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针对具有推力幅值和方向约束的航天器交会问题,本文提出了基于模型预测控制算法的制导策略。在建立推力幅值约束和方向约束数学模型的基础上,将交会相对动力学模型与约束模型预测控制理论相结合,以离散二次型函数为性能指标,建立了航天器交会的模型预测控制算法。本文分析了影响系统稳定性的三大因素:局部镇定器、终端代价函数和终端约束集。仿真结果证实了算法的有效性和可行性:在推力大小和方向有约束的情况下,实现了追踪航天器与目标航天器的快速交会。
Aiming at the problem of spacecraft intersection with thrust amplitude and direction constraints, a guidance strategy based on model predictive control algorithm is proposed in this paper. Based on the establishment of mathematical models of thrust amplitude constraints and directional constraints, the relative dynamics model of intersection and the constraint model predictive control theory are combined. With discrete quadratic function as the performance index, a model predictive control algorithm of spacecraft rendezvous is established . This paper analyzes three factors that affect system stability: local ballast, terminal cost function and terminal constraint set. The simulation results show the effectiveness and feasibility of the algorithm: the rapid rendezvous between the spacecraft and the target spacecraft is realized under the constraint of the thrust size and direction.