Özet:

In this paper, landing dynamics for a helicopter fitted with an oleo pneumatic landing gear in the front and tail gears has been analysed with a seven degree of freedom mathematical model. Dynamic equations have been developed using Lagrange principle to investigate the effects of vibrations on the structure during landing phase of the helicopter. The bounce, roll, pitch, yaw acceleration response of helicopter landing obtained by numerical simulation in Matlab/Simulink. The developed model by Lagrange method will be useful to measure the vibration levels on landing and taxing of helicopter with uncertainties. This approach is also helpful to optimize the stiffness and damping properties of landing gear.

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