Gyro motion boundedness under uncertain angular acceleration about vehicle output axis
Abstract
An analysis of the motion of a singleaxis rate gyroscope mounted in a space vehicle which has uncertain timevarying acceleration and deceleration about the output axis of the gyro is presented. Using a Liapunov function, a condition for boundedness of the gyro motion is derived. It is shown that by a proper selection of the parameters of the gyro, its motion can be forced to remain in a small neighborhood (called region of ultimate boundedness) of the origin in the thetaderivative of theta plane after a certain finite interval of time for any bounded uncertain timevarying acceleration and deceleration. Analytical relations for the selection of gyro parameters to keep the error caused in the measurement of the input rate due to angular acceleration and deceleration within desirable limits are derived.
 Publication:

IEEE Transactions on Aerospace Electronic Systems
 Pub Date:
 September 1982
 DOI:
 10.1109/TAES.1982.309275
 Bibcode:
 1982ITAES..18..630S
 Keywords:

 Angular Acceleration;
 Equations Of Motion;
 Gyroscopic Stability;
 Liapunov Functions;
 Spacecraft Motion;
 Spin Stabilization;
 Angular Velocity;
 Gimbals;
 Gyroscopes;
 Matrices (Mathematics);
 Spacecraft Instrumentation