The International Mars Exploration Programme and Current Planetary Protection Measures

Transcription

1 The International Mars Exploration Programme and Current Planetary Protection Measures G. Kminek European Space Agency Vice-Chair, COSPAR Panel on Planetary Protection

2 The prospect for life on Mars - up, down, and up again Planet Mars Mariner Viking Lander MGS Antarctic Dry Valleys Cueva de Villa Luz MRO Phoenix Black Smoker Life on Earth Rio Tinto

3 Current and Planned Missions Operational Towards Mars Sample Return Mars Express Mars Reconnaissance Orbiter (Italian SHARAD) MAVEN ESA-NASA ExoMars Trace Gas Orbiter Mars Odyssey International Cooperation Programme ESA EDL Demonstrator NASA Astrobiology & Caching Rover Mars Exploration Rovers Mars Science Laboratory ESA ExoMars Rover Station Network

4 Growing up

5 MSL Science Payload Mastcam REMS RAD ChemCam REMOTE SENSING Mastcam (M. Malin, MSSS) Color and telephoto imaging, video, atmospheric opacity ChemCam (R. Wiens, LANL/CNES) Chemical composition; remote micro imaging DAN CONTACT INSTRUMENTS (ARM) MAHLI (K. Edgett, MSSS) Hand lens color imaging APXS (R. Gellert, U. Guelph, Canada) Chemical composition MAHLI APXS Brush Drill / Sieves Scoop MARDI ANALYTICAL LABORATORY (ROVER BODY) SAM (P. Mahaffy, GSFC/CNES) Chemical and isotopic composition, including organics CheMin (D. Blake, ARC) Mineralogy Rover Width: Height of Deck: Ground Clearance: Height of Mast: 2.8 m 1.1 m 0.66 m 2.2 m ENVIRONMENTAL CHARACTERIZATION MARDI (M. Malin, MSSS) Descent imaging REMS (J. Gómez Elvira, CAB, Spain) Meteorology / UV RAD (D. Hassler, SwRI) High energy radiation DAN (I. Mitrofanov, IKI, Russia) Subsurface hydrogen 5

6 Mars Landing Sites (Previous Missions and MSL Candidates) 6

7 Candidate Landing Sites Eberswalde Crater (24 S, 327 E, 1.5 km) contains a clay bearing delta formed when an ancient river deposited sediment, possibly into a lake. Gale Crater (4.5 S, 137 E, 4.5 km) contains a 5 km sequence of layers that vary from clay rich materials near the bottom to sulfates at higher elevation. Holden Crater (26 S, 325 E, 1.9 km) has alluvial fans, flood deposits, possible lake beds, and clayrich sediment. Mawrth Vallis (24 N, 341 E, 2.2 km) exposes layers within Mars surface with differing mineralogy, including at least two kinds of clays. 7

8 Programme Building Blocks E X O M A R S ESA and NASA have agreed to to embark on on a joint Mars robotic exploration programme: Initial missions have been defined for for the the 2016 (January) and 2018 launch opportunities; Missions for for 2020 and beyond are are in in a planning stage; The joint programme s ultimate objective is is an an international Mars Sample Return mission ESA-led mission Launcher: NASA Atlas V-431 Orbiter: ESA Payload: NASA-ESA EDL Demo: ESA 2018 NASA-led mission Launcher: NASA Atlas V-531 Cruise & EDL: NASA Rover 1: ESA Payload: ESA-NASA Rover 2: NASA

9 2016 Mission Objectives E X O M A R S 2016 TECHNOLOGY OBJECTIVE Entry, Descent, and Landing (EDL) of of a payload on on the the surface of of Mars. SCIENTIFIC OBJECTIVE To study Martian atmospheric trace gases and their sources. Use of of aerobraking to to achieve science orbit. Provide data relay services for for landed missions until

10 2016 Trace Gas Orbiter Payload E X O M A R S PRIORITISED GOALS INSTRUMENTS 1. Detect a broad suite of atmospheric trace gases and key isotopes with high sensitivity. MATMOS (ppt) US, CAN B, F, RUS H/W Science 2. Map their spatial and temporal variability with high sensitivity. NOMAD (10 1 ppb) B, E, I, UK USA, CAN 3. Determine basic atmospheric state by characterising P, T, winds, dust and water aerosol circulation patterns. EMCS (P, T, dust, ices, H 2 O) MAGIE (Full hemisphere WAC) USA, UK F USA B, F, RUS 4. Image surface features possibly related to trace gas sources and sinks. HiSCI (HRC 2 m/pixel) USA, CH UK, I, D, F Excellent coverage of of high-priority objectives. 10

11 EDL Demonstration 2016 EDL Module (EDM) E X O M A R S E X O M A R S EDM A A European technology demonstrator for for landing medium-large payloads on on Mars; Mars; Provides a limited, but but useful means to to conduct scientific measurements during the the dust dust storm storm season. EDM PAYLOAD Integrated payload mass mass estimate: 3 kg; kg; Lifetime: 4 sols; sols; Data: 1 pass pass of of Mbits. 11

12 2018 Mission Concept Key mission concept features Cruise/EDL system derived from MSL, launched on Atlas V 531 class vehicle Land in ~10 km radius landing ellipse, up to -1 km altitude, within +25 to -15 degrees latitude NASA MAX-C rover will perform in situ exploration of Mars and acquire/cache sets of scientifically selected samples Instrument/Sensing Mast Quad UHF Helix High Gain Antenna Low Gain Antenna SHEC Sample Cache Hazard Cameras Sampling/Science Arm 2.2m Ultraflex Solar Array

13 2018 ExoMars RM Objectives E X O M A R S 2018 TECHNOLOGY OBJECTIVES Surface mobility with a rover (having several kilometres range); Access to to the the subsurface to to acquire samples (with a drill, down to to 2-2- m depth); Sample acquisition, preparation, distribution, and analysis. SCIENTIFIC OBJECTIVES To search for for signs of of past and present life life on on Mars; To characterise the the water/subsurface environment as as a function of of depth in in the the shallow subsurface. 13

14 ExoMars Pasteur Payload E X O M A R S Panoramic camera system x x HRC HRC WAC WAC Two Wide Angle Cameras (WAC): Color, stereo, 34 FOV One High-Resolution Camera (HRC): Color, 5 FOV ~3-m ~3-m penetration, penetration, with with ~2-cm ~2-cm resolution resolution (depends (depends on on subsurface subsurface EM EM properties) properties) 0 Aeolian deposits 0 (m) Sedimentary filling (ns) Spectral Spectral range: range: μm, μm, Sampling Sampling resolution: resolution: nm nm Ground-Penetrating Radar 10 0 Distance 14(m) Analytical Analytical Lab Lab

15 ExoMars RM Laboratory E X O M A R S

16 2018 ExoMars RM - International E X O M A R S

17 Science Aspects for Mars Sample Return NASA has has established a End-to-End Science Advisory Group with with international participation to: to: Identify Mars Mars sample return return science objectives and and priorities Identify science needs for for sample selection, acquisition, control and and analysis

18 Mars Sample Return Architecture Caching rover deposits cache Cache Fetch rover retrieves cache Lander collects contingency sample Sky Crane descent Sky Crane descent Mars Ascent Vehicle (MAV) Orbiting Sample (OS) 500 km orbit Rendezvous and capture of OS Verify flight containment system Caching Mission MSR Orbiter MSR Lander Earth divert of ERV Earth Entry Vehicle (EEV) Sample Receiving Facility (SRF)

19 NASA-ESA Programme Coordination

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21 Implementing Planetary Protection Constraints UN OUTER SPACE TREATY Article IX: IX: avoid harmful contamination of of celestial bodies and adverse changes in in the the environment of of the the Earth COSPAR PLANETARY PROTECTION POLICY AND IMPLEMENTATION GUIDELINES Maintains and promulgates policy for for the the reference of of spacefaring nations as as internationally accepted standard to to guide compliance with Article IX IX of of the the Outer Space Treaty SPACE AGENCY POLICY States compliance with COSPAR Planetary Protection Policy Requirements derived from policy Binding for for flight projects Coordinated between Agencies

22 The Gold Standard Viking 75 Biology experiment Mission Objective: Search for life on Mars GC-MS Bioburden controlled assembly Terminal Sterilization of Lander

23 Planetary Protection Constraints Today SAM/MSL BIOBURDEN CONSTRAINTS Range from standard class assembly to to sterile flight systems More stringent for for missions with life life detection investigations, sample return and landing in in Mars special regions Sample return missions have additional constraints for for containment and hazard assessment Needs to to be be reflected from the the very begin of of the the mission definition phase and continuously monitored during the the project life life cycle Phoenix IMPACT AVOIDANCE CONSTRAINTS Impact probability constraint for for launcher upper stages Impact probability constraints for for primary and secondary targets Impact probability constraints for for orbiter systems Compliance is is affected by by trajectory, mission design, flight hardware design, reliability of of systems and redundancy levels used Scope goes well beyond end-of-life of of the the specific mission Mars 2 3 Aim point

24 Bioburden Control Today TYPICAL BIOBURDEN VALUES Non-controlled manufacturing: spores/m 22 Class cleanroom: spores/m 22 Class cleanroom: 1000 spores/m 22 Aseptic environment: < spores/m 22 People! (Pathfinder) TYPICAL BIOBURDEN CONSTRAINTS Less than 300 spores/m 22 on on general surfaces Less than 3x10 55 spores on on an an entire Mars lander system TYPICAL BIOBURDEN CONTROL MEASURES Frequent cleaning of of all all flight hardware with alcohol or or precision cleaning methods Heat sterilization (~ (~ 125 C) of of more than 50% of of the the flight hardware per per size Several thousand bioburden assays to to control the the bioburden levels Recontamination prevention by by design, barriers, and analysis Very complex machinery (MSL) Large size more than 1000 m 2 of accountable surface area (MSL)

25 Last but not least - Training TRAINING OPPORTUNITIES NASA and ESA training courses are are offered on on an an annual basis Projects usually have their own tailored training courses Training needs for for a typical Mars flight project is is in in the the order of of several 100 participants over a time period of of several years TRAINING LEVELS Depends on on the the mission type Depends how much the the individual is is involved with flight hardware