Method of damping nutation motion with minimum spin axis attitud

Details Method of damping nutation motion with minimum spin axis attitud Method of damping nutation motion with minimum spin axis attitud

1980-08-29

1983-06-07

Frankfort, Charles E.

Aeronautics and astronautics

Spacecraft

Attitude control

244170, B64G 126, B64G 138

Patent

active

043867502

ABSTRACT:
In a method of and apparatus for damping nutation of a spinning spacecraft (10), spin axis attitude disturbances are substantially reduced by controlling at least one nutation damping gas thruster (18) to fire with non-uniform gas pulses. During the beginning of a nutation control sequence, the duration of successive gas pulses is gradually increased (up pulsed) from zero to a predetermined maximum duration. The duration of successive pulses is then maintained constant for a time period. Finally, at the end of the nutation control sequence, the duration of successive gas pulses is gradually reduced to zero (down pulsed). Up pulsing of the gas thruster (18) is initiated in response to a predetermined maximum nutation angle measured by an accelerometer (20). Down pulsing of the thruster (18) is initiated in response to a predetermined minimum nutation angle. The number of variable and constant duration gas pulses delivered by the thruster (18) depends upon the mass distribution of the spacecraft (10).

REFERENCES:
patent: 3189299 (1965-06-01), Garner et al.
patent: 3643897 (1972-02-01), Johnson
patent: 3758051 (1973-09-01), Williams
patent: 3937423 (1976-02-01), Johansen
patent: 3944172 (1976-03-01), Becker
Clark, R. N. et al., "Scheme to Improve Limit Cycle Performance of an Attitude Control System", Journal of Spacecraft and Rockets, vol. 12, No. 4, Apr., 1974, pp. 253-254.

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