T.S. Hullander, D.J. Barrett, J. Elmore, W. Braisted, G.J. Frank, D.C. Walling , H. Wriley Gay

The engine inlet to the A V -8B aircraft has been experiencing an unacceptably high number of High Cycle Fatigue (HCF) failures which adversely effect the reliability, maintainability, and supportability of the fleet. The cause of the HCF failures is resonant vibration of the stiffened skin structure of the inlet. A low-cost retrofit solution to the HCF failure problem is required. This paper describes the design and demonstration of a passive damping solution to mitigate the HCF problem and significantly extend the life of the current hardware. Details of the passive damping design process are presented. Analytical techniques were utilized to determine the optimal design given the operational and installation constraints. Testing was conducted that verified the survivability and integrity of the damping materials across the operating temperature range after exposure to various chemicals encountered during operation. Two designs were fabricated and tested on AV-8B hardware. Results from the testing indicate that the damping designs are highly effective at reducing vibration amplitudes in the inlet structure and thereby extending the fatigue life of the inlet. A simple installation procedure was developed and demonstrated. Installations of the engine inlet damping system to the AV-8B fleet is currently underway.

23rd ICAF Symposium of the international Committee on Aeronautical Fatique, 2005, Hamburg

Conference Poster

englisch

A5, 15 Seiten

DGLR-Bericht, 2005, 2005-03, 23rd ICAF Symposium of the international Committee on Aeronautical Fatique - Proceedings; S.429-443; 2005; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

damping, vibrations, fatigue, life extension

Bestellbar

2005