Aircraft Landing Gear Parameter Estimation and Simulation using Elimination Method
In this paper, an elimination method has been developed and applied for identification of an aircraft’s landing gear properties. A nonlinear simulation model of the Grumman A-6 Intruder main landing gear has been developed, simulated and validated against static and dynamic test data, obtained by the engineers at the Aircraft Landing Dynamics facilities at NASA Langley Research Centre. This mathematical model has been proven to generate realistic responses of the landing gear during taxiing along an undulating surface under various configurations. By using the simulated data, an elimination method has been applied to deduce the nonlinear variables of the landing gear model via a developed searching algorithm. It is capable of identifying the aircraft landing gear properties, such as spring stiffness, damping coefficients, frictional constants and tyre deflection force, for the parameter estimation process in Matlab/Simulink.
Aircraft Landing Gear Simulation Grumman A-6 Intruder Non-Linear Dynamic Modelling Tyre Deflection Parameter Estimation Elimination Method System Identification.
Ka Wai Lee Timothy Kam Pavel M. Trivailo Doug Sherman
School of Aerospace, Mechanical and Manufacturing Engineering,Royal Melbourne Institute of Technolog Defence Science & Technology Organisation,506 Lorimer St, Fishermans Bend, Victoria 3207 Australia
国际会议
2011年亚太航空航天技术学术会议(APISAT 2011)
澳大利亚
英文
1-10
2011-02-28（万方平台首次上网日期，不代表论文的发表时间）