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针对再入飞行器激波层辐射加热,应用有限体积法计算辐射传输方程,引入了一种边界处理方式——虚网格方法,根据化学非平衡流场数据,计算出飞行器表面辐射加热热流。通过分析发现:采用虚网格方法处理辐射传输边界,能够确保真正的边界条件得到应用,满足真实的物理意义,且辐射传输计算的空间网格、立体角网格、初始温度值的收敛性很好,计算结果精度误差小于2.5%。利用虚网格方法计算飞船再入返回时的辐射加热,结果表明计算所得壁面辐射热流与其他研究者辐射热流计算结果符合良好。
Aiming at the radiative heating of the reentry vehicle shock wave, a finite volume method is used to calculate the radiation transmission equation. A boundary treatment method - the virtual grid method is introduced. Based on the chemical non-equilibrium flow field data, the radiation heating heat flux of the aircraft surface is calculated. Through the analysis, it is found that using the virtual grid method to deal with the radiation transmission boundary can ensure that the real boundary conditions are applied and satisfy the true physical meaning. The spatial grid, the solid angle grid and the convergence of the initial temperature value of the radiation transmission are very Well, the error of calculation result is less than 2.5%. Using the virtual grid method to calculate the radiative heating when the spacecraft reentry and returning, the results show that the calculated wall radiation heat flux is in good agreement with other researchers’ radiative heat flow calculation results.