北京航空航天大学学报 ›› 2011, Vol. 37 ›› Issue (7): 777-781.

• 论文 • 上一篇    下一篇

高超声速再入滑翔飞行器多约束轨迹快速优化

王俊波, 宋勋, 宋剑爽, 任章   

  1. 北京航空航天大学 自动化科学与电气工程学院,北京 100191
  • 收稿日期:2010-09-10 出版日期:2011-07-30 发布日期:2011-08-04
  • 作者简介:王俊波(1985-),男,安徽省亳州人,博士生,popolwb@163.com.

Rapid trajectory optimization for hypersonic reentry vehicles with multi-constraints

Wang Junbo, Song Xun, Song Jianshang, Ren Zhang   

  1. School of Automation Science and Electrical Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
  • Received:2010-09-10 Online:2011-07-30 Published:2011-08-04

摘要: 为适应高超声速再入滑翔飞行器高动态、多约束的特点,提出了一种快速轨迹优化方法.轨迹优化时将倾侧角控制曲线表示为飞行器能量参数的分段线性函数,从而使纵向轨迹优化问题转化为多维非线性规划问题,并采用序列二次规划(SQP,Sequential Quadratic Programming)方法进行优化求解.横侧向轨迹控制采用偏航角跟踪视线角的方法,设计了视线角误差走廊边界随速度变化的取值,研究了倾侧角反转策略,避免了传统优化中求解倾侧角反转时刻所需的迭代运算.仿真结果表明:该轨迹优化方法在一般高性能微机上生成一条约10 000 km左右的飞行轨迹耗时约5 s,具有较快的优化速度,且精度较高,有一定的工程应用价值 .

Abstract: A rapid trajectory optimization was developed to handle the high dynamic and multi-constraints accompanying with hypersonic reentry vehicles. The equation of constraints in reentry process was established and the control variable of bank-angle was displayed as a subsection linear function of flight energy parameter during the process of trajectory optimization. The longitude constrained reference trajectory optimization was converted to a nonlinear optimization problem,and solved using sequential quadratic programming (SQP) method. The lateral motion was controlled by yaw angle tracking aspect angle and the error corridor of aspect angle was designed. The logic of back angle- reversal is developed to avoid traditional calculation by iteration. The simulation results indicate that the algorithm is able to generate a 10 000 km range reentry trajectory in about 5 s on the desktop computer. And the algorithm has fast calculation,high guidance precision and effective for implementation.

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