Payload deployment from shuttle with linear and angular velocity

Details Payload deployment from shuttle with linear and angular velocity Payload deployment from shuttle with linear and angular velocity

1980-02-28

1982-11-16

Barefoot, Galen L.

Aeronautics and astronautics

Spacecraft

Spacecraft formation, orbit, or interplanetary path

244137R, B64G 164

Patent

active

043592015

ABSTRACT:
A payload such as a spacecraft is deployed from launch vehicle with linear and angular velocity, using a structural arrangement for applying a tangential, single point ejection force to the spacecraft, in which, the single point ejection force and the spacecraft/launch vehicle reaction points enclose the spacecraft center of mass and center of percussion.

REFERENCES:
patent: 3380687 (1968-04-01), Wrench et al.
patent: 3815849 (1974-06-01), Meston
patent: 4082240 (1978-04-01), Heathman et al.
patent: 4213586 (1980-07-01), Sengstock et al.
SCG 66710V/Dec. 1976, "Syncom IV-Space Shuttle Orbital Flight Mission", Public Ser. Satellite Consortium Conference, Wash. D.C., Jan. 1977.
SCG 66626V/"StS Optimized Spin Stabilized Satellite for Experimental Services", 10/18/76, Hughes Aircraft.
Wheelon, "The Impact of Space Shuttle on the Future of Communication Sat.", 11/9/78.

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