M. Lacabanne, J.P. Esquerre

The aeroelastic behaviour of civil transport aircraft must be accurately predicted at a very early stage of design. After the initial design, the aeroelastician will have to meet the dynamic structural requirements for the first aircraft and all the series aircraft. The paper presents the process leading to the aeroelastic justification of a two engine short medium range civil aircraft. The theoretical models are first described in the state of development reached just before the ground vibration tests. After the ground vibration tests, the dynamic model is improved and validated. Finally, the aeroelastic model including the unsteady aerodynamic forces and control law representation is validated by the comparison of theoretical results and flight vibration test results. The methods used for the analysis of flutter flight tests are reviewed. The comparison between theoretical and flight test results is provided for frequencies and dampings versus speed and, also, for the transfer functions between accelerometers and the excitation. The good comparison of frequencies and dampings validates the aeroelastic model. Nevertheless, some deviations between the aircraft and model transfer functions show that the model could be improved.

International Forum on Aeroelasticity and Structural Dynamics 1991, Aachen

Conference Paper

englisch

21,0 x 29,7 cm, 9 Seiten

DGLR-Bericht, 1991, 1991-06, International Forum on Aeroelasticity and Structural Dynamics 1991 Proceedings; S.594-602; 1991; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aeroelasticity

Bestellbar

1991