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Human Exploration human and operations

OUTLOOK after the CM 2012

MPCV / SM Lunar Lunar Polar Sample Return

EC Workshop and Exploration Madrid, 18 Feb. 2013

International context and operations

• The remains one of ESA’ s destinations for Exploration.

• The Orion / MPCV (SM) – approved at the CM 2012 - opens a new perspective for cooperation between ESA and NASA in the area of Human Exploration

• The technology developed in the context of phase B1 provides options for future cooperation in the area of Lunar Exploration with

EC WS Madrid 18Feb2013 2 MPCV – ORION SM human spaceflight and operations

• ESA will supply the Orion / MPCV SM for the 2017 unmanned Exploration-1 Mission, including ground and operation support.

• Provisions for the construction and delivery of a second SM (FM2) are taken.

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MPCV SM: ESA Elements human spaceflight and operations

Structure SM Harness Consumable Storage • Upper cylinder • delivery system • Tank platform • Gas delivery system • main cylinder • Lower platform Thermal Control • MDPS • Passive thermal control • Active thermal control • Thermal control unit

Data Management • Command & management unit Propulsion • Pressure control assembly • pressurant tanks • propellant tanks • Propellant/isolation system Electrical Power • Tubing • Power control & distribution unit • Fill & drain valves Solar Generator • Aucillary thrusters • Solar array wing assembly • RCS thrusters • Main engine • Thrust vector control Solar array drive assembly • propulsion drive electronics • Solar array drive mechanism • Solar array drive electronics Moon Exploration human spaceflight and operations

• As a consequence of the overall economic situation and the need for ESA Member States to set priorities, the Lunar Lander project could not be funded at the CM 2012

• International cooperation provides opportunities for technology validation and extended scientific return: • Surface access & knowledge: -Resource Lander (>2017), • Science and technology: Lunar Polar Sample Return - LPSR (>2020)

• Need to Bridge funding gap to MC 2014: New activities GSTP, GSP

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ESA – cooperation human spaceflight and operations Lunar Resource Lander human spaceflight and operations

• Russia’s main technology provisions: – of a Large Platform – High thrust propulsion – RTGs

• ESA potential contributions: – Drill to acquire subsurface frozen samples – Hazard Detection and Avoidance Experiment – Visual Navigation Experiment to validate Precision Landing technology.

• ESA contribution to of instruments.

Luna-Resource Lander human spaceflight and operations

Reloading mechanism with samples' encapsulation unit

Moon Drill – adapted from ExoMars Drilling device

ExoMars: Drill Bread Board, Engineering models tested in Laboratory and conditions – needs design adaptations and qualification. Hazard Detection and Avoidance human spaceflight Experiment and operations

HDA Experiment LIDAR • Scanning mechanism • Pulsed fibre laser @ 1064 nm • Measurement rate: 0.2 – 1 Hz Optical assembly • Variable Field of view: 20o-40o Scanning LIDAR concept @ NEPTEC • Mass / Power < 12 kg / 80 W • Volume: 220x320x190 mm3 Electronics based on VNU • Image processing and navigation filter CPU board @ Maxwell • IP board: Technologies • CPU board: 3xIBM 750FX PowerPCTM processors, 1800 MIPS, 512 kB of On- Chip L2 cache, 256 MB of SDRAM IP board • SpaceWire I/F (custom design) • Mass / Power < 4.5 kg / 25 W VNU mechanical configuration • Volume: 300x300x200 mm3 (TBC) ( VPU as example)

Visual Absolute/Relative Terrain human spaceflight Navigation Experiment (VNE) and operations

VNE

CAM Camera • RadHard CMOS detector: 1000 optics • Image acquisition rate: 10 Hz (max.) Camera • Field of view: 50o electronics • Mass / Power < 0.5 kg / 4.5 W CAM conceptual design @ OIP Sensor • Volume: 50x50x50 mm3 VNU:

• Image processing and navigation filter CPU board • IP board: @ Maxwell • CPU board: 3xIBM 750FX PowerPCTM Technologies processors, 1800 MIPS, 512 kB of On- Chip L2 cache, 256 MB of SDRAM IP board • SpaceWire I/F (custom design) • Mass / Power < 4.5 kg / 25 W • Volume: 300x300x200 mm3 (TBC) VNU mechanical configuration (GAIA VPU as example) Missions Technology human spaceflight Development and operations

Mission Launch Propulsion High Rover High Drill Precision Thrust Mobility (2m) Landing 1. Luna-Glob 2015 (Medium) Lander 2. Luna-Glob 2016 3. Luna-Resource 2017 X (Small) X Visual Nav. / Lander HDA

5. LPSR 1 Lander / 2020 X X Return Stage 6. LPSR 2 Lander / 2020+ X x X X Large Rover

Lunar Polar Sample Return (LPSR) human spaceflight and operations

• Main goal is to bring back frozen samples, rich in volatiles, from the Moon polar regions for analysis in laboratories;

• Ideally samples can be taken from Moon craters, but very low temperatures not compatible with today’s technology for Landing Platform and / or Rover design (even with use of RTGS);

• Frozen samples can be obtained from subsurface drilling (1.5 to 2 m) in illuminated areas. Alternatively samples from shadow areas may be considered; LPSR Technology human spaceflight and operations

• The LPSR mission concept is still evolving, main elements are: a. First Lander with Sample Return Stage b. Second Lander with high mobility Rover

• Main technologies needed by the LPSR missions: – High Thrust propulsion; – RTGS; – Drill and Sample handling – Precision landing – Rover navigation across shadow zones (TBC) – Thermal control of frozen sample on the ascent and return trajectory.

Lunar Polar Sample Return human spaceflight and operations

• LPSR is a very complex and ambitious mission and an evolution of past Russian missions to the equatorial regions of the Moon;

• Will explore the polar regions, a landing place for future human missions;

• A mission with high technology challenges LPSR Conceptual and of high scientific interest; Design

• A precursor mission to Mars Sample Return (MSR). Back – up slides human spaceflight and operations

Aurora Programme human spaceflight and operations

ESA Programme (2001) for the human and robotic exploration of the

time Automatic Mars Missions

Cargo Elements of First Human ISS first Human Mission Mission to Mars

Moon Bases Mars Sample ExoMars Return (MSR)

20Jan2011 16 International Context human spaceflight and operations

Evolution of Russian human spaceflight Missions and operations Landers Development Logic human spaceflight and operations

Luna-Glob (lander) Luna-Resource Luna Sample return

Base landing platform Landing platform with improved performance

MPCV SM Overview human spaceflight and operations

GN2 / GO2 Tanks Avionics Platform Water Tank

Propellant Tanks

Solar Arrays Main Engine Auxiliary Thruster Diameter Body 3,83 m

Height of SM 2,72 m Radiators Total mass 13.000 kg Lunar 8.000 kg ISS mission

RCS Power generation 11.1 kW Stage capability in nominal Thruster Adapter conditions SM to CM heat rejection 5 kW capability Lunar Lander Payload human spaceflight and operations