TP17
We welcome all relevant contributions — theory, observations, instruments, experiments, analogues — from experts of different fields including science, engineering, industry, agencies, human exploration, resources, economy and policy.
The number of Lunar exploration missions in preparation and planned to arrive and operate at the lunar surface in the next decade is growing at a fast pace. Those missions will have to study, operate in, and survive the lunar environment. They will also perturb and modify the pristine environment significantly. The lunar space environment is a highly dynamic system governed by coupling processes between the solar wind/magnetospheric plasma, energetic particles, neutral and dust exosphere, lunar regolith and near surface dust, and magnetic anomalies. In recent years, almost all space agencies and many private companies and universities have been active in the preparation of new missions to the moon. Characterizing the pristine state as early as possible before it is contaminated by human activity (e.g. due to lunar landings or surface units outgassing) is of interest.
The session is supported by ILEWG LUNEX EuroMoonMars, the COSPAR PEX Panel on Exploration and COSPAR SCB commission (Space Studies of the Earth-Moon System, Planets, and Small Bodies), EuroSpaceHub Earh Space Innovation, IDSEA, Space Renaissance International
Introduction: The Moon has experienced a highly asymmetric volcanic history, with 90% of volcanic activity recorded on the nearside and only 10% on the farside [1]. One possible explanation to the asymmetry has been suggested to be the combination of a thinner crust and a concentration of heat producing elements (i.e. Th, U, and K) underneath the lunar nearside [2]. In turn, a concentration of radiogenics can cause a long-standing thermal anomaly in the mantle of several hundreds of K, which could have lasted up to present-day [2, 3]. Such asymmetry in the subsurface temperature at present-day will induce gravity field anomalies that can affect crustal thickness inversions. Interestingly, thermal anomalies have also been suggested to affect the degree-3 component of the tidal response of the Moon [3].
Here, we combine thermal evolution models that account for crustal thickness variations [2] with gravity and topography inversions for crustal thickness that take thermally-induced density anomalies as input [4, 5]. Thus, we provide a coupled, self-consistent estimate of the lunar mantle temperature and its crustal structure.
Methods: This work builds upon the 3D laterally heterogeneous geodynamic models in [2], where the thermal evolution of the Moon is solved in a 3D spherical shell geometry, using the code GAIA [6]. In particular, we focus on the best-fit model (Fig. 1), which is consistent with both Apollo heat flow experiments [7] as well as with the recent Blue Ghost Mission 1 LISTER [8] and LMS [9] experiments.
Figure 1: Surface heat flux distribution from one of the
best-fit models in [2]. This setup consists of a radiogenic
anomaly of ~1200 km in radius, and 30 ppm Th equivalent
concentration for a 1.6 km thick layer. Bulk abundance
of radiogenics is equivalent to 90 ppb Th.
The setup in Fig. 1 consists of a geodynamic model overlaid with a crustal thickness model, as described in [2]. At present-day, this model produces a temperature field which predicts a positive thermal anomaly of ~100-200 K underneath the nearside Procellarum KREEP Terrane (PKT), and two smaller anomalies (~50-100 K) underneath the farside highlands terrane (positive) and south pole-Aitken basin (negative).
The 3D temperature field is then discretized into layers from the surface to the core and converted into a density field assuming a mantle density and thermal expansion coefficient of 3400 kg/m3 and 2x10-5 K-1, respectively. Thereafter, the gravity anomaly associated with density variations within each layer is computed following [10], using the DSP code [11]. These anomalies are then fed into a global inversion model that self-consistently solves for mare and feldspathic crustal thickness from observed gravity and topography [1]. For this calculation, we neglect crustal temperature anomalies as these do not lead to important density anomalies given the expected low thermal expansivity in the crust and smaller temperature variations. We then run a second thermal evolution model using the updated crustal thickness model to ensure that the iteration between crustal thickness and geodynamic models converges.
Results and discussion: The update in crustal thickness resulting from our approach is shown in Fig.2. As expected, regions where subsurface temperatures were higher than average result in a crustal thinning (e.g., PKT, Farside Highlands). Conversely, regions of colder-than-average interior, such as basins, show crustal thickening subsequent to our calculation (e.g., SPA).
Figure 2: Variations in crustal thickness inversion induced
by temperature anomalies in the mantle. Locations of
Procellarum KREEP Terrane (PKT), farside highlands, south
pole-Aitken, Apollo 15, Apollo 17, and mare Crisium are
annotated in the map.
The most prominent variation in crustal thickness is related to the nearside temperature anomaly and reflects the shape of the modeled PKT area. Within this area, we obtain a crustal thinning of ~20% (~8.5 km) with respect to the original crustal thickness model which did not account for a variable mantle density [5]. The secondary temperature anomalies associated with the farside highlands and the south pole-Aitken basin induce a crustal thinning and thickening, respectively, of about 3 km. Outside of these three regions, we see moderate crustal thickening throughout the lunar surface.
Notably, when using the updated crustal thickness to run the thermal evolution model a second time, we see negligible differences in the present-day thermal state of the Moon. This result implies that the conclusion drawn in [2] from the results of the geodynamic model are not significantly affected by the interaction between mantle temperature and crustal thickness. We note, however, that the geodynamic model is non-unique and its resolution coarser than that of the crustal thickness inversion, which leaves room for further sensitivity analysis.
Conclusion: In this work we successfully quantify the effect of predicted mantle thermal anomalies predicted by geodynamic models on lunar crustal thickness inversions. We build a self-consistent model of the present-day thermal state and crustal structure of the Moon. We find differences with respect to previous crustal thickness inversions up to 20% in the procellarum KREEP terrane region, which can be of interest for future works that rely on local crustal thickness estimates. As future steps, we will consider the effect of the predicted thermal anomalies on seismic velocities, which can also be estimated from the output of geodynamic models. Additionally, we will use the present-day interior temperature distribution derived from our model to compute the tidal response of the Moon in terms of tidal Love numbers and time-variable Stokes coefficients up to degree and order 3, using a pseudo-spectral method [12, 13]. The comparison of the computed tidal response with the values measured by GRAIL [3] will provide additional constraints to refine the model presented here.
References: [1] Broquet and Andrews-Hanna (2024). [2] Santangelo et al., (2025). [3] Park et al., (2025). [4] Wieczorek et al., 2013. [5] Broquet et al., (2025). [6] Hüttig et al. (2013). [7] Langseth et al., (1976). [8] Nagihara et al., (2026). [9] Grimm et al., (2026). [10] Wieczorek & Phillips, (1998). [11] Broquet, (2024). [12] Rovira Navarro & Matsuyama, (2024). [13] Qin, (2012).
How to cite: Santangelo, S., Broquet, A., Cascioli, G., Plesa, A.-C., Breuer, D., and Hussmann, H.: Updated lunar crustal thickness distribution from global geodynamic models, Europlanet Science Congress 2026, The Hague, The Netherlands, 7–11 Sep 2026, EPSC2026-1047, https://doi.org/10.5194/epsc2026-1047, 2026.
Introduction
During the earliest stages of the Moon, it is generally believed that the Moon underwent a global Lunar Magma Ocean (LMO) phase, which subsequently cooled resulting in fractional crystallisation [1-7]. The exact duration of this crystallisation is still debated and ages are generally provided by geochronology on lunar rocks. Since most isotope systems are susceptible to changes in temperature, which is impractical considering the considerable amount of (micro)meteorite impacts on the Moon, geochronology on zircons is favoured because of zircon’s stability and insensitivity to changes in environmental conditions.
Proper use of zircons for dating requires a good understanding of the timing of zircon formation during LMO crystallisation. Zircons likely crystallised in the final melt fraction that is strongly enriched in incompatible elements, which is also known as KREEP [8,9], but limited experimental research has yet demonstrated that zircons can indeed crystallise in this melt at lunar conditions [10]. This likely occurred following or during the proposed silicate melt immiscibility [7, 10-13]. Zircon crystallization is governed by the Zr solubility limit of the melt, and therefore, the Zr content of the bulk system. This indicates that the characteristics of the melt are of great importance in the process of crystallising zircons, including the SiO2 activity, degree of polymerisation, diffusion rates, and water content [14-22]. Here, we aim to constrain the Zr solubility of the final dregs of the LMO melt (>99% crystallization), while exploring a number of proposed bulk compositions, to assess the nature and timing of lunar zircon crystallization.
Methods
This study uses the composition of the final melt fraction of the LMO, as experimentally derived by Charlier et al. (2018) and Zhang et al. (2024), to perform zircon crystallisation (saturation) experiments with the focus placed on the partitioning of Zr between the immiscible liquids and Zr solubility and saturation for both immiscible melts. The crystallisation experiments are conducted under lunar conditions, at ~1000 °C and 0.5 GPa, on a piston cylinder press at the HPT lab at TU Delft (Fig. 1,2) and the samples are analysed with the electron probe microanalyzer (EPMA) and the Laser Ablation Inductively Coupled Plasma-Mass Spectrometer (LA ICP-MS) at Utrecht University and the VU Amsterdam, respectively. The piston cylinder press was calibrated using the albite-jadeite-quartz and fayalite-quartz-ferrosilite mineral transitions. Proposed Zr partitioning between the immiscible liquids and modelled Zr solubility limits by e.g. Borisov et al. (2025) will be experimentally tested under lunar conditions. The experimental run products and derived first results will be reported at the meeting.
Conclusions and outlook
Results of this study will create a better understanding of the behaviour of Zr in the final melt fraction of the LMO and the conditions required to crystallise the enigmatic lunar zircons, with possible implications regarding the further evolution of the LMO.
Fig. 1 Pt crucible with glass Fig. 2 Piston cylinder press (HPT lab, TU Delft)
Acknowledgement
This study was supported by the NWO NWA PRELIFE grant.
References
[1] Charlier et al. (2018) GCA [2] Elkins-Tanton et al. (2011) EPSL [3] Lin et al. (2017) Nat. Geoscience [4] Longhi (2003) JGR: Planets [5] Longhi (2006) GCA [6] Rapp & Draper (2018) MaPS [7] Zhang et al. (2024) EPSL [8] Dauphas et al. (2025) PNAS [9] Taylor et al. (2009) EPSL [10] Dickinson & Hess (1982) EPSL [11] Hess et al. (1975) Proceedings Lunar Science Conference, 6th [12] Quick et al. (1977) Proceedings Lunar Science Conference, 8th [13] Roedder & Weiblen (1970) Proceedings of the Apollo 11 Lunar Science Conference [14] Baker et al. (2002) CMP [15] Boehnke et al. (2013) Chemical Geology [16] Borisov et al. (2025) Chemical Geology [17] Borisov & Aranovich (2019) Chemical Geology [18] Crisp & Berry (2022) CMP [19] Gervasoni et al. (2016) CMP [20] Shao et al. (2019) SESCI [21] Shao et al. (2020) Acta Geochemica [22] Watson & Harrison (1983) EPSL
How to cite: Royakkers, A., Steenstra, E., Vroon, P., and van Westrenen, W.: An Experimental Assessment of Zircon Crystallisation in the Final Melt Fraction of the Lunar Magma Ocean, Europlanet Science Congress 2026, The Hague, The Netherlands, 7–11 Sep 2026, EPSC2026-1177, https://doi.org/10.5194/epsc2026-1177, 2026.
Introduction
On the Moon, increasing evidence of water ice in Permanent Shadowed Regions [1-3] (PSRs) and day-night surface-exosphere hydration variability [4], is asking for a description of the delivery scenario [5]. Here, we present preliminary results from our Smoothed Particle Hydrodynamics model for volatile emissions, to monitor the evolution of a plume originating from the impact of a cometary-like object over the Moon’s surface, an event that could significantly contribute to the exogenic delivery of lunar water ice [6], in particular within PSRs.
Methods
We follow the dynamical and thermal evolution of the vaporized ejecta resulting from the impact by means of the Smoothed Particle Hydrodynamics (SPH) method [7]. This particle-based mesh-free approach integrates hydrodynamic equations and provides the evolution of velocity, density, and energy. Our model, successfully used to simulate Enceladus’ plumes [8], describes the collisional regime of fluid flow, often neglected in ejecta simulations on the Moon [9]. We consider phase transitions between water vapor and icy-grains, their viscous interaction, solar radiation effect, thermal conduction with boundaries, Moon’s gravity and tidal interaction with Earth.
Initial conditions. We use scaling relationships [10-11] to relate crater, ejecta, target, and impactor properties. We assume a top-surface lunar density of 1100 kg/m3 [12] and a cometary-like impactor with density of 500 kg/m3, size ~1.5 km, velocity of ~15 km/s [13] and an ice of 20% of the comet mass. The ejecta thermal energy fraction is taken from literature [14] and produces ice sublimation.
Boundary conditions. Our boundaries are the Moon’s surface and a 5 km radius PSR, modeled as a hemispherical crater centered on the south pole. We consider that the PSR rim touches the rim of the impact crater (20 km radius). For the thermal interaction, the Moon’s surface temperature is taken from the DIVINER data [15]. The PSR is assumed to have a temperature profile linearly decreasing with depth setting Tfloor = 50 K and Trim = 100 K, consistent with a cold-trap [16].
Results.
We simulate 10 h of evolution of the post-impact plume, using 106 particles. After ~1 h, the vapor is globally spread throughout the Moon, producing a transient exosphere. Ice accumulates on the shadowed side and poles and reaches ~20% of the initial amount of material after 10 h. The plume is dominated by vapor which gradually exceeds Hill limit, yielding a loss of ~60% after 10 h of evolution, as shown in Figure 1.
Figure 1: Temporal evolution of the particle fraction forming the plume (black stars, dominated by water vapor), accumulated on the surface (green squares), and lost from the Hill limit (purple plus markers).
The surface accumulation of ice is higher at the south pole, where the impact occurs, and gradually extends toward the north pole. The surface density gives insights into the material collected by PSRs and cold-traps located at different distances from the impact point. In particular, we obtain that vapor lingers in the area of the simulated cold-trap only at early times. Shadows and interaction with cold walls favor deposition into ice, which after 100 s reaches a stable fraction of 2 x 10-4 of the initial water amount (Figure 2).
Figure 2: Temporal evolution of the fraction of vapor and ice within the polar PSR.
According to our model and initial conditions, the ice retained within the PSR is lower than the vapor entering the area, indicating a partial local condensation. The adopted PSR temperatures keep the accumulated ice stable against sublimation on long timescales, producing a reservoir of ~2.8 x 108 kg. This value is consistent with observational estimates within PSR, which range from 107 to 109 kg [17], compatible with the hypothesis that polar impacts of hydrated objects could have been a fundamental water delivery mechanism for the present-day lunar ice.
Perspectives
We plan to explore ice accumulation dependence on impact point–PSR and estimate the exosphere contribution over a longer time. Furthermore, we consider assessing the importance of long-time processes, such as impact gardening, regolith mixing, ice exposure/burial and volatile redistribution in PSRs, on ice deposits preservation. We plan to improve initial conditions performing impact simulation and using Eulerian methods [18] to characterize the thermal behavior of the PSR and volatile stability. Moreover, we can consider the presence of dust [19], that can alter early phases. This would further support lunar science, missions and exploration. In addition, this study is applicable to other objects, such as Mercury. More generally, our model provides a numerical tool to characterize volatile emissions on various targets, including vapor-ice-dust mixture releases, triggered by drilling activities [19], planned for ExoMars and Prospect missions, or cometary activity [20].
References
[1] Li et al. 2018, PNAS, 115, 8907.
[2] Sanin et al. 2017, Icarus, 283, 20.
[3] Ohtake et al. 2024, ApJ, 963, 124.
[4] Livengood et al. 2025, Icarus, 255, 100.
[5] Thiemens et al. 2024, PNAS, 121, 52.
[6] Lucey et al. 2022, Geochemistry, 82, 125858.
[7] Monaghan 2005, Rep. Prog. Phys. 68, 1703.
[8] Teodori et al. 2026, Icarus, 443, 116765.
[9] Stewart et al. 2011, Icarus, 215, 1.
[10] Housen et al. 1983, J. Geophys. Res. 88, 2485.
[11] Housen & Holsapple 2011, Icarus, 211, 856.
[12] Hayne et al. 2017, J. Geophys. Res. Planets 122, 2371.
[13] Ivanov et al. 2001, SSR, 96, 87.
[14] O’Keefe & Ahrens 1982, JGR: Solid Earth, 87, 6668.
[15] Hurley et al. 2015, Icarus, 155, 159.
[16] Formisano et al. 2025, MNRAS, 543, 4187.
[17] Brown et al. 2022, Icarus, 377, 114874.
[18] Formisano et al. 2024, PSS, 251, 105969.
[19] Maggioni et al. 2026, PSS, 272, 106244.
[20] G. Rinaldi et al. 2025, EPSC-DPS2025-1556.
Acknowledgments
This work is supported by INAF Theory Grant “Thermophysical modeling of Permanently Shadowed Regions (PSRs) on Moon and Mercury”, INAF MiniGrant “PLUMES - Planetary fractures Lagrangian simUlations for Multi-component EmissionS”, and ISSI within the project “Thermophysical Characterization of Ice-Rich Areas on the Surface of Specific Planetary Bodies: Conditions for the Formation of a Transient Exosphere”.
How to cite: Teodori, M., Maggioni, L., Magni, G., Formisano, M., De Sanctis, M. C., Altieri, F., D'Aversa, E., Ciarniello, M., Bertoli, S., Filacchione, G., Raponi, A., Capaccioni, F., and Frigeri, A.: Investigating the contribution to lunar ware ice delivered by cometary impacts through Smoothed Particle Hydrodynamics, Europlanet Science Congress 2026, The Hague, The Netherlands, 7–11 Sep 2026, EPSC2026-996, https://doi.org/10.5194/epsc2026-996, 2026.
The South Pole-Aitken (SPA) basin on the lunar farside is the largest, oldest, and deepest confirmed impact structure on the Moon [1], making it a key archive of early lunar evolution and basin-scale impact processes. Here, we revisit the internal structure of SPA and the origin of its distinctive crescent-shaped thorium (Th) enhancement. We argue that this Th pattern is the evolved surface expression of an incompatible-trace-element (ITE)-rich impact melt sheet formed during the SPA-forming event and later modified by large impacts and volcanic resurfacing. This framework has renewed relevance following the return of Chang’E-6 (CE-6) samples from the Apollo basin within SPA.
Although SPA has been substantially degraded over time, its size strongly suggests that it originally formed as a multiring basin [2]. Two large topographic ellipses previously identified within SPA show a semi-minor-axis ratio close to the characteristic √2 spacing between adjacent rings in large multiring basins [3,4] (Fig. 1). If these ellipses represent the two outermost SPA rings, analogous to the Cordillera and Outer Rook rings of Orientale, then the intervening “Outer Terrace” may be interpreted as a mega-terrace produced by collapse of the rim-crest region during late-stage basin modification [5-7]. This interpretation is supported by the composition of the Outer Terrace, which is broadly feldspathic, similar to the surrounding farside highlands, and generally poor in Th. Its spatial correspondence with the Heterogeneous Annulus defined from spectral observations further strengthens this view [5,6,8].
A different geological regime emerges inward of the Outer Terrace. The region between the inner topographic ellipse and an inferred peak-ring ellipse, estimated from ring-spacing relationships, broadly coincides with the Mg-pyroxene-rich annulus and shows distinctly higher Th abundances [4,5,8] (Fig. 1). Further toward the basin center, the inferred peak-ring region encloses the central topographic depression and areas of relatively thin crust. Most of this inner region exhibits Th concentrations above 3 ppm, with the notable exception of the SPA Central Compositional Anomaly (SPACA) [5,8]. The size of the inferred peak-ring region is also consistent with earlier estimates for the extent of the SPA impact melt sheet [9].
We interpret the broad Th enrichment in the SPA interior as a signature of impact melt differentiation. Numerical and petrological studies suggest that the SPA-forming impact generated a large and deep melt sheet, whose subsequent differentiation produced an upper residual layer enriched in ITEs, including Th [10,11]. Such a layer provides a natural explanation for the elevated Th concentrations observed across much of the basin interior. The localized Th minimum in SPACA may represent a later modification of this original geochemical pattern. As suggested in our previous work, SPACA may correspond to an extensive cryptomare region, where volcanic resurfacing could have buried or diluted the Th-rich signature of the underlying impact melt sheet [5].
Indeed, the present crescent-shaped Th distribution as a whole appears to record a long history of post-impact modification [12] (Fig. 2). Following formation of the SPA melt sheet, several large early impacts in the northwestern basin interior, such as Von Kármán M, Von Kármán, and Leibnitz, would have excavated and redistributed Th-rich melt-sheet materials beyond the original melt-sheet boundary. Later large impacts, including Apollo and Poincaré, occurred near the inferred outer portion of the inner basin and may have removed or diluted parts of this Th-rich layer, producing local decreases in surface Th abundance. Prolonged mare and cryptomare volcanism in central SPA, especially within SPACA, further obscured the primary geochemical signature. Finally, younger craters such as Birkeland and Oresme V likely re-excavated redistributed Th-rich materials, forming the two prominent Th hotspots now observed in northwestern SPA [12].
This basin-scale framework provides important context for interpreting CE-6 samples from the southern mare plain of the Apollo basin. Laboratory analyses indicate that the landing-site mare deposits are dominated by low-Ti basalts emplaced at ~2.8 Ga, consistent with earlier remote-sensing interpretations [13–15]. However, Apollo is not simply a volcanic setting within SPA. As the largest impact basin in the northeastern SPA interior, it formed across compositionally distinct structural domains of the older SPA basin [6]. Its southwestern interior exposes Mg-rich noritic materials in areas of extremely thin crust, whereas its northeastern portion is more feldspathic [6]. These Mg-rich lithologies, likely excavated from deeper crustal levels during the Apollo-forming event (Fig. 3), have also been identified among CE-6 returned materials [16]. The CE-6 sample collection may therefore record not only local mare volcanism, but also the deeper crustal architecture and excavation history of SPA.
References:
[1] Spudis, P. D. et al. (1994) Science, 266(5192), 1848–1851. [2] Baker, D. M. et al. (2012) JGRP, 117(E12). [3] Garrick-Bethell, I. & Zuber, M. T. (2009) Icarus, 204(2), 399–408. [4] Pike, R. J. and Spudis, P. D. (1987) Earth Moon Planet, 39, 129–194. [5] Wang, X. et al. (2024) JGRP, 129(5), e2023JE008176. [6] Wang, X. et al. (2024) AJ, 168(6), 247. [7] Head, J. W. (2010) GRL, 37(2). [8] Moriarty, D. P. and Pieters, C. M. (2018) JGRP, 123(3), 729–747. [9] Potter, R. W. et al. (2012) Icarus, 220(2), 730–743. [10] Vaughan, W. M. and Head, J. W. (2014) PSS, 91, 101–106. [11] Hurwitz, D. M. & Kring, D. A. (2014) JGRP, 119(6), 1110–1133. [12] Wang et al. (2025) 55th LPSC, Abstract #1121. [13] Cui, Z. et al. (2024) Science, 386(6728), 1395–1399. [14] Zhang, Q. W. et al. Nature, 643(8071), 356–360. [15] Qian, Y. et al. (2024) EPSL, 637, 118737. [16] Li, C. et al. (2024) NSR, 11(11), nwae328.
Fig. 1. Th distribution in and around the SPA basin obtained by Lunar Prospector. The solid black lines are the topographic ellipses [3]. The solid yellow line indicates the possible location of the SPA peak ring based on the ring spacing relationship [5, 6]. The red dashed lines outline the compositional zones defined by [8].
Fig. 2. Schematic diagram of the evolution of the crescent-shaped Th distribution within the SPA basin. In (d), 1-Oppenheimer, 2-Van de Graaff, 3-Minnaert, 4-Antoniadi, 5-Numero, 6-Bose, 7-Bhabha.
Fig. 3. Schematic cross-sectional diagrams of SPA basin structure, (a) pre- and (b) post-Apollo/Schrödinger events.
How to cite: Wang, X., Head III, J. W., Wu, B., and Liu, J.: The South Pole-Aitken Basin Interior, Thorium Distribution, and Implications for Chang’E-6 Samples, Europlanet Science Congress 2026, The Hague, The Netherlands, 7–11 Sep 2026, EPSC2026-624, https://doi.org/10.5194/epsc2026-624, 2026.
Introduction: This paper presents the ongoing development of the “Terrain Testing Instrument (TTI)”, being an international payload for the planned Chinese Chang’e 8 lunar landing and roving mission in 2029.
Science Background: The lunar surface is covered by a layer of granular material referred to as the regolith which is derived through comminution of bedrock and float rocks by impact gardening and deep thermal cycling. Thickness of the regolith is typically several meters but varies between mare and highland regions as well in response to local processes. Ground penetrating radar has been used successfully on the Chinese lunar rovers Yutu and Yutu-2 to inform the stratigraphy and thickness of the regolith at fine scale. Knowledge of the physical properties of the regolith in terms of bearing and shear strength is critical for designing equipment such as ground vehicles (rovers), excavation equipment, and elements of future outposts. This will become ever more important as crewed missions will again be sent to the lunar surface, outposts will be constructed, and mining will be performed to extract local resources.
In the initial phase of lunar surface exploration by the United States and the Soviet Union, dedicated instruments were designed and used to measure in situ key physical properties of the regolith column of the Moon in various locations. This was done by penetrometry (on the Apollo missions) and vane-cone instruments (PROP-M instrument on the Lunokhod rovers). On the lunar landing and roving missions of the modern era however, no dedicated instruments have yet been flown to measure regolith physical properties. It will be particularly important to understand bearing and shear strength in the South polar region where extensive landing, roving, mining, and construction activities are foreseen over the next several decades. A general assumption is that regolith in the lunar South polar terrain would broadly resemble lunar highland regolith, as argued in the lunar geological community on the grounds of structural geology and geological mapping of the Moon. But direct measurements of physical properties will be indispensable ahead of crewed missions. The same holds true for understanding volatile contents of the regolith, at spatial scales relevant to roving and excavation. Volatiles constitute an important resource while at the same time sublimation of ices from an icy regolith in response to loading and thermal dissipation from human-emplaced structures can lead to subsistence of the ground, thus constituting a hazard.
To address this gap in critical knowledge, the authors of the present abstract are developing the so-called Terrain Testing Instrument (TTI) which has been selected as an international payload for the planned Chinese Chang’e 8 lunar landing and roving mission slated to launch in 2029.
Instrument Concept and Design: The TTI will measure regolith penetration resistance via a cone penetrometer and shear strength via a shear vane, with both techniques combined in a so-called vane-cone instrument. A permittivity sensor is integrated with the vane-cone and will allow to infer bulk density and ice content of the regolith, derived from measurement of the dielectric properties and relative permittivity.
A linear translation mechanism drives the vane-cone assembly into the regolith, followed by rotation of the front shear vane to indicate shear resistance as a function of shear angle.
Depth range of the instrument is ~5 cm as it will be carried on the relatively small JINNAH-1 rover contributed by SUPARCO, with limited available reaction force. The TTI will perform multiple measurement sequences at various locations during the first lunar day following landing. TTI overall mass is ~1.5 kg, including its electronics unit which is accommodated inside the rover.
Development Status: The instrument Structural Model (SM) has already been delivered, to be followed by the Electrical Model (EM) in the summer of 2026.
The TTI is being developed by an international team of entities from Germany, the Netherlands, France, China, and the two Special Administrative Regions Macau and Hong Kong.
References: [1] Heiken, Vaniman, Carrier (1991). Lunar Sourcebook: regolith penetration resistance and shear strength. [2] L. Ding. L. Richter, and 44 co-authors (2022). Sci. Robot. 7, eabj6660. [3] H. Seifamiri, R. C. Anderson, R. Boudreaulta, R. de Moraes, C. Dickinson, N. Gelino, P. Maghoul (2025). Geotechnical Properties of Lunar Regolith for Excavation and Construction on the Moon.
Fig. 1: JINNAH-1 rover with the TTI external assembly mounted on its rear panel. Electrodes of the permittivity sensor (PP) are integrated with the TTI shear vanes. The TTI electronics reside inside the rover body.
Fig. 2: Installing the Structural Model of the TTI external assembly on the rover Structural Model, ahead of vibration testing (March 2026).
How to cite: Richter, L., Zou, M., Foing, B., Flahaut, J., Ye, Y., and Zhao, Q.: The Terrain Testing Instrument (TTI) as a Selected Payload for the Chang’e 8 Lunar Landing Mission, Europlanet Science Congress 2026, The Hague, The Netherlands, 7–11 Sep 2026, EPSC2026-748, https://doi.org/10.5194/epsc2026-748, 2026.
How to cite: Gao, Y. and the HKOR Team at InnoHK Hong Kong Space Robotics & Energy Centre: Hong Kong Operation Robot for Chang‘E-8 Mission, Europlanet Science Congress 2026, The Hague, The Netherlands, 7–11 Sep 2026, EPSC2026-1285, https://doi.org/10.5194/epsc2026-1285, 2026.
Far-ultraviolet (FUV) surface reflectance measurements of the Moon, asteroids, icy satellites, comets and Mercury have proven surprisingly useful for advancing our understanding of planetary surfaces, expanding the primary uses of UV instruments beyond investigating planetary atmospheres and auroral processes. The Lunar Reconnaissance Orbiter (LRO) Lyman Alpha Mapping Project (LAMP) has contributed greatly to this new appreciation for planetary FUV imaging spectroscopy thanks to its 17 years of investigations. LRO-LAMP FUV spectral-imaging has enabled detailed spectral maps of the lunar dayside, nightside, and permanently shaded regions (PSRs) and are useful in the context of numerous properties not originally understood prior to LRO’s launch in 2009.
Detailed FUV spectral analyses (Gladstone et al. 2012), supplemented by laboratory efforts (Raut et al. 2018), investigate regolith structure/porosity and the relative aging of surface features by space weathering (Mandt et al. 2016; Byron et al. 2019; Byron et al. 2020; Cahill et al. 2019; Liu et al. 2018). Global searches of water signatures both inside (Magaña et al. 2022, 2023, 2024) and diurnal variations in hydration features outside of lunar PSRs (Hendrix et al. 2012; Hendrix et al. 2019) are allowing us to confirm and elucidate the findings of surface water/hydroxyl and its variability. These analyses support each other and advance the identification of compositional signatures in regolith (i.e., feldspar-rich highlands, Czajka et al. 2023; lunar swirls, Henrix et al. 2016).
See the QuickMap (https://quickmap.lroc.asu.edu) tool for a nearside view of LAMP dayside Off-band/On-band albedo ratio maps examples https://bit.ly/3n8PWGj and the Reiner-Gamma region with optical swirl boundaries https://bit.ly/3n69qeL.
The LRO Extended Science Mission 6 (ESM6) is focused on supporting the overall Artemis program. It enables more surface reflectance data at a variety of incidence and emission angles to improve signal, spectral, and photometric quality and to further develop our innovative UV reflectance techniques (Davis et al. 2017) – albeit with reduced performance at long wavelengths, following microchannel plate wear and tear. Ongoing laboratory studies are constraining the compositional and photometric properties of lunar samples and simulant analogs (Gimar et al. 2025). Observations of comets (Magaña et al. 2022), the interplanetary medium (Pryor et al. 2022, 2023, 2024), the lunar exosphere (e.g., Grava et al. 2021) and other targets are planned for ESM6, in addition to support of, and landing gas-plume imaging of, the exciting series of upcoming lunar missions, as available. Four targeted observations of interstellar comet 3I/ATLAS were obtained in November-December 2025, detecting the extended envelope of escaping neutral hydrogen atoms.
How to cite: Retherford, K., Whizin, A., Grava, C., and Byron, B. and the LRO LAMP Team: LRO Lyman Alpha Mapping Project (LAMP) Far-UV Mapping Results and Support for Artemis. , Europlanet Science Congress 2026, The Hague, The Netherlands, 7–11 Sep 2026, EPSC2026-299, https://doi.org/10.5194/epsc2026-299, 2026.
The increasing interest in lunar exploration by both institutional and commercial actors is driving the need for affordable and flexible surface mobility solutions. In this context, Space Applications Services is developing the LUVMI-M (Lunar Volatiles Mobile Instrumentation - Medium) rover, a lightweight commercial rover platform designed to support scientific investigations, technology demonstrations, and prospecting activities on the Moon. The first LUVMI-M mission is currently planned for Q4 2028 and will target operations in the lunar South Pole region.
The rover builds on nearly a decade of development within the LUVMI programme, which began in 2016 and has included several rover prototypes tested extensively in indoor and outdoor lunar analogue environments. LUVMI-M continues this heritage while introducing a modular architecture capable of accommodating a wider range of payloads. The platform provides mechanical, electrical, thermal, and data interfaces suitable for instruments such as spectrometers, imagers, environmental sensors, and regolith interaction tools. Up to 20 kg of payload mass can be distributed across multiple mounting locations, offering diverse payload fields of view and direct access to the lunar surface.
The baseline mission architecture foresees operations over one lunar day (approximately 10-14 Earth days), during which the rover is expected to traverse up to 5 km and visit up to 50 sites of scientific interest. By moving away from the immediate influence of the lander, the rover can enable cleaner measurements of the lunar exosphere and dust-plasma environment, which are of growing interest as lunar activity increases and the pristine environment becomes progressively altered by future missions. In polar landing scenarios, the rover’s design also allows for short excursions into permanently shadowed regions (PSRs), within thermal and energy constraints, offering opportunities to study volatile-rich environments.
The rover is designed to be compatible with multiple commercial lunar landers, allowing future missions to be flexible to different landing sites and exploration objectives. Recent mobility testing was conducted in ESA’s LUNA facility in Cologne and in Space Applications Services’ Moon Yard to test locomotion and navigation functions.
Beyond its technical capabilities, LUVMI-M intends to contribute to the emerging ecosystem of commercial lunar services. Through the aim of biennial rover missions and accessible payload opportunities, the LUVMI programme wants to lower the barriers for participation in lunar surface exploration and support a growing community of scientific and technological users.
This contribution presents the LUVMI-M rover concept, the Mission 1 architecture, and the current status of its technical development. It will also discuss the ways in which LUVMI-M can support participation by external teams.
How to cite: Winters, M., Hoppenbrouwers, T., Vanden Bussche, S., Pitcher, C., and Gancet, J.: LUVMI-M: A Commercial Lunar Rover Platform for Mobile Surface Exploration and Prospecting., Europlanet Science Congress 2026, The Hague, The Netherlands, 7–11 Sep 2026, EPSC2026-432, https://doi.org/10.5194/epsc2026-432, 2026.
Abstract:
Surface alteration by the exhaust plumes of lunar landers is a major concern when interpreting measurements acquired at the lunar surface [1–3]. For example, because the spectral and angular properties of lunar-emitted particles depend on regolith structure and mineralogy [4–8], lander-induced surface contamination is expected to affect particle emissions over several hundred meters around the landing site. However, the effects of lander-induced regolith disturbances on lunar particle emissions remain poorly constrained due to the lack of dedicated in situ investigations.
Using energetic neutral atom (ENA) measurements from the Advanced Small Analyzer for Neutrals (ASAN) [9] onboard the Chang’e-4 rover Yutu-2, we investigate variations in the spectral and angular properties of backscattered hydrogen ENAs as a function of distance from the Chang’e-4 lander. Excluding periods when the precipitating solar wind was disturbed by the South Pole–Aitken magnetic anomaly [10], we obtain 30 energy spectra acquired at distances of 30–930 m from the Chang’e-4 lander over a 4.5-year interval beginning one months after landing. For each spectrum, we applied a Bayesian inference method to derive the hydrogen surface binding energy and angular scattering function using an empirical hydrogen ENA energy spectrum model [6].
Our analysis shows that the surface binding energy inferred from ASAN observations is lower, at 5.0 ± 1.8 eV, within the first 150 m from the lander, compared to 6.2 ± 2.9 eV at larger distances. This transition distance of 150 m is comparable to the size of blast zones produced by previous lunar landers, suggesting that the same surface alteration processes responsible for the visible blast zone also modify the energy spectrum of lunar-emitted particles. In contrast, we find no significant dependence of the scattering function on distance from the lander. This result is contrary to previous expectations, namely that lander plume–induced disturbances in the micrometer-scale structure of the regolith inferred from photometric measurements would affect the ENA angular scattering function [1,4]. These results motivate future investigations of surface alteration using rover-borne particle instruments, particularly during the first lunar day, when transient contamination is expected [2] but not covered by the ASAN dataset.
References:
[1] Clegg-Watkins et al. (2016). Icarus, 273, 84–95. https://doi.org/10.1016/j.icarus.2015.12.010.
[2] Farrell et al. (2022). Icarus 376: 114857. https://doi.org/10.1016/j.icarus.2021.114857.
[3] Prem et al. (2020). JGR: Planets, 125(8), e2020JE006464. https://doi.org/10.1029/2020JE0064643
[4] Kenmotsu et al. (2004). Journal of Plasma and Fusion Research, 80 (5), 406–9. https://doi.org/10.1585/jspf.80.406.
[5] Szabo et al. (2023). JGR: Planets, 128 (9), e2023JE007911. https://doi.org/10.1029/2023JE007911.
[6] Wieser et al. (2024). A&A, 684, A146. https://doi.org/10.1051/0004-6361/202348876.
[7] Ricketts et al. (2025). The Planetary Science Journal, 6 (10), 244. https://doi.org/10.3847/PSJ/ae113e.
[8] Canu-Blot et al. (2026). A&A, in press: https://doi.org/10.1051/0004-6361/202659499.
[9] Wieser et al. (2020). Space Science Reviews, 216(4), 73. https://doi.org/10.1007/s11214-020-00691-w.
[10] Maynadié et al. (2026). JGR: Space Physics, 131(4), e2026JA035258. https://doi.org/10.1029/2026JA035258.
How to cite: Maynadié, T., Futaana, Y., Barabash, S., Wieser, M., Wang, X.-D., and Zhang, A.: Anthropogenic Contamination of the Lunar Surface: Characterizing the Effects of the Chang’e-4 Landing on Lunar Surface Properties, Europlanet Science Congress 2026, The Hague, The Netherlands, 7–11 Sep 2026, EPSC2026-251, https://doi.org/10.5194/epsc2026-251, 2026.
Sample return from the Moon’s South Pole-Aitken Basin (SPA) has long been recognized as a high priority destination for lunar science, appearing as a recommended medium-class NASA mission in multiple United States National Academies of Sciences Planetary Science decadal surveys. The primacy of the site arises from the unique combination of its size, antiquity, and location on the lunar farside. The South Pole-Aitken basin presents the ideal target destination to test nearly 60 years of lunar science hypotheses. Despite the recognized importance of the science, mission proposals for sample return have previously been hampered by a combination of cost and technology. During the development of the 2023-2032 Origins, Worlds, and Life (OWL) decadal survey, a mission concept named “Endurance” demonstrated the feasibility of a long-duration, long-traverse mission that could accomplish the majority of defined priority lunar science investigations at a cost cap that was commensurate with New Frontiers scale missions. This mission concept leveraged new developments in rover technology, autonomous systems development, and concepts of operations developed by the Intrepid Pre-decadal Mission Concept Study, in conjunction with the advent of technological advances in the commercial exploration marketplace. Using the Endurance point design, the OWL advocated for the development of an SPA Sample Return mission as the highest priority mission for the Lunar Discovery and Exploration Program (LDEP). In response to this recommendation, NASA convened the South Pole Aitken basin sample Return and eXploration (SPARX) Science Definition Team (SDT) to provide analysis on prioritized science objectives and implementation architectures for a South Pole-Aitken Basin sample return mission.
The SPARX SDT report is actively being reviewed by NASA, and will be released to the community in early Summer 2026. The report will include descriptions of prioritized science goals and objectives and the associated requirements for both in-situ and terrestrial laboratory measurements. The report will provide a description of a baseline implementation architecture that demonstrates a notional traverse and mission architecture for accomplishing all of the listed science objectives. Additionally, the report will include a discussion of multiple mission implementation profiles, with recommendations for their future selection criteria. Finally, the report will contain a discussion of future technologic and programmatic factors that could affect the future implementation of the mission, including the role of astronauts, commercial exploration, and international participation. This presentation will provide an overview of the newly released SPARX report, focusing on the overarching recommendations for implementation architectures, measurement requirements, and high-priority items for the next phases of mission development.
How to cite: Jozwiak, L. and the SPARX Science Definition Team: South Pole-Aitken basin sample Return and eXploration (SPARX) Science Definition Team Report: Findings and Recommendations for a Future Lunar Mission, Europlanet Science Congress 2026, The Hague, The Netherlands, 7–11 Sep 2026, EPSC2026-721, https://doi.org/10.5194/epsc2026-721, 2026.
EuroMoonMars is an ILEWG programme [1-235] in collabo ration with space agencies, academia, universities and re search institutions and industries. The programme includes research activities supporting Moon and Mars Missions for data analysis, instruments tests and development, field tests in MoonMars analogue, pilot projects, training and hands-on workshops, technical visits and outreach activities. Support for Moon, Mars and Space Missions: we have contributed to lunar missions (SMART-1, Kaguya, Chang’E 1-8, LCROSS, LRO, Chandrayaan 1-3, CLPS), as well as Mars missions (Mars Express, MRO, MER, Curiosity, Per severance, ExoMars TGO 2018 and Rosalynd Franklin Rov er 2028). LUNEX is participating to future lunar lander mis sions, including commercial landers, in particular Qosmosys and from CLPS and Artemis programme. LUNEX CEO Prof Foing is now Chief Scientist for Qosmosys lunar lander, and is coordinating possible lunar science and exploration pay loads, with LUNEX EMMESI supporting instruments teams. Data analysis, AI and Machine Learning for Space: we have developed with collaborators advanced analysis of space and astronomy data at EMMESI academy. This in cluded analysis of Earth, Moon, Mars, exoplanet time series 56th LPSC (2025) 1316.pdf & spectroscopy data . We are developing generic and spe cialized tools for AI machine learning analysis (Fazel et al). 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 Raman . 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 spectros copy, Raman spectroscopy and microscopy. We also adapted an Hyperspectral camera for sample analysis and for tele scopic observations of the Moon and other celestial objects. Space Photonics Lab : this is being developed with in col laboration 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 extracting organics from icy moons of Jupiter and Saturn, with special prototype for Enceladus plumes or surface. LUNEX ExoGe oLab 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 universi ty education cubesats with the support of Leiden University (Observatory, LIACS computer science, Physics and Optics), Leiden Instrument Schools LiS, Deft TU, InHolland Delft, ESA BIC. The development starts with a table top bench & a prototype 3U system, with spacecraft and payload func tions. First applications include an Earth and Moon remote sensing cubesat, a 3U adapted on a lunar rover platform, and a 3U shoe-box instrument deployed from surface lander. Field work and testing of instruments and protocols. Extreme environments on Earth provide similar terrain con ditions to sites on the Moon and Mars, in order to rehearse mission operations in the field and through simulations. Eu roMoonMars field campaigns were organised in specific locations of technical, scientific and exploration interest. EuroMoonMars co-sponsored Vulcano 2024 Geo Astrobiology field school, and a specific EuroMoonMars field tests at Etna, building on the experience of campaigns conducted earlier with DLR and ESA for ROBEX 2019, and ARCHES 2022 campaigns (Wedler et al 2017 & 2022) EuroMoonMars Analogue astronauts simulations. Lunex EuroMoonMars, has been organizing since 2009 in collabo ration with ESA, NASA, European and US universities a programme of data analysis, instrumentation tests, field work and analog missions for students and researchers in different locations worldwide, including Utah MDRS, IMA Hawaii HI-SEAs, Iceland, Etna/ Vulcano Italy, Atacama, AATC Poland, ESTEC Netherlands, Eifel Germany, etc… Analogue missions provide a practical ground in which researchers can test in a realistic simulation context. During these missions, students have access to special Space instrumentation, labor atories, Facilities, Science Operations, Human Robotic part nerships. In 2023-26, EuroMoonMars co-sponsored EMMPOL Moonbase isolation simulation campaigns in Po land (Hutchison, Laforet, Tataj, Della Guardia) , and at IMA International Moonbase Alliance HI-SEAs (EMMIHS) . ExoSpaceHab Xpress (ESH-X) is an innovative portable lunar base simulator designed for education, analog missions and public outreach. This habitat has been funded by Euro pean consortium EuroSpaceHub and its partner LUNEX EuroMoonMars. After inauguration at Padova Botanical Garden in Italy, ExoSpaceHab-X was shown 20/9-13/10 2023 at the Science week fair of ENS Paris Saclay, and then used at SBIC Space Business Innovation Center Noordwijk in Oct-Dec, then in Leiden with University Jan-April 2024 and 3Aug-18 Sept, Pleaux Auvergne 8 May-1 Aug, Padova Science Festival with 2000 visitors, Grenoble University Space Center in October. It is also planned for other locations in Europe. ESH-X lab-hab module is used to test experiments and investigations for Artemis programme. ExoSpaceHab-Xpress Lunar Module developed by LUNEX for research training, astronautics simulations, business innovation & outreach. Acknowledgments: We thank collaborators and partner institutions from EMMESI academy, EuroSpaceHub/GreenSpaceHub Consortia, ESA ESTEC, NASA, EuroMoonMars programme, Space Renaissance International, Qosmosys & Moon Village
https://ui.adsabs.harvard.edu/search/q=euromoonmars%20or%20eurogeomars %20or%20ilewg
How to cite: Foing, B. and the LUNEX EuroMoonMars team: ILEWG LUNEX EMMESI EuroMoonMars Earth Space Innovation Highlights , Europlanet Science Congress 2026, The Hague, The Netherlands, 7–11 Sep 2026, EPSC2026-764, https://doi.org/10.5194/epsc2026-764, 2026.
Analog missions represent a critical bridge between terrestrial research and the operational realities of future lunar surface habitats. As humanity prepares for sustained presence on the Moon Village, understanding how spatial configuration and habitat design influence crew performance, psychological well-being, and operational safety becomes essential.
This contribution presents the coordination framework and research design of the EuroMoonMars AATC Poland 2026 analog campaign, a 9-day mission schedule for July 2026 at the AATC analog habitat in Poland. The campaign integrates a multidisciplinary, crew-led research study focused on human factors in space habitat configuration, applying an activity-based architectural approach to evaluate how habitat layout, ergonomic design, and environmental stimuli affect crew dynamics in isolated and confined environments (ICE).
Coordination efforts encompass the full mission scope: scientific experiment design, logistical planning, crew role assignment, operational scheduling, and outreach strategy. The research methodology combines pre- and post-mission psychological surveys, behavioral mapping, spatial heat maps, ergonomic audits, simulated emergency evacuation drills, and environmental logging of lighting and sensory interventions. Data collected will serve as the foundational dataset for post-mission digital twin modeling using Unreal Engine 5, contributing to broader thesis research on procedural habitat design.
Key coordination challenge addresses include balancing parallel research objectives within a constrained 9-day timeline, managing crew workload across simultaneous scientific and operational tasks, and ensuring data consistency across mixed quantitative and qualitative methodologies.
Results and Lessons learned from this campaign will provide actionable architectural guidelines for future analog and lunar habitat design, directly informing the ILEWG and broader planetary science community on best practices for crew-centred habitat configuration in preparation for Moon Exploration.
How to cite: Fong, G. and Foing, B. and the LUNEX EuroMoonMars/ISU EMMPOL team July 2026: Coordinating a Human Factors EuroMoobnMars Poland EMMPOL 2026 Research Campaign at the Lunar Base Mission with AATC Analog Astronaut Training Center , Europlanet Science Congress 2026, The Hague, The Netherlands, 7–11 Sep 2026, EPSC2026-1395, https://doi.org/10.5194/epsc2026-1395, 2026.
Upcoming lunar missions are renewing opportunities to return samples from underrepresented terrains and sample states. Existing Apollo, Luna and Chang'e collections provide foundational science, but do not fully capture polar cold traps, farside and deep-crust contexts, pristine surface states, depth-resolved volatile stratigraphy, or transient properties requiring controlled return-chain conditions. For cold and volatile-rich materials, scientific value depends on retaining diagnostic properties such as volatile abundance and isotopic composition, phase state, stratigraphy, reactive surfaces, magnetic signatures, and contamination records from collection through analysis. The ESA-funded Lunar Cold and Transient Volatile-rich Return Sample Chain Needs activity addresses how science objectives, sample needs, and sample-integrity considerations can be linked to future European lunar return-chain planning.
This presentation will summarize preliminary results from the return-chain project, focusing on community input on science priorities and sample needs. We will discuss how broad lunar science drivers can be translated into target sample families, representative sampling modes, and diagnostic properties that must be retained. We will describe how these community-derived inputs are being used to identify knowledge gaps and to prepare prioritized return-chain requirements for later project work. The emphasis is on general lessons for future sample-return mission design rather than a single mission architecture.
The assessment combined a focused literature and sample-return heritage review with a structured online community survey and follow-up interviews with selected European experts. Survey and interview responses were coded to identify recurrent science questions, missing or underrepresented sample types, desired geological settings, contextual information, sample amounts, and analytical needs. Existing returned collections were mapped against sample type, provenance, context, sample state, contamination knowledge, and access constraints. The synthesis links science objectives to sample-package needs and to return-chain drivers including temperature, pressure and headspace, contamination, mechanical disturbance, magnetic exposure, and post-return handling.
Community input indicates that future sample return should be framed around targeted sample utility, not simply total returned mass. High-priority needs include cold-trap and permanently shadowed region volatile-rich materials; depth-registered volatile stratigraphy; topmost and shallow regolith preserving surface-bound species and dust state; palaeoregolith and stratified cores; young, old, and compositionally unusual volcanic materials; farside and primary crustal lithologies; South Pole-Aitken and impact-melt materials; mantle or lower-crust candidates; oriented magnetic samples; and biological or lunar-contact exposure samples. Cross-cutting return-chain drivers include retention of volatile, isotopic, mineralogical, magnetic, textural, and reactive-surface properties; preservation of geological context and stratigraphic order; and robust contamination knowledge supported by witness materials, blanks, contact-material records, and environmental logs. The survey also shows that several requirement thresholds remain only qualitatively defined, especially for mixed ice-regolith systems, transient thermal excursions, vibration and shock impacts on cores or fragile regolith, magnetic cleanliness, and acceptable contamination levels for volatile, organic, and surface-sensitive measurements. Presenting community-derived science and sample needs together with their return-chain implications, this work supports a more systematic European view of how future lunar sample-return elements can maximize science return while acknowledging technical feasibility, mission resources, and operational constraints.
How to cite: Mikesell, T. D., McDonald, F., Consuma, G., Griffiths, L., Pirie, P., Hahn, C., Sætre, C., Hutzler, A., Martin, M., Dublet-Aldi, G., Quinteros, V. S., and Kim, T.: European community-derived science and samples needs for future Lunar sample-return chains, Europlanet Science Congress 2026, The Hague, The Netherlands, 7–11 Sep 2026, EPSC2026-1145, https://doi.org/10.5194/epsc2026-1145, 2026.
In the context of increased environmental awareness that characterizes the first half of the 21st century, COSPAR has invited the space science community, via all of its Commissions, Panels and Associates representing the different disciplines and countries engaged in Space Exploration, to contribute to the development of a new Exploration Roadmap. This roadmap will present a Vision for the period 2026-2046, and a list of actions for the next decade, 2026-2036. The starting point of the design of this new Roadmap was to ask the space science community to answer the three following questions:
1- what international cooperation activities should COSPAR propose and possibly coordinate to maximize the science return of space exploration?
2- which science questions and challenges should be addressed in priority by the exploration program, in each field or domain of activity?
3- what actions should COSPAR propose to protect the environment and cultural heritage of celestial bodies?
In this communication, we will report for the first time to the European Planetary Science community assembled at the EPSC2026 about the proposed contents of the Roadmap, based on community responses to these three questions and on the synthesis proposed at the COSPAR 2026 Assembly in Florence, just one month before the EPSC. We will place a special emphasis on the central role played by international cooperation in Lunar exploration in this new Roadmap, and on the key role that the European science community is ideally prepared to play in the implementation of the Roadmap in the coming two decades. We will open all propositions of Roadmap actions to comments and suggestions by EPSC participants.
How to cite: Blanc, M., Foing, B., Galli, A., Smith, H., and Yano, H.: TOWARDS A NEW COSPAR EXPLORATION ROADMAP 2026-2046: A preliminary presentation of the Roadmap vision and proposed actions, with focus on LunarExploration., Europlanet Science Congress 2026, The Hague, The Netherlands, 7–11 Sep 2026, EPSC2026-1388, https://doi.org/10.5194/epsc2026-1388, 2026.
Introduction: As the scientific community plans for future in-situ exploration of the Moon, new instruments are being developed to meet its numerous objectives. Studying the chemical composition of the lunar crust remains an important focus. For example, searching for mantle exposures, KREEP-rich material, and volatile inventories are subjects of investigations outlined in the Artemis III Science Definition Team Report [1]. Laser Induced Breakdown Spectroscopy (LIBS) is a spaceflight-proven technique for rapidly quantifying chemical elements in geologic samples that is well suited for each of these objectives [2]. In LIBS, a pulsed laser is fired at a geologic target. A plasma then forms that cools, emitting light with energy specific to the elements present.
LIBS imaging is an emerging technique that has been applied in terrestrial geology and biology. Rather than sparse rasters, LIBS imaging involves creating dense scans (50-200 microns between points). In this way, a mm- or cm-scale image is created with each pixel composed of a LIBS spectrum. LIBS imaging has the ability to reveal chemical heterogeneity at the scale of individual grains in geologic targets - particularly valuable for studying coarsely crystalline igneous and brecciated lunar rocks. LIBS’s ability to quantify light elements gives it a significant advantage over X-ray fluorescence mapping, which is generally limited to elements heavier than Na (Z=11) [2,3].
This abstract describes a major element calibration with a flight-relevant lunar LIBS setup and applies it to chemically map a lunar feldspathic breccia, effectively simulating an in-situ analysis by a lander or rover on the Moon. A ~1.4 x 2.5 cm polished slab of the lunar meteorite Laâyoune 002 was purchased for this work. Laâyoune 002 was found in Western Sahara in 2022 and has been classified as a low weathering grade lunar feldspathic breccia [4].
LIBS Calibration: The goal of a LIBS calibration is to derive elemental compositions from raw spectra. First, 96 pressed pellets (26 mineral standards and 70 mixtures) with known chemical compositions were shot with LIBS in a lunar vacuum chamber (<10-4 mbar). These standards spanned a range of chemical compositions and matrices, including anorthosite, norite, basalt, ilmenite, pyroxene, and olivine. These spectra were input into different regression models commonly applied to LIBS calibrations. The optimal model for each major element (Si, Fe, Mg, Al, Ti, Ca, K, and Na) was trained using a 5-fold cross-validation scheme implemented with scikit-learn. Models for each element were compared based on their Root Mean Square Error of Prediction (RMSEP) and performance over different matrices, with the best performing model for each element reported (Table 1). Limits of detection (LOD) of each element were found statistically by using the slope of the calibration line and the standard deviation of the background signal (LOD2, as described in Lasue et al. [5]).
Figure 1. LIBS spectrum of an anorthosite pellet taken in vacuum conditions, with element lines annotated.
Table 1. RMSEP and LOD for all major elements
|
Element |
RMSEP (wt.%) |
LOD (wt.%) |
|
SiO2 |
3.98 |
4.8 |
|
MgO |
0.80 |
0.24 |
|
FeOT |
1.89 |
0.46 |
|
Al2O3 |
2.62 |
0.38 |
|
CaO |
1.49 |
0.12 |
|
Na2O |
0.43 |
0.24 |
|
K2O |
0.53 |
1.07 |
|
TiO2 |
1.79 |
0.22 |
LIBS Mapping: After LIBS spectra of pressed pellets were collected for test and training data, the Laâyoune 002 slab was placed in the lunar vacuum chamber and mounted on a Zaber XY stage. LIBS observations were then made, spaced in a 40x40 grid, with individual points spaced 150 microns apart. The median composition of all analyses is summarized in Table 2.
Table 2. Global median elemental composition of the scanned area.
|
Element |
Median (wt.%) |
|
SiO2 |
47.80 |
|
MgO |
1.61 |
|
FeOT |
4.63 |
|
Al2O3 |
28.93 |
|
CaO |
13.76 |
|
Na2O |
1.41 |
|
K2O |
0.37 |
|
TiO2 |
0.17 |
|
Total |
98.57 |
The high Al2O3 and CaO content of the scanned area (28.93 and 13.76 wt.%, respectively) suggests the Laâyoune 002 sample is dominated by Ca-rich plagioclase (anorthite) with minor olivine and orthopyroxene, which is consistent with other feldspathic lunar meteorites. The average derived normative plagioclase abundance is 86-89%, suggesting a strongly feldspathic lithology. Clast boundaries are clearly visible in elemental data (Fig. 2), demonstrating strong chemical heterogeneity at the sub-millimeter scale, and this variability is reflected in bimodal distributions of some major elements. The light-toned ~4x1 mm clast near the center of the scan, expected to be plagioclase-rich based on reflectance spectra, shows enhanced Al2O3 (~35 wt.%), CaO (~16 wt.%), SiO2 (~49 wt.%) and depleted FeOT (~2.5 wt.%).
Figure 2. LIBS-derived elemental heatmaps (left) and a true color image of the Laâyoune 002 slab, with a white box indicating the scanned region (right).
Discussion: In this work, LIBS mapping with planetary samples was demonstrated for the first time. A custom elemental calibration was developed, showing that a spaceflight-relevant LIBS setup can distinguish major rock-forming minerals under lunar environmental conditions. Elemental scans of a polished slab of Laâyoune 002 confirmed its composition is consistent with a feldspathic breccia dominated by anorthite and low-calcium pyroxene (<5 wt.% FeOT, >25 wt.% Al2O3, and <1 wt.% TiO2 in Table 2). No spatially coherent zones with significant FeOT and MgO enrichment were observed, indicating that the mapped region does not contain clasts derived from mare basalts or lower crust mafic material. Given the lack of mare-derived, alkali-, or KREEP-rich clasts, it is possible Laâyoune 002 was ejected from deep within the lunar highlands, but LIBS scans over a much larger area on the sample would be required to make this claim with confidence.
References: [1] Artemis III Science Definition Team (2022) NASA, 186 pp. [2] Cremers D. A. and Radziemski L. J. (2013) John Wiley & Sons, Ltd. [3] Rapin W. et al. (2017) Spectrochimica Acta Part B: Atomic Spectroscopy. [4] Gattacceca et al. (2023) Meteoritics & Planetary Science, pp. 901-904. [5] Lasue et al. (2012) JGR: Planets, 117, E1.
How to cite: Manelski, H., Bedford, C., Lee, D. J., Wiens, R., Gillis, J., Vannier, H., Klidaras, A., Jolliff, B., Ollila, A., Clegg, S., Rapin, W., and Fraeman, A.: Chemical Mapping of a Lunar Meteorite Using LIBS: Implications for Future In-Situ Exploration, Europlanet Science Congress 2026, The Hague, The Netherlands, 7–11 Sep 2026, EPSC2026-68, https://doi.org/10.5194/epsc2026-68, 2026.
The CubeSat standard has been shaping small satellite development for over two decades. What started as a university tool for hands-on spacecraft engineering has grown into a framework used by agencies and companies worldwide. The key insight was never just miniaturization but standardization,
which made development faster, cheaper, and repeatable. In recent years, the same logic has been applied to planetary surface mobility. Concepts like the CubeRover (Astrobotic/Carnegie Mellon, Iris launched 2024) and the HiveR (von Unwerth et al., Advances in Astronautics, 2023) have shown that adapting
CubeSat mechanical standards to wheeled surface platforms is possible and opens surface science to a wider range of teams and institutions. The logic is the same: standardized form factors, off-the-shelf components, and development cycles accessible to students that can still produce hardware with real mission relevance.
The work presented here integrates a 3U CubeSat mechanical base into a fully operational remote-controlled rover for in-situ spectral measurements at the DECOS MoonMars analogue facility in Noordwijk, Netherlands. The rover was developed by students under Dr. Mojtaba Raouf and Prof. Bernard
Foing at Leiden University as a demonstration platform for CubeSat-scale in-situ science. The platform uses a four-wheel tank-drive configuration driven by two L298N motor driver modules controlled by an Arduino Uno over USB serial at 115200 baud. A Raspberry Pi 3B+ serves as the onboard computer.
The spectrometer is an Ocean Optics USB4000 fiber-coupled unit covering 196 to 913 nm, interfaced through SpectraLabPro, an open-source Python-based instrument interface developed by Dr. Raouf and built on the python-seabreeze library, supporting live spectrum display, dark subtraction, and reflectance
measurements.
The mission session was conducted as a full analogue operation with two operators. The first operator suited up in EVA simulation gear, carried the rover to the target area at the DECOS field site, positioned it near the sample rocks, connected the power and established the WiFi network, then returned to the
vehicle which served as the habitat and command module. Once inside, the helmet was removed and the laptop was used to connect to the rover over WiFi, beginning the remote teleoperation phase. At no point during the science phase did the first operator have direct visual contact with the rover or the field
site. Navigation and sample targeting relied entirely on the onboard camera feeds. A second operator remained outside at a distance with binoculars providing continuous visual observation of the rover and its surroundings, relaying situational awareness to the first operator via radio throughout the session. This two-operator setup mirrors the setup of a surface EVA crew member and a habitat-based mission controller, with the external observer giving the mission controller an extra set of eyes on the rover during the analogue test.
Figure 1: EVA phase: suited operator positioning the
rover at close range to a rock target before returning to
the habitat vehicle.
Figure 3: Remote teleoperation from inside the habitat
vehicle. The operator has no direct visual of the rover or
field site during the science phase.
Figure 4: SpectraLabPro GUI showing live spectrum
acquisition alongside the Pi Camera feed of the mineral
sample.
Acknowledgements
This work was supported by the ILEWG LUNEX EuroMoonMars grant. The authors thank the LUNEX
EuroMoonMars EMMESI team and co-supervisors from Leiden University, Inholland Delft, and TU Delft
for their support and collaboration. Related activities are described in Foing et al. (LPSC 2025, abstract
1316) and Foing et al. (LPSC 2026, abstract 1625).
How to cite: Martin Enciso, I. G., Foing, B. H., Raouf, M., and Zhikhareva, A.: Rover-Based In-Situ Spectral Acquisition at a Lunar-Martian Analogue Site, Europlanet Science Congress 2026, The Hague, The Netherlands, 7–11 Sep 2026, EPSC2026-153, https://doi.org/10.5194/epsc2026-153, 2026.
1. Introduction and scientific objectives
The MINISPEC (Moon IN-situ Imaging SPECtrometer) instrument concept has been conceived with the aim to perform imaging spectroscopy directly from the lunar surface. Operating in the infrared (IR) spectral range from 0.8 to 4 µm, the instrument addresses critical needs for future lunar exploration.
The primary scientific objectives of MINISPEC are:
- mapping the local geological context near landing sites selected for robotic rovers or human crews;
- identifying hydrated minerals (H2O/OH) and detecting volatile compounds potentially trapped beneath the surface regolith;
- discriminating between adsorbed water and water ice.
2. Performance requirements
One of the challenges of the design is the optical head layout. Balancing the required optical performance with the compactness of the instrument, available mass and power resources and the harsh lunar environment.
MINISPEC utilizes a compact hyperspectral architecture based on a Linear Variable Filter (LVF) coupled with a proven space-qualify detector.
Key desired features are:
- A wide field of view angle (target 20°)
- The capability to focus both at infinity and at 1-2 meters.
- A spectral resolution of 30/40 nm across the wavelength range.
3. Technological challenges
Active illumination
For the MINISPEC instrument an active wide-band illumination concept is considered.
The goal of this subsystem is the capability to perform spectral measurements in low lunar illuminated regions, during the lunar night or in permanently shadowed regions.
Thermo-mechanical design
The lunar peculiar environment coupled with the IR working spectral range require a thorough study of the thermo-mechanical design for the instrument. The detector needs to be cooled and also the optical head. An active solution is foreseen for the detector and a passive one for the head.
Different thermal architectures are presently being considered and simulated.
Materials and coating development
In the framework of the instrument study experimental facilities are implemented for validation for advanced optical materials. These will allow the characterization of optical components, and possibly lunar analogues measurements, across a wide range from 400 nm to 5 µm to ensure long-term stability and high reflectance/transmittance and prove instrument reliability.
4. Conclusions
The MINISPEC instrument design study aims at realizing a new class of compact planetary spectrometers for the lunar surface.
Different challenges are address by the project team: radiometric modelling, optical layout, illuminator and thermo-mechanical designs.
MINISPEC aims to advance the technological maturity of a compact imaging spectrometer for in-situ characterization of both lunar and planetary surfaces.
Acknowledgements
The MINISPEC project is funded by the Italian Space Agency (ASI) via Contract number 2024-1-U.0.
How to cite: Da Deppo, V., Tosi, F., Saggin, B., Crescenzio, G., Zuppella, P., Frassetto, F., and Tiberia, A. and the MINISPEC Team: MINISPEC Moon IN-situ imaging SPECtrometer: an innovative compact IR spectrometer for lunar surface exploration , Europlanet Science Congress 2026, The Hague, The Netherlands, 7–11 Sep 2026, EPSC2026-757, https://doi.org/10.5194/epsc2026-757, 2026.
We present an innovative, cost-effective framework integrating laboratory Hyperspectral Imaging (HSI) of the Bechar010 Lunar meteorite with ground-based lunar HSI and supervised Machine Learning(ML) to generate high-fidelity mineralogical maps. A 3mm thin section of Bechar010 was imaged under a microscope with a 30mm focal length lens at 150mm working distance, using 6x binning to increase the signal-to-noise ratio, producing a data cube (X × Y × λ = 791×1024×224, 0.24mm × 0.2mm resolution) across 400-1000}nm (224 bands, 2.7nm spectral sampling, 5.5nm full width at half maximum spectral resolution) using a Specim FX10 camera. Ground-based lunar HSI was captured with a Celestron 8SE telescope (3km/pixel), yielded a data cube (371×1024×224). Solar calibration was performed using a Spectralon reference ({99}\% reflectance {<2}\% error) ensured accurate reflectance spectra. A Support Vector Machine (SVM) with a radial basis function kernel, trained on expert-labeled spectra, achieved {93.7}\% classification accuracy(5-fold cross-validation) for olivine ({92}\% precision, {90}\% recall) and pyroxene ({88}\% precision, {86}{\%} recall) in Bechar 010. LIME analysis identified key wavelengths (e.g., 485nm, {22.4}\% for M3; 715nm, {20.6}\% for M6) across 10 pre-selected regions (M1 to M10), indicating olivine-rich (Highland-like) and pyroxene-rich (Mare-like) compositions. SAM analysis revealed angles from 0.26 radian to 0.66 radian, linking M3 and M9 to Highlands and M6 and M10 to Mares. K-means clustering of Lunar data identified 10 mineralogical clusters ({88}\% accuracy), validated against Chandrayaan-1 Moon mineralogy Mapper (M3) data (140m/pixel, 10nm spectral resolution).A novel push-broom HSI approach with a telescope achieves 0.8 arcsec resolution for lunar spectroscopy, inspiring full-sky multi-object spectral mapping.
How to cite: Fazel, F., Raouf, M., Foing, B., Verbeek, F., Chegeni, A., and Chatzitheodoridis, E.: Connecting Meteorite Spectra to Lunar Surface Composition Using Hyperspectral Imaging and Machine Learning, Europlanet Science Congress 2026, The Hague, The Netherlands, 7–11 Sep 2026, EPSC2026-917, https://doi.org/10.5194/epsc2026-917, 2026.
Introduction
The transition from episodic lunar missions to a permanent settlement demands a fundamental shift in architectural methodology—moving beyond discrete, passive habitat modules toward integrated, kinetic urban systems. The Horizon Protocol presents a masterplan for a 100-person Moon Village distributed across three interdependent spatial domains: a polar surface spaceport, subsurface lava tube settlements, and a variable-gravity orbital station. This multi-node topology is integrated by a maglev and hopper surface transport network that functions as the settlement's primary urban spine, enabling resource exchange and logistical redundancy.
Autonomous Robotic Environments & Sentient Infrastructure
To address extreme thermal cycling, radiation, and seismic events, the design treats lunar architecture as an autonomous, environment-responsive robotic agent. At the polar surface, bases deploy "Sentient Infrastructure" equipped with a structural "nervous system." This includes adaptive geo-robotic foundations that function as a suspension system to mitigate moonquake propagation, and the embedding of piezoelectric sensors within 3D-printed ISRU composites for autonomous fatigue detection and self-repair. Furthermore, the protocol applies Model-Based Systems Engineering (MBSE) to validate the "Reflex Arc" logic gates, allowing these modular skins to dynamically reconfigure for optimal radiation shielding without requiring Extravehicular Activity (EVA).
Figure 1: Sentient Infrastructure: Treating lunar habitats as autonomous robotic agents.
Subterranean Kinetic Urbanism in Lava Tubes
Underground, low-latitude lava tubes host the principal long-duration habitation through a system of "Subterranean Kinetic Urbanism." Within this domain, a distributed robotic tensegrity scaffold suspends habitat modules directly within the tube center. This architectural approach provides 360° seismic isolation while the scaffolding doubles as integrated life-support nodes for atmospheric scrubbing and full-spectrum circadian lighting, establishing a highly secure and psychologically supportive environment.
Variable-Gravity Orbital Domain
To complete the protocol, a variable-gravity orbital station featuring a rotating architecture serves as the primary orbital gateway. Rather than pre-defining specific gravitational fields, this research will assess the feasibility and structural constraints to define how many varying gravity zones can be safely utilized within the constructed orbital environment. This infrastructure acts as both a logistical transit hub and a vital medical reconditioning node, assessing and managing physiological adaptations prior to crew return to Earth.
Empirical Human-Centric Validation and Conclusion
To transition from generative morphology to verified engineering logic, design proposals are empirically validated through a multi-campaign analog program. Utilizing behavioral mapping and ergonomic workflow audits from the AATC Poland 2026 mission, primary empirical data is synthesized with secondary volumetric and operational assessments of the EuroMoonMars (EMMPOL) and ExoSpaceHab Express habitats. By translating lived human experience in isolated environments into spatial design criteria, the Horizon Protocol provides a replicable methodology for lunar urbanism. It treats environmental extremes not as constraints, but as the primary generators of architectural form and resilient settlement structure.
How to cite: Velimirovic, N. and Nyamukondiwa, R.: The Horizon Protocol - Masterplanning Permanent Moon Village through Autonomous Robotic Environments and Sentient Infrastructure., Europlanet Science Congress 2026, The Hague, The Netherlands, 7–11 Sep 2026, EPSC2026-1057, https://doi.org/10.5194/epsc2026-1057, 2026.
As lunar missions transition from sporadic trips to persistent ground operations under the Artemis and the International Lunar Decade fundamentally changes the arrival and handling of cargo at the Moon's surface. All replenishment shipments encompass foodstuffs, pharmaceuticals, and testing materials, each arriving with packaging: lightweight polyethylene bags, PET-aluminum-LDPE (PAL) trilaminates, biaxially oriented polypropylene films, HDPE
containers, ZOTEK foam insulation, and Mylar/BoPET protective sheeting. Under current paradigms, this constitutes non-metabolic solid waste with no disposal pathway short of Earth return. We argue this framing is incorrect: these materials represent a secondary feedstock stream arriving at the lunar surface pre-sorted and in known quantities.
This work presents a framework for integrating mission packaging waste into the lunar construction and manufacturing supply chain through three complementary routes. First, LDPE and other thermoplastics can be compounded with lunar regolith simulant (up to 30 wt%) to produce filaments suitable for fused filament fabrication (FFF), yielding composite parts with improved overhang performance, reduced warpage, and maintained tensile strength relative to pure-polymer prints. Second, food containers with multiple layers can be processed via thermochemical conversion to gasification that sets fire to polymer layers and isolates Al 1235 foil as a solid product; this recovered metal is compatible with bound metal deposition (BMD)
additive manufacturing for structural hardware. Third, heterogeneous plastic waste subjected to pyrolysis yields carbon char and gaseous hydrocarbons that can improve regolith-binder mixtures or serve as chemical feedstocks.
Cryogenic night temperatures can be used to embrittle packaging polymers and foams, enabling low-energy cryo-grinding into fine powder feedstock without mechanical milling infrastructure.
Conversely, the diurnal thermal swing and boosted solar energy exposure during Moon day furnish the required warmth for sulfur retrieval from troilite (FeS), sulfur-based regolith concrete formation at 130-140°C, and sintering of regolith-based ceramic components. Together, these pathways offer a closed-loop model in which cargo packaging is not a waste stream but an anticipated construction input, timed to mission cadence. We present a materials inventory
model linking typical 30-day crew mission packaging manifests to projected AM feedstock yields, and discuss integration with regolith-based sulfur concrete and geopolymer binder systems for habitat construction. The thermal processing windows unique to specific lunar latitudes and the implications for base siting are also discussed. This work contributes to the quantitative case for lunar circular economy design at the mission planning stage, rather than as
an afterthought.
Keywords: Lunar ISRU, Packaging Waste, Additive Manufacturing, Recycling
How to cite: Jangam, V. and Foing, B.: In-Situ Conversion of Mission Packaging Waste into Additive ManufacturingFeedstocks for Lunar Bases, Europlanet Science Congress 2026, The Hague, The Netherlands, 7–11 Sep 2026, EPSC2026-1400, https://doi.org/10.5194/epsc2026-1400, 2026.
The prediction of Solar Activity is critical in the context of space weather and associated technological implications. Many methods have been proposed towards this and for identifying precursors of solar activity. Primarily, only whole 2D magnetograms have been used for this purpose. While physics-based models are important, we show that using light-curves reduces the dimensionality of the problem and provide interesting and useful results. Using data from Chandrayaan-2’s XSM from the ISSDC archive and GOES from NCEI, prediction of flares, background and event timing accurate to 99% has been demonstrated.
The data-driven nature of the model allows it to be applied on other wavelengths such as EUV. We aim to extend the testing and applications to a wider range of data from other missions like PROBA-3 and Aditya-L1 and from others stellar sources. Such input from Kepler, TESS and in preparation for PLATO could contribute towards habitability studies as well. Magnetogram (3D) inputs will be integrated to create a comprehensive model, and comparison of these with ground-based white light and H-alpha images conducted.
We also intend concept development of a CubeSat bus (3 or 6 U) for imaging and monitoring. Upon comparison of the main model (LSTM) with a lighter-weight and more resource-efficient network (GRU), we find the GRU provides comparable predictions to the LSTM and thus would be more amenable with CubeSat applications and parts of onboard processing where resource usage becomes critical.
How to cite: Ravishankar, S., Ravishankar, B. T., Sudhakar, M., Nyamukondiwa, R., and Foing, B.: A Lightweight Solar Activity Prediction Model compatible with CubeSat, Europlanet Science Congress 2026, The Hague, The Netherlands, 7–11 Sep 2026, EPSC2026-1398, https://doi.org/10.5194/epsc2026-1398, 2026.
Over the past decade, lunar exploration has evolved into a major arena for international scientific and technological cooperation. This paper analyzes the roles of China, Russia, and Europe in current Moon exploration efforts and examines how their interactions shape multilateral collaboration.
The study reviews recent and upcoming robotic missions: China’s successful Chang’e program, Russia’s Luna‑25, Luna‑26, and Luna‑27 - the latter originally planned with European cooperation. It also examines the International Lunar Research Station (ILRS), a crew‑capable project jointly initiated by China and Russia at the 2019 IAF GLEX in St. Petersburg. Beyond technology and science, the analysis incorporates legal, economic, socio‑cultural, historical, and human factors (workforce mobility, scientific schools, public perception). The emerging International Deep Space Exploration Alliance (IDSEA) is introduced, and its relationship with the ILRS is discussed.
The results indicate that China and Russia continue to develop their lunar programs, while Europe is re-evaluating its participation strategies. The paper concludes that lunar exploration serves as a platform for constructive international engagement, where shared scientific goals can foster cooperation across different spacefaring nations. Possible scientific and peaceful cooperation synergies with the Artemis programme and other national, international, and commercial multi‑stakeholder initiatives - in the spirit of the ILEWG Moon Village - are also discussed. Future research should focus on legal and economic frameworks that support sustainable multilateral lunar governance.
How to cite: Yuschenko, A. and Foing, B.: China, Russia, and Europe in Lunar Exploration: Scientific Cooperation and International Relations, Europlanet Science Congress 2026, The Hague, The Netherlands, 7–11 Sep 2026, EPSC2026-480, https://doi.org/10.5194/epsc2026-480, 2026.
Introduction: KEVION, a KiloElectron Volt ION irradiation facility for space science – one of NASA’s new Planetary Science Enabling Facilities – will begin full operation this Fall (2026) as part of the Laboratory for Astrophysics and Surface Physics at the University of Virginia (LASP-UVa). This resource facility is comprised of four major components: (1) a 25-300 keV Pelletron ion accelerator to provide positive atomic/molecular ions over a broad range of species, charges, and energies; (2) a novel, multi-technique analytical chamber (GRAINS) with low-energy ion gun built around an X-ray photoelectron spectrometer and in situ UV-Vis-NIR optical spectroscopy; (3) a specialized cryogenic chamber (ICE) for radiolytic astrochemistry studies of solid-state ices; and (4) a minimally-equipped chamber (TEST) for ion implantation, instrument performance testing, and user-customized experiments.
With the deployment of Juno, Juice and Europa Clipper to Solar System bodies with radiation-exposed surfaces, along with the anticipated Dragonfly and CNSA’s Tianwen-4 missions, and new galactic and interstellar science from the James Webb Telescope, the KEVION facility addresses an identifiable gap in available community tools for high-impact Planetary Science research. The KEVION high-energy linear accelerator, a Peabody Scientific light-ion accelerator, and low-energy (< 5 keV) ion guns will deliver positive ions appropriate for simulating magnetospheric, cosmic-ray, and solar wind interaction with surfaces to provide transformative research in studies of space weathering, radiolysis, radiosynthesis, sputtering, and surface charge. Meanwhile, the TEST chamber can be utilized to facilitate science instrument development and radiation damage.
Details: Investigators proposing across all NASA, ESA, JAXA, and other programs are invited to utilize the KEVION facility over the course of their research. A full-time facility instrument scientist (Dr. Adam Woodson) is available to assist with experiment planning, accelerator operation, instrument instruction, and analytical procedure. Specific details of the Pelletron accelerator and available analytical techniques associated with each end-chamber are outlined below and summarized on the KEVION website and at NASA’s science link, https://science.nasa.gov/wp-content/uploads/2024/01/kevion-2024.pdf.
Ion Accelerator: The National Electrostatics Corp. Pelletron ion implanter will generate isotopically pure ion beams with energies between 25 and 300 keV for simulated space weathering, radiolysis, materials characterization, measurement of fundamental parameters, and instrument prototyping applications. This range is sufficient to simulate a substantial cross section of energetic particles originating from the Sun, which vary in energy from ~300 eV/amu in the slow Solar Wind, to ~50 keV in transient Interplanetary Coronal Mass Ejection events, to > 1 MeV in the suprathermal tail. Similarly, magnetospheric ion energies generally range from a few keV to a few tens of keV as measured in Mercury’s and Titan's interaction regions, to MeV particle fluxes at the Moons of Jupiter [1-3]. The NEC instrument is designed to provide beam currents of 300 μA into the beamline Faraday Cup. Lower energy (0.2 – 4 keV) ions, appropriate for solar wind simulation, are available from a standard or m/q select-ed ion gun mounted on the GRAINS chamber.
GRAINS Chamber: The GRAINS chamber will enable comprehensive analytical measurement and monitoring of surface (1–3 monolayers, ML), near-surface (to ~10 nm depth) and bulk (to ~10 μm depth) material characteristics. In situ sample characterization can be done by: quadrupole secondary-ion mass spectroscopy (SIMS), X-ray photoelectron spectroscopy (XPS), Rutherford scattering (forward and RBS), and UV-Vis-NIR optical reflectance (or trans-mission). A low-energy ion gun for 3D compositional analysis by sputter depth profiling, charge neutralization, and irradiation can provide fluence dependent details over decades of energies/depths/time; and an electron flood gun for positive surface charge neutralization is available. Multiple, integrated analytical techniques on the same chamber eliminates the need to transfer samples between systems, thereby reducing the logistic complexity of such experiments as well as the risk of contamination due to atmospheric exposure.
ICE Chamber: Investigation into solid-phase radiochemistry is of high-importance, as icy bodies and granular surfaces act as substrates for simple and com-plex molecular species formation by gas-grain chemistry and photolytic / radiolytic reactions, and also serve as reservoirs for important reactive species in interstellar cold clouds. The ICE cryogenic end-chamber is equipped with an in-situ gas-dosing system, FT-IR spectrometer for Vis-IR reflectance / transmission, an in-situ quartz crystal microbalance system (QCM), a UV-Vis interferometer for coupled mass and density/porosity/thickness measurement, and a +/- ion-neutral mass spectrometer.
TEST Chamber: The TEST chamber is a large-diameter, mu-metal-lined UHV vacuum vessel, intended for instrument response testing over varied ion species/energies. In some instances, the TEST chamber may be outfitted with additional research tools from an investigator’s home institution for experiments beyond the capabilities of GRAINS or ICE.
Usage Information: The KEVION accelerator and analytical chambers are available at no cost for NASA awarded projects (~6 months/year), and we also welcome other ESA, JAXA, academic, governmental, and industrial clients as users at a nominal, tier-ed cost. Facility resources are available to clients “in person” with training, or analyses can be carried out “remotely” by facility personnel in consultation with users.
Contact Information: For more information on how to utilize the KEVION or to solicit information for proposals, please contact PI Dukes (cdukes@virginia.edu) or Instrument Scientist Woodson (akw8r@virginia.edu). Else, a “Request for Service” form can be submitted directly on the KEVION Website: https://engineering.virginia.edu/kevion.
Acknowledgments: We thank NASA for their support of the KEVION facility through the PSEF program (Award #80NSSC23K0200).
References: [1] Jasinski et al. 2020 [2] Connerney et al. 2017 [3] Bennett et al. Chem. Rev. 113, 12, 9086–9150 2013.
How to cite: Dukes, C. A., Woodson, A. K., Johnson, R. E., Terwisscha van Scheltinga, J., Ihlefeld, J., Reinke, P., Garrod, R., and Cleeves, L. I.: KEVION: An ion irradiation and sample analysis research facility for planetary science, Europlanet Science Congress 2026, The Hague, The Netherlands, 7–11 Sep 2026, EPSC2026-1198, https://doi.org/10.5194/epsc2026-1198, 2026.
How to cite: Ismayilova, G., Raouf, M., Martin Enciso, I., Zhikareva, A., and Foing, B. and the LUNEX EuroMoonMars/Leiden/Delft TU/ In Holland EMEC team: LUNEX EMEC3 Raspbi Rover: A Compact Teleoperated Rover for VNIRSpectroscopy in Planetary Analogue Environments, Europlanet Science Congress 2026, The Hague, The Netherlands, 7–11 Sep 2026, EPSC2026-1391, https://doi.org/10.5194/epsc2026-1391, 2026.
