Joint design method for heat transport and bearing structure of hypersonic aircraft wing

• Main Authors: ZHAO HANG, BU XUEYU, GONG CHUNLIN, WU WEINAN, WANG JIANLEI, GOU JIANJUN, JIA SHUZHEN
• Format: Patent
• Language: Chinese; English
• Published: 12.05.2023
• Subjects: CALCULATING; COMPUTING; COUNTING; ELECTRIC DIGITAL DATA PROCESSING; PHYSICS

The invention provides a joint design method for a heat transport and bearing structure of a hypersonic aircraft wing. According to the topological optimization design of the hypersonic aircraft bearing structure based on the thermal-mechanical coupling condition and the wing heat transport path topological design based on the high-thermal-conductivity material, different reference schemes are provided on the bearing structure and the heat transport structure respectively, and the two schemes are designed in a combined mode. And a bearing/heat transport structure joint design scheme is obtained. Compared with a single bearing structure and a single heat transport structure, the bearing/heat transport structure has higher implementation possibility, higher bearing/heat transport capacity and lower mass cost, and provides a reference with more practical significance for structural design of hypersonic aircrafts. 本发明提出一种高超声速飞行器机翼的热输运和承载结构联合设计方法，基于热-力耦合条件下进行的高超声速飞行器承载结构拓扑优化设计以及基于高导热材料的机翼热输运路径拓扑设计分别在承载和热输运结构上提供不同的