganti (Airbus) -
12:00
SEEDS tool, a Simplified Ecodesign Evaluation for new Development in Space 10mSpeaker: Perrine Cau
-
12:30
Rapid Life Cycle Assessment Software for Future Space Systems’ Design - The Assessment and Comparison Tool 20m
As opposed to performance, cost, safety, and programmatic metrics, impacts on Earth or on the space environment have not been drivers of space systems and missions designs until recently. This is changing thanks to a shift of mindset, growing risk related to space debris, and a need to anticipate regulations that are likely to be applied to the space industry.
The new Assessment and Comparison Tool (ACT) software is made to create configurations of space systems and rapidly perform their life cycle assessment (LCA) based on user-known data and assumptions. Users can input high-level system values and select the relevant LCA datasets used to compute the environmental impacts of that system. This tool will be used in early design phases or other decision-making processes as support to identify key technology, life cycle steps, or components of future designs in order to adapt them to mitigate related environmental impacts while being aware of potential trade-offs and hotspot shifting.
Early analyses are crucial to help engineers make design choices that can reduce environmental impacts, a process called ecodesign [1]. To perform the assessment, the systems’ production, material sourcing, emissions, operational phase, transport, and other contributions from the product’s entire life cycle are compiled to assess impacts with LCA indicators.
The tool is designed for evolution. It embeds a modular data structure which allows scope extensions and implementations of newer calculation methodologies as the scientific research progresses. Besides the science gaps, technology gaps can be highlighted from the computed impacts and the intention to mitigate part of them using ecodesign processes.
The presentation at the CleanSpace Industry Days 2023 will include a description of the Assessment and Comparison Tool, its functionalities and capabilities, and will detail the ongoing and needed research to fill knowledge gaps in LCA for space systems. Ideas to model reusability, vehicles for new launch architectures, and new missions will be shared regarding environmental impacts. Lastly, future developments of the tool will be discussed following four main focus: LCA and environmental aspects of space systems in ACT, modularity of the code, software backend improvement, and user experience.[1] ESA Space Safety, Clean Space, “ecodesign”, https://www.esa.int/Space_Safety/Clean_Space/ecodesign, consulted on 19.07.2023.
Speaker: Mr Mathieu Udriot (EPFL Space Center)
-
11:30
-
11:30
→
13:00
End-of-Life Management & Zero Debris: How to reach Zero Debris WS: Active Debris Removal and Space Debris release
-
11:30
→
13:00
In-Orbit Servicing & Debris Removal: Robotics
-
11:30
Grappling and Refuelling Active Solution for Propellants (GRASP) - A Concept for a European Active Side to the RAFTI Open License Interface 15m
Orbit Fab is developing an orbital infrastructure of space vehicles to serve as the in-orbit propellant supply chain. The RAFTI open license service valve acts as a drop-in replacement for fill and drain valves which enable ground fuelling as well as in space refuelling services to customers who embark the valve on their platforms. Customers are able to equip their platforms for refuelling with minimal impacts to their systems due to the RAFTI being a passive, light weight and small form factor interface. Orbit Fab vehicles serve customers through an active electromechanical and fluidic interface which handles the docking and refuelling via RAFTI. Currently in qualification by the US Orbit Fab team is the GRIP (Grappling Resupply Interface for Propellants) which serves the active interface needs of the upcoming US government and commercial missions for hydrazine refuelling. An active interface with complementary capability is required to serve the whole space propulsion ecosystem, especially for the higher pressure propellants used in electric propulsion. As such, the parallel development of GRASP (Grappling and Refuelling Active Solution for Propellants) is being pursued by the UK team to develop a product that is pressure agnostic, modular and compatible with RAFTI. The parallel development is also pursued to provide an attractive European product built with local capabilities, which will be unencumbered by export constraints currently associated with the GRIP interface. A concept is already established for the design of the GRASP mechanism, with further iterations expected as the development campaign matures. GRASP is expected to be needed for near term Orbit Fab propellant deliveries through European built propellant depots and shuttles. The development status of the GRASP active refuelling interface is presented, along with the overall development plan and roadmap for the implementation of GRASP into Orbit Fab missions and technological architectures. A preliminary concept of GRASP and initial pathfinder test results are also presented, where the key mechanical building blocks and kinematics of the soft and hard capture operations have been validated in a relevant environment.
Speaker: Sebastian Hill (Orbit Fab) -
11:45
Minimum invasive refueling coupling, for teleoperated refueling operations. 15m
Despite the drastic launch cost reductions in the last 20 years and the various attempts to design multifunctional docking and refueling interfaces in US and Europe, Satellite Operators industry does not seem interested in adopting a particular coupling. A simple coupling is proposed, for a second time (as per AIAA 2006-5660), based on an adapter, applicable to existing fill & drain valves.
Speaker: Mr Charalampos Kosmas (LUNAR CARGO P.C.) -
12:00
Development of Modular Robotic System for Servicing and Deorbiting Missions 15m
The growth of space industry is unprecedented in recent times. Each year more satellites occupy Earth’s orbit, providing services such as telecommunication, imagining and navigation. The rapid expansion of space industry resulted in increase of hazards connected with space debris. The defunct man-made objects exceed the number of functional satellites and constitute a risk of collision to spacecraft. This article focuses on a progress of technologies for active debris removal and servicing developed by PIAP Space Sp. z o.o., Polish aerospace company. The robotic suite consists of components that include robotic manipulator, end effectors, dedicated vision system as well as force and torque sensor. The devices are under development in the TITAN, EROSS IOD and ORBITA projects. The objective of the TITAN project is to develop and demonstrate a 7-degrees-of-freedom robotic manipulator system for on-orbit servicing and small debris removal missions. The design of the manipulator is based on scalable joints and boom elements that enable its integration with various systems. Polish Space Research Centre is cooperating in the development of the control subsystem of the technology readiness level 6 demonstrator. The Launch Adapter Ring Gripper EM was developed in the EROSS+ project. Further models are under development in EROSS IOD. The gripper constitutes an end effector for a robotic arm of a servicing satellite and is designed to grasp and clamp interface of a target satellite during the berthing manoeuvre. This enables attitude and trajectory control including deorbiting as well as maintenance and repair operations. Multiple devices are developed within the ORBITA project. The Multipurpose Servicing Gripper is mounted on a robotic arm as an end effector. It is intended for conducting upkeeping operations on on-orbit satellites by grappling parts of the target satellites and using interchangeable tools. The vision system for the purpose of launch adapter ring position estimation during rendezvous is based on time-of-flight detector. The calculations of spatial transformations of the technology demonstrator are conducted on dedicated computer which uses parallel computing to expedite processing. The force and torque sensor is intended to be placed on the end of robotic arm, prior to its end effector. A proprietary controller and software compatible with strain gauge sensor are under development. The outlined devices are meant to be used as building blocks in upcoming space missions. They can be incorporated into future and already existing solutions owning to their compatibility with the European space industry ecosystem. Beforehand a series of demonstrations is planned. The TITAN manipulator entered MAIT phase and on ground verification end of 2023. The force and torque sensor functional and selected environmental tests shall be finalised end of 2023. The functionality of the Launch Adapter Ring Gripper will be evaluated during the in-orbit demonstration. The developments are intended to help in providing safer and cleaner space.
Speaker: Dominik Kleszczyński (PIAP Space) -
12:15
Unveiling the Potential of Cooperative Multi-Agent Spacecraft for ADR, IOS, and Cyclic Space Economy 15m
Space exploration and exploitation depend on the development of in-orbit robotic capabilities for tasks such as servicing satellites, removing orbital debris and its recycling, or construction and maintenance of orbital assets. Manipulation and capture of objects in orbit are key enablers for these capabilities. Using today's single space manipulator systems with low autonomy and universality for capture limits the advancement of the mentioned key tasks. The ambition of the team around Space scAvengers startup, strongly supported by Telespazio, is to go beyond the well-established single-system servicing approach. The Cooperative Multi-Agent Spacecraft (COMAS) technology and concepts are being analyzed to support an approach to future in-orbit services based on swarms of small spacecraft acting as coordinated agents. Under the ESA PECS contract, Space scAvengers are halfway towards MDR of SAM-1 (Space scAvengers Mission 1) which aims to be the world’s first swarm ADR mission with a goal to demonstrate the flexibility of the swarm approach for ADR, particularly for the cooperative, mainly autonomous inspection, mating, capture, and repositioning of selected European uncooperative debris from a business interesting orbit to a junkyard orbit chosen. Draft of the SAM-1 Conops, key requirements, and the system concepts will be discussed during the presentation. Particular attention will be paid to the preliminary market potential and the expected impact of COMAS technology on ADR, IOS, and the cyclic economy in space.
Speaker: Dr Marek Gebura (Space scAvengers) -
12:30
Extending Ground Segment Products for supporting a large range of In-Orbit Services 15m
With the support of ESA and National administrations, Europe is developing its capability to deploy and operate infrastructure covering a large range of in-orbit services, from deorbiting and satellite life extension solutions to the in-orbit replacement of damaged subsystems. As one of the leading operations and ground segment providers in Europe, Telespazio are extending their ground infrastructure and operations capabilities with partners with the objective to provide support to a large portfolio of in-orbit services. This covers essentially the development of tools and expertise for close proximity operations as well as robotics control. Artificial intelligence for automation and autonomous operations on-board and on-ground is a major technology that is integrated with first priority in the Telespazio infrastructure. AI techniques will span from Statistical Learning, Timeseries regression and Random Forest classifiers to predict and recommend automated operational procedures, to physics informed neural network to realize a digital twin of space assets and provide a prediction of in orbit service maneuverers.
The presentation will described the infrastructure that will be available at Telespazio for supporting In-Orbit Servicing missions and the future plans of Telespazio to increase their involvement in this domain.Speaker: Marc Niezette (Telespazio Germany GmbH)
-
11:30
-
13:00
→
14:00
Lunch break 1h
-
14:00
→
15:00
Keynote by Former ESA Director General, Jean-Jacques Dordain: "Bridging Earth and Space for Environmental Responsibility" 1h
-
15:00
→
16:30
Ecodesign for Space: Green propellants
-
15:00
Single Score Methodology for Space LCA 20mSpeaker: Lily Blondel (Università di Pisa)
-
15:20
Comparative life cycle sustainability assessment of novel monopropellant systems. 20m
In the research field of novel monopropellants, there is a strong emphasis on the toxicity of hydrazine and the required non-toxic nature of the potential replacements for this widely used monopropellant. Novel monopropellants are often praised for their handling procedures which are less strict, costly and wasteful compared to hydrazine. However, while the sustainability improvements in this part of the life cycle have been well-documented, there has been less attention with respect to the implications for other processes in the entire life cycle of the propulsion system. Furthermore, there has been little research on the manner in which the total environmental impact of a propulsion system changes due to the system-level design changes required to accommodate novel monopropellants.
This research will therefore systematically compare how the sustainability of a monopropellant propulsion system changes when hydrazine is replaced by novel monopropellants. For a case study of a 150 kg minisatellite in an Earth Observation constellation, five potential propulsion systems are designed at a conceptual level, to be used with respectively hydrazine, ASCENT, LMP-103S, SHP163 and 98% concentrated hydrogen peroxide. A life cycle sustainability assessment (LCSA) is performed for each of these designs, resulting in an in-depth comparison of the environmental, economic and social sustainability of each of the systems. The LCSA is performed using the Strathclyde Space Systems Database (SSSD) and will extend the database to include the relevant propulsion system components which are compatible with the specific monopropellants.
The findings of this research will allow for a better understanding of the overall impact of replacing hydrazine by each of the novel monopropellants considered. Furthermore, potential improvements in the production processes of the novel monopropellant systems may be identified, to inform a more sustainable life cycle in the future. Lastly, a detailed overview of the absolute environmental impact of propulsion systems using novel monopropellants will allow for a less ambiguous usage of the term “green” in this context.
Speaker: Pepijn Deroo -
15:40
Water Propulsion – The Ultimate Green Technology 20m
State-of-the-art satellite chemical propulsion systems are based on conventional toxic propellants such as Hydrazine or its derivatives, which are environmentally harmful and therefore very extensive in handling.
Although, harmless to the environment, cold gas thrusters cannot reach the performance of chemical combustion technology, requiring big and high pressure gas tanks.
Electric propulsion technology offers very high specific impulse, which is required for highly efficient orbital manoeuvres, but due to the low thrust provided, no debris mitigation manoeuvres can be performed. Here, usually thrust of multiple magnitudes higher than EP can provide is required, to change orbit quickly for collision avoidance. Furthermore, the gases used as propellant are usually quite costly.
ArianeGroup is developing the Water Propulsion System as the ultimate green technology. Pure water is used as propellant, which is decomposed via electrolysis to generate hydrogen and oxygen, once the spacecraft is in orbit. The combination of hydrogen and oxygen offers 50% higher specific impulse compared to Hydrazine based thrusters. The gases are generated and stored under pressure until thrust is required. Then, the gases are pressure fed to one or several chemical thrusters to be recombined and expelled.
Not only is water green in every sense – no harm to the environment, easy handling, high performance, low cost – but it is also a convenient way to store hydrogen in space.
Furthermore, water offers many synergetic effects by combining multiple spacecraft subsystems, such as the life support system (drinking water, respiratory oxygen generation) or the power supply system (regenerative fuel cell).Speaker: Mr Malte Wurdak (ArianeGroup) -
16:00
Laser beam melting for the manufacturing of rocket engine parts: a study of the environmental impacts 20m
Compared to Conventional Manufacturing (CM), Additive Manufacturing (AM) can enable the production of complex and optimized shapes while reducing the manufacturing cycle. For this reason, it is increasingly used to manufacture parts of rocket engines. AM is often presented as being able to be more economical in raw material and is seen as a “clean” process, without it having been fully demonstrated. Does it really show environmental advantages and if so, under which circumstances?
This paper presents an evaluation of the environmental impacts - from cradle to factory gate - of the Laser Beam Melting process used to produce one kilogram of a selection of metals (aluminum, stainless steel, Inconel and titanium). This helps to identify the major contributors of the impacts and find strategies to environmentally improve the process. In a second step, a comparative simplified Life Cycle Analysis is presented for the manufacturing of a turbopump volute casing (in aluminum or Inconel) with Laser Beam Melting or a CM process (casting).Speakers: Laurence Rozenberg, Mathilde Jullienne, Noémie Boucherit
-
15:00
-
15:00
→
16:30
End-of-Life Management & Zero Debris: How to reach Zero Debris WS: Collision risk management and Space Situational Awareness
-
15:00
→
16:30
In-Orbit Servicing & Debris Removal: Guidance, Navigation and Control (GNC)
-
15:00
Trajectory Optimization for The Proximity Rendezvous Operation Considering The Relative Navigation Error 15m
Autonomous spacecraft proximity operation is demanded to achieve future missions, such as in-orbit servicing, active debris removal, object inspection and in-orbit assembly. The relative navigation is one of the factors which affect the overall performance and reliability of the rendezvous. Generally, the relative navigation sensors such as cameras with image processing or LiDAR are used to obtain the relative position or the attitude. However, when rendezvous to the non-cooperative target, the relative navigation at the proximity will be unstable and navigation performance is easily deteriorated by absence of illumination, shadows, strong reflection from the target, shape and surface of the target, etc. If the worst condition for navigation, the solution will be unstable and contains larger error, and in the worst case, the solution cannot be obtained. Those large error or absence of the navigation directly leads to the failure of the rendezvous and forced to rendezvous from the beginning again. In order to avoid the unstable navigation, the trajectory which can expect high reliability and precision navigation needs to be obtained. Hence in this research, the trajectory optimizing the relative navigation accuracy is studied. The two relative navigation accuracy model was adopted for general image processing with single camera toward the small satellite and LiDAR based matching toward the used rocket body. The simulation results revealed that the optimized trajectory is obtained for both cases and both cases had the low navigation error expectation throughout the rendezvous process. The proposed approach can be used for any relative sensors as long as their performance is evaluated beforehand.
Speaker: Mr Yu Nakajima (Politecnico di Milano) -
15:30
Opportunities and Challenges in Deep Learning-based Spacecraft Pose Estimation for Future In-orbit Servicing missions. 15m
In recent years, interest towards in-orbit servicing (IOS) and active debris removal (ADR) has been increasing rapidly, thus resulting in increased technology demonstration and commercial orbital-servicing missions. Future IOS and ADR missions are expected to be more autonomous, and sensor perception is critical to gain knowledge and information about the target, especially if the target is known and non-cooperative. Monocular sensors are widely preferred in space applications due to mass limitations imposed by other sensors, such as LiDARs. Monocular vision sensors encompass various sensors such as RGB, Thermal/Infrared, and Event Cameras, each with different data but operating under the single principle of pin-hole cameras. RGB cameras have been prominent in space missions and have a long space heritage for earth-orbit and deep-space missions. Recent developments in computer vision and AI, especially deep learning, unlock new realms of possibility with monocular vision sensors. In IOS and ADR missions, it enables more autonomous spacecraft with a wide range of capabilities, including navigation, rendezvous and docking scenarios, grasping and manipulating objects using actuators such as robotic arms, and many others. As deep learning research evolves in this space domain, the challenges encountered will be specific to the characteristics of the spacecraft environment domain.
Deep learning algorithms are known for their requirements for large amounts of data. However, no large datasets are available for in-orbit targets, and it is harder to acquire for individual mission targets. So, the primary research go-to solution is to generate data using simulators synthetically. SPEED[1], SPEED+[2], and SPARK [3] are standard datasets with synthetically generated images accompanied by small proportion images from the laboratory environment. With synthetically generated data used for training, the problem of domain gap arises when the trained model is applied to test data from lab setup or actual space imagery. There is a significant drop in performance when the model encounters data not seen in training or out-of-training distribution. Several steps have been made to tackle the problem, from the data perspective, adding different modalities and performing multi-modal data fusion, and from an algorithm perspective, training the algorithm with an adversarial approach to solving these problems. However, such practices lead to the problem of significantly larger models, which are hard to deploy in edge devices or a resource-contained environment. In a multi-modal setup, the data from these different sensors are entirely hostile to one another.
Recently Event cameras are gaining popularity with the new generation of hardware development. With the deep learning algorithms catching up for event sensing, it allows space applications to reduce the domain gap. Event cameras are known for their extremely high dynamic range, up to 120 dB and low power consumption, which makes them highly suitable for space applications. However, it has unique challenges for use cases, including spacecraft pose estimation.
This talk will discuss the challenges in selecting the hardware and choosing the correct algorithm development strategy for spacecraft pose estimation. Also, the challenges in algorithm development include domain gap, dataset generation, and model deployability, along with the opportunities in the evolution of current research to tackle these problems, including domain adaptation, multi-model training, neural architecture search and quantization-aware training. This talk will additionally explore the following questions: 1. Can RGB camera data be complemented with the data from other cameras in a multi-modal data fusion? 2. Can an Event camera be considered for spacecraft pose estimation? 3. Domain gap challenges in deep learning and how domain adaption approach can solve the problem and its importance for spacecraft pose estimation. 4. Deploying model in edge devices and how neural architectural search is evolving to find the optimum topology of the architecture to help in deployment in edge devices.
[1] Kisantal, Mate, et al. "Satellite pose estimation challenge: Dataset, competition design, and results." IEEE Transactions on Aerospace and Electronic Systems 56.5 (2020): 4083-4098.
[2] Park, Tae Ha, et al. "SPEED+: Next-generation dataset for spacecraft pose estimation across domain gap." 2022 IEEE Aerospace Conference (AERO). IEEE, 2022.
[3] Rathinam, Arunkumar, et al. (2022). SPARK 2022 Dataset : Spacecraft Detection and Trajectory Estimation [Data set]. Zenodo. https://doi.org/10.5281/zenodo.6599762
Speaker: Arunkumar Rathinam (University of Luxembourg)
-
15:00
-
16:30
→
17:00
Refreshment break 30m
-
17:00
→
18:00
Ecodesign for Space: Launchers
-
17:00
Ariane 6 & P120C Process improvements contribution to a more sustainable European Launcher manufacturing 20m
Together with Ariane 6 & P120C major industrialists, ESA identified a set of improvements with relevant cost assessment.
The principal purpose of the activities is to reduce the costs required to manufacture Ariane 6 and furthermore to increase sustainability. In the longer term, ESA’s contribution to, and management of, the Process Improvement activities are of the utmost importance so as to enable synergies and provide a frame for the optimisation of the Ariane 6 supply chain. Modernisation of the launcher manufacturing means through Process Improvement, will support the following European space industrial priorities:- Intelligent automation,
- Predictive maintenance,
- Asset sensors implementation.
These activities enable and are a precursor to a fully robotised and intelligent value chain end-to-end. Three major achievements for the activities have been defined:
Achievement 1: to reduce manufacturing cost.
For a given process the current man hours and material costs are measured. The industrialist assesses a percentage of manufacturing cost reduction, resulting in an estimated cost reduction. It is expected to be achieved as from the manufacturing of the sixteenth shipset onwards.Achievement 2: to reduce lead time.
For a given process the industrialist will reduce the process time, by reducing labour and machine hours. Thus, optimising the use of labour, assets and energy resources. The current process time is measured and will be monitored against the envisaged process time reduction.Achievement 3: to reduce environmental impact.
The environmental impact of the European Launcher product will be reduced through the introduction of more sustainable processes (eco-design approach). As the activities are directly contracted by ESA to the industrialist, the Agency has visibility on the current process, the improved one, and the associated environmental assessments. ESA proposes a process for the companies to assess and monitor the environmental impact of their manufacturing processes. This approach follows the reference set by ESA in ESSB-HB-U005 Space System Life Cycle Assessment (LCA) guidelines, and it is split into the following steps:- Identification of the steps in the process affected by the process improvement activity to be implemented. The general process flow proposed in the ESA LCA Questionnaire developed by the Clean Space Office is proposed as a basis for this evaluation.
- Provide a baseline scenario per activity: environmental impact of the current process.
- Provide an assessment of how the Contractor expects to reduce the environmental impact of its process through process improvement. In this step, the Contractor shall indicate which is the environmental impact mitigation measurements contained in each Process Improvement activities.
- Provide a resulting scenario per activity: environmental impact of the proposed process after the implementation of the Process Improvement activity.
This third achievement will be presented at the Clean Space Industry Days 2023.
It constitutes an innovative approach aiming at evaluating the environmental impact of Launch System Ground Segment applying similar concepts and methodology to those used for product LCA. The approach will first concentrate on Global Warming impact and energy consumption. The Agency gives the flexibility to the industrialist to propose additional parameters depending on the assessed perimeter.
A pilot case with a major Ariane 6 industrialist is already ongoing. Among the key gains from the activities identified for the Pilot Case, the team is already observing: reduction of internal and external logistic effort, reduction of necessary reworks, replacement of environmental unfriendly & hazardous processes, and reduction of energy consumption – all these factors affecting the environmental impact of the currently standing processes.
This approach sets the reduction of environmental impact as a priority for D/STS in one of its main Programmes.
Speaker: Nicoletta Wagner (ESA STS) -
17:20
Comparison of the Environmental Impact of Production and Launch Emissions of Different Common Launcher Architectures and Propellants 20m
Space travel is at a turning point in its history. In 2022, more space objects were launched into space than ever before. The announced number of satellites for constellations will require an unprecedented transport capacity. At the same time, humanity is faced with the challenge of converting its activities to sustainable operations. Against this background, the question arises as to how space activities can be
carried out in an environmentally friendly manner.
This presentation aims to contribute to this by examining the environmental impacts of stage production and launch emissions using typical mission scenarios. Common payload capacities are defined for target orbits in order to be able to compare the environmental impacts. Subsequently, different launcher system architectures are developed for the defined orbits. These differ in their staging as well as the propellant system used.
In the next step, the subsystem masses and volumes are determined on the basis of a generic design. Using generic environmental indicators, the overall impact of production is calculated.
The environmental indicators are based on the analysis of the Ariane 6 LCA study conducted by ArianeGroup. Individual values were determined for each subsystem.
Finally, the analysis is used to evaluate and compare different propellant systems and launcher system architectures in terms of their environmental impact from production and launch. This is done based on the two functional units per ton payload and depending on one launch into the target orbit.
The work is intended to contribute to making space transport more environmentally friendly to shed light on the influence of propellant choice and stage architecture in terms of environmental impact.Speaker: Jan-Steffen Fischer (University of Stuttgart, Institute of Space Systems) -
17:40
MaiaSpace's update on the implementation of LCA and ecodesign in the development of a semi-reusable minilauncher 20m
MaiaSpace is a European space tech company, designing, manufacturing and operating more sustainable space transportation solutions. It is driven by the belief that space stands as a major enabler for a better and more sustainable life on Earth, contributing to future challenges mankind is facing: climate change, resources run out, digital divide, data collection. Its first and primary focus is on flying a reusable, eco-responsible and competitive launcher by 2026 and its objective is to become a space mobility champion. This launcher will be propelled by liquid oxygen and biomethane thanks to four Prometheus engines, already under development by ArianeGroup on behalf of ESA, and its first stage will be derived from Themis, a reusable lower-stage demonstrator, also being developed by ArianeGroup for ESA. MaiaSpace has the ambition to have the best impact of the industry on the Earth and space environments. Realizing this ambition has a cost and requires a strong sustainability engineering approach at all levels of the company. To achieve this, MaiaSpace has been evaluating the environmental impacts of its launch service through a Life Cycle Assessment model since day one, which has been updated and consolidated since. In addition, due to the current limitations of existing reference methods for launchers LCA and ecodesign, a methodology was developed to address some major issues. It includes the management of reusability in LCA and the derivation of characterization factors that provide a rough order of magnitude estimate of the effect of high-altitude emissions on climate change. MaiaSpace has initiated and will co-fund a PhD project to better understand these high-altitude effects. Based on this baseline LCA model and this methodology, MaiaSpace has set itself environmental targets and is implementing an ecodesign strategy to achieve them. To this aim, a set of tools were developed to manage costs and environmental impacts in a consistent way to efficiently support targets monitoring and decision-making. A few design trade-offs were successfully realized by incorporating environmental impacts indicators in the process. After 1.5 years of setting up and implementing ecodesign on a real project, MaiaSpace can provide a valuable return on experience by highlighting difficulties and sharing successes, and underlines the importance of setting a methodological standard to evaluate and compare the environmental performance of launchers.
Speaker: Loïs Miraux (Maia)
-
17:00
-
17:00
→
18:30
End-of-Life Management & Zero Debris: How to reach Zero Debris WS: Re-entry safety
-
17:00
→
18:30
In-Orbit Servicing & Debris Removal: Guidance, Navigation and Control (GNC)
-
17:15
A fault-tolerant AI processor to accelerate onboard computer vision workloads 15m
In the context of in-orbit servicing, the implementation of a space-servicing vehicle necessitates a specific level of autonomic decision-making capabilities. This requirement becomes particularly crucial when dealing with active debris removal of defunct satellites that exhibit uncooperative behaviour during the removal process, potentially also displaying unpredictable attitude behaviour. To address these challenges safely, computer vision plays a vital role in providing real-time visual perceptual and situational information to the lower-level control system of the space-servicing vehicle. To enable the reliable execution of computer vision tasks on board a spacecraft, Magics is currently developing a radiation-hardened AI processor specifically optimized for such computer vision workloads.
While several AI processors are entering the space market, it is worth noting that they are mostly upscreened commercial components not explicitly designed to withstand hostile environments like space. Given the safety-critical nature of in-orbit servicing tasks, it is crucial to ensure a high level of fault tolerance in the onboard computer. However, with upscreened components, this typically requires the use of triple-modular redundancy (TMR), which significantly increases the area requirements. Moreover, sustainability is a key concern, as the space-servicing vehicle needs to withstand long-term radiation exposure to avoid contributing to the space waste problem itself.
To address these challenges, a dedicated radiation-hardened AI processor is essential. Magics' MAG-AIA00101-SC is such a processor, designed to be radiation-hard by design, delivering high computational performance (10 TMACs/s) to support advanced AI workloads. It boasts a peak power consumption of only 1 W, making it suitable for small satellites with passive cooling requirements. The processor incorporates a programmable RISC-V microcontroller unit (MCU) and features a vector engine to facilitate real-time image pre-processing. Additionally, a large-scale dedicated AI engine is integrated to accelerate AI model inference. As the platform is optimized for computer vision tasks, it supports various modern peripherals essential for space missions with high data throughput demands. To further aid in AI model compilation and optimization, support for the open-source TVM platform will be provided.
In conclusion, the proposed radiation-hardened AI processor offers reliable and sustainable neural network inference capabilities for state-of-the-art computer vision workloads in space. This processor is particularly well suited for aiding control systems of satellites in safety-critical applications that require perceptual information at their input, as seen in active debris removal operations. It maintains competitiveness with commercially available components in terms of computational efficiency and software development ecosystem while providing the added advantage of being fault-tolerant and long-term reliable.Speaker: Dr Jasper Wouters (Magics Technologies NV) -
17:30
Progress in vision-based navigation technologies for non-cooperative close proximity operations 15m
LMO is a Luxembourg based company involved in the development of vision-based navigation technologies for close proximity operations, with a focus in modern algorithms, their embedding in space-capable state-of-the-art electronics and their interaction with the spacecraft GNC system. Progress has been made through three main streams covering the development, implementation and validation in space: (1) a development programme (called DIOSSA) funded by Luximpulse and with technical supervision from ESA, focused on computer vision algorithms and deployment in electronics, (2) the participation in one of the consortia for the ESA PoC-1 project, and (3) a first in-flight demonstration in space, in a project called AUDACITY.
In this talk, the progress made in these 3 projects as well as the lessons learnt will be shared with the Clean Space community, highlighting the main challenges found, gaps identified, and the next steps. The vision on how these building blocks come together in a future Active Debris Removal mission will also be presented.
Speaker: David Regad (LMO) -
17:45
A multispectral camera solution for guidance and navigation on space servicing vehicles 15m
MDA UK together with City University of London (CUL) is developing VIRGO (Visible and InfraRed Guidance Optics), this is a multispectral camera solution which combines two spectral bands, thermal infrared (TIR) and visible (VIS), with complementary sensitivities and capabilities, into a single architecture design. Furthermore, this solution comprises algorithms for sensors data fusion and pose estimation developed by CUL to provide an autonomous navigation suite.
Such technology development, currently funded under the ESA GSTP project MuLaN, will be critical to the space transportation logistics ecosystem, which will require flight ready rendezvous and in-orbit servicing capability to satisfy the evolving institutional and commercial transportation needs.
In particular, the recent ESA In-Orbiting servicing industrial workshop (2022) showed a potential in the market, considering that an estimate of 245 GEO satellites are approaching EOL by 2035, so they would require servicing, life extension or removal to achieve the net-zero strategy aimed to be reached in 2030.VIRGO is being designed with modularity in mind with flexibility to expand functionality with inclusion of additional visible subsystem for wide-angle inspection and docking (< 15 m) or long range (> 250 m) instead. The current baseline design includes an additional visible subsystem to allow wide angle field of view for close-range rendezvous capabilities up to 5 m distance from the target spacecraft.
VIRGO is primarily targeting for its usage on on-orbit servicing rendezvous and docking scenarios, and so it utilises a bespoke pose estimation algorithm which assures effectiveness from 250 m down to 5 m. The algorithm provides regular updates regarding position and attitude of the target to allow safe guidance of the chaser spacecraft; with the additional benefit of the multispectral system allowing operation in a multitude of illumination conditions and providing more information to the algorithm than separate optical systems could.
VIRGO is expected to reach TRL 6 within the current calendar year, this will be achieved by means of an Engineering Model demonstrating critical functions verification in relevant environment.
Speaker: Chiara Palla (MDA UK) -
18:00
A reliable visible camera suite for In-Orbit Servicing 15m
With easier access to space and the arrival of new players, the number of satellites is increasing sharply. From the 2000s to the 2020s, the annual number of objects launched into space rose from a hundred per year to more than a thousand. In the same time, the risk of collision between active satellites and inactive objects and space debris has become more tangible and is monitored daily. Awareness of the need for a sustainable Space and economic interests are behind the emergence of In-Orbit Servicing. Thus, services such as satellite life extension, refuelling, upgrade or repair are expected to grow in the coming years. This trend will likely benefit from sensors and actuators that will not be a burden, either physically or economically, to the servicer vehicles. As low mass, low power and affordable sensors, cameras appear to be the sensor of choice for a growing number of future servicers needing to perform rendezvous and proximity operations in space.
With this in mind Sodern is developing AURICAM and HiCAM visible cameras to serve the purpose of reliable navigation and rendezvous solutions. Both cameras withstand radiations from LEO to GEO.
HiCAM is a small-medium field of view camera benefiting from high TRL subassemblies coming from HYDRA star tracker flight proven since 2012, and the Narrow Angle Camera (NAC) being developed for ESA Mars Sample Return (MSR) Earth Return Orbiter (ERO) mission. HiCam is expected to effectively support far range rendezvous operations.
AURICAM is a compact high-resolution camera derived from the AURIGA star tracker that was developed for the OneWeb constellation. Available with a medium or wide field of view, AURICAM is expected to be well suited for at least medium to close range rendezvous and proximity operations.
It will be shown how we believe these cameras can fit into a vision-based rendezvous system and support with some overlap the different phases of a typical rendezvous. To illustrate part of this, the example of a demonstration of ARAMIS vision-based rendezvous solution during a final approach simulated on a robotic test bench with a camera representative of AURICAM will be presented.Speaker: Laurent Majewski
-
17:15
-
18:00
→
18:30
Ecodesign for Space: Ecodesign Sessions Wrap-up
-
09:30
→
11:00
-
-
09:30
→
11:00
Ecodesign for Space: Space Life Cycle Perception Board Game
-
09:30
Space LCP Board Game 1h 30m
The Life Cycle Perception Board Game is a teamwork challenge where you build the environmental life cycle of a space mission. You'll learn the types of issues to consider when evaluating the environmental impacts of a space mission. By comparing what you think with the real facts, you'll see why sustainability in mission design matters from the start.
-
09:30
-
09:30
→
11:00
End-of-Life Management & Zero Debris: Deorbit & Passivation technologies
-
09:30
Advancements in Inflatable Drag Devices for Satellite De-Orbiting by SPACEO 18m
This presentation will review the progress made by SPACEO in the field of inflatable drag devices, which are a crucial technology for the de-orbiting of satellites.
SPACEO identified and tested a range of materials tailored for the unique demands of the space environment. These materials exhibit characteristics such as extreme durability, lightness, and resistance to harsh space conditions. Validation tests performed on these materials confirmed their suitability for constructing inflatable drag devices.
Alongside materials development, SPACEO has also made strides in creating accurate and reliable sizing models for these inflatable drag devices. The models' successful validation with testing activities of inflatable beams in 3 points bending demonstrates their potential for predicting structural performance in real-world de-orbiting operations.
Significant strides have been made with the completion of Technology Readiness Level (TRL) 4, an essential step towards translating research into applicable technology. This stage involved the production and laboratory testing and model validation of a 10m2 inflatable sail and a 3m diameter torus.
These advancements by SPACEO set a precedent for future efforts in tackling the clean space problem, offering promising avenues for the efficient, safe de-orbiting of satellites. Space was recently selected by ESA BIC Portugal and will be invested by Portugal Ventures. Further research and development are underway to advance these technologies to deployment in space, paving the way for a cleaner, safer space environment.
Speaker: Joao Pedro Loureiro (SPACEO) -
09:48
Deorbiting Solid Rocket Motor equipped with Thrust Vector Control – a base for propulsion system for controlled re-entry 18m
As one of the most promising end-of-life disposal solutions, solid propulsion for direct deorbitation is under development in Łukasiewicz Research Network – Institute of Aviation and polish partners for ESA. The presented work is split into two activities, one describing a Solid Rocket Motor Engineering Model Development and second concerning a dedicated Thrust Vector Control System concept. Both projects are in an advanced stage and an annual update is provided in this presentation.
The motor’s manufacturing phase status, materials verification and subsystems tests results are described. This allows to present the technological challenges that result from development of high ΔV and low acceleration solid propulsion system. Proposed solutions are to be verified in a full scale Engineering Model on-ground test campaign under preparation.
The thrust vector control system, based on an outside flap system, had been tested in the vacuum chamber. Within the presentation development of test facility, dedicated installation and cold-gas test results will be discussed. Performance of the testing model will be validated, simulations compared to results and development plan will be discussed.
Combined projects have a great potential in terms of providing a simple and reliable solution for direct deorbitation and therefore cleaner space environment. The continuous effort of IoA and its partners prove that those initiatives show great performance during testing on the ground.Speaker: Ms Ewa Majewska (Lukasiewicz Research Network - Institute of Aviation) -
10:06
The Deorbiting Kit: Optimised solution for ESA’s Zero Debris Policy Implementation 18m
The upcoming changes in policy and regulation concerning the European launcher and space industry are going to have a range of consequences on the mission and system design, particularly on dual launches and on ESA missions.
Now that the US Federal Communications Commission (FCC) is adopting new rules to address the growing risk of "space junk" or abandoned satellites, rockets and other debris through a new "5-year-rule" requiring launchers and low-Earth operators to dispose of their in-orbit assets within five years following the completion of missions, it is expected that similar European regulations will follow. In addition to this, ESA is expect to implement a zero net debris policy on all its new missions, which includes the launch elements.
This means that launch adapters need to re-enter within 5 years at best for commercial missions, or be disposed of immediately for ESA missions. This greatly restricts their operational range and imposes in some case unrealistic mission scenarios for the launchers, having to release dual launch adapters under 500km altitude. To solve this issue, the deorbiting kit has been optimised to focus on the immediate disposal service by homogenising its avionics with the D-Orbit standard product lines, focused on achieving the best compromise between reliability and competitiveness while keeping the modularity and scalability aspects that allow it to be used on both launcher elements and satellites.
The kit is a small spacecraft completely independent from the host and is installed on the ground before the launch. Its objective is to carry out the necessary functions to safely perform a controlled re-entry or reduce the altitude of the host at end-of-life or after a failure. By using this, launchers can extend their dual launch capabilities further, and comply to the Zero Debris policy, while satellites can mitigate their end of life reliability and guarantee a safe disposal.
D Orbit aim to contribute to the preservation and remediation of the space environment via several programmes developed with international partners and institutional entities (e.g. ESA, UKSA, ASI, …).Speakers: Diego Garces de Marcilla (D-Orbit UK), Ms Gemma Saura Carretero (D-Orbit UK Ltd), Mr Stefano Antonetti (D-Orbit S.p.A.) -
10:24
Equipment for Satellite End-of life Management and Deorbit 18m
At the end of their active phases satellites have to be removed from their operational orbits and passivated in order to avoid the creation of debris and thus secure the use of these orbits for active and future satellites. As part of the Clean Space / CleanSat activities ArianeGroup extended its portfolio with the following components / technologies that will be presented:
- A SMA (Shape Memory Alloy) valve which is a pyro-free passivation system that allows a passivation of pressurized system without the typical life limitation of a classical pyrovalve. This valve recently celebrated its first operation in space.
- A demisable propellant tank made out an Aluminum alloy: Tanks were identified as a critical element of the re-entry phase because they are usually made of Titanium, which has a very high melting temperature, or include a composite overwrap that is hardly demisable.
- An active deorbit system: In case of lager LEO satellites with a certain causality risk of ground impact an active deorbit over an uninhabited area, with sufficient clearance of landmasses and traffic routes has to be performed. For this operation a high thrust engine is required that applied a high total impulse over a short time period to the spacecraft. As an example the deorbit system of the METOP SG satellite is presented that uses a 400N class Hydrazine thruster that was developed by ArianeGroup as a launcher RACS (Roll and Attitude Control) thruster was subsequently qualified as a deorbit engine.
Speaker: Malte Wurdak (ArianeGroup) -
10:42
Introducing the European Reconfigurable Battery Unplugging System: a Step Towards Sustainable End-of-Life Management for Small-Satellites Constellations 18m
Addressing the pressing need for space debris mitigation, and thanks to ESA ARTES funding, Argotec and ABSL jointly developed a novel End-of-Life management system optimized for small-satellites constellations: the first technology demonstrator has been developed and is known as European Reconfigurable Battery Unplugging System (EReBUS).
The project delved into the development of standardized and widely compatible avionics product specifically designed to meet necessary conditions for the safe end-of-mission passivation of Li-ion battery cells, accordingly to applicable regulations. The ultimate goal is to provide a sustainable and reliable COTS solution for small satellites and constellations, aligning with Space Debris Mitigation requirements and ensuring the safety of future missions, particularly in the realm of small telecom spacecraft.
The project encompasses two primary facets: the electronic passivation system and its compatibility with Commercial Off-The-Shelf (COTS) 18650 Li-ion cells. The electronic passivation system serves as a critical component, seamlessly integrating with the satellite's power management system. Throughout the satellite's operational life, this system operates transparently. When the satellite reaches the end of its mission life, the reprogrammable control logic triggers redundant relay-based switches, isolating the battery from the avionics platform and subsequently managing its safe discharge. Upon the completion of the discharge phase, the battery is completely isolated. A comprehensive passivation test campaign has been conducted, simulating real-world scenarios and demonstrating the battery's passivation behavior under varying environmental conditions, including worst-case scenarios.
On the Li-ion battery front, our project entails the selection and testing of two distinct types of Li-ion cells tailored to suit both Low Earth Orbit (LEO) and Geostationary Orbit (GEO) applications. Over the past year, rigorous accelerated and mission-representative cycling tests have been conducted. For each cell type, four 2s2p-sized modules have been meticulously manufactured, ready for testing under a range of conditions.
Furthermore, our project includes abuse tests to investigate the safety mechanisms of the system when subjected to extreme conditions. These tests encompass scenarios such as over-discharge, over-charge, external short-circuits, and over-temperature conditions.Speaker: Emilio Fazzoletto (argotec)
-
09:30
-
09:30
→
11:00
In-Orbit Servicing & Debris Removal: Circular economy in space
-
09:30
The Space Rider System key-role for a future cleaner and sustainable space environment. 18m
The Space Rider program, part of the space transportation systems of the European Space Agency (ESA), aims to reach a step-further into Europe’s space access capabilities by developing an uncrewed, automated, and reusable spaceplane capable of carrying out multiple missions to and from low Earth orbit (LEO).
The primary scope of this presentation is to focus on possible use of SR as cooperative platform for space assets (structures and satellites) capable of performing a whole set of services such as: orbital life extension, in-orbit placement, de-orbit, and retrieval of experiment results, in space assembling, goods manufacturing, and recycling (contributing in this way to the ESA Zero Debris approach and end-of-life management).
Representative of the above functional areas is the operational interaction of SR with SROC payload, and it foreseen operations scheduled for the maiden flight. The SROC (Space Rider Observer Cube) is an ESA technology demonstration mission based on a CubeSat deployed from Space Rider that will perform inspection, rendezvous and dock with a dedicated retrieval mechanism hosted in the SR cargo bay. SROC will allow the development and in-orbit demonstration of technologies and capabilities for small-satellite proximity operations, with a particular focus on propulsion, GNC, and docking/retrieval mechanisms.
The presentation will also show the ongoing studies, based on recent published ESA guidelines on safe close proximity operations, to evolve the SR vehicle in a prepared and co-operative target for Close Proximity Operations (CPO) with other institutional or commercial orbital vehicles. In particular, system elements will be presented to define strategies and system requirements for the definition of approach and rendez-vous with SR zones and phases, evaluations in terms of concept of operations, capture interfaces, visual markers, and robotics. In this regard, a feasibility study with IOSHEX orbital module for joint operations in space with SR is ongoing, focusing also on the capability to provide a joint system able to perform active debris removal (for example, through use of SR cargo-bay or via placement of de-orbiting kits).
Furthermore, future capabilities for interoperability between SR and other orbital vehicles in terms of power and data exchange, fluids and propellants and robotic operations, payloads re-allocation and exchange from/to the SR cargo bay are investigated.
Early studies of orbital robotics TRL raising are ongoing, including development of in-space complex operations robotic arm concepts to perform interactive operations with SR and enhanced mission servicing and in-orbit operations. These capabilities will be the base for commercial in-orbit servicing and circular economy implementation.Speakers: Mr Antonio Rinlducci (ESA), Fabio Caramelli (ESA) -
09:48
Toward a Circular Space Economy: Overcoming Blockers for Sustainability 18m
In recent years, the escalating space debris problem and the finite nature of our resources have spurred a critical need to reevaluate our approach to satellite missions and operations. To address these challenges and foster a more sustainable space ecosystem, the concept of a circular economy on orbit has emerged. This presentation will delve into the key aspects of this paradigm shift, highlighting the significance of circular design principles and the impact of market dynamics on its successful implementation.
Moving towards a circular space economy is vital to continue using space sustainably. Disposal should be a last resort, but is currently fundamentally the only option due to the way we design spacecraft in the first place. Growbotics, a new space company, has been founded to address some of the blockers hindering a circular space economy. We aim to shed light on the significance of integrating Design for Manufacture, Assembly, Repair (DFMAR) principles into spacecraft design rather than the conventional approach. By prioritizing maintenance, repair, re-use, and recycling in the design phase, we can revolutionize space missions and satellite technology. This talk will explore the potential benefits of circular design, including reduced space debris, minimized resource consumption, and enhanced cost-effectiveness.
Speaker: Ms Portia Bowman (Growbotics Space Ltd) -
10:06
Role of refueling in the global satellite ecosystem. 18m
On-orbit refueling (OOR) is growing into a major building block of the hustling space economy. OOR finds application in GEO, LEO and cis-Lunar orbits.MEV-1 and MEV-2 were ground breaking demonstrations, which have validated the use-case of satellite life extension and garnered interest from the satellite asset owners and operators. Though, different methods of life-extension are possible, refueling offers the most efficient and cost-effective solution. Refueling finds a unique use case in GEO and LEO orbits. Refueling would offer a direct economic benefit for satellite operators in GEO by extending the use of their high CAPEX satellite assets. In the LEO ecosystem however, satellites such as Aelous 1 would benefit greatly from having refueling accessibility. 4 year life extension would have bought in additional cost benefit to society and would have enabled continuous use of their expensive payload. On-orbit servicing and debris removal would become economically viable with the integration of refueling in their operations. A reduction in costs in the region of 70-80% could be foreseen by including refueling as a part of debris removal services. We, at OrbitAID aerospace are developing a solution to enable refueling in LEO and GEO by building a constellation of propellant tanker satellites.
Speakers: Nikhil Balasubramanian (OrbitAID Aerospace Private Limited), Mr Sakthikumar Ramachandran (OrbitAID Aerospace) -
10:25
Guidance, Navigation, and Control of In-Orbit Assembly of Large Antennas – technologies and approach for IOANT 15m
Introduction
IOANT is an on-going activity supported by the European Space Agency aimed at the development of a versatile autonomous GNC system for in-orbit assembly (IOA) of large antennas.
The target is to advance the Technology Readiness Level of several key GNC technologies to 4. To reach this, the activity is structured into two phases:
Phase 1 consists in the definition of a feasible end-to-end in-orbit assembly scenario, including vehicles, mechanisms, and interfaces. A complete GNC solution will be developed and validated using an integrated, coherent, and incremental detailed design, validation, and verification approach.
Phase 2 will advance the GNC solution by designing and performing a series of end-to-end proof of concept tests in a suitable ground facility, using a scaled-down version of the scenario studied in phase 1 and scaling back up the conclusions.
The technologies proposed to be studied can be applied to the assembly of a wide variety of antenna missions, also telescopes and, in a more general sense, mission where the assembly of structures is present.
This presentation discusses: the proposed scenarios – mission, system, and the GNC architecture challenges and proposed concepts; details and justifies the potential architectures and design solutions; and outlines prospective methodologies for prototyping, verification, and validation. The emphasis of this presentation is on the proposed design and not on results or analysis.Motivation and challenge
Enhancements in the communications capacity of future satellites can be achieved by increasing the reflector surface area, producing narrower beams. Current and projected missions rely on foldable or deployable antenna concepts to provide larger reflective surfaces, but these systems are limited by the launcher capabilities both in terms of mass and volume.
A natural solution to the limitations imposed by a single launch is to split the payload into several launches, and then perform assembly operations in orbit. This is becoming possible in part thanks to the latest advances in on-orbit servicing and are the key to unlock the future of communications in space.
In-orbit assembly presents several benefits. It permits the construction of structures that do not fit into a single launcher, even opening the door to structures that could not be created on ground because of the limitations imposed by gravity. It can also increase the longevity and reliability of missions by replacing faulty, damaged, or outdated elements. There are also potential cost-savings, by reducing the mass required for protection and deployment mechanisms, and also reducing ground testing.
However, in-orbit assembly also presents a number of challenges that are currently being studied, both in terms of the system and in terms of the GNC. From the point of view of the system, such a mission requires multiple vehicles to transport and assemble modular segments; it is also expected to have contacts between several elements, which requires the use of manipulators and locking and interlocking mechanisms and introduce disturbances during the assembly process. The main GNC challenges appear in the Control department; the structures will experience large changes in physical properties as the assembly goes on, particularly in the mass-inertia (MCI) properties and the flexible properties. The developed control system needs to take those variations into account and be robust to uncertainties.GNC architecture and design
The proposed mission and system definition step includes the establishment of needs and characteristics: 1) for large orbital antennas, through a survey of and subsequent perimeter definition for the IOA system paired with a representative End-to-End (E2E) scenario for which to tailor a flexible solution; and 2) for the IOA concept, the definition of an IOA solution – mechanisms, interfaces, requirements – that can be applied to the identified scenario and perimeter.
The proposed GNC solution aims to be versatile and adaptable to different scenarios. The Navigation can make use of existing and well proven techniques, such as visual-based navigation systems with fiducial markers. The proposed Guidance approach will be concentrated on the use of on-board constrained convex-optimization for trajectory-planning, including a model predictive control (MPC) framework. The Control problem tackles several objectives, taking into account the importance of controller robustness. Thus, well proven robust control techniques will be considered along with modern techniques, for robust stability, performance and sensitivity. The inherent high non-linearity of a robotic manipulator will also be taken into account in the design of the proposed control scheme for the manipulator operations, and combinations of linear and non-linear control schemes will also be studied in this framework. The proposed control techniques will be combined with System Identification capabilities, to enhance GNC performance. These functions need to be managed autonomously, with no continuous Ground intervention, so a highly autonomous Mode Manager is part of the proposed GNC.Methodology for DDVV
The activity proposes an incremental design based on the chain Model-in-the-Loop (MIL) ➔ Autocoding ➔ Software-in-the-Loop (SIL) ➔ Processor-in-the-Loop (PIL) Testbench ➔ E2E Proof of Concept Testbench.
This approach allows to minimize the risks during the activity. In addition, this chain can provide invaluable support during the Design and Development phases and possibility to test V&V requirements already at early and intermediate design phases, allowing fast design iterations and feedback already at the early design phases and the possibility to correct design problems at those early phases, thus, making more affordable the required effort.
The MIL phase relies on the use of a detailed, multi-physics simulator to captures the main real-world effects and allows to simulate the behaviour of manipulators, contact dynamics, and changes of physical properties. This simulator is used to validate the first version of the developed GNC algorithms in MATLAB/Simulink and associated physical modelling tools.
Through a process of autocoding, these algorithms can be converted into C-code to be embedded for execution in test boards. A SIL and PIL stage ensures that the code generated is equivalent to the original algorithms and that it can be executed into a representative processor.
Finally, a scaled version of the algorithms developed will be used in ground test facilities using scaled-down models, replacing the simulated dynamics by real vehicles and manipulators, whose results can be scaled back and used to derive conclusions on the original, large-scale mission.Speaker: Mr Nuno Paulino (GMV)
-
09:30
-
09:30
→
13:00
Planetary Boundaries Fresk 3h 30m
Want to understand environmental issues to preserve a habitable planet ? Please join for a 3 hours fresk to immerse yourself into the planetary boundaries concept and take action. All the data in the workshop comes from scientific studies published in peer-reviewed journals and you will be driven by a certified animator through collaborative reflection and creativity methods to discover and exchange about this now very important concept.
Please email Aurelie Gallice-Tanguy - aurelie.gallice@ext.esa.int - to register to the Planetary Boundaries Fresk
-
11:00
→
11:30
Refreshment break 30m
-
11:30
→
13:00
End-of-Life Management & Zero Debris: EOL for SmallSats
-
11:30
ADEO-N2 - Dragsail Deorbit Misson - The European Commercial Passive De-Orbit Subsystem Enabling Space Debris Mitigation for CubeSats, SmallSats and Constellations 15m
The ADEO-N subsystem is the smallest of a scalable drag augmentation device family ADEO that uses the residual Earth atmosphere present in Low Earth Orbit (LEO) to passively de-orbit small satellites. For the de-orbit manoeuvre a large surface is deployed which multiplies the drag effective surface of the satellite significantly. Thereby the drag force is increased, causing accelerated decay in orbit altitude. An advantage of a drag augmentation device compared to other de-orbit methods is, that it does not require any active steering and can be designed for passive attitude stabilization thereby making it applicable for non-operational, non-stabilized spacecrafts as well. The ADEO-N subsystem consists of four deployable booms that span a sail in a planar shaped configuration. While the sail is made of an aluminium coated polyimide foil, its coating thickness was chosen such that it provides sufficient protection from the LEO space environment. ADEO-N (ADEO-N2 mission) successfully deployed its 3.6 m² drag sail onboard of D-Orbit’s “Dauntless David” ION Satellite Carrier on the 15th of December 2022. The deployment could be recorded by the onboard camera system and gives an outstanding and great video and photo evidence of the performance of the ADEO-N drag sail module.
Beginning with the sail deployment the onboard telemetry data directly from the ION Satellite Carrier is constantly collected and the results investigated together with our partners ESA, D-Orbit and the company Astos. By means of these data the performance of the ADEO-N dragsail is studied in detail from 500 to 400 km orbital altitude.
First outcome is that the deorbit time is already reduced by the factor of approximately 5-10, which is already a great result considering the satellite mass and dragsail area. Additionally, it can be stated that due to the usage of ADEO a stabilisation effect has set, keeping the rotation at 1.5 deg/sec after about 2 months.
All over the gained data and results give a lot of confidence in the ADEO subsystem and its possible contribution to the Zero Debris Policy and Requirements.Speaker: Mr Daniel Stelzl -
11:45
Assessing impacts of Zero Debris approach on Cubesats: A System Analysis 15m
According to the market predictions, more than 18 thousand small satellites will be launched in orbit in the next 10 years. The advances in satellite system miniaturization, together with the lower costs of manufacturing and testing, make them an attractive option for many applications such as global connectivity and Earth imaging.
Within the ESA Zero Debris approach, more stringent regulations are being defined to address the changes in the space debris environment. As a result of an extensive work of experts from all directorates and subsystems, the new ESA Space Debris Mitigation Standard will be released by the end of this year and become applicable to all new ESA missions.
CubeSats have until now adhered to space debris mitigation measures through natural compliance, being injected in low earth orbits with a natural decay below 25 years. The absence of a propulsion system for disposal manoeuvres or collision avoidance, the use of commercial-off-the-shelf components with low reliability and the limited trackability features makes them one of the most impacted categories by the new ESA Space Debris Mitigation Standard.
In this presentation, the most relevant requirements will be identified, analyzing the challenges and the changes needed in the mission architecture and in the spacecraft design. A trade-off between different disposal strategies to comply with the new requirements will be performed, together with a study of the causes of the most recurrent system failures. Finally, possible solutions and way forward will be presented.Speaker: Lucia Suriani (European Space Agency) -
12:00
SmallSat End-of-Life Workshop 1h
-
11:30
-
11:30
→
13:00
End-of-Life Management & Zero Debris: Methods and tools for Zero Debris and re-entry
-
11:30
Utilization of a risk index to incentivize satellite operators to follow best practices for post mission disposal: the mission index module of the Space Sustainability Rating 18m
Recent long-term simulations of the space environment extrapolating the current launch rate under present space debris mitigation measures suggests that the space environment will become unstable, leading to an exponential increase of the collision rate. The analysis of the extrapolation scenarios defines an acceptable level of risk (i.e., an orbital capacity) that is compatible with a stable evolution of the space environment, this risk level can however only be achieved under strict compliance to existing guidelines and best-practices for every mission. As current guideline compliance assessment approaches comport limitations such as obsolescence of disposal criteria due to an increasing launch traffic or the impossibility to account for the current aggregated level of compliance of space missions, an alternative risk-based approach was formulated under the appellation of “debris index”. A derived version was tested, and implemented under the operation of the Space Sustainability Rating (SSR).
This presentation depicts the process applied by the SSR to use a risk-based approach for quantifying the sustainability level of space missions: the mission index. As a first step in the assessment, the SSR uses parameters provided by satellite operators in order to perform an evaluation. The required parameters for computing an index value are listed, allowing to demonstrate the possibility to define precise and quantified impact assessments based on high level parameters. The accessibility of the required parameter list is discussed. The formulation of the index metric as a risk-based approach is then described, using the collision probability and severity terms at a given epoch. The index value integration process is explained, allowing to demonstrate the usability of the index metric over the entire lifetime of an object, also considering different trajectory evolution scenarios based on the disposal strategy. The presentation especially highlights the importance of implementing a post mission disposal strategy through the comparative analysis of mission disposed and not disposed, at different altitudes and with different disposal success rate values. Finally, the presentation focusses on how a tool such as the SSR can leverage the risk metric defined and incentivize satellite operators to implement more sustainable end-of-life practises.
Speaker: Mr Adrien Saada (Space Sustainability Rating) -
11:48
A cloud-based multi-fidelity solution for space debris assessment 18m
The proliferation of space debris has become an escalating crisis, yearning an urgent need for comprehensive mitigation strategies. One prominent strategy for space debris mitigation involves the deliberate planning of space missions and post-mission disposal ensuring re-entry of spacecrafts into Earth's atmosphere. To ensure effective disposal, re-entry predictions through advanced atmospheric modeling and improved technologies need to be enhanced. In this work, we will present refined models on a spacecraft-oriented tool that allows to run multi-fidelity exo- and endo-atmospheric assessments. This cloud-based solution consists of 3 components:
-
Re•Propagate: This component encompasses the propagation of satellite state and attitude, as well as the propagation of
uncertainties for collision risks and consequences assessment. It
leverages the latest CPU-intrinsic parallelisation capabilities and
high-level multiprocessing capabilities by Ray to ensure optimal
performance. This component is designed to provide a
time-to-solution in the range of milliseconds to be integrated in a
design or operational loop, or to run massive collision risks
assessment over the entire lifetime of a satellite. -
Re•Entry: This component handles the prediction of the re-entry trajectory of satellites, including ablation and
fragmentation and is capable of yielding the number of fragments and
their ground footprint. Once again, it is designed to be embedded in
design and optimisation loops and therefore aims at a
time-to-solution of the order of tens of seconds. -
Re•CFD: This component is a high-fidelity multi-physics computational fluid dynamics simulation tool. It leverages a fast
rasterization algorithm based on video games and distributed memory
parallelization technologies to ensure optimal performance and
reduced time-to-solution. This tool is meant to be used in
pre-design or optimization framework of space vehicles to yield
accurate results of flow around re-entering objects, driving design
choices such as the thickness of a satellite shell to ensure total
demise.
The architecture of the software is designed to be modular and scalable, allowing for the addition of new services and capabilities as requires. The use of cloud-based services and microservices architectures ensures high availbaility and fault tolerance, providing a reliable and efficient system for users.
Overall, this work demonstrates how the platform proposed by Re CAE aims at democratizing access to lifecycle assessment and design-for-demise and at providing the tools to the many to go for the zero debris target as soon as possible !
Speaker: Dr Thibault Bridel-Bertomeu -
-
12:06
Methodologies and Tools to Ensure the Safe and Sustainable Re-entry of Spacecrafts 18m
As the realm of space exploration continues to progress, the need to ensure the secure and sustainable operation of spacecraft during end-of-life re-entry has become increasingly critical. To meet this challenge, aerospace engineers are employing specific methodologies and tools for meticulous analysis. Among these tools, the Debris Risk Assessment and Mitigation Analysis (DRAMA) has emerged as an indispensable resource for assessing risks associated with re-entry and designing spacecraft to comply with the stringent space debris requirements set forth by the European Space Agency (ESA). DRAMA offers a suite of software tools, particularly for end-of-life analysis, the Survival And Risk Analysis (SARA) module, tailored to evaluate a spacecraft's survivability during re-entry into Earth's atmosphere and assess its risk on ground.
Within this framework, DEIMOS Space was responsible for the SESAM (Spacecraft Entry Survival Analysis Module), part of DRAMA’s SARA module, being subcontractor of HTG under an ESA contract. This intricate analysis demands the integration of multiple disciplines, encompassing entry dynamics, aerothermodynamics, thermo-mechanical load evaluation, deformation, and fragmentation processes. Precise modelling of these phenomena, alongside meticulous consideration of object properties such as geometry, mass distribution, and materials, is critical in accurately predicting the risks associated with re-entry. The true essence of achieving remarkable results lies in the users' extensive experience and mastery which elevates DRAMA’s potential.
This paper underscores the significance of adhering to ESA's space debris requirements and also highlights the pivotal role that the DRAMA tool plays in achieving this objective. It presents several noteworthy projects where DRAMA was employed to conduct re-entry and risk analyses, subsequently applying Design for Demise (D4D) techniques to minimize on-ground casualty risk. Moreover, the paper offers a comprehensive overview of the significance of D4D solutions in end-of-life simulations and highlights how the DRAMA tool substantially enhances the safety and sustainability of space exploration. By harnessing the potential of DRAMA and D4D techniques, aerospace engineers can confidently ensure spacecraft's safe operation throughout their lifecycle, thereby reducing environmental impact and safeguarding both human lives and property on the ground.Keywords: re-entry, risk, debris, design for demise.
Speaker: Ms Andreea Burlou (Deimos Space SRL) -
12:24
A Direct Approach for Assessing Demise Capability and Modelling Correlation for DRAMA: A Case Study on Composite Materials 18m
Based on current projections of launch rates, the global threat of space debris reentering Earth's atmosphere, primarily caused by the use of highly durable spacecraft components, necessitates the adoption of multiple complementary mitigation strategies. To address this issue effectively, integrating a dedicated Design for Demise approach during the early stages of spacecraft design enables a gradual and efficient solution.
This presentation outlines a comprehensive research level method for evaluating composite material demise and integrating it into a spacecraft atmospheric reentry risk assessment analysis model. It summarizes the work conducted under a Network Partnering Initiative research project between EPFL and ESA, supported by several industrial partners, to identify innovative composites systems to improve spacecraft overall demisability. Following an extensive evaluation of demise-relevant properties through dedicated test campaign, an experimental-to-model correlation method has been developed specifically tailored for DRAMA’s reentry risk assessmenttool-SARA.Thisapproachshouldfacilitateintegrationofnewlytestedmaterialintothisanalysistool, thereby reducing uncertainties related to casualty risk by performing more realistic reentry simulations.
This multi-collaborative project aims to get a step forward towards the casualty risk mitigation of reentry surviving space debris by novel demisable material implementation.Speaker: Alexandre Looten (EPFL) -
12:42
Extension of ESA’s Survival And Risk Analysis tool with hemisphere and lattice shapes 18m
The very dynamic nature of space flight activity, in combination with a progressive growth in space debris, requires associated space debris mitigation standards and practices to co-evolve. Similarly, there is a strong need for the development of tools to assess and verify compliance with those standards and derived requirements for specific satellite missions. The Debris Mitigation Facility (DMF) includes a set of activities run by the European Space Agency (ESA) to address those needs. The well-known and widely used Meteoroid and Space Debris Terrestrial Environment Reference (MASTER) model and the Debris Risk Analysis and Mitigation Assessment (DRAMA) tool suite are being combined into a single framework following the model-based engineering paradigm to facilitate mission-centric design and execute dedicated workflows tailored towards the verification of space debris mitigation requirements.
This paper will give an overview of some of the new functionalities added to the Survival And Risk Analysis (SARA) module of the Debris Risk Analysis and Mitigation Assessment (DRAMA) tool in the framework of the DMF facility activities. First of all, a new primitive which is a hollow hemisphere has been added. Since no analytical expressions exist for aerothermodynamics, a numerical approach has been taken. A database is created using Computational Fluid Dynamics (CFD) and Direct Simulation Monte-Carlo (DSMC) tools on a discretized set of attitudes, for three flow conditions, and for different stages of the ablation process. The aerodynamic forces and heating rates are normalized so that they can be used during the full trajectory simulation in SARA. Secondly, the overload function has been extended to include the shading effects between over-ridden objects. The overload function can now also be extended by a user-defined database.
This overload functionality has been tested on two shapes for which an association with an existing primitive is difficult. The first shape is a shape-optimized bracket, as shown in figure 1. The second shape is a lattice structure as shown in figure 2. The aerodynamic and aerothermal behaviour is characterized using both CFD and DSMC tools.
Both shapes have void spaces and thin structures with small local radii, which could improve the demise process with respect to traditional non-optimized shapes. This possible by-product of shape optimization with the objective of mass reduction is also discussed in the current paper.Speaker: Martin Spel (R Tech)
-
11:30
-
11:30
→
13:00
In-Orbit Servicing & Debris Removal: Circular economy in space
-
11:30
Manufacturing using waste from space resources for a circular space economy 18m
To allow a zero-waste circular economy in space, technologies to turn heterogeneous metal-rich waste streams into new usable products in situ must be developed. While recycling space debris is one target application, such a system can also be used to process byproducts from space resources utilization. Such byproducts are for example generated by the molten salt electrolysis (MSE) process currently under development to produce oxygen from the lunar regolith. Recent work from ESA and its partners showed that MSE can remove up to 96 wt.% of the oxygen present in regolith simulant, leaving behind solid waste rich in useful metallic elements (e.g. Si, Al, Fe) [1]. The productive use of those metallic byproducts however still has to be demonstrated. A candidate technology to manufacture mechanical parts directly in space from those recovered metals is Metal3D, a system developed by Airbus & ESA to demonstrate metal based additive manufacturing in space [2].
The presented work aims to combine MSE of lunar regolith with the Metal3D technology, to demonstrate a first ever end-to-end process from lunar material to metal alloy parts. This starts with a detailed characterization of the metal-rich byproducts of the MSE process. Post-processing steps are then designed accordingly, to yield specific alloys in sufficient quality and quantity to be used for additive manufacturing. A key consideration is the variability in material composition throughout the process, linked to changes in the regolith feedstock and to the repeatability of the MSE process. Assessing the overall resilience of the proposed solution to such changes is critical in evaluating its potential to process metallic waste from both space resources processing and space debris removal.
We propose to present first characterization results of metals derived from the molten salt electrolysis of regolith simulants, with an evaluation of material variability. The heterogeneous nature of the material will be highlighted, together with the presence of intermetallic phases from the Al-Si-Ca & Al-Si-Fe systems. The alloy feedstocks that can be gained from this (e.g. Aluminium, Silumin) and potential post-processing strategies will be discussed. Finally, the overall vision for an end-to-end process will be presented, highlighting its potential for a zero-waste approach to the use of space resources, and its possible synergies with the recycling of space debris.
References:
[1] Lomax, B.A., Conti, M., Khan, N., Bennett, N.S., Ganin, A.Y., Symes, M.D., 2020. Proving the viability of an electrochemical process for the simultaneous extraction of oxygen and production of metal alloys from lunar regolith. Planetary and Space Science 180, 104748. https://doi.org/10.1016/j.pss.2019.104748
[2] Airbus Defence & Space, 2022. In space manufacturing and assembly. https://www.airbus.com/en/newsroom/news/2022-05-in-space-manufacturing-and-assembly (accessed 12/07/2023).Speaker: Timon Schild (ESRIC - European Space Resources Innovation Centre) -
11:48
Orbiting Sustainability: Crafting a Circular Economy White Paper for Space 1h 12m
-
11:30
-
13:00
→
14:00
Lunch break 1h
-
14:00
→
15:30
End-of-Life Management & Zero Debris: Design for Demise
-
14:00
SpaceCraft Object Risk Evaluation Database (SCORED) 20m
The ESA SCORED activity aims to establish a comprehensive database of approved material and component models for use in destructive re-entry (DRE) and hypervelocity impact (HVI) simulations. As its primary output, the project will deliver a repository of model definitions that can be accessed by both ESA personnel and third-parties using a web-browser and processes to be used when constructing models for inclusion within the database.
The data structure used to describe the various models within the repository is designed to be tool agnostic, and the tools used to construct the database were selected to permit the ongoing expansion and enhancement of the data model with relatively low levels of software engineering effort.
Models have been identified and imported from a number of existing sources in order to provide an initial population. These include material properties, DRE and HVI material models, HVI BLE definitions, HVI component definitions and DRE component definitions sources from ESTIMATE, DRAMA v3.1.0, Ernst Mach Institute (EMI) and Belstead Research Limited.
A destructive test campaign examining the demise behaviour of Ariane Group 1N thrusters has been undertaken within the activity at DLR’s hypersonic wind tunnels in Cologne. The results of this campaign have been used to construct new material models for Haynes 25, and two enhanced DRE models of a small thruster. In addition, new models for the assessment of HVI of electrical harnesses protected by a sandwich panel have been constructed from existing experimental test results by EMI. New DRE models for generic fill/drain valves constructed of titanium, steel and Inconel, and mid-size 10N and large 50N thrusters have also been constructed from product data in public domain.
As well as interactive use over the web, extract tools have been written to generate the material and component files needed by DRAMA, allowing the data stored within the SCORED database to directly drive the models embedded within future versions of ESA’s regulatory assessment tool.
Speaker: James Beck (Belstead Research Ltd) -
14:20
The Topology Optimization approach, a promising technology to adopt as a Design for Demise solution 20m
Due to the multiplication of private actors in the space adventure, France has adopted in 2008 the French Space Operation Act (FSOA), which establish a national regime of authorization and supervision for space activities. Then, the Technical Regulations has clearly addressed the concepts of safety and sustainability of space activities, including the safety of people and property. Within this framework, CNES, the French Space Agency, is in charge of ensuring compliance with the Technical Regulations associated with the FSOA.
To be able to predict the debris survivability of a space vehicle and its associated fragments during their atmospheric re-entry, and assess the prospective risk on the ground, CNES develops its own spacecraft-oriented tool named PAMPERO [1]. One of its objectives is to provide a fine expertise of the whole fragmentation process.
To ensure the safety use of space, PAMPERO also enables the analysis of new solutions in the design of vehicles and their components, allowing reducing as much as possible the potential risks on the ground. In this context, in [2, 3] PAMPERO highlights that the most influencing parameters on the spacecraft's demise are the predictions of the heat load and the fragmentation process. Following these issues, in a recent paper [4], PAMPERO analyses the impact of different technologies applied to the re-entry of TARANIS satellite.
In order to extend this previous work, a promising technology that can be seen as a Design for Demise solution is introduced here, this is the topology optimization approach. This technology, coupled to additive manufacturing, is usually adopted for reducing the mass, with equivalent mechanical or thermal performances [5, 6].
The goal of this presentation is to highlight how the resulting freeform of this approach, can allow better demisability compared to classical shape.
To deal with this goal, atmospheric re-entry simulations are performed on a specific case study. The improvement of design, in terms of ground risk, is assessed using numerical simulations performed with Pampero.
[1] Van Hauwaert, P, et Al., Pampero v3, a spacecraft-oriented reentry analysis code, 2nd International Conference on Flight Vehicles, Aerothermodynamics and Re-entry Missions & Engineering (FAR), 19 - 23 June 2022. Heilbronn, Germany.
[2] J. Dumon & al. REBUILD AND DATA EXPLOITATION OF THE AVUM RE-ENTRY EVENT FOR BREAK-UP MODEL DEVELOPMENT. The 2nd International Conference on Flight Vehicles, Aerothermodynamics and Re-entry Missions Engineering (FAR), 19-23 June 2022, Heilbronn, Germany
[3] M.Spel & al. DEMISABILITY STUDY OF INDUSTRIAL TEST CASES WITH THE SPACECRAFT-ORIENTED CODE PAMPERO, 8th European Conference on Space Debris ESA/ESOC, Darmstadt, Germany ( Virtual Conference), 20 - 23 April 2021
[4] H. Pasquier & al. DESIGN FOR DEMISE AND DESIGN FOR CONTAINMENT TECHNOLOGIES FOR THE REDUCTION OF THE DEBRIS CASUALTY AREA: IMPLEMENTATION ON A MICROSATELLITE AND GAIN EVALUATION WITH DEBRISK AND PAMPERO SOFTWARES, 17th ECSSMET, Toulouse, France 28-30 March 2023.
[5] SJI Walker, F Romei, J Becedas Rodríguez, F Dalla Vedova, J Beck. An Overview of the Application of 3D Printed Spacecraft Structures within the ReDSHIFT Project. INTERNATIONAL ASTRONAUTICAL CONGRESS: IAC PROCEEDINGS, 1-10
[6] Meng, L.; Zhang, W.; Quan, D.; Shi, G.; Tang, L.; Hou, Y.; Breitkopf, P.; Zhu, J.; Gao, T. From Topology Optimization Design to Additive Manufacturing: Today’s Success and Tomorrow’s Roadmap. Arch. Comput. Methods Eng. 2020, 27, 805–830.
Speaker: Dr Stephane Galera (CNES) -
14:40
A Multiscale Heating Correction Code for Space Debris Demise Simulations 20m
When simulating space debris during atmospheric entry, the thermal environment is often modelled using heat flux correlations, with the resultant thermal loads being averaged over simplified representations of spacecraft (complex compound shapes composed of geometric primitives). Although this procedure is computationally efficient, the application of averaged heat fluxes to such compound shapes can lead to what is known as the multiscale heating problem, where an inappropriate length scale is used to assess the magnitude of a given heat flux. This can potentially result in significant inaccuracies being introduced in debris temperature history, demise altitude, and ground casualty risk projections.
CRITIC, a new tool that wraps the SESAM code included in ESA's DRAMA debris simulation suite, has been developed in order to demonstrate a solution to this issue. CRITIC is designed to address the multiscale heating problem by intervening in a standard SESAM analysis at breakup and demise events in order to calculate thermal scaling factors based upon the overall size of a compound shape. These factors are then generated for and applied to any "new" compound shapes that result from breakup events, and the SESAM analysis is continued until the next such event.
CRITIC is found to perform well when run on simplified test cases, achieving excellent agreement in thermal history between compound shapes and geometrically similar single-component shapes. A significant difference in ground risk assessment is also found between cases run with and without CRITIC scaling. Although the work performed here provides a good proof of concept, significant effort would still be required to generally apply this methodology, both in terms of gathering the required data from CFD and experiments as well as in determination of appropriate lengthscales for more complex shapes.
Speakers: James Merrifield (Fluid Gravity Engineering), Nathan Donaldson (Fluid Gravity Engineering Ltd) -
15:00
On Demisable Fiber Reinforced Plastic Composites 20m
Fiber reinforced plastics (FRPs) have previously been considered demisable because of their organic nature and the fact that they would be able to burn at ground conditions. However, entry flight simulations revealed that this assumption was overly optimistic. Instead of quickly burning away, fiber reinforced composites typically behave similar to the materials used in ablative thermal protection systems. This means that the composites go through a thermal decomposition with production of char residue, which keeps the fibers attached and the part solid. Thereby, the thermal decomposition of the matrix absorbs huge amounts of heat and creates a protective cold gas layer on the surface of the part. This results in FRPs being a problematic material category in respect of the ground-risk and the design of demisable hardware.
The majority of the plasma wind tunnel tests conducted on FRPs in the past showed a high demise resistance, but a small number of tests demonstrated a more favorable behavior that resulted in an increased demise rate. The COMP2DEM project aims at identifying the parameters that determine the behavior and deriving design rules that allow formulation of composites with increased demisability.The project has now come to an end. In this talk, we present the project and its results and discuss the different types of demise behavior observed in the simulations and what led to that behavior. We conclude with a set of preliminary best-practices and an outlook to suggested future developments.
Speaker: Thorn Schleutker (German Aerospace Center DLR) -
15:20
Challenges in the development for a demisable Xenon Tank 10m
With the number of LEO satellites also increases the need for a demisable tanks in case of an uncontrolled reentry. Simulations have shown that it is not enough to only melt the aluminum liner during the reentry if market relevant tank sizes of around 40L and 150bar operating pressure are considered. The composite of the vessel must degrade to a high extent so that an impact to ground does not harm people and their belongings. The challenges hereby are the decomposition of the matrix and ablation of the carbon fibers, especially in an oxygen poor surrounding. Within the ESA ARTES program, PEAK has worked on the development and testing of such systems. This presentation gives a short overview of the development path and challenges, including historical setbacks as well as planned work on the path to a demisable Type 3 COPV.
Speaker: Philipp Heher (Peak Technology)
-
14:00
-
14:00
→
15:30
End-of-Life Management & Zero Debris: Design for Removal
-
14:00
Preparing for a Cleaner Space: Introduction to ESA's Design for Removal 10mSpeaker: Estefania Padilla (ESA)
-
14:10
Markers Supporting Navigation Development and Qualification 20m
ADMATIS LTD. joined to ESA Clean Space initiative in 2018 in PEMSUN project to perform feasibility study of passive navigation aids capable to function in VNIR and TIR spectra. Based on the first promising results continuation projects included the full development and manufacturing of Markers Supporting Navigation (MSN project) in 50 to 5m and 5 to 0m ranges, respectively. Markers are developed to withstand long term (>12 years) LEO environment. The objective is to equip satellites with passive navigation aids that are still detectable long after the satellite itself is non- operational. Detectability is ensured using combinations of various thermo-optical coatings to maximise contrast in VNIR and TIR against representative backgrounds. Spatial geometry also helps visual navigation processes. The evaluation of detectability is tested using VNIR and TIR cameras under controlled lab conditions in open-air.
Two types of markers have been developed; the “2D Marker” aimed to support navigation from 50m to 5m, while the “3D Marker” is aimed to support navigation from 5m down to capture. Coating of the markers have been qualified to long term (>12 years) Copernicus LEO environment in the MSN and MSN-FD projects.
2D markers are equipped with an ADM-developed laser retroreflector. These LRRs are typically used to perform orbit determination by laser ranging from ground. Using these LRRs it is possible to determine the spin-rate of tumbling objects of defunct (client) satellites to prepare the capture by the servicer. During the qualification activities performed in the MSN-FD project, these LRRs have also been tested long term (>12 years) Copernicus LEO environment to reach TRL6, while the markers as equipment have been tested to reach TRL7 in the MSN-Q project. Results will be shown during the event.Speaker: Laszlo Szegedi (Admatis Ltd., Miskolc, Hungary) -
14:30
MICE (Mechanical Interface for Capture at End-of-Life): Qualification results and future use 20m
MICE (Mechanical Interface for Capture at End-of-Life) is a single-part passive interface designed for enabling the capture and de-orbiting of satellites at their End-of-Life or in premature malfunction by a Servicing Spacecraft in case the satellites cannot be deorbited by themselves.
MICE has been developed under several ESA contracts by a consortium led by GMV, in charge of system-level studies and requirement definition, and supported by AVS, in charge of mechanical design, analysis, manufacturing and environmental verification. MICE is part of the Clean Space effort in the area of D4R (Design for Removal) and it has been developed specifically to be integrated into upcoming Copernicus Sentinel Expansion missions guaranteeing sustainability at their End-of-Life.
MICE development has included a Breadboard Model (BM) to raise to TRL 4 (2019), an Engineering Model (EM) to raise to TRL 6 (2021) and a Qualification Model (QM) to raise to TRL 7 (2023). QM is at the end of the qualification campaign right now. It has passed through a performance test, a mechanical vibration test, a thermo-optical properties test, and a thermal-vacuum test. The last test to perform is the bonding test, expected to be finished by end of July 2023. Qualification environment was defined to envelope the six Copernicus Sentinel Expansions missions’ requirements so with only one qualification campaign MICE is ready for all of them. The MICE qualification campaign is planned to close in September 2023 after a Qualification Review.
Servicing spacecrafts can capture MICE-integrated satellites by means of a robotic gripper. The same consortium developing MICE is also developing CAT, a complete Capture Bay for Servicers, under an ESA contract. CAT operates in two steps: first, a controlled approach to perform initial contact and capture by grasping MICE with a gripper, and second, a rigidization of the contact between Servicer and Target spacecrafts by means of three clamping mechanisms placed around the Launch Adapter Ring (LAR). The robotic gripper proposed in CAT design has been developed in parallel to MICE and will be used to verify functionality and performance in End-to-End tests at the Platform-art facility at GMV.
Current MICE design material is stainless steel 15-5PH (H1025). This material was selected to make MICE compatible with significant deorbiting loads in uncontrolled scenarios with potential extreme temperatures (>150ºC). With a wide range of environment and load compatibility, MICE has the potential to become a standard for mechanical capture of cooperative and uncooperative spacecrafts, not only for removal but also for servicing. Due to its small installation impact and its excellent and extensively verified performance, a simple mechanism like this one could make a big impact on the fight against debris generation.
Speaker: Carmen Camañes (AVS) -
14:50
A PASSIVE DEVICE FOR POSTMORTEM DETUMBLING / ANTITUMBLING OF LEO SATELLITES, TO FACILITATE ACTIVE REMOVAL 20m
To limit the risk of cascading collisions, we will need active debris removal missions to retrieve satellites that die before they can be deorbited. It is well understood that sudden fatal failures can cause a dead satellite to tumble uncontrollably, but even properly decommissioned satellites may start tumbling spontaneously from solar radiation pressure torque buildup, making capture extremely challenging in both cases. The availability of a detumbling/antitumbling device ensuring passive stabilization of dead satellites could greatly reduce the risk and cost of debris removal missions.
We describe a passive magnetic damping device attached to a satellite's structure, which dissipates the kinetic energy and angular momentum thanks to eddy currents resulting from differential angular rates between the satellite and the Earth’s magnetic field, eventually stopping the tumbling motion.
Detailed sizing and simulation activities have demonstrated that one such small and lightweight device is capable of detumbling a medium-to-large satellite within just a few weeks, while also preventing self-tumbling. The presentation reviews the current development status, from initial sizing to performance simulations and vibration tests of two prototypes. These steps pave the way for the final development stages of a universally available detumbling function that can be a game-changer for active debris removal.
Speakers: Maxime SENES, Mr Kristen Lagadec, Mr Frédéric Payot -
15:10
The puzzling dynamic evolution of defunct satellites: a challenge for Active Debris Removal missions 20m
ESA under the umbrella of the Clean Space Initiative has promoted complementary activities in view of Active Debris Removal (ADR) missions.
One of the main challenges driving the complexity of the rendezvous and capture of a debris is its rotational state. In-orbit observations of defunct satellites do not show an ideal Gravity Gradient capture, but instead large angular rates letting the target in a permanent or quasi-permanent spinning state. The prediction and estimation of the angular rates of defunct satellites to be captured is therefore crucial for the design of the chaser and to confirm the feasibility of these critical operations.
This paper shares what we have been learning over the past years about the dynamic evolution of defunct satellites in Low Earth Orbit, how complex it is and how to do this assessment properly.
Such satellite is assumed to have been prepared for Design for Removal (D4R) during its development phase and to be equipped in particular with a Magnetic Detumbling System (e.g. automatic short circuiting of Magnetic Torquers), 2D Navigation Aids including features to support ground-tracking and attitude reconstruction, 3D Navigation Aids to support precise pose and attitude determination for the last phase of the capture and a Mechanical Capture Interface to allow its capture with a robotic gripper.
Due to the complexity of the YORP effect created by Solar Radiation pressure, together with the low authority of existing Passive Magnetic Damping Systems (short-circuited Magnetic Torquers and Eddy currents), the proposed verification process to assess the long-term dynamic evolution mainly relies on extensive simulation campaigns performed on a dedicated High-Fidelity simulator.
Although simulations tackle all dynamic configurations including tumbling at low angular rates, the spinning configuration deserves special understanding. Analytical models of spin-averaged and orbit-averaged torques developed by ESA and ABSpaceConsulting are shared, covering Gravity Gradient, Solar Radiation Pressure (YORP effect), S/C Residual Magnetic Dipole, atmospheric drag, Eddy currents and Magnetic Detumbling Systems. They are very helpful to interpret the complex behaviour shown by the simulations, identify S/C driving parameters and representative initial conditions, and sweep parameters accordingly.
Guidelines related to the set-up of a representative High-Fidelity simulator and to the simulation campaigns are proposed, to avoid artefacts and wrong conclusions, and with a suggested list of S/C and orbit driving parameters.
Representative simulations with their interpretation are presented, covering a variety of initial conditions for LEO missions, highlighting the impact of the sun elevation evolution and the criticality of Solar Arrays orientation with respect to the principal axes of inertia.
The post-launch attitude reconstruction to be performed in-orbit to confirm the feasibility of a planned ADR mission is another important verification step and the use of navigation aids developed by ESA is explained.
Preliminary conclusions and recommendations are finally proposed.Speaker: Alain BENOIT (ABSpaceConsulting)
-
14:00
-
15:30
→
16:00
Refreshment break 30m
-
16:00
→
17:30
End-of-Life Management & Zero Debris: Design for Demise
-
16:00
Generic separation technologies to improve demise behaviour 18m
Design for Demise has become an increasingly important subject over the last years. Primarily to achieve compliant uncontrolled re-entries but with the updated regulations potentially also for future controlled re-entries.
Several recent projects have shown that one important method to improve the demise behaviour can be an early fragmentation of the spacecraft structure or an active separation of units from the structure. By separating/opening items, inner parts can be exposed earlier to the aerothermal heat fluxes increasing the overall demised mass.
This presentation will show the current status of the Airbus development of generic separation technologies derived from the successful implementation of separation brackets for the Sentinel 1 radar antenna.
Besides the current maturity and development roadmap, an insight into the expected performance, the design, modelling and validation methods for implementation and the flexible inclusion in an overall satellite development and AIT flow will be presented.
Next to the advantages of the technology, potential limitations and compatibility with other Design for Demise/Containment strategies will also be elaborated.Speaker: Martin Weihreter (Airbus) -
16:18
Demise Testing and Modelling of Glass Materials and Demisable Bipod Concepts 18m
The demisability of optical payloads is challenging due to the high performance materials used. Two high ground risk aspects, glass materials used in lenses and mirrors, and titanium bipods, were tested and carefully modelled in this work.
A number of previous works have attempted to assess the demisability of glass materials, in particular Zerodur, although little material demise testing has been performed. In this work, a set of material demisability tests were carried out in conjunction with an assessment of the glass viscosity-temperature curve. The tests demonstrate that, although material deformation can be observed earlier, material removal is driven by the viscosity of the material, and not by a melting temperature. The rate of material removal can be correlated directly with the viscosity, and a model has been derived which successfully rebuilds the material loss in a set of tests performed in the DLR L2K high enthalpy wind tunnel. This model, implemented in the SAMj destructive re-entry simulation tool, demonstrates that Zerodur is significantly less demisable than estimated by current models.
A titanium bipod designed to support an 8kg mirror was also tested in the L2K facility, and the demise of the bipod was clearly demonstrated to be linked to the length scales of the different parts of the bipod. The cutouts which enable the flexure of the bipod melted first, promoting a fragmentation of the bipod into smaller parts, and the small length scale of the legs and foot resulted in the demisability being relatively good. Using 3D printing, bipods with a set of demise enhancing features were produced. A hollow version of the bipod, and then a bipod with a set of holes allowing the flow to pass through were tested. Both models satisfied the load and flexure requirements of the original bipod design. The hollow bipod was seen to improve the demisability slightly due to the lower mass of the object. The design with holes, however, demonstrated a substantial improvement in the demisability of the bipod, consistent with halving the length scale of the object. This suggests that flow holes are an effective design-for-demise technique, and it is strongly recommended that more research is put into this concept.Speaker: James Beck (Belstead Research Ltd) -
16:36
Influence of the Selected Alloy and the Dynamic Loads on the Demisability of Aluminium 18m
After more than two decades years of experimental and numerical simulation of the demise of materials and components during the entry flight, our knowledge on the phenomena involved in this destructive process and correct modelling thereof is still quite limited. There are many unknowns regarding the behaviour of the various materials and material categories and huge uncertainties. It is therefore necessary to make educated guesses in the modelling. The chosen simplifications and estimates can have an impact on the results of the numerical predictions and thus influence the results of the ground risk predictions and in consequence the design-for-demise measures and effort taken to make the risk compliant with the requirements.
We aim to contribute to the design-for-demise community by closing some of the gaps in the knowledge and understanding. These are the questions of whether alloys of one base metal can be considered to behave the same and the threshold that should be used for defining a metal to be demised.In the frame of the ESA projects CHARDEM and DEPT, four aluminium alloys of dissimilar elemental composition underwent not only destructive entry flight testing in the arc heated facilities of DLR, but also vast thermophysical characterization. We use this data to show to which degree the alloy selection influences the demisability and demise behaviour and check which influence the selection of the alloy has on the behaviour.
It has been known for some time that the selection of a criterion for when a material can be considered demised in the numerical simulations is not easy. Earlier experimental simulations had shown diverse behaviour for the various metals and alloys and some materials differed quite a bit from the typical assumption that a material demises once it reaches melting temperatures. In the DEPT project, we investigated an aluminium alloy at different conditions by static and dynamic testing. In combination with older data, e.g. from the EU project ReDSHIFT, the results show an interesting correlation between mechanical loads and demise temperature.
In this talk, we present and discuss the results of the experimental investigations. We assess the impact of the two discussed simplifications on the demisability of materials and what this means for numerical simulations of the destructive entry flight. Best practices and recommendations for the DIVE guidelines are derived and presented.
Speaker: Thorn Schleutker (German Aerospace Center DLR) -
16:54
DRACO mission phases A-B1 outcomes and way forward 18m
The work presents the achievements of DRACO (Destructive Re-entry Assessment Container Object) during phases A-B1. This ESA mission aims to enhance the understanding of the multi-disciplinary physics governing the destructive re-entry of a LEO-representative small satellite.
Several trade-offs have been conducted during these phases, including mission and system architecture, mission analysis, sensors selection and placement, identification of objects of interest and their locations, capsule external interfaces and separation mechanism, thermal protection system design, materials selection, and definition of operations with a focus on the separation from the launcher and capsule activation. All these aspects were supported by re-entry simulations run in DRAMA and PAMPERO to assess the impact of design modifications on the satellite's demisability.
A glimpse on the outcomes will be presented, highlighting the relevant results that are currently driving the subsequent phases of the mission.Speaker: Mr Saul Campo (Elecnor Deimos) -
17:12
Demisability of Platform Optics and Electronics 18m
Controlling the levels of space debris has become a greater focus of the industry given the volume of spacecraft expected to be launched in the foreseeable future. The re-entry of spacecraft into the Earth’s atmosphere can contain fragments which are able to survive the loads and heat experienced during re-entry into the atmosphere. These same fragments will also have a probability to cause harm or damage to humans and the environment.
There have been numerous studies and projects that have been performed in order to gain better understanding of re-entry processes and to assure that more spacecraft fragments demise during re-entry manoeuvres. Yet, substantial knowledge gaps on the demise and fragmentation processes of various components remain to be closed.
The objective of this D4D activity being discussed is to enhance the knowledge on the demise of optical and electronic equipment of satellite platforms in order to establish validated re-entry models. For this purposes equipment potentially causing re-entry risks, as star trackers, battery modules, and electronic equipment have been analysed and investigated in on-ground demise tests in a representative environment.
Given the casualty risk is driven by the number and size of re-entering fragments, ascertaining the demise behaviour of the aforementioned components will aid in improving the modelling and simulation of spacecraft component demise behaviour, and further industries understanding and capabilities in more sustainable spacecraft design.Speaker: Bradley Lockett (OHB)
-
16:00
-
16:00
→
16:20
End-of-Life Management & Zero Debris: Design for Removal
-
16:00
CAT: A Satellite Capture Payload Bay for ADR Servicing 20m
Abstract
In the latest years ESA has taken a proactive role in the area of Active Debris Removal (ADR) by preparing the new generation of Earth Observation satellites for a potential removal as part of their End-of-Life management. In this respect, the six Copernicus Sentinel Expansion Missions have adopted the Design for Removal Interface Requirements Document produced by ESA and are taking the required actions to implement it. It is encouraged that in the future, most missions should meet D4R guidelines to enable its uncooperative capture and deorbiting at End of Life. Client-side prescriptions are designed to work in close cooperation with active capture systems at servicing satellites.
In a previous activity, the consortium has designed a passive capture interface (MICE) to be placed at client-side, which is currently undergoing qualification. Now we are reporting results from development and maturation of the technologies for capture and removal at the servicer satellite side. This includes the development of a compatible end-effector, clamping devices, optical navigation, avionics and control required to perform all the associated operations. These elements are being consolidated and integrated within a single/unified system: CAT – the Return Capture Payload Bay, which is intended to become the key payload onboard future ADR servicer satellites. Validation of the complete capture system will be described. It comprises integrated operation of a representative servicer bay breadboard and a client LAR face developed for this purpose.
This presentation will outline design, development, manufacturing integration and validation of capture payload breadboard up to TRL4 with a clear focus on a straightforward path to fly. It will cover CAT navigation system capabilities and capture process control aspects. CAT functions are designed to work in close coordination with the servicer GNC to perform the last approach navigation (from 5m up to capture), capture, stabilization and securing of the stack for de-orbiting the failed/uncontrolled S/C.
Preliminary CAT breadboard results will be described together with an overview of its principal units: the end-effector, compatible with the MICE standard and able to auto-align both sides in the presence of navigation errors; a robotic actuator designed to reduce misalignments at capture, link both vehicles in a compliant way and relocate the servicer with respect to the client; LAR clamping devices compatible with deorbiting loads and the avionics and navigation equipment, including lighting equipment and a visual servoing system with embedded machine vision algorithms.
Keywords: capture, payload, robotics, ADR, optical navigation, clamping
Speakers: Fernando Gandia (GMV), Manuel Prieto (GMV)
-
16:00
-
16:20
→
17:30
End-of-Life Management & Zero Debris: Workshop: Standardized removal interface
-
16:20
Standardized Removal Interface Workshop 1h 10m
-
16:20
-
17:30
→
18:30
Clean space Industry Days Wrap-up: Clean Space Industry days Wrap-Up
-
09:30
→
11:00
