摘要
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。
Along with the increasing diversity and complexity of space launch missions, it is of great significance to study new adaptive guidance methods that have higher precision and adaptability to satisfy the maneuverability, flexibility and high satellite injection accuracy requirements of launch vehicles. This paper presents a summary of the analytical solutions of opti- mal vacuum trajectories for launch vehicles and proposes a new iterative guidance method different from the traditional itera- tive guidance based on Newton method. This new method is particularly suitable for large attitude angles. Its analytic form of the Jacobian matrix is derived. Finally, numerical simulations are performed. Simulation results demonstrate that the adap- tive iterative guidance proposed has higher precision and powerful adaptability. Besides, the algorithm in this guidance method is simple and easy to implement. Therefore, it possesses high engineering application value.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2011年第9期1696-1704,共9页
Acta Aeronautica et Astronautica Sinica
关键词
运载火箭
迭代制导
最优轨迹
大姿态角
解析解
launch vehicle
iterative guidance
optimal trajectory
large attitude angle
analytical solution
