Flight Flutter Testing; Control Surface Actuator; External Excitation; Modal Analysis; Frequency Response Functions
Abstract :
[en] Flutter testing is used to demonstrate that the aircraft flight envelope is flutter free.
Response measurements from deliberate excitation of the structure are used to identify and
track frequency and damping values against velocity. In this paper, the common approach of
using a flight control surface to provide the excitation is examined us ing a mathematical
model of a wing and control surface whose rotation is restrained by a simple actuator. In
particular, it is shown that it is essential to use the demand signal to the actuator as a reference
signal for data processing. Use of the actuator force (or strain) or control angle (or actuator
displacement) as a reference signal is bad practice because these signals contain response
information. It may also be dangerous in that the onset of flutter may not be seen in the test
results. Control sur face flutter is of particular concern.
Disciplines :
Aerospace & aeronautics engineering
Author, co-author :
Wright, Jan R; University of Manchester > School of Engineering
Wong, Jerry; University of Manchester > School of Engineering
Cooper, Jonathan Edward; University of Manchester > School of Engineering
Dimitriadis, Grigorios ; Université de Liège - ULiège > Département d'aérospatiale et mécanique > Interactions Fluide-Structure - Aérodynamique expérimentale
Language :
English
Title :
On the use of control surface excitation in flutter testing
Publication date :
June 2003
Event name :
International Forum on Aeroelasticity and Structural Dynamics, IFASD 2003
Event organizer :
Council of European Aerospace Sciences, American Institute of Aeronautics and Astronautics
Event place :
Amsterdam, Netherlands
Event date :
du 4 juin au 6 juin 2003
Audience :
International
Main work title :
Proceedings of the 2003 International Forum on Aeroelasticity and Structural Dynamics
