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首页> 外文期刊>International journal of structural stability and dynamics >EXPERIMENTS ON BUCKLING AND POSTBUCKLING OF THIN-WALLED CFRP STRUCTURES USING ADVANCED MEASUREMENT SYSTEMS
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EXPERIMENTS ON BUCKLING AND POSTBUCKLING OF THIN-WALLED CFRP STRUCTURES USING ADVANCED MEASUREMENT SYSTEMS

机译：先进测量系统对薄壁CFRP结构屈曲和后屈曲的实验

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摘要

The aircraft and space industry strives for significantly reduced development and operating costs. Reduction of structural weight at safe design is one possibility to reach this objective which is aimed by the following two running research projects: the EC project "COCOMAT" and the ESA study "Probabilistic Aspects of Buckling Knock Down Factors". These projects develop improved concepts and tools for a fast and reliable simulation of the buckling and the postbuckling behavior of thin-walled structures up to collapse, respectively, which allow the exploitation of considerable reserves in primary fibre composite structures in aerospace applications. For the validation of the concepts and tools, a sound database of experiments is needed which is also performed within these projects. This paper focuses on the experimental activities within these projects performed at the buckling test facility of the Institute of Composite Structures and Adaptive Systems (DLR). It presents an overview about the DLR buckling, postbuckling and collapse tests which are already finished and gives an outlook to the results which are expected until the end of the running projects. This paper explains the working of the buckling test facility, the advanced measurement systems, which are running in parallel to the tests, and gives exemplarily two test results. The structures considered are unstiffened cylinders (ESA study) as well as panels, which are understood as sections of cylinders, stiffened by stringers (COCOMAT project). The unstiffened cylinders are more related to space applications (e.g. Ariane busters or parts of the international space station ISS) and the stiffened panels focus more on aircraft structures (e.g. fuselage). The load case considered for all investigations presented in this paper is axial compression under static loading although the test facility is also ready to apply torsion and internal pressure, as well as dynamic axial impact.
机译：航空航天业努力降低开发和运营成本。在安全设计中减轻结构重量是实现此目标的一种可能性，该目标的目标是以下两个正在运行的研究项目：EC项目“ COCOMAT”和ESA研究“屈曲爆破因素的概率方面”。这些项目开发了改进的概念和工具，分别用于快速可靠地模拟直至破裂的薄壁结构的屈曲和后屈曲行为，从而允许在航空航天应用中利用初级纤维复合结构中的大量储量。为了验证概念和工具，需要一个完善的实验数据库，这些数据库也在这些项目中执行。本文重点研究在复合结构和自适应系统研究所（DLR）的屈曲测试设施进行的这些项目中的实验活动。它概述了已经完成的DLR屈曲，后屈曲和坍塌测试，并对预期的结果进行了展望，直到运行项目结束为止。本文介绍了屈曲测试设备，高级测量系统（与测试并行运行）的工作原理，并示例性地给出了两个测试结果。所考虑的结构是未加劲的圆柱（ESA研究）以及面板，这些面板被理解为由桁条加劲的圆柱截面（COCOMAT项目）。未加劲的圆柱体与空间应用（例如，阿丽亚娜克星或国际空间站ISS的一部分）更相关，而加劲的面板则更侧重于飞机结构（例如，机身）。尽管测试设备也准备好施加扭转和内部压力以及动态轴向冲击，但本文中所有研究均考虑的载荷工况为静态载荷下的轴向压缩。

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