Critical nutation dampling on spinning bodies via momentum wheels or similar devices
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United States of America Patent
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Aug 18, 1998
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N/A
app pub date -
Oct 25, 1995
filing date -
Oct 25, 1995
priority date (Note) -
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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.
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