LANDERS FOR GALILEAN SATELLITES ZIGZAG HISTORY OF THE ENDEAVOUR
description
Transcript of LANDERS FOR GALILEAN SATELLITES ZIGZAG HISTORY OF THE ENDEAVOUR
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 LASMA
RAMAN-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