This paper studies the optimal landing trajectory and control strategy for helicopter in tail rotor pitch lockup. A flight dynamics model of a single rotor helicopter with a tail rotor is established. The optimal safe landing and control problem is formulated into a nonlinear optimal control problem, and solved numerically using direct multiple shooting and sequential quadratic programming algorithms. The optimal safe landing process and control strategies for the sample helicopter encountering high tail rotor pitch lockup and low tail rotor pitch lockup are investigated respectively. Simulation results show that when the tail rotor is stuck at high pitch, it provides a large lateral force, which is beneficial for a high-power state landing with low forward speed and descent rate. When the tail rotor is stuck at low pitch, it provides a small lateral force, which is beneficial for flying at an economic speed (low-power state), but is not conducive to a safe landing afterwards. If a conventional landing is attempted in this situation, the yaw rate at touchdown would be very high and could be dangerous. If an autorotation landing is applied, the landing will be safer with a much lower yaw rate at touchdown.


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    Title :

    Landing Trajectory and Control Optimization for Helicopter in Tail Rotor Pitch Lockup


    Additional title:

    Lect.Notes Computer


    Contributors:
    Yang, Huayong (editor) / Liu, Honghai (editor) / Zou, Jun (editor) / Yin, Zhouping (editor) / Liu, Lianqing (editor) / Yang, Geng (editor) / Ouyang, Xiaoping (editor) / Wang, Zhiyong (editor) / Yan, Xufei (author) / Chen, Renliang (author)

    Conference:

    International Conference on Intelligent Robotics and Applications ; 2023 ; Hangzhou, China July 05, 2023 - July 07, 2023



    Publication date :

    2023-10-16


    Size :

    12 pages




    Type of media :

    Article/Chapter (Book)


    Type of material :

    Electronic Resource


    Language :

    English




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