基于解析剖面的时间协同再入制导

王肖; 郭杰; 唐胜景; 祁帅

doi:10.7527/S1000-6893.2018.22565

航空学报 >

2019 , Vol. 40 >Issue 3: 322565 - 322565

DOI: https://doi.org/10.7527/S1000-6893.2018.22565

电子电气工程与控制

基于解析剖面的时间协同再入制导

王肖 ,
郭杰 ,
唐胜景 ,
祁帅

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北京理工大学宇航学院, 北京 100081

收稿日期: 2018-07-26

修回日期: 2018-08-15

网络出版日期: 2018-11-14

基金资助

国家自然科学基金（11572036）；北京理工大学研究生科技创新项目（2018CX10011）

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Time-cooperative entry guidance based on analytical profile

WANG Xiao ,
GUO Jie ,
TANG Shengjing ,
QI Shuai

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School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China

Received date: 2018-07-26

Revised date: 2018-08-15

Online published: 2018-11-14

Supported by

National Natural Science Foundation of China (11572036);Graduate Technological Innovation Project of Beijing Institute of Technology (2018CX10011)

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摘要

针对高超声速滑翔飞行器再入段时间协同制导问题，提出一种基于高度-速度剖面的预测校正协同制导律。首先在高度-速度剖面内设计了参考轨迹，利用两个轨迹参数在线预测剩余飞行航程和时间；通过数值算法校正两个轨迹参数以满足航程和时间约束并求取实际控制量，结合侧向航向角走廊实现了单飞行器的时间约束再入制导。在此基础上分析了飞行器的时间可调范围，针对多飞行器协同再入任务设计了协同飞行时间和协同策略，实现了时间协同再入飞行。该策略考虑到再入过程中的通讯困难，避免了弹间通讯，且充分利用了飞行器纵向动力学，时间可控范围较大，更加适用于实际的再入过程。仿真结果说明了时间约束再入制导律对时间的可控性和协同策略的有效性。

关键词： 高超声速滑翔飞行器; 时间协同; 再入制导; 预测校正; 高度-速度剖面

本文引用格式

王肖 , 郭杰 , 唐胜景 , 祁帅 . 基于解析剖面的时间协同再入制导[J]. 航空学报, 2019 , 40(3) : 322565 -322565 . DOI: 10.7527/S1000-6893.2018.22565

Abstract

Aiming at the time-cooperative guidance problem for hypersonic gliding vehicles in the entry phase, a predictor-corrector cooperative guidance law based on altitude-velocity profile is proposed. Firstly, the reference trajectory is designed in the altitude-velocity profile, and the range-to-go and time-to-go are predicted online using two trajectory parameters. The two trajectory parameters are corrected by numerical algorithm to meet the range and time constraints and the actual control input is obtained. Combined with the lateral heading angle corridor, the time-constrained entry guidance is implemented for a single vehicle. On this basis, the adjustable range of the flight time of a single vehicle is analyzed. The coordination flight time and the coordination strategy are designed for multi-vehicle coordinated entry mission, realizing the time-cooperative entry flight. This strategy considers the communication difficulties in the entry process, avoids the communication between vehicles, and makes full use of the longitudinal dynamics of the vehicle, making the controllable range of flight time larger, which is more suitable for actual entry flight. Simulation results illustrate the time-controllability of the time-constrained entry guidance and the effectiveness of the coordination strategy.

Key words： hypersonic gliding vehicles; time-cooperation; entry guidance; predictor-corrector; altitude-velocity profile

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