Gust Load Alleviation Using Nonlinear Reduced Models For Control Law Design N.D.Tantaroudas K.J. Badcock, A. Da Ronch University of Liverpool, UK Bristol,

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Presentation transcript:

Gust Load Alleviation Using Nonlinear Reduced Models For Control Law Design N.D.Tantaroudas K.J. Badcock, A. Da Ronch University of Liverpool, UK Bristol, 13 December 2012 FlexFlight: Nonlinear Flexibility Effects on Flight Dynamics Control of Next Generation Aircraft

Overview Very large or very flexible aircraft - low frequency modes-large amplitudes - coupled rigid body/structural dynamics TestCase-UAV configuration -Modal Analysis(Nastran) -Model Identification of the Structural Model-Implementation -Model Order Reduction -Gust Responses/Linear Aerodynamics(Strip Theory) -Control design Using Reduced Models for Worst Gust Case

Model Reduction eigenvalue problem of Jacobian A FOM projection onto aeroelastic eigenmodes

UAV Configuration DSTL UAV[P. Hopgood] Wing -Span:16.98m -Taper Ratio:0.44 -Root Chord:1.666m -Tip Chord:0.733m -Control Surface:16/100chord Tail -Dihedral:45deg -Taper Ratio: Root Chord:1.393m -Tip Chord:0.678m -Control Surface:25/100 chord

Model Identification Beam Reference system –j-node: Finite Element equation-dimensional form : Modal Analysis(Nastran) -Match the frequency of the low frequency modes - Match modeshapes Limitations -High frequency modeshapes difficult to be matched

Model Identification From 2D plate to 1D beam model

Mode Identification Part F -Hz F Tuned -HzModeshape Wing First Bending Mode Wing Second Bending Mode Wing First In Plane Bending Mode Wing Third Bending Mode Wing First Torsional Mode Wing Fourth Bending Mode Wing Second In Plane Bending Mode Tail First Bending Mode Tail Torsional Mode

Model Identification f=1.45Hz

Model Identification f=6.27Hz

Model Identification f=13.20Hz

Model Identification f=24.01Hz

Model Identification

Model Order Reduction -Wing Tip Vertical Deflection Time Response Without Aerodynamics Harmonic Follower Force -ROM/NROM –structural eigenvalues

Aeroelastic Gust Responses -Wing tip vertical displacement Reduced Basis-Structural

Aeroelastic Gust Responses -Wing tip vertical displacement Reduced Basis -Structural +Aero

Worst Case Gust 1 minus-Cosine Gust for several gust lengths

Worst Case Gust-Reduced Models

FOM linear beamROM linear beam FOM nonlinear beamROM nonlinear beam

Control Design Using Reduced Models Linear Controller Tuning Parameters :control input weight :noise weight Linear Reduced Order Model

Control Design Using Reduced Models

Control Design Using Non Linear Reduced Models

Non Linear Restoring Forces-Stability 3dof of freedom aerofoil

Non Linear Restoring Forces-Stability hardening spring softening spring->instability 3dof aerofoil 1 minus cosine Gust Softening Spring Linear Control Design in this case??

Instability

Conclusions-Future Work Reduced Basis identified with Linear Aerodynamics - Structural eigenvalues - not always perfect descriptions when gust included -Structural+aero - for improved predictions Linear Control techniques suitable for Non Linear Structures - Structural Nonlinearity  stability of the system Future Work -I ntroduction of the rigid body and flight dynamics in Beam Framework -Control of the DSTL UAV with gust -Softening nonlinearity  need for Non Linear Control?