Method for acquiring three-axis earth pointing attitude for an i

Details Method for acquiring three-axis earth pointing attitude for an i Method for acquiring three-axis earth pointing attitude for an i

1990-01-12

1991-06-04

Peters, Jr., Joseph F.

Aeronautics and astronautics

Spacecraft

Attitude control

B64G 124

Patent

active

050207440

ABSTRACT:
A method for making a transition between a spin-stabilized spacecraft operating mode and a 3-axis stabilized mode includes the step of determining the orientation of the spin axis. A reference object detector such as a sun sensor produces a pulse as it crosses the reference, thereby completely specifying the attitude of the spinning spacecraft at that instant. Angular rate information is used to update the attitude information while a feedback system controls torques for slowing the spin and for assuming the desired attitude.

REFERENCES:
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patent: 4161780 (1979-07-01), Rudolph et al.
patent: 4617634 (1986-10-01), Izumida et al.
patent: 4725024 (1988-02-01), Vorlicek
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"An Attitude Acquisition System for Communication Spacecraft Using Spinning Initialization of Inertial Parameters SIIP", by M. Schwarzschild, Aug. 14, 1989, AIAA Guidance, Navigating and Control Conference, Boston, Mass.
Search of prior art using NERAC in four parts, each of which is a list of titles with abstracts.
"A Fast Attitude Recovery System for Communications Satellites: Experience of Eutelsat 5", by Van Holtz et al., published in relation to the 12th Annual AAS Guidance and Control Conference, Feb. 4-8, 1989.

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