Non Destructive Testing Testmeasurement on VL-3 by …pyrodynamics-india.com/home/pdf/ISI-TN-2.pdf · 2012-09-29 · isi-sys GmbH Wasserweg 8 Tel.:+49(0)561-739798-0 http: // Page

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Our resolution is the wavelength of light

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Non Destructive Testing Testmeasurement

on VL-3 by Shearography/ESPI

(Photo courtesy of Aveko/Vanessa Air)

In cooperation with

and

© by isi-sys GmbH



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Measurement Task and Background

This measurement was done to examine two areas of the VL-3 fuselage by shearographic NDT methods

especially for delaminations. The two areas are marked in the image below by A1 and A2. The locations

include repaired areas. The applied sensor is a SE2 with 1,4MPixel CCD and 800mW Laser power.

Fig. 1: Locations A1 and A2 (original picture courtesy of Aveko/Vanessa Air)

Locaton A1

The photo below shows the SE2 Shearography sensor in front of the loction A1. The fuselage is

turned by 90°. The following image show selected results by mechanical and flood light loading.

Fig. 2: Location A1 and SE2-Vibrography Sensor

A1 A2



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Fig. 3: Location A1 Upper: Sensor view; Lower: Local out of plane deformation due to the compression

by fingertip at the area of a delaminated area (compare results of thermal loading in the next image.

Fringes are here generated by special real-time mode.



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Fig. 4: Differential deformation measurement of A1 after heat loading by flood light (upper image). The

different sign of the lower image is resulting from measurement during the heating process with

reference before heating. Both measurement show clearly the repair (yellow) and a delamination (red).



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Locaton A2

The fuselage was turned by 90° such as for area A1, so the measurement direction and setup

was also similar as above. However the area of interest was divided into three measurement

parts: One above the middle axis of the fuselage, one below and additional an overlapping

region in the middle with the axis in the center of the measurement. The overlap provide a

sufficient overview and permits an easy combination of the three parts again.

Along the middle axis of the fuselage the mounting zone of the two fuselage parts is visible due

to the different thermal expansion and deformation especially in the measurement in the

middle. Also the asymmetric differential deformation above and below the middle axis might

be due to inhomogeneous production – assuming that the heating was uniform. However

repeating the test leads to the same results as selected in the following.

Fig. 5: Location A2 (upper part)

Foam layer part

Cable duct

Str

ing

er



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Fig. 6: Location A2 (middle part) Upper: Live image Lower: Differential deformation due to heat loading

Mounting part of the two fuselage halves

Reference mark

Reference mark



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In the following image the area is marked, which shows an unsymmetrical distribution between the

upper and the lower half of the mounting part of the two fuselage halves, which can either be due to a

delamination or due to the cable duct area.

Fig. 7: Location A2 (middle part), demonstration of repeatability of the measurement

even with simple thermal loading by manual controlled flood light.



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Fig. 8: Location A2 (lower part)

Reference mark

Reference mark



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Fig. 9: Location A2 (lower part) demonstrating repeatability of the measurement

even with simple thermal loading by manual controlled flood light.

Reference mark

Documents

Non Destructive Testing Testmeasurement on VL-3 by …pyrodynamics-india.com/home/pdf/ISI-TN-2.pdf · 2012-09-29 · isi-sys GmbH Wasserweg 8 Tel.:+49(0)561-739798-0 http: // Page