A Case Study in NASA-DoD - The Black Vault

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Orbit
Number
Description
1-S Sun-synchronous (98.4 deg inclination), 250 to 300 n mi
circular, sun-oriented [81
1-E Sun-synchronous, 250 to 300 n mi circular, earth-oriented [13]
2 Elliptical, 7000 x 200 n mi, polar [13]
3 Geosynchronous (19,372 n mi) circular, low inclination,
sun-oriented [4]
4 10,000 n mi circular, low inclination [2]
5 12 hr orbit, 21,000 x 900 n mi, 63.4 deg inclination [3]
6 Geosynchronous circular, low inclination, earth-oriented [1]
7 3200 x 150 n ml, 30 deg inclination [1]
8 180 n mi circular, polar [1]
Ti'e velocity increments required to place the spacecraft into the
above standard orbits are given in Table H-1. These AVs were used for
the selection and sizing of appropriate kick stages.
The payloads were also ordered according to the spacecraft capabilities
that are needed to accommodate the payload. In addition to
mission altitude and orientation, we also used payload weight, power,
data rate, stabilization requirements, and pointing accuracy as filters
for assigning spacecraft. These assignments are given in Tables H-2
to H-5 where the letters "x" or "y" indicate a compatibility between
spacecraft capability and payload requirements. The letter "y" in the
AEM spacecraft row applies when that spacecraft's maximum altitude
capability is assumed to be geosynchronous rather than its current limit
of 1000 n mi; this was one of the spacecraft design excursions that was
examined in the study.
PROGRAM OPTION DEVELOPMENT
On the basis of information provided by SAMSO, it appeared that
the Space Test Program would be orbiting approximately 114 payload packages
during the 1980-1990 time period. Since there were only 64 representative
payloads in the sample we had available to work with, it wab
Numbers in brackets are the number of the bluebook payloads
accommodated by the orbit.