This article studies a new concept deployable structure.
本文研究一种新概念展开机构。
In this paper, a deployable structure consisting of sub structure, active cable and passive calbe is introduced.
文中介绍了一种展开结构，它包括子结构、主动索、被动索。
Based on the deployable structure of a mirror and the operation principle, the finite element method was used to analyze the unit naked mirror and some different mirror support schemes.
基于展开镜结构工作原理，运用有限元方法分析了展开式反射镜单元的裸镜及其支撑方案。
The results provide precise measurements of the dynamics characteristics of the space deployable structure in the time-frequency domain, which are helpful for improving the system analysis and design.
实现了对航天可展结构动力学性能在时频域内的“精细”考察，将有助于提高航天器结构的分析与设计水平。
From the Deployable plug-ins and fragments dialog, select our plug-in, select to deploy it as a directory structure, then deploy it to the directory as shown in Figure 67.
从可部署的插件及片断对话框中选择我们的插件，选择将其作为directorystructure进行配置，接下来在目录上对其进行配置如图67所示。
The MQInput node is required to identify the message flow as the main deployable flow. Here is the new project structure.
识别消息流作为主要可部署流需要MQInput节点。
Based on flexible multi-body system dynamics theory, kinematic and dynamics equations of deployable space cable-pole structure are derived.
基于柔性多体系统动力学理论，推导了可展空间索杆结构的运动学与动力学方程。
Finally, on the basis of J2EE structure, the article realizes the deployable domain component assembly by XML language and develops a prototype of MES software for disperse manufacturing.
最后，在J2EE软件体系结构的基础上，利用xml语言实现了可部署的领域构件的装配，并开发了适合离散制造的MES软件的原型系统。
The research work in the paper is composed of two parts: the dynamic optimization of the deployable large flexible net antenna for satellite and the systemic optimization design of structure.
本文的研究工作由两部分组成：一是大型星载可展开天线的动力优化设计，二是工程结构的系统优化设计。
The flexible cable net deployable antenna have a simple structure and distinct working theory, so it is the ideal structure form of large satellite antenna at present.
周边桁架可展开天线结构形势简明，工作原理清晰，是目前大型卫星天线理想的结构形式。
The characteristics of nonlinear equations for a deployable truss structure with clearances are analyzed, numerical solution method for such equations is studied.
针对带铰接间隙大型桁架式伸展机构的动力学方程，分析了方程的非线性特性，研究了其数值求解方法。
Structure precept and fold pattern of inflatable sunshield were proposed, then the deployable state and fold state of sunshield can be fit for size require.
提出遮光罩的结构方案、折叠方式和结构中各组件合适的材料，使得结构展开状态和折叠状态分别能够达到一定的尺寸要求。
This paper deals with stability of a deployable flexible structure.
研究了一类可伸缩挠性梁结构的稳定性。
Based on modular design idea of the spacecraft structure, a hinged deployable configuration for the spacecraft was designed.
基于航天器结构的模块化设计概念，设计了一种空间可展开航天器模块化结构构型，即铰链展开式构型。
Based on modular design idea of the spacecraft structure, a hinged deployable configuration for the spacecraft was designed.
基于航天器结构的模块化设计概念，设计了一种空间可展开航天器模块化结构构型，即铰链展开式构型。
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