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FUEL TANK SAFETY - 3D COMPUTATIONS FOR ATTACHMENT AND CONDUCTION ASSESSMENT

机译:燃油箱安全 - 附件和传导评估的3D计算

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The evolutions of the Certification Specifications CS 25.954 [1] and CS 25.981 [2] and associated policy [3] [4], change the justification to prevent catastrophic fuel vapour ignition due to lightning. This change results in carrying out many tests for all arrangement and design taking into account manufacturing escape, accident and aging: the "fault tolerant approach". The new type of computations is now part of the assessment to justify the current distribution in the arrangement of fuel tank and the design of the samples used for conduction and attachment tests. This paper presents the methodology applied by Dassault Aviation to quantify the current distribution for conduction and attachment problematic. Important efforts have been performed - to validate computation by dedicated tests - and to increase technical collaboration with DGA-TA thus making it possible to specify the test set-up and samples with a better understanding of lightning strike distribution produced on the Airplane. The first application concerns 3D computations at aircraft level for conduction aspect, to quantify the current distribution for all arrangements depending on many parameters like: location, type of assemblies, families of fasteners, etc. These computations are more and more reliable to specify the injected current level during the test on samples and to estimate the waveform (rise-time for example). Indeed, for conduction aspect, 3D computations are performed at aircraft level integrated a few thousands of individual fastener joints to quantify the lightning threat levels for each fastener family and each aircraft zones. This work is presented in a dedicated paragraph. For attachment aspect, the same computations are also used to quantify the current on the skin versus the internal current on the stiffener/rib/spar. For metallic, composite or hybrid arrangements, the test set-up could be adjusted to reproduce these distributions. This work requires an important collaboration in terms of computation and measurements with DGA-TA to understand, to optimize and to simplify the methodology if necessary.
机译:认证规范CS 25.954 [1]和CS 25.981 [2]和相关政策[3] [3] [3],改变了防止由于闪电引起的灾难性燃料蒸汽点火的理由。这一变化导致考虑到制造逃生,事故和老化的所有安排和设计的许多测试:“容错方法”。新型计算现在是评估的一部分,以证明燃料箱排列的电流分布以及用于传导和附接测试的样品的设计。本文介绍了Dassault Aviation应用的方法,以量化导通和附着的电流分布。已经执行了重要的努力 - 以专用的测试验证计算 - 并提高与DGA-TA的技术协作,从而可以指定测试设置和样本,并更好地理解飞机上产生的雷击分配。第一申请涉及飞机水平的3D计算进行传导方面,以量化所有布置的当前分布,这取决于许多参数:位置,组件类型,紧固件的系列等。这些计算越来越可靠地指定注入在样品测试期间的电流水平并估计波形(例如上升时间)。实际上,对于传导方面,在飞机水平上进行3D计算,该飞机级集成了几千个单独的紧固件接头以量化每个紧固件家族和每个飞机区域的闪电威胁。这项工作是专门的段落。对于附件方面,相同的计算也用于量化皮肤上的电流与加强件/肋/脚的内部电流。对于金属,复合或混合装置,可以调整测试设置以再现这些分布。这项工作需要在使用DGA-TA的计算和测量方面进行重要协作,以便在必要时进行优化和简化方法。

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