Research on the Attitude Control Law of Hypersonic Flight Vehicle

被引：0
|
作者：
Zhou, Hongcheng [1 ,2 ]
Wang, Daobo [2 ]
Yang, Juan [1 ]
机构：
[1] JinLing Inst Technol, Inst Informat, Nanjing 211169, Jiangsu, Peoples R China
[2] Nanjing Univ Aeronaut & Astronaut, Coll Automat Engn, Nanjing 210016, Jiangsu, Peoples R China
来源：
IAEDS15: INTERNATIONAL CONFERENCE IN APPLIED ENGINEERING AND MANAGEMENT | 2015年 / 46卷
关键词：
SMALL-SCALE HELICOPTER; TRACKING CONTROL; UAV HELICOPTER;
D O I：
10.3303/CET1546027
中图分类号：
T [工业技术];
学科分类号：
08 ;
摘要：
Hypersonic flight vehicle has strong-nonlinearity, quick time-variability, strong-coupling features. In order to realize its flight effective control, the airflow attitude angle needs to be controlled precisely. Based on the accurate tracking of the airflow attitude angle command, the predetermined flight path can be realized to accomplish flight tasks. Use dynamic surface (DSC) to design the airflow angle attitude control law, which proves the stability and the time-delay compensation effect. The simulation results show that this method has good tracking control and fast convergence.
引用
收藏
页码：157 / 162
页数：6
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