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空间飞行器天线
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  spacecraft antenna
     Application of Finite Element Method in the Thermal Analysis of Spacecraft Antenna Reflector
     有限元法在空间飞行器天线反射器热分析中的应用
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  相似匹配句对
     Optimum Antenna Polarizations for Target Discrimination in Clutter
     跟踪天线
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     Millimetre Wave Antennas
     毫米波天线
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     Application of Finite Element Method in the Thermal Analysis of Spacecraft Antenna Reflector
     有限元法在空间飞行器天线反射器热分析中的应用
短句来源
     Design of Radio Wave Receiving Antenna with Low Frequency and Broad Band for Space Vehicle
     空间飞行器低频率宽频带射电波接收天线的设计探讨
短句来源
     ATTITUDE IDENTIFICATION OF SPACECRAFT
     空间飞行器的姿态识别
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  spacecraft antenna
As known, spacecraft antenna design is an everdemanding task, due to the tight requirements on performance and the small available space.
      
Both methods have been improved and adapted to the special needs of spacecraft antenna analysis.
      
Replacing the 5-foot-diameter spacecraft antenna with an omni directional antenna raises the transmitter power output requirement to 1watt.
      
This is reasonable in that, for example, pointing the spacecraft antenna is functionally similar to pointing a ground station antenna.
      
These signal nulls occur when the orientation of the spacecraft antenna with respect to the ground station is in the 80to 90-deg range.
      
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The finite element method is an attractive means for the thermal analysis of spacecraft components with high thermal stability requirements.The application of finite element method in the thermal analysis of spacecraft antenna reflector is discussed.The on orbit steady and transient temperature profiles of a spacecraft parabolic antenna reflector are calculated by using finite element method.The necessary temperature data were provided for the thermal distortion analysis and the selection of the thermal control...

The finite element method is an attractive means for the thermal analysis of spacecraft components with high thermal stability requirements.The application of finite element method in the thermal analysis of spacecraft antenna reflector is discussed.The on orbit steady and transient temperature profiles of a spacecraft parabolic antenna reflector are calculated by using finite element method.The necessary temperature data were provided for the thermal distortion analysis and the selection of the thermal control measures.

有限元方法是求解对热稳定性要求较高的空间飞行器部件温度场的一种行之有效的方法。文章给出了空间飞行器天线反射器热分析的有限元求解方法,应用有限元法计算了某卫星抛物面天线反射器的在轨稳态和瞬态温度场,为进一步的在轨热变形计算以及热控方案的选择提供了必要的温度数据。

 
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