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spectral radiation intensity
相关语句
  光谱辐射强度
     Then a spectral radiation intensity expression was also derived for the thermal cavity-plume combination radiation.
     同时还推导了热空腔—喷气流组合辐射的光谱辐射强度的表达式。
短句来源
     The spectral transmission of gas were calculated by the SLG model and air by LOWTRAN7.0.The spectral radiation intensity outgoing plume surface,and that after being absorbed by the air path of 0.88? km was calculated. By comparing,the results was basically accord with that in reference.
     给出一台推力为1.125×106N的液体火箭发动机喷焰表面以及经过海平面0.88 km水平路程大气衰减后的光谱辐射强度,经比较与参考文献给出的结果基本一致.
短句来源
  相似匹配句对
     A SPECTRAL MODEL FOR SOLAR RADIATION
     太阳短波辐射分光谱计算模式
短句来源
     SPECTRAL DISTRIBUTION OF SOLAR RADIATION ON ANTARCTICA
     南极大气外太阳辐射的能谱分布
短句来源
     ray radiation.
     因而可能是一种潜在的辐射防护剂。
短句来源
     THE SPECTRAL REPRESENTATION
     谱表示
短句来源
     Radiation and apoptosis
     电离辐射与细胞凋亡
短句来源
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  spectral radiation intensity
The spectral emissivity was determined by comparing the spectral radiation intensity of the sample to that of the fixed-point blackbody over the wavelength range 550 to 750 nm.
      


This paper describes a spectroscopic method of determination ofthe temperature distribution of a flame jet. This method is used to measurethe lateral integrated spectral intensity profile of the flame jet Iλ_g(x), thespectral radiation intensity of a reference source behind the flame Iλ_s, and thecombined spectral radiation intensity profile Iλ_(gs) (x) of the flame superposedby the reference source observed through the flame. The integrated spetral transmission of flame can be...

This paper describes a spectroscopic method of determination ofthe temperature distribution of a flame jet. This method is used to measurethe lateral integrated spectral intensity profile of the flame jet Iλ_g(x), thespectral radiation intensity of a reference source behind the flame Iλ_s, and thecombined spectral radiation intensity profile Iλ_(gs) (x) of the flame superposedby the reference source observed through the flame. The integrated spetral transmission of flame can be evaluated by substracting the intensity of twoscans and dividing it by the intensity of the reference source. Thesemeasurements which can be realized by using of grating monochromatorwith photomultiplier detector, are sufficient to determine the radial distribu-tion of the volume absorption and emission coefficients. The volume absorptioncoefficient profile has been determined by Barr's method based of a numericaltechnique for performing an Abel inversion on the observed intensityprofile. Once the radial profile of the absorption coefficient has been obtainedan iterative procedure is used to find the radial profile of the volume emissioncoefficient. Finally the ratios of these two profiles are used to evaluate thetemperature radial profile of the flame jet using Kirchhoff's Law and plan-ck's Law with the assumption of local thermodynamc equilibrium. Compa-rison of flame core. temperature measured by this spectroscopic method withthat by the transient thermocouple method indicated that the results of thesetwo measurments are in quite good agreement with each other.

本文简述用光电光谱仪法测定轴对称火焰温度分布的基本原理。由直接检测的火焰射流弦向钠D线的光谱积分辐肘强度分布I_(λg)(x)、参考光源的光谱辐射强度I_(λs)和迭加参考光源透过的火焰光谱积分总辐射强度分布I_(λgs)(x),然后分别用积分方程变换加迭代计算法和等温阶跃串联火焰近似计算法,逐步算出光谱体积吸收系数径向分布K_λ(r)和光谱体积发射系数径向分布ε_λ(r)。最后假设存在局部热平衡条件,由基尔霍夫定律和普朗克定律来得火焰射流的径向温度分布T(r)。用串联火焰近似计算法求得的中心温度与用动态热电偶测得的中心温度基本相附。

The problem of thermal cavity (afterburning cylinder of a jet engine) and plume combination radiation is considered.The radiative transfer differential equation was derived.The solution of the differential equation was then obtained under the radiative boundary conditions.The detailed solution of radiative transfer equation was elaborated for a thermal cavity,filled with high temperature gas and surrounded with multiple walls of different temperatures.The detailed spectral radiant intensity expression was also...

The problem of thermal cavity (afterburning cylinder of a jet engine) and plume combination radiation is considered.The radiative transfer differential equation was derived.The solution of the differential equation was then obtained under the radiative boundary conditions.The detailed solution of radiative transfer equation was elaborated for a thermal cavity,filled with high temperature gas and surrounded with multiple walls of different temperatures.The detailed spectral radiant intensity expression was also given for the back hemisphere.Then a spectral radiation intensity expression was also derived for the thermal cavity-plume combination radiation.Finally a numerical example was given.Its results show that the spatial distribution of the thermal cavity-plume combination radiation has a pear shape just like that of measurements.The spectral distribution is also consistent with measurements.

讨论了热空腔(喷气发动机的加力筒)和喷气流的组合辐射问题,推演了组合辐射的辐射传输微分方程,导出了有边界辐射条件下的解。讨论了由多个温度不同的壁面组成且腔内充满高温燃气的热空腔辐射传输方程解的具体形式,导出了它向后半球的光谱辐射强度的表达式;同时还推导了热空腔—喷气流组合辐射的光谱辐射强度的表达式。最后给出算例,算例结果表明,热空腔—喷气流组合辐射的空间分布具有与实测分布较一致的梨形包络,其光谱分布也与实测的光谱分布的一致性较好。

The infrared characteristics of liquid rocket plume,in spectrum 2~5?μm,was calculated using integral method of radiation transfer equation.The absorption of air at sea level was considered.The temperature and mole fraction of components in the cylindrical plume vary in axial and radial directions.The absorption and emission of gaseous components: H_2O,CO_2,CO were considered in computation.The spectral transmission of gas were calculated by the SLG model and air by LOWTRAN7.0.The spectral radiation intensity...

The infrared characteristics of liquid rocket plume,in spectrum 2~5?μm,was calculated using integral method of radiation transfer equation.The absorption of air at sea level was considered.The temperature and mole fraction of components in the cylindrical plume vary in axial and radial directions.The absorption and emission of gaseous components: H_2O,CO_2,CO were considered in computation.The spectral transmission of gas were calculated by the SLG model and air by LOWTRAN7.0.The spectral radiation intensity outgoing plume surface,and that after being absorbed by the air path of 0.88?km was calculated.By comparing,the results was basically accord with that in reference.

用传输方程积分法计算液体火箭喷焰在光谱2~5μm的红外特性,并考虑了经过海平面一定长度的水平路程后大气对液体火箭喷焰辐射的衰减作用.计算喷焰的形状为圆柱形,温度和组分的摩尔分数沿轴向和径向变化.计算中考虑气体组分H2O,CO2,CO的吸收与发射,喷焰内燃气的光谱透过率用SLG模型计算,大气的光谱透过率用LOWTRAN7.0计算.给出一台推力为1.125×106N的液体火箭发动机喷焰表面以及经过海平面0.88 km水平路程大气衰减后的光谱辐射强度,经比较与参考文献给出的结果基本一致.

 
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