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High-resolution Digital Terrain Models (DTMs) of the lunar surface can provide crucial spatial information for lunar exploration missions. In this paper, we propose a method to generate high-quality DTMs based on a synthesis of deep learning and Shape from Shading (SFS) with a Lunar Reconnaissance Orbiter Narrow Angle Camera (LROC NAC) image as well as a coarse-resolution DTM as input. Specifically, we use a Convolutional Neural Network (CNN)-based deep learning architecture to predict initial pixel-resolution DTMs. Then, we use SFS to improve the details of DTMs. The CNN-model is trained based on the dataset with 30, 000 samples, which are formed by stereo-photogrammetry derived DTMs and orthoimages using LROC NAC images as well as the Selenological and Engineering Explorer and LRO Elevation Model (SLDEM). We take Chang’E-3 landing site as an example, and use a 1.6 m resolution LROC NAC image and 5 m resolution stereo-photogrammetry derived DTM as input to test the proposed method. We evaluate our DTMs with those from stereo-photogrammetry and deep learning. The result shows the proposed method can generate 1.6 m resolution high-quality DTMs, which can clearly improve the visibility of details of the initial DTM generated from the deep learning method.

A model of the interaction of small meteoroid bodies with the Earth’s atmosphere, using the saturated vapor pressure of the meteoroid, was applied to analyze the light curves of meteors, making it possible to estimate the parameters of meteoroids. An automated method for estimating meteoroid body parameters was developed. The effect of uncertainty in the dependence of the saturated vapor pressure on the meteoroid body parameters is analyzed, the limitations and features of the model are discussed. Модель взаимодействия мелких метеорных тел с атмосферой Земли, использующая давление насыщенного пара вещества метеороида, была использована для анализа кривых блеска метеоров, что позволило оценить параметры метеороидов. Был разработан автоматизированный метод оценки параметров метеорного тела. Проанализировано влияние неопределенности в зависимости давления насыщенного пара от температуры на параметры метеорного тела, обсуждаются ограничения и особенности модели.

Table 2: Mean (ν) and standard deviation (σ) on separation s and position angle p (multiplied by the separation) in seconds of degrees for each satellite. N is the number of observations by satellite (one number per coordinate). The year appearing next to each observatory name corresponds to the observed Mars opposition. Table 3: Mean (ν) and standard deviation (σ) on right ascension and declination in seconds of degrees for each satellite. }N} is the number of observations by satellite. Table 4: Mean (ν) and standard deviation (σ) on right ascension and declination for each satellite. Both angles are multiplied by the distance spacecraft-moon to obtain kilometers. }N} is the number of observations by satellite. In the Pasewaldt et al. (2015) publication positions of Phobos have been determined using control point (CP) and/or limb point (LF) measurements. The former are based on the satellite's control network, a set of identifiable surface features well-distributed over the body's surface and defining its reference system. Recent MEX SRC measurements have been distinguished into observations made during linear and non-linear pointing variations. If the observations' pre-fit residuals deviated by more than three sigma from the mean value, they have been additionally categorised as an outlier. In case of only a few outliers it could not be clarified whether they have been related to non-linear variations in pointing or not. Some measurements are based on fits of the shape model-derived limb to only very short limb point arcs in the image (see also subsection 3.2.1). Table 5: Mean (ν) and standard deviation (σ) on sample and line in pixel and kilometer for each satellite. }N} is the number of observations by satellite. MRO (single) gathers data where only one moon was observable at a time. Table 6: Initial conditions and related uncertainties of Phobos and Deimos in the ICRF after fit at initial epoch J2000 (Julian day 2451545.0). Units are }km} and }km/sec}. All digits have been kept for reproducibility of our results. (5 data files).

The Moon is an archetypal atmosphere-less celestial body in the Solar System. For such bodies, 38 the environments are characterized by complex interaction among the space plasma, tenuous 39 neutral gas, dust and the outermost layer of the surface. Here we propose the SELMA mission 40 (Surface, Environment, and Lunar Magnetic Anomalies) to study how airless bodies interact with 41 space environment. SELMA uses a unique combination of remote sensing via ultraviolet and 42 infrared wavelengths, and energetic neutral atom imaging, as well as in situ measurements of 43 exospheric gas, plasma, and dust at the Moon. After observations in a lunar orbit for one year, 44 SELMA will conduct an impact experiment to investigate volatile content in the soil of the 45 permanently shadowed area of the Shackleton crater. SELMA also carries an impact probe to 46 sound the Reiner-Gamma mini-magnetosphere and its interaction with the lunar regolith from the 47 SELMA orbit down to the surface. SELMA was proposed to the European Space Agency as a 48 medium-class mission (M5) in October 2016. Research on the SELMA scientific themes is of 49 importance for fundamental planetary sciences and for our general understanding of how the 50 Solar System works. In addition, SELMA outcomes will contribute to future lunar explorations 51 through qualitative characterization of the lunar environment and, in particular, investigation of 52 the presence of water in the lunar soil, as a valuable resource to harvest from the lunar regolith.

The presentation summarizes INPPS (International Nuclear Power and Propulsion System) flagship non-human (2020th) and human (2030th) Mars exploration missions. The 2020th first flagship space flight is the complex, complete test mission for the second flagship towards Mars with humans (2030th). The most efficient approach is the completely tested first INPPS in the 2020th as the preparation of the second flagship with humans on board. The second INPPS (2030th) is also the regular space transportation tug Mars-Earth. International requests for human Mars space flight is realizable by rationales for pursuing two INPPS Mars missions in the proposed period: 1) successful finalization of the European-Russian DEMOCRITOS and MEGAHIT projects with their three concepts of space, ground and nuclear demonstrators for INPPS realization (2017), 2) successful ground based test of the Russian nuclear reactor with 1MWel plus the important thermal emission solution by droplet radiators (2018), 3) reactor space qualification by Russia until 2025 and 4) the perfect celestial Earth-Mars-Earth-Jupiter/Europa trajectory in 2026-2031 to carryout maximal INPPS space flight tests. Set of issues of INPPS space system and all subsystems became identified and studied during DEMOCRITOS. Consequently critical performance will be studied by parallel realizations of the ground and nuclear demonstrators (until 2025). The INPPS space demonstrator considers directly results of ground and nuclear demonstrator tests. Realization of the space demonstrator in form of the first space qualification of INPPS with all subsystems in the middle of the 2020th plus INPPS tests for about one to two years - first in high Earth orbit and later in nearby Earth space environment means a complete concepts driven approval for all INPPS technologies for non-human/human INPPS-Mars missions. Space subsystem results of MARS-INPPS design (with arrow wing shaped radiators) will be described. In dependence - from a cluster with worldwide selected electric thrusters - the MARS-INPPS payload mass is up to 18 tons. This very high payload mass allows to transport three different payloads at once - scientific, pure commercial and new media communication. The realization including tests is sketched: especially the need of non-human flagship Mars flight, the test towards Europa (including real time radiation monitoring) for maximal human Mars mission preparation for the second INPPS with humans to Mars. INPPS missions implicate Apollo and ISS comparable outcomes for science technologies, international dedication and in addition for space commercialization. Insofar - this MARS-INPPS presentation - convince high attendance of conference participants, commercial and new media investors.

We study the thermal conditions in the polar areas of the irregularly shaped Martian moon Phobos. As was previously discussed, we consider direct illumi- nation by the Sun, eclipses by Mars, Mars shine, and single scattering of solar light by other surface areas of Phobos.

We evaluate the gravity equilibrium forms of the irregular-shaped Martian moons, Phobos and Deimos. We derive their normal ellipsoids and propose the el- lipsoidal height system to characterize the surface to- pography. We study the height distributions on Pho- bos and Deimos and compare their statistics with those of nearly spherical terrestrial planets. We identify a new criterion for determining surface equilibrium of the Martian moons and discuss its generality to other small bodies.

We propose the co-registration of laser profiles to high resolution Digital Terrain Models (DTMs) as an approach for retrieving surface elevation changes at the poles of Mars. The edge of this method is validated using reprocessed and simulated Mars Orbiter Laser Altimeter (MOLA) profiles. The ultimate goal is to apply this method to MOLA and HRSC DTMs to generate seasonal and long-term elevation change time series at the Martian poles with high spatial and temporal resolution.

The goal of Project GAUSS is to return samples from the dwarf planet Ceres. Ceres is the most accessible ocean world candidate and the largest reservoir of water in the inner solar system. It shows active cryovolcanism and hydrothermal activities in recent history that resulted in minerals not found in any other planets to date except for Earth's upper crust. The possible occurrence of recent subsurface ocean on Ceres and the complex geochemistry suggest possible past habitability and even the potential for ongoing habitability. Aiming to answer a broad spectrum of questions about the origin and evolution of Ceres and its potential habitability, GAUSS will return samples from this possible ocean world for the first time. The project will address the following top-level scientific questions: 1) What is the origin of Ceres and the origin and transfer of water and other volatiles in the inner solar system? 2) What are the physical properties and internal structure of Ceres? What do they tell us about the evolutionary and aqueous alteration history of icy dwarf planets? 3) What are the astrobiological implications of Ceres? Was it habitable in the past and is it still today? 4) What are the mineralogical connections between Ceres and our current collections of primitive meteorites? GAUSS will first perform a high-resolution global remote sensing investigation, characterizing the geophysical and geochemical properties of Ceres. Candidate sampling sites will then be identified, and observation campaigns will be run for an in-depth assessment of the candidate sites. Once the sampling site is selected, a lander will be deployed on the surface to collect samples and return them to Earth in cryogenic conditions that preserves the volatile and organic composition as well as the original physical status as much as possible., Section 3.4 revised; List of team members updated; Typos corrected