非均匀气动加热下隔热层结构的优化设计

Optimization Design of Heat Insulation Layer with Non-Uniform Heat Flow Loads

为获得非均匀气动加热条件下高超声速飞行器不同部位的合适的热防护系统厚度,发展了一种基于网格变形技术(ASD)的隔热层结构优化方法。以高超声速飞行器的复合材料隔热层结构为研究对象,采用有限元法在局部均布热流载荷、三角形均变热流载荷和二次函数热流载荷等作用条件下建立隔热层结构的热固耦合分析模型,提出了基于ASD技术与热固耦合分析相结合的结构轻量化设计方法。结果表明,基于网格变形技术能够快速有效地解决优化过程中的网格自动更新问题,并得到了光滑柔顺的厚度形状曲线,优化后更充分发挥了隔热层结构各层材料的承载能力。

An optimization method using arbitrary shape deformation（ ASD） technique is proposed in this paper to minimize the different thicknesses of composite heat insulation layer for a hypersonic vehicle with non-uniform aero-thermal loads. The thermo-structural coupling analysis of heat insulation layer for the hypersonic vehicle is studied by use of the finite element method,the effect of non-uniform heat flow load conditions such as partially uniform distributed load,triangular distributed load and quadratic function load on the lightweight of heat insulation layer are also analyzed,and lightweight design and parameterization analysis are proposed. The result shows that the presented method can automatically and rapidly update the finite elements meshes without any change of the mesh topology,the optimized smooth profile of thickness is obtained,and the load bearing capacity of multilayer insulation can be used more fully after optimization.