The Panel on EXploration of the Committee on SPAce Research (COSPAR) of the International Science Council (ISC) is actively preparing for the 2026 Assembly in Florence a new edition of its RoadMap for Exploration, with contributions from all relevant Scientific Commissions of COSPAR. The main goal of this RoadMap is to provide a 20-year perspective on the upcoming developments of Human and robotic exploration of the Solar System, to identify with the relevant scientific communities the greatest scientific benefits that are expected from planetary exploration, and to suggest ways to secure the largest possible scientific return from investments in exploration made by an increasingly broad spectrum of players. To achieve this goal, PEX and COSPAR will identify and promote the most promising mechanisms for international cooperation. We will identify the best practices to preserve the natural environments and sometimes sparse resources available at the different destinations in the Solar System, particularly at the Moon and Mars. We will also identify the critical technology developments needed for science, in the spirit of the Horizon 2061 foresight exercise. We will explore the best approaches for securing a sustainable exploration program offering participation opportunities to all public and private stakeholders. We will also explore the conditions that will favor an open cooperation between all these stakeholders for the benefit of scientific discoveries and of a peaceful expansion of Humankind into outer space.
In the context of the EGU, we will emphasize the outstanding contributions to this RoadMap that are expected from the European community, and engage with the audience and with EGU participants on their participation in this new version of the COSPAR RoadMap for Exploration.
How to cite: Blanc, M., Galli, A., and Smith, H. D.: Towards a sustainable and environment-friendly development of international cooperation in planetary exploration: building a new COSPAR Exploration RoadMap, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-13179, https://doi.org/10.5194/egusphere-egu25-13179, 2025.
The Lunar Dust Experiment (LDEX) onboard the Lunar Atmosphere and Dust Environment Explorer (LADEE) mission orbited near the lunar equator for about 6 months (9/2013 - 4/2014) and discovered a permanently present dust exosphere engulfing the Moon, comprised of particles ejected from the surface by the continual micrometeoroid bombardment. Re-flying LDEX on a polar orbit enables mapping the dust ejecta production over the entire lunar surface and improves our understanding of volatile retaining in permanently shadowed regions (PSR) and their potential for in-situ resource utilization (ISRU). The CU/LASP internally funded project is for developing a flight concept to adopt our existing LDEX Engineering Model (EM) to be accommodated onboard a CubeSat for a future flight opportunity. The LDEX EM is a fully functional instrument with a high technical readiness level (TRL 9). This CubeSat precursor will justify flying a follow-up larger mission with a more advanced dust instrument capable of in situ compositional and isotopic analysis based on impact ionization time-of-flight mass spectrometry. LASP instruments, like the Surface Dust Analyzer (SUDA) onboard the Europa Clipper mission launched in 2024, and the Interstellar Dust Experiment (IDEX) onboard the Interstellar Mapping and Acceleration Probe (IMAP) to be launched in 2025, could be used for an on-orbit exploration of the volatile content of PSRs. This talk will summarize the LADEE/LDEX findings and the new CubeSat project, including the anticipated results from the proposed CubeSat polar mission.
How to cite: Horanyi, M. and Knapmiller, S.: The Lunar Dust Experiment (LDEX) as a CubeSat payload on polar orbit around the Moon , EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-14802, https://doi.org/10.5194/egusphere-egu25-14802, 2025.
We report on the development of two promising analysis and sampling tools for use on the Moon that promise to enhance science return in upcoming lunar missions and which would inform the search for potentially valuable resources that would be worthwhile exploiting. Building on the success of ISRO's Chandrayaan missions, our efforts aim at 1) creating an advanced drilling instrument with an integrated sensing unit, referred to as the “Moon Sensing Drill" (MSD), and 2) a “Soil and Pebble Sampler” (SPS). The MSD partially builds on concepts already studied in Europe under an “instrumented drill" heading whereas the SPS is entirely new. We are realizing the systems in collaboration between D Y Patil International University in Pune, India, and European entities.
The MSD would be able to drill autonomously into lunar regolith and analyze the subsurface column in real-time, including detection of 3He, volatiles and key minerals. Moreover, temperature and thermal conductivity sensors would be part of the drill. The design is based primarily on a percussive drilling system, with the sensors incorporated inside the drill stem. The sensor data will be sent wirelesslessly to an electronics unit that integrates the information. This way, no rotary transmission of signal cables to and from sensors needs to be incorporated into the drill. Power transmission to the sensors is however via slip rings. The system can either be carried on a lunar rover or on lander Maximum drilling depth into the regolith is 20 cm. We are currently designing and building a demonstrator.
The Soil Pebble Sampler (SPS) is a versatile tool designed to allow the collection and analysis of soil / regolith and pebble samples. In particular, the SPS is the first ever concept for uncrewed missions for controlled sampling of both soil and pebbles in a single tool. This will be key to future sample return missions to the Moon, such as Chandrayaan-4 in the ISRO space program.
In the case of Drilling Mode, SPS employs a rotary drill equipped with radial blades and an external, thin-walled auger to drill into soil. With progressing depth, a longitudinal cavity (“tunnel") incorporated in the drill stem is filled with regolith. One of the SPS assemblies is the ball-end vibrating mechanism, which is able to shake particles loose from the drill and therefore keep debris from becoming lodged in the drill tip and the associated samples. Moreover, the vibrating mechanism is essential in shaking out the soil that would have been pressed into the sample tunnel.
A stable 3-jaw gripping structure is at the end of the ball-end vibrating mechanism and uses that mechanism's sideways motion capability to pick up a pebble.
How to cite: Richter, L., Prabhat, R., Dinesh, K., Chakrabartty, S., and Ng, T.: Enhancing Lunar Exploration: Drilling, Sensing, and Sampling Systems for In-Situ Regolith Subsurface Analysis and for Sample Return, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-18455, https://doi.org/10.5194/egusphere-egu25-18455, 2025.
Building on more than 60 years of success in experimental space research, the Swedish Institute of Space Physics (IRF) has developed a comprehensive test, qualification, and calibration infrastructure known as IRF SpaceLab. This facility supports space hardware development and manufacturing. IRF SpaceLab includes the following capabilities:
- Co-60 Irradiation Facility: Provides dose rates ranging from 1 kR over 3.5 days to 1 kR in 5 hours, depending on the distance to the source. These moderate dose rates make the facility ideal for realistic radiation testing of space hardware.
- Radioactive Isotope Collection: Features a wide array of isotopes for detector characterization, including Co-60, Cs-137, Ni-63, H-3, Ba-133, and Ra-226.
- Thermal-Vacuum Chambers: Offers three chambers designed for testing hardware at different scales: board level, instrument level (<50 cm), and nano/micro-satellite scale (<1 m). The latter chamber is equipped with an LN2-cooled shroud and solar flux simulators, suitable for thermal balance tests.
- Shaker (35 kN): Capable of mechanical testing of objects up to 100 kg in a clean environment.
- Ion (+/-), Neutral, and Electron Beam Facility: Operates within an energy range of 50 eV to 50 keV and includes a 4-degree-of-freedom turntable.
- Particle-Surface Interaction Facility: Designed for surface characterization, particularly for surface-based ion mass analyzers.
One of the key advantages of the IRF SpaceLab is the integration of these diverse facilities within a single premises operated under a small research institute environment. This setup minimizes formalities and administrative overhead. IRF SpaceLab is open to external users to support space and planetary exploration initiatives (https://spacelab.irf.se/).
How to cite: Kerenyi, M., Barabash, S., and Wittmann, P.: IRF SpaceLab – a Swedish opening research infrastructure to support space and planetary exploration, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-15221, https://doi.org/10.5194/egusphere-egu25-15221, 2025.
Jupiter and its icy moons—Europa, Ganymede, and Callisto—are among the most intriguing targets in the Solar System for studying habitability and searching for life. Substantial evidence suggests that these moons harbor subsurface water oceans beneath their icy crusts, with conditions that may support the development and sustainability of life. To investigate this, the European Space Agency (ESA) has launched the JUpiter ICy moons Explorer (JUICE) on April 14th, 2023.
The Jovian radiation environment is extremely hazardous for space exploration. High-energy electrons trapped in the Jovian system can penetrate thick shielding walls and accumulate large doses in electronic components and materials reducing their operational lifespan significantly. High energy particles can also disassociate biological molecules that migrated from the icy moons’ oceans to the surface hindering the detection of biosignatures from orbit.
For these reasons, JUICE carries a RADiation hard Electron Monitor (RADEM), with a novel design, capable of measuring high energy electrons, protons, and ions. RADEM is an engineering instrument, that is continuously operated throughout the mission including its cruise phase, but that can also contribute significantly to scientific investigations of the Jovian system. The same is true for the cruise phase. JUICE joins an increasing but still limited Solar fleet that includes STEREO-A, Solar Orbiter, Parker Solar Probe, BepiColombo, and near-Earth spacecraft, having already observed dozens of Solar Energetic Particle events.
In this work, we will take a deep dive into the two first years of RADEM observations, calibration activities, and scientific highlights, including a cosmic ray calibration campaign, cross-calibrations with STEREO-A and SOHO, and observation of the Van Allen belts during JUICE’s world first Lunar-Earth Gravity Assist.
How to cite: Pinto, M., Rodríguez-García, L., Santos, F., Dresing, N., Vainio, R., Cohen, C., Palmerio, E., Gonçalves, P., Altobelli, N., Witasse, O., Santin, G., Evill, R., and Marques, A.: Two years of observations with the JUICE mission radiation monitor, RADEM., EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-16587, https://doi.org/10.5194/egusphere-egu25-16587, 2025.
The Jupiter Icy Moons Explorer (JUICE), launched by the European Space Agency on April 14th, 2023, is on an eight-year journey to the Jovian system, arriving in July 2031. Among its eleven experiments, the Planetary Radio Interferometric and Doppler Experiment (PRIDE) stands out conduction Earth-based radio measurements. PRIDE leverages a network of Very Long Baseline Interferometry (VLBI) radio telescopes worldwide to perform radio science experiments [Gurvits 2023]. These experiments include radio occultation studies of Jupiter’s atmosphere, monitoring space weather, and precisely determining the dynamics of the JUICE spacecraft, and the ephemerides of Jupiter and its moons. For instance, these ephemerides are essential for understanding the long-term orbital and interior evolution of the icy moons, shedding light on their tidal interactions and geological history.
The University of Tasmania (UTAS) plays a role in this mission through its operation of a continent-wide network of five large radio telescopes: Hobart-12m, Katherine-12m, Yarragadee-12m, Hobart-26m, and Ceduna-30m. Since 2010, these telescopes have been used for planetary tracking by conducting radio science experiments to support missions such as Venus Express, Mars Express, and BepiColombo [Molera Calves 2021]. During the 2023-2024 period, UTAS’s VLBI radio telescopes have been actively monitoring the X-band radio downlink signals from various spacecraft, including Mars Express, Tianwen-1, BepiColombo, Solar Orbiter, and JUICE [Kummamuru 2023, Maoli 2023, Noor 2025 and Edwards 2025]. These observations are particularly valuable during solar conjunctions, when the spacecraft are aligned with the Sun, allowing for precise measurements of the solar corona. In addition, several we have reported and studied the transit of Coronal Mass Ejections (CMEs) across the radio propagation path. These observations provide estimates of the propagation and velocities of CMEs, enhancing our ability to forecast space weather events and their potential impacts.
How to cite: Molera Calves, G., White, O., Edwards, J., Cimo, G., Dirkx, D., Gisolfi, L., and Pallichadath, V.: Deep space weather radio observations of JUICE spacecraft with VLBI radio telescopes, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-17634, https://doi.org/10.5194/egusphere-egu25-17634, 2025.
The Hera mission was launched on 7 October 2024 and will reach its destination, the binary asteroids Didymos and Dimorphos, in late 2026. Hera carries the hyperspectral imager Hyperscout-H. Its sensor consists of 2048 × 1088 pixels arranged in macro pixel blocks of 5 × 5 pixels. The 25 pixels of each block are covered with filters in 25 different wavelengths where the center response ranges from 657 to 949 nm. Therefore, each of the 2048 × 1088 micro pixels provides brightness information for one wavelength, and the actual macro pixel resolution is only about 409 × 217 pixels. Any simple interpolation approach between micro pixels is strongly affected by pixel-to-pixel variations in spectra and by varying albedo and shading effects caused by surface inclination. This makes the resultant spectra very noisy.
To retrieve more accurate spectra with higher spatial resolution, we have developed a family of novel demosaicing methods. We separate the spectrum at each micro pixel into a normalized spectrum and a brightness scaling factor. Ratios of measured values from adjacent pixels are used to iteratively compute the normalized spectra, which are then brightness scaled to reproduce the measured values. This approach allows replenishment of the complete data cube of 2048 × 1088 × 25 pixels.
Four days after launch, the three cameras aboard Hera acquired images of the Moon and the Earth. Because of the large distance, the resolution of these images was limited. However, the Hyperscout-H images of the Earth demonstrated that color images at full micro pixel resolution can be reconstructed from the replenished data cube.
On 12 March 2025, Hera will perform a fly-by of Mars, and images of Mars and Deimos will be acquired from distances of about 20,000 and 1,000 km, respectively. Hyperscout-H is planned to acquire one image with both Mars and Deimos in the field of view. We will apply our demosaicing methods to replenish the complete data cubes and reconstruct color images at full micro pixel resolution.
How to cite: Grieger, B., de León, J., Goldberg, H., Kohout, T., Kovács, G., Küppers, M., Nagy, B. V., Popescu, M., and Prodan, G.: Superresolution color images of Mars and Deimos acquired by the Hyperscout-H hyperspectral imager aboard the Hera mission, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-7092, https://doi.org/10.5194/egusphere-egu25-7092, 2025.
A time-of-flight mass spectrometer (TOF-MS) separates charged particles by their mass-per-charge ratio on the basis of their transit times through an electric field. For accurate mass determination, ions must be guided from the source inlet, through the ion-optical system, and onto the detector as a beam with a controlled, narrow opening angle. This requires careful dimensioning of the electrodes and computation of the applied electric fields to control beam deflection and achieve both spatial and temporal focusing across the entire detector plane. The primary goal of this work is to develop an efficient optimisation framework for TOF-MS ion-optical designs that addresses performance trade-offs and computational challenges. For spaceborne instrumentation, high sensitivity and resolution must be balanced against size and mass constraints, making their design and optimisation particularly challenging.
The ion-optical design process involves trading off numerous interdependent parameters without an analytical solution. Mathematically, this problem can be interpreted as a derivative-free constrained optimisation problem with high dimensionality. Bieler et al. (2011) successfully used an adaptive particle swarm algorithm (APSA) to optimise voltages and electric fields for several existing ion-optical systems [1], including the Reflectron TOF (RTOF) mass spectrometer flown on the Rosetta mission of the European Space Agency. However, their approach focused on optimising voltages for predefined ion-optical geometries, without addressing the simultaneous optimisation of geometry and voltages during the early design phase. This limitation restricts the flexibility of the optimisation process and may lead to suboptimal ion focusing.
This work fills that gap by applying a particle swarm algorithm during the early design phase of a novel TOF-MS instrument. Using the SIMION® ion and electron optics simulator [2] at its base, this approach simultaneously optimises both the electrode geometries and the applied voltages, resulting in more precise control over the electric field profiles. Additionally, parallel computation techniques are implemented at thread and process levels to efficiently manage a large number of degrees of freedom, reducing computation time by allowing multiple independent particle swarms to explore the solution space concurrently. This approach provides a scalable framework for designing more precise and computationally efficient spaceborne TOF-MS instruments, contributing to the development of next-generation instruments for planetary exploration and scientific research.
[1] A. Bieler, K. Altwegg, L. Hofer et al., ‘Optimization of mass spectrometers using the adaptive particle swarm algorithm,’ Journal of Mass Spectrometry, vol. 46, no. 11, pp. 1143–1151, 2011, issn: 1096-9888. doi: 10.1002/jms.2001.
[2] D. A. Dahl, ‘Simion for the personal computer in reflection,’ International Journal of Mass Spectrometry, Volume 200: The state of the field as we move into a new millenium, vol. 200, no. 1, pp. 3–25, 25th Dec. 2000, issn: 1387-3806. doi: 10.1016/S1387-3806(00)00305-5.
How to cite: Bonny, R. F., Aebi, A. E., Fausch, R. G., Doriot, A. C., Müller, D. R., and Rubin, M.: Optimising the Design of Spaceborne Time-of-Flight Mass Spectrometers with Particle Swarm Algorithms, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-9964, https://doi.org/10.5194/egusphere-egu25-9964, 2025.
Building upon the heritage of the Life Marker Chip (LMC) developed for Mars exploration (Sims et al. 2012), I present an advanced integrated photonic biosensor for in-situ molecular detection in space environments. The system employs an asymmetric Mach-Zehnder Interferometer (aMZI) fabricated using silicon nitride waveguide technology, enabling label-free detection of biomolecules through refractive index sensing. Material-selective surface functionalization allows targeted immobilization of probe molecules exclusively on the waveguide sensing areas, enhancing sensitivity - down to ppt levels - and specificity. I demonstrate the successful detection of multiple biomarkers with this novel system, including DNA and polycyclic aromatic hydrocarbons, as well as selectivity of chiral enantiomers of the amino acid phenylalanine (Ligterink et al. in prep.).
Next, I will outline the future development of the LMC. By integrating light sources, detectors, and microfluidic sample handling on a single chip, the size and complexity will be reduced compared to previous systems. The compact, integrated design eliminates the need for external optical components while maintaining high sensitivity, making it particularly suitable for space applications where size, mass, and robustness are critical. This work represents a significant step toward developing field-deployable molecular detection capabilities for planetary exploration.
Sims et al. 2012: Sims, M.R., Cullen, D.C., Rix, C.S., Buckley, A., Derveni, M., Evans, D., García-Con, L.M., Rhodes, A., Rato, C.C., Stefinovic, M. and Sephton, M.A., 2012. Development status of the life marker chip instrument for ExoMars. Planetary and Space Science, 72(1), pp.129-137.
How to cite: Ligterink, N. F. W.: The Next-Generation Life Marker Chip: A Photonic Biosensor for Space Exploration, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-4996, https://doi.org/10.5194/egusphere-egu25-4996, 2025.
The AMADEE-24 mission, conducted by the Austrian Space Forum (ÖWF) in March and April 2024 in Armenia, was a high-fidelity Mars analog mission aimed at preparing for future human exploration of the Red Planet. The mission brought together scientists and engineers from across the globe to test innovative technologies, operational workflows, and scientific methods in a Martian-like environment. By simulating the challenges of human-robotic exploration, AMADEE-24 focused on optimizing the science return of future crewed missions to Mars and advancing planetary research.
The Armenian test site was selected for its geological and environmental similarities to Mars, offering a unique analog terrain to conduct field experiments in geology, planetary geology, astrobiology, engineering, and human factors research and testing exploration strategies and scientific instruments. It addressed key scientific and operational objectives, including the validation of exploration technologies, the refinement of mission protocols, and the development of new approaches for conducting science in remote environments.
One of the core focuses of AMADEE-24 was planetary geology and astrobiology. The analog astronauts, equipped with state-of-the-art tools such as Raman spectrometers and remote sensing devices, conducted fieldwork to investigate the mineral composition of the terrain and search for biosignatures—indicators of potential past or present life.
The mission also placed significant emphasis on human factors and mission operations. AMADEE-24 tested EVA protocols, communication strategies with Mission Support under time delay, and astronaut performance in isolation. These studies provided crucial data on the efficiency and safety of crewed operations in extreme environments, helping to optimize decision-making processes and workflows for future Mars missions.
AMADEE-24 also served as a testbed for new exploration tools. The mission tested drones, autonomous systems, and other robotic technologies in the challenging Armenian terrain. The validation of these tools in a Mars-like environment ensures that future exploration missions will be equipped with robust, reliable instruments capable of collecting high-quality scientific data under harsh conditions.
Mission requires a critical operation on payload management during AMADEE-24, which was essential for the efficient execution of the mission's science objectives. Here, we also present, the complexity of managing scientific payloads in a Mars analog environment required careful planning to ensure optimal use of instruments and seamless integration of scientific and operational workflows. The results of this operation provide insights into payload prioritization, instrument deployment strategies, and data handling processes.
The scientific outcomes of AMADEE-24 are expected to make contributions to planetary exploration research. The mission’s findings will help refine science protocols, improve instrumentation strategies, and enhance comparative planetology studies. The interdisciplinary nature of the mission, involving scientists from various fields, highlights the importance of collaboration in addressing the complex challenges of human Mars exploration.
AMADEE-24 marked a significant milestone in Mars analog research, providing valuable insights into the science, technology, and human factors that will shape future crewed missions to Mars. By bridging the gap between Earth-based experiments and space missions, AMADEE-24 plays a crucial role in humanity’s preparation for the first steps on athe Martian surface.
How to cite: Özdemir-Fritz, S. and Groemer, G.: Exploring Mars on Earth: Scientific Outcomes of the AMADEE-24 Mission , EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-10818, https://doi.org/10.5194/egusphere-egu25-10818, 2025.
The internal structure of small asteroids (diameter < 1 km) remains poorly known, and recent spacecraft/surface interactions performed by the Osiris-REX and Hayabusa2 missions produced unexpected results about their physical properties.
What is the level of macro- and micro-porosity? What are the cohesive forces? Are the bodies stratified, heterogeneous or more homogenous? The answers to these questions have strong implications for both the long-term evolution of these bodies and for planetary defense.
Seismology experiments on such objects are difficult due to the low gravity and the possible small amount of natural seismic sources on these objects. However, during its pass close to the Earth in 2029, seismic activity will be generated in the asteroid Apophis by tidal stresses. This unique opportunity of natural seismic sources is exploited by the SIA instrument concept, which is planned to be deployed to the surface of the asteroid by the ESA RAMSES mission before the close encounter of Apophis with the Earth.
We first present and justify both the science case and the concept of operations of the seismic measurements on Apophis during the close encounter with the Earth. We then describe the instrument itself by presenting the current development status and system budgets. Finally, we discuss the lander platform requirements to reach the seismometer measurement performances and the science objectives.
How to cite: Cadu, A., Garcia, R., Murdoch, N., De Martini, J., Sournac, A., Wilhelm, A., Carpi, P., Mimoun, D., Kawamura, T., Lognonné, P., Michel, P., and Bousquet, P.: Seismic Instrument for Asteroids (SIA): a seismometer based on geophone sensors for the RAMSES mission to Apophis, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-17253, https://doi.org/10.5194/egusphere-egu25-17253, 2025.
The M-MATISSE mission, currently in its Phase A study by the European Space Agency (ESA), is a Medium-class (M7) candidate that aims to explore the complex interactions between Mars' magnetosphere, ionosphere, and thermosphere (MIT coupling). This two-spacecraft mission, comprising identical payloads on board "Henry" and "Marguerite", will investigate how these interactions are influenced by space weather and the lower atmosphere. The spacecraft will follow different orbits with apocenters at 3,000 km and 10,000 km altitude, respectively, and pericenters at 250 km altitude, allowing for a comprehensive understanding of the Martian environment.
The MaCro instrument, which utilizes an inter-satellite radio link, will study occultation events in the Martian atmosphere, covering altitudes from 1,000 km to the surface, including the ionosphere and neutral atmosphere. Occultations occur when one spacecraft disappears behind the Martian disk as seen from the other spacecraft. Operating at two frequencies simultaneously—UHF and S-band—MaCro allows for a clear distinction between the ionospheric plasma and the neutral part of the atmosphere. The instrumentation setup consists of two software-defined transceivers (SDR) at UHF and S-band, stabilized by a highly stable oven-controlled crystal oscillator (OCXO) on each spacecraft. The observables include the shift of the carrier frequencies caused by the bending of the radio ray path in the atmosphere/ionosphere and the received signal power.
This presentation provides an overview of the MaCro instrument's technical concept and scientific objectives.
How to cite: Vorderobermeier, T., Andert, T., Paetzold, M., Tellman, S., Plettemeier, D., Budroweit, J., Imamura, T., Ando, H., Genova, A., Hahn, M., Noguchi, K., Oschlisniok, J., Peter, K., Schäfer, W., Sanchez-Cano, B., and Leblanc, F.: The M-MATISSE Crosslink Occultation Instrument MaCro, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-11879, https://doi.org/10.5194/egusphere-egu25-11879, 2025.
SWEATERS (Space WEATher Ena Radiation Sensors) project has the purpose to realize an innovative ENA sensor for Space Weather application and plasma monitoring.
ENA (Energetic Neutral Atoms) signal detection is a well proven technique able to provide information about Solar wind interaction with planetary environments providing plasma global imaging.
SWEATERS sensor is a new ENA instrument concept based for the first time on gas detector technique. The challenge of the project is to apply advanced particle detection technologies developed in the HEP field to instruments for space application, e.g. ENAs in space.
The MicroMegas gas detector (MM) developed at CERN is the baseline for this new ENA sensor concept. The main advantage is to provide all the requested items of ENA detection (mass, energy, direction) in a unique and compact system.
Sensors installed on a cluster of platforms orbiting at low altitude around the Earth could provide new detailed information on the plasma populations generated in perturbation phenomena.
How to cite: De Angelis, E., Mura, A., Pilo, F., Maestro, P., and Orsini, S. and the SWEATERS team: A novel ENA instrument for Space Weather monitoring: SWEATERS (SWEATERS-Space WEATher Ena Radiation Sensors) project, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-20037, https://doi.org/10.5194/egusphere-egu25-20037, 2025.
The Venus Emissivity Mapper (VEM) is a groundbreaking instrument designed to transform our understanding of Venus. Developed for NASA’s VERITAS and ESA’s EnVision orbiters, this advanced push-broom multispectral imager is tailored to reveal the planet’s surface. VEM features a 14-band filter assembly, an InGaAs detector with thermoelectric cooling, a turn-window mechanism, and a dual-stage baffle system to ensure performance in Venus's harsh environment. Weighing just 6 kilograms, it will achieve over 70% global coverage, enabling unprecedented surface mapping. VEM promises to unveil Venus's secrets and deepen our understanding of Earth’s enigmatic sister planet.
Optics: The VEM/VenSpec-M Optics (VEMO), developed by CNES and LESIA, uses a telecentric 3-lens system for precision imaging. Its entrance lens focuses the Venusian scenery onto a filter assembly, while relay optics with <1 magnification transfer the image to a 16.4 mm focal length detector. With a 46.4° field of view, it achieves a 207 km swath width at a 250 km orbit. The filter assembly (0.86–1.18 µm), developed by Bertin Winlight and CILAS, maps the image across 14 filter stripes, enabling surface emission measurements and atmospheric corrections.
Detector: The VEM detector features an InGaAs short-wave infrared sensor with an integrated thermoelectric cooler, eliminating the need for a cryocooler. Qualified for space, it undergoes rigorous environmental testing. The detector covers 400–1700 nm (optimized to 790–1510 nm), with 640 x 512 pixels at a 20 µm pitch, operating from -40°C to +70°C (baseline 0°C). Its quantum efficiency peaks at ~85%, aligning with the VEM spectral range. System-level analyses show signal-to-noise ratios around 100, even at the mission's end, with a margin exceeding 100%. While a radiation test campaign is complete, managing increased dark current from proton irradiation remains a challenge.
Testing and Analysis: A thermal cycling test was conducted as part of the evaluation campaign on two flight-representative sealed detectors following the MIL-STD-883 standard (method 1010, condition A). The temperature range was adjusted to -43°C to -40°C and +85°C to +88°C, staying within the detector’s non-operative limits. The test involved 100 cycles with a 125°C total range achieved in 16 minutes, resulting in a gradient of approximately 8°C per minute. A follow up of the structural analysis has been performed showing that the loads at the VEMO interface are higher than initially expected, resulting in increased loads at the detector level. The engineering team will explore potential solutions, including updates to the mechanical design to mitigate the loads.
Keywords: VERITAS, VEM, EnVision, VenSpec-M, Venus, IR, N-IR, SWIR, InGaAs, Imaging
Acknowledgments: CNES/LESIA for its contribution on the optics development.
How to cite: Rosas Ortiz, Y. M. and the team Venus Emissivity Mapper (VEM) for VERITAS and Envision: Instrument Design Updated of the Venus Emissivity Mapper (VEM) for VERITAS and Envision, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-20977, https://doi.org/10.5194/egusphere-egu25-20977, 2025.
The deployment of surface seismometers on the Moon and Mars has demonstrated their ability to recover both internal structure and seismicity of these planetary bodies.
However, on planets with dense atmospheres and extreme surface conditions like Venus, seismometers deployed at the surface face significant challenges, including short measurement durations due to the high temperature limitations of the electronics and elevated background noise due to ground deformations generated by atmospheric dynamics. However, the relatively unconstrained internal structure of Venus is an important missing piece in our understanding of the formation and evolution of Solar System planets.
In response, atmospheric seismology measurement concepts that rely on detecting infrasound generated by seismic waves -- already successfully demonstrated on Earth – are being explored for Venus exploration. In this context, we present a comparison of the seismic wave detection capabilities for ground based sensors, atmospheric balloon sensors, and airglow imagers measurements concepts. We then examine the scientific potential of different airglow imager configurations, demonstrating not only their relevance for Venus seismology but also their applicability to broader, high-level science questions. Furthermore, we address technical challenges associated with such a mission concept. are also discuss. These discussions provide valuable insights for the design of future missions to explore Venus’ seismicity and internal structure.
How to cite: Garcia, R. F., Grott, M., and Van Zelst, I. and the ISSI team "Seismicity on Venus: Prediction and Detection": Seismology on Venus: from measurement concepts to implementation in a planetary mission, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-6634, https://doi.org/10.5194/egusphere-egu25-6634, 2025.
The Cosmic Dust Analyzer (CDA) on the Cassini spacecraft has convincingly demonstrated the scientific value of mass spectra of ice particles ejected by the plume on Saturn's ice moon Enceladus. Trace amounts of organic and inorganic molecules embedded in ice particles revealed invaluable insight into the chemical composition of the ocean beneath the moon's icy crust. However, it became quickly obvious that to address open questions about the astrobiological nature of the ocean requires impact ionisation mass spectrometers with a considerably higher mass resolution than that of the CDA instrument of m/Δm ~ 50. Other CDA shortcomings include target cleanliness issues and the low detection cadence of 1 impact per second.
The High Ice Flux Instrument (HIFI) is a reflectron-type impact mass spectrometer specifically designed for such applications. It has a mass resolution of 1000 to 2000 and has been optimized for using the electronics of the Surface Dust Analyser instrument on Europa Clipper for recording the spectra. To ensure a high mass resolution HIFI has a long drift region and uses a set of electrostatic Einzel lenses to prevent the ion beam from diverging before entering the single stage reflectron region. The reflectron optics is composed of 23 precision machined electrostatic electrodes to guarantee a smooth reflecting field. In contrast to previous reflectron impact mass spectrometers such as CIDA enter the impacting particles the spectrometer through the reflectron to strike the target at a right angle. The target itself is a highly polished Titanium carrier coated with 250 nm of high purity Iridium (nm surface roughness). The high atomic mass of Iridium ensures that no target lines as well as target cluster lines appear in the mass range ≤ 200 u relevant for the compositional analysis of mineral and ice particles.
The instrument performance has been verified through the impact of metal particles at high velocities. Additionally, experiments were conducted with ice particles to illustrate the capacity of HIFI to discern minute quantities of salts and organics in the spectra of water ice.
How to cite: Kempf, S., Creager, M., Tucker, S., Sternovsky, Z., Hsu, S., Cable, M., Nouzak, L., Abel, B., and Postberg, F.: Sniffing the Enceladus Plume: The High Ice Flux Instrument (HIFI) Compositional Analyzer, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-20361, https://doi.org/10.5194/egusphere-egu25-20361, 2025.
Laboratory experiments constructed following the principle of hydrodynamic similarity often prove to be surprisingly accurate models of large-scale atmospheric flow phenomena. In the von Kármán Laboratory of Environmental Flows we designed new innovative experiment configurations, which are modified versions of the water-filled differentially heated rotating annulus setting, a widely used laboratory-scale minimal model of the mid-latitude Terrestrial atmospheric circulation. In the framework of our ESA-sponsored VERATAC (Venus Radar Topography and Atmospheric Circulation) project and in preparation for ESA's EnVision mission to Venus, we intend to model the hydrodynamic instabilities emerging in the superrotating upper atmosphere of the planet Venus, where the cloud tops circle the planet ca. 60 times faster than the rotation period of the surface. In our preliminary experiments and numerical simulations, we have explored the character of the atmospheric flow patterns developing at different values of the radial temperature gradient and rotation rate, while also applying an azimuthally (zonally) inhomogeneous, dipole-like heating and cooling along the rim of the cylindrical tank. These boundary conditions imitate the thermal driving provided by the meridional temperature contrast – yielding an Eady cell-like overturning convection on Venus – and the thermal difference between the day side and night side, both of which are essential conditions for superrotation to occur. Besides the better understanding of the Venusian atmosphere, this experimental configuration may also be a useful model of the large-scale atmospheric circulation of tidally locked exoplanets, on which a large pool of new empirical data is expected to become available in the coming decade from new space observatories.
How to cite: Vincze, M.: Laboratory-scale experimental modeling of superrotating planetary atmospheres , EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-14290, https://doi.org/10.5194/egusphere-egu25-14290, 2025.
We are proposing a mission concept for Active Debris Removal (ADR) of multiple uncooperative debris targets from Low Earth Orbit, using a minisat spacecraft ("mothership") carrying several Coulomb Drag based Plasma Brake¹ modules. The Plasma Brake technology enables very high downmass/upmass ratios for debris deorbiting. In optimal conditions, the ratio for such a mission could be up to 60, representing a radical increase in ADR performance of 1-2 orders of magnitude compared to the current state-of-the-art ADR missions, and drastically improving the cost efficiency compared to one-object-per-mission approaches. The Plasma Brake is especially competitive in the ~700-1200 km altitude range. The applicable debris mass limit of this deorbiting method is dictated by the demisability of the targets and is roughly 500 kg / Plasma brake unit. It provides a scalable, cost-effective method for reaching a net-zero space debris operations in the long term.
The mission scenario consists of transfers between targets and a sequence of mothership operations repeated at each target: rendezvouz, detection, approach, de-tumbling of the target, attachment of a Plasma Brake module to the target. The critical core technologies needed to realize the mission, and are currently at low TRL, include:
- Sensors, actuators and algorithms required for the proximity operations used to approach and de-tumble the target object,
- Capture/attachment technologies for uncooperative targets like: kinematic structures, Hoberman sphere mechanisms, electrostatic adhesive,
- Adaptation of Plasma Brake concept to work with uncooperative targets,
- Framework for choosing the targets of a a multi-object touring mission that maximizes the downmass/upmass ratio, including the navigation scheme and navigation algorithms.
Most ADR technologies so far are only viable for deorbiting large pieces of debris. The proposed system allows the effective deorbiting of much smaller pieces of debris as well, maintaining its effectiveness indefinitely to clean up the debris that is required by zero-debris targets.
The mission concept and development of the critical core technologies needed for the mission to TRL 4 (testing prototypes in laboratory environment) have been proposed in EIC Pathfinder call of October 2024 by the authors.
¹Janhunen, P., Electrostatic plasma brake for deorbiting a satellite, J. Prop. Power, 26, 370-372, 2010, https://arc.aiaa.org/doi/10.2514/1.47537
How to cite: Genzer, M., Janhunen, P., Haukka, H., Knuuttila, O., Nyman, L., Kestilä, A., Yli-Opas, P., Mäkiniemi, K., Olivares Mendez, M., Martinez Luna, C., Bera, A., Scarpa, F., Maligno, A., Klimavicius, M., and Malinauskas, T.: PREMIER - Plasma Brake Multi-target Active Debris Removal Mission for Low Earth Orbit, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-4073, https://doi.org/10.5194/egusphere-egu25-4073, 2025.
The concept of Plasma Brake is based on the ionospheric plasma Coulomb drag. It is analogous to the air drag in the neutral atmosphere. The dragging obstacle against the orbital plasma RAM flow is established by an electrostatic field with a high voltage difference with respect to the ambient plasma, typically -1 kV. The potential structure is supported by a long 4-wire tether with single aluminium wires with thickness of less than 50 um. The redundant structure makes the tether resilient against micro-meteoroids. The tether deployed by the Plasma Brake is stabilised by the gravity gradient. As the negative tether is attracting plasma ions, a current system between the tether and the ambient plasma is set up. However, the required high voltage power system and its power consumption is such that the Plasma Brake can be considered as a passive debris removal system. In addition, the hair-thin tether sets no harm to other space assets based on micro-meteoroid and space debris flux models such as MASTER-2009. In this presentation, we overview the Plasma Brake plasma physics, deorbiting capabilities, past and future CubeSat in-orbit experiments, and technology development in ESA framework.
How to cite: Toivanen, P., Janhunen, P., Kivekäs, J., Polkko, J., Genzer, M., Hieta, M., and Haukka, H.: Plasma Brake for Space Debris Mitigation, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-15048, https://doi.org/10.5194/egusphere-egu25-15048, 2025.
After a successful entry and descent on Titan, on 14 January 2005, the probe remarkably survived the landing and continued radioing from the surface to the overflying Cassini, until the orbiter set below Titan’s local horizon.
The inter probe-satellite Huygens to Cassini sinal provided, other than the communications functionality, an unanticipated bistatic radio scattering experiment from Titan’s surface. This the our knowledge the furthest bistatic link experiment established between two spacecrat to date.
In the paper we summarize the high-quality measurements of the 2098 MHz (14.3 cm) postlanding radio signal, focusing on the variations observed in signal strength. The mechanism that creates this pattern is physically interpreted as multipath interference between the direct signal and the signal reflected on Titan’s surface.
A roughness property of pebble sizes in the order of 10cm is finally derived. It should be noted that this measurement is in a completely new direction from the after-landing cameras fixed view, complementing the surface knowledge of the Huygens landing area.
How to cite: Pérez-Ayúcar, M.: Cassini-Huygens bistatic experiment from Titan's surface, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-18991, https://doi.org/10.5194/egusphere-egu25-18991, 2025.
During the Cassini Prime (2004-2008) and Equinox (2008-2010) missions, the Radio Science Subsystem onboard the Cassini spacecraft conducted seven bistatic radar (BSR) observations of Titan, Saturn’s largest moon. A variety of terrains, including unique geological features such as plains and dunes identified by the Cassini RADAR, were observed across equatorial, mid-latitude, and south-polar regions.
In this radio science experiment, Cassini’s High-Gain Antenna (HGA) transmitted unmodulated, right-hand circularly polarized signals at three frequencies—S-band (λ=13 cm), X-band (λ=3.6 cm) and Ka-band (λ=0.94 cm)—toward Titan’s surface. The antenna was pointed to enable quasi-specular reflections from the illuminated portion of the moon’s surface to be received by NASA’s Deep Space Network (DSN) antennas on Earth, which have the capability to receive both left-hand and right-hand circularly polarized components of the reflected signals. The investigation of quasi-specular echoes, when detectable, can provide constraints on surface roughness and near-surface effective dielectric constant, which is connected to the structural and compositional properties of Titan’s terrains.
Analysis of the BSR data from these seven experiments reveals highly heterogeneous scattering behavior across Titan’s surface. Reflections range from barely detectable signals, characterized by broad, diffuse echoes just above the noise floor, to narrower and more powerful reflections suggesting the presence of very smooth and isolated patches of land. Such heterogeneity in surface scattering was also noticed during ground-based observations of Titan by means of the Green Bank Telescope and Arecibo Observatory.
In this work, we present a detailed analysis of this largely unexploited dataset, highlighting regional variations in forward scattering and providing preliminary findings about surface roughness and near-surface dielectric constant of various regions on Titan. Whenever possible, we compare the BSR findings with Cassini SAR maps of Titan’s surface and discuss correlations between scattering variations observed by the two instruments.
How to cite: Brighi, G., Poggiali, V., Mastrogiuseppe, M., Zannoni, M., Hayes, A., and Tortora, P.: Cassini Bistatic Radar Campaign during the Prime and Equinox Missions: Heterogeneous Reflections from Titan's Solid Surfaces, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-18169, https://doi.org/10.5194/egusphere-egu25-18169, 2025.
During Juno’s extended mission, the spacecraft performed four close flybys of the Galilean satellites. Each encounter with a Galilean satellite occurred during the ascending node crossing of the orbit and reduced the orbital period of the spacecraft, phasing the orbit for the subsequent encounter. During each encounter, a radio occultation experiment could be performed using Juno’s radio science instrumentation. During the Ganymede encounter in June 2021 and Europa encounter in September 2022, occultations of the moon’s ionospheres were performed. Both yielded detections of the moon’s ionospheres, with the Ganymede occultation revealing the importance of electron impact ionization. During the close encounters with Io in December 2023 and February 2024, although the spacecraft was not occulted by the limb of the moon, it was occulted by the Alfven wing connecting Io to Jupiter. Increased electron density was detected in the Alfven wing with the occultation method for the first time, providing independent verification of in-situ measurements of the wing. The unique observation geometries of each of these four flybys – a consequence of the complex interaction between Jupiter’s magnetosphere and the moons – required adapting traditional radio occultation techniques to invert the radio frequency measurements into electron density estimates.
How to cite: Buccino, D., Caruso, A., Gomez Casjus, L., Parisi, M., Zannoni, M., Gramigna, E., Coffin, D., Withers, P., Tortora, P., Park, R., and Steffes, P.: The Unique Observation Geometries of Juno’s Radio Occultations of the Galilean Satellites , EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-7170, https://doi.org/10.5194/egusphere-egu25-7170, 2025.
Geodetic calculations concerning gaseous giants hold great importance in planetary astrophysics and fundamental physics, as they provide critical insights into planetary structure, dynamics, and evolution. Advancing our understanding of the shape of gaseous planets is essential for improving the precision of radio occultations—a remote sensing technique used to sound the atmospheres of celestial bodies. Accurate shape modeling also contributes to better constraining interior models, allowing for a deeper understanding of the physical processes governing gas giants and other celestial bodies, including Earth. Such advancements are not only key for refining our knowledge of planetary dynamics but also offer valuable insights into the formation of our stellar system and similar planetary systems. Additionally, these developments facilitate the characterization of exoplanetary atmospheres, which is vital for the study of planets beyond.
The shape of a fluid, rotating celestial body is primarily determined by its rotation rate and internal density distribution, which together define the planet's gravitational potential. This shape is further refined by the effects of zonal winds, which introduce an additional centrifugal term, generating perturbations that can significantly deviate from the profile expected for a solid rotating body. These perturbations are particularly pronounced at low latitudes, where the centrifugal component is most significant. We present a method, building on the approaches of Lindal et al. (The Astronomical Journal, Vol. 90, n. 6, 1985) and Galanti et al. (GRL, Vol. 50, e2022GL102321, 2023), to calculate the shape of a gas giant by harmoniously integrating data from gravity experiments, wind measurements, and radio occultation observations. This integrated methodology allows for a precise estimation of the planet's shape, accounting for both its internal structure and atmospheric dynamics. The results obtained from applying this method to a real case will be illustrated, with a focus on Jupiter. This will be done in light of the most recent gravity experiment data and radio occultation measurements from the Juno spacecraft, as well as the latest zonal wind measurements obtained with the Hubble Space Telescope and James Webb Space Telescope.
How to cite: Fonsetti, M., Caruso, A., Zannoni, M., Tortora, P., Galanti, E., Kaspi, Y., and Smirnova, M.: Geodetic Modeling of Gas Giants: An Integrated Approach Applied to Jupiter, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-16961, https://doi.org/10.5194/egusphere-egu25-16961, 2025.
The main characteristic of Venus that distinguishes it from the other planets is its rotation period, which is very long at 243 Earth days. Although several solutions of this period have been determined using different methods (either from Venus’s orbit or from Earth), this parameter remains poorly constrained. In particular, there is a difference of 7 minutes between the lowest and highest estimates of the rotation period. Currently, only a 3 minute variation in the Length Of the Day (LOD) can be explained by modeling various effects such as the tidal torque exerted on Venus by the Sun and the coupling between the atmosphere and the planet. In our study, we propose a new estimate of the rotation period of Venus using Doppler tracking data from the Venus Express spacecraft. The Venus Express (VEX) mission was launched by the European Space Agency (ESA) in November 2005 and orbited Venus for almost 8 years. The main objective of the mission was to study the planet's atmosphere. To determine a new solution for the rotation period of Venus, we use the Precise Orbit Determination (POD) method, which involves a least-squares adjustment of the difference between the Doppler data collected on Earth and the Doppler data obtained by the numerical integration of forces that can affect the spacecraft's motion. We found a rotation period for Venus of 243.0200 ± 0.0007 days, within the range of values reported in the literature and obtained using different methods and databases. However, the expected periodic variations in the rotation period or the precession rate could not be detected due to the lack of sensitivity of Doppler measurements in the signature of these parameters on the VEX’s trajectory. ESA's EnVision mission, scheduled for launch around 2031, aims to study Venus from its deep core to the top of its atmosphere. We have carried out simulations to predict EnVision's performance. The predicted uncertainty in the rotation period is 0.6 seconds, compared to the uncertainty of 1 minute obtained with VEX. For the precession rate, the predicted uncertainty is 0.2%, compared to 7% obtained with ground-based radar data. The near-polar and low eccentricity of the spacecraft's orbit will provide greater sensitivity to the planet's rotational state.
How to cite: Lévesque, M., Rosenblatt, P., Marty, J.-C., and Dumoulin, C.: Venus' rotation state using Venus Express tracking data and expected outcomes for the EnVision radio-science experiment., EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-16350, https://doi.org/10.5194/egusphere-egu25-16350, 2025.
The Signal of Opportunity using NASA’s Gravity Recovery and Interior Laboratory (GRAIL) radio signals to remotely sense the Lunar ionosphere has been successfully demonstrated. The GRAIL mission consisted of an identical pair of spacecraft approximately 100 km apart in a circular polar orbit around the Moon; during the science mission period, the GRAIL’s X-band Radio Science beacon (RSB) data provide applicability for the radio occultation of the lunar electron density profiles with the uncertainty of frequency residual measurement ~ 1 mHz corresponding to ~ 2 x 108 m-3 electron density uncertainties. We will present our observation updates of the Lunar ionosphere in terms of the near-surface electron profiles versus altitude retrieved from the RSB data to understand its spatial and temporal variations during the GRAIL science mission period. The nature of the lunar ionosphere is a long-standing mystery; GRAIL’s observations of the near-surface electron density profiles and its responses to solar winds and storms impact the near-surface plasma environment.
How to cite: Yang, Y.-M., Oudrhiri, K., Withers, P., Stubbs, T., Erwin, D., and Buccino, D.: Radio Occultation Observations of the Lunar Ionosphere Variations Over GRAIL Mission Period, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-14687, https://doi.org/10.5194/egusphere-egu25-14687, 2025.
NASA’s Europa Clipper flagship mission launched on October 14, 2024 and will arrive at Jupiter in April 2030. There, it will investigate the habitability of Jupiter’s moon Europa. Gravity and Radio Science (G/RS) is one of ten complementary investigations devoted to understanding Europa through studies of its ice shell and ocean, its composition, and its geology. G/RS makes use of the Europa Clipper telecommunications system to obtain radiometric tracking data during the Europa flybys.
Unlike past missions, the primary raw data for the G/RS investigation are obtained from Open-Loop Receivers (OLR) at the Deep Space Network (DSN) ground stations. Indeed, the flyby geometry, spacecraft attitude, and spacecraft antenna configuration are such that the signal-to-noise ratio of the return radio signals will be small (<10 dB-Hz) and insufficient for the typical closed-loop tracking. Processing of the OLR with special retracking algorithms will be necessary to obtain range-rate (Doppler) observations. Given the lack of a stable oscillator onboard Europa Clipper, two-way tracking will be used to achieve high frequency stability, leveraging the accurate DSN clocks. Radio tracking during the flybys will be performed at a single frequency (X-band), so careful modeling of media perturbations is important to maximize the G/RS results. We will discuss recent work to assess the impact of media perturbations from the Io Plasma Torus on orbit reconstruction and geophysical parameter recovery.
G/RS will obtain measurements of Europa’s static and time-variable gravity field. The tidal Love number k2 will verify the presence of a subsurface ocean and help constrain the ice shell. The moment of inertia, derived from degree-2 gravity coefficients, will help determine the interior structure. The radio tracking data will also be sensitive to Europa’s ionosphere when geometry allows.
We will present the G/RS investigation and observation plans, its expected performance, and provide a first look at the tracking data during cruise.
How to cite: Mazarico, E., Buccino, D., Castillo-Rogez, J., Dombard, A., Genova, A., Hussmann, H., Kiefer, W., Lunine, J., McKinnon, W., Nimmo, F., Park, R., Roberts, J., Tortora, P., and Withers, P. and the Europa Clipper G/RS Team: The Europa Clipper Gravity and Radio Science (G/RS) Investigation, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-2924, https://doi.org/10.5194/egusphere-egu25-2924, 2025.
The LUCY spacecraft was launched in 2021. After two gravity assists at Earth and the flybys at binary main-belt asteroid (152830) Dinkinesh in November 2023 and just recently at (52246) Donaldjohanson in the asteroid belt the spacecraft is now on its way to characterize several trojan asteroids. These outer solar system asteroids are located in the Lagrange points L4 and L5 of the Jupiter-Sun system.
The first flyby will be at (3548) Eurybates and its moon Queta in August 2027, followed directly by the flyby at (15094) Polymele with its moon Shaun (informal name) in September 2027. Two more flybys in the so-called Greek camp in the L4 point are at (11351) Leucus in April 2028 and at (21900) Orus in November 2028. After orbiting the Sun once more the spacecraft will reach the L5 swarm of asteroids and will flyby at the binary system of (617) Patroclus and Menoetius in March 2033.
During these flybys the mass of the target asteroids shall be determined using the Doppler tracking method. Analytic solutions for the error estimation of the mass determination have already shown that the required precision will be met. However, this analytic approach does not take into account several error sources like time limited tracking, no Doppler data +/- 2h around closest approach, uncertainties in the initial spacecraft position and velocity for a flyby, non-gravitational forces, etc. Another contributing error source is the Doppler noise imposed on the signal. Doppler data from ESAs Rosetta mission and NASAs New Horizons spacecraft as well as tracking data recorded during the first 3 1/2 years of LUCYs cruise phase could be analyzed regarding distance, solar wind turbulence, integration times etc. A numeric orbit determination using simulated Doppler data can provide the most realistic error estimation using all perturbing forces and uncertainties. A detailed analysis of the error of the mass determination for all flybys shall be presented.
How to cite: Hahn, M., Paetzold, M., Andert, T., Levison, H., Noll, K., and Marchi, S.: Mass Determination of the Lucy Mission target asteroids using radio tracking data, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-19903, https://doi.org/10.5194/egusphere-egu25-19903, 2025.
The UAE’s Emirates Mission to the Asteroid Belt (EMA) is scheduled to launch later this decade. The mission will rendezvous with the water-rich asteroid (269) Justitia, and along the way will flyby 6 different main belt asteroids. The EMA mission goals combine both scientific investigation on the nature of water-rich asteroids and determining the resource potential present in asteroidal bodies. While all of the asteroid flybys will be too fast to enable precise mass estimates, the rendezvous with Justitia will include estimating its mass, gravity field and internal density distribution as a main scientific goal. The approach to be taken will mimic other asteroid rendezvous missions such as NASA’s NEAR, Dawn and OSIRIS-REx missions. Specifically, a combination of optical navigation images along with radio metric tracking from the Earth during an orbital phase will be combined to determine the asteroid precise spin state, total mass, and gravity field coefficients.
Upon arrival at Justitia, the EMA spacecraft will first have a few flybys of the asteroid to determine its overall mass. Following this will be an extended mission phase where it will orbit the asteroid to measure its higher gravity coefficients. After the gravity field is appropriately mapped, the mission will focus on observations of its surface with multi-spectral instrumentation. While the first orbital phase is driven by navigation needs, gravity science will process tracking and optical navigation measurements through all of the orbital phases of the mission in order to produce the highest fidelity gravity field feasible.
This talk will introduce the specific challenges that the EMA mission will need to overcome at Justitia. Challenges and opportunities exist for the orbital phase of the mission, as depending on the precise spin state and total mass of the body, a sun synchronous orbit may be feasible and advantageous for the other imaging instruments. A key scientific result will be the bulk density measurement and comparison of the measured gravity field with the overall shape model of the asteroid, enabling constraints on the internal distribution of material in this body. The talk will also review the expected performance based on mission design and current knowledge of Justitia’s likely shape, spin and density range.
Funding support for the EMA project was provided by the United Arab Emirates Space Agency and its knowledge partner, the University of Colorado Boulder’s Laboratory for Atmospheric and Space Physics.
How to cite: Scheeres, D., McMahon, J., Villa, J., Pugliatti, M., Landis, M., Hayne, P., and AlMazmi, H.: Gravity Science Goals for the UAE EMA Mission, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-13874, https://doi.org/10.5194/egusphere-egu25-13874, 2025.
We describe research and instruments development highlights from ILEWG LUNEX EuroMoonMars Earth Space Innovation EMMESI academy, EuroSpaceHub/GreenSpaceHub partners contributing to MoonMars and space missions, Field Research, Astronautics and Entrepreneurship.
Sample analysis: we analysed various samples including meteorites from Moon, Mars, asteroids, and analogue field samples from campaigns (Vulcano, Etna, Hawaii HI-SEAS) using spectrometry, hyperspectral imaging and Ra-man .
LUNEX also participates in collaboration with TU Delft in the study of ice, minerals and organics mixture relevant for Moon, Mars and icy Moons.
Payload development: we have developed a test bench for sample analysis using reflectance and transmission spec-troscopy, Raman spectroscopy and microscopy. We also adapted an Hyperspectral camera for sample analysis and for telescopic observations of the Moon and other celestial objects. Space Photonics Lab : this is being developed with in collaboration with Fotonika Latvia, with cubesat synergy .
Shoebox instruments for laboratory tests and analogue were developed for future Moon and Mars missions. We are conceiving a concept of a shoebox module for extract-ing organics from icy moons of Jupiter and Saturn, with special prototype for Enceladus plumes or surface. LUNEX ExoGeoLab lander is currently adapted with shoebox instruments for supporting future missions to Moon, Mars and icy moons.
Cubesats for education, EarthMoonMars exploration: LUNEX EMMESI has initiated the development of univer-sity education cubesats with the support of Leiden Univer-sity (Observatory, LIACS computer science, Physics and Optics), Leiden Instrument Schools LiS, Deft TU, InHol-land Delft, ESA BIC.
How to cite: Foing, B. and the TEAM ILEWG LUNEX EMMESI EUROMOONMARS EARTH SPACE INNOVATION 2023-24: Instruments Development and Analogue Simulations: ILEWG LUNEX EMMESI EuroMoonMars Earth Space Innovation 2023-24 Highlights, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-14771, https://doi.org/10.5194/egusphere-egu25-14771, 2025.
The new phase of exploration offers multiple perspectives, for the space community and for many other sectors of activity. But it also brings some threats to the preservation of scientific research and environmental stewardship of Mars. A proactive integration of environmental awareness into the new wave of exploration will be the best way to mobilize public and private stakeholders, federate their resources and their creativity, and preserve for future generations the natural environment of Mars. The new wave of robotic and sample return from Mars will hopefully take place in an era of increased environmental awareness for our own planet, in which close monitoring of environmental impacts of human activities will drive innovative solutions to mitigate them
In this presentation we describe land-use and management policies by various countries and U.S. Agencies in an effort to balance environmental preservation, resource utilization and economic interests. In particular we compare the U.S federal land management system and ecotourism policies with preservation of natural landscapes and resource use. We describe the Mars Sample return re-re-design concepts from the eight selected teams with regard to sustainable exploration of Mars.
How to cite: Smith, H., Blanc, M., and Galli, A.: COSPAR Panel on Exploration (PEX) Exploration Roadmap: The Case for Mars, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-18084, https://doi.org/10.5194/egusphere-egu25-18084, 2025.
The Allende meteorite, which fell in northern Mexico in 1969, is one of the most significant meteorites ever studied. As a carbonaceous chondrite, it represents some of the oldest and most primitive material in the solar system, dating back over 4.5 billion years. It provides insights into the early solar nebula and the processes of planetary formation. Through chemical composition analysis of the meteorite’s refractory inclusions, a deeper understanding of the building blocks of planets and the chemical evolution of our solar system can be gained [1].
In this contribution, we present the chemical composition analysis of a chondrule from the Allende meteorite. A space-prototype Laser Ablation Ionization Mass Spectrometer (LIMS) [2] was used to map a selected chondrule, and the element abundance of more than 19 elements was retrieved and quantitatively studied. The chondrule itself was identified as a porphyritic olivine, depleted in volatiles compared to the surrounding matrix. SEM-EDX and Raman spectroscopy were used for cross-validation.
Unsupervised machine learning (ML) was used to dimensionality reduce and cluster the pre-processed LIMS data to find distinct groups of different chemical compositions. This allowed the separation of the compositionally different materials present in the studied sample and allowed for their comparison [3]. The retrieved element maps suggest the presence of two rims around the chondrule, and their possible formation times and processes will be discussed in this contribution. Furthermore, another approach to reduce the dimensionality of the acquired LIMS data based on image segmentation will be presented, together with a discussion of the benefits and feasibility of applying unsupervised ML on board a spacecraft.
[1] Neuland, M. B. et al., 2021, doi:10.1016/j.pss.2021.105251.
[2] Riedo, A. et al., 2012, doi:10.1002/jms.3104.
[3] Gruchola, S. et al., 2024, doi:10.3847/PSJ/ad90b6.
How to cite: Gruchola, S., Keresztes Schmidt, P., Riedo, A., Tulej, M., and Wurz, P.: Composition Analysis of an Allende Chondrule using a Space-Prototype Laser Ablation Ionization Mass Spectrometer, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-11994, https://doi.org/10.5194/egusphere-egu25-11994, 2025.
In contemporary laboratory settings, there is a need for flexible and immediate approaches to updating, sharing, and analyzing acquired data. With this vision in mind, we initiated the development of the SLab Tools package at INAF-IAPS, which supports the Spectroscopy Laboratory (SLAB) dedicated to visible and near-infrared reflectance spectroscopy. SLab Tools comprises a database, a web app, and a Windows 10/11 app designed to streamline laboratory work.
As we developed the components, we decided to enhance the initial idea by transforming the SLab-dedicated app into a more general and flexible multi-platform app, offering a broader range of features. Consequently, the project was renamed HyperLab.
HyperLab aims to provide seamless access to SLab data and various statistical algorithms. It is also gaining the capability to open and analyze scientific files saved in the PDS format. Key goals of the project include: a) Simplifying routine tasks for laboratory personnel by relating multiple acquisitions and correlating them with supplementary information on measurements and samples. b) Enhancing the value of scientific data by sharing it with the research community. c) Providing the community with a modern tool that can be accessed via phone or tablet.
HyperLab's features include applying smoothing functions, calculating a continuum-removed spectrum with real-time visualization, and computing common absorption band parameters such as band center, band depth, and band area.
Significant effort has been invested in developing features related to the SLab setup, which played a crucial role at the project's inception. This includes allowing users to apply different data analysis techniques to spectra and accessing ancillary information such as sample type, category (mineral, rock, meteorite, synthetic), and acquisition geometry.
Both the web application and the multi-platform app are designed to offer the same comprehensive functionalities when working with SLab data, ensuring users can seamlessly switch between platforms without losing access to any features. The web app plays a pivotal role in the overall architecture by functioning as both the back-end for the multi-platform app and a self-contained web tool. It is responsible for managing data searches and handling the saving and retrieval of data from the database.
Acknowledgments: This project was funded by INAF in 2023 under the ‘Call for Funding of Fundamental Research 2023’, in the Data Analysis Grant category.
How to cite: Carraro, F., Carli, C., and Fonte, S.: HyperLab Project, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-8332, https://doi.org/10.5194/egusphere-egu25-8332, 2025.
The ESA Planetary Science Archive (PSA) hosted at the European Space Astronomy Centre (ESA/ESAC) is a multi-mission archive currently supporting ten planetary missions, from missions beyond their post-operations phase to missions currently being operated. The data are being archived following the NASA Planetary Data System (PDS) Standard (version 3 or 4, depending on the mission). Missions currently in operations or within their cruise phase, such as ExoMars Trace Gas Orbiter (TGO), BepiColombo, and JUICE, archive the data in PDS4 format and follow the concept of operational archiving, where data are regularly generated and delivered to the PSA in small batches (e.g. daily). The PSA provides various means to access these data: through a web User Interface (UI), a secure FTP server, or via programmatic access with the EuroPlaNet Table Access Protocol (EPN-TAP) to the data holdings. The PSA supports data access with different proprietary status (either public or private when within their proprietary period) to ensure adequate support to the mission instrument teams. Ongoing developments with the integration of the PSA in the ESA Datalabs platform open additional ways to access and visualise the data directly from a web browser. In this work, we will illustrate the different means of searching for, downloading, and using the PDS4 planetary data archived in the PSA.
How to cite: Cornet, T., Bentley, M. S., Coia, D., Docasal, R., Grotheer, E., Heather, D., Lim, T., Oliveira, J. S., Osinde, J., Raga, F., Ramos, G., and Sainz, J.: Data in the ESA Planetary Science Archive: A cookbook to access them , EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-15928, https://doi.org/10.5194/egusphere-egu25-15928, 2025.
The Electron Drift Instrument(EDI) onboard of four Cluster spacecrafts measures electric filed E in the near Earth orbit. By measuring a drift of 1keV electrons the instrument determines the value of the electric field E in the plane perpendicular to the magnetic field B.
The Cluster mission life-time is more then 20 years. Over this time the EDI provides data for electric field, drift velocity, electron counts. Data are provided with various time intervals from milliseconds to 4seconds. Therefore it is possible to track fast changes in boundaries.
Instrument teams collect data, extracts physical values from raw data, calibrate them and deliver these values as data products to ESA central archive.
Once the instrument is in space many aspects of data handling become routines and can be automated. In the last decade the industrial big data segment produced many tools that can be used to automate scientific data processing.
How to cite: Rashev, M. and Daly, P.: Data archive for EDI instrument on Cluster spacecrafts: measurements and data processing, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-2166, https://doi.org/10.5194/egusphere-egu25-2166, 2025.
We propose an instrument, MsRAIN designed to investigate the feasibility of creating artificial rain outside Earth and in low gravity conditions. MsRAIN is the second generation of instruments, where the first generation was tested onboard the International Space Station (ISS) in May 2023 through the Saudi Space Agency (SSA) Cloud Seeding in Microgravity Experiment. MsRAIN is designed to work in future human colonies on the Moon and Mars as it can help in having a better spatial distribution of water on the colonies.
MsRAIN is composed of four hydrophobic chambers each containing an air pump, small water container, humidifier, silver iodide container, meteorological sensors, power supply, and high-speed cameras.
The core perspective in MsRAIN is that physical experiments are needed to understand the possibility of artificial rain formation on the Moon and Mars. Little is known about the behavior of condensation of water vapor on aerosol particles in reduced (fractional) gravity environments (less than the nominal 1 g that occurs on Earth).
On Earth, cloud seeding missions are widely used in many countries to enhance the amount of precipitation in rain scarcity regions, however, the seeding agents (silver iodide for example) sprayed in the air can be affected by the Earth’s gravity and fall to the ground and to the water bodies which can affect the environment. The lower gravity conditions on the Moon and Mars could help seeding agents stay longer in the atmosphere (if any), consequently providing a better chance for the formation of water droplets.
The MsRAIN payload team is led by mid-career scientists, engineers, graduate, and undergraduate students from different research institutes in Saudi Arabia. The team includes SSA and the King Fahd University of Petroleum and Minerals (KFUPM).
How to cite: Farahat, A. and Smith, H.: Examining MsRain for the Possibility of Creating Artificial Rain with Cloud Seeding Techniques on the Moon and Mars Future Human Settlements , EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-1412, https://doi.org/10.5194/egusphere-egu25-1412, 2025.
Study Problematics
Space situational awareness (SSA) main object is to produce as real-time an overall picture of the space situation as possible. By developing abilities, methods and models to observe objects and bodies located in near Earth space and by predicting space weather phenomena, the risks of damage to both people and property caused using space can be reduced.
In this study discussion we focus into problematics that we have especially with the final phase trajectory calculations for space debris, deorbiting satellites and other bodies. Despite we can know the orbits of the satellites or debris very well, the final atmospheric entry determination is challenging. This challenge will be discussed and the main elements of future improvements that should be developed to reach more precise determination capabilities will be introduced. The main problematics to predict the atmospheric entering bodies (manmade and natural) can summarized to following focus areas:
- Earth atmosphere is not perfect circle in real life. Space weather events cause significant changes in the upper atmosphere composition and altitude [1] [2].
- Satellites aren’t optimal nor unified in shape and satellite mass is not really known. Satellite models for de-orbiting calculations simplifies [3] the shape and surface area of the satellite.
- The velocity of the satellite is high and hard to follow in the end and angle of attack of the atmospheric re-entry is unclear.
FSSAC Probabilistic Solution Approach
The Finnish Space Situational Awareness Center (FSSAC) is developing systems to estimate the impact areas and effects of space objects entering Earth’s atmosphere. Accurate orbital parameters are critical for determining impact points [4], but publicly available data, such as TLEs processed with the SGP4/SDP4 model, lack precision. These datasets are updated infrequently and exclude certain objects, such as military satellites.
To address this, FSSAC integrates additional data like covariance matrices, SGP4-XP, CPF, and Sp3c products, alongside Satellite Laser Ranging (SLR) data. The Metsähovi SLR telescope is being upgraded with a new laser emitter to expand coverage of RSOs, enhancing orbit modeling accuracy. Reliable atmospheric models are also essential, but existing options, such as NRLMSISE‐00 [5], are outdated and can produce errors of 20–30% during high solar activity.
FSSAC is advancing atmospheric models and orbit propagation tools to support accurate re-entry predictions. These efforts aim to provide timely warnings for high-risk RSOs, prioritizing public safety.
References
[1] https://www.ilmatieteenlaitos.fi/ajankohtaista/1244013
[2] Baruah, Y., et.al. (2024). “The loss of Starlink satellites in February 2022: How moderate geomagnetic storms can adversely affect assets in low-earth orbit”. Space Weather, 22, e2023SW003716. https://doi.org/10.1029/2023SW003716
[3] https://sdup.esoc.esa.int/
[4] Pardini, Carmen, and Luciano Anselmo. "Overview of some basic requirements for a reentry prediction service for civil protection applications." Proc. 1st NEO and Debris Detection Conference, Darmstadt, Germany. 2019.
[5] Picone, J. M., et al. ”NRLMSISE-00 empirical model of the atmosphere: Statistical comparisons and scientific issues”, JGR Volume107, IssueA12, 2002, https://doi.org/10.1029/2002JA009430
How to cite: Haukka, H., Nyman, L., Harri, A.-M., Kestilä, A., Genzer, M., Koskimaa, P., Knuutila, O., and Jaakonaho, I.: Trajectory calculations problematics with the Earth atmosphere entering bodies and FSSAC probabilistic solution approach, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-4088, https://doi.org/10.5194/egusphere-egu25-4088, 2025.
The proliferation of space objects is increasingly becoming a large concern, with mega-constellations in low Earth orbit (LEO) exponentially increasing active spacecraft numbers, now over eleven thousand. The Pervasive Sensing group at the University of Birmingham is exploring a method of opportunistic observations of these spacecraft from a dedicated satellite equipped with a high-resolution sub-THz inverse synthetic aperture radar (ISAR) imaging payload [1]. The work includes orbit identification, optimised conjunction analysis and encounter parametrisation. We also demonstrate the use of a novel radar simulation technique – the Graphical Electromagnetic ISAR Simulator for Sub-THz waves (GEIST) [2] – to synthesise large datasets of radar images from diverse perspectives. This is linked with the Pervasive Sensing group’s development of heuristic and ML-based classification techniques [3] to identify satellite anomalous behaviour and/or damage to external infrastructure.
[1] E. Marchetti et al., "Space-Based Sub-THz ISAR for Space Situational Awareness—Concept and Design," in IEEE Transactions on Aerospace and Electronic Systems, vol. 58, no. 3, pp. 1558-1573, June 2022, doi: 10.1109/TAES.2021.3126375
[2] G. Jones et al., "Novel Simulation Method for Sub-THz ISAR Imaging of Space Objects," 2024 21st European Radar Conference (EuRAD), France, pp. 272-275, doi: 10.23919/EuRAD61604.2024.10734967.
[3] M. Coe et al., "Segmentation and Classification of Sub-THz ISAR Imagery," 2024 International Radar Symposium (IRS), Poland, pp. 233-238, ieeexplore.ieee.org/document/10645054
How to cite: Jones, G., Coe, M., Beesley, L., Hart, T., Karikari, E., Pope, F., Gashinova, M., and Alconcel, L.-N.: Opportunistic LEO spacecraft observation with space-borne sub-THz ISAR imaging, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-5152, https://doi.org/10.5194/egusphere-egu25-5152, 2025.
M-MATISSE is one of the three mission candidates for the ESA M7 science mission call, all currently passing the Phase A with selection of the mission expected in the middle of 2026 and a possible launch at 2037. The M-MATISSE proposal involves two spacecraft (Henri and Marguerite) with almost identical scientific payload to investigate the Mars plasma environment from two vantage points on different elliptical orbits simultaneously. The main goal of M-MATISSE is, for the first time at Mars in its complexity, to explore, characterize and ultimately understand the global dynamic response of the near-Mars plasma environment to solar wind dynamics, solar energetic events and flares. In the scope of the mission is to study the dynamics induced at Mars’ environment during quiet and extreme solar wind conditions, i.e. space weather effects on the system, including the crucial lower layers of the ionosphere connecting the Mars surface and space, so far only infrequently sampled by existing missions. Also, M-MATISSE would provide essential data to enable forecasting of potential global hazard situations in robotic and human exploration of Mars. The proposed M-MATISSE configuration involves six scientific instruments on both spacecraft, two of them being actually consortia of several scientific sensors with common data processing units.
The Solar Particle at Mars (SP@M) experiment is a part of the Mars Ensemble of Particle Instruments (M-EPI) suite of three particle sensors. SP@M will study distributions of 30 keV to 1 MeV electrons and 30 keV to 10 MeV ions with 4 electron and 4 ion telescopes per spacecraft aiming to monitor parallel/antiparallel/ perpendicular to interplanetary magnetic field fluxes of energetic particles. In this contribution we focus on the description of the SP@M design as achieved in the middle of the Phase A, ongoing development activities incl. digital signal processing and electron-ion discrimination, and performance simulations. The scientific tasks of SP@M will be presented as well.
How to cite: Prech, L., Nenon, Q., Devoto, P., André, N., Thomas, V., Nemec, F., and Sanchez-Cano, B.: Solar energetic particle instrument SP@M for ESA M7 mission candidate M-MATISSE, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-6435, https://doi.org/10.5194/egusphere-egu25-6435, 2025.
Magnetometers are prime instruments of scientific spacecraft targeting the space plasma environments of solar system bodies. Despite extensive ground calibration efforts, regular inflight calibration activities of these magnetometers have shown to be crucial to maintain necessary data quality levels over time. Classically, 12 parameters influence the calibration: 3 gain values, 6 angles defining magnetic sensor orientations, and 3 zero level offsets that correspond to instrument outputs in vanishing ambient fields. Particularly in low fields, accurate choice of offset levels are of utmost importance. To achieve this, measurements of Alfvénic fluctuations in the solar wind are typically used. We investigate the influence of sensor noise levels on the accuracy of different calibration parameters, particularly on the offsets, using THEMIS/ARTEMIS magnetic field measurements.
How to cite: Timmermann, G., Kolhey, P., Auster, H.-U., Richter, I., and Plaschke, F.: Influence of sensor noise levels on magnetometer calibration parameters, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-8702, https://doi.org/10.5194/egusphere-egu25-8702, 2025.
NASA's upcoming Dragonfly rotorcraft mission is planned to be deployed to the surface of Saturn’s moon Titan [1]. As part of the Dragonfly Entry Aerosciences Measurements (DrEAM) suite [2], the Dragonfly entry capsule will include a subsystem known as the COmbined Sensor System for Titan Atmosphere (COSSTA). This subsystem is being developed by the Supersonic and Hypersonic Technologies Department at the DLR Institute of Aerodynamics and Flow Technology, in collaboration with NASA. One of the components of COSSTA is a pressure sensor developed by the Finnish Meteorological Institute (FMI). This sensor, named COSSTA-PL, is designed to measure static pressure on the entry capsule's backshell.
The sensor is based on FMI’s pressure sensors previously developed for Mars landers, mostly sharing its design with MEDA PS [3], the pressure sensor of the Perseverance rover. Its core components, the Barocap® pressure sensor heads, are developed by Vaisala. The optimal measurement range of COSSTA-PL is up to about 10 hPa, but it has a capability to measure pressures up to at least 20 hPa.
Due to possible exposure to extremely cold temperatures during the long cruise, several tests have been performed with a prototype model and individual components to confirm that the sensor endures temperatures down to -150 °C. The pressure calibration is planned to be performed mainly at FMI in the 0 to 20 hPa pressure range and -70 to +55 °C temperature range, and calibration down to -150 °C (TBC) is continued at the COSSTA level.
References
[1] Lorenz, R. D. et al. (2018). Dragonfly: A Rotorcraft Lander Concept for Scientific Exploration at Titan, Johns Hopkins APL Technical Digest 34(3), pp. 374-387.
[2] Brandis, A. et al. (2022). Summary of Dragonfly’s Aerothermal Design and DrEAM Instrumentation Suite, 9th International Workshop on Radiation of High Temperature Gases for Space Missions, 12 – 16 Sep 2022, Santa Maria, Azores, Portugal.
[3] Jaakonaho, I. et al. (2023). Pressure sensor for the Mars 2020 Perseverance rover, Planetary and Space Science 239, 105815, https://doi.org/10.1016/j.pss.2023.105815.
How to cite: Jaakonaho, I., Hieta, M., Genzer, M., Polkko, J., Thiele, T., Harri, A.-M., and Gülhan, A.: COSSTA-PL - Low-pressure sensor for Dragonfly entry capsule, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-10176, https://doi.org/10.5194/egusphere-egu25-10176, 2025.
On 14 April 2023, the JUICE spacecraft was launched to the Jovian system to study the emergence of potentially habitable worlds around gas giants. The Neutral-Ion Mass Spectrometer (NIM), developed by the University of Bern, will characterise the atmospheres of the Galilean moons and analyse subsurface material ejected by Europa’s plumes. NIM uses a power-efficient hot cathode filament which creates an electron beam to ionize atoms and molecules for mass spectrometric analysis.
For this mission, we employ customized yttrium oxide (Y2O3) cathodes produced by Kimball Physics, based on the ES-525 design. For example the filament legs are lengthened to minimize heat loss through conduction. Additionally, a thicker coating is applied to enhance longevity. Given the criticality of correct cathode operation, two cold-redundant cathodes are installed in the NIM instrument.
This study compares the performance of the space-qualified cathodes in the Proto Flight Model (PFM) instrument, post-launch (in orbit) commissioning, with both expected performance metrics and laboratory-tested cathodes in the Flight Spare (FS) instrument.
During commissioning, the PFM cathodes underwent conditioning lasting several hours. While both cathodes were successfully conditioned, cathode 2 exhibited performance comparable to FS cathodes, whereas cathode 1 deviated from the pre-flight performance. This deviation was further investigated through additional investigations and tests. Preliminary findings suggest that launch-induced vibrations caused slight bending of the cathode legs, resulting in asymmetry between the emitting disk and the surrounding repeller electrode.
The cathodes operate within a nominal emission range of 100 to 300 μA. Without active beam shaping, power consumption varies between 1.2 and 1.6 W (up to 1.8 W for the deviating PFM cathode 1) with a current draw of 860 to 980 mA (up to 1030 mA). Optimal beam shaping increases the current requirement by approximately 20 mA. Despite limited available data, we successfully fit our measurements to the Richardson-Dushman equation, describing the relation between operation parameters and emission current, enabling a comparison with theoretical emission expectations.
The heating current drawn by the cathode is expected to increase over the long term (up to a lifetime of 10,000 operational hours) due to degradation of the coating. In contrast, short-term behaviour (up to 100 hours) reveals a "learning" effect: cathodes exhibit improved performance when used under specific active beam-shaping configurations, an effect disrupted after exposure to air.
During the post-launch commissioning of the cathodes in orbit, the LV subsystem was commissioned as well. The commissioning, including the cathodes, bake-out heater, low-voltage electrodes, as well as the necessary electronics was successful. Long-term monitoring of the cathodes' performance in both laboratory and space environments continues.
How to cite: Wyler, S. S., Fausch, R., Vorburger, A., and Wurz, P.: Post Launch Performance of a Hot Cathode for Electron Ionization of a Space Borne Time-of-Flight Mass Spectrometer (NIM on board JUICE), EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-10630, https://doi.org/10.5194/egusphere-egu25-10630, 2025.
Since 2009, the Lunar Reconnaissance Orbiter (LRO) has been mapping the Moon to unprecedented detail, capturing, among others, high-resolution images and altimetric profiles to acquire invaluable datasets for understanding its evolution. Transforming this wealth of data into detailed maps and terrain models depends on the accurate determination of the spacecraft's trajectory. This is achieved through a precise orbit determination process, which relies on radio tracking data acquired by ground stations. Furthermore, the orbit determination of LRO can allow scientists to refine estimates of the Moon's geophysical parameters (e.g., gravity field, tidal response), advancing our understanding of its internal structure and history (Goosens et al., 2024; Mazarico et al.,2014).
The reliability of these estimates is intrinsically tied to the accuracy of the spacecraft's orbit reconstruction. LRO's motion is influenced by various perturbative forces, among which non-conservative forces, such as the pressure exerted by solar or planetary radiation, pose significant challenges. These forces, typically small in magnitude, are complex to model accurately. An incorrect modeling of non-gravitational effects can introduce errors in orbit determination that build up over time, leading to biases in scientific measurements and potentially resulting in incorrect interpretations of the Moon's geophysical properties.
To mitigate the errors introduced by mismodelling, a multi-arc approach is typically employed in the orbit determination process, dividing the mission timeline into shorter arcs. However, this approach reduces sensitivity to long-term gravitational signals, such as those originating from the Moon’s inner core. By refining the spacecraft's dynamical model, it becomes possible to extend the duration of the arcs, potentially enabling the recovery of previously undetected signals and a better understanding of the Moon’s interior. The availability of LRO’s extensive radiometric data, recorded during intervals unaffected by wheel off-loading maneuvers, offers an ideal dataset for developing and testing more refined physical-numerical models.
This work focuses on enhancing the modeling of non-gravitational accelerations acting on the LRO to detect long-term lunar gravity signals. To address this task, we test innovative modelling techniques based on ray-tracing methods and compare them against traditional approaches to evaluate their accuracy and effectiveness. Our results show that the ray-tracing is a powerful tool to refine the dynamical model of the spacecraft for planetary geodesy and geophysics investigations. This framework not only helps obtaining an accurate trajectory reconstruction but also provides a means for gaining deeper insights into the Moon's internal dynamics, contributing to a more comprehensive understanding of its geophysical and evolutionary processes.
How to cite: Zurria, A., Cascioli, G., Mazarico, E., and Iess, L.: Refining Non-Conservative Force Modeling of LRO for Long-Term Lunar Gravity Signals, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-12150, https://doi.org/10.5194/egusphere-egu25-12150, 2025.
De-orbiting via re-entry into the Earth's atmosphere is the modus operandi of end-of-life LEO satellite disposal despite the uncertainties regarding the impact of ablated materials and intact debris. Elements that have never existed naturally within our atmosphere, such as hafnium and niobium, which originate solely from ablated satellites and rocket bodies, have already been detected in the stratosphere. This ablated material will only increase as early- and next-generation LEO constellations reach the disposal phase of their lifecycle. Starlink alone has requested to add a further 30,000 satellites to their existing mega-constellation, with others following suit. Of particular interest are the re-entry mass and fluxes of very high melting point de-orbiting materials that are unlikely to ablate, such as the laser medium used in inter-satellite optical communication links. We present the results of a preliminary study into the projected mass and geographic fluxes of ablated material and intact objects into the upper atmosphere.
How to cite: Beesley, L., Whitlock, P., Hart, T., Karikari, E., Pope, F., and Nani-Alconcel, L.: Survey of the estimated mass of ablated material and intact debris from 'end-of-life' LEO spacecraft entering the atmosphere, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-12796, https://doi.org/10.5194/egusphere-egu25-12796, 2025.
The JUpiter ICy moons Explorer (JUICE), the European Space Agency’s first large-class mission under the Cosmic Vision 2015–2025 program, is dedicated to exploring the potential habitability of Jupiter’s icy moons: Europa, Callisto, and Ganymede. Launched on April 14, 2023, JUICE is currently in an 8-year cruise phase to Jupiter, utilizing gravity assists from Venus, Earth, and the Moon. Notably, JUICE is the first spacecraft to execute a Lunar-Earth gravity assist (LEGA), which was successfully completed in August 2024. This maneuver provided a critical trajectory adjustment while also allowing several onboard instruments to operate during the flyby.
Shortly after the Moon gravity assist, JUICE experienced an unforeseen acceleration attributed to an outgassing event. During the LEGA, radiometric observables, including Doppler and ranging data in the X-band, were collected by ESA’s New Norcia deep space station. These measurements were analyzed to characterize the outgassing-induced delta-V acting on JUICE. The analysis involved reconstructing the outgassing event and comparing it with models. The characterization of this event using radiometric data provides insights that complement measurements from other onboard instruments. For instance, the spacecraft’s reaction wheels recorded an excess torque as they compensated for the perturbation to maintain attitude control. The High-Accuracy Accelerometer (HAA), the Particle Environment Package (PEP), and the Submillimetre Wave Instrument (SWI) also captured data related to the outgassing event, enhancing its overall characterization.
In this work, we analyze radiometric measurements to provide a detailed quantification of the magnitude and orientation of the outgassing force during the flyby. These findings improve our understanding of non-gravitational forces affecting JUICE and contribute to refining our knowledge of the spacecraft's dynamical environment.
How to cite: Cappuccio, P., Sesta, A., Syndercombe, T., De Filippis, U., Durante, D., Di Benedetto, M., and Iess, L.: Estimation of Spacecraft Outgassing During the Lunar-Earth Gravity Assist of JUICE Using Radiometric Observations , EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-16492, https://doi.org/10.5194/egusphere-egu25-16492, 2025.
This study aims to investigate the potential and feasibility of multi-sensor image integration to combine images from orbital or airborne platforms with rover-based images in planetary exploration. We use images taken with the airborne Modular Aerial Camera System (MACS) and a hand-held camera, the Integrated Positioning System (IPS), on a steep hillside on Vulcano Island, Sicily. Typical use-cases in planetary exploration are for robotic navigation, localization of exploration targets or improved target coverage combining additional viewpoints.
MACS was operated on a Vertical Take-Off and Landing (VTOL) drone. The images were used to simulate the orbital images overflying the hillside, while the IPS images were used to simulate a ground-based platform (e.g. rover). The aerial images were taken at a constant height level, resulting in different distances to the ground due to elevation changes in the terrain. The IPS images are taken with a 16mm lens camera mounted diagonally upwards relative to the other sensors on the system. The hillside is captured along a path that is approximately parallel to the steep scarp, maintaining a distance of at least 100 meters from it. Images are taken at multiple stops always covering the whole hillside with a swivel movement. This simulates different stereo angles to experiment with later during 3D reconstruction. The resulting dataset includes images from two different sensors with a high viewpoint discrepancy. We evaluate the performance of image matching when using this dataset regarding among other things varying scales, resolution and wavelength. Also, we investigate terrain specific influences on the matching quality as well as methods to overcome the viewpoint discrepancy between MACS and IPS images, resulting in large image parallaxes and local variation of the difference in image resolution. Lastly, we evaluate the quality of resulting 3D reconstruction as well as of the estimated intrinsic and extrinsic camera parameters and the possibility for their improvement.
We compare the results to earlier tests based on orbital planetary images, using various different matching methods. An evaluation with focus on feature-based matching approaches was done on images coming from the High Resolution Stereo Camera (HRSC) on ESA’s MarsExpress mission [1, 2]. Multiple performance metrics were analyzed which showed that different methods excel under different criteria. Also, it emphasized the need for a certain richness in features to ensure precise and accurate points. A majority of feature detectors reach subpixel accuracy, but only in feature rich images, while cross-correlation points as input to least-squares matching (LSM) [3] outperform otherwise.
[1] Schriever, A. and Gwinner, K., EPSC 2024, DOI: 10.5194/epsc2024-986
[2] Jaumann, R., et al. PSS 55 (7–8), 928–952 (2007) DOI: 10.1016/j.pss.2006.12.003.
[3] Gwinner, K., et al. PE&RS 75(9), 1127-1142 (2009), DOI 10.14358/PERS.75.9.1127
How to cite: Schriever, A., Gwinner, K., Irmisch, P., Kraft, T., and Brauchle, J.: Experimental Study of Image Matching Techniques for Co-Registration and Data Fusion of Orbital and Ground-Based Planetary Images, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-16985, https://doi.org/10.5194/egusphere-egu25-16985, 2025.
Hera, the European Space Agency’s pioneering planetary defense mission, was successfully launched on October 7, 2024, from Cape Canaveral aboard a SpaceX Falcon 9 rocket. This milestone marks a critical step in the Asteroid Impact and Deflection Assessment (AIDA) collaboration, which Hera undertakes in synergy with NASA’s DART mission. The mission's primary objective is to perform an in-depth post-impact analysis of the Didymos binary asteroid system, focusing on Dimorphos, the smaller moon that served as DART’s impact target.
Hera’s investigations aim to evaluate the effectiveness of the kinetic impactor technique as a method for asteroid deflection, while also providing critical insights into the physical and compositional characteristics of Dimorphos. These findings will not only refine our understanding of asteroid behavior under kinetic impact but also contribute to developing strategies for planetary defense against potential future asteroid threats.
Central to Hera’s scientific approach is its advanced radio science experiment. This includes an X-band radio link, which supports high-precision Earth-based two-way range and range-rate measurements, alongside Delta-Differential One-Way Ranging (Delta-DOR) observations. Additionally, the mission leverages inter-satellite ranging between Hera’s main spacecraft and its two CubeSats, Juventas and Milani, complemented by optical navigation imaging and altimetry data. Together, these techniques will significantly enhance the accuracy of Hera's data and allow for a more comprehensive reconstruction of the impact event and its aftermath.
This work provides a summary of the Hera radio science experiment investigation, the experimental framework and operational plans during its cruise phase and its close-proximity operations at the Didymos system. Furthermore, it discusses the expected scientific outcomes of Hera’s radio science experiment, emphasizing its pivotal role in advancing planetary defense capabilities and contributing to the broader goals of asteroid science.
How to cite: Gramigna, E., Tortora, P., Lasagni Manghi, R., Zannoni, M., Park, R. S., Tommei, G., Le Maistre, S., Scheeres, D. J., Kueppers, M., and Michel, P.: The Radio Science Experiment on Hera, Juventas and Milani, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-17955, https://doi.org/10.5194/egusphere-egu25-17955, 2025.
The European Space Agency mission LUMIO (Lunar Meteoroid Impacts Observer) aims to characterize the lunar and near-Earth meteoroid environment by imaging impact flashes on the far side of the Moon. During its 1-year operative phase along a quasi-periodic Halo orbit about the Earth-Moon Lagrangian point L2, LUMIO will observe the lunar far side while keeping its line of sight to the Earth unobstructed. With this geometry, the LUMIO spacecraft may be the first miniaturized satellite to exploit its radio communication system to carry out bistatic radar observations of the near-limb regions of the Moon, which may help characterize the surface roughness and dielectric constant around recent impact sites. Furthermore, high-frequency VIS-NIR images collected by the LUMIO-Cam during science operations represent an opportunity for testing innovative orbit determination techniques, such as using precise timing of stellar occultations to complement ground-based radiometric measurements. Stellar occultation measurements are expected to improve the navigation accuracy during science observation windows, aiding in absolute positioning of the impact sites and reducing the reliance on ground tracking. This work will outline the proposed LUMIO Radio Science Experiment, its main objectives, and expected performances, highlighting the potential of bistatic radar observations and stellar occultations to enhance the characterization of lunar impact flashes.
How to cite: Lasagni Manghi, R., Brighi, G., Banzi, D., Gomez Casajus, L. A., and Ferrari, F.: The LUMIO Radio Science Experiment, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-19429, https://doi.org/10.5194/egusphere-egu25-19429, 2025.
The multiple space particle spectrum analyzer has been proposed as the scientific payload of the Formosat-8C satellite (FS-8C). This multiple space particle energy spectrometer is a small, low-weight, low-power consumption advanced analyzer. Its design was originally derived from the STE (Supra Thermal Electron) detector on the STEREO satellite. This analyzer uses an evolved a multi-channel detector component, which can measure electrons and ions in the energy range of approximately 1 ~ 200 keV, and can establish high-energy neutral atom imaging, hoping to provide information to the space science community more valuable data. The prototype of this payload has been initially produced, and it can comply with the overall interface specifications of the FS-8C, including a size of < 2U, a weight of < 5kg, an average orbital power consumption of less than 2W. We expect to complete the delivery of the flying model in September 2026 according to the schedule.
How to cite: Chiang, C.-Y., Chang, T.-F., Yen, T.-E., Cheng, Y.-T., Chen, C.-T., Cheng, Y.-R., Tsai, S.-C., Kuo, P.-Y., Chan, C.-H., Li, P.-J., Liu, P.-J., and Hung, T.-P.: Design and Development of multiple space particle energy spectrum analyzer, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-20702, https://doi.org/10.5194/egusphere-egu25-20702, 2025.
All-Sky Electrostatic Analyzer (A-ESA) is a scientific payload that will be mounted on a lunar rover and is designed to observe the variations of plasma environment on the Moon. A-ESA is composed of an electrostatic analyzer on the top, and an MCP assembly, power supply units and electronics are located under it. A-ESA has the entrance scanning deflectors and the inner scanning deflectors. The entrance of A-ESA is electrically scanned within ~90∘in vertical direction, i.e. A-ESA has hemi-spherical field of view (FOV). When A-ESA is operating in observation mode, the collection of science data is divided into 8 parts in horizontal direction and 6 parts in vertical direction. And it generates 16 energy levels via sweeping high voltage. Therefore it can measure the plasma distribution function and charged particle energy in hemi-sphere space on the lunar surface. Since the launch of the science payload project, PDR, CDR, TRR and PAR reviews have been completed. Now we are carrying out function tests and performance tests. Initial function tests between A-ESA and the lunar rover have been performed too. At the end of 2024, the A-ESA has been delivered to Taiwan Space Agency (TASA).
How to cite: Chang, T.-F., Chiang, C.-Y., Tsai, S.-C., Cheng, Y.-R., Yen, T.-E., Huang, Z.-Y., Chan, C.-H., Chen, C.-T., Li, P.-J., Liu, P.-J., Cheng, Y.-T., Kuo, P.-Y., Hung, T.-P., Lyu, Y.-T., Tsai, C.-L., Shiu, S.-H., Tsai, J.-R., and Lin, S.-F.: Development of the All-Sky Electrostatic Analyzer for a Lunar Rover, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-20719, https://doi.org/10.5194/egusphere-egu25-20719, 2025.
Martian atmosphere consists dominantly of CO2 gas. Observations of atmospheric CO2 amount would provide crucial knowledge on Martian CO2 annual cycles, surface air pressure variations, and atmospheric dynamics including dust storms. This team explores a great potential to use a Martian differential absorption lidar (DIAL) operating at the 2-um CO2 absorption band for the purpose. For the considered system, closely-spaced wavelengths are selected so that Martian environmental impacts such as surface reflection, atmospheric scattering, and absorption from other trace gases on the lidar return signals are very similar, but the difference in CO2 absorption is substantial. The Martian CO2 amount and surface air pressure could be retrieved from the measured CO2 differential absorption optical depth at the selected wavelengths. Simulation studies found that return signals from the surface for a Martian space-borne CO2 DIAL system could have sufficient signal strengths that allow column CO2 amount and surface air pressure measurements with 1% and 1 Pa precision, respectively, after horizontally 5 km averaging under normal weather/dust conditions. These CO2 and pressure measurements would significantly improve Martian weather and climate modeling and prediction. Current study of the Martian CO2 DIAL system and laboratory experiments show that a 2-um CO2 DIAL system for Martian atmospheric applications can be developed with existing fiber laser and lidar technologies. These results indicate that Martian space-borne CO2 DIAL systems significantly improve next-generation Mars’ weather and climate predictions and greatly benefit future human Mars explorations. We report the latest progress in the lidar development including certain instrumentation and laboratory experimental results.
How to cite: Campbell, J., Liu, Z., Geng, J., Lin, B., and Yu, J.: 2-um Differential Absorption Lidar for Martian Atmospheric CO2 and atmospheric Pressure measurements, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-13826, https://doi.org/10.5194/egusphere-egu25-13826, 2025.
Phase Change Materials (PCMs) are increasingly recognized for their potential in effective thermal management of space systems. PCM based heat accumulators maintain the temperature stability of electronic payloads in Spacecraft, Orbiters, and Landers, ensuring their reliability during operations. The primary challenge lies in understanding the complex convection dynamics that occurs during the solid-liquid phase transition. Key factors influencing the phase change dynamics in a space or planetary environment include the absence of atmospheric pressure, variations in incident heat flux, and low or varying gravitational acceleration. Under such conditions, the imbalance between convective and diffusive heat fluxes during the solid-liquid phase change leads to complex morphologies at the phase interface, which interfere with the effectiveness of heat transfer through the accumulator. In this study, we investigate the influence of variable gravity and its relative orientation with the global temperature gradient, defined by angle α, on the performance of the PCM-based heat accumulator. We study the spatio-temporal changes in flow dynamics across the orientation angle range from 0° to 180°, where, α = 180° corresponds to the alignment of the incoming heat flux with the gravity field, and α = 0° depicts the configuration where they are oriented in opposite direction. We conduct statistical analysis of coherent structures and global heat transport characteristics to examine the influence of variable gravitational conditions and orientation angles on the flow dynamics, heat transport, and thus the overall melting process of PCM. In addition, the variation in the energy storage capacity of PCM is provided under different operational conditions, which contributes to our understanding of the requirements for PCM in the design of thermal management systems for spacecraft. The results are vital in assessing and designing a PCM-based heat accumulator for long-term passive thermal control in space and planetary environments.
How to cite: Kansara, K., Singh, S., Dwivedi, N. K., and Khodachenko, M. L.: Spatio-Temporal Analysis of Phase Change Material Based Heat Accumulator Under Space and Planetary Environment, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-552, https://doi.org/10.5194/egusphere-egu25-552, 2025.
Posters virtual: Thu, 1 May, 14:00–15:45 | vPoster spot 3
EGU25-16329 | Posters virtual | VPS27
Some problems of gravity assist and terraforming of MarsThu, 01 May, 14:00–15:45 (CEST) | vP3.6
Some problems of gravity assist and terraforming of Mars
Introduction
Here we consider versions of terraforming that would allow colonists to live without pressure suits. The current mass of the Martian atmosphere is 2.5x1016 kg [1]. We consider 4 variants of terraforming. C indicates how many times we need to increase the mass of the atmosphere. For version v1 we assume a pressure of 10 kPa at the bottom of Hellas Planitia, C= 8.6, for v2 we use 10 kPa at the reference level for Mars and C=16.4, for v3 we use 101.3 kPa at the bottom of Hellas Planitia, C= 87.3, and for v4 we use 101.3 kPa at the reference level for Mars, C= 166.1.
For variant v4, 1 body with a radius of ~100 km (and density of 1000 kg m-3) would be sufficient.
Possible sources
Celestial bodies orbiting far from the Sun contain large amounts of water, CO2, nitrogen, etc. There are two places where there are enough bodies useful to our problem: the Kuiper Belt (KB) and the Oort Cloud (OC) [2]. The Kuiper Belt (KB) contains over 70,000 objects with diameters larger than 100 km. The mass of the KB is large enough [2, 3]. The total mass of the OC is ~3×1025 kg [4]. The problem is the large distance from the Sun, so we consider only the KB as the source.
Transporting bodies
Initially ion engines change orbit of the chosen body, in order to later use the effect of gravity assist. This requires precise maneuvering. Since there are many bodies in the KB whose size is sufficient for gravity assist, we assume that a change in velocity of ~50 m/s (using the engine) is sufficient. However, in our case, gravity assist is fraught with significant danger. KB bodies are unstable when volatiles escape. To calculate possible tidal effects, we use the methods developed in [5].
The gravity assist may be used to reduce the relative velocity of Mars and the impactor. This is important because strong heating of the atmosphere will lead to the escape of gases [6].
[1] Mars Fact Sheet. NASA.
[2] Hargitai, H. and Kereszturi, A., 2015, ISBN 978-1-4614-3133-6.
[3] Lorenzo I. 2007. Monthly Notices RAS. 4 (375), 1311–1314.
[4] Weissman, P. R. 1983. Astronomy and Astrophysics. 118 (1): 90–94.
[5] Czechowski, L., 1991. Earth, Moon and Planets, 52, 2, 113-130 DOI: 10.1007/BF00054178
[6] Czechowski, L., et al., 2023. Icarus, doi.org/10.1016/j.icarus. 2023.115473.
How to cite: Czechowski, L.: Some problems of gravity assist and terraforming of Mars, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-16329, https://doi.org/10.5194/egusphere-egu25-16329, 2025.
EGU25-10294 | Posters virtual | VPS27
Method of electromechanical analogies in calculations of natural frequencies of multi-mass mechanical and biological systemsThu, 01 May, 14:00–15:45 (CEST) | vP3.13
With the growth of industry, transportation and machinery the issue of studying and damping vibrations and acoustic oscillations has become critical. Up to 4,000 earthquakes occur on Earth each year. Structures such as skyscrapers and bridges must be designed to withstand ground vibrations without damage. Machinery and tools operate with components that torsion and vibrate in the form of structural nodes. These nodes are connected by specific links to form complex multi-mass mechanical systems. Preventing vibration damage to multi-mass structures remains a pressing problem today. Therefore, the development of methods to calculate the amplitude, frequency and phase of the generated vibrations is a relevant task. Currently known methods of dynamic calculations are the use of analytical techniques for determining the intrinsic frequency of transverse and longitudinal oscillations of shells, rods and rotating machine parts (L.D. Landau, E.M. Lifshitz, V.I. Mossakovskiy, K.V. Frolov). Each task solved with these methods must strictly define the initial and boundary conditions of the oscillatory process. The application of these computational methods to multi-mass systems is very labor-intensive because, in addition to the calculation of amplitude, frequency, and phase, it is necessary to take into account the mode of oscillation. The study of free oscillations in multi-mass systems requires the formation of a system of linear differential equations and the use of cyclic frequency equations for multi-mass systems. Currently, simpler engineering methods such as electromechanical analogies were widely adopted in engineering practice. This period also saw the beginning of research into the resonant frequencies of living organisms to ensure the safety of vehicles subjected to vibration loads. This research was particularly important to the aerospace industry. When launching rockets carrying astronauts, spacecraft experience tremendous vibration shocks. In order to avoid harmful resonance effects, the natural frequencies of the astronaut's body and its organs must be determined. We have used a method based on electromechanical analogies to calculate the resonance frequencies. This method is based on the model of the astronaut's body as a vibrating system proposed by Prof. I. K. Kosko. The computational scheme of this model was developed for the first time. The astronaut's body was modeled as a lumped mass system connected by elastic links, the stiffness of which was determined according to the series and parallel rules. The study used data on the elastic modulus and mass of each part of the astronaut's body. The intrinsic frequency of the astronaut's body was calculated to be 1.702 Hz. The results highlight the importance of taking these data into account when designing the damping system for the astronaut's seat in order to prevent the vibration frequency of the rocket from coinciding with the resonance frequency of the astronaut's body. This approach allows the identification of frequencies that must be avoided to minimize the risk of damage caused by vibration loads. This work demonstrates the application of electromechanical analogies as a simplified engineering method for determining the natural frequencies of complex multi-mass systems such as the human body.
How to cite: Sokol, G., Snobko, D., Kadilnikova, T., and Dalik, M.: Method of electromechanical analogies in calculations of natural frequencies of multi-mass mechanical and biological systems, EGU General Assembly 2025, Vienna, Austria, 27 Apr–2 May 2025, EGU25-10294, https://doi.org/10.5194/egusphere-egu25-10294, 2025.
