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