摘要
针对某铰接肋式星载天线背架肋展开的可靠性进行了研究。根据该天线展开过程中两阶段运动机理的不同，分别对绳索在脱离铰接点前后两阶段建立了相应的力学分析模型。在此基础上，考虑到结构几何尺寸误差以及太空环境等随机性因素的影响，构建了基于力矩和累积功两种失效模式的可靠性功能函数，并利用一次二阶矩法推导出各功能函数的可靠性计算公式。对一个12米口径的天线的设计方案进行了可靠性分析，分析结果验证了所建模型的合理性和有效性。此研究为大型星载可展开天线结构系统的可靠性分析提供了必要的理论基础和参考依据。
The deployment reliability of the frame rib difference in movement principium between the of a certain large satellite antenna was studied. According two phases that were distinguished by the cable＇ s off the to the hinged point in the deployment process of the antenna, two corresponding mechanical analysis models were established. Then, in consideration of the influences of the dimension errors and space environments on the deployment reliabili- ty, the performance functions of rotation work and rotation moment were established respectively, and the reliability computation formulas for them were derived using the method of second-order moment. Finally, the reliability anal- ysis for the antenna with the caliber of 12-meter was conducted, and the results verified the rationality and the feasi- bility of the presented models. This study provides the theoretical basis and reference for the deployment reliability analysis of a large satellite antenna.
出处
《高技术通讯》
CAS
CSCD
北大核心
2012年第3期320-325,共6页
Chinese High Technology Letters
基金
863计划（2006AA042402）和国防预研（Y13406040101）资助项目.
关键词
星载天线
铰接肋天线
背架肋
功能函数
一次二阶矩
运动可靠性
satellite antenna, hinged-rib antenna, frame rib, performance function, second-order moment,movement reliability
