ポリイミド系宇宙用多層膜熱制御材料の熱放射特性の推算

概要

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Thermal control materials covering a spacecraft for Mercury orbiter mission are required to have stability against the severe thermal environment. This paper describes a prediction method for the temperature dependence of the total hemispherical emittance and the incident angle dependence of the solar absorptance α of multilayer thermal control materials. The present method is performed by using data for the optical constants of thin polyimide films and vapor-deposited metal in the wavelength region from 0.25 to 100μm. This paper provides the values of in the temperature range from 173 to 773K and α in the incident angle region from 0 to 90° of three types of multilayer thermal control material, which is based upon a thin polyimide film coated with aluminum on the back surface. The predicted results are compared with the measured ones. These results agree well each other on the whole. According to these agreements, it has been demonstrated that this prediction method is an effective means to predict thermal radiation properties of multilayer thermal control materials.
社団法人日本航空宇宙学会の論文
2002-04-05