为了保证星载天线的在轨工作,需要严格限制天线的热变形.文章参考国外先进天线设计案例并考虑国内生产工艺,以某卫星抛物天线反射面为研究对象,采用全碳纤维复合材料夹层结构设计新型天线反射面构型.首先,给出天线型面误差的计算过程来反映天线热变形程度;然后,基于正交试验法,对某卫星的天线反射面型面误差值影响因素进行分析;最后,在此基础上分别对蒙皮与芯层完成低热膨胀系数的优化设计.仿真结果显示:文章设计的全碳纤维材料天线夹层结构因热变形而产生的型面误差仅约为原先设计的全铝反射面的1/6,证实了全碳纤维材料天线夹层结构在低变形方面的优势及此优化设计方案的可靠性.%To ensure the work of space-borne antenna,the thermal deformation is restricted.Re-ferring to foreign advanced cases and taking care of domestic existing process technology,the ar-ticle puts space-borne parabolic antenna reflector as the research obj ect and designs a new reflec-tor,the core and the skin of which are both made of CFRP.Firstly,the profile error is calculated to reflect the degree of thermal deformation.Then,the influence factor of thermal deformation is analyzed based on orthogonal test.Lastly,on the basis of this,the CTE design of the skin and the core is optimized.The simulation results show that the profile error of the CFRP parabolic antenna reflector designed in this paper is 6 times lower than that is designed before and made of aluminum alloy.The advantage of the CFRP sandwich structure antenna reflector and the reliabi-lity of optimized scheme designed in this paper can be proved based on the above analysis.
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