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Phases and timeline System architecture with support facilities

For further information. Plan Général des Opérations COROT COR-0-PL-2061-CNES Ed 1.1. Presentation of commissioning. Phases and timeline System architecture with support facilities LEOP (Launch and Early Orbits Phase) MIP (Orbit raise) including beginning of life calibrations

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Phases and timeline System architecture with support facilities

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  1. For further information Plan Général des Opérations COROT COR-0-PL-2061-CNES Ed 1.1 Presentation of commissioning Phases and timeline System architecture with support facilities LEOP (Launch and Early Orbits Phase) MIP (Orbit raise) including beginning of life calibrations First station acquisition First observing run (technical)

  2. Orientation maneuverStraylight measurement (baffle efficiency) If late launch Technical Run = IR1 IFAR Commissioning timeline Cover opening (1st light) LEOP 4 days Launch + 15 days Technical Run Launch + 60 days IR 1 BMP Mise à poste CCC MIP Commissioning phase Satellite orientation Payload periodic calibration Station acquisition phase Solar Wings rotation BOL calibration (cover closed, then opened) Gyro calibration

  3. Lanceur (Baïkonour) Autorité de Conception Equipe projet COROT Equipe projet filière Proteus Architecte Industriel Satellite DMS Entités opérationnelles SSO Entités en support aux opérations PGGS Centre de Contrôle Salle de Contrôle Principale CNES CNES Réseau de Communication Centre d’Orbitographie Opérationnelle CNES CNES Station Principale (ICONES) Centre d’Opérations du Réseau CNES CNES Stations 2 GHz TC/TM CNES Stations 2 GHz Localisation CNES Components LEOP

  4. Autorité de Conception Equipe projet COROT Equipe projet filière Proteus Architecte Industriel Satellite Entités opérationnelles SSO Entités opérationnelles laboratoires Entités en support aux opérations Support permanent Phases critiques de mission Atelier Logiciel de Vol Centre de Mission Centre Informatique LESIA CNES CNES PGGS Chaîne d’Expertise Etalonnages Centre de Contrôle LESIA CNES Alerte Transits Planétaires Réseau de Communication Salle de Contrôle Principale LAM CNES CNES Station Principale (ICONES) CNES + Interface N1 CDC-LAM Station Secondaire (ALC) INPE Station de back-up (VGS) IFA Components Commissioning

  5. Use of ground stations • LEOP Phase Tried-and-trusted facilities • ICONES : TTCET KRN, TTCET AUS TC/HKTM, doppler data • Stations 2 GHz + kit : HBK : TC/HKTM, angular data (kit SEBB monosat) KRN : TC/HKTM, doppler and angular data (kit SEBB multisat) • Stations 2 GHz : AUS : angular data Facilities specifically developped • Stations 2 GHz : KRU Homère : TC/HKTM, angular data (3801+SLE)

  6. Alcantara (INPE) Tests of communication (exchange of files) with INPE control center successful Arrival of TTCET in packing cases on 23.08.2006 Should be inserted smoothly in the operations during first observing run…

  7. Vienna (IFA) All system tests completed • Radiofrequency compatibilty • Ground communications (exchange of files) • Tracking of Calipso (twice)

  8. Launch and launcher mission Negative chronology • H0 - 10:20:00 : DMS COROT et LCM Starsem in bunkers • H0 - 10:10:00 : Communication checks EGSE checks & battery management operationsAbort by customer  new attempt within 10 days • H0 - 05:00:00 : Removal of thermal cover • H0 - 04:20:00 : State Commission for 3-stage LV fuellingAbort by customer  new attempt at D+1 • H0 - 01:25:00 : 3-stage LV fuelling completion • H0 - 00:45:00 : VSOTR deconnected, high pressure STVVD ON • H0 - 00:30:00 : Servicing platforms retraction • H0 - 00:10:20 : SRP (Spacecraft Readiness Panel) for automatic abort • H0 - 00:02:30 : Umbilical drop off • H0 - 00:00:20 : First and second stage engines ignitionAbort by customer not possible If abort by LV, LV is removed from the pad and refurbished • H0 : Lift-off Holds authorized

  9. Annie OK Michel OK Thien OK Launch and launcher mission

  10. Launch and launcher mission Positive chronology • Mission analysis review on 24.07.2006 • Thermal constraints taken into account • Short-duration mission • separation at H0 + 00:50:02, i.e 28 min before pass over HBK (init sequence completed, LTTM download after TC sending) • No separation visibility by Russian ground stations • injection confirmed later by Starsem (no mobile station available for real time status over HBK) • End of mission after atmosphere re-entry of Fregat

  11. Launch and launcher mission Launch time Eclipse duration (slot 01/10/2006 to 31/10/2006) RAAN = 14.5° 15.7 min RAAN = 194.5° 36.5 min

  12. Launch and launcher mission(positive chronology)

  13. Launch and launcher mission(positive chronology) Separation and first orbits Séparation

  14. Init and deployment sequence Triggered by reconfiguration module (RM) after detection of separation Boot of on-board processor (PM) and drivers Once active, the on-board software executes the automatic sequencefor solar wing deployment (+Y, then -Y) 7 min Gyros ON for unfolding monitoring, then OFF • AOCS automatic sequence to BBQ • RDP0 : Rate Damping Phase – 0, • RDP1 : Rate Damping Phase – 1, • SPP : Sun Pointing Phase, • BBQ : Barbecue (<0.37°/s) • -Xs towards the Sun MAG + MTB MAG + CSS + MTB 2 h MAG + CSS + MTB+ 2 RW LEOP (D1) The CCC orders the spacecraft to switch from SAFE to REDUCEDcommand & control mode

  15. STAM (Star acquisition mode) • STAM Helio (+ ramp) : speed reduced to 0.25°/s and convergenceof the kinetic momentum towards Sun (in the back) • STAM Inertial : speed damped to 0 et and canonical rendez-voustowards the inertial reference frame (optimal roll) MAG + CSS + MTB + GYROS + STR + 4 RW LEOP (D2,3) The CCC authorizes the spacecraft to send payload housekeeping telemetry (DTM + HKTMR : CUIVRE 1, 2, CUTH) All avionics are set to ON : GPS, STR , 2 gyros, et 2 additional reaction wheels STAM preparation and GPS data available for orbit computation by G2 High-rate TM emission (733 kbits) and GPS datation available NOM AOCS and NOM CC

  16. Maneuvers (OCM2) to calibrate thrusters Maneuvers (OCM4) for orbit corrections MIP (beginning of life) Opening of the cover, in visibility • Cover surveillance inhibition • Release (heating of a shape memory alloy) Payload is set to ON Checks of temperatures Authorization of on-board FDIR algorithmsSelection of master clock (BS2) Thermal regulation set to ON BS2, ETN, BCC set to ON (in this order) After PBS boot, payload is ready to receive TC 1553 Beginning of life calibrations (cover closed) Gyro calibration The satellite is ready for the first station acquisition phase

  17. Orbit correction strategy To keep a capacity inV to • Make the mission richer : orbit plane drift after a year of operation (stellar fields closer to the eye center) • End of life : perigee maneuver to accelerate the spacecraft deorbitation (IADC recommendations) Target orbit • Semi-major axis : 896 km • eccentricity : frozen orbit • Inclination,  : stability of the orbit plane ( = 14.5 in J2000)

  18. Orbit correction strategy Precision of injection (osculated) parameters

  19. Orbit correction strategy Correction of errors (1/2) • Semi-major axis • Dispersions at 3 : 5 km • No strong mission constraint • Minimal correction (Hohmann transfer of 1.5 km) if necessary to manage the risk of collision with Fregat if no reentry (contingency) • Reminder : no altitude control after opening of the cover • Eccentricity • Dispersions at 3 : 0.001 • Mission constraint : eMOY < 0.005 over 3 years • Compatible with natural drift (if perigee well chosen)  No specific correction expected

  20. Orbit correction strategy Correction of errors (2/2) • Inclination • Dispersions at 3 : 0.083 degrees • Mission constraint : stability of the orbit plane (before orbit drift) • V (11 /s) applied at a node by series of 2 thrusts • RAAN • Dispersions at 3 : 0.12 degrees • Mission constraint : RA of the eye center • The depointing capacity of the satellite is fully compatible with this dispersion  No correction expected

  21. Orbit correction strategy Fuel budget LEOP : roughly 12 m/s (worst case)

  22. The station acquisition phase Scenario over 7 days 4 times a year Spacecraft orientation (coupled with housekeeping maneuvers if needed) Transition - step by step - toward Observation mode Programming of • Asteroseismology channels • Exoplanet channels Operations in Mission Center are twofold Scientific / Command and Control To start and feed Mission ACS Mode

  23. Transition on TC Transition on TC with automatic return Order number in a nominal sequence , , ... Ê Ë Transition on anomaly (automatic) Transition on PROTEUS configuration change Mode flower OFF SAFE Station Acquisition Ê VALIDATION IMAGE VEILLE Modes dédiés aux ASTERO CALIBRATIONS DEBUT DE VIE Ë VALIDATION ECARTOMETRIE GROSSIERE Ì Í VALIDATION IMAGE CALIBRATION VALIDATION ECARTOMETRIE FINE EXOPLANETES PERIODIQUE Î VALIDATION PLAN DE MASQUES Ï OBSERVATION

  24. Preliminary step Spacecraft attitude maneuver for a new run ToolCorotsky Alpha=101.72;delta=-0.2 Rot=7.28 Choice of a field among some candidates (Scientific Committee) Dates of beginning/end of run Checks for technical feasibility Attitude Quaternion for the selected field

  25. Preliminary step Spacecraft attitude maneuver for a new run

  26. Transition on TC Transition on TC with automatic return Order number in a nominal sequence , , ... Ê Ë Transition on anomaly (automatic) Transition on PROTEUS configuration change Preliminary step OFF SAFE Phase de Mise en station Ê VALIDATION IMAGE VEILLE Modes dédiés aux ASTERO CALIBRATIONS DEBUT DE VIE Ë VALIDATION ECARTOMETRIE GROSSIERE Ì Í VALIDATION IMAGE CALIBRATION VALIDATION ECARTOMETRIE FINE EXOPLANETES PERIODIQUE Î VALIDATION PLAN DE MASQUES Ï OBSERVATION

  27. Transition on TC Transition on TC with automatic return Order number in a nominal sequence , , ... Ê Ë Transition on anomaly (automatic) Transition on PROTEUS configuration change Step 1 OFF SAFE Phase de Mise en station Ê VALIDATION IMAGE VEILLE Modes dédiés aux ASTERO CALIBRATIONS DEBUT DE VIE Ë VALIDATION ECARTOMETRIE GROSSIERE Ì Í VALIDATION IMAGE CALIBRATION VALIDATION ECARTOMETRIE FINE EXOPLANETES PERIODIQUE Î VALIDATION PLAN DE MASQUES Ï OBSERVATION

  28. Step 1 Sky recognitionIdentification of starsInstrument geometric calibration Astero channel ToolsFindstars/Identstars CCD A1 Full images Extraction of stellar objects (with mv) Removal of offset, sky background, cosmics, electronic gain and smearing Threshold for thresholded images Identification of targets (using Tycho catalog) Instantaneous line of sight CCD A2 ToolAlpage Focal plane cartography Optical distortion reestimate (polynomial) 2 x 3 images 2 successive orbits

  29. Star Tracker field of view Zs- PROTEUS platform

  30. Ys+ Zs- S STR masked by the Earth Step 1 ANTICENTER Autumn (close to J280) Zs- toward the Sun Star Tracker unavailable over the night side of the Earth

  31. Ys+ Zs- S Better case STR masked by the Earth Step 1 ANTICENTER Spring (close to J94) Zs- not toward the Sun Star Tracker unavailable over the day side of the Earth

  32. PSOtrans Instant of transition Conventional orbital position PSOtrans Favorable position all over the year STR masked by the Earth Including roll angle

  33. Transition on TC Transition on TC with automatic return Order number in a nominal sequence , , ... Ê Ë Transition on anomaly (automatic) Transition on PROTEUS configuration change Step 2 OFF SAFE Phase de Mise en station Ê VALIDATION IMAGE VEILLE Modes dédiés aux ASTERO CALIBRATIONS DEBUT DE VIE Ë VALIDATION ECARTOMETRIE GROSSIERE Ì Í VALIDATION IMAGE CALIBRATION VALIDATION ECARTOMETRIE FINE EXOPLANETES PERIODIQUE Î VALIDATION PLAN DE MASQUES Ï OBSERVATION

  34. XV YV Step 2 Line of sight calibrationDelta_quaternionAttitude correction maneuver Astero channel ToolIdentstars Thresholded images Trajectory of seamarks(e.g over 3 orbits) • Time series of seamark positions : • - 64 couples of thresholded images / orbit • 50 seamarks by image (both CCD) • quality flags • Instantaneous line of sight 0E1 CCD A1 CCD E1 + + + PSOtrans y + ToolAlpage 0A1 0E2 CCD A2 CCD E2 x Expected position Line of sight orbital variation Bias between payload and platform(on each axis) Delta_quaternion at PSOtrans 0A2

  35. Transition on TC Transition on TC with automatic return Order number in a nominal sequence , , ... Ê Ë Transition on anomaly (automatic) Transition on PROTEUS configuration change Step 2 OFF SAFE Phase de Mise en station Ê VALIDATION IMAGE VEILLE Modes dédiés aux ASTERO CALIBRATIONS DEBUT DE VIE Ë VALIDATION ECARTOMETRIE GROSSIERE Ì Í VALIDATION IMAGE CALIBRATION VALIDATION ECARTOMETRIE FINE EXOPLANETES PERIODIQUE Î VALIDATION PLAN DE MASQUES Ï OBSERVATION

  36. Step 2 Line of sight calibrationDelta_quaternionAttitude correction maneuver Astero channel ToolCorotsky CCD A1 Full images Bias incorporated into Q_att 360 arcsec (3) + + + Once correction maneuver completed : 15 arcsec (3) Expected position PSOtrans CCD A2 ToolFindstars/Identstars Line of sight control Extraction of additional stellar objects(if necessary) 1 image

  37. Bias computation Validated during system tests • Blind static test with thresholded images produced by instrument test bench (with video simulator) Corotsky Line of sight (corrected) : Alpha = 101.698 Delta = -0.247 Roll = 0.0 Corotsky Line of sight (target) : Alpha = 101.6 Delta = -0.23 Roll = 0.0 Identstars/Alpage/Deltachoice Bias : psi = 0.001813 theta = -0.097946 phi = -0.017328 Recorded in BDE Q_att step2  G2 Q_att step0  G2 Threshold images (N0) Line of sight (simulated) : Alpha = 101.502 Delta = -0.213 Roll = 0.0 Sign and amplitude are correct Error < 4 arcsec Including max errorAlpage < 1 arcsec

  38. Large window Small window Dark window Step 3 Upload of windowingStart of rough ecartometryACS in open loop control Astero channel ToolsSismowind/Sismoparam CCD A1 • Windowing • large window memory plan (PMG) • scientific memory plan (PMS) • Set of constraints • size and position of objects • CCD readout time- EMC patterns (crosstalk) • Generation of telecommand parameters • Camera controller (CS16) • Extraction unit and DPU (TC 1553) • Checks on EM test bench before uploading CCD A2

  39. Transition on TC Transition on TC with automatic return Order number in a nominal sequence , , ... Ê Ë Transition on anomaly (automatic) Transition on PROTEUS configuration change Step 3 OFF SAFE Phase de Mise en station Ê VALIDATION IMAGE VEILLE Modes dédiés aux ASTERO CALIBRATIONS DEBUT DE VIE Ë VALIDATION ECARTOMETRIE GROSSIERE Ì Í VALIDATION IMAGE CALIBRATION VALIDATION ECARTOMETRIE FINE EXOPLANETES PERIODIQUE Î VALIDATION PLAN DE MASQUES Ï OBSERVATION

  40. Large window Step 3 Upload of windowingStart of rough ecartometryACS in open loop control Astero channel Once rough ecartometry is running : DPU 1/2 selected as nominal input ACS estimator ON Orbital behavior analysis (4/6 orbits) CCD A1 VEG mode CCD A2 PROTEUS MI-BO mode

  41. Large window Step 4 ACS in closed-loop controlSwitch to scientific windowsStart of fine ecartometry Astero channel Switch to ACS Mission mode when flyingover the PSOtrans Orbital behavior analysis (1 orbit) CCD A1 VEG mode CCD A2 PROTEUS MI-BF mode

  42. Transition on TC Transition on TC with automatic return Order number in a nominal sequence , , ... Ê Ë Transition on anomaly (automatic) Transition on PROTEUS configuration change Step 4 OFF SAFE Phase de Mise en station Ê VALIDATION IMAGE VEILLE Modes dédiés aux ASTERO CALIBRATIONS DEBUT DE VIE Ë VALIDATION ECARTOMETRIE GROSSIERE Ì Í VALIDATION IMAGE CALIBRATION VALIDATION ECARTOMETRIE FINE EXOPLANETES PERIODIQUE Î VALIDATION PLAN DE MASQUES Ï OBSERVATION

  43. Step 4 ACS in closed-loop controlSwitch to scientific windowsStart of fine ecartometry Astero channel Switch from PMG to PMS Spacecraft attitude definitely driven by instrument guide stars Orbital behavior analysis (2 orbit) CCD A1 VEF mode Small window Guide stars Dark window CCD A2 PROTEUS MI-BF mode

  44. Transition on TC Transition on TC with automatic return Order number in a nominal sequence , , ... Ê Ë Transition on anomaly (automatic) Transition on PROTEUS configuration change Step 5 OFF SAFE Phase de Mise en station Ê VALIDATION IMAGE VEILLE Modes dédiés aux ASTERO CALIBRATIONS DEBUT DE VIE Ë VALIDATION ECARTOMETRIE GROSSIERE Ì Í VALIDATION IMAGE CALIBRATION VALIDATION ECARTOMETRIE FINE EXOPLANETES PERIODIQUE Î VALIDATION PLAN DE MASQUES Ï OBSERVATION

  45. Step 5 Exo channel Sky recognitionIdentification of bright starsInstrument geometric calibrationIdentification of all stars ToolExowind Full images 64-exposure 128-exposure CCD E1 • Removal of offset, sky background, cosmics, electronic gain, smearing and EMC patterns • Identification of saturating stars • Selection of bright objects for calibration • Focal plane cartography • Optical distortion reestimate (polynomial) • Once geometry is reestimated : • Identification of stellar objects (using Exodat) • Extraction of PSF as a function of : • spectral type • position in the field of view CCD E2 3+1 accumulations 4 successive orbits

  46. Transition on TC Transition on TC with automatic return Order number in a nominal sequence , , ... Ê Ë Transition on anomaly (automatic) Transition on PROTEUS configuration change Step 6 OFF SAFE Phase de Mise en station Ê VALIDATION IMAGE VEILLE Modes dédiés aux ASTERO CALIBRATIONS DEBUT DE VIE Ë VALIDATION ECARTOMETRIE GROSSIERE Ì Í VALIDATION IMAGE CALIBRATION VALIDATION ECARTOMETRIE FINE EXOPLANETES PERIODIQUE Î VALIDATION PLAN DE MASQUES Ï OBSERVATION

  47. Alternate methodunder implementation m v=12 - 85 p x m v=12 - 125 p x m v=15 - 55 p x m v=15 - 65 p x Step 6 Upload of windowingValidation (subset of objects) Exo channel ToolExowind • Automatic process to assign a maskto each Exobasket stellar object • PSF fitting/SNR optimization • Generation of telecommand parameters • Extraction unit and DPU (TC 1553) • Checks on EM test bench before uploading ToolVPM process Subset of 500 windows/CCD Geometric/SNR control 256 templates / CCD

  48. Transition on TC Transition on TC with automatic return Order number in a nominal sequence , , ... Ê Ë Transition on anomaly (automatic) Transition on PROTEUS configuration change Step 7 OFF SAFE Phase de Mise en station Ê VALIDATION IMAGE VEILLE Modes dédiés aux ASTERO CALIBRATIONS DEBUT DE VIE Ë VALIDATION ECARTOMETRIE GROSSIERE Ì Í VALIDATION IMAGE CALIBRATION VALIDATION ECARTOMETRIE FINE EXOPLANETES PERIODIQUE Î VALIDATION PLAN DE MASQUES Ï OBSERVATION

  49. Step 7 Start of scientific processes Both channels Start of all scientific software processes Telemetry production : light curves, seismology mask images and exoplanet imagettes ToolSismomask Upload of optimized photometric masks PSF fitting/SNR optimization ToolAlert function Targets oversampled on request in casea transit event is expected List of other oversampled objects (selected APs)

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