Case Study on Selecting Optimal Design for Main Central Cone of LEO Satellite
Keywords:
Satellite, Structure, Central Cone, buckling, modal analysis, DesignAbstract
Satellite structures must endure the stresses encountered during and after launch while providing support for additional equipment. The central cone plays a crucial role in achieving this objective, serving as one of the key structures of the satellite. The primary aim of this study is to assess and choose the most effective design for the central cone intended for Low Earth Orbit satellites. To fulfill this objective, six distinct central cone designs were created using Siemens NX, all subjected to identical boundary conditions. These designs encompass three different concepts which are grid, sandwich, and semi-monocoque utilizing both CFRP and aluminum materials. Each cone underwent a comprehensive evaluation, comparing factors such as weight, stiffness, buckling, and stress strength through analyses conducted with Simcenter 3D. In the second phase of the study, some design iterations were made to make the selected central cone more optimum for Low Earth Orbit satellites by performing same analyzes and applying same boundary conditions with previous phase.
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