A Case Study in NASA-DoD - The Black Vault
A Case Study in NASA-DoD - The Black Vault
A Case Study in NASA-DoD - The Black Vault
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sunlight. <strong>The</strong>se surfaces <strong>in</strong>clude the backside of the solar array, the<br />
louver radiator surface (AEM), the thermal control trim radiator, the<br />
shunt dissipater panel, solar array and antenna appendages, and the<br />
S-band antenna.<br />
Radiators for dissipat<strong>in</strong>g heat generated <strong>in</strong>side the spacecraft<br />
are used on both the AEM and the STPSS. In the case of the STPSS<br />
(which has no louvers) the control of component temperatures with<strong>in</strong><br />
the spacecraft is achieved with a comb<strong>in</strong>ation of radiators, second<br />
surface mirrors, and thermostatically controlled heaters. On the AEM,<br />
component temperature control is achieved with louvers and thermalcontrol<br />
trim radiators. <strong>The</strong> basel<strong>in</strong>e design radiator for the AEM<br />
spacecraft radiator is sized to satisfy the HCMM mission requirements<br />
and is pa<strong>in</strong>ted white. <strong>The</strong> radiator's properties can be adjusted by<br />
pa<strong>in</strong>t stripes to atta<strong>in</strong> the desired trim.<br />
S<strong>in</strong>ce most of the elements of the AEM thermal control subsystem<br />
have been flight-proven on previously designed Boe<strong>in</strong>g spacecraft, they<br />
should be considered at least state of the art if not off-the-shelf.<br />
<strong>The</strong> same holds true for the TRW-proposed STPSS design.<br />
COMPARATIVE EVALUATION OF THE STPSS AND MMS SPACECRAFT<br />
To date, contracts have not been awarded for the design, development,<br />
or production of either the MMS or the STPSS. Consequently, the<br />
<strong>in</strong>formation available for mak<strong>in</strong>g a comparative evaluation of the MMS<br />
and STPSS is less detailed than for the AEM-STPSS evaluation. However,<br />
based on the <strong>in</strong>formation from GSFC, Aerospace Corporation, and TRW,<br />
thermal control subsystem concepts are sufficiently well def<strong>in</strong>ed that<br />
a reasonable comparative technical evaluation can be made.<br />
<strong>The</strong> same two differences between the AEM and STPSS are <strong>in</strong>dicated<br />
for the STPSS and MMS (Table G-1). <strong>The</strong> MMS spacecraft uses two louvers<br />
on each of three modules: power module, ACS module, and the C&DH module.<br />
As previously stated, the STPSS relies on radiators, second surface<br />
mirrors, and thermostatically controlled heaters for ma<strong>in</strong>ta<strong>in</strong><strong>in</strong>g the<br />
spacecraft structure and components with<strong>in</strong> specified temperature limits.<br />
Louvers are generally considered to be more expensive than heaters.<br />
However, personal contact with a thermal control system eng<strong>in</strong>eer at