In this paper, a new type of foldable winged unmanned aerial vehicle is designed, and the structure of the aircraft is analyzed. The dynamic model is established and an improved sliding mode control algorithm is used to control the attitude of the aircraft. In addition, a centroid position control method using attitude compensation is designed for the coupling characteristics of this aircraft. The simulation proves that the attitude and position of the new aircraft can be effectively controlled.


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    Title :

    Hover Control of New type ducted aircraft


    Contributors:
    Liu, Peijun (author) / Deng, Hongbin (author) / Wang, Shikun (author) / Li, Kewei (author) / Wei, Yiran (author)


    Publication date :

    2019-10-01


    Size :

    2358140 byte




    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English



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