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0<br />

8-4<br />

specific tools for each main arcas of cngincering<br />

design arc shown. They can be concurredy call<br />

on demand by the different experts working in<br />

parallel for trade off or validation on diflcrent<br />

fields : clcctrical, thermal, mechanical , orbit<br />

environment, attitudc and orbit contrbl,<br />

dynamic , propulsion, payload accomodatidn,<br />

mission; satellite programmation, ctc ...<br />

i<br />

Presently, SYSTEMA is uscd primarily in thc<br />

first part of the developmcnt process (fig 4).<br />

from phase A proposals, mission and s.\tclli!c<br />

layout tradc-offs to the end of ph?, * L with<br />

dctailcd satellite design optimisation . VI' up to<br />

proposals for a phase C activity. I<br />

If additional risks causcd by eventual flaws rjr<br />

bugs in numerical simulations arc acccptcd -<br />

these risks arc assumed to bc affordable far<br />

small tactical satellites with not vcly<br />

sophisticatcd missions -, phase C validation tjy<br />

mcans of such concurrcnt engiiieering only tools<br />

would saw not only thc major portion of the<br />

environmcntal tcsts costs (thcrmal, kacuum. suh,<br />

vibrations) but also would rcducc thc schcdulc<br />

induced costs.<br />

Such an approach has dcmonstratcd its<br />

cfficicncy through thc SSOT prograinmc (fig 5).<br />

S80T is a microsatellite launchcd this sunimcr<br />

as a conipanion of TOPEX - POSEIDON<br />

SPACFCRAR on ARIANE. SSOT has<br />

bcncfitcd from an intcnsivc use of SYSTEMA<br />

from thc first stage of dcsign to the dclivcry ;it<br />

the launch sitc. A programme conducted in a<br />

very short timc for a very competitive cost.<br />

I CONCLUSION 1<br />

The approch prcscnted above is far from a<br />

rcvolution. It is only an evolution.<br />

To be efficient suck concurrcnt engineering<br />

tools need to be validatcd and calibrated by<br />

refcrcncc to the data gathered during previous<br />

dcvclopmenl tcsts or during in orbit monitoring<br />

of opcrational spacccrarts. In that sense such an<br />

approach capitaliscs the whole cxpcrience<br />

acquircd by MATRA MARCONI SPACE<br />

through prcvious or currcnt low earth orbit<br />

programmes : SPOT 1,2,3 - ERS 1 and 2,<br />

HELIOS - SPOT 4 and Polar Platform.<br />

The SYSTEM\ usc built-in flexibility givcs thc<br />

opportunity to quickly update a current design<br />

and thus allows to follow cvolutions of<br />

technologics or accomodatc a newly availablc<br />

equipmcnt.<br />

SYSTEMA ;~llows a short rcaction timc and a<br />

quick acconiodntion on the satcllitc as soon as<br />

cmcrging rcquircmcnts arc formulated by the<br />

uscrs.<br />

~ll~iisimiiotts<br />

Jw rhis Seciion appear immediaiely<br />

afim ilte Fmrc~lt mnshiion.)<br />

i.

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