SC 20th, Paris, 15 September 2006 1 Phases and timeline System architecture with support facilities...

SC 20th, Paris, 15 September 2006

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Phases and timelineSystem architecture with support facilitiesLEOP (Launch and Early Orbits Phase)MIP (Orbit raise) including beginning of life calibrationsFirst station acquisitionFirst observing run (technical)

Presentation of commissioning

For further information

Plan Général des Opérations COROTCOR-0-PL-2061-CNES Ed 1.1


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Orientation maneuverStraylight measurement (baffle efficiency)

4 days Launch + 15 days Technical Run Launch + 60 days IR 1

Satellite orientation

BOL calibration (cover closed, then opened)

Station acquisition phase

Payload periodic calibration

Solar Wings rotation

Cover opening(1st light)

Commissioning phase

BMP IFAR

LEOP

Mise à poste

CCC MIP

Gyro calibration

If late launchTechnical Run = IR1

Commissioning timeline


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Components

LEOP

Entités opérationnelles SSO Entités en support aux opérations

Réseau de Communication

Centre de Contrôle

Station Principale (ICONES)

Centre d’Orbitographie Opérationnelle

Stations 2 GHz TC/TM

Stations 2 GHz Localisation

Centre d’Opérations du Réseau

Salle de Contrôle Principale

Autorité de ConceptionEquipe projet COROTEquipe projet filière ProteusArchitecte Industriel Satellite

CNES

CNES

CNES

CNES

CNES

CNES

CNES

CNES

PGGS

Lanceur (Baïkonour)

DMS


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Commissioning

Entités opérationnelles laboratoires Entités opérationnelles SSO Entités en support aux opérations

Support permanent

Phases critiques de mission

Centre de Mission

Réseau de Communication

Centre de Contrôle

Station Principale (ICONES)

Station Secondaire (ALC)

Salle de Contrôle Principale

Centre InformatiqueAtelier Logiciel de Vol

Chaîne d’Expertise Etalonnages

Alerte Transits Planétaires

Autorité de ConceptionEquipe projet COROTEquipe projet filière ProteusArchitecte Industriel Satellite

CNES

CNES

INPE

CNES

CNES

CNES

CNESLESIA

LESIA

LAM

PGGS

Station de back-up (VGS) IFA

+ Interface N1 CDC-LAM

Components


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LEOP Phase Tried-and-trusted facilities

ICONES : TTCET KRN, TTCET AUSTC/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)

Use of ground stations


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Tests of communication (exchange of files) with INPE control center successful

Arrival of TTCET in packing cases on 23.08.2006

Alcantara (INPE)

Should be inserted smoothly in the operations during first observing run…


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All system tests completed

Radiofrequency compatibilty Ground communications (exchange of files) Tracking of Calipso (twice)

Vienna (IFA)


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Negative chronology

H0 - 10:20:00 : DMS COROT et LCM Starsem in bunkers

H0 - 10:10:00 : Communication checksEGSE 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 possibleIf abort by LV, LV is removed from the pad and refurbished

H0 : Lift-off

Ho

lds

au

tho

rize

dLaunch and launcher mission


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Annie OK Michel OK Thien OK

Launch and launcher mission


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Positive chronologyMission 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



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Launch time

Eclipse duration (slot 01/10/2006 to 31/10/2006)RAAN = 14.5° 15.7 minRAAN = 194.5° 36.5 min


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 October 11, 2006 November 01, 2006

14.5 01h 30m 19.0s 00h 07m 44.7s

October 10, 2006 October 31, 2006

194.5 13h 32m 16.5s 12h 09m 43.5s


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Launch and launcher mission(positive chronology)


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Separation and first orbits

Séparation

Launch and launcher mission(positive chronology)


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LEOP (D1)

7 min

Init and deployment sequenceTriggered by reconfiguration module (RM) after detection of separationBoot of on-board processor (PM) and driversOnce active, the on-board software executes the automatic sequence

for solar wing deployment (+Y, then -Y) Gyros ON for unfolding monitoring, then OFF

The CCC orders the spacecraft to switch from SAFE to REDUCEDcommand & control mode

2 h

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

MAG + CSS + MTB+ 2 RW


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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 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

High-rate TM emission (733 kbits) and GPS datation available

NOM AOCS and NOM CC


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Opening of the cover, in visibility Cover surveillance inhibition Release (heating of a shape memory alloy)

MIP (beginning of life)

Maneuvers (OCM2) to calibrate thrusters

Maneuvers (OCM4) for orbit corrections

Gyro calibration

Payload is set to ONChecks of temperaturesAuthorization of on-board FDIR algorithmsSelection of master clock (BS2)Thermal regulation set to ONBS2, ETN, BCC set to ON (in this order)After PBS boot, payload is ready to receive TC 1553

The satellite is ready for the first station acquisition phase

Beginning of life calibrations (cover closed)


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To keep a capacity inV toMake 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 orbitSemi-major axis: 896 kmeccentricity : frozen orbit Inclination, : stability of the orbit plane ( = 14.5 in J2000)

Orbit correction strategy


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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 YES

Eccentricty e -- 0.001271 0.002 0,001271 0,001 YES

Inclination i ° 90.0 ±0.1 90.0 ± 0.083 YES

RAAN (for the whole launch period)* ° 14,50 ±0.2 14,50 ± 0.12 YES

Argument of perigee ω ° 65,56 -- 65,59 ±30 /N A



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Correction of errors (1/2)

Semi-major axis Dispersions at 3 : 5 km No strong mission constraintMinimal 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



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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



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DispersionslanceurSOYUZ

Orbite visée àl'injection

Orbite pire cas àl'injection

Correction pire cas à réaliser V pir e cas Nombredema œn uvresOC 4M

Orbitefinal e pirecas(**)

3a anom anom-3a Transfer td e HOHMANNdeacollision

a nom +/- 3σa

5 km HOHMANN 1.5 km 0.8 m/s ( *) 13σe e=0 (Ex,ey) =(0, - 3σe) 3σe + e G

0.0 01 0.0 0225 0 m/s 03σ i inom inom - 3σ i 3σ i inom

0.0 83de g

0.0 5 deg 11 m/s 3

3σΩ Ωnom Ωnom - 3σΩ 3σΩ Ωnom +/- 3σΩ

0.1 2 deg 0 0 m/s 0TOTAL

11. 8 m/s 3

Fuel budget LEOP : roughly 12 m/s (worst case)



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4 times a year

Spacecraft orientation(coupled with housekeeping maneuvers if needed)

Transition - step by step - toward Observation mode

Programming of 1. Asteroseismology channels2. Exoplanet channels

Operations in Mission Center are twofoldScientific / Command and Control

The station acquisition phase

To start and feed Mission ACS Mode

Scenario over 7 days


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VEILLE

SAFEOFF

VALIDATIONECARTOMETRIE GROSSIERE

VALIDATIONECARTOMETRIE FINE

VALIDATION IMAGEEXOPLANETES

VALIDATION IMAGEASTERO

VALIDATIONPLAN DE MASQUES

OBSERVATION

Station Acquisition

CALIBRATIONPERIODIQUE

Modes dédiés auxCALIBRATIONSDEBUT DE VIE

Transition on TCTransition on TC with automatic returnOrder number in a nominal sequenceTransition on anomaly (automatic)Transition on PROTEUS configuration change

, , ...

Mode flower


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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

Alpha=101.72;delta=-0.2

Rot=7.28

Preliminary step

Spacecraft attitude maneuver for a new run

Tool

Corotsky


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Preliminary step

Spacecraft attitude maneuver for a new run


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VEILLE

SAFEOFF






OBSERVATION

Phase de Mise en station




, , ...

Preliminary step


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VEILLE

SAFEOFF






OBSERVATION





, , ...

Step 1


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Step 1

Astero channel Sky recognitionIdentification of starsInstrument geometric calibration

Tools

Findstars/Identstars

Extraction of stellar objects (with mv)Removal of offset, sky background, cosmics, electronic gain and smearingThreshold for thresholded imagesIdentification of targets (using Tycho catalog)Instantaneous line of sight

Full images

Tool

Alpage

Focal plane cartographyOptical distortion reestimate (polynomial)

2 x 3 images2 successive orbits

CCD A1

CCD A2


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PROTEUS platform

Star Tracker field of view Zs-


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ANTICENTER Autumn (close to J280)Zs- toward the Sun

Star Tracker unavailable over the night side of the Earth

Step 1

Ys+

Zs-

S

STR masked by the Earth


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ANTICENTER Spring (close to J94)Zs- not toward the Sun

Star Tracker unavailable over the day side of the Earth

Step 1

Ys+

Zs-

S

STR masked by the Earth

Better case


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Conventional orbital position PSOtrans

Instant of transition

STR masked by the Earth Including roll angle

PSOtrans

Favorable position all over the year


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VEILLE

SAFEOFF






OBSERVATION





, , ...

Step 2


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Step 2

Astero channel Line of sight calibrationDelta_quaternionAttitude correction maneuverAttitude correction maneuver

Tool

Identstars

Time series of seamark positions :- 64 couples of thresholded images / orbit- 50 seamarks by image (both CCD)- quality flagsInstantaneous line of sight

Tool

AlpageLine of sight orbital variationBias between payload and platform(on each axis) Delta_quaternion at PSOtrans

XV

YV

0E2

CCD A1 CCD E1

CCD E2CCD A2

0E1

0A1

0A2

+

Trajectory of seamarks(e.g over 3 orbits)

Expectedposition

+ +PSOtrans

x

y

Thresholded images

+


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VEILLE

SAFEOFF






OBSERVATION





, , ...

Step 2


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+

Step 2

Astero channel Line of sight calibrationLine of sight calibrationDelta_quaternionDelta_quaternionAttitude correction maneuver

Tool

Corotsky

Bias incorporated into Q_att

Tool

Findstars/Identstars

Line of sight control Extraction of additional stellar objects(if necessary)

CCD A1

CCD A2

++

PSOtrans

Expectedposition

Full images

1 image

Once correction maneuver completed : 15 arcsec (3)

360 arcsec (3)


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Validated during system testsBlind static test with thresholded images produced by instrument

test bench (with video simulator)

Q_att step2 G2

Identstars/Alpage/DeltachoiceBias : psi = 0.001813

theta = -0.097946phi = -0.017328

Recorded in BDE

Q_att step0 G2

Sign and amplitude are correctError < 4 arcsecIncluding max error Alpage < 1 arcsec

CorotskyLine of sight (target) :Alpha = 101.6Delta = -0.23Roll = 0.0

CorotskyLine of sight (corrected) :Alpha = 101.698Delta = -0.247Roll = 0.0

Threshold images (N0)Line of sight (simulated) :Alpha = 101.502Delta = -0.213Roll = 0.0

Bias computation


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Step 3

Astero channel Upload of windowingStart of rough ecartometryStart of rough ecartometryACS in open loop controlACS in open loop control

Tools

Sismowind/Sismoparam

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 A1

CCD A2

Large window

Small window

Dark window


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VEILLE

SAFEOFF






OBSERVATION





, , ...

Step 3


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Step 3

Astero channel

CCD A1

CCD A2

Once rough ecartometry is running :

DPU 1/2 selected as nominal inputACS estimator ONOrbital behavior analysis (4/6 orbits)

Large window

Upload of windowingUpload of windowingStart of rough ecartometryACS in open loop control

PROTEUS MI-BO mode

VEG mode


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Step 4

Astero channel ACS in closed-loop controlSwitch to scientific windowsSwitch to scientific windows

Start of fine ecartometryStart of fine ecartometry CCD A1

CCD A2

Large window

VEG modeSwitch to ACS Mission mode when flyingover the PSOtrans

Orbital behavior analysis (1 orbit)

PROTEUS MI-BF mode


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VEILLE

SAFEOFF






OBSERVATION





, , ...

Step 4


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Step 4

Astero channel ACS in closed-loop controlACS in closed-loop controlSwitch to scientific windows

Start of fine ecartometry CCD A1

CCD A2

Small window

Dark window

Switch from PMG to PMSSpacecraft attitude definitely driven by instrument guide starsOrbital behavior analysis (2 orbit)

PROTEUS MI-BF mode

VEF mode

Guide stars


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VEILLE

SAFEOFF






OBSERVATION





, , ...

Step 5


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Step 5

Exo channel Sky recognitionIdentification of bright starsInstrument geometric calibrationIdentification of all starsTool

ExowindRemoval of offset, sky background, cosmics, electronic gain, smearing and EMC patternsIdentification of saturating starsSelection of bright objects for calibrationFocal plane cartographyOptical 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

Full images64-exposure128-exposure

3+1 accumulations4 successive orbits

CCD E1

CCD E2


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VEILLE

SAFEOFF






OBSERVATION





, , ...

Step 6


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Step 6

Exo channel Upload of windowingValidation (subset of objects)

Tool

Exowind

Tool

VPM process

Subset of 500 windows/CCDGeometric/SNR control

Automatic process to assign a maskto each Exobasket stellar objectPSF fitting/SNR optimization

Generation of telecommand parameters- Extraction unit and DPU (TC 1553)Checks on EM test bench before uploading

mv=12 - 85 px mv=12 - 125 px

mv=15 - 65 px mv=15 - 55 px

Alternate methodunder implementation

256 templates / CCD


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VEILLE

SAFEOFF






OBSERVATION





, , ...

Step 7


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Step 7

Both channels Start of scientific processes

Tool

Sismomask

Upload of optimized photometric masks PSF fitting/SNR optimization

Start of all scientific software processesTelemetry production : light curves, seismologymask images and exoplanet imagettes

Tool

Alert functionTargets oversampled on request in casea transit event is expectedList of other oversampled objects (selected APs)

SC 20th, Paris, 15 September 2006 1 Phases and timeline System architecture with support facilities...

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