论文部分内容阅读
飞行器以很高的马赫数再入大气层时 ,头部激波层、尾迹的气体辐射产生的紫外、可见、红外特征信号 ,是地面监测和反导制导系统探测、识别的主要依据 ;同时 ,头部气体层热辐射也是再入体壁面加热热流的重要源项。激波层内高温气体吸收系数是目标紫外、可见光、红外辐射特性计算、热防护计算和气动流场辐射场耦合计算的基本参数。本文分析了再入过程中高超声速稀薄气体流的非平衡现象 ,采用三温度模型 (电子能温度 Te、振动能温度 TV、转动和平动能温度 TR)来表征激波层内非平衡态的气体组份各个能级占有数分布 ,并由原子分子辐射理论直接计算 N2 ,N+ 2 ,N,N+ ,O2 ,O+ 2 ,O,O+ ,NO,NO+和 e-等 1 1种主要空气组元各种能级跃迁对辐射的贡献 ,最终得到平稀和非平衡高温空气吸收系数计算模型。计算结果可见光区与试验结果符合较好 ,紫外、红外区结果稍差
When the aircraft reenters the atmosphere at a high Mach number, the ultraviolet, visible and infrared characteristic signals generated by the gas radiated from the shock layers and wake of the head are the main basis for the detection and identification of the ground monitoring and anti-missile guidance systems. At the same time, the head Department of gas layer heat radiation is re-entry wall heat flow is an important source of heat. The absorption coefficient of high temperature gas in the shock wave layer is the basic parameter for the calculation of target UV, visible light, infrared radiation characteristics, thermal protection calculation and aerodynamic field radiation field coupling calculation. In this paper, we analyze the non-equilibrium phenomenon of the hypersonic lean gas flow during reentry. The three temperature models (electron temperature Te, vibrational temperature TV, rotational and kinetic temperature TR) are used to characterize the non-equilibrium gas components The distributions of the energy levels in each energy level and the direct calculation of the energy of 1 1 main air species such as N2, N + 2, N, N +, O2, O + 2, O, O +, NO, NO + and e- Level transition to the contribution of radiation, and finally get the calculation model of flat and non-equilibrium high temperature air absorption coefficient. Calculation results visible region and the test results in good accordance with the UV, the infrared region results slightly worse