Optimal periodic control for spacecraft pointing and attitude determination
Optimal periodic control for spacecraft pointing and attitude determination
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DOI：
10.2514/3.21130
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发表时间：
1993-12
影响因子：
2.6
通讯作者：
M. Pittelkau
中科院分区：
文献类型：
--
作者：
M. Pittelkau
一种新的方法，自主磁滚转/偏航控制的极轨道，天底指向动量偏置航天器被认为是基线姿态控制系统的下一个泰罗斯系列。结果表明，滚动/偏航动态与磁控制周期性时变。最优周期控制律，然后开发。控制设计的特点是一个状态估计器，估计姿态，姿态角速度和环境扭矩干扰地球传感器和太阳传感器的测量，没有陀螺仪是必要的。状态估计器兼作动态姿态确定和预测功能。除了改进的性能之外，最优控制器允许比否则所需的小得多的动量偏差。给出了仿真结果。
A new approach to autonomous magnetic roll/yaw control of polar-orbiting, nadir-pointing momentum bias spacecraft is considered as the baseline attitude control system for the next Tiros series. It is shown that the roll/yaw dynamics with magnetic control are periodically time varying. An optimal periodic control law is then developed. The control design features a state estimator that estimates attitude, attitude rate, and environmental torque disturbances from Earth sensor and sun sensor measurements; no gyros are needed. The state estimator doubles as a dynamic attitude determination and prediction function. In addition to improved performance, the optimal controller allows a much smaller momentum bias than would otherwise be necessary. Simulation results are given.