landers for galilean satellites landers for galilean satellites zigzag history of the endeavour 05...
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LANDERS FOR GALILEAN SATELLITES
ZIGZAG HISTORY OF THE ENDEAVOUR
05 March , 2013
Laplace-Ganymede lander mission
LEV ZELENYI and OLEG KORABLEV
Missions to the Jupiter System I
• VOYAGER !!!!• Galileo (1989-2003)• JUNO polar orbiter launched Aug.2011
• Since 1996: ~20 cancelled proposals:– Europa Orbiter (NASA 2002)– Jupiter Icy Moons Orbiter (JIMO, NASA 2005)– Jovian Europa Orbiter (JEO, ESA 2007)
Around 2007:• NASA: Jupiter Europa orbiter mission
(Flagship) + - SURFACE ELEMENT ??• ESA: Laplace (L-Class)
Missions to the Jupiter System II
– NASA: Jupiter Europa Orbiter (JEO), planned to study Europa and Io.
– ESA: Jupiter Ganymede Orbiter (JGO), planned to study Ganymede and Callisto
– JAXA: Jupiter Magnetospheric Orbiter (JMO), planned to study Jupiter's magnetosphere.
– Roscosmos: Europa Lander, planned to land on Europa's surface for in situ studies.
EJSM Europa Jupiter System Mission : 2008
Космос для человечества
EUROPA LANDER
ICE COVER
RUSSIAN SPACE AGENCY
RUSSIAN ACADEMY OF SCIENCES
“Without a surface element, EJSM is just preparatory for a very future mission with goals really related to ASTROBIOLOGY” Olga Prieto-Ballesteros
WHY LANDER ??
• SOVIET EXPERIENCE IN SOFT LANDINGS (MOSTLY LAVOCHKIN ASSOCIATION ACHIEVMENTS)
first automatic return of lunar samples--3
first lunar rover -2
2. MARS
-No successful landings
3. VENUS !
FIRST AND LAST LANDINGS BY SOVIET VENERA”s
4. Preparations for PHOBOS Landing
1. MOON
Luna 24
Luna 16, 20, 24
Venera 9-14 results
To look through the clouds, to descend, and to land
Venera 9-10 measured the solar flux at the surface – the basic figure to calculate greenhouse. Nightglow spectra. 1975
• Venera 11-12 measured atmospheric spectra and fluxes down to the surface. Mass spectrometer showed an anomaly = in 36Ar/40Ar ratio, and measured the isotopes of neon.
Gas-chromatographer measured CO and other minor constituents in the low atmosphere. Detection of electric activity; measurements of physical and chemical properties of clouds.
Спектры ИОАВVenus 11 dayside spectra
Colour panorama (Venera 13-14)
Laplace-Europa Lander mission (I):
Development:2008: Preliminary assessment2008: Initial industrial study 20082009: Europa Lander workshop 20092010: radiation load/scenario/landing
site assessment; lander payload definition
2011: further scenario development; orbiter payload definition; payload accommodation
Mission architecture:• Europa lander, full mass 1210 kg,
target 50 kg of mass for science• Telecom and science orbiter, 50 kg
science payload• Multiple fly-bys of Ganimede, Callisto
and Europa;• Final circular orbit around Europa
with a height of 100 km;• Soft landing, target surface mission
duration 60 days. Surface analysis by drilling (30 cm depth) possibly melting probe (<5 kg). Orbiter supports telecommunication. Optional TM directly to Earth via VLBI
• Target total radiation dose <100kRad behind 5 g/cm2 Al (300 kRad tolerant components)
Roscosmos IKI TSNIIMASH Lavochkin Assoc
Laplace-Europa Lander mission (II):
Resources:• 50 kg on the lander, including sample
handling and (partially) radiation shield
• 3.2 kbit/s via HGA to 70-m dishes• Lander data relay via orbiter• 50 kg on the orbiter, including
(partially) radiation shield
Science Goals:• The main appeal of the present mission is
search for life on or its signatures on Europa
– Sample acquisition, concentration– Subsurface access
• Establishing geophysical and chemical context
– Biology-driven experiments should provide valuable information regardless of the biology results
• Lander is to provide ground truth for remote measurements and enhance the detection limits
• Orbiter: versatile remote observations; landing site characterization; Jupiter science
Roscosmos IKI TSNIIMASH Lavochkin Assoc
Proof-of-the-concept payloadsLander:• 12 instruments 20 kg• 4-5 kg melting probe• Drill for 30-cm depthOrbiter:• 6 instruments, incl. radioscience
From Europa Lander to Ganymede Lander
• An absolute need for the Orbiter for retranslation• No reconnaissance information on Europa because of NASA
Europa Orbiter cancellation • Impossibility for the planned Russian 400-kg Europa Orbiter to
fulfill both the reconnaissance and telecom functions• Moreover, 400-kg Europa Orbiter is incompatible with the
telecom function only because of high radiation burden in orbit around Europa
Ganymede Lander in coordination with ESA JUICE or a JOINT project with ESA
+ +
Ganymede Lander: play safe !
• Detailed reconnaissance from JUICE for choosing the Ganymede Lander landing site
• Landing using ESA Visual Navigation system• Telecommunication via JUICE, if logistics permit• Dedicated small (?) Ganymede orbiter for telecommunication
and limited science
+ + +
+
Science objectives• Characterize Ganymede as planetary object
including its habitability• Study the Jupiter system as an archetype for
gas giants
EJSM-Laplace1. Why is Ganymede an habitable world
Why are Ganymede and Europa habitable worlds ?
Surface/Deep habitats
The habitable zone is not restricted to the Earth’s orbit…
Возможна ли жизнь на Европе и Ганимеде?
Deep habitats
Deep habitats
Необходимые составляющие• Жидкая вода• Элементы• Энергия• Время
Научные задачи: Обитаемость Солнечной системы
Science objectives• From direct search for life on Europa to
determining the habitability of Ganymede– Establishing geophysical and chemical context for
habitability – Lander is to provide the ground truth for remote
measurements and enhance the detection limits• Orbiter:
– Complement JUICE (2-points observations, etc)– High-resolution measurements of target areas– Others…
Instrument Conditions Composition Habitability Prototype Mass(estimated)
Seismometer OPTIMISM/Mars 96 495g +electronics
Magnetometer MMO Bepi Colombo 770g
TV camera set CIVA/Rosetta; Phobos 11 1200g
Optical microscope Beagle-2; Phobos 11 300g
IR spectroscopy No direct prototype;
technique well established
(2000g)
IR close-up spectrometer
CIVA/RosettaMicrOmega/ExoMars (1000g)
GCMS
GAP/Phobos 11; COSAC/Rosetta (5000g)
Wet chemistry set (option 1) Urey/ExoMars1 2000g
Immuno-arrays (option 2) SOLID/ExoMars1 (1000g)
Raman spectroscopy RAMAN-LIBS/ExoMars1 1100g2
Laser-ablation MS LASMA/Phobos 11 1000g
XRS (TBD) No prototype (2000g)
Various sensors MUPUS/Rosetta 2350g
Radiation dose RADOM/Chandrayaan-1 100g
20315g
Europa Lander model payload
Largely applicable to Ganymede?
Ganymede surface science• A set of instruments on the Lander
– Assume max mass of instruments and aux systems of 50 km to include:
• instruments; • sampling device(s);• Deployment• Data handling• Radiation protection for instruments out of common
compartment
• Penetrator(s)
Landing scheme +IMPACTOR2007 presentation
Penetrator(s)?• To be released from the orbit• Mass 5-15 kg• Payload <2 kg
Orbiter payload• Reconnaissance
– Full mapping from JUICE– Landing sites/target areas– WAC+HRC– What resolution required ? Meters ? (orbit not yet defined…) compare
to JUICE final orbit (200 km polar), 5 µrad IFOV
• Magnetometer– Boom of several meters!
• Radioscience?• Some plasma instruments • Some optical instruments/ others JUICE losers • More info after the JUCIE selection To define requirements on the Orbiter
Космос для человечества
THANKS FOR ATTENTION)
Ио Европа
Ганимед Каллисто
THANKS FOR ATTENTION•
Lander instruments/systems• Set of context instruments
– Panoramic camera (stereo, filters or color)– Various sensors (temperature, conductivity, radiation, etc)
• Geophysical package– Seismometer – Magnetometer
• Geochemistry– Contact (GCMS, Laser Ablation/Raman, XRD/XRS, …)– Sampling system: robotic arm– Remote (IR spectroscopy)
Sampling/mechanisms• Robotic arm with sampling device
– Heritage: Phobos-Grunt, Luna-Resource– Mass: 3-5 kg (including commanding?)– Chomic-type perforator (mass-?)– Scoop/sampling cylinder (?)– Dedicated context and close-up cameras (mass ~ 500g) – APX-type instrument(s) (mass ~500 g)
• Common sample preparation system for GCMS, laser ablation, XRD, etc ???• Mast for panoramic camera/IR spectrometer
– Stereo camera (type Phobos, Space-X)– High-resolution camera (Type ExoMars)– IR spectrometer (type LIS, or ISEM
• Magnetometer boom
• No drilling on the lander
Geophysical package• Seismometer
– No need for a state-of-the-art Mars-type device– Two-axis– Lognonnee-type or Manukin-type?– Mass: <2 kg (?)– Deployment required or placement on the foot suffice? – To include tiltmeter?
• Magnetometer– Keep mass within 1 kg – Deployment necessary!
Instrument Conditions Composition Habitability Prototype Mass(estimated)
Seismometer OPTIMISM/Mars 96Luna-Resurce ~2000 g +shield
Magnetometer MMO Bepi Colombo 770g +boom+ shield
TV camera set
ExoMars 1200g + mast + shield
IR spectroscopy LIS Luna-Resource, ISEM ExoMars 1400 +shield
Robotic arm 3500Optical microscope Beagle-2; CUPI/ExoMars 500g + shield
GCMS
GAP/Phobos 11; COSAC/Rosetta 6000g
Laser-ablation MS +Raman Spectro
LASMARAMAN-LIBS ExoMars 3000g
XRD ExoMars 1500g
XRF APX/ MER 500g+shield
Various sensors Rosetta, Luna Resource, 2500g
Radiation dose RADOM/Chandrayaan-1 100g
~25 000 g
Ganymede Lander model payload
Orbiter payload• Reconnaissance
– Full mapping from JUICE– Landing sites/target areas– WAC+HRC– What resolution required ? Meters ? (orbit not yet defined…) compare
to JUICE final orbit (200 km polar), 5 µrad IFOV
• Magnetometer– Boom of several meters!
• Radioscience?• Some plasma instruments • Some optical instruments/ others JUICE losers • More info after the JUCIE selection To define requirements on the Orbiter