Case study on selecting optimal main central cone of low earth orbit satellite

Abstract

In this thesis, determination and selection of the most optimum central cone design concept for low orbit satellites of 1000 kg and above from large class satellites is explained. The designs of the cone and cone assembly parts in the study were made with Siemens NX, and the analyzes (modal analysis, static structural analysis, buckling analysis) applied for comparisons were made with Simcenter 3D. The study consists of two stages, in the first stage, a total of 6 cones, 3 different design concepts (semi-monocoque, grid, sandwich) from 2 different materials, Aluminum and CFRP, were compared and two cones were selected after the return-lump study. In the second stage, after the iterations on these two cones, the most optimum central cone design was decided by repeating the return-lump study. In comparisons, mass, stiffness, static strength and buckling strength were determined as criteria.