为了提高空间飞行器的快速入轨能力, 满足空间飞行器弹道/轨道设计工作的快速、精确、可靠要求, 对空间飞行器弹道/轨道一体化快速设计方法进行了研究。首先, 对空间飞行器进行动力学建模, 分析弹道/轨道一体化设计需要满足的过程约束和终端约束, 给出空间飞行器的飞行时序; 为保证求解效率, 针对传统的弹道设计数值求解算法进行了创新改进, 综合应用改进牛顿迭代法、Broyden秩1方法和最速下降方法, 保证算法在初值不准的条件下仍能快速收敛; 最后, 研究了一种新的内外多层次求解策略, 同时将弹道段和轨道段分轮进行一体化设计, 进一步提高了算法的可靠性。仿真结果表明, 本文所研究的空间飞行器弹道/轨道一体化快速设计方法可在30 s内实现弹道/轨道设计, 设计精度为0.5 m。该设计算法可靠、快速、精确, 可应用于空间飞行器的快速入轨设计中。

To improve the rapid response of a spacecraft and ensure that its trajectory-orbit unified design meets the requirements of speed, accuracy, and reliability, a rapid trajectory-orbit unified design method for spacecrafts was studied. First, the dynamic model of a spacecraft was constructed. The process and terminal constraints required for a spacecraft's trajectory-orbit unified design were analyzed and its flight procedure was given. Then, the traditional trajectory design numerical solution was improved. Through application of the improved Newtonian, Broyden rank-1, and steepest descent methods, the convergence of the methods was ensured when the initial value wad incorect. Finally, a multi-step and multi-layer method was considered, and the algorithm was further improved. The simulation result reveals that the proposed rapid trajectory-orbit unified design method for a spacecraft can be executed in 30 s, and the design orbital precision is 0.5 m. The algorithm is reliable, rapid, and accurate, and can be applied to trajectory-orbit unified designs of rapid-response spacecrafts.