航空学报 > 2011, Vol. 32 Issue (9): 1696-1704   doi: CNKI:11-1929/V.20110511.1345.001

基于最优解析解的运载火箭大气层外自适应迭代制导方法

傅瑜1, 陈功1,2, 卢宝刚1, 郭继峰1   

  1. 1. 哈尔滨工业大学 航天工程系, 黑龙江 哈尔滨 150001;
    2. 中国空气动力研究与发展中心, 四川 绵阳 621000
  • 收稿日期:2010-12-20 修回日期:2011-03-11 出版日期:2011-09-25 发布日期:2011-09-16
  • 通讯作者: 崔乃刚(1965-) 男,博士,教授,博士生导师。主要研究方向:飞行器动力学与控制、非线性滤波理论及其应用。 Tel: 0451-86413452 E-mail: cui_naigang@163.com E-mail:cui_naigang@163.com
  • 作者简介:傅瑜(1985-) 男,博士研究生。主要研究方向:飞行器轨迹优化设计和自主制导方法。 Tel: 0451-86412766 E-mail: fuyulucky13@163.com

A Vacuum Adaptive Iterative Guidance Method of Launch Vehicle Based on Optimal Analytical Solution

FU Yu1, CHEN Gong1,2, LU Baogang1, GUO Jifeng1, CUI Naigang1   

  1. 1. Department of Astronautics Engineering, Harbin Institute of Technology, Harbin 150001, China;
    2. China Aerodynamics Research & Development Center, Mianyang 621000, China
  • Received:2010-12-20 Revised:2011-03-11 Online:2011-09-25 Published:2011-09-16

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。

关键词: 运载火箭, 迭代制导, 最优轨迹, 大姿态角, 解析解

Abstract: 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 optimal vacuum trajectories for launch vehicles and proposes a new iterative guidance method different from the traditional iterative 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 adaptive 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.

Key words: launch vehicle, iterative guidance, optimal trajectory, large attitude angle, analytical solution

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