Technique employing the modified SIMP topology optimization method to determine the panel-to-panel support bracket position in a spacecraft body
Authors: Borovikov A.A., Tushev O.N.
Published in issue: #1(145)/2024
DOI: 10.18698/2308-6033-2024-1-2331
Category: Aviation and Rocket-Space Engineering | Chapter: Design, construction and production of aircraft
One of the most important requirements to spacecraft design is that of ensuring dynamic compatibility between the spacecraft and the launch vehicle, which consists in limiting the first fundamental tones of the spacecraft’s natural oscillations. Selecting the optimal number and installation positions of the panel-to-panel brackets connecting the spacecraft thermal honeycomb panels appears to be one of the approaches to solving the problem. “Manual” selection of the panel-to-panel brackets position is extremely ineffective and could be rather time consuming; therefore, the authors previously proposed a technique using the SIMP topology optimization method. Its essence lies in simulating the area of possible installation of the panel-to-panel brackets with the hexagonal finite elements and further topology optimization. However, using the SIMP method in standard formulation significantly increases the number of required design variables (at least three per one bracket), and, consequently, the computation time. This paper proposes modification to the SIMP method making it possible to use a minimum number of the design variables (one variable per one bracket). To illustrate efficiency of the developed apparatus, it uses a test problem as an example and compares the results obtained through the standard and modified versions of the SIMP method.
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