Bernaerts SatelliteStatus

Information about Bernaerts SatelliteStatus

Published on January 16, 2008

Author: Tomasina

Source: authorstream.com

Content

PROBA 2 Satellite Status:  PROBA 2 Satellite Status ROB, 5 November 2007 D. Bernaerts (1), K. Gantois (2) (1) European Space Agency/ESTEC – Keplerlaan 1, NL 2200AG Noordwijk, The Netherlands www.esa.int (2) Verhaert Space, Hogenakkerhoekstraat 9, Kruibeke, Belgium www.verhaertspace.com Slide2:  Overview Introduction: PROBA 2 Overview PROBA 2 Manufacturing and Integration Status PROBA 2 Remaining Satellite Activities PROBA 2 Launch PROBA 2 Commissioning and Mission Preparations Slide3:  Introduction : The PROBA series PROBA 1 Development: 1998-2001 Mission: 2001 - current PROBA 2 Development: 2003-2007 Mission: end 2008 - … PROBA 3 – in preparation Development: foreseen 2007-2010 Mission: foreseen 2011 - … Slide4:  Introduction : Mission Objectives In Orbit Demonstration Mission concept demonstrations SC Platform technology demonstrations Instrument technology demonstration Primary instrument selection: prospect for operational mission after demonstration Slide5:  Small mission for in orbit demonstration of platform and payload technologies Developed within the frame of the ESA technology programme Accomodation of guest payload providing user data PROBA 2 expands on PROBA 1 experience demonstrated for 6 years in orbit e.g.: small mission development life-cycle autonomous on board flight dynamics advanced avionics technology agile gyro-less design based on low cost autonomous star tracker Introduction : Mission Objectives Slide6:  software development methodology (auto-coding and integrated software & system validation cycle) unified ground support equipment and mission operations center ground segment automation observation user programme Introduction : Mission Objectives Slide7:  Orbit: Spacecraft designed for LEO sun-synchronous orbit Altitude between 700 and 800 km (728km baseline) Local time of ascending node 6:00 Sun pointing with automatic manoeuvring Mission duration: 2 Years Volume: 600 mm x 700 mm x 850 mm Mass: 130 kg Power Consumption: 53 - 86 W RF: S-band, 64 kbit/s uplink; 1 Mbit/s downlink Ground station: Redu (Belgium) Launcher: Rockot (auxillary passenger of SMOS) Introduction : PROBA 2 key figures Slide8:  Mixed Honeycomb structure Alu/CFRP Passive thermal control (except Battery) Deployable solar panels with 3-Junction GaAs cells Single box miniature avionics: LEON based Data handling system unregulated power bus 25-28.9V Payload processing 18 Ah Lithium-Ion battery (0°C-40°C) S-band communication system (2 Mbit/s downlink, 64kbit/s uplink) 3-axis stabilised ACNS 4 reaction wheels 3 redundant magnetotorquers 2 three-axis magnetometers 2 Star Trackers with 2 optical heads 2 GPS Cold gas propulsion system PROBA 2 subsystems Slide9:  XUV solar Radiometer with diamond detectors 4 channels covering a wide temperature range 200-220 nm Herzberg continuum range (interference filter) Lyman-alpha (121.6 nm, interference filter) Aluminium filter channel (17-70 nm) incl. He II at 30.4 nm Zirconium filter XUV channel (1-20 nm) High cadence (up to 100Hz) PROBA 2 Instruments – LYRA Slide10:  SWAP (Sun Watcher using APS and image Processing) Monitoring of solar space weather phenomena (coronal holes, flares, CME signatures) EUV (17.5 nm) 1000x1000 imaging with active pixel sensor A full disk image every minute. PROBA 2 Instruments – . Slide11:  Image recognition and compression functions: SWAP produces 10x more data than its TM budget: near loss-less image compression image selection automated detection of space weather events: flares, EIT waves, prominence/filament eruptions autonomous flare tracking. Demonstration of new technologies : compact EUV imagers: CMOS sensor off-axis, shutterless optical configuration PROBA 2 Instruments – . Slide12:  DSLP TPMU Direction of Flight Dual Segmented Langmuir Probes: study background plasma of earth’s magnetosphere Thermal Plasma Measurement Unit measure ion densities and compostion measure electron temperature measure floating potential of the spacecraft body Institute of Atmospheric Physics, Cz. PROBA 2 Instruments – Plasma payloads Slide13:  Introduction : PROBA 2 block diagram Slide14:  New Technologies Introduction : PROBA 2 block diagram Slide15:  PROBA 2 Satellite Status Unit/Instrument manufacturing, testing and integration status: All units accepted and integrated on Spacecraft with the following exceptions: ESP: qualification problem encountered. Re-manufacturing and qualification ongoing. Delivery expected end of 2007. AOCS IF: Final acceptance testing ongoing. Delivery December 2007. ADPMS: technology and qualification issues encountered concerning PCB manufacturing and the mounting of components (including the new LEON processor). Recovery action ongoing. MCPM acceptance testing to be performed in ADPMS Onboard software status: All onboard software produced, validated and delivered. Integration testing on hardware and system validation ongoing. Slide16:  PROBA 2 Satellite Status Slide17:  PROBA 2 Satellite Status Ground Segment : Ground segment produced and undergoing factory acceptance tests. Deployment at ground segment site (Redu) planned during next months. Incorporation of additional ground stations (Svalbard) to be performed (pending launch status). Operations : Operational procedures for platform defined, implemented and tested Operational procedures for instruments defined and being implemented and tested Slide18:  Integrated Software development and System Validation approach: S/C design phase EM/FM Unit Manuf. PFM S/C integration System Validation Operations PROBA 2 Satellite Status Slide19:  PROBA 2 Satellite Status System status: System integration complete (except units of previous slide: qualification models integrated) System Thermal Vacuum Testing completed System Validation Testing ongoing : SVT’s for Platform nominal and contingency procedures completed SVT for instrument operations planned end November Slide20:  Remaining Satellite Activities System validation test 5 (instrument operations) Satellite vibration tests (Jan-Feb 2008) Satellite Flight Acceptance Review part 1 (March 2008) Completion of missing units (ADPMS) Final FAR Satellite Storage Transportation and launch campaign Slide21:  PROBA 2 Launch PROBA 2 co-passenger on SMOS-Launch Mission analysis review (FMAM) completed and safety review ongoing Final orbit and launch scenario selected and analysed Launch date to be confirmed !!! (conflicts with other missions) Current launch date: end 2008 Slide22:  Commissioning and Operations Preparations All operations procedures are available and tested (or under test). Furthermore, high level commissioning plan defined. However, detailed commissioning timeline still under preparation. Involvement of Svalbard ground station for LEOP, Commissioning and routine operations to be finalised. Deployment of ground segment at ground station site to be completed. TBC: joint test with science ground segment? Practical arrangements with science ground segment for commissioning to be finalised. Test definition and follow up Analysis of results Feedback to operations

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