Retuning the actuator proportional-integral-derivative controller of spinning missiles

被引：5

作者：

Zhou, Wei ^{[1
,2
]}

Yang, Shuxing ^{[1
,2
]}

Zhao, Liangyu ^{[1
,2
]}

机构：

[1] Beijing Inst Technol, Sch Aerosp Engn, 5 South Zhongguancun St, Beijing 100081, Peoples R China

[2] Minist Educ, Key Lab Dynam & Control Flight Vehicle, Beijing, Peoples R China

来源：

PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING | 2017年 / 231卷 / 14期

基金：

美国国家科学基金会;

关键词：

Actuator controller; hinge moment; retuning method; spinning missiles; FLIGHT VEHICLE; CONING MOTION; PID CONTROL; AUTOPILOT; STABILITY; DESIGN; INSTABILITIES; SYSTEM;

D O I：

10.1177/0954410016668909

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

The hinge moment acting on the actuator will cause an out-of-plane moment, which is a destabilizing factor to the angular motion of spinning missiles. A new tuning criterion for the actuator controller is proposed to decrease the out-of-plane moment. It is noted that the integral element does not decrease the out-of-plane moment. A carefully designed proportional-derivative controller with some compromises can ensure the stability of the missile and provide good performance for the actuator.

引用

页码：2594 / 2602

页数：9

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