Optimum Design of a microsatellite structure with vibration constraint

One of the most critical design points in satellites is to achieve the minimum mass (or weight) by meeting all the requirements and constraints (constraints on strength, location and pointing vibrations). In this regard, the structure can play a very important role because the structural designer has more freedom of action in determining the design of the structure compared to other subsystems. In the present study, the process of designing the structure of a small satellite, with the aim of achieving the lowest possible weight and maintaining the prevailing requirements (vibration constraint), has been investigated. The process used to achieve the above goal is a change in the geometric dimensions of the structure. Satellite modeling steps with all subsystems have been performed in solidwork software and in ANSYS software, modal analysis, strength and random vibrations have been performed. Also, using the optimization of genetic algorithm in this software, the geometric parameters of the structure such as the thickness of the frame have been obtained in such a way that the structure has reached the lowest possible weight and by satisfying the prevailing conditions for vibration constraints, strength and random vibrations. The results show that by choosing the right thickness of frame, the weight and frequency of the first satellite mode can be significantly reduced, and at the same time, the optimal final structure satisfies all the constraints applied by the launcher and has sufficient strength and rigidity. Is.