摘要
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。
In satellite formation flying, a controllable follower satellite flies around a leader spacecraft or space station to carry out various missions. The attitude control problem for this formation flying was studied using quaternion based control law assuming that the orbit information is known for both satellites, The desired attitude of the follower is determined from the orbit information with expressions given for the angle, angular velocity and angular acceleration of the satellite. Long duration, large angle attitude tracking maneuvers are achieved with three pcrpendicular reaction wheels. Simulations show that the control law can effectively control the attitude and angular velocity of the follower to match the predicted movement for one or more orbit periods, and that the total moment is acceptable.
出处
《清华大学学报（自然科学版）》
EI
CAS
CSCD
北大核心
2006年第11期1914-1917,共4页
Journal of Tsinghua University(Science and Technology)
基金
国家自然科学基金资助项目(10672084)
关键词
卫星
编队飞行
姿态跟踪机动
大角度
satellite
formation flying
attitude tracking controllarge angle
