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介绍了热-结构耦合分析原理,并建立了空间充气可展薄膜天线的分析模型。给出热荷载和基本假定,计算了出其在低地轨道(LEO)下运行2个周期的温度场及时间温度曲线。并以此为基础进行了空间充气可展薄膜天线的热应力和热变形分析。空间充气可展薄膜天线的最高温度56.5℃,最低温度-92.8℃,同一时刻最大温差达93.10℃,最大Von Mises应力为931 511 Pa,最大Y向变形为9.666 mm,最大Y向变形RMS值为1.792 mm。对空间充气可展薄膜天线研制具有参考价值。
The principle of thermo-structure coupling analysis is introduced, and an analytical model of space-expandable membrane antenna is established. Given the thermal load and the basic assumptions, the temperature field and the time temperature curve of two cycles running under Low Earth Orbit (LEO) are calculated. Based on this, the thermal stress and thermal deformation of space-expandable membrane antenna were analyzed. The maximum temperature of the space-expandable membrane antenna is 56.5 ℃ and the minimum temperature is -92.8 ℃. The maximum temperature difference at the same time is 93.10 ℃, the maximum Von Mises stress is 931 511 Pa and the maximum Y-direction deformation is 9.666 mm. The maximum Y-direction deformation RMS value is 1.792 mm. It is of reference value to the development of space inflatable membrane antenna.