A Case Study in NASA-DoD - The Black Vault

-184-
Appendix I
L-AEM SPECIFICATIONS
STATEMENT OF WORK FOR A SHUTTLE LAUNCHED ADAPTATION
OF THE AEM FOR LARGE DIAMETER PAYLOADS THAT
RESULTED IN THE L-AEM DESIGN
5.0 CONTRACTOR TASKS
4
5.1 BASELINE DEFINITION
The Contractor shall design a baseline adaptation of the AEM base module
for comparison with other vehicles by the Contractor. The baseline
design shall be consistent with the following requirements:
0 The payload interface shall be hexagonal 60 in. in maximum
diameter.
* The spacecraft shall be three-axis stabilized with control
capability to 0.5 deg in pitch and roll and 1 deg in yaw,
with capability to be modified to control to 6 arc minutes
or spin stabilized with control capability to ±1 deg.
0 Solid propulsion shall be provided to inject the spacecraft
into a circular orbit at altitudes up to geosynchronous altitude
(orbiter altitude 150 n mi).
0 A SGLS-compatible telemetry, timing, and control shall be
provided using Carrier I with capability to also incorporate
Carrier II for transmitting payload data at high data rates.
• Provision shall be made for payload weights up to 1000 lb.
• The power system array shall be one-axis with setable angle
with 100 sq ft of array area. Two 20 Ahr batteries will be
provided.
* The thermal system shall use louvers and heaters with a maximum
power input from a payload of 10 W (insulated).
0 No single-string failure modes.
5.2 SHUTTLE INTERFACE
5.2.1 The shuttle interface shall be defined including an adapter
to support one or more spacecraft with payloads in the shuttle
over the short or long spacelab tunnel or over Orbital Maneuvering
System kit.
5.2.2 IUS interface shall be defined.
5.2.3 Mixed DoD payloads shall be considered.