Presentation of commissioning Phases and timeline System architecture with support facilities LEOP (Launch and Early Orbits Phase) MIP (Orbit raise) including beginning of life.
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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) For further information Plan Général des Opérations COROT COR-0-PL-2061-CNES Ed 1.1 SC 20th, Paris, 15 September 2006 1 Commissioning timeline Orientation maneuver Straylight measurement (baffle efficiency) If late launch Technical Run = IR1 Cover opening (1st light) LEOP 4 days Launch + 15 days BMP Technical Run Launch + 60 days IFAR IR 1 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 SC 20th, Paris, 15 September 2006 2 Components Lanceur (Baïkonour) Autorité de Conception Equipe projet COROT Equipe projet filière Proteus Architecte Industriel Satellite DMS LEOP Entités opérationnelles SSO Entités en support aux opérations PGGS SC 20th, Paris, 15 September 2006 4 Centre de Contrôle CNES Salle de Contrôle Principale CNES Réseau de Communication CNES Centre d’Orbitographie Opérationnelle CNES Station Principale (ICONES) CNES Centre d’Opérations du Réseau CNES Stations 2 GHz TC/TM CNES Stations 2 GHz Localisation CNES Components Commissioning 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 Atelier Logiciel de Vol LESIA Centre de Mission Chaîne d’Expertise Etalonnages LESIA Centre de Contrôle CNES Alerte Transits Planétaires LAM Réseau de Communication CNES Station Principale (ICONES) CNES Station Secondaire (ALC) INPE Station de back-up (VGS) IFA CNES CNES PGGS + Interface N1 CDC-LAM SC 20th, Paris, 15 September 2006 5 Centre Informatique Phases critiques de mission Salle de Contrôle Principale CNES 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) SC 20th, Paris, 15 September 2006 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… SC 20th, Paris, 15 September 2006 7 Vienna (IFA) All system tests completed Radiofrequency compatibilty Ground communications (exchange of files) Tracking of Calipso (twice) SC 20th, Paris, 15 September 2006 8 Launch and launcher mission Holds authorized Negative chronology H0 - 10:20:00 : DMS COROT et LCM Starsem in bunkers H0 - 10:10:00 : Communication checks EGSE checks & battery management operations Abort 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 fuelling Abort 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 ignition Abort by customer not possible If abort by LV, LV is removed from the pad and refurbished H0 : Lift-off SC 20th, Paris, 15 September 2006 9 Launch and launcher mission Annie OK SC 20th, Paris, 15 September 2006 10 Michel OK Thien OK 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 SC 20th, Paris, 15 September 2006 11 Launch and launcher mission Launch time Launch date (UTC) RAAN, deg October 10, 2006 October 31, 2006 14.5 19h 30m 19.0s 18h 07m 44.7s 194.5 07h 32m 16.5s 06h 09m 43.5s Launch date (Local Time BKR - UTC+6h) RAAN, deg 14.5 194.5 October 11, 2006 November 01, 2006 01h 30m 19.0s 00h 07m 44.7s October 10, 2006 October 31, 2006 13h 32m 16.5s 12h 09m 43.5s Eclipse duration (slot 01/10/2006 to 31/10/2006) RAAN = 14.5° RAAN = 194.5° SC 20th, Paris, 15 September 2006 12 15.7 min 36.5 min Launch and launcher mission (positive chronology) SC 20th, Paris, 15 September 2006 13 Launch and launcher mission (positive chronology) Separation and first orbits Séparation SC 20th, Paris, 15 September 2006 14 LEOP (D1) Init and deployment sequence 7 min 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 sequence for solar wing deployment (+Y, then -Y) Gyros ON for unfolding monitoring, then OFF AOCS automatic sequence to BBQ RDP0 : RDP1 : SPP : BBQ : 2h Rate Damping Phase – 0, Rate Damping Phase – 1, Sun Pointing Phase, Barbecue (<0.37°/s) MAG + MTB MAG + CSS + MTB MAG + CSS + MTB + 2 RW -Xs towards the Sun The CCC orders the spacecraft to switch from SAFE to REDUCED command & control mode SC 20th, Paris, 15 September 2006 15 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 STAM (Star acquisition mode) STAM Helio (+ ramp) : speed reduced to 0.25°/s and convergence of the kinetic momentum towards Sun (in the back) STAM Inertial : speed damped to 0 et and canonical rendez-vous towards the inertial reference frame (optimal roll) MAG + CSS + MTB + GYROS + STR + 4 RW High-rate TM emission (733 kbits) and GPS datation available NOM AOCS and NOM CC SC 20th, Paris, 15 September 2006 16 MIP (beginning of life) Maneuvers (OCM2) to calibrate thrusters Maneuvers (OCM4) for orbit corrections Payload is set to ON Checks of temperatures Authorization of on-board FDIR algorithms Selection 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 Opening of the cover, in visibility Cover surveillance inhibition Release (heating of a shape memory alloy) The satellite is ready for the first station acquisition phase SC 20th, Paris, 15 September 2006 17 Orbit correction strategy To keep a capacity inV 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) SC 20th, Paris, 15 September 2006 18 Orbit correction strategy Precision of injection (osculated) parameters Parameter Symbol Unit Value Tolerance Actual Dispersion (3sigma) Compliance Semi-major axis a km 7276.34 ±10 7276.34 ±5 Y ES Eccentricty e -- 0.001271 0.002 0,001271 0,001 Y ES Inclination i ¡ 90.0 ±0.1 90.0 ± 0.083 Y ES ¡ 14,50 ±0.2 14,50 ± 0.12 Y ES ¡ 65,56 -- 65,59 ±30 N/A RAAN (for the whole launch period)* Argument of perigee SC 20th, Paris, 15 September 2006 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 SC 20th, Paris, 15 September 2006 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 SC 20th, Paris, 15 September 2006 21 Orbit correction strategy Fuel budget LEOP : roughly 12 m/s (worst case) Dispersions lanceur SOYUZ 3a Orbite vise ˆ l'injection Orbite pire cas ˆ l'injection Corre ction pire cas ˆ raliser anom anom - 3a Transfert de HOHMANN de acollision e=0 (Ex,ey) =(0, - 3e) 3e + eG inom inom - 3i 3i 5 km 3e 0.00225 0.083 deg nom - 3 0.12 deg Orbite finale pire cas (**) 0 m/s 1 0 inom 0.05 deg nom 3 Nombre de manÏ uvres OCM4 anom +/- 3a HOHMANN 1.5km 0.8 m/s (*) 0.001 3i V pire cas 11 m/s 3 nom +/- 3 3 0 0 m/s 0 11.8 m /s 3 TOT AL SC 20th, Paris, 15 September 2006 22 The station acquisition phase 4 times a year Scenario over 7 days Spacecraft orientation (coupled with housekeeping maneuvers if needed) Transition - step by step - toward Observation mode Programming of 1. Asteroseismology channels 2. Exoplanet channels Operations in Mission Center are twofold Scientific / Command and Control SC 20th, Paris, 15 September 2006 23 To start and feed Mission ACS Mode Mode flower OFF SAFE Station Acquisition Modes dédiés aux CALIBRATIONS DEBUT DE VIE VEILLE VALIDATION IMAGE ASTERO VALIDATION ECARTOMETRIE GROSSIERE CALIBRATION PERIODIQUE VALIDATION ECARTOMETRIE FINE VALIDATION IMAGE EXOPLANETES VALIDATION PLAN DE MASQUES OBSERVATION , , ... SC 20th, Paris, 15 September 2006 24 Transition on TC Transition on TC with automatic return Order number in a nominal sequence Transition on anomaly (automatic) Transition on PROTEUS configuration change Preliminary step Spacecraft attitude maneuver for a new run Tool Corotsky Alpha=101.72;delta=-0.2 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 SC 20th, Paris, 15 September 2006 25 Rot=7.28 Preliminary step Spacecraft attitude maneuver for a new run SC 20th, Paris, 15 September 2006 26 Preliminary step OFF SAFE Phase de Mise en station Modes dédiés aux CALIBRATIONS DEBUT DE VIE VEILLE VALIDATION IMAGE ASTERO VALIDATION ECARTOMETRIE GROSSIERE CALIBRATION PERIODIQUE VALIDATION ECARTOMETRIE FINE VALIDATION IMAGE EXOPLANETES VALIDATION PLAN DE MASQUES OBSERVATION , , ... SC 20th, Paris, 15 September 2006 27 Transition on TC Transition on TC with automatic return Order number in a nominal sequence Transition on anomaly (automatic) Transition on PROTEUS configuration change Step 1 OFF SAFE Phase de Mise en station Modes dédiés aux CALIBRATIONS DEBUT DE VIE VEILLE VALIDATION IMAGE ASTERO VALIDATION ECARTOMETRIE GROSSIERE CALIBRATION PERIODIQUE VALIDATION ECARTOMETRIE FINE VALIDATION IMAGE EXOPLANETES VALIDATION PLAN DE MASQUES OBSERVATION , , ... SC 20th, Paris, 15 September 2006 28 Transition on TC Transition on TC with automatic return Order number in a nominal sequence Transition on anomaly (automatic) Transition on PROTEUS configuration change Step 1 Astero channel Sky recognition Identification of stars Instrument geometric calibration Tools Findstars/Identstars 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 A1 Full images CCD A2 Tool Alpage Focal plane cartography Optical distortion reestimate (polynomial) SC 20th, Paris, 15 September 2006 29 2 x 3 images 2 successive orbits Star Tracker field of view Zs- PROTEUS platform SC 20th, Paris, 15 September 2006 30 Step 1 ANTICENTER Autumn (close to J280) Zs- toward the Sun Star Tracker unavailable over the night side of the Earth Ys+ ZsS STR masked by the Earth SC 20th, Paris, 15 September 2006 31 Step 1 ANTICENTER Spring (close to J94) Zs- not toward the Sun Star Tracker unavailable over the day side of the Earth Ys+ ZsS Better case STR masked by the Earth SC 20th, Paris, 15 September 2006 32 Instant of transition Conventional orbital position PSOtrans Favorable position all over the year PSOtrans STR masked by the Earth SC 20th, Paris, 15 September 2006 33 Including roll angle Step 2 OFF SAFE Phase de Mise en station Modes dédiés aux CALIBRATIONS DEBUT DE VIE VEILLE VALIDATION IMAGE ASTERO VALIDATION ECARTOMETRIE GROSSIERE CALIBRATION PERIODIQUE VALIDATION ECARTOMETRIE FINE VALIDATION IMAGE EXOPLANETES VALIDATION PLAN DE MASQUES OBSERVATION , , ... SC 20th, Paris, 15 September 2006 34 Transition on TC Transition on TC with automatic return Order number in a nominal sequence Transition on anomaly (automatic) Transition on PROTEUS configuration change Step 2 Astero channel Line of sight calibration Delta_quaternion Attitude correction maneuver Tool Identstars Time series of seamark positions : - 64 couples of thresholded images / orbit - 50 seamarks by image (both CCD) - quality flags Instantaneous line of sight Tool Trajectory of seamarks (e.g over 3 orbits) CCD A1 ++ y 0A1 Alpage CCD E1 + Line of sight orbital variation Bias between payload and platform (on each axis) Delta_quaternion at PSOtrans SC 20th, Paris, 15 September 2006 35 0E1 + CCD A2 Expected position Thresholded images PSOtrans CCD E2 x 0A2 YV 0E2 XV Step 2 OFF SAFE Phase de Mise en station Modes dédiés aux CALIBRATIONS DEBUT DE VIE VEILLE VALIDATION IMAGE ASTERO VALIDATION ECARTOMETRIE GROSSIERE CALIBRATION PERIODIQUE VALIDATION ECARTOMETRIE FINE VALIDATION IMAGE EXOPLANETES VALIDATION PLAN DE MASQUES OBSERVATION , , ... SC 20th, Paris, 15 September 2006 36 Transition on TC Transition on TC with automatic return Order number in a nominal sequence Transition on anomaly (automatic) Transition on PROTEUS configuration change Step 2 Astero channel Line of sight calibration Delta_quaternion Attitude correction maneuver Tool CCD A1 Corotsky Full images Bias incorporated into Q_att 360 arcsec (3) + + Once correction maneuver completed : Expected position Tool CCD A2 15 arcsec (3) PSOtrans Findstars/Identstars Line of sight control Extraction of additional stellar objects (if necessary) SC 20th, Paris, 15 September 2006 37 1 image Bias computation Validated during system tests Blind static test with thresholded images produced by instrument test bench (with video simulator) 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 SC 20th, Paris, 15 September 2006 38 Corotsky Line of sight (corrected) : Alpha = 101.698 Delta = -0.247 Roll = 0.0 Sign and amplitude are correct Error < 4 arcsec Including max error Alpage < 1 arcsec Step 3 Astero channel Upload of windowing Start of rough ecartometry ACS in open loop control Tools Sismowind/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 SC 20th, Paris, 15 September 2006 39 Large window Small window Dark window CCD A2 Step 3 OFF SAFE Phase de Mise en station Modes dédiés aux CALIBRATIONS DEBUT DE VIE VEILLE VALIDATION IMAGE ASTERO VALIDATION ECARTOMETRIE GROSSIERE CALIBRATION PERIODIQUE VALIDATION ECARTOMETRIE FINE VALIDATION IMAGE EXOPLANETES VALIDATION PLAN DE MASQUES OBSERVATION , , ... SC 20th, Paris, 15 September 2006 40 Transition on TC Transition on TC with automatic return Order number in a nominal sequence Transition on anomaly (automatic) Transition on PROTEUS configuration change Step 3 Astero channel Once rough ecartometry is running : Upload of windowing Start of rough ecartometry ACS in open loop control CCD A1 DPU 1/2 selected as nominal input ACS estimator ON Orbital behavior analysis (4/6 orbits) Large window CCD A2 PROTEUS MI-BO mode SC 20th, Paris, 15 September 2006 41 VEG mode Step 4 Astero channel Switch to ACS Mission mode when flying over the PSOtrans Orbital behavior analysis (1 orbit) ACS in closed-loop control Switch to scientific windows Start of fine ecartometry CCD A1 VEG mode Large window CCD A2 PROTEUS MI-BF mode SC 20th, Paris, 15 September 2006 42 Step 4 OFF SAFE Phase de Mise en station Modes dédiés aux CALIBRATIONS DEBUT DE VIE VEILLE VALIDATION IMAGE ASTERO VALIDATION ECARTOMETRIE GROSSIERE CALIBRATION PERIODIQUE VALIDATION ECARTOMETRIE FINE VALIDATION IMAGE EXOPLANETES VALIDATION PLAN DE MASQUES OBSERVATION , , ... SC 20th, Paris, 15 September 2006 43 Transition on TC Transition on TC with automatic return Order number in a nominal sequence Transition on anomaly (automatic) Transition on PROTEUS configuration change Step 4 Astero channel Switch from PMG to PMS Spacecraft attitude definitely driven by instrument guide stars Orbital behavior analysis (2 orbit) ACS in closed-loop control Switch to scientific windows Start of fine ecartometry CCD A1 VEF mode Small window Guide stars Dark window CCD A2 PROTEUS MI-BF mode SC 20th, Paris, 15 September 2006 44 Step 5 OFF SAFE Phase de Mise en station Modes dédiés aux CALIBRATIONS DEBUT DE VIE VEILLE VALIDATION IMAGE ASTERO VALIDATION ECARTOMETRIE GROSSIERE CALIBRATION PERIODIQUE VALIDATION ECARTOMETRIE FINE VALIDATION IMAGE EXOPLANETES VALIDATION PLAN DE MASQUES OBSERVATION , , ... SC 20th, Paris, 15 September 2006 45 Transition on TC Transition on TC with automatic return Order number in a nominal sequence Transition on anomaly (automatic) Transition on PROTEUS configuration change Step 5 Exo channel Tool Exowind Sky recognition Identification of bright stars Instrument geometric calibration Identification of all stars 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) Full images 64-exposure 128-exposure CCD E2 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 SC 20th, Paris, 15 September 2006 46 3+1 accumulations 4 successive orbits Step 6 OFF SAFE Phase de Mise en station Modes dédiés aux CALIBRATIONS DEBUT DE VIE VEILLE VALIDATION IMAGE ASTERO VALIDATION ECARTOMETRIE GROSSIERE CALIBRATION PERIODIQUE VALIDATION ECARTOMETRIE FINE VALIDATION IMAGE EXOPLANETES VALIDATION PLAN DE MASQUES OBSERVATION , , ... SC 20th, Paris, 15 September 2006 47 Transition on TC Transition on TC with automatic return Order number in a nominal sequence Transition on anomaly (automatic) Transition on PROTEUS configuration change Step 6 Exo channel Upload of windowing Validation (subset of objects) Alternate method under implementation Tool Exowind Automatic process to assign a mask to 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 Tool m v=12 - 85 px m v=12 - 125 px m v=15 - 55 px m v=15 - 65 px VPM process Subset of 500 windows/CCD Geometric/SNR control SC 20th, Paris, 15 September 2006 48 256 templates / CCD Step 7 OFF SAFE Phase de Mise en station Modes dédiés aux CALIBRATIONS DEBUT DE VIE VEILLE VALIDATION IMAGE ASTERO VALIDATION ECARTOMETRIE GROSSIERE CALIBRATION PERIODIQUE VALIDATION ECARTOMETRIE FINE VALIDATION IMAGE EXOPLANETES VALIDATION PLAN DE MASQUES OBSERVATION , , ... SC 20th, Paris, 15 September 2006 49 Transition on TC Transition on TC with automatic return Order number in a nominal sequence Transition on anomaly (automatic) Transition on PROTEUS configuration change Step 7 Both channels Start of scientific processes Start of all scientific software processes Telemetry production : light curves, seismology mask images and exoplanet imagettes Tool Sismomask Upload of optimized photometric masks PSF fitting/SNR optimization Tool Alert function Targets oversampled on request in case a transit event is expected List of other oversampled objects (selected APs) SC 20th, Paris, 15 September 2006 50