P.H. Denke, J.C. Yu

More powerful aircraft engines, higher speeds, and high lift devices subjected to jet impingement create a need for improved methods of sonic fatigue analysis. The matrix difference equation (MOE) method is a new approach to finite element modeling of vibrating structures. The method features simplified data preparation, detailed inodeling, low-computing cost, fast tum-around, and reliable results. The paper describes a recent extension to sonic fatigue. The outboard wing flap of the C-17 military transport is subjected to direct jet impingement during take-off and landing. Extensive analysis and test programs were conducted, but additional verification was wanted before first flight. The MOE computer code was available, but it needed added capability to compute responses to random forcing functions. The program was extended as required, the revised program was tested, and numerous analytical studies were conducted over an eight month period. The paper describes the. basic MOE method, the extensions to acoustic fatigue analysis, and some of the C-17 flap analytical results.

DGLR/AIAA 14th Aeroacoustics Conference, 1992

Conference Paper

englisch

21,0 x 29,7 cm, 6 Seiten

DGLR-Bericht, 1992, 1992-03, DGLR/AIAA 14th Aeroacoustics Conference - Proceedings; S.779-784; 1992; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aeroacoustics, acoustic fatigue, c-17 aircraft

Bibliothek

1992