摘要 为实现双反射面偏置天线在航天系统中的应用,提出一种基于连杆连接的双反射面偏置天线可展开双轴指向机构设计方案,并研制出原理样机、完成相关试验验证。本文首先针对双反射面偏置天线的特点以及航天系统的特殊要求,分析和对比传统天线指向机构不同构型的特点,完成了双反射面偏置天线指向机构的构型设计;其次通过有限元方法对指向机构进行动力学分析并针对双轴连杆、锁紧释放装置等关键部件进行理论分析与结构优化;最终根据设计方案完成了指向机构原理样机的研制并进行振动试验与振动试验后双轴夹角精度的测量。试验结果表明压紧状态下指向机构一阶基频达到103 Hz,振动试验后双轴夹角精度为21″,满足指向机构设计要求,结构设计合理可行。 To realize the application of dual-reflector offset antennas in aerospace systems,a design scheme for a deployable biaxial pointing mechanism for a spaceborne double reflector offset antenna based on a connecting rod connection is proposed,a principle prototype is manufactured,and an experimental verification is conducted.This study first analyzes and compares the characteristics of different configura⁃tions of traditional antenna pointing mechanisms according to the characteristics of the dual-reflector offset antenna and the special requirements of aerospace systems,and it helps realize the structural design of the dual-reflector offset antenna pointing mechanism.Then,the finite-element method is used to analyze the dynamics of the pointing mechanism,and further theoretical analysis and optimization design are carried out for the key components,such as the biaxial connecting rod and locking device.Finally,according to the design plan,a prototype of the pointing mechanism is manufactured,then the vibration test and the measurement of the two-axis angle accuracy after the vibration test are carried out.The test results demon⁃strate that the first-order natural frequency of the pointing mechanism is 103 Hz and the angle deviation be⁃tween the two axes after the vibration test is 21″,which meets the design requirements of the pointing mechanism,and the structural design is reasonable and feasible.
出处 《光学精密工程》 EI CAS CSCD 北大核心 2021年第3期582-591,共10页 Optics and Precision Engineering
基金 国家自然科学基金资助项目(No.51705497) 国防科工局民用航天预研项目(No.D020208)。
关键词 双反射面偏置天线 可展开双轴指向机构 结构优化 dual-reflector offset antenna deployable biaxial pointing mechanism structure optimization
