Use of bifurcation methods in the identification and control of flexible aircraft dynamics

N. Baghdadi*, M. H. Lowenberg, A. T. Isikveren

*Corresponding author for this work

Research output: Chapter in Book/Report/Conference proceedingConference Contribution (Conference Proceeding)

Abstract

Modern commercial aircraft designs are continuously driven towards a light weight and large aspect ratio configurations to meet performance and mission requirements. Consequently, these aircraft are characterised by flexible structures having large structural deformations, and in turn, the frequency separation between the flexible and rigid body modes is greatly reduced. In the presence of nonlinearities, the effects of flexibility on the flight dynamics of such vehicles have been shown to be significant. Conventional methods are not suitable to accurately predict the stability characteristics and handling qualities of such vehicles. This paper demonstrates the effects of flexibility on the dynamics, stability and control of elastic aircraft using a novel analysis framework based on bifurcation and continuation tools linked to classical aeroelastic methods. The robustness of different control law designs to supress nonlinear aeroelastic induced instabilities is also investigated.

Original languageEnglish
Title of host publicationCollection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
Publication statusPublished - 2010
Event51st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference - Orlando, FL, United States
Duration: 12 Apr 201015 Apr 2010

Conference

Conference51st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
CountryUnited States
CityOrlando, FL
Period12/04/1015/04/10

Fingerprint

Dive into the research topics of 'Use of bifurcation methods in the identification and control of flexible aircraft dynamics'. Together they form a unique fingerprint.

Cite this