Helicopter flight dynamic modeling and controller design during autorotation glide
Helicopter's autorotation flight dynamic modeling and control system design were studied in this paper.Firstly,a helicopter dynamics model after engine failure was established.Then,a trim calculation of autorotation was performed to obtain the steady-state decent rate corresponding to the forward speed during autorotation.The aerodynamic characteristics in different collective pitch under the given forward speed and decent rate were calculated.The PI controller based on descent rate error was designed in combination with a normal flight state speed following system based on the robust parameter design method.Finally,simulation verification and result analysis were conducted.The results show that the helicopter rotational speed can return to the desired value and stabilize within a certain time by using the prescribed PI controller,so that the helicopter can successfully enter the steady autorotation.This study is a guide to the design of the autorotation controller after helicopter engine failure.
autorotation glideflight dynamic modelingrobust parameter designPI control
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