Dynamic bias for orbital yaw steering

Details Dynamic bias for orbital yaw steering Dynamic bias for orbital yaw steering

1996-01-12

1998-08-11

Grant, William

Aeronautics and astronautics

Spacecraft

Attitude control

244171, 364454, 364459, B64G 128, B64G 136, B64G 138

Patent

active

057915989

ABSTRACT:
A method and apparatus for steering a low-earth-orbit communication satellite requiring sun-orientation for solar-power accumulation is disclosed. Momentum-bias both maintains nadir pointing and adds yaw-steering moments for sun-trackig attitude control, simultaneously. The method has two principal steps: 1) open-loop momentum decoupling, for correcting the calculated steering torque, and closed-loop attitude compensation, to correct for perturbations about the calculated attitude in accordance with one of two control law definitions. This combines the advantage of stable gyroscopic attitude control with those of open-loop yaw steering.

REFERENCES:
patent: 4071211 (1978-01-01), Muhlfelder et al.
patent: 4294420 (1981-10-01), Broquet
patent: 5184790 (1993-02-01), Fowell
patent: 5205518 (1993-04-01), Stetson, Jr.
patent: 5308024 (1994-05-01), Stetson, Jr.
patent: 5452869 (1995-09-01), Basuthakur et al.
H.J. Dougherty et al., "Analysis and Design of Whecon -An Attitude Control Concept", AIAA 2.sup.nd Communications Satellite Systems Conference, Apr. 8-10, 1968, No. 68-461, pp. 1-10.
R. Weiss et al., "Seasat-A Attitude Control System", J. Guidance and Control, vol. 1, No. 1, pp. 6-13.

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