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首页> 外文期刊>Journal of guidance, control, and dynamics >Time-Optimal Reorientation of a Spacecraft Using an Inverse Dynamics Optimization Method
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Time-Optimal Reorientation of a Spacecraft Using an Inverse Dynamics Optimization Method

机译：使用逆动力学优化方法的航天器时间最优定向

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This paper proposes a rapid attitude trajectory generation method for satellite reorientation, which is suitable for both rest-to-rest and track-to-track maneuvers. The problem is first formulated and solved using academic software readily used for generating optimal guidance trajectories offline. Then, the problem is reformulated using a Bezier polynomial parametrization of the quaternion trajectory, which naturally satisfies the unit quaternion norm constraint. The parameters of the quaternion trajectory polynomial and of the speed profile are varied to arrive at a quasi-optimal solution that is both feasible and exactly matches the endpoint conditions specified in the problem. The reduction in the number of varied parameters due to the predetermined structure of the trajectory leads to a fast computational speed as well as a solution that satisfies the end constraints at each iteration. The paper includes numerical simulation results obtained for several cases.
机译：提出了一种用于卫星定向的快速姿态轨迹生成方法，该方法适用于静止到静止和轨道到轨道的机动。首先使用易于离线生成最佳指导轨迹的学术软件来制定和解决该问题。然后，使用四元数轨迹的Bezier多项式参数化来重新求解该问题，该参数自然满足单位四元数范数约束。改变四元数轨迹多项式的参数和速度曲线的参数，以得出既可行又与问题中指定的终点条件完全匹配的准最优解。由于轨迹的预定结构而导致的可变参数数量的减少导致了快速的计算速度以及满足每次迭代的最终约束的解决方案。本文包括几种情况下获得的数值模拟结果。

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