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首页> 外文期刊>Journal of guidance, control, and dynamics >Solution Strategies for an Extension of Wahba's Problem to a Spinning Spacecraft
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Solution Strategies for an Extension of Wahba's Problem to a Spinning Spacecraft

机译：将Wahba问题扩展到旋转航天器的解决方案策略

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摘要

Several methods have been devised to estimate the optimal attitude quaternion and angular velocity for an axially symmetric spacecraft given only a tinie series of vector attitude measurements and a rigid-body model of the' spacecraft dynamics. These methods solve a generalization of the Wahba problem that is applicable to a low-complexity spinning spacecraft such as a sounding rocket. They have the advantages of enabling rate estimation without gyros and avoiding the divergence issues of an extended Kalman filter. Measurements at different times are combined via the closed-form quaternion state transition matrix that makes use of Euler equations for a rigid body. The problem takes the form of six or more nonlinear equations in six or seven unknowns, and these equations can be partially solved analytically to facilitate a numerical solution of the remainder. Representative simulation results illustrate both the merits of these solution strategies and some of the practical issues that arise during implementation.
机译：已经设计了几种方法来估计轴向对称航天器的最佳姿态四元数和角速度，仅给出矢量姿态测量的微小序列和航天器动力学的刚体模型。这些方法解决了Wahba问题的一般化问题，该问题适用于诸如探测火箭之类的低复杂度旋转的航天器。它们具有以下优点：无需陀螺仪即可进行速率估算，并且避免了扩展卡尔曼滤波器的发散问题。通过封闭形式的四元数状态转换矩阵对不同时间的测量值进行组合，该矩阵利用Euler方程来计算刚体。该问题采用六个或七个以上未知数中的六个或更多非线性方程式的形式，可以通过解析方式部分求解这些方程式，以利于对其余方程进行数值求解。代表性的仿真结果既说明了这些解决方案策略的优点，也说明了在实施过程中出现的一些实际问题。

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