Precision platform pointing controller for a dual-spin spacecraf

Boots – shoes – and leggings

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Details

364459, 244164, 244171, B64G 136

Patent

active

047528842

ABSTRACT:
A pointing apparatus for a dual-spin spacecraft utilizing a first sensor for sensing the time of arrival of an inertial attitude reference as the spinning portion of the spacecraft rotates, and a second sensor for sensing the time of arrival of an index reference which relates the position of the despun portion with the spinning portion. A digital processor estimates the spin rate and phase of the spinning portion from the inertial attitude reference time of arrival, estimates the relative spin rate and phase between the spinning portion and the despun portion from the index reference time of arrival, and estimates the bearing friction bias torque on the motor means which controls the pointing direction of the despun portion of the spacecraft. The spinning portion spin rate and phase estimates are added with the relative spin rate and phase estimates to produce an estimate of the despun portion spin rate and phase, and the despun portion spin rate and phase estimates and the friction bias torque estimates are subtracted from commanded despun portion spin rate, phase and friction bias torque states. A torque command is generated for controlling the motor means from the subtracted estimates.

REFERENCES:
patent: 3714434 (1973-01-01), Mears, Jr. et al.
patent: 3757336 (1973-09-01), Rosen
patent: 4161780 (1979-07-01), Rudolph et al.
patent: 4617634 (1986-10-01), Izumida et al.

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