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以航天飞行器的复合材料隔热层为研究对象,提出了基于遗传算法和有限元(FEA)参数化分析的优化设计方案。其中,以遗传算法为优化方式,基体材料层、隔热材料层、耐烧蚀陶瓷层的厚度为设计参数,隔热层的组合厚度及各层热应力为优化目标;优化过程中调用ANSYS软件对种群中个体进行有限元参数化分析,并将分析结果返回遗传算法程序中构造适应度函数。设计中通过改变遗传算法的种群范围、遗传代数、交叉率以及变异率,最终得到数种隔热层的结构方案,相应结构可以保证在满足各层材料的热应力低于其许用应力的情况下,隔热层组合厚度最小。
Taking the composite thermal insulation of a spacecraft as a research object, an optimized design scheme based on genetic algorithm and finite element (FEA) parametric analysis is proposed. Among them, taking the genetic algorithm as the optimization method, the thickness of the base material layer, the insulation material layer and the erosion-resistant ceramic layer is a design parameter, the combined thickness of the heat insulation layer and the thermal stress of each layer are the optimization objectives; in the optimization process, ANSYS software Finite element parametric analysis of individuals in the population is carried out, and the analysis results are returned to the genetic algorithm program to construct the fitness function. In the design, by changing the population size, genetic algebra, crossover rate and mutation rate of genetic algorithm, several kinds of heat insulation layer structure schemes are finally obtained. The corresponding structure can ensure that when the thermal stress of each layer material is lower than the allowable stress Under the minimum thickness of the insulation layer combination.