多约束下升力式再入飞行器可达域计算方法  

A method for calculating reachability regions of lift re-entry vehicles with multiple constraints

作　　者：冉云霆 泮斌峰[1] RAN Yunting;PAN Binfeng(School of Astronautics,Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《北京航空航天大学学报》2025年第3期904-909,共6页Journal of Beijing University of Aeronautics and Astronautics

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.

关 键 词：可达域 再入飞行器 过程约束 平衡滑翔 间接法 

分 类 号：V448.235[航空宇航科学与技术—飞行器设计]