A method for analyzing the shock response characteristics of a satellite with frame-panel configuration

Abstract

The high magnitude and frequency of the shock load generated by the dynamic action of a satellite with a frame-panel configuration will lead to equipment damage on the satellite. However, the mechanical properties of the plate-rod coupling will result in a significant difference in the transmission and attenuation characteristics of the shock load. Moreover, the accuracy of the response analysis and evaluation of the key components are lacking. In this article, both direct integration and modal superposition methods are used to analyze the transient response of a satellite with frame-panel configuration. Furthermore, the advantages and disadvantages of the two methods are compared, and the possible factors affecting the precision and duration of the calculation results are presented. Simulation data show that the effect of time is very short for this type of explosion shock, and high-frequency modes require a larger proportion of the response provoked. Although the modal superposition method can solve the problem of a large amount of calculation and long computation time by modal order truncation and adjusting the time step, high-order modes are easily ignored, which affect the accuracy of the calculation results. The direct integration method is more suitable for the shock response analysis of the satellite with frame-panel configuration.