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针对固面天线反射器在轨运行时自身结构因素受环境温度变化引起热变形的问题,以一口径为1.2 m的星载蜂窝夹层结构固面反射器为研究对象,首先采用有限元仿真软件详细分析了温度由20℃降到-80℃时,不同蒙皮材料、胶层厚度、蜂窝刚度和蜂窝的热膨胀系数(CTE)对反射器热变形型面精度均方根(RMS)的影响规律,其次采用热压罐成型工艺制备了M55J和T300蒙皮材料的两种典型蜂窝夹层结构反射器对仿真结果进行试验验证。结果表明:M55J蒙皮材料发射器的热变形比T300蒙皮材料反射器的小,同时发现发射器的热变形与胶层的厚度基本呈线性关系,胶层厚度越薄,反射器的热变形越小,且当胶层厚度一定时,蜂窝的热变形占主导因素,其刚度变化值提升2倍时影响趋势突变,此时蒙皮刚度对蜂窝热变形的抑制作用明显,当蜂窝的热膨胀系数改变11倍时,反射器热变形均方差(RMS)改变值大于80%。经试验测得环境温度由20℃降到-80℃时两种典型反射器的热变形的RMS值与仿真计算差值分别为15.7%、15.2%,证明仿真结果可靠,可通过优化相应的结构参数为星载天线反射器的设计提供参考。
Aiming at the problem that the self-structural factors of solid-state antenna reflectors are subject to thermal deformation caused by the change of ambient temperature when the orbiting reflector is in orbit, a solid-surface reflector with a diameter of 1.2 m on-board honeycomb sandwich structure is taken as the research object. Firstly, finite element simulation software The effect of different skin materials, adhesive layer thickness, honeycomb stiffness and honeycomb CTE on the root mean square (RMS) accuracy of reflector thermal deformation profile was analyzed when the temperature dropped from 20 ℃ to -80 ℃. Secondly, two typical honeycomb sandwich reflectors with M55J and T300 skin materials were fabricated by autoclave molding process to verify the simulation results. The results show that the thermal deformation of M55J skin material emitter is smaller than that of T300 skin material reflector. At the same time, it is found that the thermal deformation of emitter is basically linear with the thickness of the adhesive layer. The thinner the thickness of the rubber layer, The smaller the thickness of the honeycomb, the more the thickness of the honeycomb is, the thermal deformation of the honeycomb is the dominant factor. When the stiffness variation of the honeycomb increases by 2 times, the trend of the honeycomb deformation changes suddenly. When changing 11 times, the mean square error (RMS) change of the reflector is greater than 80%. The experimental results show that the difference between RMS value and simulation value of the thermal deformation of two typical reflectors is 15.7% and 15.2% when the ambient temperature is lowered from 20 ℃ to -80 ℃, respectively. The results prove that the simulation results are reliable and can be obtained by optimizing the corresponding structure The parameters provide reference for the design of the satellite antenna reflector.