小卫星太阳翼铰链对挠性动力学方程耦合系数的影响  

Influence of Small Satellite Solar Wing Hinges on CouplingCoefficients in Flexible Dynamic Equations

作　　者：高鸽 刘雪峰 魏峰 王天罡 GAO Ge;LIU Xuefeng;WEI Feng;WANG Tiangang(Shenzhen Aerospace Dongfanghong Satellite,Ltd.,Shenzhen,Guangdong 518057,China)

机构地区：[1]深圳航天东方红卫星有限公司,广东深圳518057

出　　处：《航天器工程》2024年第2期33-40,共8页Spacecraft Engineering

摘　　要：针对小卫星太阳翼机械系统产品选型时,展开机构的铰链类型、铰链刚度对卫星挠性太阳翼系统动力学方程中耦合系数影响规律不明确的情况,文章首先建立带挠性太阳翼的振动方程,给出使用动力学方程中的参量计算附件平动、转动耦合系数的公式;然后,基于小卫星常用的两种铰链类型以及铰链不同刚度,采用有限元法,对比相同卫星构型下铰链对太阳翼展开模态的影响;并获取相应的太阳翼振型、质量与质量元位置参数;最后,以某小卫星太阳翼为例,基于动力学方程中的耦合系数计算方法,采用输出参量与数据处理软件相结合方式,开展了不同铰链对耦合系数和铰链选型的影响分析。结果表明:文章分析的不同铰链、刚度的太阳翼结构参数以及耦合系数变化规律,对于铰链的设计和选型具有理论参考价值。In the selection of mechanical product of small satellite solar wing system,the influence of hinge type and hinge stiffness of deploying mechanism on coupling coefficient in dynamic equation of satellite-flexible solar wing system is not clear.Firstly,the vibration equation with a flexible solar wing is established in this paper,and the formula for calculating the coupling coefficient of the appendages by using the parameters in the dynamic equation is given.Then,based on the two types of hinges commonly used in small satellites and the different stiffness of hinges,the finite element method is used to compare the influence of hinges on the deployment mode of solar wings under the same satellite configuration.The corresponding vibration mode,mass and mass element position parameters of the solar wings are obtained.Finally,taking the solar wing of a small satellite as an example,based on the coupling coefficient calculation method in the dynamic equation,the influence of different hinges on the coupling coefficient and hinges selection principle are analyzed by combining the output parameters with data processing software.The result shows that the structural parameters and the coupling coefficient with different hinge type and stiffness analyzed in this paper have theoretical reference value for the selection and design of hinges.

关 键 词：卫星太阳翼 铰链 挠性附件 耦合系数 模态分析 

分 类 号：V416[航空宇航科学与技术—航空宇航推进理论与工程]