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The satellite structural mass is considered a crucial parameter during the process of satellite structural design. This article discusses the structural configuration, design, and analysis of a small satellite. | Nội dung Text Configuration design and modeling of an efficient small satellite structure Engineering Solid Mechanics 8 2020 7-20 Contents lists available at GrowingScience Engineering Solid Mechanics homepage www.GrowingScience.com esm Configuration design and modeling of an efficient small satellite structure Ali Aborehaba Mohammed Kassema Ahmed Farid Nemnema M. Kamela and Hisham Kamelb a Aircraft Mechanics Departement Military Technical College Cairo Egypt b Automotive Departement Military Technical College Cairo Egypt A R T I C L EI N F O ABSTRACT Article history The satellite structural mass is considered a crucial parameter during the process of satellite Received 10 July 2019 structural design. Sandwich structures acquire a considerable role in minimizing such mass while Accepted 3 September 2019 maintaining structural integrity. This article discusses the structural configuration design and Available online analysis of a small satellite. A small Earth remote sensing satellite is chosen from the published 3 September 2019 Keywords data as a case study. Its structural design configuration is of a rectangular box that is based upon Configuration design metallic alloys. Through a comprehensive study the most suitable design configuration for the Satellite structure given mission is selected. A contribution has been made in developing a novel hexagonal primary Small satellite structure that is based upon Aluminum honeycomb sandwich panels. The satellite configuration Sandwich structure process and structural design procedure are thoroughly presented. The finite element modeling of honeycomb sandwich panels according to sandwich theory is introduced. Such modeling is validated numerically in comparison with published data. The analysis process is implemented using finite element analysis considering the loads during the ground and launch phases. The proposed structural design results in a significant mass reduction of 15 when compared with the baseline case .
