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1
GAIA System Level Technical Reassessment Study
Final PresentationESTEC, April 23rd 2002
Part 1b
Development & AIV
Contents
1- AIV approach
2- Schedule
3- Costing approach
•PLM Model philosophy–PLM SM (structural model), with flight structure, dummy units and blank mirrors.
Used for mechanical qualification at satellite level, including alignment stability verification.
The thermal validation is proposed at PFM level.
–PLM EO-EM (electro-optical engineering model), with EM CCD & video electronics chains. Used to validate data acquisition and processing.
–PLM PFM, all flight hardware, for full proto-flight qualification at module / satellite levels.
•SVM Model philosophy–SVM SM, with flight structure and propulsion, SM units and solar array, dummy sunshade. Used for mechanical qualification at satellite level.
–SVM AVM, (Avionics Model), consisting in a « flat » assembly of EM or FM electrical units. Used for avionics & software validation.
–SVM PFM, all flight hardware, for full proto-flight qualification at module / satellite levels.
Satellite Model Philosophy (1/2)
Satellite Model Philosophy (2/2)
•Satellite Model Philosophy: three models
–SM model, made of the assembly of PLM-SM and SVM-SM.Used for satellite-level mechanical qualification.
–AVM model, made of the SVM AVM complemented by the EM payload data handling electronics (PDHE) having direct interfaces with the SVM.
Used for satellite-level avionics validation (mainly: payload interfaces, AOCS closed loop).
–PFM model, made of the assembly of PLM-PFM and SVM-PFM.Used for satellite-level full proto-flight qualification, and
ground segment interface system test.
SADummy
A.I. A.I.SVMPFM structure
SMUnits
Mechan.Testing
• Static load (qualif.)
Mechan.Testing
• Fit check• Shock test
A.I.PLM
PFM structure
Dummies &Mirror Blanks
Mechan.Testing
• Static load (qualif.)
A.I.
A.I.
PLM-SM
Mechan.Testing
• Acoustic test• Sine vibration qual test• µ setting
SVM-SM
Propulsiondummies
• Metrology
PLM thermal
tent
A.I. Refurbishment & PFM activities
SunshieldDummy
A.I.
SMUnits
SM Spacecraft
AIV flow : SM validation
CDMU EM PCDU EM
SVM avionic bench
PLM-EM
• Elec. reference tests• Software tests
Function.& Perfo.Testing
Function.& Perfo.Testing
Avionic bench
Function.& Perfo.Testing
AstroVPU EM
Astro FPA EM
Function.& Perfo.Testing
Function.& Perfo.Testing
PhotometerVPU EM
PhotometerFPA EM
Function.& Perfo.Testing
Function.& Perfo.Testing
RVSFPA EM
Function.& Perfo.Testing
RVSVPU EM
PDHEEM
FEEP EM&simul.
Function.& Perfo.Testing
Star tracker PFMSun sensor simul.
MGAEM & simul.
Function.& Perfo.Testing
SSMMEM
Function.& Perfo.Testing
PDHEsimul.
Spacecraft avionic bench
Function.& Perfo.Testing
PDHEEM
Function.& Perfo.Testing
AIV flow : Avionic bench
A.I. Refurbshmt
Refurbshmt
SVM structure
PLM structure
A.I.A.I.
PFMunits
At ambiant• SVM Software tests
A.I.
PFMOptics
Function.& Perfo.Testing
At ambiant
Function.& Perfo.Testing
Perfo in vacuum• thermal vacuum• thermal balance• thermoelastic behaviour
Mechan.Proto-Qualif
EMCTest
A.I.
PFM FPAs& Elec. units
At ambiant
PFM Spacecraft
ThermalAcceptance
• Reference measurt• Thermal balance
SVM + SL• Thermal vacuum
SVM• Control measurt
• Reference measurt• Acoustic test• Sine vibr. Test• Fit-check• Control measurt
• Conducted• Radiated
Function.& Compat.
Test
RF &Gnd Segt
Compatib.Test
SVM-PFM
PLM-PFM
• Reference measurt• Software tests
Function.& Perfo.Testing
Function.& Perfo.Testing
A.I.
Sunshield PFM
Deploymenttest
• Pyro test• SS deployment testt
SL-SM
• RF tests• Final software tests• SL//ground segment tests
SA PFM
PropulsionPFM
A.I.
AIV flow : PFM validation
1- AIV approach
2- Schedule
3- Costing approach
Contents
ID Task Name
1 Technology Developments2 Payload Technology
3 Ground Verification
4 P/L Data Hand. Electr.
5 Optimum Compression Algorithm
6 CCD
7 CCD Validation Activity (Completed)
8 CCD & FPA Techno. Demonstrators
9 Optics
10 - High Stability Optical Benches
11 - Payload Mirrors
12 - Payload Structure
13 Active Pointing Control
14 - Laser Metrology & Active Optics
15 - Inch-worm mechanism
16 Data Base Architecture (on-going activity)
17 Spacecraft Technology
18 - mN Feep Qualification
19 - Large Size Deployable Solar Array
20 Phased Array Antenna
21 GAIA System Level Techn. Reassess. Study
22 GAIA Definition Phase 23 Competitive Definition Phase 24 Tech. Consultancy Phase #125 Tech. Consultancy Phase #226 Definition Phase #127 Definition Phase #228 Implementation Contractor Selection 29 Implementation Phases30 Phase B231 Phase C/D32 Launch Campaign33 Launch 28-0
H2 H1 H2 H1 H2 H1 H2 H1 H2 H1 H2 H1 H2 H1 H2 H1 H2 H1 H2 H1 H2 H1 H2 H199 2000 2001 2002 2003 2004 2005 2006 2007 2008 2009 2010 20
Gaia Programme Overall Schedule
t 0 3 6 9 12 15 18 21 24 27 30 33 36 39 42 45 48 51 54 57
Phase B
Reviews PDR System CDR Units CDR System58
Phase C/D
SVM PFM structure devt (24) AIT (2)SM
campaignPLM PFM Torus & structures devt (26,5) AIT (2,5)
SL AIT (2)
SVM EM avionics & PFM batch 1 (18) SVM AIT (15) SL AIT (2) on SVM AVMEM Software update & maintenance
FPA EM devt (13) FPA EM AIT (6-9)campaign
PLM EM electronics (18-21) E-O AIT (6) EM PLM (6)
Mech., therm. & RCS integration
PFM SVM PFM Units (batch 2) SVM AIT (10)
campaign FPA PFM devt (21) FPA PFM AIT (12)Spares
PLM PFM electronics (18-24) AIT (7)
Optics design (9) Optics MFG (24) PLM AIT (16-18)
SL AIT (9)
task (duration in months)
margin
dummies & SM
blanks & dummies
SVM delivery
PLM delivery
SL delivery
Satellite schedule
•Critical paths are:
–FPA & electronics EM – FPA & electronics FM – PLM PFM AIT – SL PFM AIT where detectors, but also electronics planning must be carefully managed.
=> Electronics shall predeveloped by technology programmes
–PLM PFM optics – PLM PFM AIT – SL PFM AIT
–PVM (& SLM) structures – SM SL tests – PLM PFM AIT - SL PFM AIT
as SVM shall not be on the critical path of the payload, we have chosen to postpone the AIT of RCS PFM after the SM SL tests.
•The total development lasts 58 months, up to satellite delivery.
Schedule analysis
Contents
1- AIV approach
2- Schedule
3- Costing approach
G A IA S a te llite P ro d u ct T ree
C entra l T ubeS hear W a llsU pper F loorA n tenna Base P la teS ide W a llsS treng thners & M isc.
S V M S truc tu re
C entra l D ata M g t U n itS o l id Sta te M ass M em ory
C D M S U n its
M LI (excep t sunsh ie ld)H ea ters & Therm is to rsP a in ts & M isc.
S V M T herm a l H ardw are
X B dT ransponderR F D istr ibu t ion U n itX B d LG As
A ct ive A n tenna E lec.M G A a rray
X B d ac t ive M G A
T T &C
P ower C on tro l & D is tr . U n itS o la r A rrayB a tte ry
P ow er C on trol S ys tem
S ta r T rackerS un A cqu is it ion S ensorsA tt i tude A nom aly D etec torG yrom eter
A tt i tude & O rb it C on trol S ys tem
N 2H 4 T hrus terT ankF low C on trolP ip ing & B racke ts
C hem ica l P ropu ls ion FE E P C lus ter
S V M H arness S V M S o ftw are
S V M E G S ES V M M G S E
S V M G S E
S erv ice M odu le (S V M )
S truc tu reM echan ism sS h ie ld
S unsh ie ld
T en t S truc tu reM LI S hee tsC overs & T herm a l B a ff lesA ctua to rs & P yros
O ptica l & T herm a l Tent
P ay load D ata H and ling E lectron icsP LM S o ftw are
P ay load D a ta M anagem ent
P LM H arness
T orus Struc tu reB ipodsT herm al H WS tray ligh t Ba ff les
P LM O ptica l B ench
M irro rsM irror M oun ts
A stro T elescopes
A lignm en t M echan ism sB as ic Ang le M on ito r ingW ave fron t S ensor
M on ito r ing & C on trol
M ir ro rsM irror M oun ts
S pec troT e lescope
T e lescope A ssem b ly
C C D a rraysO ptical F il te rsF ron t End E lec tron icsS truc ture & Therm al
A stro F oca l P lane
A stro Video Process . U n it
A s trom etr ic D e tec t ion A ssem b ly
O p tics & G ra t ingS truc ture & Therm al
R V S S pectrom e ter
C C D a rraysO ptical F il te rsF ron t End E lec tron icsS truc ture & Therm al
R V S F oca l P lane
R V S Video Process . U n it
R V S D e tec t ion A ssem b ly
C C D a rraysO ptical F il te rsF ron t End E lec tron icsS truc ture & Therm al
P ho tom ete r Foca l P lane
P ho tom ete r Video Process . U n it
P ho tom ete r D e tec tion A ssem b ly
O p tica l B ench Assem b ly
P LM E G S EP LM M G SEP LM O G SE
P LM G S E
P ay load M odu le (P LM )
S a te l l i te E G SES ate ll i te M G SE
S atel l i te G SE
G A IA S ate l l i te
Product Tree
M a na ge m e nt0 0 00 0 0-A A
P ro du c t A ssura n ce0 0 00 0 0-A B
a ) E n g . S yn th e s isb ) P erfo rm a n ce & V e rif ica tio n E n g .b ) M iss io n E n g . & O p e ra tio nsc ) M e ch a n ica l & Th e rm a l E n g .d ) E lec trica l E n g .e ) D a ta H a n d lin g & C o m m . E n g .f) D yna m ics E n g .
E n g in e erin g & D e ve lo p m e nt0 0 00 0 0-A C
a ) In du s tria l s yn th e s isb ) S V M p ro cu rem e ntc ) P arts m a na g em e nt & E n g .
In d u stria l D e ve lo pm e nt0 0 00 0 0-A D
S L P ro je c t O ff iceP rim e
00 00 00 -A
a ) S L A IT co ord ina tion & E n g.b ) S M S L A ITc ) A V M A ITd ) P F M S L A ITe ) S p ec if ic S L G S Ef) S L T e s t fac ilit ies
S L A IT & G S E0 0 00 00 -B
S L A IT & G S EP rim e
00 00 00 -B
a ) P L M M a n ag e m e ntb ) P LM P Ac ) P L M E n g . S yn th e s isd ) P L M M e ch a n ica l & Th e rm a l E n g .e ) P L M E le ctrica l & D e te c tio n E n g .f) P LM O ptica l E n g .g ) P LM Ind u stria l d e vp t. & p ro cu re m e nt
P L M P ro je c t O ff ice1 0 00 00 -A
a ) P L M A IT C o rd in a tionb ) S M P L M A ITc ) E O M P L M A ITd ) P F M P L M A ITe ) P L M G S Ef) P L M T es t F a c ilit ies
P L M A IT & G S E1 0 00 00 -B
1 1 00 0 0 - O p tica l B e n ch(s tru c t., th e rm . & s tra ylig h t ba ff le s)1 2 0 00 0 - M e can ism s(a lig n t, B A m o n ito rin g , W F sen so r)1 3 00 0 0 - A s tro te lescop es1 4 00 0 0 - S p ec tro te le sco pe
A s tro F o ca l P la ne A sse m b lyA s tro V id e o P ro ce ss ing U n it
1 5 00 0 0 - A s tro de te ction
R V S sp e c trom e te r (o p tics & g ra tin g )R V S F P AR V S V P U
1 6 00 0 0 - R V S de tec tion
P h o to m e te r F P AP h oto m e te r V P U
1 7 00 0 0 - P h o to m e te r d e te ction
1 7 00 0 0 - O p t.& the rm a l Te n t1 8 00 0 0 - P L M h a rne ss1 9 0 00 0 - P aylo ad D a ta H a nd ling & S o ftw a re
P L M P ro d u c ts
P L MP rim e
10 00 00
a ) S V M M a na g e m e ntb ) S V M P rod u c t A ssura n cec ) S V M E n g. S yn the s is & V e rif ica tione ) S V M E le c trica l E n g .d ) S V M M e ch a n ica l & Th e rm a l E n g .f) S V M D a ta H a n d lin g E n g.g ) S V M A O C S & P ro pu ls io n E n g .h ) S V M C o m m u n ica tio n E n g .i) S V M Ind u s tria l d evp t & p rocu rem e nt
S V M P ro je ct O ff ice2 0 00 00 -A
a ) S V M A IT C o o rd in a tionb ) S M S V M A ITc ) A V M A v ion ic va lid a tiond ) P F M S V M A ITe ) S V M G S E
S V M A IT & G S E2 0 00 00 -B
S tru c tu re & Th e rm a l2 10 000P o w e r & H a rn e ss2 20 000A O C S & P rop u ls ion2 30 000D a ta H a nd lin g & S W2 40 000T T C & C o m m2 50 000
S V M P ro d u c ts
S V MS u b co n tra c to r
20 00 00
S u n sh ie ldS u b co n tra c to r
30 00 00
G A IA SLO p tio n 1
P rim e
Work Breakdown Structure
•2 options are considered :–Option 1 : Astrium as Spacecraft Prime, SL AIV and PLM Contractor
SVM is sub-contracted
–Option 2 : Astrium as Spacecraft Prime and PLM Contractor,
SVM is sub-contractedSatellite AIV is sub-contracted
Reference Industrial Organisation
•First objective = use of Soyuz instead of Ariane 5–Present status indicates that this is OK, at (almost) no penalty for the astrometric performance; Spectro performance improved.–Launch mass is compatible with a Soyuz ST 2-1A from Baikonour (growth potential).
•Second objective = reduce satellite cost–Overall satellite design (especially the payload) has been made simpler, more robust and safer for science goals achievement (see next view-graph)–SVM should benefit from a good reusability of a Planck-type platform, for which the time-lag is adequate (Planck is only 3 years ahead of Gaia).
•Further activities during the end of the study will aim at consolidating this encouraging status.
Conclusion at Final Presentation