Location

Brunswick, ME

Start Date

1-1-1997 12:00 AM

Description

Bench fatigue testing of the H-46 DCU rotor system components for flight qualification has provided a unique opportunity for the assessment of modal acoustic emission (MAE) as a possible health monitoring technique for crack growth detection. The DCU bench test program provided a variety of types of fatigue tests on actual helicopter dynamic system components with representative noise environments. The bench test program required to support the qualification of a production helicopter involves bench fatigue testing six specimens of each component or assembly and the DCU program had 17 components and assemblies which required qualification tests. Fatigue testing of this type exhibits some of the noise characteristics which are presumed to exist in dynamic components during flight such as bearings and pins interacting with component surfaces. Additional noises encountered during fatigue testing were from the test rig and electromagnetic interferences. Gathering time histories of both growing cracks and noise are important goals for assessment of the applicability of MAE to health monitoring.

Book Title

Review of Progress in Quantitative Nondestructive Evaluation

Volume

16B

Chapter

Chapter 7: New Inspection Procedures

Section

Techniques for Process Control

Pages

1999-2004

DOI

10.1007/978-1-4615-5947-4_261

Language

en

File Format

application/pdf

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Jan 1st, 12:00 AM

Modal Acoustic Emission Monitoring of Helicopter Rotor System Dynamic Components During Bench Fatigue Tests

Brunswick, ME

Bench fatigue testing of the H-46 DCU rotor system components for flight qualification has provided a unique opportunity for the assessment of modal acoustic emission (MAE) as a possible health monitoring technique for crack growth detection. The DCU bench test program provided a variety of types of fatigue tests on actual helicopter dynamic system components with representative noise environments. The bench test program required to support the qualification of a production helicopter involves bench fatigue testing six specimens of each component or assembly and the DCU program had 17 components and assemblies which required qualification tests. Fatigue testing of this type exhibits some of the noise characteristics which are presumed to exist in dynamic components during flight such as bearings and pins interacting with component surfaces. Additional noises encountered during fatigue testing were from the test rig and electromagnetic interferences. Gathering time histories of both growing cracks and noise are important goals for assessment of the applicability of MAE to health monitoring.