摘要: As a novel thermal protection technique for hypersonic vehicles, Magnetohydrodynamic (MHD) heat shield system has been proved to be of great intrinsic value in the hypersonic field. In order to analyze its effective working condit... 展开 As a novel thermal protection technique for hypersonic vehicles, Magnetohydrodynamic (MHD) heat shield system has been proved to be of great intrinsic value in the hypersonic field. In order to analyze its effective working condition during the hypersonic reentry flight, a physical model is constructed for the MHD heat shield system equipped with a normal solenoid magnet. By taking the real gas effect into account, numerical simulations are conducted for the thermochemical nonequilibrium MHD flow field around a typical hypersonic reentry vehicle, namely Oribital Reentry Experiment (OREX) capsule. After that, the performances of MHD thermal protection and MHD shock control under different flight conditions are analyzed. Results show that, for the OREX capsule, the MHD heat flux mitigation is not obvious until the magnetic interaction parameter is above 1.0 with a corresponding flight altitude above 55.74 km and a flight Mach number above 17.41. Considering that the magnetic interaction parameters of the high altitude cases are larger, the saturation effect of MHD heat flux mitigation is stronger. Moreover, the performance of MHD shock control is also improved with the increase of flight altitude, but the saturation effect of shock control is absent. The performance of the system can be significantly improved by seeding the inflow with potassium particles. There also exists a saturation effect in the seeding amount, and an adequate seeding mass fraction is suggested to be 0.01. 收起