P. Bösch, T. Nielsen, Y. Radiant

A major airframe fatigue test is required by the Airworthiness Authorities as part of the Type Certification of the A380, the worlds first twin-deck commercial aircraft. The aircraft has been designed against fatigue and damage tolerance requirements, and the purpose of the fatigue test is to provide the evidence to validate the design. Previous major fatigue tests, from the A300 to the A340-600, were performed as multi-section tests, mainly nose fuselage, wing-box/ centre fuselage, rear fuselage and tail planes. For A380, the novel fuselage cross section and different materials have led to the decision to test the complete fuselage, including load introduction from the empennage units in combination with all of the fixed wing structure. This major fatigue test will be carried out incorporating all typical design features and relevant fatigue loading conditions of each of the A380 major structural components. The test loads will be applied under computer control by 182 hydraulic actuators and an internal pressurization system, to simulate in-service ground and flight loading conditions. Artificial damages for crack growth test will be introduced in the test article after completing at least one design service life. The test will then be continued to 2.5 life times to obtain the structure crack growth behaviour. After completion of the fatigue test, the test article will be disassembled in selected areas and a tear down inspection performed.

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

Conference Paper

englisch

A5, 12 Seiten

DGLR-Bericht, 2005, 2005-03, 23rd ICAF Symposium of the international Committee on Aeronautical Fatique - Proceedings; S.353-364; 2005; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

fatigue tests, a380 aircraft

Bestellbar

2005