A model predictive control technique with guaranteed resolvability and required thruster silent times for small-body proximity operations
A model predictive control technique with guaranteed resolvability and required thruster silent times for small-body proximity operations
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DOI：
10.2514/6.2006-6780
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发表时间：
2006-12
期刊：
影响因子：
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通讯作者：
J. Carson;Behçet Açikmese
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文献类型：
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作者：
J. Carson;Behçet Açikmese
The guidance and control algorithms for enabling spacecraft proximity operations about small celestial bodies are developed by using a model predictive control approach. Separate feedforward and feedback components are utilized. The feedforward, or open-loop, guidance is based on a pseudo way-point generation algorithm that uses a discrete linear-timevarying model of the dynamics that incorporates required thruster silent times. This leads to a convex formulation of the open-loop trajectory generation problem with control and state constraints. Particularly, the pseudo way-points are generated through the solution of a second-order cone programming problem (a subclass of semi-definite programming), and there are interior point methods to compute the global optimum with a deterministic stopping criteria and a prescribed level of accuracy. Feedback control is implemented to track the pseudo way-point trajectories in a manner that guarantees the resolvability for the open-loop problem, enabling the ability to update the guidance profile in a robust, model-predictive manner. The robust guidance and control algorithm with resolvability is demonstrated in the simulation of a spacecraft landing onto a small asteroid possessing a significant gravity field; incorporating a gravity model into the algorithm provides notable improvements in controller performance.
