A Case Study in NASA-DoD - The Black Vault

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1. Spacecraft configurations are based on descriptions provided
by Goddard Space Flight Center (GSFC) for the MMS, by TRW
for the STPSS, and by Boeing for the AEM and L-AEM.
2. Space Test Program payloads described in Current STT -2yloads ( 2 6 )
(the so-called "Bluebook") are considered representative of
those that would be flown during the period 1980-1990.
3. All spacecraft are compatible with the use of solid rockets
for orbit translation, which usually requires spin stabilization.
The AEM and STPSS are designed with that in mind.
The MMS normally uses a hydrazine propulsion module or the
Interim Upper Stage (IUS) for orbit translation in a threeaxis-stabilized
attitude, but according to GSFC it can also
be spin stabilized for orbit translation.
4. Space Test Program missions are intended to be flown as
secondary payloads, which implies that Space Test Program
payloads would rely on solid rocket kick stages
for
translation from the nominal shuttle parking orbit to the
desired mission orbit rather than on changing the shuttle
orbit altitude and inclination to meet the payload requirements.
5. Nominally, two Space Test Program flights per year are scheduled;
the minimum is one.
6. All payloads are launched using the space shuttle.
7. Servicing of payloads in orbit or retrieval of spacecraft
for reuse is not considered.
Space Shuttle Operations
As just mentioned, this study is restricted to consideration of the
space shuttle for the primary launch vehicle. As currently envisioned,
the space shuttle will have the capability of placing 65,000 lb of payload
into a 150 n ml earth orbit with an inclination of 28.5 deg when
operating out of the Eastern Test Range (ETR).
To place payloads in
*
Although the IUS uses solid rockets, its use by the Space Test
Program is considered a special case because of the high cost of that
design.