Engineering calculation and analysis of aerodynamic heating for hypersonic rocket sled

Abstract

Abstract Aerodynamic heating and temperature distribution are one of the problems that must be considered in the design of hypersonic rocket sled. In order to evaluate the aerodynamic heating environment of hypersonic rocket sled, the typical monorail rocket sled with cone cylinder combination is taken as the research object, the aerodynamic heating calculation methods such as Modified Newton Theory, Reynolds Analogy Theory, Reference Enthalpy Method and Fourier’s Law of Heat Conduction are used, and the temperature variation law of rocket sled conical surface under Mach 5 and Mach 7 ballistic is calculated and compared with the measured data in the literature to verify the accuracy of the calculation program. The engineering calculation method can provide a reliable design basis for the rocket sled structure and thermal protection configuration. The analysis of the calculation results shows that when the speed of hypersonic rocket sled exceeds Mach 5, serious thermal heating problem cannot be ignored, and protective measures such as thermal protective materials and helium channel should be taken.