Dynamic response reliability analysis of airplane inner-flap mechanism

Based on the virtual prototype technology and reliability theory, the dynamic response reliability of an airplane's inner-flap mechanism was analyzed. Firstly, the finite element software Patran and the dynamic software ADAMS were applied to build the virtual prototype of the inner-flap coupled with rigid and flexible bodies. Under given aerodynamic load, the driving force varying with time of the inner-flap mechanism and satisfying the required moving laws was simulated by ADAMS. Secondly, the randomness of the slip track, the rolling wheel size, and the aerodynamic load were taken into consideration, on which the dynamic seizure reliability was analyzed under the constant maximum driving force of the screw. Through the minimizing transformation of performance stochastic process, the moments method and the stochastic response surface method were used to approximate the characteristic distribution of the performance function. The reliability analysis methods were programmed in conjunction with ADAMS and the seizure failure probability of the inner-flap mechanism was solved, providing a feasible reference method for the reliability design of the flap mechanism.