Martian In Situ Investigations
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1 Mars MetNet Mission and Payload Precursors Martian In Situ Investigations Saariselkä, EuroPlanet Workshop Dr. Ari-Matti Harri Finnish Meteorological Institute
2 Finnish Meteorological Institute, Finland Lavochkin Association, Russia Russian Space Research Institute, Russia Instituto Nacional de Técnica Aeroespacial, Spain Dr. Ari-Matti Harri
3 Goal: wide-spread surface observations network around Mars to investigate atmospheric physics, meteorology and planetary interior and crust. Secondary goal: Landing safety of future missions. Protype development performed in Entry, descent and landing system qualified for Mars ( ) Precursor mission and a series of missions to start in and to extend over several subsequent launch windows. The Mars MetNet Mission concept Successor of the Netlander Mission s atmospheric leg. Mission lead : FMI Systems lead : LA Payload lead : FMI / IKI Payload : INTA Other collaborators are invited to join the mission efforts
4 Surface Pressure, mb MetNet Mission For Mars MetNet Network Science Objectives Atmosphere Surface to Atmosphere interactions & the Planetary Boundary Layer (PBL) Atmospheric dynamics and circulation Cycles of CO 2, H 2 O and dust. Dust raising mechanisms The evolution of Martian climate Network missions / Proposals: Mars-92/96 Marsnet Intermarsnet NetLander MESUR PASCAL METNET Viking Lander Surface Pre ssure s Year 1 Year 2 Year 3 Year VL-2 8 VL A reocentric Longitude, degr ees
5 Chosen concept (5 candidates) Additional IBD deployment Main IBD deployment Entry Braking by means of additional IBD Separation of main IBD Landing event Science mission on-surface operations Penetration
6 MetNet Mission For Mars Main Parameters of the MetNet Lander PARAMETER VALUE Vehicle mass 22.2 kg Payload mass 4.0 kg Landing speed m/s Diameter of MIBU 1m Diameter of AIBU 2m
7 HIAD/IRVE-3 Hypersonic Inflatable Aerodynamic Decelerator (HIAD) Dimensions: 56 cm x 3000 cm (cylinder) Diameter (infl.): 3m Total mass: 100 kg
8 MetNet penetrator with inflatable heat shield & aerobrake Inflated configuration Aerobrake device Penetrator body Instrument & system bay Inflatable heat shield Penetrator nose cone retracted Rigid section of the heat shield
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11 Thermal protection system tests MetNet Mission For Mars
12 Low altitude drop test MetNet Mission For Mars
13 MetNet Mars Precursor Mission (MMPM)
14 MMPM Primary Goals Carry out the MMPM flight to Mars Demonstrate the feasibility and robustness of the MetNet concept Prove that MetNet is capable of operating at Mars incl high latitudes Carry out scientific observations at the Martian surface
15 MMPM Mass budget MMPM Mass Kg EDLS 12.0 Landing Module 13.2 Lander body 9.2 P/L Module 4 Total Entry Mass 22.2
16 Strawman payload MetSIS and OWLS (INTA) Solar Irradiance Sensor with Optical Wireless System PanCam (RUS) Panoramic camera Magnetometer (INTA) MetHumi (FIN) Humidity sensor Mass Table PanCam MetTemp (x2) Dust Sensor MetBaro MetSIS and OWLS Magnetometer MetHumi Instrument reserve Total 100g 20g 42g 100g 115g 75g 15g 42g 509g Dust Sensor (INTA) MetTemp (RUS) Temperature sensors MetBaro (FIN) Pressure sensor
17 MetSIS and OWLS (INTA) Solar Irradiance Sensor with Optical Wireless System SIS, PanCam, Temperature sensors and Humidity device are located in the boom. SIS communicates with DPU by using the optical link (OWLS) All the payload is designed to withstand the landing shock of 500 g in the payload bay and about 1000 g outside the payload bay. MetTemp (RUS) Temperature sensors MetHumi (FIN) Humidity sensor
18 MetBaro Pressure sensor is located inside he MNL payload bay The magnetometer and dust sensor, are located in the payload bay inside the MNL. DS is mounted on the frame of the MNL MAG is mounted on the inflatable braking device Magnetometer (INTA) Inflatable braking device MetBaro (FIN) Pressure sensor Dust Sensor (INTA)
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21 MMPM-1 Mission resources: systems Mass The overall Payload bay mass is now tight INTA instrument allocation has not changed Energy MMPM-1: Solar cells and pre-charged (no RTG) Availability of RTGs was low for MMPM-1 schedule Solar cells mounted on the fabric of the inflatable system (up to 500 mw permanent) Command and data systems Freescale controller based system Results in mass savings More flexible design cycle gives more speed after the initial design
22 MetNet Conceptual System Structure
23 Switches MetNet Mission For Mars MetNet MMPM-1 Power Supply MNL power supply is implemented by using very flexible solar cells mounted on the lander additional braking unit, rechargeable batteries and non-rechargeable batteries. Due the general low power level requirement, the instruments are specially designed to operate with very low power. Power system will provide +5V ± 0,25V digital and +12V ± 0,15V analog power lines for the instruments. +5V dig +5V ana +12V POWER SYSTEM 12.8V 28->7.2V 7.2V Charger S/C power Solar Cells Batteries
24 MetNet MMPM-1 System Electronics
25 Deco der/f ormat er T x - C tr l Central Electronics Decod er/ Format er MetNet Mission For Mars MetNet MMPM-1 Radio System and SC Connection MMPM1 Power Conditioning 28V Power line Spacecraft S/C Power System Data Handling System Bi-directional serial Communcations Link RS422 Connector Pair Radio System / Tx Radio System / Rx Antenna/receiv er Hailing Tx Beacon 2 / Tx Beacon 1 / Tx Antenna/receiv er
26 Mounting the MetNet Lander on S/C Bracket MetNet Lander capsule Adjustable angle brace Adapter S/C frame
27 MetNet Lander capsule SSS Jacket Jacket Jacket cover SSS MetNet Lander Valve Pyrolock Spring
28 Preliminary separation and spinning system Rotational platform Platform MetNet Lander ring SSS base Rotation platform MetNet Lander ring Fixator ring Reduction gear MetNet Lander boss Guide tube Base of the system of separation and spinning Movable fixator Drive Adjusting nut Separation System Parameters Rate of rotation, deg/s 150 Separation force, N Spring pusher Pyrolock Pyrolock pin Platform Force duration, s 0.05 Rate of separation, m/s 7
29 Option: Low-lift Mars MetNet Mission Precursor IP-cruising stage A single MetNet Lander could be sent to Mars using SLBM LV Acceleration from LEO by electric propulsion engine (used for more than decade) Small interplanetary cruise stage (heritage from earlier missions) Low cost Requires communications satellite around Mars (MEX, NASAs orbiters, special comsat) MetNet Lander SLBM launch vehicle Volna
30 MetNet Mission For Mars
31 METNET Payload Precursors REMS / Mars Science Laboratory (2012 ) DREAMS / ESA ExoMars-2016 (EDM & TGO) METEO / ESA ExoMars-2018/2020 (Rover) MEDA / NASA Mars-2020 (Rover) These science payloads are Precursors for MetNet science investigations First short-term network with DREAMS to take place during the EDM mission (EDM/EXO-16 + REMS/MSL) MetNet investments are paying off in advance
32 Concluding remarks METNET Mission development continues Payload Precursors paving the way MSL / REMS performs well and is providing an unprecedented data record DREAMS on its way Diurnal cycle investigations require additional modelling efforts combined with observations Surface-atmosphere exchange processes currently under investigation METNET Mission elements have already taken the first steps at Mars
33 & Beyond Odyssey Mars Global Surveyor MRO Mars Express MAVEN Aeronomy Orbiter ESA-IKI ExoMars Trace Gas Orbiter Operational MER Phoenix Mars Science Laboratory ESA EDL Demonstrator InSIGHT ESA Rover NASA Rover MSR Pen etrat ion ExoMars 2016 launch party , FMI / A-M. Harri Sivu 33 / 17
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