Planetary experiments

LEVUS Lunar UV spectrometer LEVUS is designed for remote study of the exosphere in the electromagnetic radiation range 30-150 nm. The LEVUS prototype is PHEBUS onboard the ESA BepiColombo mission.
Specifications:
Mass: 7,5 kg
Operational power consumption : < 25 W
Instrument is developed by LATMOS (France), ISAS (Japan) and Space Research Institute.
PI – Prof. O.I. Korablev
LGNSThe Lunar gamma-ray and neutron spectrometer (LGNS) is designed for remote study of the elemental composition and water content of Moon’s regolith on the basis of measurements of secondary thermal, epithermal and fast neutrons, as well as gamma-rays in the energy range of 300 keV – 6 MeV. The LGNS prototypes are HEND operating on Martian orbit since 2001 as part of scientific payload of NASA’s Mars Odyssey mission, and MGNS designed for Mercury researches onboard the ESA BepiColombo mission.
Specifications:
Mass: 6,5 kg
Operational power consumption : < 6,2 W
Instrument is developed by Space Research Institute.
PI – Prof. I.G. Mitrofanov
LUMISLunar IR spectrometer LUMIS is designed for remote study of the regolith chemical composition in the wavelength range 1-16 mkm.The design requirement for the spectral resolution for the Moon’s surface study is 50 cm−1.The sensitivity of the instrument has to be significantly higher aiming for the detection of the 6-μm hydration band in permanently shadowed areas and on the dark side of the Moon. To increase the SNR, the instrument’s IFOV will be as high as 7° (the surface resolution of about 6 km from a 50 km circular orbit). The detector of LUMIS is a photovoltaic MCT coupled to the Stirling cooler. Its maximum sensitivity will be optimized at about 6 μm according to the main instrument scientific goal.
Specifications:
Mass: 12,1 kg
Operational power consumption : < 20 W
Instrument is developed by Space Research Institute.
PI – Dr. A.V. Shakun
LSTCThe Lunar Stereo Topographic Camera (LSTC) will perform stereo imaging of the Moon surface to derive cartographic/topographic data products needed to support navigation of future lunar missions. The LSTC is composed of two identical optical heads and a common data processing unit. One of the optical heads looks forward within the orbit plane and the other looks backwards.
Specifications:
Mass: 8 kg
Operational power consumption : < 21 W
Frame area on the surface: 22,6 x 16,1 km / 11,3 x 8,1 km
Pixel size on the surface: 3,75 …4,7 m / 1,6 …2,4 m
Instrument is developed by Space Research Institute.
PI – Dr. I.V. Polyansky
RLC-LMulti-purpose radar complex RLС-L is designed to conduct studies of the subsurface structure of the Moon, inclusions of large rocks and voids, dielectric constant of regolith, surface roughness.
Specifications:
Mass: 28 kg
Operational power consumption : < 20 W
Frequency range: 17.5-22.5 MHz, 144-176 MHz
Instrument is developed by Kotel’nikov Institute of Radio Engineering and Electronics of the Russian Academy of Sciences and Special Design Bureau.
PI – Prof. V.M. Smirnov

Plasma experiments

LPMS-LGLunar magnetometer LPMS is designed for measurements of DC magnetic fields along the Moon orbit.
Specifications:
Mass: 3,44 kg
Operational power consumption : < 12 W
Magnetic field range 0-600 nT.
Measurement cadence up to 16 Hz
Instrument is developed by Space Research Institute.
PI – Dr. A.A. Skalsky
LEMILunar electromagnetic field investigation LEMI is designed for measurements of AC magnetic and electric fields along the Moon orbit.
Specifications:
Mass: 3,65 kg
Operational power consumption : < 7 W
Frequency range: 40 kHz
Instrument is developed by Space Research Institute, Institute of Atmospheric physics (Czech Republic).
PI– Prof. O. Santolik, Institute of Atmospheric physics.
BMSW-LGThe plasma spectrometer BMSW-LG is designed to observe solar wind flow and its interaction with the lunar surface. BMSW-LG measures the energy spectra of the proton and alpha particle fluxes and the magnitude and direction of the total ion flux in the energy range from 100 eV to 4 keV with time resolution up to 0.031 s. BMSW-LG consists of three blocks. The main block is designed to measure solar wind; the detector of the reflected flow – to measure parameters of the plasma flow reflected from the Moon surface, the DSS sensor – to accurately determine the direction to the Sun.
Specifications:
Mass: 6,4 kg
Operational power consumption : < 3,5 W
Instrument is developed by Charles University (Czech Republic) and Space Research Institute.
PI– Prof. Jana Safrankova, Charles University.
ASPECT-LThe energetic particle spectrometer ASPECT-L is designed to measure fluxes of ions and electrons in the energy range from 20 keV to 400 keV for electrons and from 20 kev to 1000 keV for ions with time resolution up to 0.1 s. Main goal of the experiment is to investigate the the role of energetic particles in lunar surface evolution and exosphere formation.
Specifications:
Mass: 3,2 kg
Operational power consumption : < 3,3 W
Instrument is developed by Institute of Experimental Physics (Slovak Republic)
PI – Dr. Jan Balaz.
LINA-RLINA-R instrument is a panoramic ion energy-mass analyzer. Main goal of the experiment is to investigate the interaction of solar wind with Lunar surface, regolith desorption, exosphere chemical composition. The instrument consists of two sensors LINA-R-1 and LINA-R-2. Each sensor performs measurements of ion velocity distribution function within energy range 5 to 5000 eV and mass analysis of neutral atoms. Energy resolution ΔЕ/Е is of about 10%, mass resolution М/ΔМ is about 40.
Specifications:
Mass: 6,7 kg
Operational power consumption : < 6 W
Instrument is developed by NPP Astron Electronika (Russia) and Space Research Institute.
PI – Prof. O.L. Vaisberg, Space Research Institute
LNTLNT is a neutral atom spectrometer.
Specifications:
Mass: 3,8 kg
Operational power consumption : < 11,7 W
Instrument is developed by Institute of Space Physics (Sweden).
PI – Prof. S. Barabash.

Others

PKD Ultrastable radiowave receiver PKD is designed to make precise measurements of spacecraft location and speed to investigate heterogeneity of the gravitational field of the Moon. PKD has a receiver, operating in the Ka frequency band (32 GHz), and two antennas. The nadir antenna will accept the signal from Radio Beacon installed on the landing platform. The active zenith antenna will accept a signal from the Earth.
Specifications:
Mass: 2,1 kg
Operational power consumption : < 15 W
Instrument is developed by Space Research Institute.
PI – Prof. A.S. Kosov.
METEOR-L Meteor-L is a dust analyzer. This instrument is applied for the registration of the physicodynamical parameters of meteor particles (mass, speed) in cosmic space.
Specifications:
Mass: 2,9 kg
Operational power consumption : < 5,5 W
Instrument is developed by Vernadsky Institute of geochemistry (Russia).
PI– Prof. V.V. Vysochkin.
SSRNI-2 SSRNI-2 is an interface electronic block between the spacecraft and scientific instruments. It relays commands, receives and stores science data, delivers electric power.
Specifications:
Mass: 5 kg
Operational power consumption : < 10 W
Instrument is developed by Space Research Institute.
PI – Dr. K.V. Anufreichik.