Location

La Jolla, CA

Start Date

1-1-1998 12:00 AM

Description

The effectiveness of boron/epoxy repairs in retarding or arresting cracks in skin grade aluminum have been investigated [1–3]. The durability or long-term performance of bonded composite repairs on damaged structures is still an issue that poses a great technical challenge. This is mainly due to the delamination of the composite doubler and/or the deterioration of the interfacial strength of these repairs. Delamination of composite materials, in spite of current technological advancement in their processing techniques, represents a considerable problem. This is caused by the lack of close contact between the plies due to defects such as voids or spots of excess resin formed during curing of the composite. Fortunately, most repair patches are thin section composites and most of the above mentioned defects induced during fabrication may not be severe. This coupled with proper fabrication encourage the utilization of composite repairs of aircraft structural components. Achievement of an optimum quality adhesive interface and the prevention of its degradation with time are also formidable tasks. This involves, surface preparation and tight quality control [4], means by which their long term performance can be evaluated [5, 6], and effective nondestructive methods to assess their long term cumulative damage [7].

Book Title

Review of Progress in Quantitative Nondestructive Evaluation

Volume

17B

Chapter

Chapter 5: Engineered Materials

Section

Coatings, Films and Bond

Pages

1403-1410

DOI

10.1007/978-1-4615-5339-7_181

Language

en

File Format

application/pdf

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Jan 1st, 12:00 AM

Evaluation of Bonded Boron/Epoxy Repairs on Aircraft Skin With Simulated Damage

La Jolla, CA

The effectiveness of boron/epoxy repairs in retarding or arresting cracks in skin grade aluminum have been investigated [1–3]. The durability or long-term performance of bonded composite repairs on damaged structures is still an issue that poses a great technical challenge. This is mainly due to the delamination of the composite doubler and/or the deterioration of the interfacial strength of these repairs. Delamination of composite materials, in spite of current technological advancement in their processing techniques, represents a considerable problem. This is caused by the lack of close contact between the plies due to defects such as voids or spots of excess resin formed during curing of the composite. Fortunately, most repair patches are thin section composites and most of the above mentioned defects induced during fabrication may not be severe. This coupled with proper fabrication encourage the utilization of composite repairs of aircraft structural components. Achievement of an optimum quality adhesive interface and the prevention of its degradation with time are also formidable tasks. This involves, surface preparation and tight quality control [4], means by which their long term performance can be evaluated [5, 6], and effective nondestructive methods to assess their long term cumulative damage [7].