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卫星编队飞行的应用之一是受控卫星在目标卫星、空间站、载人飞船周围以“编队飞行”的形式相伴飞行,对目标进行观测或者执行更多的操作。该文研究这种应用中的姿态控制问题。假设两个飞行器的轨道信息已知,由轨道信息确定实现姿态跟踪调节所需的一种可能的期望姿态,给出了解析表达式,包括姿态角、姿态角速度及角加速度。采用基于四元数的控制律,用3个动量轮实现了卫星长时间、大角度姿态跟踪机动。仿真结果显示,在超过一个周期的仿真时间内,姿态及姿态角速度与期望姿态的吻合程度比较好,而且力矩的花费也不是太大。
One of the applications of satellite formation flying is that controlled satellites fly in “formation flying” around target satellites, space stations and manned spacecraft, observe the targets or perform more operations. This paper studies the problem of attitude control in this application. Assuming that the orbital information of the two aircraft is known, a possible expected attitude needed to achieve attitude tracking adjustment is determined by orbit information, and analytical expressions including attitude angle, attitude angular velocity and angular acceleration are given. Using the control law based on quaternions, the long-time and large-angle attitude tracking maneuver of the satellite is realized by using three momentum wheels. The simulation results show that the attitude and attitude angular velocities are in good agreement with the expected attitude in more than one cycle of simulation time, and the torque is not too expensive.