Certificate of Registration Media number Эл #ФС77-53688 of 17 April 2013. ISSN 2308-6033. DOI 10.18698/2308-6033
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Development of a spacecraft load bearing structures using topology optimization for two versions of manufacturing technologies

Published: 28.09.2018

Authors: Borovikov A.A., Tushev O.N.

Published in issue: #9(81)/2018

DOI: 10.18698/2308-6033-2018-9-1807

Category: Aviation and Rocket-Space Engineering | Chapter: Design, construction and production of aircraft

The article compares the approaches to the development of load bearing structures using topology optimization (TO) for two manufacturing options. As an example of the design, the spacecraft adapter is used. In the first variant, a construction for manufacturing by additive technologies is intended, in the second — for manufacturing by traditional methods (machining, welding, etc.). As a problem solver, the MSC Nastran software package is used. Also, the article considers the problems of using the TO in the development of the design and looks at ways to solve them. The TO method, design variables, constraints and objective function are indicated. Recommendations for the preparation of the initial model and the choice of the parameters of the TO algorithm for the variants considered and a detailed description of each stage of the design development are given. A comparison of the obtained structures with a description of the advantages and disadvantages of the approaches is shown. According to the results of the analysis, the conclusions on the use of the TO for the design development of the spacecraft adapter are made. In addition, recommendations on the use of the TO in the manufacture of construction by traditional methods in conditions of insufficient information about the product being developed are given

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