1. LANDERS FOR GALILEAN SATELLITES ZIGZAG HISTORY OF THE ENDEAVOUR
Laplace-Ganymede lander mission
LANDERS FOR GALILEAN SATELLITES ZIGZAG HISTORY OF THE ENDEAVOUR
LEV ZELENYI and OLEG KORABLEV
05 March , 2013

2. Missions to the Jupiter System I
VOYAGER !!!!
Galileo ( )
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)

3. Missions to the Jupiter System II
EJSM Europa Jupiter System Mission : 2008
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.

4. Космос для человечества
EUROPA LANDER
RUSSIAN SPACE AGENCY
RUSSIAN ACADEMY OF SCIENCES
ICE COVER
“Without a surface element,
EJSM is just preparatory
for a very future mission
with goals really related
to ASTROBIOLOGY”
Olga Prieto-Ballesteros
Космос для человечества

5. WHY LANDER ?? SOVIET EXPERIENCE IN SOFT LANDINGS
(MOSTLY LAVOCHKIN ASSOCIATION ACHIEVMENTS)
1. MOON
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

6. Luna 17 6

7. Luna 24
Luna 16, 20, 24 7

8. 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 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 ИОАВ
Venus 11 dayside spectra
Colour panorama (Venera 13-14)

9. Laplace-Europa Lander mission (I):
Development: 2008: Preliminary assessment 2008: Initial industrial study : Europa Lander workshop : 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

10. 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
Proof-of-the-concept payloads
Lander:
12 instruments  20 kg
4-5 kg melting probe
Drill for 30-cm depth
Orbiter:
6 instruments, incl. radioscience
Roscosmos IKI TSNIIMASH Lavochkin Assoc

11. 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 +  +

12. 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 +  + + +

13. Science objectives
Characterize Ganymede as planetary object including its habitability
Study the Jupiter system as an archetype for gas giants

14. 1. Why is Ganymede an habitable world
Научные задачи: Обитаемость Солнечной системы
Why are Ganymede and Europa habitable worlds ?
Возможна ли жизнь на Европе и Ганимеде?
Необходимые составляющие
Жидкая вода
Элементы
Энергия
Время
The habitable zone is not restricted to the Earth’s orbit…
Surface/Deep habitats
Deep habitats
Deep habitats 14

15. 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…

16. Europa Lander model payload
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/Rosetta
MicrOmega/ExoMars
(1000g)
GCMS
GAP/Phobos 11; COSAC/Rosetta
(5000g)
Wet chemistry set (option 1)
Urey/ExoMars1
2000g
Immuno-arrays (option 2)
SOLID/ExoMars1
Raman spectroscopy
RAMAN-LIBS/ExoMars1
1100g2
Laser-ablation MS
LASMA/Phobos 11
1000g
XRS (TBD)
No prototype
Various sensors
MUPUS/Rosetta
2350g
Radiation dose
RADOM/Chandrayaan-1
100g
20315g
Largely applicable to Ganymede?

17. 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)

18. Landing scheme +IMPACTOR
2007 presentation

19. Penetrator(s)? To be released from the orbit Mass 5-15 kg
Payload <2 kg

20. Orbiter payload Reconnaissance Magnetometer Radioscience?
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

21. Космос для человечества
THANKS FOR ATTENTION)
Европа Ио
Ганимед
Каллисто
Космос для человечества

22. THANKS FOR ATTENTION

23. 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)

24. Sampling/mechanisms No drilling on the lander
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

25. Geophysical package Seismometer Magnetometer
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!

26. Ganymede Lander model payload
Instrument
Conditions
Composition
Habitability
Prototype
Mass
(estimated)
Seismometer  
OPTIMISM/Mars 96
Luna-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
3500
Optical 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
1500g
XRF
APX/ MER
500g+shield
Various sensors
Rosetta, Luna Resource,
2500g
Radiation dose
RADOM/Chandrayaan-1
100g
~ g

27. Orbiter payload Reconnaissance Magnetometer Radioscience?
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

28. Синтезированный ландшафт Венеры по данным радара КА “Galileo”
Радиокарта Венеры
Изображение поверхности Венеры,
полученное советским посадочным аппаратом «Венера-13» в 1982 г.

29. Синтезированный ландшафт Венеры по данным радара КА “Galileo”
Радиокарта Венеры
Изображение поверхности Венеры,
полученное советским посадочным аппаратом «Венера-13» в 1982 г.