제어로봇시스템학회:학술대회논문집
- 1991.10a
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- Pages.395-400
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- 1991
Satellite Attitude Control Using Optimal Control Law
최적제어 기법을 이용한 위성의 자세제어
Abstract
In spinning satellite, a gyrotorquer generates a control torquer along two orthogonal axes normal to the spin axis of the vehicle. Matrix Fraction Description(MFD) are used to obtain minimal realization of the transfer matrix relating the attitude angles and the rate of rotation of the gimbals of gyrotorquer. In this paper, the Linear Quadratic Gaussian with Loop Transfer Recovery and H.meihodologies are used to design controller for spinning satellite.
Keywords