Spacecraft propulsion system thruster firing system

Details Spacecraft propulsion system thruster firing system Spacecraft propulsion system thruster firing system

1992-12-22

1993-10-12

Peters, Jr., Joseph F.

Aeronautics and astronautics

Spacecraft

With fuel system details

244169, B64G 126, B64G 140

Patent

active

052518558

ABSTRACT:
Thrusters in a propulsion system of a spacecraft spin stabilized by rotation about a spin axis are fired to increase the orbital velocity of the spacecraft in a maneuver direction along the orbital velocity vector. The propulsion system comprises a pair of thrusters juxtaposed on a common support at the periphery of the spacecraft. The thrusters have thrust axes perpendicular to the spin axis and offset relative to a transverse axis of the spacecraft by equal and opposite offset angles. Each thruster is fired separately and alternately when its thrust axis is substantially parallel to the maneuver direction while the spacecraft is rotating about its spin axis.

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Ninomiya, et al., "Attitude and Orbit Control System of the Japanese Halley's Comet Explorers `SAKIGAKE` and `SUISEI`", NEC--Research & Development, No. 83, Oct. 1986, pp. 82-91.

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