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It is known from the Apollo Era that planetary dust poses many challenges for future space exploration. Lunar dust was shown to be one of the complex challenges to overcome for missions on the moons surface due to its adherance to materials and fine partciulate nature. Dust mitigation strategies and technologies are vital as we continue to persue further plans to explore planets outside of our own. Ongoing research into the effects of lunar dust contamination is widespread across the space industry and the development of new mitigation technologies will shape future surface exploration missions.
This 2 day workshop aims to continue knowledge sharing in the planetary dust community across Europe and provide a platform for scientists, engineers and experts to share their knowledge and research regarding planetary dust, with an emphasis on lunar dust. The workshop will cover planetary dust properties, contamination effects, and mitigation strategies as well as defining gaps in current research.
The workshop will consist of keynote lectures, short presentations and poster sessions, plus the opportunity for networking and discussion.
This paper seeks to review the understanding of the forces acting on dust particles, how these affect their behaviour, how we can measure and quantify these, and what the consequences are especially if we are trying to run real-world simulations in different gravity and fluid fields or absence thereof (e.g. Earth atmosphere, Earth vacuum, Lunar exosphere).
Specifically, forces due to gravity, electrostatics, fluid drag and van der Waals effects will be addressed. The paper will begin with a review of the origins of these forces, their relative strength and range of action. Methods for measuring them and quantifying them will be covered, including some recent work on a novel method known as the “Mechanical Surface Energy Test”.
The issue of how these forces are likely to affect the behaviour of dust in low and micro-gravity environments will then be addressed, including in the development of critical equipment required to establish a functioning lunar economy, and the testing of this equipment in Earth-bound laboratories. Some early work to illustrate this challenge will also be demonstrated.
Lunar dust poses a critical challenge for surface missions due to its abrasiveness, electrostatic adherence and fine particulate nature. SolSys Mining will contribute to ESA’s Planetary Dust Contamination Workshop 2025 by presenting LuNOR, a European lunar simulant—available in both mare and highlands variants, with dedicated dust simulant formulations forthcoming in 2026. Produced from raw Nordic rock sources via an industrial, multi-stage process that promotes consistency, authentic particle shapes and lithological complexity, LuNOR combines fidelity with sustainability through local sourcing and optimized production. Proof-of-concept batches have already been developed under Norwegian Space Agency funding, and SolSys is currently developing methods for producing glass and composite particles for higher fidelity variants.
We hope our presentation will foster an open discussion on the topic of simulants and LuNOR, which will in turn help define the most critical simulant fidelity parameters for contamination studies, such as particle shape distributions, compositional proxies and glass content, so that our next development phases deliver a tailored European platform for dust characterization, contamination monitoring and mitigation-technology testing.
Title: Sensing and Modelling Planetary Dust Reactive Oxygen Species (ROS) and their Effects on Space Missions by High-Fidelity ROS-Activated Dust Simulants
Christos D. Georgiou M.Sc., Ph.D.1 and Elias Chatzitheodoridis M.Sc., Ph.D.2
1,2 Co-Chiefs of Science & Technology Innovations & Operations, Stellar Discoveries, Greece
1 Oral presentation
Abstract
Reactive Oxygen Species (ROS: superoxide radicals, O2•−, hydroxyl radicals, •OH, hydrogen peroxide, H2O2) are constantly generated in dusts (planetary or cosmic) of our Solar system, as demonstrated by direct observations and experiments with planetary dust simulants. Planetary dusts that produce ROS can have a negative impact on missions to Mars, the Moon, Europa, Enceladus, the ISS, and the GSS, as well as a positive impact on other missions. For the former, they can compromise astronaut health, oxidatively deteriorate payload instruments and sensors, and pollut space station inner/outer habitats, destroy biosignatures for alien life search etc. For the latter, dusts selected for sample return missions should be properly handled to preserve the naturally occurring ROS activation for valid simulation studies, and their ROS can be used as O2 source for astronaut support (by O2-harvesting technologies such as our “OxR-From Reactive Oxygen Detection to Oxygen Farming” project; https://www.esa.int/Enabling_Support/Space_Engineering_Technology/Moon_and_Mars_superoxides_for_oxygen_farming), even for monitoring/prognosing Moon/Mars quakes. ROS contamination of space missions by planetary dusts can be modelled by the development of ROS-activated dust simulants. We can produce high-fidelity dust simulants with various types of ROS activation by a process that subjects their mineral source to a high thermal/kinetic energy impact, analogous to high energy impacts on planetary regolith by meteorites. Such thermal/kinetic process enables the simulated planetary dusts to acquire ROS activation of the following types, which are novel, and previously not identified and quantified by chemical means: (I) ROS activation embedded in the simulated dusts during their formation, of the following ROS activation sub-types: a) MEtal OXide Reactive Salts (MEOXRS), composed of metal salts of the ROS superoxide radical (O2•−) and peroxide (O22−); b) Fe-II Reactive Impact Glass (FeRIG), made by Fe2+-rich grains of iron nanoparticles (np-Fe°) that are distributed on the surface of the resulting impact glass spherules/agglutinates. (II) Intrinsic ROS activation potential generated on the surface of the fractured particles of the simulated dust, which is caused by the formation on their surface of silica free radicals, negative and positive charges. MEOXRS, FeRIG, intrinsic ROS activations can be complemented, on demand, with additional Perchlorate Reactive Chlorine Species (PERCS) and Pyrite (FeS2) and Iron Sulfide (FeS) ROS activations, specific for Mars and Moon dust simulants. Existing/commercially available simulants, are (i) dust analogues, which may possess partial intrinsic activation potential, (ii) artificially generated (e.g., by UV exposure, fresh grinding), and (iii) lacking chemical identification and quantification (the latter can be addressed by unique analytical tools of ours). ROS-activated dust simulants can be used to model, using specific ROS sensors of ours (calibrated on the dust simulants), the identification and quantification of the ROS components induced by planetary dusts, which pollute any space environment, mission, base/station, astronauts, equipment etc. The sensors (microfluidic for mission deployment) are the aforementioned and ESA-IDEAS-funded, (i) OxR (at TRL4) and (ii) LunarDBCR (“Lunar Dust Biotoxic Chemical Reactivity”; under development at TRL4), which identify/measure the ROS O2•−/H2O2, and •OH, correspondingly, and also the (iii) PERCS sensor (ready for development) that identifies/measures the PERCS HClO/ClO−. Having specifically identified the ROS/PERCS that affect space missions, these can be, then, eliminated by specific, non-toxic/corrosive, antioxidant chemicals (Georgiou NASA-2022 NOI no N1-21RFISRNom-0006).
Metal asteroids are a topic of increasing interest within both the public and private space sectors, as the in-situ resource utilization (ISRU) and asteroid mining communities continue to develop. As 16 Psyche is the largest known M-class asteroid in the main asteroid belt, it can be considered a prime target for further investigation. Despite this heightened level of interest, many fundamental unknowns remain. Limited existing data predicts a composition of 30-60% metal (predominantly iron and nickel) and the remainder as silicate rock. However, both the physical properties (including detailed composition, grain size, material compaction) and behaviours (including response to micrometeorite impacts and ion irradiation) of the surface material remain unknown.
This research, conducted at ESA’s Vulcan Analogue Sample Facility, aims to better understand the impact processes on 16 Psyche and their influence on the presence (or lack thereof) of a surface regolith. Hyper velocity impact experiments will be conducted using the two-stage gas gun at the University of Kent. Small copper projectiles (~2mm) will be fired at a metal meteorite to determine if the large metal crystals present will shatter and be comminuted, thus contributing to a metal rich surface regolith, or if they will instead melt, therefore not significantly contributing to a surface regolith. In doing so, we aim to predict the composition and physical structure of 16 Psyche’s surface material. We hypothesize that upon impact the crystals will shatter and produce a loose regolith-like material. If this is the case, there are likely to be positive implications for future asteroid mining activities due to the ease of metal extraction from regolith compared to impact-melt crusts.
An estimation of this surface material will enable further, more complex surface research of 16 Psyche, and most importantly for the Vulcan Facility, underpin the development and production of surface simulants of the asteroid. It may also contribute to derisking any future landers, as well as improving the understanding of its utilization potential for resource extraction on Psyche and other metal asteroids. Beyond this, we hope our research can help inform a deeper understanding of the processes of formation and weathering of metal asteroids.
Presentation of the to-be-commissioned ESTEC vacuum dust adhesion facility.
The Virtual Formulation Laboratory (VFL) is a computational tool (based on empirical modelling) developed to simulate and optimise the behaviour of complex particulate systems. While initially designed for bulk solids handling in terrestrial manufacturing, the technology offers a framework for modelling and analysing lunar regolith simulants, addressing critical challenges in extra-terrestrial dust characterisation and handling.
This study proposes the adaptation of the VFL to predict the behaviour of lunar regolith simulants under various reduced gravity conditions and environmental constraints. By incorporating parameters such as particle morphology, cohesion, adhesion, and electrostatic properties, the tool supports virtual testing of regolith characteristics, including flowability, caking, particle breakage, and dust adhesion—key factors affecting mission-critical systems such as mobility platforms, life support systems, and scientific instrumentation.
The VFL can be employed for:
• Characterisation and simulation of dust/regolith behaviour under lunar conditions
• Development and optimisation of regolith simulant formulations to mimic certain features of site-specific lunar soils
• Assessment of contamination risks to materials and mechanical components
• Support for dust mitigation strategies through virtual testing
• Design of dust testing protocols within simulated lunar environments
By building a physics-based knowledge database and integrating empirical data from existing simulants, the VFL can help researchers and engineers better understand the interactions of lunar dust with systems and surfaces. This supports early-stage decision-making for material selection, equipment design, and mission planning—ultimately reducing costs and improving the reliability of lunar operations.
The Vulcan Facility was created by the NHM in London as a contract deliverable for ESA [1][2][3]. It is now located at ESA’s UK site and houses a collection of Lunar, Martian, and asteroid analogue samples (or ‘simulants’) and benchtop analytical equipment for fundamental properties characterisation. Feedstock materials are also available for design and production of new simulants.
The primary aim is to conduct simulants-focused research and technical activities, and apply geoscience expertise to support and de-risk exploration technology development preparing for planetary surface exploration (including sample return missions). European simulant priorities were determined following a user survey and European simulants workshop in 2022.
The Vulcan Facility also provides support and future planning for sample curation activities within ESA and Europe [4]. This includes defining standards and procedures in preparation for long-term storage, handling, and analyses of returned samples to Europe.
The Vulcan Facility led the selection of a Lunar Highland simulant for the Luna Facility dust chamber based at the EAC [5]. This included rigorous characterisation of several anorthositic simulants to inform decision-making [6].
Recent studies include: the creation of lunar south pole simulants designed for use in rocket plume-surface interaction experiments, to understand the regolith’s response to landing spacecraft on the Moon, and could be used to investigate potential damage to infrastructure [7]; and the creation of MARSIE (Mars Advanced Regolith Simulant for Iron Extraction) to develop and test methods for extracting resources from the local Martian regolith [8].
Future research includes: development of more high-fidelity, landing site-specific simulants for the Moon and Mars to support future mission development; design and creation of a Phobos simulant to support the MMX mission; investigation of how shocked minerals affect ISRU processes and traversability of lunar regolith; and additive manufacturing and radiation shielding tests with high-fidelity lunar simulants.
References: [1] Smith C. L. et al. (2017) LPSC Abstract #1218 [2] Smith C. L. et al. (2018) LPSC Abstract #1623 [3] Martin D. J. P. and Duvet L. (2019) LPSC Abstract #2663 [4] Hutzler A. et al. (2023) Hayabusa Symposium Abstract [5] Schlutz, J. et al. (2024) European Lunar Symposium (ELS) Abstract. [6] Zemeny A. et al. (2024) Front. Space Technol. 5:1510635. [7] Martin M. et al. (2025) LPSC Abstract #2519. [8] Wilkinson F. et al. (2025) LPSC Abstract #2449.
Additional Information: Funding administered via ESA’s Exploration, Preparation, Research, and Technology (ExPeRT) Programme (reference E3CX-014), as part of the Terrae Novae European Exploration Envelope Programme (E3P).
An overview of the LUNA analogue testing facility in Cologne
One major environmental constraint during exploration missions is the presence of charged dust-like particles. Therefore, it is of utmost importance to characterise the properties of the dust particles present on the exploration sites and their transportation mechanisms to enable efficient mitigation techniques to be put in place. The main objective of the DUSTER (Dust Study, Transport, and Electrostatic Removal for Exploration Missions) project is to investigate in detail the charging and cohesion of the dust grain in the regolith. The project addresses key questions about the surfacing of airless bodies as well as engineering-oriented concerns regarding the adhesion of dust particles to man-made surfaces (spacecraft, instruments, spacesuits, solar panels, etc.).
The goal of DUSTER is to develop the instrumentation and technologies for in situ analysis of the electrical charging and transport of those dust particles, as well as to develop a ground based test facility to validate the instrument in representative conditions and improve dust charging and transportation models. We will present the three-sensor DUSTER instrument, with special emphasis on the Active Lofted Dust Experiment (ALDE), the first results from this experiment and the plan for future developments. In addition, the laboratory facility that has been used to test ALDE will be presented.
The Moon's surface regolith has endured billions of years of space weathering, including solar wind and UV/cosmic ray bombardment, resulting in a highly charged surface. Some of this charging is permanent due to the embedded solar wind ions in the crystal structures of the Moon's exposed surface minerals. Given the low gravity environment, the inability to discharge due to dry and vacuum conditions, and the fine grained nature of the regolith, the electrostatic properties of the surface dominate the behaviour of the finer fractions of the regolith.
Therefore, this project revolves around experimenting with 4 Apollo samples to directly measure the electrostatic potentials of these samples, and 3D image the structure of the regolith when it is charge-dominated. This will improve our understanding of the sources of the charges, the stickiness of the lunar dust, and the methods required to remove dust from sensitive surfaces. It will also contribute to the design and creation of more representative regolith simulants, supporting the wider lunar science and technology communities.
The key to dealing with dust contamination lies in understanding its adhesive behaviour. It is currently unclear which of several adhesion forces (namely electrostatic and van der Waals forces) would dominate for the different particle sizes present on the Moon. The complex radiative environment under ultra-high vacuum as well as the high variation in shape, composition, and size of the particles makes it difficult to separate different contributions. This PhD research will use complimentary experimental techniques to investigate the adhesion of lunar dust simulant particles; centrifuge testing at Onera and AFM (atomic force microscope) testing at ESA/ESTEC. The use of different approaches allows us to overcome some of the limitations associated with on-earth testing. The objective is to obtain useful data and improve our understanding of the parameters determining adhesion behaviour.
Centrifuge testing is a method for measuring the adhesion behaviour of a large population of particles. This technique can be carried out in a vacuum chamber, thus affords some control over the environment. Centrifuge testing on space-relevant optical solar reflector (OSR) surfaces was carried out at under high vacuum both with and without vacuum ultra-violet illumination in order to compare adhesion values under different charging conditions. In order to measure the adhesion of the smallest particles AFM force-distance curves were obtained under N2 atmosphere, using individual LDS particles which were bonded to the cantilevers, in lieu of standard AFM tips. The surface roughness of each particle can be characterised using AFM topography measurements in order to provide context for the importance of van der Waals forces under these conditions. Methods of charging the particles in situ prior to measurement are also being investigated.
It is well known from the apollo era that lunar dust is a great challenge for lunar surface operations and must be addressed to achieve sustained human presence on the moon. Lunar Dust can cause many potential problems for surface missions and space equipment so minimising dust contamination, understanding the potential effects, and having effective dust mitigation techniques are essential for humanity to successfully return to the moon. The Space Resources Challenge invites teams to design and operate a rover to excavate lunar regolith and sort it by particle size for further processing. The challenge culminates with selected teams field testing their rovers at the LUNA facility. Part of the evaluation criteria is reducing the dust contamination to the lunar environment from the rover activities, which is evaluated using a range of passive sensors to monitor the levels of dust throughout the challenge. The method for monitoring the dust contamination was tested at LUNA to assess its feasibility for being able to compare the levels of dust contamination generated by each team.
Planetary dust particles are a severe threat to different sensitive surfaces of landers and rovers. The success of future missions requires tools for modelling such environments. Technical challenges are linked to accurately model major factors influencing the contamination transport: reconstruction of the plume flow field, regolith erosion, electrostatics, and particle-surface interactions.
A DUSTFLOW simulation tool was developed under the ESA Technology Development Element (TDE) programme [1] to address the complex multiphysics conditions characteristic of the lunar environment. While primarily intended for lunar applications, the tool is also adaptable to other extraterrestrial environments, such as Mars. Its core functionality lies in predicting particulate contamination transport and surface deposition during landers' descent and ascent phases.
Additional applications include risk assessment for assets in proximity to the landing zone and analysis of internal contamination within habitats.
One of the most computationally challenging tasks is to simulate particle movement and interactions due to the enormous number of transported particles. The Apollo lander's number of moved particles can reach up to 1011, assuming an erosion rate of the regolith is at 50 kg/s and a specific size distribution [2]. Storage of such data, assuming 6 DOF (degrees-of-freedom), would require 104 TB, and the computational expense of such a simulation would also be a significant obstacle to obtaining valuable results. A combined Eulerian-Lagrangian simulation approach is applied to reduce the number of particles in the simulation. Larger particles are simulated as 6 DOF, and an advected scalar field is considered for lower diameters.
The presentation will cover the software design and selected contamination simulation results for the full-scale test cases.
References
[1] ‘Particle modelling inside fairings during pre-launch and launch - CCN’, CCN1 to ESA Contract 4000131165.
[2] J. E. Lane and P. T. Metzger, ‘Estimation of Apollo Lunar Dust Transport using Optical Extinction Measurements’, Acta Geophys., vol. 63, no. 2, pp. 568–599, Apr. 2015, doi: 10.1515/acgeo-2015-0005.
To be completed today
Lunar regolith poses one of the main risks and challenges to any lunar surface mission due to the abrasion nature of particles on the Moon, the extreme environment, and the uncertain particle properties. While efforts to gain a deeper understanding of the fundamental properties of regolith particles increased in the past, tests still focused mainly on low-fidelity tests. With the increased accessibility of high fidelity and mature lunar simulants, effects on materials, components, and their performance degradation can be accurately evaluated. In the scope of this work, the degradation of solar cells and MLIs will be evaluated during an entire lunar mission. These components have been identified due to their high exposure to the dust environment and their susceptibility. A lunar mission has two main phases of concern: the lunar descent, where lunar regolith particles are accelerated to high velocity and the operational phase. The lunar regolith and suitable mitigation strategies must also be well characterized for an improved degradation model. This pitch introduces how we aim to achieve extensive knowledge of the material and component performance with key tests of thermo-optical parameters of different lunar simulant and component configurations within a representative environment. With this knowledge, simulation models can be converted directly into performance parameters. Knowing the effects of lunar dust on these key components and materials helps define test parameters and design tests and procedures for future lunar missions, leading to less margin and mass and a cost and risk reduction.
Within the frame of future lunar missions, the evaluation of the change in the performance of representative covering materials is required to estimate the effect of particulate contamination induced by the dust coverage over time (natural or man-induced).
This paper reports on the existing large set of data on the effect of LHS-1 & LHS1-25A deposits (LDS from Space Ressource Technologies) on thermo-optical properties of more than 20 different materials (Coverglasses, Optical Solar Reflectors, Second Surface Mirrors, white and black paintings, MLI outer layers…). Trends of properties versus percentage of dust coverage are available and a metric is proposed to link dust coverage to degradation of solar absorptance and emissivity for all tested material families.
Modification of thermal control surfaces is still a big uncertainty for lunar surface missions. For thermal engineers, changes in thermo-optical properties over mission lifetime can be crucial for thermal design feasibility. Literature from measurement campaigns shows a significant increase especially of radiator coatings’ solar absorptivity. The shortcoming of legacy measurements is their focus on dust coverage rate in % and obviously they are conducted exclusively with lunar dust simulants (LDS). In contrast, simulations and measurements of natural dust coverage rates are usually provided in mass deposition per area. Hence, there is a missing link between the changes in thermo-optical properties and the dust coverage rate caused by natural and anthropogenic processes.
A recent measurement campaign conducted by ONERA under an ESA contract in the scope of the ESA Argonaut program, established a correlation between dust coverage in % and dust deposition in mass deposition per area for the LDS LHS-1 and LHS-1-25A via hundreds of measurements for various thermal control surfaces.
Based on the ONERA measurements, a theoretical approach was derived which accounts for differences in particle size distribution, particle shapes and thermo-optical properties between LDS and natural regolith. The result of this approach is a set of equations that empirically links dust coverage in mass deposited per area for real regolith with predictions of modification factors for thermal control surfaces. The approach and results for a selection of coatings will be presented at the workshop.
Both in manned and robotic exploration the crew protection and reduction of material degradation are key aspects in lunar (or Mars) surface applications. One of the main risks is caused by the exposal and interaction with lunar regolith and dust. Due to its irregular shape and sharp edges, lunar dust is highly abrasive and poses a substantial risk for joints and moving parts. The DEAR project is focusing on performance risk studies as well as the use of E-fields for regolith transportation (dedicated presentation). Different simulants with varying particle sizes were chosen to evaluate the degradation of sealings, penetration through the sealings and performance loss of mechanisms and space suit materials. This was realized in form of a robotic arm wearing a space suit textile performing typical movements. The experience to reproducibly apply the regolith simulants will be discussed. Within this presentation, the collection of the regolith simulants on the space suit materials, as well as the redistribution and migration into the textile depending on the particle size is investigated and presented. The tests inside the DEAR box environment were linked to field studies from analog mission campaigns. Also, the damage and performance degradation of the textile was analyzed to identify critical parts and movements. The DEAR box is now ready to perform lifetime functional testing in a representative dusty environment. Project is co funded by ESA.
Abrasive, electrostatically charged lunar regolith threatens every surface that humans, robots, rovers, and habitats interact with, from sealing gaskets to the mucous membranes of astronauts (NASA Science). Current engineering responses largely treat dust as a passive contaminant, yet long‑duration stays will demand materials that actively interact dynamically with their users and environments. Researchers from TU/Eindhoven and RWTH Aachen present our concepts on interaction‑design‑enabled textile system that encompasses electrodynamic electrodes and micro‑structured fibre geometries for architectural, mobility, and wearable textiles in exoplanetary contexts. We intend to create textiles that can attract and repel regolith, creating opportunities for dynamic everyday interaction in long-term scenarios. For example, when the crew enters an airlock or wipes down an interior panel, a low‑power pulse in the textile shuttles regolith away, while the wiping textile structurally contains sensing and actuation yarns that adapt for cleaning efficacy and indicate remaining dust load.
By fusing human‑computer interaction principles with emergent electro‑textile engineering, the project offers a practicable path toward safer, cleaner, and more sustainable long-term lunar operations. Our international team intends to iteratively prototype textiles, testing them in interaction scenarios, including inflated garments, rovers, and habitats. Our project concept builds on recent in‑situ demonstration of electrodynamic dust shields, which expelled >95 % of adhered particles on the lunar surface, but reframes the technology to also attract regolith and as a soft, modular interface that should be handled, repaired, and possibly up‑cycled by astronauts. We are seeking interactive evaluations in ESA‑compatible dust chambers and everyday lunar scenarios that will quantify removal efficiency, user workload, and system durability against the Lunar Surface Innovation Consortium performance targets (NASA). The resulting design guidelines will be released as an open‑science “Textile Interaction Handbook for Regolith Management", enabling mission planners to integrate dust‑aware fabrics into mobile rovers, inflatable laboratories, and next‑generation xEVA suits.
Within the context of lunar dust mitigation technologies, increasing attention is being directed toward the design and development of high-performance polymers that combine exceptional thermo-mechanical properties with enhanced abhesion, i.e., non-sticking ability when in contact with micrometric dust particles of lunar regolith. These materials represent a promising, reliable, energy-saving and effective solution to the critical challenges posed by the challenging and harsh Moondust environment, which can lead to mechanical clogging, obscuration of optical systems, malfunctioning of electronic components, interference with extravehicular activities, and damage to astronauts’ visors, gloves, and boots, even to causing serious respiratory injuries if inhaled.
The threat is worsened by the unique chemical and physical nature of lunar dust: electrically charged, extremely adherent, and composed of sharp, hard, irregularly shaped particles capable of causing abrasion and wear to exposed surfaces.
To address these complex issues, in the framework of SELf hEaling iNnovative hydrofobic polimEric material (SELENE) project, the Italian Aerospace Research Centre (CIRA) and Sapienza Università di Roma, under Italian Space Agency (ASI) financial support, have started the design of a novel, lightweight and multifunctional hybrid co-polyimide composite engineered for enhanced passive dust mitigation and self-healing capabilities. The proposed material integrates, in an advanced polymeric bulk, appropriately chemically formulated and functionalized according to an innovative chemical strategy, to possess superior abhesion behaviour, two complementary self-healing mechanisms. These will be achieved through the incorporation of specially designed microcapsules, including healing agents and crosslinking catalysts triggered by the Moon's environmental characteristics itself, and by means of intrinsic strategies, consisting of blending with a secondary polymer capable of establishing reversible non-covalent bonds with the main co-polyimide matrix. This synergistic approach not only restores structural integrity after surface damage exerted by abrasion of dust particles but also allows the composite to recover nearly all of its original outstanding mechanical performance.
Both in manned and robotic exploration, crew protection and the reduction of material degradation are key aspects of lunar and Martian surface exploration. One of the main risks arises from exposure to and interaction with lunar regolith and dust. In addition to preventing the accumulation of harsh, sharp-edged particles, the CHARON project’s "cleaning hardware recovery operations" will focus on the reliable removal of lunar surface contamination, specifically for use in material and personnel airlocks. Larger dust particles (d > 5 µm) pose a threat to ocular safety, while smaller particles (d < 5 µm) represent a health risk to astronauts when inhaled. On the hardware side, abrasive dust degrades surface properties and can cause leaks in seals (a topic of the DEAR presentation). Additionally, a cleaning method for highly sensitive surfaces (such as coatings and optical surfaces) and complex geometries (like textile structures and sealing surfaces) is essential.
CO2 snow jet cleaning is a highly efficient, contactless, non-abrasive, and residual-free spraying method for removing dust contamination. The contamination is pushed off the surface and scrubbed from the air using filtration systems. By monitoring the contamination concentration within the air stream with PAC monitors, a real-time measure of the cleaning effectiveness is provided which ensures the final level of cleanliness. This presentation will discuss the CO2 cleaning method, a dedicated machine, and initial test results and applications.
The possibility of future lunar exploration missions is threatened by the risk that lunar regolith poses to the durability and performance of equipment, as well as to the health of those carrying out activities in the lunar environment. A clear gap in knowledge exists between these challenges and the efficiency of current mitigation technologies. Thus, it is paramount that these technologies are developed, and a primary mitigation method is identified.
This collaboration between University College Dublin and OHB SE investigates the efficiency of multiple techniques for removing lunar regolith simulants of different grain sizes from surfaces of varying roughness. Experiments were carried out in a controlled environment. Three lunar regolith simulants of TUBS-M, TUBS-T, and Kīlauea Volcanic Ash were used in conjunction with three various surfaces including sandpaper, an anodised aluminium plate, and a spacesuit textile. Five various cleaning methods were investigated in this research study, including a Space Brush, Dust Roller, Particle Stamp, Particle Rocker, and Plastic Glue. The cleaning efficiency of each method was measured and compared across different simulant-surface combinations.
Key results indicate that the Particle Rocker performed the best across all lunar regolith simulant and surface types. This is likely due to the large contact area of the tool, its strong adhesivity, and the combined shearing/compressive force exerted by the tool as it rocked back and forth. Furthermore, it was also found that TUBS-T experienced the highest rate of removal across all surfaces due to its flat and tabular morphology. In contrast, TUBS-M experienced the lowest removal efficiency, likely due to the angular and jagged shape of its finer particles.
In the frame of the OSIP activity "Lunar Regolith Ineractions with Environments and Robotic Systems", the efficiency of an EDS system embedded in glass and Kapton samples was successfully tested in vacuum under UV irradiation, across a variety of simulants. The results of this test campaign will be presented.
Both in manned and robotic exploration the crew protection and reduction of material degradation are key aspects in lunar (or Mars) surface applications. One of the main risks is caused by the exposal and interaction with lunar regolith and dust. Whereas the CHARON project (dedicated presentation) is focusing on the removal of dust from complex structures the DEAR project focus on the contamination caused performance risks studies (dedicated presentation) and use of E-fields for regolith transportation. Within the presentation the development and results of multi electrode systems and optimization of electric pulse applications for high efficient regolith momentum transfer will be shown. The laboratory mock up based results are presented addressing application like electronic conveyor belts and cleaning of for example solar cells or radiators. The multiparameter investigations are accompanied by dedicated simulations, mandatory to transfer concepts into potential lunar applications. Project is co funded by ESA.
As humanity ventures towards prolonged lunar habitation and exploration, the management of lunar dust contamination within manned modules emerges as a critical concern. Lunar dust, characterized by its abrasive nature and electrostatic properties, poses multifaceted challenges to both human health and equipment integrity. This paper explores the strategy and challenges associated with controlling lunar dust contamination for I-Hab, the Gateway International habitat.
Key strategies for lunar dust contamination control encompass both proactive and reactive measures. Proactively, implementing dust-resistant materials and defining operational constraints can minimize dust entry into modules. Additionally, employing robust filtration systems and establishing strict decontamination protocols for spacesuits and equipment can mitigate internal dust accumulation. Reactively, developing efficient cleaning technologies, such as electrostatic dust removal systems and adhesive-based cleaning mechanisms, proves essential for maintaining habitable conditions within modules.
However, several challenges persist in the effective management of lunar dust contamination. The fine, abrasive nature of lunar dust necessitates the development of durable and resilient materials capable of withstanding its erosive effects over prolonged periods.
Landers, rovers and habitable modules are designed to properly work for a lifetime that ranges from days to 15 years of operations. This paper deals with the approach which was used to define criticality of internal and external sensitive items, together with possible mitigations and verification methods. Dust testing was proposed for materials characterization and design consolidation of non-maintainable items. TAS facilities are herein presented, as well as test definition approach and results.
Both in manned and robotic exploration the crew protection and reduction of material degradation are key aspects in lunar (or Mars) surface applications. One of the main risks is caused by the exposal and interaction with lunar regolith and dust. Whereas the DEAR project focus on the contamination caused performance risks studies (dedicated presentation) the DuReCo project is investigating potential hard surface coatings for dust protection. The fundamental technology of SERAMCOATING covers spray coating of SiC on large and complex geometries. With the possibility to apply larger surface thickness on existing flight geometries the hard, thermal and chemical resistant coating might open interesting space application opportunities. Within a first project the coating was successful applied on space representative materials. In a next step potential applications for dust repellent surfaces, dust elevated temperature resistance and mechanism surfaces will be investigated. The project is funded by ESA.
LOADER (Lifting and Offloading Add-on Device for EL3/Argonaut Resources) is a concept-stage electro-mechanical system designed to support the European Large Logistics Lander, Argonaut, by enabling the autonomous deployment of scientific payloads and surface infrastructure on the lunar surface. The LOADER concept addresses a key operational challenge for future lunar missions: the safe and reliable offloading of large or delicate equipment in the presence of pervasive and potentially damaging lunar dust.
This presentation will introduce the LOADER concept and explore the potential dust contamination risks associated with its mechanical systems and interfaces. It will provide an overview of mitigation strategies currently under evaluation, such as sealed actuators, passive barrier solutions, surface coatings, and mechanical design adaptations intended to minimize ingress and accumulation of lunar dust. The session aims to stimulate discussion on dust-tolerant design principles and identify synergies with ongoing lunar surface systems development.
The rapid expansion of space exploration demands novel and disruptive technologies. Among the most critical advancements for enabling sustained lunar missions are nuclear-based power systems. A primary objective is to generate reliable energy for scientific payloads, rovers, and power stations on the lunar surface, where solar power alone is insufficient. Power systems for space nuclear applications include Advanced Stirling Radioisotope Generators (ASRGs) and fission reactors.
Lunar dust would require several challenges and potential risks for a nuclear power reactor due to its abrasive, adhesive, and electrostatic properties. The fine, sharp particles can cause wear and tear on mechanical components such as pumps, valves, and moving parts, leading to malfunctions and reduced efficiency. Dust accumulation on equipment surfaces may interfere with cooling mechanisms, sensors, and other critical systems, potentially causing overheating or functional degradation. In cooling systems, lunar dust can act as an insulating layer, reducing heat dissipation efficiency, while also blocking radiators or heat exchangers, increasing the risk of system failure. Additionally, dust buildup on radiation shielding may compromise its effectiveness, potentially increasing radiation exposure to surrounding equipment and personnel. The interaction of lunar dust with reactor materials could also lead to corrosion or contamination, accelerating maintenance demands and reducing operational lifespan. If the dust infiltrates the reactor’s core or fuel systems, it could block essential pathways, degrade fuel efficiency, or trigger unexpected chemical reactions. Moreover, the electrostatic properties of lunar dust may interfere with sensitive electronics and sensors, causing inaccurate readings and jeopardizing safe operations. Safety protocols, inspections, and repairs could also be hindered by dust obstruction, complicating maintenance efforts. Addressing these challenges is critical to ensuring the reliability and safety of nuclear power systems in lunar environments.
Mitigation strategies shall be mandatory and carefully developed to address dust-related challenges. Protective enclosures can be used to shield the reactor and minimize dust exposure, while dust-repellent coatings on sensitive equipment can help reduce accumulation. Implementing dust removal systems will reduce the dust accumulation. Additionally, advanced radiation shielding materials resistant to the abrasive nature of lunar dust can enhance protection and longevity.
In summary, while lunar dust is not inherently radioactive, its properties make it a serious consideration for nuclear reactor operation on the Moon. Proper design and protective measures would be essential to ensure the long-term stability and safety of such reactors. Thus, this paper intends to provide a preliminary list of all the foreseen challenges and related required R&D developments that will be needed for the lunar surface nuclear power systems.