Forecasting of the Spacecraft Dynamic Loading Under the Rocket Engine Thrust Oscillations of the Launch Vehicle

Abstract

During the rocket launch into working orbits, the rocket structure and its spacecraft are subjected to extreme dynamic impacts. During this period, the rocket structure and the spacecraft may be subjected to vibroacoustic loads, which can lead to malfunctions of the devices and the strength of the light, thin-walled spacecraft. Testing the spacecraft’s self-oscillations and predicting the spacecraft’s reaction to dynamic loads from the launch vehicle (LV) is a complex task, the relevance of which is manifested in the significant saving of material and technical resources invested in spacecraft development. An approach has been developed to predict the dynamic loads of spacecraft launched into working orbits using LVs (of various layout schemes). The approach makes it possible to estimate the values of dynamic loads (spectral densities of vibration accelerations) of the spacecraft under the propulsion system thrust oscillations acting on the LV structure in the active part of the liquid LV flight. The approach includes mathematical modeling of spatial oscillations of the launch vehicle structure by its structural and layout scheme and preliminary experimental determination of the power spectral density of the rocket engine structure.