바이어스 모멘텀 위성체의 롤/요 자세제어기 설계 : Open-Loop 방법Roll/Yaw Feedback Control Law Design for a Pitch Bias Momentum Spacecraft : Open-Loop Approach

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An open-loop oont개l technique for the roll/yaw attitude control of a pitch bias momentum spacecraft is presented in this paper. The control law is based upon the gyroscopic roll/yaw dynamics, which is due to a pitch bias momentum wheel. It is assumed that spacecraft bo요-fixed thrusters are used to produce control torques. The control law design consists of two separate stages. In the first stage, the initial nutational motion is stabilized while pointing maneuver is achieved during the second stage of control action. Thruster magnitude limitation is also taken into account which results in a series of impulsive inputs. The new control law is open-loop type and eagy to implement.
Publisher
한국항공우주학회
Issue Date
1997-08
Language
Korean
Citation

한국항공우주학회지, v.25, no.4, pp.123 - 132

URI
http://hdl.handle.net/10203/76203
Appears in Collection
AE-Journal Papers(저널논문)
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