The dynamic equation of the rigid - flexible coupling nonlinear system is derived based on lagrange equation by adopting centralized parameters method . and we make a numerical simulation of the antenna ' s supporting beam ' s vibration when the satellite is rotated a little angle surrounding the z axis 本文首先采用集中参数法，利用拉格朗日方程推导了卫星?天线系统的刚柔耦合动力学方程，并对该方程进行了数值仿真，获得了系统的调姿响应和天线结构的模态。
This thesis presents the theoretical analysis about the design of the tunable antennas with multilayered structure theory and microstrip antenna ' s analytical methods . and it improves three typical kinds of antennas , and uses the voltage controlled ferroelectric materials . we analyze the tuning features of the antenna by simulation under the condition of different permittivity of the ferroelectric materials , and discuss the feasibility of improvement from microstrip antenna to tunable antenna 本文结合多层介质理论及微带天线的分析方法对可调谐天线进行理论分析,并对矩形贴片天线、圆形贴片天线、微带振子天线三种典型的微带天线结构进行改进,引入压控铁电薄膜材料,仿真分析在改变铁电薄膜介电常数条件下天线的调谐特性,讨论微带天线改进为可调谐天线的可行性。
Natural characteristic analysis not only verifies whether the natural frequencies and mode shapes of the antenna are reasonable or not , but also is the base of the structural response analysis , fatigue resistivity computing and the other dynamics problems . the structure design of antenna is a complicated systems engineering , which is generally limited to multiple objects that influence each other , so we need to keep the balance among those objects by decision - making technology of multiple objects to ensure every target optimized 固有特性的分析不仅能检验天线结构的固有频率和振型是否合理，而且也是结构响应分析、动强度计算等其他动力学问题研究的基础；天线的结构设计是一个复杂的系统工程，它通常受到多个目标的限制，而各目标往往是相互影响的，甚至是相互矛盾的，因此需要借助多目标决策技术，平衡各目标，以保证空间天线最优的满足各项设计指标。
A method is presented to find these stretchy members and calculate their length in folded state . the result of the geometric analysis of the model made in my lab is presented . the impact response produced by the tension springs in the diagonal members is very serious and a stowing mechanism is designed for the control of the impact 由于可展天线结构展开动力来源于对角杆中拉伸弹簧，所以结构在展开过程中冲击力比较大，为了控制其展开速度，同时为了完成天线的收拢过程，需要电机来进行控制，本文提供了一种电机控制机构的设计方案。
The method of moments is used to analyze and calculate the broadband characters of impedance , voltage satanding wave ratio ( vswr ) , gain and radiation pattern of larger angle lpda , and the relation between these characters and the parameter of antenna construction is discussed in this paper . based on analysis and calculation , the antenna is designed and tested , and the measured results are in good agreement with the theoretical calculation 本文采用矩量法分析和计算了对数周期天线在张角较大时，它的阻抗、电压驻波比、增益及方向图的宽带特性，讨论了这些特性与天线结构参数之间的关系.根据分析和计算，设计并制作天线进行实验测试，理论计算和测试结果表明，两者吻合较好
We acquired the system ' s dynamic response when the satellite attitude was adjusted and the mode of the antenna . then modal analysis and dynamic analysis have been done to the satellite - antenna system by using the finite element analysis ( fea ) software of ansys . through the analysis we got the system ' s connatural characteristic , the amplitude - frequency characteristic of harmonic response , the power spectrum density of random vibration response , the maximal amplitude and resuming time of impact response 其次借助ansys有限元分析软件，对系统进行了模态分析和动力学响应分析，获得了不同天线结构参数下的卫星?天线系统的固有特性，简谐响应的幅频特性，随机振动响应的功率谱密度，以及冲击响应的最大幅值和恢复时间等。
The deployable space structure is a new type of space architecture bome with space science and technology development in recent years . but in our country the technique in this field is somewhat weak . the deployable parabolic antenna designed and made in our lab can make a progress in this field 可展开天线结构是国际上空间航天结构中研究的一个重点和热点，但国内在这方面的研究比较薄弱，作者本人和课题组其他成员经过几年的研究，在这方面做出了一定的贡献，使得国内在可展开天线这方面的技术有了很大进展。
Following the developing of the aeronautical technology , higher request was brought forward to deployable antenna on satellites from every relative field . a lot of structural concept for deployable antenna was given out by aeronautic scholar . astromesh deployable antenna is one of them , which has most potential for space application 随着宇航科技的发展，各相关学科对空间可展天线提出了更高的要求，主要体现在大口径、高精度两方面，为此各国学者提出了形式众多的空间可展天线结构概念，环形桁架可展天线是其中最具潜力的结构形式之一，是本文研究的一个重要方面。
The essential structural mechanism and construction properties of hoop truss deployable satellite antenna are investigated in this thesis . three - dimensional parametric models of the antenna ' s arms and hoop truss are built by using three - dimensional parametric modeling technology . and statics analysis of hoop truss has been carried out in this thesis 本文针对大型环形桁架可展开卫星天线这一具体天线结构，利用参数化造型技术获得天线展开臂和天线环形桁架的三维参数化实体模型，并对天线环形桁架进行了静力学特性分析。
Based on finite element and general reliability analysis , the structural optimization design model based on probability is constructed , which refers the cross - section areas as the design variables , refers the minimum of the frame ’ s weight as the object with the reliability restricts of stress and displacement 在结构广义可靠性分析的基础上，构建了以杆截面积为设计变量，使结构重量极小化为目标函数，同时具有应力和位移广义可靠性约束的优化设计数学模型，并将其应用于天线结构的优化设计之中。
