火星环绕器高增益天线在轨热设计及波束指向影响分析  

On-orbit Thermal Design and Beam Pointing Error Impact Analysis of High Gain Antenna of Mars Orbiter

作　　者：张顺波 任红宇 靳春帅 刘伟栋 李春晖 李勇 ZHANG Shunbo;REN Hongyu;JIN Chunshuai;LIU Weidong;LI Chunhui;LI Yong(Shanghai Aerospace Electronic Technology Institute,Shanghai 201109,China;Shanghai Institute of Satellite Engineering,Shanghai 201109,China)

机构地区：[1]上海航天电子技术研究所,上海201109 [2]上海卫星工程研究所,上海201109

出　　处：《深空探测学报（中英文）》2023年第1期44-51,共8页Journal Of Deep Space Exploration

基　　金：“天问一号”火星探测任务。

摘　　要：梳理了火星环绕器2.5 m口径高增益天线在热设计、–195℃超低温环境适应性及热变形指向偏差评估分析与验证方面存在的技术难点,开展了设计和验证工作。基于热设计状态对天线在轨工作过程中典型工况下的温度场和热变形分布进行了仿真分析,并研制了一套大口径反射面天线真空热变形测量系统,完成了热变形测试验证。基于热变形数据,采用半物理仿真分析方法对高增益天线热变形后的波束指向偏差进行了评估分析。结果表明,热变形导致的波束指向偏差最大为0.028°,增益损失不超过0.5 dB,指向偏差和增益损失均在设计裕度范围内。经在轨测试,天线增益指向性能测试值与预估值吻合,有效验证了天线热设计和验证方法的准确性。The technical difficulties on thermal design,suitability under–195℃ultra-low temperature condition,analysis and verification of beam pointing error caused by thermal distortion for high gain antenna of Mars orbiter were summarized,and relevant design and verification were completed.Based on thermal design state,the temperature field and thermal distortion of high gain antenna under typical working conditions during the operation on orbit were simulated and analyzed.A vacuum thermal distortion measurement system for large aperture reflector antenna was designed and developed.According to vacuum thermal distortion test data,the beam pointing error was evaluated by a hybrid simulation method.The results show that the maximum beam pointing error is 0.028°,and the gain loss is less than 0.5dB,both of which are within the design margin.The on-orbit test results confirm that the beam pointing performance is consistent with the evaluation,which effectively verifies the accuracy of the thermal design and verification method.

关 键 词：火星环绕器 高增益天线 超低温 热变形 波束指向偏差 

分 类 号：V416.6[航空宇航科学与技术—航空宇航推进理论与工程]