Spacecraft attitude control with avoidance constraint

Details Spacecraft attitude control with avoidance constraint Spacecraft attitude control with avoidance constraint

1989-09-27

1992-03-03

Peters, Jr., Joseph F.

Aeronautics and astronautics

Spacecraft

Attitude control

244171, B64G 124, B64G 136

Patent

active

050925431

ABSTRACT:
The attitude of a space vehicle is controlled to direct an instrument in a particular direction. For certain maneuvers, the reorientation may temporarily result in an undesirable orientation of the spacecraft. For example, the instrument may be a telescope which, during slewing of the spacecaft from one direction in space to another, may pass through an attitude in which it is directed toward the Sun. A control system is provided which performs the attitude control with an avoidance constraint. The control system generates a first signal representative of the current and desired final orientations, and slews the attitude in response thereto. A second signal is also generated which represents the difference between the current orientation of a vector associated with the spacecraft and a vector in space which it is to avoid. A threshold signal is generated when the difference between the avoidance vectors is a particular value. When the threshold value is reached, the control system slews in response to a combination of the first and second signals.

REFERENCES:
patent: 3219826 (1965-11-01), Letaw, Jr.
patent: 3427453 (1969-02-01), Gill et al.
patent: 3490719 (1970-01-01), Cantor et al.
patent: 4642648 (1987-02-01), Hulland et al.
patent: 4687161 (1987-08-01), Plescia et al.
patent: 4997146 (1991-03-01), Weyandt, Jr.
Tuns NTR Evaluation Form-Detail Report; T22A dated May 2, 1990.

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