Location

Seattle, WA

Start Date

1-1-1996 12:00 AM

Description

With the evolution of light and stiff composite technology as a viable alternative to metals, wide-spread applications of bonded composite structures are being accepted in the aerospace industry. Although several bonded composite structures are currently in-service, the certification cost often negates the demonstrated benefits of composite material based structures. One of the key requirements for the certification and the subsequent implementation of the new composite-composite bonded structure is the assurance of the integrity of the adhesive bond joints. In this paper, a reflection frequency spectrum of the reflected ultrasonic oblique wave (in a pitch-catch mode) from an adhesively bonded graphite-epoxy aircraft wing-spar structure is obtained and mapped. Different types of programmed defects such as inclusions, voids, and interface contamination at the adhesive substrate were evaluated using the reflection factor technique.

Book Title

Review of Progress in Quantitative Nondestructive Evaluation

Volume

15B

Chapter

Chapter 5: Engineered Materials

Section

Bonded Joints

Pages

1299-1304

DOI

10.1007/978-1-4613-0383-1_169

Language

en

File Format

application/pdf

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Jan 1st, 12:00 AM

Evaluation of Adhesion Integrity in Graphite Epoxy Bonded Structures Using Ultrasonic Reflection Factor Analysis

Seattle, WA

With the evolution of light and stiff composite technology as a viable alternative to metals, wide-spread applications of bonded composite structures are being accepted in the aerospace industry. Although several bonded composite structures are currently in-service, the certification cost often negates the demonstrated benefits of composite material based structures. One of the key requirements for the certification and the subsequent implementation of the new composite-composite bonded structure is the assurance of the integrity of the adhesive bond joints. In this paper, a reflection frequency spectrum of the reflected ultrasonic oblique wave (in a pitch-catch mode) from an adhesively bonded graphite-epoxy aircraft wing-spar structure is obtained and mapped. Different types of programmed defects such as inclusions, voids, and interface contamination at the adhesive substrate were evaluated using the reflection factor technique.