摘要
大型星载天线可展开机构主要是用于抛物球面天线,关于抛物柱面天线机构设计较少。选取偏馈式抛物柱面天线作为研究对象,通过单元模块对抛物线方向等分,构成折线段对抛物线拟合。模块单元的抛物线方向和柱面方向由相同结构肋单元组成,采用复数矢量法进行机构运动建模分析,可以得到驱动滑块位移与展开角度之间的关系;通过ADAMS软件分别基本单元模块和简化整体模块进行运动仿真,可以得到肋单元滑块位移与关节角度变化关系和主要形成抛物柱面支撑点的运动轨迹,为模块展开可靠性和地面模拟实验提供设计依据。
At present,a large satellite antenna deployable mechanism is mainly used for spherical parabolic antenna,the design of parabolic cylinder antenna mechanism is less.This paper selects offset parabolic antenna as the research object,through the module of the parabolic part,the line segment is used to do the parabola fitting.The parabola direction and the cylinder direction of the module unit are composed of the same structural rib unit.The complex vector method is used to analyze the motion of the mechanism and obtain the relationship between the displacement of the slider and the angle.ADAMS software is used to simulate the motion of the basic unit module and the simplified whole module and obtain the relationship between the displacement of the slider and the angle of the joint and the trajectory of the supporting point of the parabolic cylinder.The basis is provided for the design of the module reliability and the ground simulation experiment.
作者
董自瑞
DONG Zirui(Nanjing University of Aeronautics and Astronautics College of Astronautics,Nanjing 210016,China)
出处
《机械制造与自动化》
2018年第6期119-123,共5页
Machine Building & Automation
基金
中央高校基本科研基金(NS2015085)
关键词
抛物柱面
可展机构
模块化
parabolic cylinder
deployable mechanism
modularization
