Abstract
The scanning laser Doppler vibrometry (SLDV) technique provides velocities of a structure at 2-dimensional (2-D) angularly evenly spaced (in the laser scanning sense) data points. This causes an unevenly spaced data point distribution on the surface of the test structure. In many cases evenly spaced data point distribution with square or rectangular grids is highly desirable. In this study the SLDV velocity data of a partial surface area of an aircraft fuselage were mapped to truly spatial evenly spaced coordinates by using the spatial DFT-IDFT technique with minimum distortion. This 2-D data mapping technique certainly is not limited to the fuselage, hut can he very useful for many other 3-D structures.
Highlights
Other than convenience, noncontact, and high accuracy, one of the main features of the Scanning Laser Doppler Vibrometry (SLDV) technique is that real and imaginary velocity data of tens of thousands of points on a vibrating surface can be gathered within a relatively short period of time (Oliver, 1991; Sriram, Craig, and Hanagud, 1990)
The high spatial resolution provides great advantages that have contributed to the development of a number of new techniques in the areas of structural angular velocity extraction (Kochersberger, Mitchell, and Wicks, 1991; Sun and Mitchell, 1991), structural system identification (Li, Mitchell, and Lu, 1994), and spatial modal parameter estimation (Arruda, Sun, and Mitchell, 1992)
Small, and flat structures, such as beams and plates, the variations of the spaces between data points on the measured surface caused by the constant scanning angle increment are usually small due to the smaller scanning angle
Summary
Noncontact, and high accuracy, one of the main features of the Scanning Laser Doppler Vibrometry (SLDV) technique is that real and imaginary velocity data of tens of thousands of points on a vibrating surface can be gathered within a relatively short period of time (Oliver, 1991; Sriram, Craig, and Hanagud, 1990). F igure I shows a scan ned grid of data points from a sectio n of a commercial aircraft fuse lage with th e unit s of scanni ng angle in dex in both the X (lo ngitudin al) and Y (circumfere nti al) directions. When this evenl y spaced (in th e sense of sca nning angle) data point grid is converted to a grid a lo ng th e surface of th e fuse lage (Fig. 2) , th e scanned area becomes pincushion shaped , the grid is no lo nger rectangular, and the space between data points is qu ite vari ab le.
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