ПРОЕКТИРОВАНИЕ КРОНШТЕЙНА КРЕПЛЕНИЯ ОПТИЧЕСКОГО СОЛНЕЧНОГО ДАТЧИКА КОСМИЧЕСКОГО АППАРАТА С ИСПОЛЬЗОВАНИЕМ ТОПОЛОГИЧЕСКОЙ ОПТИМИЗАЦИИ

Abstract

Object of the research is a bracket of solar sensor mounting of spacecraft. Goal of the research is to reduce mass of the spacecraft bracket subject to strength and thermal resistance considerations. Mass reduction is carried using topology optimization based on SIMP-material model (Solid Isotropic Material with Penalization). Optimization problem statement is compliance(or strain energy) minimization subject to volume constraint. For strength and thermal analysis finite element method is used implemented in Ansys Workbench 18.2 software. As result of topology optimization, a material distribution data inside a design domain is obtained for different volume fractions. Based on that result new CAD-model has been developed using Siemens NX software which taking into account manufacturing constraints and providing manufacturing of the designed part using machining. Structural analysis performed for two load cases corresponds to launch regime and maximum lateral acceleration has shown that optimized structure has sufficient strength. Thermal analysis performed in Steady State Thermal software module has shown that thermal resistance requirement also met. As result of proposed research bracket mass reduction of 2.5 times has been achieved. Directions of future work has been outlined. Improvement of proposed method may consist from incorporating of coupled thermal-structure analysis into topology optimization process.