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

Wei Zhou; Shuxing Yang; Liangyu Zhao

doi:10.1177/0954410016668909

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

Wei Zhou
, Shuxing Yang^*
, Liangyu Zhao

^*此作品的通讯作者

空天科学与技术学院

Beijing Institute of Technology
Ministry of Education in China

科研成果: 期刊稿件 › 文章 › 同行评审

5 引用（Scopus）

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.

源语言	英语
页（从-至）	2594-2602
页数	9
期刊	Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering
卷	231
期	14
DOI	https://doi.org/10.1177/0954410016668909
出版状态	已出版 - 1 12月 2017

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title = "Retuning the actuator proportional{\textendash}integral{\textendash}derivative controller of spinning missiles",

abstract = "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{\textendash}derivative controller with some compromises can ensure the stability of the missile and provide good performance for the actuator.",

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AU - Zhao, Liangyu

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N2 - 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.

AB - 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.

KW - Actuator controller

KW - hinge moment

KW - retuning method

KW - spinning missiles

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ER -

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

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