首页 | 官方网站   微博 | 高级检索  
     

复杂禁飞区高超声速飞行器路径-轨迹双层规划
引用本文:张源,张冉,李惠峰.复杂禁飞区高超声速飞行器路径-轨迹双层规划[J].宇航学报,2022,43(5):615-627.
作者姓名:张源  张冉  李惠峰
作者单位:北京航空航天大学宇航学院,北京 100191
基金项目:国家自然科学基金(62103014);
摘    要:针对高超声速飞行器在复杂禁飞区的规避场景,为解决现有轨迹规划方法对任务初值依赖性强的问题,提出一种基于双层规划建模的路径-轨迹规划方法。其中,上层为路径规划,为轨迹提供路径点引导信息,避免轨迹陷入局部解;下层为轨迹规划,利用上层输出的路径点信息,将轨迹分割成多个横向机动小的子段,解析求解横纵向飞行剖面,减小运动模型简化误差。数值仿真表明,与现有轨迹优化方法相比,本方法能够选择指标更优的路径,提高了轨迹规划的全局性能;解析飞行剖面制导误差不超过0.03%,解决了大范围横向机动的剖面解析难题。

关 键 词:双层规划  禁飞区规避  高超声速飞行器  路径规划  解析解  
收稿时间:2021-07-30

Dual level Path trajectory Generation with Complex No fly Zone Constraints for Hypersonic Vehicle
ZHANG Yuan,ZHANG Ran,LI Huifeng.Dual level Path trajectory Generation with Complex No fly Zone Constraints for Hypersonic Vehicle[J].Journal of Astronautics,2022,43(5):615-627.
Authors:ZHANG Yuan  ZHANG Ran  LI Huifeng
Affiliation:School of Astronautics, Beihang University, Beijing 100191, China
Abstract:Aiming at the avoidance for hypersonic vehicle in complex no fly zones, in order to solve the problem that the existing trajectory generation methods are strongly dependent on the initial guess, a path trajectory generation method is proposed based on the dual level planning modeling. Among them, the upper level is for path planning, providing path points information for the trajectory to avoid local solutions; the lower level is for trajectory planning, using the path points output by the upper layer to divide the trajectory into several sub segments with small lateral maneuver, and the lateral and longitudinal flight profiles are analytically solved to reduce the simplification error of the motion model. Numerical simulations show that, compared with the existing methods, this method can select the path with better indicators and then improve the global performance. In addition, the guidance error of analytical flight profile is less than 0.03%, which solves the analytical problem of large scale lateral maneuvering.
Keywords:Dual level planning  No fly zone avoidance  Hypersonic vehicle  Path planning  Analytical solution  
点击此处可从《宇航学报》浏览原始摘要信息
点击此处可从《宇航学报》下载全文
设为首页 | 免责声明 | 关于勤云 | 加入收藏

Copyright©北京勤云科技发展有限公司    京ICP备09084417号-23

京公网安备 11010802026262号