Dwarakanath, A and Murthy, CRL and Viswanath, S and Dwarakanath, K and Rao, RMVGK (1996) Evaluation of damage in foam sandwich components of aircraft. In: 14th World Conference on NDT - Trends in NDE Science and Technology (14th WCNDT), DEC 08-13, 1996, NEW DELHI, INDIA.Full text not available from this repository.
Tn the current set of investigations foam sandwich panels and some components of an aircraft comprising of two layer Glass Fiber Reinforced Plastic(GFRP) face sheets of thickness 1mm each with polyurethene foam as filler of thickness 8mm were examined for detection of debonds and defects. Known defects were introduced in the panels in the form of teflon insert, full foam removal,half foam removal and edge delamination by inserting a teflon and removing it after curing. Two such panels were subjected to acoustic impact and analysis was carried out in both time and frequency domains. These panels were ultrasonically scanned to obtain C-SCAN images as reference to evaluate Acoustic Impact Test (AIT) results. In addition both Fokker bond testing and AIT(woodpecker) were carried out on the same panels and also some critical joints on the actual component. The results obtained from these tests are presented and discussed in this paper.
|Item Type:||Conference Paper|
|Additional Information:||Copyright of this article belongs to A A Balkema.|
|Department/Centre:||Division of Mechanical Sciences > Aerospace Engineering (Formerly, Aeronautical Engineering)|
|Date Deposited:||26 Apr 2011 06:16|
|Last Modified:||26 Apr 2011 06:16|
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