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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    Title :

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


    Contributors:
    Zhou, Wei (author) / Yang, Shuxing (author) / Zhao, Liangyu (author)


    Publication date :

    2017-12-01


    Size :

    9 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





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