1 gaia system level technical reassessment study final presentation estec, april 23rd 2002 part 1b...

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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


Avionic bench


AstroVPU EM

Astro FPA EM



PhotometerVPU EM

PhotometerFPA EM



RVSFPA EM


RVSVPU EM

PDHEEM

FEEP EM&simul.


Star tracker PFMSun sensor simul.

MGAEM & simul.


SSMMEM


PDHEsimul.

Spacecraft avionic bench


PDHEEM


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


At ambiant


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



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


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


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

1 gaia system level technical reassessment study final presentation estec, april 23rd 2002 part 1b...

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