Deformation measurement in the wind tunnel for an UAV leading edge with a morphing mechanism

Conference paper (2016)

Authors

M. Radestock Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR)

J. Riemenschneider Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR)

H.P. Monner Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR)

O. Huxdorf Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR)

N.P.M. Werter Aerospace Structures & Computational Mechanics - Aerospace Engineering

R. De Breuker Aerospace Structures & Computational Mechanics - Aerospace Engineering

Research Group

Aerospace Structures & Computational Mechanics (Aerospace Engineering) (TU Delft)

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Published Date

2016

Language

English

Reuse Rights

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Faculty

Aerospace Engineering

Department

Aerospace Structures & Materials

Research Group

Aerospace Structures & Computational Mechanics

Abstract

In a wind tunnel experiment a morphing wing with span extension and camber morphing was investigated. The considered aircraft is an unmanned aerial vehicle (UAV) with a span of 4 m. During the investigations a half wing model was analysed with pressure and structural measurement. The half wing model has three different morphing mechanisms. The focus is on the morphing leading edge concept, which will be shortly described with the main objectives. First of all the morphing leading edge will be described. Afterwards the results of the wind tunnel measurement for pressure distribution, balance and deformation measurement will be presented and discussed.

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