Simulation And Test Of Aeroheating And Thermal Response Of TPS For Hypersonic Vehicle

Hypersonic vehicle is an important direction of development of aerospace technology,which will play an important role in national defense and security in the future. Such aircrafts suffer extremely thermal environment during flight, so the forecast of aerodynamic heating and thermal protection system (TPS) design is one of the key technologies of hypersonic vehicle design and manufacture.The aeroheating of the hypersonic vehicle is coupled with thermal response of the TPS. Using numerical method to analyse the coupled problem needs building simulation model of hypersonic vehicle. it involves high-temperature chemical non-equilibrium boundary layer, turbulence model and the heat transfer model of complexity structure with new type material. And solving these difficulties need spend a lot of computer resources and time; Simulating hypersonic flight in wind tunnel, even if without considering it will spent a large number of human and financial resources, must face the challenge to build the construction can simulate flight conditions in Mach number more than 10. Taking into account the focus of our research is the thermal environment of aeroheating and the thermal response of the TPS, as to by which way to achieve this thermal environment is not important, as long as the heat energy absorbed by the TPS is equal to the real heat energy during flight, the thermal response of the TPS will be able to reproduce. Therefore, it is a better way that through infrared radiation simulating the heat flux of aeroheating, which is easy to implement with low technical difficulty, and test-bed can form as the shape of the test model flexibility. In this paper, using engineering algorithm as control program of the test system, inputting measured thermal response parameters of the TPS into the control program to calculate the aeroheating , amd loading heat by infrared radiation, accomplishing the coupling analysis of aeroheating and thermal response.This paper is mainly for simulating thermal environment and thermal response of TPS when hypersonic vehicle re-entry. And aim to design the test platform which can accurately calculate and simulate the aeroheating environment, build a reasonable model of TPS for hypersonic vehicle. In this paper, the following researches are done:1,study thermal environment of flight and engineering algorithm to carry out calculation of aeroheating2,study insulation mechanism of thermal protection system and insulation materials to design the thermal protection system3,Study thermal measurement techniques to design measure systems and high-speed data acquisition system4,Study fuzzy PID control technology to achieve fuzzy control of heat load, improve the response rate and loading precision of the load devices5,Develop software for measuring and control system . The software can load track data of hypersonic vehicle, calculate transient aeroheating, load the aeroheating, and realize high-speed measurement and data treatment, automaticallyIn this paper, the test system can measure the thermal conductivity of the material used by hypersonic vehicle, and implement test about aeroheating coupled with thermal response of TPS, forecast the thermal environment and optimize the design of the TPS. The research shows this system can improve the efficient at initial design stage, and enrich the means for design of the hypersonic vehicle.