Frequency Reliability Sensitivity Analysis of Aircraft Tension Joints

Abstract

For the commonly used aircraft tensile joints, the finite element method is used to obtain the natural frequencies of the tensile joints. According to the failure criterion that the absolute value of the difference between the natural frequency and the excitation frequency should be less than the specified value, define the vibration limit state equation of the aircraft tensile joint and calculate the resonance failure probability of the aircraft tensile joint in multiple failure modes. This article use the Monte Carlo method random sampling, then we can obtain the mean and standard deviation of the natural frequencies of the aircraft’s tensile joints. We also calculate the reliability of the statistical properties of the random parameters to the natural frequencies of the system at each excitation frequency and study the influence of the statistical characteristics of the parameters on the probability of resonance of the aircraft tensile joints.