Critical nutation dampling on spinning bodies via momentum wheel

Details Critical nutation dampling on spinning bodies via momentum wheel Critical nutation dampling on spinning bodies via momentum wheel

1995-10-25

1998-08-18

Grant, William

Aeronautics and astronautics

Spacecraft

Attitude control

244170, 244171, B64G 128, B64G 138

Patent

active

057948925

ABSTRACT:
A method and system of damping nutation of a spacecraft (20) having a desired spin axis along a first principal inertia axis utilizes a momentum source (28) oriented along a second principal inertia axis perpendicular to the first principal inertia axis. An angular rate of the spacecraft (20) is sensed along an axis transverse to both the first principal inertia axis and the second principal inertia axis. An angular rate signal representative of the angular rate is generated. The angular rate signal is processed to form a control signal representative of a desired torque to drive the momentum source. The desired torque has a first additive component proportional to a derivative of the angular rate to critically damp the nutation under an at least second order model of the spacecraft (20). The momentum source (28) is driven in dependence upon the control signal. Preferably, the desired torque has a second additive component proportional to a momentum stored in the momentum source (28) to inhibit a conversion of the nutation into a tilt of the desired spin axis.

REFERENCES:
patent: 3591108 (1971-07-01), Perkel et al.
patent: 4193570 (1980-03-01), Hoffman et al.
patent: 4858858 (1989-08-01), Bruederle
patent: 5012992 (1991-05-01), Salvatore
patent: 5269483 (1993-12-01), Flament

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