Side plasma flow and stagnation of a conical blunt body vehicle under an axial dipole magnetic field

The study of plasma flow under the thermal protection magnetic field of reentry vehicle is helpful to verify the magnetic control thermal protection technology and further understand its flow law. By solving hypersonic magnetohydrodynamics equations and combining with dipole magnetic field conditions, the plasma flow mechanism of radio attenuation measurement (RAM)-CII (RAM Experiment) spacecraft at 61 km altitude is analyzed and compared with orbital reentry experiment (OREX) spacecraft under the same conditions. The results show that the plasma flow of RAM-CII is more complex than that of OREX, and there are several regions with different Lorentz force directions near the aircraft, which play the role of plasma ejection and adsorption. Under the action of Lorentz force, the side flow of the aircraft will be separated and reattached, and the fluid stagnation zone will be generated. The results show that for different shapes of aircraft, the flow laws caused by magnetic thermal protection technology are different, and the side flow may be greatly affected.