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随着空间发射任务的多样化和复杂化,为了满足运载火箭的机动性、灵活性以及卫星高精度入轨的要求,需要研究制导精度更高、适应能力更强的自适应制导方法。本文总结了运载火箭大气层外最优轨迹的解析解;基于牛顿迭代法,研究了一种不同于以往迭代制导思想、适用于大姿态角范围的迭代制导方法,并推导了其雅可比矩阵的解析式;最后对该迭代制导方法进行了仿真验证。仿真结果表明,所给出的迭代制导方法具有较高的制导精度和较强的适应性,同时该迭代制导方法计算简单、易于实现,具有较强的工程应用价值。
With the diversification and complexity of space launch missions, in order to meet the requirements of launch vehicle maneuverability, flexibility and high-precision satellite orbit, it is necessary to study adaptive guidance methods with higher guidance accuracy and adaptability. This paper summarizes the analytic solution of the optimal trajectory outside the atmosphere of launch vehicle. Based on the Newton iteration method, an iterative guidance method that is different from the previous iterative guidance idea and suitable for large attitude angle range is derived and its Jacobian matrix is derived Finally, the iterative guidance method is verified by simulation. The simulation results show that the proposed iterative guidance method has high guidance accuracy and strong adaptability. Meanwhile, the iterative guidance method is simple and easy to implement and has strong engineering application value.