Dr. Gareth A. Vio

Photo of Dr. Gareth Vio

BEng (Hons) PhD Manchester SMAIAA AACM FTSA

Lecturer in Aerospace Engineering

Phone:    +61 (0)2 9351 2394
Fax:         +61 (0)2 9351 7060
E-mail:     gareth (dot) vio at sydney (dot) edu (dot) au
Address: Room N306, Aeronautical Engineering Building J11
                 School of Aerospace, Mechanical and Mechatronic Engineering
                 The University of Sydney
                 NSW 2006
                 Australia

Qualifications

  • PhD, Aerospace Engineering, The University of Manchester, 2005
  • BEng (Hons), Aerospace Engineering, The University of Manchester, 1999

Employment history

  • Lecturer in Aerospace Engineering, The University of Sydney, 2010-present
  • Research Associate, The University of Liverpool, UK, 2007-2010
  • Research Associate, The University of Manchester, UK, 2005-2007
  • Research Assistant, The University of Manchester, UK, 2002-2005

Current Undergraduate Teaching

Past Undergraduate Teaching

Research interests

  • Non-linear Aeroelasticity
  • Non-linear Vibration
  • Non-Linear System Identification
  • Gust Response
  • Aeroelastic Tailoring
  • Design of Composite Structures
  • Morphing Structures
  • Natural Selection Optimisation
  • Frangibility

Research Projects

  • AeroThermoElasticity

    The eld of aeroelasticity and particularly aerothermoelasticity is becoming more prominent and gaining more research in the aerospace field. With hypersonic transport increasingly becoming a not too distant prospect, research and development into this flight regime is paramount to enhance our understanding in this area. For many years, aeroelasticity has been seen as a degradation to aircraft performance. The majority of previous aeroelastical studies are with reference to quantifying this loss in performance to define fl ight envelope boundaries and aircraft limitations. At the forefront of aeroelastical studies, a paradigm shift is being realised such that aeroelasticity is no longer seen as causing performance degradation, but rather, structures are being designed to take advantage of aeroelastical effects. Aerothermoelasticity, the interaction between thermal e ects and aeroelasticity, is key to this body of work. Thermal effects in the supersonic and hypersonic regime have been the topic of a number of research investigations.

  • Aeroelastic Tailoring

    Composites have been aliated with aeroelastic tailoring since their advent in the 1970s. Since then, they have been continually gaining ground on aluminium in the aerospace industry because of their high strength to weight ratio. Despite the vast body of research on advanced composites, they are not being fully exploited for their directional properties in their current application on aircraft structures. In light of this reality, and the prediction that a fully composite non-conventional airframe will de ne the future commercial airliner, a novel wing box design is proposed that is situated in the gap between what currently exists and the potential of what could be.

  • Non-linear Energy Sinks

    Modern aircraft are becoming ever lighter as designers strive for greater eciency, which has seen a continuing trend towards newer, lighter and more structurally ecient materials. As a result, aircraft structures are becoming inherently less sti , and more susceptible to flutter and other aeroelastic phenomena. Lighter, fl exible structures, are also subject to higher induced stresses from gust loads. These structures are designed with advanced materials, such as composites, to withstand such stresses. However, reduction of loads and stresses in any structure is always optimal. Previous research has generally focussed on independent mechanisms to obtain either gust or utter suppression, and there exists little research that considers the application of a single mechanism to achieve these goals simultaneously. Obviously, such a device is more desirable if it can achieve similar performance to the independent systems.

  • Non-linear Vibration and System Identification

    The identification of the presence of nonlinearities and their localisation is of extreme importance in system for maintenance and safety.

  • Highly Flexible Structures

    Aircraft are becoming more flexible due to a reduction in structural mass. THis as a consequence has reduced the stiffness of the flying platform. This reduction induceds higher degree of flexibility onto the structure. Been able to accurte model these effect adn their consequence on teh loads of an aircraft of imperative for the safe operation.

  • Non-Linear Aeroelastic Prediction

    Non-linearity appear in everyday life and in aircraft have unwated effect, that can lead to fatigue related issue or catastrophic events. THese non-linearity arise from structures, mechanical systems, aerodynamics, control laws. Been able to assess and predict were the non-linear behaviour is safe to oeprate is of critical importance.

  • Passive Gust Alleviation

    There is interest, particularly at AFRL Air Vehicle Directorate in the development of unmanned High Altitude Long Endurance (HALE) or Sensorcraft air vehicles that are able to provide a 360 degree sensor coverage whilst maintaining moderate stealth characteristics. The sensor requirement has naturally led to a re-visit of the pioneering work into joined-wing aircraft by Wolkovich. Typical joined-wing sensorcraft structural lay-outs differ considerably form onventional aicraft configurations, where the the aeroelastic behaviour is likely to be very different. Much of the work on sensorcraft has been focused upon the optimisation of the aircraft structure. The outer wing of the sensor craft design leads to the high aspect ratio, which is very favourable for reduction in fuel consumption and range extension. However, it produces high bending moments stemming from manoeuvres or gusts. Due to its significant flexibility there have been concerns about:

    • the ability to maintain a shape that does not affect the sensor performance
    • the loads that may result from gusts
    • the need to use non-linear static and dynamic aeroelastic analysis in order to account for the large geometric deflections.

    One of the critical design cases for joined-wing designs is the buckling of the rear wing structure. Previous work has shown that non-linear buckling analysis is required in order to estimate accurately the deflections and resulting loads that occur. Linear analysis for buckling under critical gusts loads significantly increased the wing optimized structural weight, almost doubling it, and when non-linear analysis is used, the wing tip deflection increases and the optimized wing weight increases significantly again. The use of some form of gust load alleviation system is therefore very desirable, as this should lead to a significant reduction in structure, and hence weight, that is required. One possible solution is the design of active load alleviation systems using all of the control surfaces; however, such an approach is complex, requiring the avionics for such a system to be carried on the sensorcraft, and a certain amount of system redundancy must be included to allow for system failures.

  • Morphing Structures

    There is a growing interest in the development of adaptive aeroelastic structures to allow aeroelastic deflections to be used in a beneficial manner. They are a subset of Morphing Structures, but rather than attempting to change the wing plan-form, the stiffness of the structure is adjusted to influence the aerodynamic performance. Such an approach will lead to more efficient aircraft designs. For example, the wing twist could be adjusted throughout the entire flight in order to maintain a shape giving optimal lift-drag ratio for maximum range, and also as a means of roll and loads control. Other concepts are being developed to change the wing leading and trailing edge shape in order to adjust the lift coefficient, and also to change the wing planform shape. In recent years, a number of research programmes, for example the Active Aeroelastic Wing and the Morphing Programme, have started to develop active aeroelastic concepts. active aeroelastic concepts on a number of large wind tunnel models. The research programme is devoted towards investigating the use of changes in the internal aerospace structure in order to control the static aeroelastic behaviour. Such an approach is desirable, and arguably advantageous compared to other possible concepts. For instance, the use of leading and trailing control surfaces to control wing twist can lead to increased drag and poor observability characteristics. The use of smart materials (e.g. piezo and shape memory alloys) has received considerable attention in recent years, but still suffers from limits in the amount of force that can be achieved currently in relation to that required to twist or bend a wing. The key idea exploited in the Adaptive Internal Structures approach is to make use of the aerodynamic forces acting upon the wing to provide the moment to twist the wing. By changing the position of the shear centre of the wing, the bending moment, and hence the amount of twist, will also change. A far smaller amount of energy is required to adjust the structure compared to that required to twist the wing and keep it in that shape. Such an approach is very attractive for active aeroelastic wing concepts and leads the way for the adaptive structural control of aerodynamic performance as well as roll and loads control.

  • Non-Linear Damping Identification

    The problem of modelling damping in structures is not well-understood because often in traditional structural design it is not actually important, mainly because there are no instabilities and there is no reason to accurately model it. In the aeroelastic problem, instead, the occurrence of instabilities may strongly depend on damping and catastrophic events can occur. Flutter is a characteristic form of self-excited oscillations that can arise through the interaction of an aerodynamic flow with the elastic modes of a mechanical structure, e.g. the bending and torsion modes of an aircraft wing. The occurrence of flutter compromises the operational safety, flight performance and energy efficiency of the aircraft. From the structural point of view, the main sources of damping in a wing are the friction in joints, viscous damping due to air flow and material damping. Modelling of damping is a very difficult issue because the level of damping in a structure can depend, for example, on the material, the methods used for manufacturing and the final finishing processes. The interfacial damping mechanism, instead, results from Coulomb friction between members and connections and can depend on clamp force of bolts or welded connections. For all these reasons, normally the identification is preferred to modelling because trying to extract damping parameters by experiments is simpler than collecting all the information to model damping accurately. Damping identification in aeroelastic structure is often performed during Ground Vibration Testing (GVT). Very little attention has been given at the damping identification process while an aircraft is in flight, as different non-linear regions, both structural or damping, can be entered, giving different energy dissipation. A number of experimental techniques are available for the identification of modal parameters using curvefitting methods or signal processing techniques.

  • Worst Gust Response

    Unsteady loads calculations play an important part across much of the design and development of an aircraft, and have an impact upon the concept and detailed structural design, aerodynamic characteristics, weight, flight control system design, control surface design and performance. They determine the most extreme stress levels and estimate fatigue damage and damage tolerance for a particular design. The certification of large commercial aircraft is covered by the EASA CS-25 (Certification Specifications) or FAR-25 documents. A range of load cases that has to be accounted for are described and are a primary prerequisite for assuring structural integrity over the operating environment of the aircraft. Loads requirements are defined in the context of the design envelope. Certification specifications require that enough points, on or within the boundary of the design envelope, are investigated to ensure that the most extreme loads for each part of the aircraft structure are identified. The flight conditions and manoeuvres, which provide the largest aircraft loads, are not known a-priori. Therefore the aerodynamic and inertial forces are calculated at a large number of conditions to give an estimate of the maximum loads, and hence stresses, that the structure of the detailed aircraft design will experience in service. A simplistic estimate of the number of analyses required would multiply the numbers of conditions to give 10,000,000. Even with simplistic models of the aircraft behaviour this is an unfeasible number of separate simulations. However, engineering experience is used to identify the most likely critical loads conditions, meaning that approximately 100,000 simulations are required for conventional aircraft configurations. Furthermore these analyses have to be repeated every time that there is an update in the aircraft structure. Within the modern civil airframe industry, each of these loads calculation cycles takes a considerable time. The number of different flight conditions that need to be considered to assess the maximum loads that will be encountered by a civil aircraft is large and must be reduced. At present engineering experience is used to achieve a significant reduction for conventional aircraft geometries whose response can be calculated using assumptions of linearity. With the advent of non-linear control systems and new manufacturing techniques, even conventional aircraft are becoming increasingly nonlinear and the linearity assumption is becoming unacceptable.

Research Groups

Vibration and Aeroelasticity Group at The Univeristy of Sydney

Publications

    Journal Under Review

  • D. Munk, G.A. Vio and G. Steven, "Topology and shape optimisation methods using evolutionary algorithms", submitted to Structural and Multidisciplinary Optimization Accepted
  • D. Munk, G.A. Vio and G. Steven, "Structural Optimisation of a Conventional UAV Wing using an Updated Moving Iso-Surface Threshold Technique", submitted to Aerospace Science and Technology
  • D. Munk, G.A. Vio and D. Verstraete, "Transient Temperature Effect on the Aerotehrmoelastic Response of a Wing", submitted to AIAA Journal
  • Journal Under Preparation

  • N.F. Giannelis and, G.A. Vio, "Non-Linear ANalysis of Acoustic-Aeroelastic Interaction", to be submitted to Journal of Vibration and Acoustics
  • N.F. Giannelis, G.A. Vio and O. Levinski, "Computational Benchmark of Commercial Fluid-Structure Interaction Software", to be submitted to Aeronautical Journal
  • N.F. Giannelis, G.A. Vio and I. Manchester, "Convex Optimisation of the Aeroelastic Galloping Problem: Computational and Experimental Verification", To be submitted to Journal of Fluids and Structures
  • Abstracts Submitted to Conferences

  • D.J. Munk, G.A. Vio and G. Steven, "Aerothermoelastic Structural Topology Optimisation for Hypersonic Transport Aircraft Wing", WCSMO, Sydney, Australia, 2015.
  • N.F. Giannelis, G.A. Vio, "Computational Benchmark of Commercial Fluid-Structure Interaction Software", IFASD, Saint Petersburg, Russia, 2015.
  • N.F. Giannelis, G.A. Vio and I. Manchester, "System Identification of the Aeroelastic Galloping Problem via Convex Optimisation", IFASD, Saint Petersburg, Russia, 2015.
  • D. Munk, G.A. Vio and G. Steven, "A Novel Method for the Vibration Optimisation of Structures Subjected to Dynamic Loading", IFASD, Saint Petersburg, Russia, 2015.
  • Journal Publications

  • D. Munk, G.A. Vio and D. Verstraete, "Response of a Three-Degree-of-Freedom Wing with Stiffness and Aerodynamic Nonlinearities at Hypersonic Speeds", Nonlinear Dynamics, 2015
  • N.F. Giannelis, G.A. Vio, D. Verstraete and J. Steelant, "Temperature Effect on the Structural Design of a Mach 8 Vehicle", Applied Mechanics and Materials, Vol 553, pp. 249-254, 2014
  • B.J. Morrell, D.J. Munk, G.A. Vio and D. Verstraete, "Development of a Hypersonic Aircraft Design Optimization Tool", Applied Mechanics and Materials, Vol 553, pp. 847-852, 2014
  • J.D. El Tom and G.A. Vio, "Novel Wing Box Design", Applied Mechanics and Materials, Vol 553 pp. 243-248, 2014
  • G. Georgiou, G.A. Vio and J.E. Cooper, Aeroelastic tailoring and scaling using Bacterial Foraging Optimisation, Structural and Multidisciplinary Optimisation, 50(1), 81-99, 2014
  • H.H. Khodaparast, G. Georgiou, J.E. Cooper, L. Riccobene, S. Ricci, G.A. Vio and P. Denner, "Efficient Worst Case '1-cosine' gust loads prediction", Journal of Aeroelasticity and Structural Dynamics, 2(3), 33-54, 2012.
  • M.R. Amoozgar, S. Irani and G.A. Vio, "Aeroelastic instability of a composite wing with a powered engine", Journal of Fluids and Structures, 36, 70-82, 2012.
  • A. Manan, G.A. Vio, M.Y. Harmin and J.E. Cooper, “ Optimisation of aeroelastic composite structures using evolutionary algorithms ”, Engineering Optimization, 42(2), 171-184, 2010.
  • Z Gu, S. O. Oyadiji and G.A. Vio, " Fuzzy adaptive control of hysteretic based-isolated structural system under seismic disturbances", International Journal of Applied Mathematics and Mechanics, 5(1), 89-101, 2009.
  • M.J. de C. Henshaw, G.A. Vio et all, “Nonlinear aeroelastic prediction for aircraft applications”, Progress in Aerospace Sciences, 43(4), pp 65-137, 2007.
  • G.A. Vio. G. Dimitriadis and J.E. Cooper, “A comparison of bifurcation and LCO amplitude prediction methods applied to the aeroelastic galloping problem”, Journal of Fluids and Structures, 23(7), 983-1011, 2007.
  • G.A. Vio, J.E. Cooper, G. Dimitriadis, K. Badcock, M. Woodgate and A. Rampurawala, “Aeroelastic system identifcation using transonic CFD data for a wing/store configuration”, Aerospace Science and Technology, Vol 11, No (2-3), 2007, pp 146-154.
  • G. Dimitriadis, G.A. Vio, "Demonstrating the identification of nonlinear vibrating systems to undergraduate students", International Journal of Mechanical Engineering Education, 35(4), 336-360, 2007.
  • Z.Q. Gu, G.A. Vio, S.O. Oyadiji, "Vibration control of nonlinear systems using RBF-based sliding mode control", International Journal of Applied Mathematics and Mechanics, 3(4), 56-68, 2007.
  • N.V. Taylor, G.A. Vio, A.M. Rampurawala, C.B. Allen, K.J. Badcock, J.E. Cooper, A.L. Gaitonde, M.J. deC. Henshaw, D.P Jones and M.A. Woodgate, "Aeroelastic simulation through linear and non-linear analyses: a summary of flutter prediction in the PUMA DARP", Aeronautical Journal, 110(1107), 333-343, 2006.
  • G.A. Vio, J.E. Cooper, "Limit cycle oscillation prediction for aeroelastic systems with discrete bilinear stiffness", International Journal of Applied Mathematics and Mechanics, 1(3), 100-119, 2005.
  • Book Contributions

  • G. Dimitriadis, G.A. Vio, D. Shi, "An expert system for the identification of nonlinear dynamical systems", In Intelligent Computing, D.S. Huang, K. Li, G.W. Erwin editors, volume 4113 of Lecture Notes in Computer Science, pages 1263-1268, Springer-Verlag, Berlin/Heidelberg, 2006.
  • J.E. Cooper, V. Hodigere-Siddaramaiah, G.A. Vio, S. Miller and G. Dimitriadis, "Adaptive aeroelastic structures for improved aircraft performance", In World Forum on Smart Materials and Smart Structures technology, B.F. Spencer, M. Tomizuka, C.B. Yun and R.W. Chen editors, pages 415-417, CRC Press, 2008.
  • Invited Conference Contributions

  • J.E. Cooper, G. Dimitriadis, G.A. Vio, J.R Wright and Y. Zhang, "Non-linear aeroelasticity - Identification and Prediction", 6th International Conference on Mathematical Problems in Engineering and Aerospace Sciences, Budapest, June 2006.
  • Peer Reviewed Conference Publications

  • N.F. Giannelis and G.A. Vio, "Computational Benchmark of Commercial Fluid-Structure Interaction Software", 16th Australian International Aerospace Congress, Melbourne, Australia, 2015
  • N.F. Giannelis and G.A. Vio, "Effect of Structural Nonlinearity on the Dynamic Response of a Coupled Acoustic-Aeroelastic System", 16th Australian International Aerospace Congress, Melbourne, Australia, 2015
  • D.J. Munk and G.A. Vio, "Effect of Structural Uncertainty on Flutter Velocity", 16th Australian International Aerospace Congress, Melbourne, Australia, 2015
  • D.J. Munk, G.A. Vio and D. Verstraete, "Effect of Structural Non-Linearities on the Aeroelastic Response", 16th Australian International Aerospace Congress, Melbourne, Australia, 2015
  • D.J. MunkG.A. Vio and D. Verstraete, "Simulation of Non-Linear Heat Loading in UAVs and its Effect on Structural Integrity", Fourth Australasian Conference on Unmanned Systems, Melbourne, Australia, 2014
  • N.F. Giannelis and G.A. Vio, "Aeroelastic Optimisation of an Alternative High Altitude Long Endurance Wing Stiffening Structure", Fourth Australasian Conference on Unmanned Systems, Melbourne, Australia, 2014
  • D. Verstraete and G.A. Vio, "Temperature effects on flutter of a Mach 5 transport aircraft wing", ASME International Mechanical Engineering Congress and Exposition, Houston, 2012.
  • J. Worotynska, G.A. Vio, C. Mouser, "Experimental and computational investigation of chordwise flexible structures", ICAS Conference, Brisbane, Australia, September 2012.
  • I.F. Fitzpatrick, G.A. Vio, "Design of Composite structures for Improved Aeroelastic performance", ICAS Conference, Brisbane, Australia, September 2012.
  • D.S. Stanley and G.A. Vio, "Non-linear Behaviour of a Wing due to Underwing Stores", ICAS Conference, Brisbane, September 2012.
  • G.A. Vio, "Bifurcation Prediction of the Aeroelastic Galloping Model with Structural and Damping Non-Linearities", 15th Australasian Wind Engineering Society Workshop, Sydney, Australia, 2012.
  • G.A. Vio, "Damping Identification and Location in a Structurally Nonlinear Aeroleastic System", 14th AIAC, Australia, 2011.
  • G.A. Vio, S. Miller and J.E. Cooper, "Gust Alleviation Device Applied to the Sensorcraft Platform", 14th AIAC, Australia, 2011.
  • G. Dimitriadis, G.A. Vio, D. Shi, "An expert system for the identification of nonlinear dynamical systems", International Conference on Intelligent Computing, Kunming, China, August 2006.
  • G.A. Vio, G. Dimitriadis and D. Shi, "System identification of theoretical and experimental data for mechanical systems";, 9th International Conference on Recent Advances in Structural Dynamics, Southampton, UK, 2006.
  • G.A. Vio, G. Dimitriadis, J.E. Cooper, K Badcock, M. Woodgate and A. Rampurawala, "Aeroelastic system identification using transonic CFD data for a 3D wing", 9th International Conference on Recent Advances in Structural Dynamics, Southampton, UK, July 2006.
  • G. Dimitriadis, G.A. Vio and J. E. Cooper, "Limit Cycle Prediction For Subsonic Aeroelastic Systems Using Nonlinear System Identification", 8th International Conference on Recent Advances in Structural Dynamics, Southampton, UK, July 2003.
  • Other Conference Publications

  • D.J. Munk, G.A. Vio and D. Verstraete, "Aerothermoelastic Structural Topology Optimisation for hypersonic Transport Aircraft Wing", 8th European Symposium on Aerothermodynamics for Space Vehicles, Portugal, 2015.
  • S.L. Kukreja, G.A. Vio, T. Andrianne, N.A. Razak and G. Dimitriadis, "NAR(MA) identification of the stall flutter response of a rectangular wing in a wind tunnel", 53rd AIAA Structures, Structural Dynamics and Materials Conference, Waikiki, Hawaii, USA, April 2012.
  • G.A. Vio, and G. Dimitriadis, "Computational and Experimental identification of non-linear damping in an aeroelastic system", 53rd AIAA Structures, Structural Dynamics and Materials Conference, Waikiki, Hawaii, USA, April 2012.
  • J. Worotynska, G.A. Vio, M. Berci and G. Dimitriadis, "Experimental and computational investigation of chordwise flexible structures", 53rd AIAA Structures, Structural Dynamics and Materials Conference, Waikiki, Hawaii, USA, April 2012.
  • G.A. Vio, G. Georgiou, J.E. Cooper, "Composite structures to Improve Aeroelastic performance", 53rd AIAA Structures, Structural Dynamics and Materials Conference, Waikiki, Hawaii, USA, April 2012.
  • H.H. Khodaparast, G. Georgiou, J.E. Cooper, L. Riccobene, S. Ricci, G.A. Vio and P. Denner, "Efficient worst case "1-cosine" gust loads prediction", CEAS International Forum on Aeroelasticity and Structural Dynamics, Paris, France, June 2011.
  • G. Georgiou, G.A. Vio and J.E. Cooper, "Aeroelastic optimisation using evolutionary methods", CEAS International Forum on Aeroelasticity and Structural Dynamics, Paris, France, June 2011.
  • H.H. Khodaparast, G. Georgiou, J.E. Cooper, L. Travaglini, S. Ricci, G.A. Vio and P. Denner, "Rapid prediction of worst case gust loads", 52nd AIAA Structures, Structural Dynamics and Materials Conference, Denver, Colorado, USA, April 2011.
  • G.A. Vio, M. Prandina and G. Dimitriadis, "Damping identification in a nonlinear aeroelastic structure", International conference on Noise and Vibration, ISMA2010, Leuven, Belgium, 2010.
  • G.A. Vio, S. Marques and J.E. Cooper and K.J. Badcock, "Adaptive aeroelastic concept applied to a civil jet aircraft model", 51st AIAA Structures, Structural Dynamics and Material Conference, SDM2010, Orlando, Florida, 2010.
  • J.E. Cooper, A. Suleman, S. Ricci, S. Miller, G.A. Vio, L. da Luz, A. Gomez, F. Lau, L. Cavagna, A. De Gaspari, L. Riccobene, A. Scotti, M. Terraneo, "SMorph - Smart aircraft morphing technologies project",51st AIAA Structures, Structural Dynamics and Materials Conference, Orlando, Florida, USA, April 2010.
  • S. Miller, G.A. Vio and J.E. Cooper, "Control of rotating spars for an adaptive aeroelastic wing", RTO-AVT168 Symposium on Morphing Vehicles, Lisbon, Portugal, April 2009.
  • S. Miller, G.A. Vio and J.E. Cooper, "Adaptive wing tip devices for gust alleviation, trim and roll control", RTO-AVT168 Symposium on Morphing Vehicles, Lisbon, Portugal, April 2009.
  • G.A. Vio, K.J. Badcock and J.E. Cooper, "Drag reduction using Active Aeroelastic applied to a full scale commercial aircraft", International Forum on Aeroelasticity and Structural Dynamics, Seattle, USA, June 2009.
  • S. Miller, G.A. Vio and J.E. Cooper, "Development of an adaptive wing tip device", 50th AIAA Structures, Structural Dynamics and Materials Conference, Palm Springs, CA, USA, May 2009.
  • S. Miller, G.A. Vio and J.E. Cooper, "Wing design incorporating a passive loads alleviation device", RAeS Aircraft Structural Design Conference, Liverpool, UK, October 2008.
  • G.A. Vio and J.E. Cooper, "Optimisation of composite wing structures for passive gust alleviation", RAeS Aircraft Structural Design Conference, Liverpool, UK, October 2008.
  • G.A. Vio, J.E. Cooper, "Optimisation of composite structures for gust alleviation using evolutionary algorithms", 12th AIAA Multidisciplinary Analysis and Optimization Conference, Victoria, BC, Canada, September 2008.
  • G.A. Vio, J.E. Cooper, S. Miller and M. Blair, "Aeroelstic scaling of the sensorcraft for wind tunnel testing under gust loads", 12th AIAA Multidisciplinary Analysis and Optimization Conference, Victoria, BC, Canada, September 2008.
  • G.A. Vio, G. Dimitriadis and J.E. Cooper, "Data clustering for the identification of the bifurcation behaviour in non-linear aeroelastic systems using a coupled harmonic balance/genetic algorithm approach", International conference on Noise and Vibration, ISMA2008, Leuven, Belgium, 2008.
  • G.A. Vio, J.E. Cooper, A. Manan and M.Y. Harmin, "Optimization of aeroelastic composite structures using evolutionary algorithms", ASMO UK, Bath, UK, Jul 2008.
  • G.A. Vio, J.E. Cooper, "Optimisation of composite structures for aeroelastic applications using evolutionary algorithms", 49th AIAA Structures, Structural Dynamics and Materials Conference, Schaumburg, IL, USA, April 2008.
  • G.A. Vio, G. Dimitriadis, J.E. Cooper, K.J. Badcock, "Linear and on non-linear transonic flow behaviour of the Goland+ wing", International Forum on Aeroelasticity and Structural Dynamics, Stockholm, Sweden, June 2007.
  • J.E. Cooper, V.H. Siddaramiah, G.A. Vio, S. Miller and G. Dimitriadis, "Adaptive aeroelastic structures for improved aircraft performance", World Forum on Smart materials and Smart Structures Technologies, Nanjing, China, May 2007.
  • G.A. Vio, G. Dimitriadis, J.E. Cooper, K.J. Badcock, "Flight-regime dependant reduced order models of CFD/FE aeroelastic systems in transonic flow" 48th AIAA Structures, Structural Dynamics and Materials Conference, Waikiki, Hawaii, USA, April 2007.
  • G.A. Vio, G. Dimitriadis, J.E. Cooper, "Improved implementation of the Harmonic balance method" 48th AIAA Structures, Structural Dynamics and Materials Conference, Waikiki, Hawaii, USA, April 2007.
  • V.H. Siddaramiah, J.E. Cooper, G.A. Vio, "Drag minimisation using adaptive aeroelastic structures", 48th AIAA Structures, Structural Dynamics and Materials Conference, Waikiki, Hawaii, USA, April 2007.
  • G.A. Vio, G. Dimitriadis, "Nonlinearity characterization for nonlinear dynamic system identification using an expert approach", International Conference on Noise and Vibration Engineering, ISMA 2006, Leuven, Belgium, September 2006.
  • Z. Yang, G. Dimitriadis, G.A. Vio, J.R. Wright, J.E. Cooper, "Identification of structural freeplay non-linearities using the non-linear resonant decay method", International Conference on Noise and Vibration Engineering, ISMA 2006, Leuven, Belgium, September 2006.
  • G. Dimitriadis, G.A. Vio, J.E. Cooper, "Application of higher-order harmonic balance to nonlinear aeroelastic systems", 47th AIAA Structures, Structural Dynamics and Materials Conference, Newport, RI, USA, May 2006.
  • G.A. Vio, G. Dimitriadis, J.E. Cooper and D. Shi, "Identification of non-linear dynamic systems using an expert approach", 47th AIAA Structures, Structural Dynamics and Materials Conference, Newport, RI, USA, May 2006.
  • G. Benini, G.A. Vio, G. Dimitriadis, J.E. Cooper and J. R. Wright, "Flutter Clearance of a Nonlinear Aircraft", CEAS International Forum on Aeroelasticity and Structural Dynamics, Munich, Germany, June 2005.
  • M. Amprikidis, J.E. Cooper, C. Rogerson, G. Vio, "Adaptive internal structures for active aeroelastic aircraft", CEAS International Forum on Aeroelasticity and Structural Dynamics, Munich, Germany, June 2005.
  • M. Amprikidis, J.E. Cooper, C. Rogerson, G. Vio, "On the use of adaptive internal structures for wing shape control", 46th AIAA Structures, Structural Dynamics and Materials Conference, Austin, Texas, USA, April 2005.
  • G. Dimitriadis, G.A. Vio, J.E. Cooper, "Stability and LCO Amplitude Prediction For Aeroelastic Systems With Structural And Aerodynamic Nonlinearities Using Numerical Continuation", AVT Symposium on Flow-Induced Unsteady Loads and the Impact on Military Applications, Hungary, Budapest May 2005.
  • N.V. Taylor, G.A. Vio et al., "A comparison of linear and non-linear flutter prediction methods: summary of PUMA DARP aeroelastic results", RAeS Aerospace Aerodynamics Research Conference, London, UK 2004.
  • G. Dimitriadis, G.A. Vio and J.E. Cooper, "Stability and Limit Cycle Oscillation Amplitude Prediction for Multi-DOF Systems with Piecewise Linear Non-Linearities", International Conference on Noise and Vibration Engineering, ISMA 2004, Leuven, Belgium, September 2004.
  • G.A. Vio, G. Dimitriadis and J.E. Cooper, "On The Solution of the Aeroelastic Galloping Problem", International Conference on Noise and Vibration Engineering, ISMA 2004, Leuven, Belgium, September 2004.
  • G. Dimitriadis, G.A. Vio and J.E. Cooper, "Stability and LCO Amplitude Prediction for Simple Nonlinear Aeroelastic Systems", 45th AIAA Structures, Structural Dynamics and Materials Conference, Palm Springs, California, USA, April 2004.
  • G.A. Vio, G. Dimitriadis and J.E. Cooper, "Nonlinear Aeroelastic Research at the Dynamics and Aeroelasticity Research Group", TTCP-AER-TP4-CP4-C2 Flutter and LCO Prediction, Manchester, UK, June 2003.
  • G.A. Vio, I.B. Carrington, A. Sedaghat, J.E. Cooper, J.R. Wright, "Limit Cycle Oscillation Prediction for Non-Linear Aeroelastic Systems Using Normal Form Theory", Aeronautical Society Conference, London, UK, September 2002.
  • G.A. Vio, J.E. Cooper, J.R. Wright, "Limit Cycle Oscillation Prediction for Aeroelastic Systems with Discrete Structural Non-Linearities", 43rd AIAA Structures, Structural Dynamics and Materials Conference, Denver, Colorado, USA, April 2002.
  • G.A. Vio, J.E. Cooper, "Limit Cycle Oscillation Prediction for Aeroelastic System with Non-Continuous Non-Linearities", International Conference on Discrete, Continuous and Impulsive Systems, London, Canada, July 2001.
  • A. Sedaghat, J.E. Cooper, G.A. Vio, J.R. Wright, "Nonlinear Aerodynamics Modelling for Aeroelastic Systems", International Conference on Noise and Vibration Engineering, ISMA 2000, Leuven, Belgium, September 2000.