摘要
针对升力式再入飞行器再入过程中的热流率、过载和动压受约束问题,提出一种多约束条件下的再入可达域计算方法。基于虚目标法建立了不考虑状态不等式过程约束的再入可达域最优控制模型;基于无过程约束问题的最优控制设计预测校正方法,将状态不等式约束转换为控制不等式约束;以X-33再入飞行器为对象完成数值仿真验证。数值仿真结果表明:与传统的依赖于平衡滑翔假设的“软约束”方法相比,所提方法可实现“硬约束”,即使飞行器在短时间内进行大幅度机动,各项过程约束仍能严格满足。
In view of the heat flow,overload,and dynamic pressure constraint problems during the reentry process of the lift reentry vehicle,a calculation method of the reentry reachability region under multiple constraints is designed.Using the virtual target method,an optimal control model for the reentry reachability region is developed without the state inequality restrictions.A predictive correction method is designed based on the optimal control without process constraints,which converts state inequality constraints into control inequality constraints.The numerical simulation of the X-33 is completed.The results of the numerical simulation demonstrate that,in contrast to the conventional"soft constraint"method,which depends on the quasi-equilibrium glide conditions,the suggested method is capable of achieving“hard constraint,”meaning that all process constraints can still be strictly satisfied even in the event that the aircraft makes large maneuvers quickly.
作者
冉云霆
泮斌峰
RAN Yunting;PAN Binfeng(School of Astronautics,Northwestern Polytechnical University,Xi’an 710072,China)
出处
《北京航空航天大学学报》
北大核心
2025年第3期904-909,共6页
Journal of Beijing University of Aeronautics and Astronautics
关键词
可达域
再入飞行器
过程约束
平衡滑翔
间接法
reachable region
reentry vehicle
process constraints
balanced glide
indirect method
作者简介
通信作者:泮斌峰.E-mail:panbinfeng@nwpu.edu.cn。
