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本文采用四元数法给出了航天器姿态机动的动力学模型，通过引入一种拟欧拉角，根据最优控制理论建立了一种姿态反馈开关控制逻辑，并对闭环系统的稳定性进行了分析。仿真结果验证了所述方法的有效性。
In this paper, the dynamic model of attitude maneuver of spacecraft is given by quaternion method. By introducing a kind of pseudo Euler angle, a control logic of attitude feedback switch is established according to the optimal control theory. The stability of the closed-loop system Analysis. Simulation results verify the effectiveness of the proposed method.