摘要
研究了采用反作用飞轮为执行机构的整星零动量卫星绕Ｘ轴大角度偏置飞行模式的姿态解耦控制问题。首先给出卫星姿态运动学和动力学模型，然后在控制作用中引入非线性项对姿态动力学模型线性化，进一步对线性模型进行状态反馈解耦和极点配置。最后，给出了数学仿真算例和仿真结果。
This paper designs an attitude decoupling control law for small satellite in large-angle biased flight mode about roll axis of zero-momentum system via reaction wheels.Attitude kinematics equations and dynamics equations are established firstly in this paper,then a nonlinear item is introduced in the controller to linearize the attitude dynamics equations, and then a state feedback decoupling law and a pole assignment law are designed for the linearized model.At last,a numerical simulation example is given.
出处
《航天控制》
CSCD
北大核心
1999年第1期11-18,共8页
Aerospace Control
