Publications
197 results found
Ng BF, Hesse H, Palacios R, et al., 2014, Aeroservoelastic state-space vortex lattice modeling and load alleviation of wind turbine blades, Wind Energy, Vol: 18, Pages: 1317-1331, ISSN: 1095-4244
An aeroservoelastic model, capturing the structural response and the unsteady aerodynamics of turbine rotors, will be used to demonstrate the potential of active load alleviation using aerodynamic control surfaces. The structural model is a geometrically non-linear composite beam, which is linearized around equilibrium rotating conditions and coupled with time-domain aerodynamics given by a linearized 3D unsteady vortex lattice method. With much of the existing work relying on blade element momentum theory with various corrections, the use of the unsteady vortex lattice method in this paper seeks to complement and provide a direct higher fidelity solution for the unsteady rotor dynamics in attached flow conditions. The resulting aeroelastic model is in a state-space formulation suitable for control synthesis. Flaps are modeled directly in the vortex lattice description and using a reduced-order model of the coupled aeroelastic formulation, a linear-quadratic-Gaussian controller is synthesized and shown to reduce root mean square values of the root-bending moment and tip deflection in the presence of continuous turbulence. Similar trend is obtained when the controller is applied to the original non-linear model of the turbine. Trade-offs between reducing root-bending moment and suppressing the negative impacts on torsion due to flap deployment will also be investigated.
Hesse H, Palacios R, Murua J, 2014, Consistent Structural Linearization in Flexible Aircraft Dynamics with Large Rigid-Body Motion, 53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, Honolulu, Hawaii, Publisher: American Institute of Aeronautics and Astronautics, Pages: 528-538, ISSN: 0001-1452
Wang Y, Wynn A, Palacios R, 2014, Nonlinear Model Reduction and Aeroelastic Control of Flexible Aircraft Described by Large Finite-Element Models, 55th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
Tantaroudas ND, Da Ronch A, Gai G, et al., 2014, An Adaptive Aeroelastic Control Approach by using Nonlinear Reduced Order Models, AIAA Aviation and Aeronautics Forum and Exposition, 16-20 June 2014, Atlanta, Georgia, USA
Ng BF, Hesse H, Palacios R, et al., 2014, Efficient Aeroservoelastic Modeling and Control using Trailing-Edge Flaps of Wind Turbines, United-Kingdom-Automatic-Control-Council (UKACC) 10th International Conference on Control (CONTROL), Publisher: IEEE, Pages: 1-6
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Buoso S, Palacios R, 2014, A NONLINEAR VISCOELASTIC MODEL FOR ELECTROACTIVE INFLATED MEMBRANES, 11th World Congress on Computational Mechanics (WCCM) / 5th European Conference on Computational Mechanics (ECCM) / 6th European Conference on Computational Fluid Dynamics (ECFD), Publisher: INT CENTER NUMERICAL METHODS ENGINEERING, Pages: 4300-4312
Ronch AD, McCracken AJ, Tantaroudas ND, et al., 2014, Assessing the Impact of Aerodynamic Modelling on Manoeuvring Aircraft, AIAA Atmospheric Flight Mechanics Conference
Ng BF, Hesse H, Palacios R, et al., 2014, Model-based Aeroservoelastic Design and Load Alleviation of Large Wind Turbine Blades, 32nd ASME Wind Energy Symposium
Van Parys BPG, Ng BF, Goulart PJ, et al., 2014, Optimal control for load alleviation in wind turbines, 32nd ASME Wind Energy Symposium
Simpson RJS, Palacios R, Hesse H, et al., 2014, Predictive Control for Alleviation of Gust Loads on Very Flexible Aircraft, 55th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
Wynn A, Wang Y, Palacios R, et al., 2013, An Energy-Preserving Description of Nonlinear Beam Vibrations in Modal Coordinates, Journal of Sound and Vibration, Vol: 332, Pages: 5543-5558, ISSN: 0022-460X
Conserved quantities are identified in the equations describing large-amplitude free vibrations of beams projected onto their linear normal modes. This is achieved by writing the geometrically-exact equations of motion in their intrinsic, or Hamiltonian, form before the modal transformation. For nonlinear free vibrations about a zero-force equilibrium, it is shown that the finite-dimensional equations of motion in modal coordinates are energy preserving, even though they only approximate the total energy of the infinite-dimensional system. For beams with constant follower forces, energy-like conserved quantities are also obtained in the finite-dimensional equations of motion via Casimir functions. The duality between space and time variables in the intrinsic description is finally carried over to the definition of a conserved quantity in space, which is identified as the local cross-sectional power. Numerical examples are used to illustrate the main results.
Hesse H, Palaciosy R, 2013, Model reduction in flexible-aircraft dynamics with large rigid-body motion, ISSN: 0273-4508
This paper investigates the model reduction, using balanced realizations, of the unsteady aerodynamics of maneuvering exible aircraft. The aeroelastic response of the vehicle, which may be subject to large wing deformations at trimmed flight, is captured by coupling a displacement-based, exible-body dynamics formulation with an aerodynamic model based on the unsteady vortex lattice method. Consistent linearization of the aeroelastic problem allows the projection of the structural degrees of freedom on a few vibration modes of the unconstrained vehicle, but preserves all couplings between the rigid and elastic motions and permits the vehicle flight dynamics to have arbitrarily-large angular velocities. The high-order aerodynamic system, which defines the mapping between the small number of generalized coordinates and unsteady aerodynamic loads, is then reduced using the balanced truncation method. Numerical studies on a representative high-altitude, long-endurance aircraft show a very substantial reduction in model size, by up to three orders of magnitude, that leads to model orders (and computational cost) similar to those in conventional frequency-based methods but with higher modeling fidelity to compute maneuver loads. Closed-loop results for the Goland wing finally demonstrate the application of this approach in the synthesis of a robust utter suppression controller. © 2012 AIAA.
Dizy J, Palacios R, Pinho ST, 2013, Homogenisation of Slender Periodic Composite Structures, 53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, Honolulu, Hawaii [Lockheed Martin Best Student Paper Award], Pages: 1473-1481
Ng BF, Hesse H, Palacios R, et al., 2013, Aeroservoelastic Modelling and Robust Load Alleviation of Very Large Flexible Wind Turbine Blades, American Wind Energy Conference WINDPOWER 2013 Conference & Exhibition, Chicago, Illinois, USA
Hesse H, Palacios R, 2013, Model Reduction in Flexible-Aircraft Dynamics with Large Rigid-Body Motion, 54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, Boston, Massachusetts
Simpson R, Palacios R, 2013, Numerical Aspects of Nonlinear Flexible Aircraft Flight Dynamics Modeling, 54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, Boston, Massachusetts
Arbos-Torrent S, Ganapathisubramani B, Palacios R, 2013, Leading- and Trailing-Edge Effects on the Aeromechanics of Membrane Aerofoils, Journal of Fluids and Structures, Vol: 38, Pages: 107-126
Wang Y, Wynn A, Palacios R, 2013, Robust Aeroelastic Control of Very Flexible Wings using Intrinsic Models, 54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, Boston, Massachusetts
Fogell NA, Sherwin S, Cotter CJ, et al., 2013, Fluid-structure iInteraction simulation of theinflated shape of ram-air parachutes, 22nd AIAA Aerodynamic Decelerator Systems Technology Conference, Daytona Beach, Florida [Best Student Paper Award]
Cook R, Palacios R, Goulart P, 2013, Robust gust alleviation and stabilization of very flexible aircraft, AIAA Journal, Vol: 51, Pages: 330-340
Simpson RJS, Palacios R, Murua J, 2013, Induced Drag Calculations in the Unsteady Vortex Lattice Method, AIAA Journal, Pages: 1-10
Gonzalez A, Munduate X, Palacios R, et al., 2013, Aeroelastic Tools for 2D Airfoils with Variable Geometry For Wind Turbine Applications, European Wind Energy Association Annual Event, Vienna, Austria
Palacios R, Wang Y, Wynn A, et al., 2013, Condensation of Large Finite-Element Models for Wing Load Analysis with Geometrically-Nonlinear Effects, International Forum of Aeroelasticity and Structural Dynamics 2013, Pages: 1-25
Murua J, Martinez P, Climent H, et al., 2013, T-tail flutter: Potential-flow modelling and experimental validation, International Forum of Aeroelasticity and Structural Dynamics, Bristol, UK
Hesse H, Palacios R, 2013, Reduced-Order Aeroelastic Models for the Dynamics of Manoeuvring Flexible Aircraft, International Forum of Aeroelasticity and Structural Dynamics 2013, Pages: 1-25
Dizy J, Palacios R, Pinho ST, 2013, Shear Effects in the Homogenisation of Slender Composite Beams, 5th European Conference for Aerospace Sciences (EUCASS), Munich, Germany
Murua J, Martinez P, Climent H, et al., 2013, T-tail Flutter: Potential-Flow Modelling and Experimental Validation, 16th International Forum of Aeroelasticity and Structural Dynamics
Hesse H, Murua J, Palacios R, 2012, Consistent structural linearization in flexible aircraft dynamics with large rigid-body motion
This paper investigates the linearization, using perturbation methods, of the struc-tural deformations in the nonlinear ight dynamic response of aircraft with slender, flex- ible wings. This has been achieved by first coupling a displacement-based, geometrically- nonlinear flexible-body dynamics formulation with the 3D Unsteady Vortex-Lattice Method, followed by a consistent linearization of the structural degrees of freedom, which are as- sumed to be small in a body-flxed reference frame. The translations and rotations of that reference frame can be arbitrarily large, however. The resulting system preserves all cou- plings between rigid and elastic motions and can be projected onto a few vibration modes of the unconstrained aircraft with arbitrarily-large, geometrically-nonlinear deformation at a trim condition. The dynamics of the system are then written in tensor form, with up to cubic terms due to the nonlinear rigid-body terms, and with a limited number of coeficients that can be pre-computed prior to the time-marching simulation. Numerical studies on a representative HALE UAV are presented to illustrate the approach and results are compared to the mean-axes solution. © 2012 by Henrik Hesse, Joseba Murua, Rafael Palacios.
Murua J, Palacios R, Graham JMR, 2012, Applications of the Unsteady Vortex-Lattice Method in Aircraft Aeroelasticity and Flight Dynamics, Progress in Aerospace Sciences, Vol: 55, Pages: 46-72
Hesse H, Palacios R, 2012, Consistent Structural Linearisation in Flexible-Body Dynamics with Large Rigid-Body Motion, Pages: 1-14
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