过载发动机内壁面总热流和辐射热流的动态测量研究

In order to obtain the total heat flux and radiative heat flux on the inner wall of solid rocket motor (SRM) under overload condition, a double-point Gordon heat flux sensor equipped with sapphire window was designed to measure the total heat flux and radiative heat flux simultaneously. The variation of heat flux at the inner wall of the SRM was obtained. With the simulated overload test SRM on ground, the thermal test was carried out and the dynamic total heat flux and radiative heat flux on the inner wall of the test SRM with aluminized propellant were obtained. The test results show that the heat flux measuring equipment can withstand the harsh condition of high temperature, high pressure and strong erosion of molten particle gas in the SRM under overload conditions. The peak total heat flux density on the lower wall of the SRM test section is 7.5 MW·m^-2, the peak total heat flux density and radiative heat flux density on the side wall are 3.9 MW·m^-2 and 1.1 MW·m^-2, respectively. The test results could be used for validating the numerical simulation and providing the heat flux parameters for the refined design of the thermal protection system of SRM.