Technology Reference Studies
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1 In the proceedings of the 8th ESA Workshop on Advanced Space Technologies for Robotics and Automation 'ASTRA 2004' ESTEC, Noordwijk, The Netherlands, November 2-4, 2004 Technology Reference Studies P. Falkner A. Lyngvi, M.L. van den Berg, D. Renton, A. Atzei and A. Peacock Dr. ASTRA WS2004, ESTEC, Nov 04 Page 1
2 Outline Technology Reference Studies (TRS) Background Venus Entry Probe (VEP) Deimos Sample Return (DSR) Jupiter Explorer Mission (JEM) Interstellar Heliopause Probe (IHP) Relevance for Robotics Conclusion Dr. ASTRA WS2004, ESTEC, Nov 04 Page 2
3 Background Strategic focus on critical technology developments for potential future science missions Study technologically demanding, science driven missions that are not part of the science program Identifying critical technologies to enable future missions Establishing a roadmap for technology developments (e.g. TRP2/GSTP4 technology plan) Enable low resource exploration missions Assist the community and ESA in future proposal submission and assessment Enable new low-cost science mission scenarios at increased frequency Provide focus and references for technology development Provide technology in time Dr. ASTRA WS2004, ESTEC, Nov 04 Page 3
4 Current Technology Reference Studies Venus Entry Probe (VEP) Deimos Sample Return (DSR) Jovian Minisat Explorer (JME) Interstellar Heliopause Probe (IHP) Solar Polar Orbiter (SPO) Dedicated talk at ASTRA 2004 Atomic Interferometer X-ray Interferometer Gamma Ray Imager Selection Process: Selected to serve with a small number of TRSs a wide application range DSR small gravity environment, docking & rendezvous, re-entry,.. JEM High radiation, long distance (communication & power supply) VEP Aerobot, Microprobes, localisation & communication, IHP Nuclear power, autonomy, lifetime, solar sails Dr. ASTRA WS2004, ESTEC, Nov 04 Page 4
5 Technology Reference Studies Top-level assumptions: Small launcher, low cost typical Soyuz-Fregat class Use of MicroSat or MiniSat Enable more frequent & phased approaches Based on Highly Integrated Payload Suites Use of Centralised Processing and Power Supply Based on resource reduction and optimisation (Payload and S/C-subsystems) Designed to low cost Dr. ASTRA WS2004, ESTEC, Nov 04 Page 5
6 Venus Entry Probe Detailed in-situ & remote study of the Venus atmosphere Origin and evolution of Venus atmosphere Comparative planetology Composition of lower atmosphere Atmospheric chemistry Greenhouse effect Tracking active volcanism Aerosol analysis/exobiology Analysis of large (ø ~ 7 µm) cloud particles Atmospheric dynamics Super-rotation Hadley cell circulation? Weather patterns in main cloud deck Polar vortices Dr. ASTRA WS2004, ESTEC, Nov 04 Page 6
7 Venus Entry Probe Launch by Soyuz-Fregat 2-1B from Kourou Earth escape, 150 days transfer VEP Two MiniSat s: Low Venus Orbiter - LVO orbit: km x km, inclination = 90 Remote sensing atmospheric investigations concurrent with aerobot Dry mass: 258 kg VRS LVO Venus Relay Satellite VRS orbit: 250 km x 7500 km, inclination = 75 to 90 Deploys entry probe from HEO (250 km x km) Studies ionosphere and (sub)-surface Dry mass: 450 kg Long duration aerobot (VEP) Global in-situ atmospheric coverage Atmospheric microprobes (VMP) Vertical profiles of p, T, flux, wind velocity VRS SF-2B Fairing Dr. ASTRA WS2004, ESTEC, Nov 04 Page 7
8 Venus Entry Probe Key Technological Challenges Aerobot Atmospheric entry Balloon material Gas storage Survivability in Venus atmosphere (~14 days) Miniaturized payload Miniaturized power source 200 g acceleration Atmospheric Microprobes Localization and communication Aero-thermodynamic design Miniaturized payload Sub-system integration See session :00h 3-Nov Dr. ASTRA WS2004, ESTEC, Nov 04 Page 8
9 Small Body Sample Return to Deimos AIM To study and develop the technology required to return a 1kg sample of Deimos Regolith back to Earth Dr. ASTRA WS2004, ESTEC, Nov 04 Page 9
10 Deimos Sample Return 1. Launch into a 200 x km HEO Earth orbit on a Soyuz-Fregat 2B 2. Earth-Mars Transfer 3. Mars Orbit Insertion to 500 x km orbit 4. Mars Orbit Maneuvers to enter into a co-orbit with Deimos ( km circular orbit) Earth Departure Mars-Deimos Operations 5. Sample Collection Maneuvers 6. Mars Orbit Maneuvers to return to 500 x km orbit 7. Mars-Earth Transfer 8. Earth Entry Vehicle (EEV) performs Direct Re-Entry Dr. ASTRA WS2004, ESTEC, Nov 04 Page 10
11 Sampling Method: Preliminary Proposal Obtain Sample quickly and efficiently from the homogeneous regolith on Deimos surface Optimize sampling method for a small, low gravity body Touch-and-Go Sampling Sampling will require high precision control Operations will require high autonomy due to communication lag time Highly Autonomous Guidance, Navigation and Control System Dr. ASTRA WS2004, ESTEC, Nov 04 Page 11
12 Earth Entry Vehicle (EEV) door bandage bio-shield Sample door bio-shield separation mechanism s Provides break in contamination chain Performs direct Re-Entry Protects against contamination on Impact (must survive a hard landing) Contains a beacon for localization and recovery after impact Mass ~ 50 kg Dr. ASTRA WS2004, ESTEC, Nov 04 Page 12
13 Deimos Sample Return Key Technological Challenges Low Gravity Sample Return Sample Mechanism Obtain a sample from a low gravity body Obtain a sample in a short time frame (few seconds) Highly Autonomous Micro GNC System Perform delicate sampling maneuvers Earth Re-Entry Capsule Perform Earth direct entry Safely land in designed zone Planetary Protection Guidelines Dr. ASTRA WS2004, ESTEC, Nov 04 Page 13
14 Jupiter Minisat Explorer Scientific goals: Study the Jovian environment (e.g. radiation, magnetic field) Jupiter s moons, especially Europa: study the global topography (surface features, including recent or current activity) study the composition of the (sub)surface mapping of the ice thickness is a subsurface ocean present? Dr. ASTRA WS2004, ESTEC, Nov 04 Page 14
15 Jupiter Minisat Explorer Launch with Soyuz-Fregat Jupiter transfer Venus-Earth-Earth Gravity Assist Transfer duration: 6 years Solar cell based power system Two satellite configuration: 1. JEO (Europa Orbiter) 200 km circular polar orbit achieved after > 1 year tour science phase duration: maximum of ~60 days 2. JRS (Data Relay S/C): Highly elliptical polar Jupiter orbit Avoiding Radiation Belts Jupiter Dr. ASTRA WS2004, ESTEC, Nov 04 Page 15
16 Jupiter Minisat Explorer Mass budget JRS (kg) JEO (kg) Jupiter Relay Sat Power AOCS 8 8 Propulsion CMDS Communications Structure Thermal 10 6 Radiation shielding 8 27 Total Soyuz Fregat 2B launch Europa Orbiter Launch Date Total DV (m/s) Duration (yrs) 19-Jul Jul Apr Oct Jan Jun Feb May Oct Aug Nov Dr. ASTRA WS2004, ESTEC, Nov 04 Page 16
17 Jupiter Minisat Explorer Key Technological Challenges Development of low resource deep space minisats Deep space as well as Jupiter s extreme radiation environment: Radiation hardened components ( ( 1 Mrad) + radiation shielding Radiation optimised solar cells (LILT), development required Development of highly integrated systems (especially low resource radar) Maximize the use of solar power, even at ~5 AU from Sun Low power deep space communication Planetary protection compatible systems Microprobe System A low cost series of missions to explore the Jovian system in a phased strategic approach is realistic Dr. ASTRA WS2004, ESTEC, Nov 04 Page 17
18 Interstellar Heliopause Probe Scientific objective: Explore and investigate the interface between the local interstellar medium and the heliosphere IHP Investigate the nature of the interstellar medium Investigate how the interstellar medium affect the solar system Investigate how the solar system impact the interstellar medium Technologies for IHP are of great benefit for Outer Planet missions Dr. ASTRA WS2004, ESTEC, Nov 04 Page 18
19 Interstellar Heliopause Probe Soyuz Fregat 2B launch Solar sail mission with a=1 mm/s 2 Close approach to the Sun R=0.25AU Jettison sail at 5 AU Reach 200 AU in 25 years Dr. ASTRA WS2004, ESTEC, Nov 04 Page 19
20 Strawman payload Instrument Mass (kg) Power (W) Plasma analyser 2 1 Plasma and radio wave experiment Magnetometer Neutral and charged atom detector Energetic particle detector Dust analyser UV-photometer CPU+CPS Structures 2 - Total (incl. 20 % system margin) Dr. ASTRA WS2004, ESTEC, Nov 04 Page 20
21 Current Spacecraft Configuration System Mass (kg) Science instruments 22 Attitude Determination and Control 35 Telemetry, tracking and command 61 On-board data handling 12 Thermal Control 14 Power 42 Mechanisms and structure 27 Total mass 213 Sail System mass will be approximately kg Total launch mass: kg including 20 % system margin Dr. ASTRA WS2004, ESTEC, Nov 04 Page 21
22 Interstellar Heliopause Probe Key Technological Challenges Solar Sail: Deployment system of large structures > m 2 Very large, thin and light sail film < 2 µm Light boom structures < 100 g/m ADCS Sail jettison mechanism S/C bus Radioisotope power (specific power of ~ 10 W/kg) Deep space communication (Optical vs. RF) Lifetime and Autonomy Dr. ASTRA WS2004, ESTEC, Nov 04 Page 22
23 Conclusions TRS: Selected to provide references for Solar System Exploration Provides realistic set of Requirements for Technology Development Several Technologies already identified ESA Technology Programme Aim: Provide Technology for Science Missions in time High relevance for robotics and automation Need serious funding Dr. ASTRA WS2004, ESTEC, Nov 04 Page 23
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