Lunar soil studies are planned on-board the Luna-27 polar landing probe of the scheduled Luna-Recourse mission. A sensor, which is called DLS-L, was designed as an additional analytical unit, integrated into a Gas Chromatography GC-L instrument of a Gas Analytical Package, targeted to study products, pyrolytically evolved from soil samples of a close location near the Lunar probe landing point. Gas Analytical Package for direct study of volatiles in the accessible lunar regolith at the landing site is a complex of three instruments: a TA-L thermal analyzer, a GC-L gas chromatograph, and an NGMS neutral gas mass spectrometer. The DLS-L aims in an independent measurement of pyrolytical output dynamics and integral content of H2O, CO2, and in retrieving of isotopic ratios D/H, O-18/O-1(7)/O-1(6), C-13/C-12 for isotopologues of H2O and CO2. The DLS-L sensor data would help for further understanding of physics and chemistry of the Lunar body, as original data of polar Lunar soil first-ever direct study.

A renewed interest in Moon exploration has been forming in recent years due to its close proximity as well as identification of key resources such as water ice in Lunar polar regions. Furthermore, the launch industry has been transforming with increased availability in the variety and instance of spacecraft launchers. Additionally, rideshare missions are becoming the new norm. Rideshare missions not only to LEO but even to Geosynchronous Transfer Orbit are currently available, reducing the cost of access to the deep space. Electric propulsion is also becoming more widespread. Advances in these varied fields will possibly converge in capable small spacecraft designs that will be able to carry out complex missions in deep space. This particular study focuses on identifying key sizing parameters of such a spacecraft. An initial trajectory design utilizing AGI's Systems Tool Kit (STK) was carried out involving low-thrust orbit raising from Geosynchronous Transfer Orbit with eventual Lunar capture. Preliminary lunar station keeping was examined. Later, key design parameters such as eclipse times, communication durations etc. were investigated. Overall, a broad framework was obtained upon which optimization studies and preliminary design can be conducted.

In 1994, the bistatic radar sounding of the Moon was carried out from the Clementine spacecraft. Analysis of the measurement results showed that the intensity and polarization of the radio echo in a small region at the South Pole differed from the values typical of ordinary lunar soil, but were similar to those obtained from radar surveys of Greenland ice and Jupiter satellites. Thus, an assumption was made about the existence of water ice deposits in the lunar soil, which until now could neither be confirmed nor disproved. In 2023, the launch of the Russian Luna 26 orbiter is planned, on which a radar complex will be installed to conduct radar sounding of the Moon on megahertz waves. The main problem of bistatic observation of the Moon is the difficulty of determining the area that is involved in the formation of the reflected signal. Here we discuss the method of localizing the place of reflection of radio signals using the known ballistic parameters of a spacecraft and numerical simulation.

Mass spectrometers are valuable tools for the in situ characterization of gaseous exo- and atmospheres and have been operated at various bodies in space. Typical measurements derive the elemental composition, relative abundances, and isotopic ratios of the examined environment. To sample tenuous gas environments around comets, icy moons, and the exosphere of Mercury, efficient instrument designs with high sensitivity are mandatory while the contamination by the spacecraft and the sensor itself should be kept as low as possible. With the Rosetta Orbiter Spectrometer for Ion and Neutral Analysis (ROSINA), designed to characterize the coma of comet 67P/Churyumov-Gerasimenko, we were able to quantify the effects of spacecraft contamination on such measurements. By means of 3D computational modeling of a helium leak in the thruster pressurization tubing that was detected during the cruise phase we examine the physics involved leading to the measurements of contamination. 3 types of contamination can be distinguished: i) Compounds from the decomposition of the spacecraft material. ii) Contamination from thruster firing during maneuvers. iii) Adsorption and desorption of the sampled environment on and from the spacecraft. We show that even after more than ten years in space the effects of i) are still detectable by ROSINA and impose an important constraint on the lower limit of gas number densities one can examine by means of mass spectrometry. Effects from ii) act on much shorter time scales and can be avoided or minimized by proper mission planning and data analysis afterwards. iii) is the most difficult effect to quantify as it changes over time and finally carries the fingerprint of the sampled environment which makes prior calibration not possible.

NASA's Lunar Precursor Robotic Program (LPRP), formulated in response to the President's Vision for Space Exploration, will execute a series of robotic missions that will pave the way for eventual permanent human presence on the Moon. The Lunar Reconnaissance Orbiter (LRO) is first in this series of LPRP missions, and plans to launch in October of 2008 for at least one year of operation. LRO will employ six individual instruments to produce accurate maps and high-resolution images of future landing sites, to assess potential lunar resources, and to characterize the radiation environment. LRO will also test the feasibility of one advanced technology demonstration package. The LRO payload includes: Lunar Orbiter Laser Altimeter (LOLA) which will determine the global topography of the lunar surface at high resolution, measure landing site slopes, surface roughness, and search for possible polar surface ice in shadowed regions, Lunar Reconnaissance Orbiter Camera (LROC) which will acquire targeted narrow angle images of the lunar surface capable of resolving meter-scale features to support landing site selection, as well as wide-angle images to characterize polar illumination conditions and to identify potential resources, Lunar Exploration Neutron Detector (LEND) which will map the flux of neutrons from the lunar surface to search for evidence of water ice, and will provide space radiation environment measurements that may be useful for future human exploration, Diviner Lunar Radiometer Experiment (DLRE) which will chart the temperature of the entire lunar surface at approximately 300 meter horizontal resolution to identify cold-traps and potential ice deposits, Lyman-Alpha Mapping Project (LAMP) which will map the entire lunar surface in the far ultraviolet. LAMP will search for surface ice and frost in the polar regions and provide images of permanently shadowed regions illuminated only by starlight. Cosmic Ray Telescope for the Effects of Radiation (CRaTER), which will investigate the effect of galactic cosmic rays on tissue-equivalent plastics as a constraint on models of biological response to background space radiation. The technology demonstration is an advanced radar (mini-RF) that will demonstrate X- and S-band radar imaging and interferometry using light weight synthetic aperture radar. This paper will give an introduction to each of these instruments and an overview of their objectives.