基于能量的高超声速飞行器再入混合制导方法

王青; 莫华东; 吴振东; 董朝阳

doi:10.13700/j.bh.1001-5965.2013.0383

基于能量的高超声速飞行器再入混合制导方法

doi: 10.13700/j.bh.1001-5965.2013.0383

1. 北京航空航天大学自动化科学与电气工程学院, 北京 100191;
2. 北京航空航天大学航空科学与工程学院, 北京 100191

基金项目:

国家自然科学基金资助项目（61074027，61273083）；国防预研基金资助项目（9140C48020212HK0101）

详细信息

作者简介:
王青（1968- ），女，山东蓬莱人，教授，wangqing@buaa.edu.cn.

中图分类号: TP273
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- 被引次数: 0
出版历程
- 收稿日期: 2013-07-02
- 网络出版日期: 2014-05-20

Energy-based hybrid reentry guidance for hypersonic vehicles

1. School of Automation Science and Electrical Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
2. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 针对大升阻比高超声速飞行器滑翔再入制导问题，提出一种基于能量的混合制导方法.建立以能量为自变量的三自由度运动学方程，利用拟平衡滑翔特性将过程约束转换成倾侧角约束.纵向制导在初始下降段采用固定数值倾侧角飞行，在拟平衡滑翔段基于剩余航程随能量单调变化的特性将标准轨迹进行分段，然后分段进行在线预测校正制导.侧向制导基于横程与能量的近似线性关系，设计了由分段漏斗形横程走廊控制的倾侧角反转逻辑，以保证侧向制导精度.分析研究和仿真结果表明该方法易于实现，有效减小了制导指令的解算时间，制导和落点精度高，且对再入初始偏差及过程扰动不敏感.
- 再入制导 /
- 预测校正 /
- 航路点 /
- 拟平衡滑翔条件 /
- 高超声速飞行器
Abstract: An energy-based hybrid reentry methodology was developed for hypersonic vehicles. The three-degree-of-freedom reentry kinematic equations was conducted based on energy, and typical inequality constraints was converted to the constraints of bank-angle by using quasi-equilibrium glide condition (QEGC). Longitude guidance used a constant bank angle in initial descent, and segmented the standard trajectory in quasi-equilibrium glide phase since the range-to-go was monotonically decreased with energy, then used predictor-corrector online in every segment to reduce the calculating time. Lateral guidance designed a lateral reversal logic based on the crossrange corridor for crossrange varied almost linearly with energy between two bank reversals. The simulation results show that the proposed algorithm has the obvious decrease of calculating time, high guidance precision and is not sensitive to initial errors and disturbers.
- reentry guidance /
- predictor-corrector /
- way-point /
- quasi-equilibrium glide condition (QEGC) /
- hypersonic vehicles

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参考文献(10)

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