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Contribution of Alcatel Alenia Space Italia to fundamental physics space missions Workshop

Contribution of Alcatel Alenia Space Italia to fundamental physics space missions Workshop FUNDAMENTAL PHYSICS IN SPACE WITH SMALL PAYLOADS INFN LNF Frascati, 21-23 March 2006. FUNDAMENTAL PHYSICS PROJECTS. AAS-I projects/activities relative to fundamental physics space missions

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Contribution of Alcatel Alenia Space Italia to fundamental physics space missions Workshop

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  1. Contribution of Alcatel Alenia Space Italia • to fundamental physics space missions • Workshop • FUNDAMENTAL PHYSICS IN SPACE WITH SMALL PAYLOADS • INFN LNF Frascati, 21-23 March 2006

  2. FUNDAMENTAL PHYSICS PROJECTS • AAS-I projects/activities relative to fundamental physics space missions • Lageos II satellite integration • STEP (Satellite Test of the Equivalence Principle) • Two Phase A studies performed for ESA as prime contractor • LISA (Laser Interferometer Space Antenna) for gravitational waves detection • Participation to the Phase A study with the responsibility of the design of the optical bench and participation to the technology development of the laser source with the responsibility of the fiber delivery system • LPF (LISA Pathfinder) • D&D of the Inertial Sensor Electrode Housing and Test Mass and of the Caging Mechanism Assembly in the frame of LPF Implementation Phase • GG (Galileo Galilei) mission for the test of the EP • Phase A study performed for ASI as main industrial contractor

  3. FUNDAMENTAL PHYSICS PROJECTS STEP • Satellite Test of Equivalence Principle (STEP) Phase A studies (1993, 1996) • Mission objective: Verification of the EP within 1 part in 1018 • AAS Role: Prime Contractor (customer ESA) • AAS Specific Tasks: • System requirements and spacecraft design • Spacecraft-instrument interface design • Modelling and analysis of the enviromental disturbance (air drag, magnetic field, self-gravity,..) impacts on the EP measurements

  4. FUNDAMENTAL PHYSICS PROJECTS STEP • Satellite design drivers of the STEP payload • Cryogenic environment necessary to operate the differential accelerometers  liquid helium cryostat, limited lifetime (6 months) • Low Earth Orbit (400 km) required to get a large driving accelerations on the proof masses  “drag-free” control system operated with proportional thrusters fed by the helium evaporated from the cryostat • Ultra sensitive accelerometers  minimization of any coupling with the spacecraft generated disturbances (self-gravity, tides of the helium in the cryostat) Mass: 1000 kg (P/L  260 kg) Power: 450 W maximum

  5. FUNDAMENTAL PHYSICS PROJECTS LISA LISA Phase A study (1999-2000) Mission objective: Gravitational waves detection AAS Role: Sub-Contractor (customer Astrium) • AAS Specific Tasks: • Optical bench opto-mechanical design and analysis • P/L opto-electronics design coordination • Ultra-stable oscillator selection Optical bench

  6. FUNDAMENTAL PHYSICS PROJECTS LISA • Key issues of the LISA optical bench design • Ultra-high dimensional stability required by the laser interferometer  the bench was designed in glass material (ULE) with very low coefficient of thermal expansion; a novel technique (hydroxy-catalysis bonding) was taken into account to be used for “gluing” the optical elements on the bench surface; the mechanical interfaces should minimize the stress on the glass. • The optical elements must be designed and realized to minimize the laser beam wavefront distortions and the straylight on the detectors (at the level of few picoW).

  7. FUNDAMENTAL PHYSICS PROJECTS LISA • High Stability Laser for Space interferometry (2001) • Objective: Development of the LISA laser source stabilized in power, frequency • AAS Role: Sub-Contractor (customer Astrium) • AAS Specific Tasks: • Fiber delivery system (laser source to optical bench) design, procurement, test

  8. FUNDAMENTAL PHYSICS PROJECTS LISA Pathfinder • LISA Pathfinder is a technology demonstration mission for LISA, with a single Spacecraft hosting the LISA Test Package (LTP); LTP is the squeezing of one LISA interferometer arm from 5x106Km to few tens cm, within a single S/C and is constituted mainly by 2 Inertial Sensors and the Optical Metrology S/S. • Within the Inertial Sensor, in the frame of LPF Implementation Phase, AAS-I is presently in charge of design and development of: • the EH: Electrodes Housing • the TM: Test Masses • as subcontractor of the Inertial Sensor Prime • the CMA (Caging Mechanism Assembly), • i.e. the Caging Mechanism and Caging Control Unit (ESA Customer) • under the scientific lead of S. Vitale (TN Univ.), the LTP architect.

  9. EH: ELECTRODE HOUSING CM: CAGING MECHANISM FUNDAMENTAL PHYSICS PROJECTS LISA Pathfinder ISS EH, TM, CM & CCU CCU: CAGING CONTROL UNIT

  10. FRAME ELECTRODES FUNDAMENTAL PHYSICS PROJECTS LISA Pathfinder EH & TM The LISA Electrode Housing provides the control, the sensing and the caging system interface for the inertial sensors (Test Masses) • Main technical challenges in EH • Special materials selection with low LTC, low outgassing, extreme low magnetic impurity, etc • Microns dimensional tolerance in machined subassemblies and assembling • Main technical challenges in TM • Very low susceptibility material with • extremely low magnetic impurities • Non standard Alloy Au/Pt casting • Dimensional tolerance in range of microns • Special Optical Machining of specific Au/Pt surface areas

  11. FUNDAMENTAL PHYSICS PROJECTS LISA Pathfinder - Caging Mechanism Assembly • Caging Mechanism • Two (+Z and –Z) mechanisms shall provide the capability to: • constrain the TM, which resides in the Electrode Housing (EH) in a defined position during launch. • move the TM into a precise position from where it shall be separated from the CM by retracting the CM device from the TM surface with minimum forces (and consequently minimum residual velocity) on the TM; • capture the free falling TM within the electrode housing once released from stowed position and to store the TM in its stowed position again. • To accomplish the above tasks, the CMA is implemented by two sub-mechanisms: • the CMSS (Caging Mechanism Subsystem), to hold the TM in place during launch and until the beginning of the flight operations • the GPRM (Grabbing, Positioning and Release Mechanism), to precisely grab, position and release the TM for scientific operations during flight • and • one Caging Control Unit (CCU)

  12. CM +Z FINGERS TEST MASS CM -Z FUNDAMENTAL PHYSICS PROJECTS LISA Pathfinder CM The Caging Mechanism shall perform pre-loading to the TM (Test Mass), being able to grab the TM in few tens seconds. High pre-load: 3000 N Launch condition Medium pre-load: 300 N Storage condition Low pre-load: 1-20 N Safe function (Grabbing, positioning and release)

  13. FUNDAMENTAL PHYSICS PROJECTS LISA Pathfinder CM GPRM plunger CMSS fingers Hydraulic actuators reservoirs Piezo-valves Piezo-pump View of one of the two CMs

  14. FUNDAMENTAL PHYSICS PROJECTS LISA Pathfinder CM GPRM plungers With CMSS fingers in “retracted position”, the GPRM plungers act on the TM to perform grabbing and positioning Test Mass (TM) View of GPRMs acting on the TM

  15. FUNDAMENTAL PHYSICS PROJECTS Galileo Galilei (GG) • Galileo Galilei (GG) Phase A study (1998) • Mission objective: Verification of the EP within 1 part in 1017 • AAS Role: Main industrial contractor (customer ASI); instrument feasibility study under the scientific leading of P.I. A. Nobili (Pisa Univ.) • AAS Specific Tasks: • System requirements and spacecraft design • Spacecraft-instrument interface design • Attitude control system design and analysis • Drag-free control design and analysis • Dynamic simulator of spacecraft and of the payload (spinning differential accelerometer) • Instrument thermal, mechanical and electronics architectural design

  16. FUNDAMENTAL PHYSICS PROJECTS Galileo Galilei (GG) • Key issues of the GG satellite design • Precise measurement of the rotation status of the satellite spinning at 2 Hz: 0.1% - 0.01%, to be performed by Earth and Sun sensors (star sensors not appropriate for such a high spin rate) • Drag-free control with FEEP micro-thrusters on a spinning satellite  modulated mode operation required synchronized with the spin • Thermal decoupling between the satellite and the payload (operating at room temperature) • Satellite “miniaturisation” (mass limit = 300 kg for a launch with Pegasus) 

  17. FUNDAMENTAL PHYSICS PROJECTS Galileo Galilei (GG) • GG payload is based on a fast rotating, high • sensitivity differential accelerometer operating • in ambient conditions • AAS contributed to GG Instrument Study for: • Instrument electronics study: • EP acquisition chain • PGB & Test Masses whirling/axial control • PGB & Test Masses E-static dampers • Instrument thermal and mechanics study: • Pico Gravity Box • Test Masses suspension and adjustment • Inchworm control • Lock/Unlock mechanism • FEEP electronics study: • Emitter HVPS (3 to 5 kV) • Accelerator HVPS (-2 to -5kV) • Neutraliser PS

  18. FUNDAMENTAL PHYSICS PROJECTS GGG - Galileo Galilei on Ground A Galileo Galilei experimental prototype (GGG) has been implemented inside a vacuum chamber for a first on ground evaluation of the GG baseline hardware in view of the in-flight test on GG satellite AAS-I/LABEN- Proel has provided a significant contribution the the GGG experiment both in terms of hw manufacturing and support for test set-up preparation and test running GGG apparatus set-up, operated at the AAS-I Laben/Proel thermal-vacuum facilities in the years 2002 and 2003

  19. AAS-I experience applicable to fundamental physics • Other projects/activities of AAS-I with technology developments applicable to fundamental physics missions in space • GOCE (Gravity field and Ocean Circulation Explorer) • Drag free control; ultra-stable structure and thermal control for ultra-sensitive accelerometers; measurement model and error analysis/budget; end-to-end performance simulator. • Laser Doppler Interferometry Mission for Earth Gravity Field • Design of laser interferometer for satellite-satellite distance measurement (~1 nm over 10 km) referred to proof-masses of ultra-sensitive accelerometers; measurement model and error analysis/budget. • GAIA laser metrology • Development of high stability optical bench • Development of laser metrology for optics stability monitoring at pm level • Nanobalance Facility • Test at sub-microN level of micro-thrusters for LISA Pathfinder, LISA, Microscope • Cold Gas Micropropulsion Thrusters, Neutralizers for FEEPs and EPDP • Development of technologies for micropropulsion/electric propulsion • Radioscience Instrumentation

  20. AAS-I experience applicable to fundamental physics GOCE GOCE (Gravity field and Ocean Circulation Explorer) • Project in Phase C/D, AAS-I Prime Contractor, Customer ESA • Gravimetric mission with ultra-sensitive accelerometers (1e-12 m/s2) • Drag-free control with ion thruster compensating the resual air drag at 250 km Main P/L instrument: 3-axis gradiometer made by six 3-axis accelerometers

  21. AAS-I experience applicable to fundamental physics Laser Doppler Interferometry Laser Doppler Interferometry Mission for Earth Gravity Field • Feasibility study (2005), AAS-I Prime Contractor, Customer ESA • Gravimetric mission based on satellite-satellite tracking with a laser interferometer. • Drag-free control with ion thruster, laser metrology (1e-9 m resolution over 10 km), ultra-sensitive accelerometers on each satellite for non-gravitational acceleration measurement 10 km The optical bench with the accelerometer and the laser interferometer

  22. AAS-I experience applicable to fundamental physics Laser metrology Laser metrology for Basic Angle monitoring in GAIA mission • Technology study (2004-06), AAS-I Prime Contractor, Customer ESA • Laser metrology based on Fabry-Perot interferometers with 1e-12 m resolution over 1 m distance). Configuration of the GAIA astrometric  telescope with the network of metrology lines Breadboard of a single metrology line 

  23. AAS-I experience applicable to fundamental physics NANOBALANCE FACILITY Nanobalance Facility • Facility realized by AAS-I with Metrological Institute “G. Colonnetti” and Polytechnic of Torino under ESA contract for the characterization of micro-thrusters, to be used for future space missions of fundamental physics (LISA Pathfinder, Microscope, LISA, GG) with a measurement res. < 0.1 microN • The Nanobalance Facility makes use of a Fabry-Perot laser interferometer. Nanobalance Facility   Intrinsic force measurement noise of the Nanobalance

  24. AAS-I experience applicable to fundamental physics Micro-Propulsion Cold Gas Thruster Application Perspectives:GAIA, Proba 3, LISA, DARWIN Cold Gas Micro PropulsionThruster(few uN to 1 mN) based on theProportional Valve (PV)and onMass Flow Sensor(MFS)under development HP PV Engineering model LP PVN 1st prototype S-MFS configuration with a heater and two thermopiles Engineered S-MFS

  25. AAS-I experience applicable to fundamental physics Neutralizers and EPDP for the FEEP Micropropulsion • Neutralizers, utilized in the FEEP Micro PropulsionSubsystem of Microscope and Lisa Pathfinder, for neutralizing the produced ion beam and avoiding spacecraft charging; • Electric Propulsion Diagnostic Package (EPDP) already implemented on SMART1, candidate for LPF and potentially for Microscope EM of the Neutralizer for the FEEP on Microscope/Lisa PF Electron Current up to 6 mA 3D Layout of Neutralizer for the FEEP on Microscope/Lisa PF Sketch of the Neutralizer operation in conjunction with a FEEP thruster

  26. AAS-I experience applicable to fundamental physics Instrumentation for Radioscience Experiments • RF Subsystem in Ka-band for the Radio Science experiment in the Cassini–Huygens mission to Saturn (operative) Future (on board MPO of Bepi Colombo Mission to Mercury): • MORE (Mercury Orbiter Radio-science Experiment), P.I.: L. Iess Uni-Roma1) a system level experiment for the study of the main geodetic and gravitational characteristics of Mercury and in addition the test of gravity theory. The key instrument will be the Ka-band Transponder (KaT) and WBRSfor precision ranging in the Ka/Ka channel link. • ISA (Italian Spring Accelerometer, P.I.: V.Iafolla(INAF-IFSI) a tri-axis accelerometer with accuracy of 10-9ms-2/√Hz in the band 3x10-5 to 10-1 Hz The data measured by ISA will be used to correct the MORE data from the non gravitational perturbations in the Mercury orbit, in particular to subtract the effects of the inertial accelerations.

  27. Heritage Present Future • Meteosat • Spot - Vegetation • ERS1-2 • ISO • Lageos • SAX • Huygens • Helios1 • Envisat :PDS • Envisat :Meris - ASAR • Topex-Poseidon • Jason1 • Clementine • MSG1 • Hélios 2 • Integral • Rosetta • Venus Express • Mars Express • Newton-XMM • Bepi Colombo • Interplanetary missions • Aurora: Exomars, MSR • Earthcare • Sentinels • Simbol’X-Pegase • Galileo Galilei • Solar Orbiter • MTG • Darwin • Xeus • Space Weather • Pleiades GS • post Hélios2 • Export • Hypseo • Sabrina • LISA • MSG 2,3,4 • Herschel • Planck • Cryosat - Siral • MetOp : IASI • MetOp: EPS • GOCE • Calipso • Pléiades • Corot • SMOS • Jason 2 • Microscope • Lisa Patfinder • Agile AAS Science Projects Overview

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