Heat Transfer Analysis And Optimizing Design Of Multi-layer Isolate Structure For Near Space Aircraft

It is necessary to take thermal protection measures for hypersonic aircraft which has essential surface aerodynamic heating problems in high speed flight. However, the thermal protection of hypersonic aircraft solved the thermal problems, it increased the weight of aircraft. Thus, the structure's weight optimization and thermal protection of hypersonic aircraft is always the focus of the research of hypersonic aircraft. In view of this, the heat transfer analysis and optimizing design of hypersonic heat insulation structure are very important to the design of hypersonic aircraft.In this paper, the hypersonic vehicle's two dimension model is calculated by using the hypersonic simulation software CFD++. The numerical results are compared with the experimental results to determine the correctness of the simulation calculation method. After that,using the same simulation calculation method to calculate the Ma equal to 6 aerodynamic heating situation of hypersonic aircraft with typical shape, and the temperature field around the aircraft is compared and analyzed at 0 degrees, 2 degrees and -2 degrees. On the basis of this, the heat transfer analysis is carried out on the typical multi-layer heat insulation structure. The influence of different material layer thickness on the thermal insulation performance and weight loss of multi-layer insulation structure in using high temperature resistant material as structure layer.Finally, multi objective genetic optimization algorithm based on ANSYS Workbench platform was used to optimize the multi-layer insulation structure, which could be applied to the multi-layer insulation structure of typical hypersonic aircraft. After optimization, the heat insulation effect is the best and the structure's weight is the lightest.