Optimization Of Random Vibration Conditions Based on Equivalent Acceleration Fatigue Damage

This article is based on the structural linear fatigue frequency domain analysis method of power spectral density function, taking a single launch vehicle equipment as the analysis object. Based on the actual flight telemetry high-frequency random acceleration vibration data at the installation position of the equipment, the actual flight telemetry non-stationary random acceleration vibration data is segmented and processed to obtain the total fatigue life damage of key parts of the equipment throughout the flight. Based on the principle of fatigue damage equivalence, the envelope of the random acceleration vibration power spectrum density for whole flight telemetry has been optimized and reduced, and the acceptance level random vibration conditions designed based on this envelope can also be proportionally reduced, providing a reference for the optimization design and application of the random vibration environment conditions for the launch vehicle.