By using a self-developed transient aerodynamic thermal simulation system of high-speed aircraft

the heat-shielding performance of metallic honeycomb panel structure was tested at different transient thermal shock rates ranging from 5℃/s to 30℃/s

with the maximum instantaneous temperature reaching 950℃. Furthermore

a three-dimensional finite element method was established to determine the heat-shielding performance of the metallic honeycomb panel structure at different simulation environments with high thermal shock rates. The numerical calculation results coincide with the corresponding experimental results

verifying the credibility and effectiveness of the experimental methods and the numerical calculation approach. The tested metallic honeycomb panel structure exhibited slight planar flexure and deformation after the experiment in the high-temperature (950℃) environment; thus

in the context of high-speed flight vehicles

this structure is particularly suitable for structural components that must be made of lightweight materials with slight deformation in a high-temperature environment.