Abstract:
This paper presents the initial design scheme of a clamp band system between the minisatellite and the launch vehicle. The finite element model (FEM) of this product is built. By performing an axial compression test, the validity of the finite element model is verified. After that, replacing the satellite with a concentrated mass point at the center of the mass, the rationality of the main structure design is validated through the modal analysis and the static analysis. It is shown that the structure has a large margin of safety and a potential for optimization. The sensitivity analysis and the design optimization are carried out by using the total mass of the satellite as the objective function, the component’s thicknesses of the main structure as the design variables, the natural frequencies in the lateral, the longitudinal and the torsional directions keeping unchanged and the strength of the main structure meeting the design requirements as constraints. The optimization reduces the total mass of the product by 11 %.
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