摘要
针对高超声速滑翔飞行器预测校正制导计算效率低的问题,提出一种基于攻角-速度剖面实时修正的预测校正制导算法。利用准平衡滑翔条件将再入过程约束转化为高度-速度剖面下的飞行走廊,设计三段式的飞行剖面进行轨迹规划以满足终端状态约束。纵向剖面在事先设定的攻角剖面的基础上,通过建立攻角增量与剩余航程增量间的映射关系,反解计算攻角修正指令,以满足航程约束。侧向制导通过航向角偏差走廊确定倾侧角符号,控制侧向的机动。数值仿真实验验证了算法能够同时满足终端速度、高度以及航程约束,且计算耗时短,具有一定的鲁棒性。
A predictive correction guidance algorithm based on real-time correction of attack anglevelocity profile is proposed to address the low computational efficiency of predictive correction guidance for hypersonic gliders.The quasi equilibrium gliding condition is applied to transform the re-entry process constraint into a flight corridor under the altitude velocity profile,and a three-stage flight profile for trajectory planning is designed to meet the terminal state constraint.On the basis of the preset attack angle profile,establishes a mapping relationship between the angle of attack increment and set up the remaining range incrementis,by the longitudinal profile,and calculates the attack angle correction command in reverse to meet the range constraint.Lateral guidance determines the tilt angle symbol through the heading angle deviation corridor to control lateral maneuvers.Numerical simulation experiments have verified that the proposed algorithm can simultaneously satisfy terminal speed,altitude and range constraints,and has short computational time and certain robustness.
作者
李青羊
刘俊辉
单家元
曹宇
Li Qingyang;Liu Junhui;Shan Jiayuan;Cao Yu(School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China;Beijing System Design Institute of Electro-Mechanic Engineering,Beijing 100854,China)
出处
《战术导弹技术》
北大核心
2024年第3期99-107,共9页
Tactical Missile Technology
基金
国家自然科学基金(62103049)
北京理工大学青年教师学术启动计划(XSQD-6120220106)。
关键词
高超声速飞行器
准平衡滑翔
飞行走廊
再入制导
攻角-速度剖面
高度-速度剖面
hypersonic vehicle
quasi equilibrium gliding
flight corridor
re-entry guidance
attack angle-velocity profile
altitude-velocity profile
