To design a thermal protection system of the hypersonic vehicle and verify the numerical computations

an aerodynamic heating transient test system together with its control software was designed and developed.The test system can measure the real-time heat flux and temperature on the surface

directly produce heat flow and temperature curve

according to hypersonic vehicle's trajectory.To simulate the heat transfer conditions at different altitudes and understand the effecting of the pressure

the test system used a vacuum chamber.To ensure that the conditions of the lower side of the thermal protection system could be simulated in a vacuum environment

a cooling bed was used

making the transient test method more reasonable and accurate.