HYPER Industrial Feasibility Study Final Presentation Hyper Technology Road Map

Transcription

1 Industrial Feasibility Study Final Presentation Hyper Technology Road Map Ulrich Johann Astrium GmbH 6 March 2003

2 Technology Road Map (1) Hyper Technology programme to support the basic FPAG recommendations (October 2002 session in Paris): Establish clearly identified theme in matter wave & quantum space-time sensors Implement strong technology development programme for preparation of payload elements Explore possibilities for a limited technology demonstration package as passenger at earliest flight opportunity Create a flight opportunity for a mission within this theme within the coming 10 years. 2 6 March 2003, Final Presentation, ESTEC

3 Share of technology developments (road map 2) take maximum advantage of heritage from other projects developments (GOCE, STEP, GP-B, Microscope, Smart 2, LISA) : Inertial Reference Sensor and DFC GOCE sensor (CAESAR) performance sufficient Drag-free Controller from GOCE & Smart-2 FEEP µ-thrusters FEEP-thrusters can be derived from Smart-2 and GOCE h/w Optical Bench Methodology transfer from Smart-2 & GP-B Laser assembly Laser developments for Smart-2 & LISA provide information basis for, despite the laser package heritage from Pharao share developments with other missions preparatory programmes e. g. PHARAO, ATOPIS, LCAO, PARCS, LISA, etc. 3 6 March 2003, Final Presentation, ESTEC

4 Technology Road Map (3) in relation to technology relevant missions Task Name Actual missions GRACE GP-B Pharao (ACES) Microscope GOCE STEP SMART 2 LISA Technology R&D Phase A Phases B to E Technology Developments Instrument TRP (AO&I) System Studies Instrument Development System PHASE B System PHASE C/D Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 4 6 March 2003, Final Presentation, ESTEC

5 Payload Technology (road map 4) Space-proof optical components for light and atoms are vital elements for Reduce mass, size of payload by (colder atoms, integrated interferometers) High-priority elements for the mission identified: Low-noise Cold Atoms Sources of High Brilliance reduction of weight and power and improving robustness by miniaturisation is highly supported both to improve system reliability and to reduce mission cost Compact Laser Source Techniques to improve stability, electro-optical efficiency and robustness are of prominent importance for various future atomic optic projects Ultra stable Raman Laser (URL) Highly stable, low noise Raman Laser of robust design are of eminent importance for coherent beam splitting of matter waves as for other applications in phase locked signal generation (telecommunication or optics) 5 6 March 2003, Final Presentation, ESTEC

6 Payload Technology (road map 5) High-priority payload elements (cntd.): Best-form & Space-flight optics (BSO) Further development of opto-mechanical design and construction methods (GP-B, SMART-2) for the optical components and interfaces considered vital to reduce development risk Ultra-Stable Microwave Source (USMS) New design and precision performance measurement important to reduce noise contribution to atom interferometry with Raman transition Numerical Simulations of Atom Interferometers Early development of software to simulate atom interferometers under real space conditions in the arbitrary gravito-inertial fields is highly recommended and considered critical for all future missions based on this technology 6 6 March 2003, Final Presentation, ESTEC

7 Further CTP/TRP Candidates (road map 6) Investigations for Mass/Size Reduction of Payload Modules Modified integrated ASU concept One drag-free sensor only on re-designed optical bench Re-design of optical bench plus sensors for higher orbit option ASU acquisition/calibration mode and phase control analysis Science Data processing algorithms, spectral behaviour, detailed model of the ASU and simulation System and Mission Aspects End-to-end system performance prediction End-to-end data reduction scheme Simplification of Drag-Free Control Concept possible by increase of obit altitude Sharing mission with co experiments or technology demonstrations 7 6 March 2003, Final Presentation, ESTEC

8 Modified integrated ASU concept Integrated 2-D ASU (advanced payload conceptual idea) IRS1 PST Virtual AOCS Ref. COM IRS2 sequential generation of two perpendicular MZ IF planes from one atomic beam (same or two subsequent clouds) highly integrated, symmetric concept requires switching of B-field collinear to active laser beams (sig pol) or B collinear to atomic beam axis (pi pol) sequential detection significant instrument development necessary path towards integrated ASU sensor?? ASUxy ASU z IF 8 6 March 2003, Final Presentation, ESTEC z 3 y x z Mirror frames ASU Y IF Y 1 counterpropagating atomic beam not shown

9 Modified integrated ASU concept Integrated 2-D ASU conceptual idea: Timing diagram 0s 1s 2s 3s 4s MOT + detection ASU IFx ASU IFy pi/2 RL1 pi RL2 pi/2 RL3 MOT + detection Possible B field orientation collinear to active laser system 9 6 March 2003, Final Presentation, ESTEC

10 Modified integrated ASU concept Integrated 2-D ASU conceptual idea (main features): Integrated (one) ASU assembly for both measurement planes (4 interferometers in one) Maximally symmetric configuration All sensitive axes are collinear (IRS, DFC ref., PST) DFC area as compact as possible (gg-effects, etc.), ASU planes as close together as possible DFC ref. and COM (can be made) centered in ASU plane intersection (RL2) Lowest ASU planes rot displacement arround intersection Laser beams (both systems) can be routed to PST for on-board internal alignment monitoring (e.g. 48 min period) and/or for on-ground calibration or testing Vacuum chamber for ASU drift tube and IRS could be omitted: no windows!, permanent vent, good vacuum, however AIVT problem, launch contamination Bad aspect ratio 1:4 to 1:5 (launch loads) Integrated ASU concept requires ASU technology development and verification Assembly, integration, verification may be more complicated Acessability during testing easier 10 6 March 2003, Final Presentation, ESTEC

11 In-orbit Technology Demonstration (road map 7) Drag-free Control (DFC) DFC is considered the primary technology requiring in-orbit demonstration using Inertial Sensor and FEEP thrusters DFC demonstration adequately covered by missions GOCE and Smart-2 launched before/during development Atom Optics and Interferometry Laser assembly technology first space demo is on Pharao, Smart-2 Compact Laser Source and Raman Laser System can be demonstrated on ground Atom and MW sources and opto-mechanical construction can be verified by complete qualification test programme Conclusion: - no need for technology flight demonstration of these items 11 6 March 2003, Final Presentation, ESTEC

12 Payload Technology Road Map (8) TRP Schedule Task Name Instrument TRP (AO&I) 1-Cold Atoms Source 2-Laser Source for Cold Atoms 3-Ultra-Stable Raman Lasers 4-Best-form / Space-flight optics 5-Ultra-Stable Microwave Sources 6-Atom Interferometer Simulations System Studies 7- Mass Reduction Investigations 8- ASU acquisition / phase control 9- Science Data processing 10- System / Mission Improvements Instrument Development System PHASE B System PHASE C/D Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q March 2003, Final Presentation, ESTEC