Optimization the position of the spacecraft instrument panel mounting points based on modal analysis

The paper presents the optimization of the location of the interface points of the spacecraft instrument panel using modal analysis, as well as a quasi-static calculation of the panel under study, confirming the effectiveness of the proposed changes in the panel design. The instrument panel is a three-layer honeycomb structure consisting of two aluminum plates and a honeycomb filler. Cellular panels have a number of advantages: a small weight of the structure, high rigidity, specific strength. Using finite element modeling, the range of natural frequencies and vibration patterns of the instrument panel was determined, which made it possible to determine the optimal location of the panel attachment points to the spacecraft body to increase the lower limit of the natural frequency range and increase its carrying capacity.