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MODAL SURVEY TESTING OF ESA ISPR RACKS FOR ISS

机译:ISS的ESA ISPR机架的模态检验测试

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Structural mathematical model predictions (naturalfrequencies, mode shapes) can show deviations from thereal dynamic characteristics of the hardware in thecomplete frequency range of interest and are thereforenot suitable for accurate flight load predictions, even incase of best practice modelling. Therefore experimentalvalidation of modal characteristics of the hardware is afundamental step in the structural verification for spaceflight systems.Modal survey tests shall be used to verify the FiniteElement Models (FEM) of the integrated hardware, asrequested and used for the Design Loads Assessment(DLA) and the Verification/Coupled Load Analysis(VLA/CLA) of the launcher system.The payloads shall demonstrate compliance with therequired quality of the mathematical models and theconstraints on dynamic de-coupling between modes ofthe payload and the modes of the launcher. This is ofgreat concern for those payloads launched on the Shuttlefor the International Space Station (ISS).The International Standard Payload Racks (ISPR's) arewithin this payload group. Seven of the ISPR's fromESA have already undergone Modal Survey Testing.This paper gives an overview of the applicable testrequirements and the test process for these racks. Itpresents the resulting experimental dynamiccharacteristics.All these racks are based on a common rack framestructure developed by Ishikawajima-Harima HeavyIndustries, Japan. Then each rack integrator furnishesthe rack with scientific equipment using customizedsupport and structural elements. The paper studies howthe specific design choices in the integration influencethe dynamic behaviour of the final integrated rack.The paper also reviews the analysis/test correlationrequirements that call for a Finite Element Modelreproducing the experimental modal parameters with acertain acceptable error. The results of the correlationfor the ESA payload racks are provided.Finally the paper outlines the lessons learned in thecomplete testing process from the prediction analysesand selection of locations for accelerometers andexciters to the actual testing execution and theanalysis/test correlation.
机译:结构数学模型预测(自然频率,模式形状)可以显示在感兴趣的完整频率范围内与硬件的实际动态特性的偏差,因此即使在最佳实践建模的情况下,也不适合准确的飞行负载预测。因此,对硬件的模态特性进行实验验证是航天系统结构验证中的基础性步骤。应使用模态检验测试来验证集成硬件的有限元模型(FEM),并应将其用于设计载荷评估(DLA)和有效载荷应证明符合所要求的数学模型的质量以及有效载荷模式与发射器模式之间动态去耦的约束。发射器系统的验证/耦合载荷分析(VLA / CLA)。对于在国际空间站(ISS)的航天飞机上发射的有效载荷,这是一个非常关注的问题。国际标准有效载荷机架(ISPR)属于该有效载荷组。来自ESA的ISPR的七个已经进行了模态检验测试。本文概述了这些机架的适用测试要求和测试过程。它代表了由此产生的实验动态特性。所有这些机架均基于日本Ishikawajima-Harima HeavyIndustries开发的通用机架框架结构。然后,每个机架集成商都使用定制的支架和结构元件为机架提供科学设备。本文研究了集成中的特定设计选择如何影响最终集成机架的动态行为。本文还回顾了分析/测试相关性要求,这些要求要求使用有限元模型来再现具有确定的可接受误差的实验模态参数。最后,本文概述了完整测试过程中的经验教训,从预测分析和加速度计和激励器位置选择到实际测试执行以及分析/测试关联。

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