Europa Lander: mission Europa Lander: mission concept and scientific goalsconcept and scientific goals

L. Zelenyi, O. Korablev, M. Martynov, E. Akim, A. Basilevsky, N. L. Zelenyi, O. Korablev, M. Martynov, E. Akim, A. Basilevsky, N. Eismont, A. Fedorova, V. Galchenko, M. Gerasimov, O. Kozlov, L. Eismont, A. Fedorova, V. Galchenko, M. Gerasimov, O. Kozlov, L.

Ksanfomality, I. Lomakin, G. Managadze, M. Podzolko, G. Popov, A. Ksanfomality, I. Lomakin, G. Managadze, M. Podzolko, G. Popov, A. Simonov, A. Sukhanov, E. Vorobyova, Yu. Agafonov, O. Prieto-Simonov, A. Sukhanov, E. Vorobyova, Yu. Agafonov, O. Prieto-

Ballesteros, M. Blanc, J.P. Lebreton, R. Pappalardo and the Europa Ballesteros, M. Blanc, J.P. Lebreton, R. Pappalardo and the Europa Lander Team Lander Team

IKI, NPOL, Keldysh Inst., Vernadsky Inst., Winogradsky Inst., Skobeltsyn IKI, NPOL, Keldysh Inst., Vernadsky Inst., Winogradsky Inst., Skobeltsyn Inst. MSU, NII PME, Soil faculty MSU, Centro Astrobiologica INTA, ESA Inst. MSU, NII PME, Soil faculty MSU, Centro Astrobiologica INTA, ESA

ESTEC, Ecole Polytechnique, JPL.ESTEC, Ecole Polytechnique, JPL.

1M-SSS 12 October 2010

Jupiter’s Galilean

satellites

Io: tidal volcanism Europa, Ganimede and Callisto: a mantle of liquid water Europa: rock-water interface

ICE SHELL >10 km

Europa is the archetype of icy world habitability

From Figueredo et al., 2003

WHAT WE KNOW NOW FOR SURE ?

WATER ICE IS DOMINATING(Pilcher et al. 1972, Clark and McCord, 1980, Clark 1981

OTHER IDENTIFIED MOLECULESSO2 (Lane et al.,1981; Noll et al.,1995; Lane & Domingue,1997; Domingue & Lane,1998).

CO2 (Smythe et al., 1998, Carlson 2001).

H2O2 (Carlson et al 1999a)AMORPHOUS H2O (Hansen & McCord, 2001)

O2 (Hall et al., 1995, 1998; Spencer & Calvin, 2002)Na, K (Johnson et al., 2002)

SALT HYDRATES (McCord et al. 1998, 1999: Kargel et. al. 2000,Dalton et al. 2005)

HYDRATES OF SULFURIC ACID (Carlson et al. 1999b, 2002)

HYPOTHETICAL COMPOSITIONS OF THE EUROPA OCEAN

1. Na-Mg-Ca-SO4-Cl-H2O – SYSTEM (neutral pH) (Kargel et al., 2000)

2. Na- K-Cl-SO4-CO3-H2O –SYSTEM (alkaline pH)

(Marion, 2001)

3. Na-H-Mg-SO4-H2O – SYSTEM (acid pH)(Marion, 2002)

MOST IMPORTANT FACTORS CONTROLLING POSSIBLE EUROPA BIOSYSTEMS

LIFE IN SULFATE SYSTEMS HIGH SALINITY HIGH PRESSURE ,

2/8/08

• NASA & ESA share mission leadership

• Two independently launched and operated flight systems with complementary payloads

EJSM-Laplace Jupiter Europa Orbiter Mission

2/8/08 7

• ~10–11 Instruments on each flight system, including Radio Science

– Jupiter Europa Orbiter (JEO):NASA-led mission element

– Jupiter Ganymede Orbiter (JGO):ESA-led mission element

• Mission Timeline– Nominal Launch: 2020– Jovian system tour

phase: 2–3 years– Moon orbital phase: 6–12

months– End of Prime Missions:

2029

K. Clark et al. JPLM. Blanc, Ecole Polytechnique

2/8/08

JEO Baseline Mission Overview• NASA-led portion of EJSM (Flagship)• Extensively studied in 2007–2008• Objectives: Jupiter System, Europa • Launch vehicle: Atlas V 551• Power source: 5 MMRTG or 5 ASRG• Mission timeline:

– Launch: 2018 to 2022, nominally 2020• Uses 6-year Venus-Earth-Earth gravity assist trajectory

– Jovian system tour phase: 30 months• Multiple satellite flybys: 4 Io, 6 Ganymede,

6 Europa, and 9 Callisto – Europa orbital phase: 9 months– End of prime mission: 2029– Spacecraft final disposition: Europa surface impact

• 11 Instruments, including radio science• Radiation dose: 2.9 Mrad (behind 2.5 mm of Al)

– Handled using a combination of rad-hard parts and tailored component shielding

2/8/08 8

2/8/08

JEO: Paving the Way for a Future Lander• Best Targets for Science - Recent

material exchange with subsurface (i.e. young in age) and rich in chemistry

– High resolution imaging, radar, IR spectroscopy, thermal imaging

2/8/08 9

• Safe for landing - Meter scale topography, heterogeneity, depth and porosity of regolith– High resolution imaging, laser altimetry, radar,

thermal inertia

– Fine scale processes: mass wasting, sputter erosion, sublimation, impact gardening, frost deposition

A LANDER FOR EUROPA

Gravity Assistant (G1)

Cruis trajectory, V=5544 m/s, rp=100 th.km

ra=20 ml.km, rp=100 th.km, i=40°

ra=20 ml.km, rp=900 th.km, i=0°

Insertion into Jupiter orbit, V=445 m/s

Increase of a perigee and inclination reduction, V=554 м/с

L. Gurvitz: PRIDE – direct radio link

What to search for on the surface ?

• Assess internal structure, measure the thickness of the ice crust

• Assess the conditions on the surface

• Measure the composition of the ice and admixtures in situ

• Search for LIFE– Biomarkers– Chirality– Cells, fossils

HERITAGE:LANDERS FOR

MARS

VENUS

MOON

ROVERS FOR

MOON

SAMPLE RETURN

MOON

PHOBOS SAMPLE RETURN (2011)

© ФГУП «НПО им. С. А. Лавочкина»Космический аппарат для посадки на Европу :: Техническое предложение

Main stages of mission

13

• Proton/Breeze-M launch (target date 2020, as in the project of Federal Space Programme)

• Electric propulsion transport module (separation in the vicinity of Jupiter)

• Using Earth, Jupiter and Galilean satellites gravity assist maneuvers

• Multiple fly-bys of Ganimede, Callisto and Europa;

• Final circular orbit around Europa with a height of 100 km;

• Separation of the Landing module and landing. Europa orbiter and supports telecommunication. Optional TM relay via NASA JEO or directly to Earth via VLBI.

© ФГУП «НПО им. С. А. Лавочкина»Космический аппарат для посадки на Европу :: Техническое предложение14

  MoonHeight, km

V, km/s Period, days rp, RJ

G1 Ganymede 1500 6.65 71.4 11.8

G2 Ganymede 120 6.48 28.6 11.1

G3 Ganymede 100 6.46 21.5 10.7

G4 Ganymede 100 6.4 24.9 10.9

C1 Callisto 400 6.2 33.4 12.7

C2 Callisto 1909 6.18 37.7 13.3

G5 Ganymede 100 5.04 21.5 12.5

G6 Ganymede 1190 4.92 19.5 12.4

C3 Callisto 3095 5.02 23.9 14.1

G7 Ganymede 958 3.66 14.3 13.2

G8 Ganymede 100 3.67 13.9 13.6

C4 Callisto 1159 3.47 15.1 14.4

G9 Ganymede 2695 2.64 10.7 13.5

G10 Ganymede 1312 2.65 7.2 11.3

G11 Ganymede 2594 2.63 5.6 9.0

E1 Europe 6069 2.36 5.3 8.9

E2 Europe 8773 2.29 5.1 8.8

G12 Ganymede 1139 1.76 5.7 11.0

G13 Ganymede 200 1.76 5.3 9.3

E3 Europe 1451 1.62 5.3 9.3

E4 Europe 1500 1.42 4.7 9.3

EOI Europe - 0.57 - -

Manoeuvres 100 m/sCorrections during tour 50 m/sRendezvous with Europe 145 m/sInsertion into Europe orbit (h = 100 km) 705 m/s

Total 1000 m/s

Initial orbit:

- Pericenter radius 900 thousand km;

- Apocenter radius 20 million km.- Period ~200 days

T = 23 Month

Insertion into Europe orbit

© ФГУП «НПО им. С. А. Лавочкина»Космический аппарат для посадки на Европу :: Техническое предложение15

Landing onto Europe surfaceLanding onto Europe surface

Landing orbit (20100 km)

Braking impulse 17.243 m/s

Europe Initial orbit (100 km)

Braking and landing

Main parameters of landing module

-Tрrust 3000 N- Specific impulse 220 s- Initial mass 1210 kg- Mass on surface 550 kg- Propellant mass 660 kg

Total value of characteristic velocity ~1600 m/s

Estimation of stability of a polar circular orbit (h=100 km):

~2 Month – without correction maneuvers ;1 Year – 200 m/s.

© ФГУП «НПО им. С. А. Лавочкина»Космический аппарат для посадки на Европу :: Техническое предложение

Spacecraft:: Overview

16

Name Mass, kg

Orbital module 395

Landing module 550

Propulsion system

385

Electric Propulsion system

860

Intermediate structure

70

S/C without propellant

2260

EPS propellant 1435

Propulsion system propellant

2005

Landing module propellant

660

S/C with propellant

6360

© ФГУП «НПО им. С. А. Лавочкина»Космический аппарат для посадки на Европу :: Техническое предложение

Landing module

17

Scientific instruments unit

Service system unit

RTG

Propulsion system 167 kg

Control system 41

Radio system 7,2

Antennas 2,2

Power system 44

Thermal system 20

Harness 20

Structure 119,5

Landing unit 12

Scientific instruments 70

Margin 47,1

Total Landing module dry mass

550 kg

On the surface of Europa the radiation dose might be 20% of the dose on the orbit around Europa

Landing site and radiation dose• Ideal landing site:

– A place where the subsurface (the ocean) has communicated with the surface

– Relatively young/unaltered by radiation processing, impact bombardment, etc.

– Relatively flat and/or smooth

• The smaller is the size of landing ellipse the more sites are available for landing

• Radiation dose is substantially different for different sites

GeologyCastalia Macula: View from northwest

Conamara Chaos

Europa Lander Science: Some Conclusions from the ELW 2009

• Search for life on Europa, or signatures of life (metabolism) is the main appeal of the Europa Lander mission

• Putative biota on Europa should be very rarified; sample preparation and concentration is required

• Sample acquisition is critical: even shallow subsurface access is challenging, though absolutely needed for life detection experiments

• Biology-driven experiments should provide valuable information regardless of the biology results (space exploration need not and cannot be hypothesis testing)

• Establishing geophysical and chemical context of the environment is critical

• Lander is to provide ground truth for remote measurements and enhance the detection limits

Measurements at the surface of Europa and access to the subsurface

• Geophysics:– Ranging measurements– Sensors (seismometer, tiltometer)

• Means of the access to the subsurface– µ-penetrator– Thermal drill – Melting probes

• Chemical analysis Melting probeMelting probe– GCMS– Raman-LIBS– Mass spectroscopy of secondary ions

• Search for life– Microscopy– Raman spectroscopy– ATR spectroscopy– LIBS, – laser mass spectroscopy

• Reasonable mass of Lander payload suite should not exceed 15-20 kg

• Radiation tolerance and protection of instruments

Penetrators

Thermal drill

Means of access to the subsurface

• No penetrators• No large melting probe• Drill ~ 50 cm or more (~20 kg:

ExoMars)• “Small” melting probe (~4 kg

Biele et al. 2010): one instrument inside? – Problem of ice sublimation

POTENTIAL BIOMARKERS

1. Geochemical, mineralogical(silicates, carbonates, phosphorites, clorides)

2. Isotopic abundances

3. Organic matter

4. Biochemical metabolites

5. Gaseous metabolites

6. Chirality

7. Cells (anabiotic?)

8. Fossils

SELECTION OF METHODS:

Multi functionality,

Determination of multiple markers

Redundancy in biomarker detection

Testing on terrestrial analogs

IR spectroscopyGCMS, MALDI, Raman

Instrument Conditions Composition Habitability Prototype Mass(estimated)

Seismometer OPTIMISM/Mars 96 495g +electronics

Gravimeter GRAS/Phobos 11 250g

Tiltometer Huygens (300g)

Magnetometer MMO Bepi Colombo 770g

TV cameras 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 Urey/ExoMars1 2000g

Immuno-arrays SOLID/ExoMars1 (1000g)

ATR spectroscopy MIMA/ExoMars1 for FTS analyzer (2000g)

Raman spectroscopy RAMAN-LIBS/ExoMars1 1100g2

LIBS RAMAN-LIBS/ExoMars1 1100g2

Laser-ablation MS LASMA/Phobos 11 1000g

XRF APXS/Rosetta 640g

XRS No prototype (2000g)

XRD3 XRD/ExoMars 1200g

INMS MANAGA/Phobos 1000g

Various sensors MUPUS/Rosetta 2350g

Radiation dose RADOM/Chandrayaan-1 100g

≈25 kg + 4 meltin

g probe + 5 m

anipulator

+20 drill + 3 service/cables = 57 kg

Instrument Conditions Composition Habitability Prototype Mass(estimated)

Seismometer OPTIMISM/Mars 96 495g +electronics

Magnetometer MMO Bepi Colombo 770g

TV cameras set CIVA/Rosetta; Phobos 11 1200g

IR spectroscopy No direct prototype;

technique well established

(2000g)

GCMS GAP/Phobos 11; COSAC/Rosetta (5000g)

One biological instrument Urey/ExoMars1 2000g

Various sensors MUPUS/Rosetta 2350g

Absolute must

Further efforts on mass/instrument list optimization required

≈15 kg + 5 melting probe or manipulator

Laplace-Europa Lander missionLaplace-Europa Lander mission

• Mission included in the project of Federal Space Programme • (Target launch date 2020-2021)

• Launch: Proton + Breese-M, or equivalent heavy launcher (Angara…) • Mission Profile:

– Transfer to Jupiter with Earth fly-by– Jupiter maneuver; multiple fly-bys of Ganimede, Callisto and Europa; Orbiting

Europa (overall duration of 6.5-7 years)– Landing onto Europa surface, analysis of surface, and, possible shell subsurface

material.– Data link via orbital spacecraft; limited direct radiolink to the Earth possible using

advanced VLBI

• Recurrent technical solutions– Orbital module, and Cruise module: Phobos SR (major modifications)– Landing module Luna-Resource (planned launch date 2013 ,– major technology developments)

• International context:– Europa Lander mission will be parallel to NASA/ESA EJSM-Laplace. NASA– EJSM Europa Orbiter data might be used for the choice of the landing sites

EUROPA

LANDER

VERY DIFFICULT, BUT DOABLE !

Coordination with JEO Highly desirable