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火箭入轨通常是沿标准轨道面的飞行控制,常规发射任务只需侧向小偏航角校正,但当今一些特殊的入轨任务要求火箭制导控制能侧向大偏航角飞行,以克服较大初始侧向偏差对末级火箭入轨的影响。文中提出了一种末级火箭的侧向大偏航非线性自适应组合制导控制方法,结合土星-5火箭IMG方法和航天飞机LTG方法各自的优点,进行了大偏航角的非线性耦合补偿修正,并对动力飞行过程的迭代算法进行了鲁棒稳定性改造。基于姿态喷嘴开关控制的六自由度数值仿真表明,提出的控制策略和算法简单可靠、稳定性好、精度高,在火箭入轨控制和空间飞行器变轨控制中具有参考和应用价值。
Rocket access orbit is usually along the standard trajectory flight control, conventional launch tasks only small lateral yaw correction, but today some special orbital tasks require rocket guidance control can be a large lateral yaw angle flight to overcome the more Influence of Large Initial Lateral Deviation on the Rocket Entry orbit of Last Stage. In this paper, a late-stage rocket lateral large yaw nonlinear adaptive combined guidance control method is proposed. Combining with the advantages of Saturn-5 rocket IMG method and space shuttle LTG method, a large yaw angle nonlinear coupling compensation Corrected, and the robustness of the iterative algorithm for the dynamic flight process was modified. The numerical simulation of six degrees of freedom based on gesture nozzle switch control shows that the proposed control strategy and algorithm are simple and reliable, good stability and high precision, which are of reference and application value in rocket trajectory control and spacecraft orbit control.