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

^*Corresponding author for this work

School of Aerospace Engineering

Research output: Contribution to journal › Article › peer-review

5 Citations (Scopus)

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–derivative controller with some compromises can ensure the stability of the missile and provide good performance for the actuator.

Original language	English
Pages (from-to)	2594-2602
Number of pages	9
Journal	Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering
Volume	231
Issue number	14
DOIs	https://doi.org/10.1177/0954410016668909
Publication status	Published - 1 Dec 2017

Keywords

Actuator controller
hinge moment
retuning method
spinning missiles

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10.1177/0954410016668909

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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–derivative controller with some compromises can ensure the stability of the missile and provide good performance for the actuator.",

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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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Keywords

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