Conveners
Managing the end of life: Current challenges and future solutions in LEO and GEO
- There are no conveners in this block
Managing the end of life: ESA Space Debris Mitigation and Re-entry Safety Framework – Status and Novelties
- There are no conveners in this block
Managing the end of life: Passivation for managing the spacecraft's end-of-life
- There are no conveners in this block
Managing the end of life: Design for Demise: Models
- There are no conveners in this block
Managing the end of life: Design for Demise: Models
- There are no conveners in this block
Managing the end of life: Designing Demisable Spacecrafts
- There are no conveners in this block
Managing the end of life: Sustainability rating
- There are no conveners in this block
Managing the end of life: Passive deorbit devices
- Tiziana Cardone (ESA)
Managing the end of life: Controlled reentry
- There are no conveners in this block
Description
Developing technologies to prevent the creation of future debris, including Design for removal
The status and novelties of the ESA Space Debris Mitigation and Re-entry Safety framework is shown in this presentation.
The ESA policy on Space Debris Mitigation makes applicable the requirements in the standard ECSS-U-AS-10C, Rev. 1 / ISO 24113:2019.
The latest update of the ECSS/ISO Space Debris Mitigation requirements was published in 2019. Furthermore, the work on the next updates of...
In the frame of the French Space Operation Act (LOS) signed on 3rd June 2008, CNES and R.Tech are particularly interested by re-entries of space debris. CNES is indeed in charge of ensuring the right application of the law, for every mission launched or operated from the French territory. To predict the debris survivability during their re-entries and assess the prospective risk on ground, the...
During re-entry into the Earth's atmosphere a spacecraft encounters strong thermal and mechanical loads. The thermal loads result in heating and eventually thermal failure (e.g. melting, combustion) of some of the spacecraft parts. The mechanical loads can result in bending and eventually breaking of parts. Both effects are considered in state-of-the-art re-entry simulation tools separately,...
The on-ground casualty risk of any re-entry (controlled or uncontrolled) shall be below 1 in 10,000. One way of reducing the risk for the system is to focus on the equipment on-board.
For equipment which does not demise, the casualty risk can be reduced by design-for-demise (D4D), this is achieved by reducing the number, size, and kinetic energy of the surviving fragments associated with...
The shift within Europe to destructive re-entry models which are grounded in test data has provided significant steps in the understanding of key phenomena, and capturing of critical effects such as length-scale dependent heating and fragmentation through joint failure. This has led to more careful modelling, both of critical parts within a wider range of components, and of fragmentation...
Usually heat flux measurements in ground test facilities as well as simulations in the hypersonic flow regime are performed at static conditions with non-moving objects. But objects performing an uncontrolled re-entry are quite likely to rotate and/or tumble. This is true for meteorites, satellites and empty stages of launch vehicles.
Previous experiments were conducted with free flying...
There are many limitations in ground testing in the laboratory, that prohibit fully realistic simulation of the destructive entry-flight. Some of these limitations could be overcome by technical solutions, others are determined by the physics (e.g. gravitational forces acting on the test hardware). The impact of the limitations varies and have been discussed in the community for years. One of...
Fluid Gravity Engineering FGE have been active in destructive entry modelling for ground safety and planetary protection applications for well over a decade. Modelling approaches have evolved significantly during the past eight years and particular attention has been focused on: (i) methods to verify component level demise and (ii) methods to assist in Design for Demise (D4D) assessment....
Design-for-demise looks at technical solutions to reduce the casualty risk on ground of re-entering satellites and their components by promoting demise during atmospheric re-entry. Earlier studies have shown that the early release of the satellite structure will also help to improve the overall demise of the satellite. A broad range of current joining samples were tested under a range of...
To ensure that near-Earth space remains commercially and scientifically viable in the future, it is of great importance to reduce the amount of space debris in orbit and minimise the generation of new debris. Major space actors such as ESA and NASA have issued guidelines for reducing space debris. An important part of this is the removal of discarded rocket stages and satellites from orbit....
In light of the increasing importance of Design for Demise (D4D), the Demisable SADM activity was initiated to better understand the breakup phenomenology of Solar Array Drive Mechanisms, as these components are recurrent units on satellites.
The first phase of the activity made use of the high fidelity reentry simulator SCARAB to recreate a detailed model of KARMA-4 TG, a commercial...
The purpose of the study is to identify and validate containment techniques that can be broadly applied to spacecraft critical elements to reduce the casualty area of the spacecraft re-entry event. In this activity, the methods to contain critical elements shall be investigated, assessed, traded-off and prototypes of the containment method(s) will be developed and tested.
Demisable Joint is a technical solution to allow an early break up of satellites structure and payload separation in order to reduce the risk posed by re-entering satellites, improving their demise. The ESA study “ITI – Innovation Triangle Initiative - Demisable Joint” aims at identifying the environment conditions, an then design, manufacturing and testing dedicated breadboards to verify this...
As the challenge of orbital debris is set to grow, the Space Sustainability Rating (SSR) was conceived to provide a new, innovative way of addressing the orbital challenge by encouraging responsible behaviour in space through increasing the transparency of organisations’ debris mitigation efforts.
The SSR will provide a score representing a mission’s sustainability as it relates to...
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...
The Deorbit Kit is intended as a modular end-of-life platform for a automated, mission budget friendly controlled re-entry of satellites. The system is planned to be highly scalable for multiple missions in the future. The targets for the Deorbit Kit will be Low Earth Orbit (LEO) spacecraft in the size range of 50 to 300 kg mass.
The system consists of electric power system, sensor...
This presentation concerns an overview of development of propulsion system consisting of Solid Rocket Motor and Thrust Vector Control designed at the Lukasiewicz Research Network – Institute of Aviation in Warsaw, Poland (L-IoA).
The protection of Earth’s orbit environment has become one of the main interest at the L-IoA. After successful pre-qualification of a solid propellant, which shall...
In the wider context of Active Debris Removal (ADR) missions, the de-orbiting kit’s plug-in solution is special in its potential to become a self sustaining product. While the aim of the initial activity addressed within Cleanspace is to deorbit a passive launch adaptor (such as a VESPA upper part) as an in-orbit demonstration, the ultimate goal is to develop a modular and scalable concept...
Thermal one-way effect Shape Memory Alloy (SMA) actuators are a lightweight, robust and cost effective alternative to conventional actuators like pyrotechnics or electromagnetic actuators. Parts machined from SMA could be pseudo-plastically deformed in cold state, later they return to their previously machined shape by simply heating them up to their phase transformation temperature. During...
We will present how the concept of passivation of the spacecraft power subsystem has evolved from the early studies to recent proposals.
OHB’s key challenges for LEO End of Life are in the selection of the best spacecraft design options available to fulfil the requirements of the missions at stake. The primary decision to be reached is whether the re-entry requirements can be met through controlled or uncontrolled re-entry. For some missions, the selection is clear, however, between these lie a trade-off space whereby either...
TAS Belgium will present the trade-off results & the component Technological tests results done under the GSTP Electrical Passivation - PCDU upgrade for power passivation in order to cover a Disposal phase (after isolation activation): at least 25 years
- Trade-off
- Tested components and associated technological tests vehicles
- Tests description
- Thermal cycling results
- Power...
