W.D. Anderson, S.R. Patel, C.L. Black, F. Zapata

This paper describes the design, flight test and analysis process used to certify the vertical tail and rudder structure for buffet loads on the F/A-22. A model was developed to predict flight test buffet loads based on aircraft flight parameters. This model is statistical in nature, so the structural design criteria were stated in probabilistic terms, allowing estimation of the maximum buffet loading for design purposes. Distributed load cases were developed for the maximum loading conditions. These probabilistic cases were supplemented with deterministic analysis based on the maximum measured loads from flight testing. The design cases were all reviewed on a structural FEM permitting the buffet team to clear the aircraft for full envelope flight operations.

International Forum on Aeroelasticity and Structural Dynamics, 2005, München

Conference Paper

englisch

21,0 x 29,7 cm, 12 Seiten

DGLR-Bericht, 2005, 2005-04, International Forum on Aeroelasticity and Structural Dynamics 2005; S.1-12; 2005; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

in getr. Zählung;

certification, structural dynamics, buffet, lockheed martin f-22 aircraft

Bibliothek

2005