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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2021, Vol. 42 ›› Issue (7): 124501-124501.doi: 10.7527/S1000-6893.2020.24501

• Fluid Mechanics and Flight Mechanics • Previous Articles     Next Articles

Simulation of magnetohydrodynamic heat shield system on reusable launch vehicles

DING Mingsong, LIU Qingzong, JIANG Tao, DONG Weizhong, GAO Tiesuo, FU Yang'aoxiao   

  1. Computational Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China
  • Received:2020-07-06 Revised:2020-07-31 Published:2020-09-14
  • Supported by:
    National Key Research & Development Plan (2019YFA0405203); National Numerical Windtunnel Project

Abstract: Magnetohydrodynamic heat shield technology has a promising future in its application on hypersonic vehicles. Considering the mechanism of plasma formation, conduction of ionization species and transportation of energy and momentum in electromagnetic flow, which are involved in hypersonic magnetohydrodynamic control, we build the numerical simulation platform of the hypersonic magnetohydrodynamic heat shield by solving high temperature nonequilibrium flow governing equations coupled with Poisson’s equation of electromagnetic fields. Using the configuration of American space shuttle "Columbia" (OV-102) and 5 different magnetic field disposition cases, the application simulation of the magnetohydrodynamic heat shield system on the hypersonic reusable launch vehicle is systematically carried out. The results show that the hypersonic magnetohydrodynamic heat shield simulation platform built in this study has the ability to simulate the aerodynamic thermal environment of complex-shaped aircraft in dipole, solenoid, uniform magnetic fields and superposition magnetic fields, and the validation result is in good agreement with the reference or the flight test data; appropriate magnetic field disposition effectively reduces the surface heat flux of the space shuttle and improves the aerodynamic thermal environment, with the surface heat flux under typical condition decreased by more than 25%; the angle between the local magnetic field and the inflow decides the magnitude and direction of Lorentz force to some extent, exhibiting a strong influence on the effect of the magnetohydrodynamic heat shield system.

Key words: magnetohydrodynamic heat shield, reusable launch vehicles, hypersonic, high temperature gas effect, aerodynamic thermal

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