Time-to-go weighted optimal trajectory shaping guidance law |
| |
Authors: | WANG Hui LIN De-fu CHENG Zhen-xuan |
| |
Affiliation: | 1. School of Aerospace Engineering, Beijing institute of Technology, Beijing 100081, China 2. China North Industries Group Corporation, Beijing 100821, China |
| |
Abstract: | For maneuvering target,the optimal trajectory shaping guidance law which can simultaneously achieve the designed specifications on miss distance and final impact angle was deduced using optimal control theory based on the time-to-go weighted function.Based on the same cost function,the closed-form solutions of the guidance law were derived when the initial displacement of missile,final impact angle,heading error and target maneuver was introduced into the lag-free guidance system.To validate the closed-form solutions,the simulation of the lag-free system was done and the simulation results exactly matched the closed-form solutions and only when the exponent is greater than zero,the final acceleration approaches to zero. |
| |
Keywords: | trajectory shaping guidance optimal control time-to-go close-form solution |
本文献已被 CNKI 维普 万方数据 等数据库收录! |
| 点击此处可从《北京理工大学学报(英文版)》浏览原始摘要信息 |
|
点击此处可从《北京理工大学学报(英文版)》下载全文 |