考虑禁飞圆的高超声速飞行器再入预测制导

王青¹, 莫华东¹, 吴振东¹, 董朝阳²

(1. 北京航空航天大学 自动化学院,100191 北京; 2. 北京航空航天大学 航空科学与工程学院,100191 北京)



摘要:

针对大升阻比高超声速飞行器同时满足过程约束、终端约束及禁飞圆约束的再入制导问题,提出了一种新的规避禁飞圆的预测校正制导方法,利用拟平衡滑翔条件将过程约束转化为倾侧角约束,结合数值预测校正方法设计倾侧角数值大小,将禁飞圆区域约束实时转化为航向角约束,设计并运用航向角偏差走廊动态补偿策略,形成新的偏差走廊来控制倾侧角符号,从而导引规避禁飞圆．分析及仿真结果表明:该方法不依赖于标准轨迹,对不同的禁飞圆具备自适应能力,能满足终端约束和过程约束,成功规避禁飞圆,制导和落点精度高,并具有鲁棒性．

关键词:  再入制导  预测校正  禁飞圆  拟平衡滑翔  高超声速飞行器

DOI：10.11918/j.issn.0367-6234.2015.02.019

分类号:TP273

基金项目:国家自然科学基金(7,3); 国防预研基金(9140C48020212HK0101).



Predictive reentry guidance for hypersonic vehicles considering no-fly zone

WANG Qing¹, MO Huadong¹, WU Zhendong¹, DONG Chaoyang²

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

Abstract:

A new predictor-corrector methodology is developed for hypersonic vehicles with multi-constraints including typical inequality constraints, terminal states and no-fly zone. The approach makes use of the quasi-equilibrium glide condition (QEGC) for converting typical inequality constraints to the constraints of bank-angle, which is parameterized and found online with predictor-corrector in longitude guidance. Lateral guidance converts no-fly zone constraints to the range of velocity azimuth angle in real time and combines with the strategy of error corridor compensation for forming a new heading error corridor, which is used to avoid the no-fly zone. The algorithm does not rely on a standard trajectory and the guidance commands are calculated in real time, which endows the algorithm with sufficient adaptability. The simulation results show that the algorithm leads the vehicle to avoid the no-fly zone successfully while satisfying the terminal and path constraints, and has high guidance precision and robustness.

Key words:  reentry guidance  predictor-corrector  no-fly zone  QEGC  hypersonic vehicles