L.H. van Zyl

For the calculation of generalized forces, an important step in the aeroelastic analysis of an aircraft, the deflections and slopes of the natural modes of the structure must be known at the aerodynamic control points. The control points do not in general correspond to the positions where deflections are measured during ground vibration tests, and modal interpolation is used to calculate the required deflections and slopes from the measured deflections. The present paper deals with the problem of modal interpolation for complex aircraft structures. The measurements are not exact, and methods such as least-squares curve fits are used, which averages out the measurement errors. These methods require the use of large numbers of accelerometers in order to obtain reliable results, which is often impracticable for complex structures. Using physical restraints together with the usual techniques of interpolation significantly improves the quality of the calculated data. Physical restraints are statements regarding the continuity of the aircraft and the behaviour of free edges. In this paper the theory for the inclusion of restraints in the least-squares method of interpolation as well as an implementation of the method is discussed. Results are presented to illustrate the effectiveness of the method.

International Forum on Aeroelasticity and Structural Dynamics 1991, Aachen

Conference Paper

englisch

21,0 x 29,7 cm, 4 Seiten

DGLR-Bericht, 1991, 1991-06, International Forum on Aeroelasticity and Structural Dynamics 1991 Proceedings; S.390-393; 1991; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aeroelasticity

Bestellbar

1991