Random Vibration Fatigue Life Analysis of Airborne Electrical Control Box

To study the influence of random vibration on fatigue life airborne equipment, an aircraft electrical control box was selected as research object. First, finite element software used to model dynamics investigate its mode frequencies. The accuracy simulations verified by performing experiments. Second, superposition method analyze flight direction (X axis), side (Y and altitude (Z axis) responses box. analysis results were combined with Miner linear cumulative damage criterion Gaussian-distribution Steinberg estimate in three directions. Finally, calculation durability test show good agreement experiment results, maximum error is 13.4%, indicating that established this paper acceptable. axes meets user requirements, along has greatest impact life, which consistent actual experimental data. can be extended predict other equipment thus practical significance for structural design reliability equipment.