Abstract:

An integration method of shock absorber performance analysis, test and design of aircraft landing gears is presented. By this method, the air polytropic exponent and the orifice discharge coefficient of shock strut can be automatically identified by using drop test results of the landing gear, and the maximum impact load of the landing gear on the runway can be minimized by adjusting the filling parameters and the variable orifice size of the shock absorber. The test results show that the presented algorithm is successful and effective.

Key words: landing gea r, shock absor ber, pa rameter identificat ion, optimizat ion