Deployable Tensegrity Structures for Space Applications
Deployable Tensegrity Structures for Space Applications
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发表时间：
2002
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通讯作者：
G. Tibert
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作者：
G. Tibert
本论文系以张拉整体概念为基础，探讨空间可展结构之发展。本文综述了空间可展开天线杆和反射面天线的最新研究进展。比较各种反射面天线之间的部署和收藏的大小，质量和精度。找形分析是张拉整体结构设计的关键步骤。这一步提出的几种方法进行审查，并分为两组，运动学和静态的方法，每种方法的优点和缺点进行了研究。两种统计方法似乎是相同的。得出的结论是，几种找形方法是可用的，但没有一个单一的方法是适合于一般张拉。提出了大型杆系结构运动学和静力学性能分析的力法。本文介绍了每级有三个支柱的可展开张拉整体桅杆的分析和设计。一个例行的物理模型的制造提出和评估。不同的部署方案进行了研究。介绍了一种利用自展开铰链展开支柱的方法，并通过四级和八级桅杆模型进行了演示。最后，张拉整体桅杆与现有的可展开桅杆的刚度进行了比较。桅杆在轴向方向上相对刚性，但在弯曲方面非常弱。提出了小卫星可展开反射面天线的设计要求。采用了用三角形索网近似反射面的概念。对动定三角索网进行了深入的分析。可实现的表面精度的网络，从表面的三角形近似和随机制造误差所产生的系统误差，进行评估。提出了新概念的基本原理及其静力学和运动学特性。建立了物理模型，以分析概念的可行性并测试各种部署方案。使用伸缩支柱的方案被认为是最合适的，并初步设计了一个直径为3米的天线，用于未来的空间使命。数值计算表明，天线是刚性的，非常轻。
This thesis deals with the development of deployable structures, based on the tensegrity concept, for applications in space. A state-of-the-art review of deployable masts and reflector antennas for space applications is presented. A comparison is made between the various reflector antennas in terms of deployed and stowed sizes, mass and accuracy. The key step in the design of tensegrity structures is the form-finding analysis. Several methods proposed for this step are scrutinised and classified into two groups, kinematic and static methods, and the advantages and disadvantages of each method are investigated. Two of the statical methods seems to be identical. It is concluded that several form-finding methods are available, but no single method is suitable for general tensegrities. The force method, for the analysis of the kinematic and static properties of large bar frameworks, is presented. The analysis and design of deployable tensegrity masts, with three struts per stage, is described. A routine for the manufacturing of physical models is proposed and evaluated. Different schemes for deployment are investigated. A way to deploy the struts using self-deployable hinges is introduced and demonstrated by fourand eight-stage mast models. Finally, the tensegrity mast is compared with an existing deployable mast with respect to stiffness. The mast is relatively stiff in the axial direction but very weak in bending. The requirements for a deployable reflector antenna used on small satellites are formulated. A concept, which uses a triangulated cable network to approximate the reflecting surface, is adopted. The kinematically determinate triangulated cable network is thoroughly analysed. The achievable surface accuracy of the net, both to systematic errors arising from the triangular approximation of the surface and random manufacturing errors, is evaluated. The underlying principles and the statical and kinematical properties of the new concept are presented. A physical model is built to analyse the feasibility of the concept and to test various deployment schemes. The scheme using telescopic struts are identified as the most suitable and a preliminary design an antenna, with a diameter of three metres, for a future space mission is performed. Numerical computations show that the antenna is stiff and extremely light.