Robotic Missions of Russian Lunar Program
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1 Robotic Missions of Russian Lunar Program Alexander Zakharov & Ilia Kuznetsov on behalf lunar science team of Space Research Institute of the Russian Academy of Sciences Moscow
2 RUSSIAN FEDERAL SPACE PROGRAM MOON, PLANETS, SMALL BODIES OF SOLAR SYSTEM OUT OF-ATMOSPHERE ALL WAVE ASTRONOMY SPACE PLASMA AND SOLAR-TERRESTRIAL PHYSICS BASIC PROBLEMS OF SPACE BIOLOGY AND MEDICINE
3 Federal Space Program a-erwards Spectrum- RG Spectrum- UV = PhSR
4 ROSCOSMOS: MOON AND MARS ARE THE FIRST PRIORITY FOR MAIN FEATURES: TWO MAIN DESTINATIONS MOON AND MARS NEW MISSION TO PHOBOS SAMPLE RETURN FROM THE MOON, PHOBOS AND MARS GRADUAL DEVELOPMENT EACH MISSION IS A BASIS FOR THE NEXT ONE MOON : POLAR REGIONS SEARCH WATER INTERNAL STRUCTURE EXOSPHERE SAMPLE RETURN MARS: SEARCH WATER SEARCH LIFE INTERNAL STRUCTURE ATMOSPHERE SURFACE SAMPLE RETURN PHOBOS: GEOCHEMISTRY INTERNAL STRUCTURE ORBITAL PARAMETERS SAMPLE RETURN
5 ROSCOSMOS: MOON AND MARS ARE THE FIRST PRIORITY FOR MAIN FEATURES: TWO MAIN DESTINATIONS MOON AND MARS NEW MISSION TO PHOBOS SAMPLE RETURN FROM THE MOON, PHOBOS AND MARS GRADUAL DEVELOPMENT EACH MISSION IS A BASIS FOR THE NEXT ONE MOON : MARS: ExoMars 2020 Luna-Glob (Luna-25) Luna-Resource Orbiter (Luna-26) Luna-Resource Lander (Luna-27) PHOBOS: PhSR 2024
6 Robotic precursors of Moon exploration Goals of the 1 st stage of Russian lunar robotic missions Goal 1: Study of mineralogical, chemical, elemental and isotopic content of regolith and search for a volatiles in regolith of polar area of Moon. Goal 2: Study of plasma, neutral and dust exosphere of Moon and interaction of space environment with Moon surface at poles. Goal 3: Study dynamic of daily processes at lunar poles, including thermal property variations of subsurface layers of regolith and evolution of hydratation and volatiles. Goal 4: Study of inner structure of Moon by seismic, radio and laser ranging methods. Goal 5: Preparation for future exploration of Moon
7 : Projects with robotic spacecrafts 1976 LUNA LUNA-29 Complex study of south polar area with rover LUNA -28 (Luna-Resurs-2) Lunar Polar Sample Return LUNA-25 (Luna-Glob) Soft landing surviving and study of regolith and exosphere LUNA-26 (Luna-Resurs-1 Orbiter) Global resources reconnaissance and cartography LUNA-27 (Luna-Resurs-1 Lander) Safety and high precision landing, study of regolith in the depth, study of exosphere and inner structure, beacon for next mission : Projects with robotic and manned spacecrafts on lunar orbit Reusable spacecraft «Corvet» Manned SC PTK-L
8 Luna-25 (Luna-Glob) Expected results Technology: Re-design of soft landing technology Pole-Earth radio link tests and experience Thermal design validation Robotic arm testing and validation Science: 1. Mechanical/thermal properties of polar regolith 2. IR composition measurements of polar regolith 3. Water content and elements abundance in the shallow subsurface of the polar regolith 4. Plasma and neutral exosphere at the pole 5. Plasma-Dust exosphere at the pole 6. Thermal variations of the polar regolith
9 Luna-27 (Luna-Resource Lander) Expected results Technology: High precision landing and hazard avoidance Pole-orbiter UHF radio link tests and experience Cryogenic drill testing and validation Science: Mechanical/thermal/compositional properties of polar regolith within 2 meters Water content and elements abundance in the shallow subsurface of the polar regolith Plasma, neutral and dust exosphere at the pole Seismometry and high accuracy ranging
10 Luna- 25 & - 27 Instruments and Experiments Direct regolith study Remote regolith study Mechanical, thermal, other properkes of regolith Exosphere inveskgakon Moon internal structure Instrument Descrip.on L- 25 L- 27 Chromatographic complex Analysis of volakles content and isotopic rakos Yes Yes* LASMA Laser Mass- spectrometry analyzer Yes Yes* PROSPECT LIS- TV- RPM Drilling, sampling, sample handling, processing and analysis package TV imaging of nearest field and objects (including RoboKc arm operakons support); IR spectra of minerals TV- Spectrometer UV and opkcal imaging of minerals with UV excitakon No Yes No Yes Yes Yes* ADRON AcKve neutrons & γ detector Yes Yes* LMK RoboKc arm (including panorama and stereo imaging) Yes Yes RAT Radio measurements of temperature of subsurface regolith TERMO Direct measurements of thermal properkes of regolith Yes Yes PmL Measurements of dust and plasma proper.es Yes Yes* ARIES Measurements of plasma and neutrals Yes No LINA Measurements of plasma and neutrals Yes Yes Radio beacon Radio signal with high stability Yes Yes SEISMO Measurements of seismic ackvity Yes Yes Reflectors Yes Yes Yes Yes
11 Why the Polar Moon? Water distribution in regolith according to data from Chandrayan-1 (ISRO) Temperature distribution in regolith according to data from Diviner onboard Lunar Reconnaissance Orbiter (NASA) Water distribution in regolith according to data from Lunar Prospector (NASA) Н2О Water distribution in regolith according to data from LEND (Russia) onboard Lunar Reconnaissance Orbiter (NASA) Area of direct registration of water in regolith in Cabeus according inpact experiment «LCROSS» (NASA)
12 The Lunar Ejecta and Meteorites (LEAM) Experiment deployed by the Apollo 17 astronauts as part of the Apollo Lunar Surface Experimental Package on 11 December 1972 LEAM per 3- hour period, integrated over 22 lunar days Number of impact events [a-er Berg et al., 1976]. The large increases at terminator crossings persist for several hours before and a-er sunrise and before the smaller increase at sunset, suggeskng parkcles may be launched on long trajectories from the terminator.
13 Landing sites
14 Luna- 25 landing site selecbon Название Широта Долгота to the SW of Manzinus 1-68,773 21,210 crater 2 Manzinus crater East - 67,476 24,613 3 Manzinus crater West - 67,371 25,697 4 to the S of PentlandA - 68,648 crater 11,553 5 to the NW of BoguslawskyC crater - 70,681 23,634 6 to the N of Boguslawsky crater - 69,545 43,544 between Boguslawsky 7 and Boussingault craters - 72,161 50,085 8 to the N of Schomberger crater - 73,882 26, SimpeliusD crater SimpeliusE crater - 71,718-70,148 8,186 10, Boguslawsky crater - 73,400 44, BoguslawskyC crater - 70,930 26,715
15 Luna-26 (Luna-Resource Orbiter) Expected results from Luna-26 Technology: Polar-orbit UHF radio link tests and experience Orbital operations Science: Space plasma in the lunar vicinity Luna-27 landing sites candidates
16 Luna Orbiter Spacecraft design (2015) Launch Soyuz-2-1b + Fregat Orbiter mass ~2000 kg Payload mass ~160 kg TM downlink or 100 Mbit/s (TBD)
17 Moon orbit inser.on ~5-7 days Orbit
18 Luna Orbiter science Moon surface science Ø Topography Ø Subsurface structure Ø Hydrogen rich regions Ø Chemical composition Ø Moon gravity field
19 Luna Orbiter science Circumlunar science Ø Exosphere Ø Solar wind Moon interaction Ø Lunar magnetic anomalies Ø Micrometeors
20 Luna Orbiter experiments 1. planetary experiments LGNS neutron and gamma ray IKI LEVUS UV exosphere France/Japan/IKI nm Bepi-Colombo PHEBUS LUMIS IR mapping IKI 1-16 mkm Exomars ACS LSTK stereo camera IKI RLC-L radar IRE 20 and 200 MHz
21 Luna Orbiter experiments 2. plasma experiments LPMS-LG magnetometer IKI DC field LEMI electromagnetic waves Ukraine/Czech R/IKI magnetic fluctuations to 40 khz BMSW-LG solar wind Czech R/IKI plasma flow direction, velocity, density ASPECT-L energetic particles Slovakia/IKI ions and electrons kev LINA-R ions and neutral spectrometer IKI major ion species kev LNT neutral atoms spectrometer Sweden/IKI
22 Luna Orbiter experiments 3. other PKD radio receiver IKI high-precision orbit measurements METEOR-L circumlunar dust GeoKhi SSRNI2 data management system IKI CANDIDATE INSTRUMENTS LYMUS/LAICA all-sky survey of L-alpha LATMOS/Rykkio U/ IKI
23 ROSCOSMOS: MOON AND MARS ARE THE FIRST PRIORITY FOR Dust instruments in the payload Destination: The Moon Destination: Mars surface Mission: Luna-Glob Lander (2019) Instrument: Lunar Dust Monitor (PmL-LG) Mission: ExoMars (2020) Instrument: Dust Suit (DS) Destination: The Moon Mission: Luna-Resource Lander (2021) Instrument: Lunar Dust Monitor (PmL-LR) Destination: Martian orbits, Phobos Mission: Boomerang (PhSR) (2024) Instrument: Dust In the Martian EnviRonment (DIMER)
24 Lunar Dust Monitor (PmL) PmL-LG Min impulse is ~10-12 N s (for SiO 2 sphere ~2 µm diameter with velocity ~1 m/c) Max impulse is ~10-6 N s (or even more). Grid before PZT plates of Impact Sensor measure particle charges from ~10-14 C (~10000 electrons).
25 PmL instrument characteris.c for Luna- Glob (Luna 25) DimenKons Weight ConsumpKon Impact Sensor IS 2 Electric Field Sensors g 5 W Ø g = 90 g < 0.01 W Cables 20 cm & 3 m 50 g < 0.01 W TOTAL 990 g PROXIMITY ELECTRONICS PROCESS OF MANUFACTURE TEMPERATURE OPEN IN SPACE PART OF IS THERMAL CAPACITY THERMAL FLU X T O P O I N T O F FASTENING RS- 485 Interface, ~ 10 Kb/s, (0.3 Mbit/day), preamplifiers, ADC, FPGA, DC- DC Engineering Model and Qualification Model passed tests. Flight prototype is under construction, Laboratory models is under analysis result. Work temperature C, storage temperature C Square of impact area S =0,025 m 2 of Impact Sensor 680 J/К 5 W
26 2026+ Roscosmos Martian Program 2024 The first stage 2020 Mars-SR! 2 Proton, Mars SR, Mars investigation Boomerang (Phobos-Soil-2) ExoMars Rover 2016 ExoMars Lander ExoMars TGO Proton, Orbiter, Two Russian instruments ASC и FREND Soil study along the Rover way Under discussion Proton, Rover, Mars Lander Mars-Rover Orbiter Proton, Phobos SR, Phobos inverstigation Under discussion
27 Why Phobos again? Phobos and Deimos are unique objects among SS small bodies: Are they: - were formed together with Mars? - captured asteroids like primitive bodies? - do they contain the Martian matter? - And step to Mars Sample Return Mission
28 Phobos studies For many years studies of Phobos have been of high priority in the Russian program on planetary research. the project was aimed to solve important scientific tasks delivery of soil samples to the Earth is an important step in preparation of a sample return mission to Mars. Phobos 2 SC Phobos-Soil SC 2011
29 PHOBOS SR ELEMENTS OF THE PHOBOS SR 1 - Main Propulsion System (MPS) 2 Migratory SC - Lander 3 Returned SC (RSC) 4 Returned Capsule (RC) 5 RSC Solar arrays 6 Solar arrays 7 - SC Truss 8 - MPS Truss
30 Phobos Sample Return (Ph+D) Main characteristics Launch Rocket Main propulsion system (wet) SC (transfer + Lander) Payload Returned SC Returned Capsule Mass of samples 2024 (TBD) Angara kg ~ 990 kg ~ 50 kg 380 kg 120 kg 0,5 kg
31 Thank you!
32 Special Thanks Luna-25 and Luna-27 PS: I.G. Mitrofanov PI: V.I. Tretiakov Luna-27 PS: A.A. Petrukovich And for all who is involved in developing the scientific instruments for Russian Spacecrafts
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