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REVIEW OF DATA REDUCTION TECHNIQUES FOR THE INTERPRETATION OF DYNAMIC QUALIFICATION WITH SWEPT-SINE EXCITATION

机译:基于正弦激励的动态定性解释的数据约简技术综述

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The dynamic qualification procedure for spacecraft structures usually includes broadband base excitation using vibration tables on an acceleration level defined by the launcher. In most cases, the frequency range of interest is covered by a logarithmic sweep. In order to prevent the structure from being overtested, low and intermediate level runs are performed before the actual qualification run. The latter is tailored to fulfil the qualification requirements based on preceding lower-level runs. The load level of the structure is generally measured by means of accelerometers sometimes using additional information from other sensor types like strain gauges. In order to define the high-level swept-sine runs it is necessary to compute the applied loads on the structure as a function of frequency. It is, thus, necessary to transform the recorded time domain measurements in a reliable way to frequency domain to obtain a realistic picture of the excitation level of critical parts of the structure. This transformation can be carried out by several means performing Hilbert transform of the time domain data or calculating RMS values and replacing the time axis by an equivalent frequency axis or using standard procedures of spectral analysis based on the Fourier transform. The paper critically reviews the benefits and problems of these procedures when using them to analyse data from swept-sine base excitation. The procedures will be thoroughly checked by using simulation data for a numerical 1 Degree of Freedom (DoF) system and a weak non-linear beam. Furthermore, they will be applied to data from the qualification test campaign of the Automated Transfer Vehicle (ATV) in 2003.The results for the several data reduction techniques from the numerical simulations, a simple beam structure and the test on the ATV are compared and evaluated. The dependency on noise, sweep-velocity and non-linearities is discussed. By means of these investigations suggestions for future measurement campaigns are made.
机译:航天器结构的动态鉴定程序通常包括在发射器定义的加速度级别上使用振动表的宽带基础激励。在大多数情况下,对数扫描覆盖了感兴趣的频率范围。为了防止对结构进行过度测试,在进行实际资格鉴定之前先进行低级和中级运行。后者是根据先前的低级别运行量身定制的,以满足资格要求。通常使用加速度计来测量结构的载荷水平,有时还使用来自其他传感器类型(如应变仪)的附加信息。为了定义高级扫频正弦运行,有必要根据频率计算结构上施加的载荷。因此,有必要以可靠的方式将记录的时域测量值转换为频域,以获得结构关键部分的激发水平的真实图片。可以通过执行时域数据的希尔伯特变换或计算RMS值并将时间轴替换为等效频率轴或使用基于傅立叶变换的标准频谱分析程序,通过几种方式执行此转换。当使用这些程序分析来自扫频正弦基激励的数据时,本文严格审查了这些程序的优点和问题。程序将通过使用数值1自由度(DoF)系统和弱非线性光束的模拟数据进行彻底检查。此外,它们还将应用于2003年自动传输车辆(ATV)资格测试活动中的数据。比较了数值模拟,简单梁结构和在ATV上进行测试的几种数据缩减技术的结果,并进行了比较。评估。讨论了对噪声,扫描速度和非线性的依赖性。通过这些调查,为将来的测量活动提出了建议。

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