Abstract
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.
Highlights
Landing is the most critical operational phase of a helicopter
Energy method used for deriving equations of motion for ship board dynamic motion and assumptions to develop a dynamic model of helicopter
The full helicopter dynamic model built by considering typical US-Navy sea hawk helicopter version
Summary
Landing is the most critical operational phase of a helicopter. During landing of helicopter on the uneven surface, a large amplitude of vibrations transmitted to the helicopter fuselage structure causing safety and comfort problems to crew and passengers. [1] presented an analytical model for dynamic analysis of landing and taking off of the aircraft from a moving deck. The mathematical model of two main oleo and single tail oleo developed and analyzed for oleo load and oleo deflection for deck landing. Salazar [7] developed a mathematical model for a helicopter with a main rotor hub and tail rotor configuration to simulate flying behavior of the helicopter. An active landing gear behavior was demonstrated by Sivakumar and Haran [8] by developing six degree of freedom mathematical model of full aircraft with tricycle landing gear configuration. Most of the papers have shown the two degree of freedom mathematical model of single landing gear. S. SIVAKUMAR math’s model of helicopter with landing gear has been developed using Lagrange method for landing dynamics of helicopter
Sign-in/Register to view highlights & summary 
Published Version (
Free)
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
