Professor Mikhail Goman

Job: Professor of Dynamics

Faculty: Technology

School/department: School of Engineering and Sustainable Development

Research group(s): Centre for Engineering Science and Advance Systems (CESAS), Nonlinear Flight Dynamics Research Group (NFD)

Address: De Montfort University, The Gateway, Leicester, LE1 9BH

T: +44 (0)116 250 61 56

E: mgoman@dmu.ac.uk

W: http://www.cse.dmu.ac.uk/~mgoman/

 

Personal profile

Mikhail Goman joined De Montofrt University in 1997 being invited and funded by the Defence Evaluation and Research Agency (known as DERA), UK and QinetiQ, Ltd. He is Professor of Dynamics since 2000 at the Faculty of Technology. His research and scientific career started in 1972 at the Central Aerohydrodynamic Institute (TsAGI, www.tsagi.com ), named after Prof N.E.Zhukovsky, in Russia. He had an extensive experience in aerodynamic modelling and nonlinear flight dynamics with special focus on critical flight regimes in extended flight envelope. For this cycle of works and practical applications he was awarded in 1992 the Zhukovsky Gold medal, the highest aeronautical accolade in Russia, for the best work in Theory of Aviation.

Mikhail Goman is a Co-Director of the newly established Centre for Engineering Science and Advanced Systems (CESAS) at the Faculty of Technology and Head of Nonlinear Flight Dynamics Research Group, which is involved in research collaboration with a number of world famous research Institutions such as TsAGI, Russia and the National Aerospace Laboratories (CSIR-NAL), India. Recently, he was leading the development of the aerodynamic model of a generic airliner in extended flight envelope as a part of the European Union 7th Framework Programme research project SUPRA (2009-2012), Simulation of UPset Recovery in Aviation (www.supra.aero). This project was aimed at creating new simulation technologies (aerodynamic modelling, motion cueing and simulator driving algorithms) in support of pilot training on available flight simulators in extended flight envelope, where stalled flight conditions may lead to the Loss-of-Control in Flight (LOC-I), the major cause of flight catastrophes in modern transport aviation. The developed SUPRA extended aerodynamic model was highly ranked by the invited technical experts from the NASA Langley Research Centre and the Boeing Company. 

Research group affiliations

Centre for Engineering Science and Advance Systems (CESAS)

Nonlinear Flight Dynamics Research Group (NFD)

Publications and outputs 

  • Experimental investigation of aerodynamic hysteresis using a 5-DoF wind tunnel manoeuvre rig
    Experimental investigation of aerodynamic hysteresis using a 5-DoF wind tunnel manoeuvre rig Gong, Z.; Araujo-Estrada, Sergio A.; Lowenberg, M. H.; Neild, Simon; Goman, M. (Mikhail G.) The high-incidence aerodynamics of a lightweight jet trainer aircraft model has been investigated using a novel five-degree-of-freedom (DOF) dynamic maneuver rig, recently updated with improved actuation and data acquisition systems, in the 7 × 5 ft closed-section low-speed wind tunnel at the University of Bristol. The major focus was to identify the nonlinear and unsteady aerodynamic characteristics specific to the stall region and which affect free-to-move aircraft-model behavior. First, the unstable equilibrium states in the limit-cycle regions were stabilized, and so observed, over a wide range of angles of attack using a simple elevator feedback control lawbased on pitch angle and pitch-rate sensor measurements. Tests with two DOF, namely, the aircraft model and rig-arm pitch angles, revealed the existence of static hysteresis in the normal force acting on the aircraft model in the stall region. Unlocking the aircraft model in roll and yaw accompanied by feedback stabilization of the lateral–directional modes of motion demonstrated the onset of asymmetric aerodynamic rolling and yawing moments in this four-DOF configuration. This observation implicitly indicates a link between the static hystereses in the normal aerodynamic force with an onset of aerodynamic asymmetry. The experimental results show the efficiency of the updated multi-DOF actively controlled maneuver rig in providing insight into complicated aerodynamic effects within the stall region. The file attached to this record is the author's final peer reviewed version.
  • Impact of Ground Effect on Airplane Lateral Directional Stability during Take-Off and Landing
    Impact of Ground Effect on Airplane Lateral Directional Stability during Take-Off and Landing Sereez, M.; Abramov, Nikolay; Goman, M. (Mikhail G.) Computational simulations of aerodynamic characteristics of the Common Research Model (CRM), representing a typical transport airliner are conducted using CFD methods in close proximity to the ground. The obtained dependencies on bank angle for aerodynamic forces and moments are further used in stability and controllability analysis of the lateral-directional aircraft motion. Essential changes in the lateral-directional modes in close proximity to the ground have been identified. For example, with approach to the ground, the roll subsidence and spiral eigenvalues are merging creating the oscillatory Roll-Spiral mode with quite significant frequency. This transformation of the lateral-directional dynamics in piloted simulation may affect the aircraft responses to external crosswind, modify handling quality characteristics and improve realism of crosswind landing. The material of this paper was presented at the Seventh European Conference for Aeronautics and Space Sciences EUCASS-2017. Further work is carried out for evaluation of the ground effect aerodynamics for a high-lift configuration based on a hybrid geometry of DLR F11 and NASA GTM models with fully deployed flaps and slats. Some aspects of grid generation for a high lift configuration using structured blocking approach are discussed.
  • Synthetic Turbulence Modeling for Evaluation of Ultrasonic Cross-Correlation Flow Measurement
    Synthetic Turbulence Modeling for Evaluation of Ultrasonic Cross-Correlation Flow Measurement Gurevich, A.; Goman, M. (Mikhail G.); Gurevich, Y.G.; Lopez, A.M. Performance of an ultrasonic cross-correlation flow measurement instrument may be significantly affected by turbulence at the location of the ultrasonic sensors. In this paper, a new method of generating Synthetic Turbulence is presented, to provide an effective tool for creating a variety of turbulent fields, which can be used to model and analyze instrument performance under different flow conditions. In the proposed method, a turbulent field is presented as a Fourier time-series in each point in space. Turbulence structures are defined by a spatial distribution of phase functions for each harmonic. Principles of designing a phase function to achieve the desirable distribution of turbulence scales, and two-point correlations, are outlined by considering the example of Uniform Isotropic Turbulence. One application of this method, presented in this work, is the mathematical modeling of ultrasonic cross-correlation flow measurement. Results predicted by the proposed mathematical model show good agreement with experimental data. The file attached to this record is the author's final peer reviewed version. The Publisher's final version can be found by following the DOI link
  • Computational Ground Effect Aerodynamics and Airplane Stability Analysis During Take-off and Landing
    Computational Ground Effect Aerodynamics and Airplane Stability Analysis During Take-off and Landing Sereez, M.; Abramov, Nikolay; Goman, M. (Mikhail G.) Computational simulations of aerodynamic characteristics of the Common Research Model (CRM), representing a typical transport airliner, are conducted using CFD methods in close proximity to the ground. The obtained dependencies on bank angle for aerodynamic forces and moments are further used in stability and controllability analysis of the lateral-directional aircraft motion. Essential changes in the lateral-directional modes in close proximity to the ground have been identified. For example, with approach to the ground, the roll subsidence and spiral eigenvalues are merging creating the oscillatory Roll-Spiral mode with quite significant frequency. This transformation of the lateral-directional dynamics in piloted simulation may affect the aircraft responses to external crosswind, modify handling quality characteristics and improve realism of crosswind landing.
  • Computational Simulation of Airfoils Stall Aerodynamics at Low Reynolds Numbers
    Computational Simulation of Airfoils Stall Aerodynamics at Low Reynolds Numbers Sereez, M.; Abramov, Nikolay; Goman, M. (Mikhail G.) Experimental results for aerodynamic static hysteresis at stall conditions obtained in the TsAGI's T-124 low-turbulence wind tunnel for NACA0018 are presented and analysed. Computational predictions of aerodynamic static hysteresis are made using the OpenFOAM simulations considering di erent grids, turbulence models and solvers. Comparisons of compu- tational simulation results with experimental wind tunnel data are made for 2D NACA0018 and NACA0012 airfoils at low Reynolds numbers Re = (0.3-1.0) millions. The properties of the proposed phenomenological bifurca- tion model for simulation of aerodynamic loads at the existence of static hysteresis are discussed.
  • Wind Tunnel Manoeuvre Rig: A Multi-DOF Test Platform for Model Aircraft
    Wind Tunnel Manoeuvre Rig: A Multi-DOF Test Platform for Model Aircraft Araujo-Estrada, Sergio A.; Gong, Zheng; Lowenberg, M. H.; Neild, Simon; Goman, M. (Mikhail G.) This paper presents recent progress in the development of a novel multi-degree-of-freedom dynamic manoeuvre rig aimed at investigation of aircraft model nonlinear and time dependent aerodynamics in the wind tunnel. The purpose and characteristics of the rig are first described, along with a description of the data acquisition, processing and presentation system. The dynamic manoeuvre rig capabilities are demonstrated via a series of experiments involving a wind tunnel model aircraft in a closed section low-speed wind tunnel. First, an experiment illustrating low-speed wind tunnel aerodynamic model identification is presented. Then, examples of experiments involving real-time control of the rig/aircraft model are shown; these are evaluated in terms of testing productivity with a focus on the development and design of aircraft control laws.
  • Positivity-Preserving Runge-Kutta Discontinuous Galerkin Method on Adaptive Cartesian Grid for Strong Moving Shock
    Positivity-Preserving Runge-Kutta Discontinuous Galerkin Method on Adaptive Cartesian Grid for Strong Moving Shock Liu, Jianming; Qiu, Jianxian; Goman, M. (Mikhail G.); Li, X. K.; Liu, Meilin In order to suppress the failure of preserving positivity of density or pressure, a positivity-preserving limiter technique coupled with h-adaptive Runge-Kutta discontinuous Galerkin (RKDG) method is developed in this paper. Such a method is implemented to simulate flows with the large Mach number, strong shock/obstacle interactions and shock diffractions. The Cartesian grid with ghost cell immersed boundary method for arbitrarily complex geometries is also presented. This approach directly uses the cell solution polynomial of DG finite element space as the interpolation formula. The method is validated by the well documented test examples involving unsteady compressible flows through complex bodies over a large Mach numbers. The numerical results demonstrate the robustness and the versatility of the proposed approach.
  • Evaluation of Aircraft Model Upset Behaviour Using Wind Tunnel Manoeuvre Rig
    Evaluation of Aircraft Model Upset Behaviour Using Wind Tunnel Manoeuvre Rig Araujo-Estrada, Sergio A.; Lowenberg, M. H.; Neild, Simon; Goman, M. (Mikhail G.) This paper discusses the development of a novel multi-degree-of-freedom dynamic manoeuvre rig aimed at investigation of aircraft upset/LOC-related behaviour in the wind tunnel. The motivation behind the development and characteristics of the rig are first described, along with example behaviour of an aircraft model exhibiting nonlinear time-dependent aerodynamics in an open-jet low-speed wind tunnel. Test objectives for assessment of upset onset scenarios - both for parameter estimation purposes and to 'physiccally simulate' the behaviour - are then described, as is the design of the upgraded instrumentation system to facilitate experimental investigation. Finally, examples of relevant behaviour involving real-time control of the rig to explore nonlinear conditions leading to upset are presented; these are evaluated in terms of prospects for such testing in aircraft development and analysis projects.
  • Flight Envelope Expansion via Active Control Solutions for a Generic Tailless Aircraft
    Flight Envelope Expansion via Active Control Solutions for a Generic Tailless Aircraft Abramov, Nikolay; Bommanahal, Mallesh; Chetty, S.; Goman, M. (Mikhail G.); Kolesnikov, E. N.; Murthy, P V Satyanarayana Aircraft dynamics at high angles of attack due to loss of stability and control essentially limits its manoeuvrability. Modern control systems implement flight envelope protection at the cost of maneuverability to improve safety in these conditions. Flight envelope boundaries, which are set taking into account deterioration of stability and controllability due to separated flow, can be expanded by appropriate design of control laws. However, such a design requires extensive analysis of the maneuver envelope of the airframe and its utilization by the flight envelope protection laws. The reliability of this analysis depends on the adequate aerodynamic modeling which captures nonlinear unsteady variation of aerodynamic loads in these flight regimes. Two novel models for unsteady aerodynamics at low and high subsonic Mach numbers are described. These models and prototyping control laws are used for closed loop computational analysis. The computational methodology of clearing flight control laws for flight envelope expansion of a Generic Tailless Aircraft (GTA) is addressed
  • Synthetic Aerodynamics Modeling for Pilot Training in the Extended Flight Envelope
    Synthetic Aerodynamics Modeling for Pilot Training in the Extended Flight Envelope Murthy, P V Satyanarayana; Abramov, Nikolay; Goman, M. (Mikhail G.) Flight at high angles of attack is associated with a variety of types of aircraft departure and post stall behaviour. Every aircraft will exhibit specific set of flight characteristics in extended flight envelope. This work was motivated by the need for using flight simulator in training pilots in those high angles of attack conditions to give pilots awareness about nonlinear aircraft behaviours and peculiarities of flight at stall and above stall. Flight simulators, equipped with representative aerodynamic models covering normal and extended flight envelope can be utilised for this purpose. A special approach of building a synthetic aerodynamic model over an available high angle of attack aerodynamic model is discussed in this paper. The Synthetic modelling presented in this paper assumes complementary transformation of a number of key aerodynamic characteristics of the original aerodynamic model with an objective to diversify post stall dynamics.

Click here to view a full listing of Mikhail Goman's publications and outputs

Key research outputs

1) J. Pattinson, M. H. Lowenberg, and M. G. Goman. Investigation of poststall Oscillations of an Aircraft Wind-Tunnel Model, Journal of Aircraft (accepted for publication).

2)  J. Pattinson, M. H. Lowenberg, and M. G. Goman. A Multi-Degree-of-Freedom Wind Tunnel Manoeuvre Rig for Dynamic Simulation and Aerodynamic Model Identification, Journal of Aircraft, Vol. 50, No. 2, March-April 2013.

3)  M. G. Goman, A. V. Khramtsovsky, and E. N. Kolesnikov.  Evaluation of Aircraft Performance and Maneuverability by Computation of Attainable Equilibrium Sets,Journal of Guidance, Control, and Dynamics, Vol. 31, No. 2, March–April 2008, pp. 329-339.

4)  M.G. Goman and A.V. Khramtsovsky. Computational framework for investigation of aircraft nonlinear dynamics,Advances in Engineering Software, Vol. 39, Issue 3, March 2008, pp.167-177, Elsevier Ltd.

5)  M. E. Sidoryuk, M. G. Goman, S. Kendrick, D. J. Walkerand P. Perfect.  An LPV Control Law Design and Evaluation for the ADMIRE Model, in the Book “Nonlinear Analysis and Synthesis Techniques for Aircraft Control”, Lecture Notes in Control and Information Sciences, Springer, 2008, ISSN 0170-8643, pp.197-229.

6)  M. G. Goman, A. V. Khramtsovsky and E. N. Kolesnikov Investigation of the ADMIRE Manoeuvring Capabilities Using Qualitative Methods, in the Book “Nonlinear Analysis and Synthesis Techniques for Aircraft Control”, Lecture Notes in Control and Information Sciences, Springer, 2008, ISSN 0170-8643, pp.301-324.

Research interests/expertise

Computational methods for investigation of critical flight regimes (high incidence departure, spin, inertia roll-coupling, flutter, etc.);

Modelling of unsteady aerodynamics at separated flow conditions (experimental and mathematical phenomenological methods);

Stabilisation of unstable systems under bounded control, control solutions for flight envelope protection, departure prevention, spin recovery, flutter suppression, etc.

Areas of teaching

Mechanical Principles, Dynamics & Control, Dynamics of Nonlinear Systems.

Qualifications

Mikhail Goman graduated from Moscow Institute of Physics and Technology, the Faculty of Aeromechanics and Flight Technology with MSc degrees in 1972 (http://phystech.edu/). He then joined  the Central Aerohydrodynamic Institute (TsAGI), Russia (www.tsagi.com|), where he received PhD degree in 1978. 

Courses taught

Module leader for "Dynamics & Control"

Membership of external committees

RAeS International Committee in Aviation Training in Extended Envelope, ICATEE (2010-present) http://icatee.org/2011/06/389/

NASA LaRC Loss-of-Control in Flight Research Working Group (2012-present)

Membership of professional associations and societies

Senior Member of the American Institute of Aeronautics and Astronautics (SMAIAA) www.aiaa.org

Conference attendance

1) N.Abramov, M.Goman, A.Khrabrov, E.Kolesnikov, B.Soemarwoto, L.Fucke, H.Smaili.  Aerodynamic Model of Transport Airplane in Extended Envelope for Simulation of Upset Recovery, ICAS 2012-3.1.2, 28th Congress of the International Council of the Aeronautical Sciences, 23-28 September 2012, Brisbane, Australia.

2) M.Bommanahal, M.Goman. Nonlinear Unsteady Aerodynamic Modeling by Volterra Variational Approach, AIAA 2012-4654, AIAA Atmospheric Flight Mechanics Conference, 13-16 August, Minneapolis, Minnesota.

3)  N.B.Abramov, M.G.Goman, A.N.Khrabrov, E.N.Kolesnikov, L.Fucke, B.Soemarwoto, H.Smaili. Pushing Ahead – SUPRA Airplane Model for Upset Recovery, AIAA 2012-4631, AIAA Modeling and Simulation Technoloies Conference, 13-16 August, Minneapolis, Minnesota.

4) E.N.Kolesnikov and M.G. Goman. Analysis of Aircraft Nonlinear Dynamics Using Non-Gradient Based Numerical Methods and Attainable Equilibrium Sets, AIAA 2012-4406, AIAA Atmospheric Flight Mechanics Conference, 13-16 August 2012, Minneapolis, Minnesota.

5) N.B. Abramov, M.G.Goman, E.N.Kolesnikov, and M.E.Sidoryuk.  Investigation of Attainable Equilibrium Sets for Clearance of Flight Control Laws, AIAA 2010-491, 48th AIAA Aerospace Science Meeting, 4-7 January 2010, Orlando, Florida.

6) E.L.Groen, M. Wentink, M. Mayrhofer, H. Smaili, B.I.Soemarwoto, M.Goman, H.H.Bulthoff.  Outline of Research Project “SUPRA” on the Simulation of Upset Recovery,The Royal Aeronautical Society Spring 2009 Flight Simulation Conference Flight Simulation: Towards The Edge of the Envelope, 3-4 June 2009.

 7) M.N.Demenkov and M.G.Goman.  Bifurcation Control of Aeroelastic Limit Cycle Oscillations, Chaos 09Second IFAC meeting related to analysis and control of chaotic systems, London 22-24 June 2009.

8) M.G. Goman and M.N.Demenkov. Multiple Attractor Dynamics in Active Flutter Suppression Problem, Seventh International Conference on Mathematical problems in Engineering & Aerospace Sciences, ICNPAA 2008, Edited by Seenith Sivasundaram, Siena, June 2008, pp. 1042-1051. 

 9) K.Vikhorev, M.G. Goman and M.N.Demenkov, Effect of Control Constraints on Active Stabilization of Flutter Instability, Seventh International Conference on Mathematical problems in Engineering & Aerospace Sciences, ICNPAA 2008, Edited by Seenith Sivasundaram, Siena, June 2008, pp. 1042-1051.

10) J.Pattinson, M.H.Lowenberg, and M.G.Goman.  A Dynamic Rig for the Wind Tunnel Evaluation of Novel Flying Vehicles The Royal Aeronautical Society The Aerodynamic Conference The Aerodynamics of Novel Configurations Capabilities and Future Requirements 27th -29th October 2008.

11) M.N.Demenkov and M.G.Goman.  Suppressing Aeroelastic Vibrations via Stability Region Maximization and Numerical Continuation Technique, Proceedings of the International Conference on Control 2008 (UKACC), Manchester, UK, September 2-4, 2008.

Consultancy work

Consultancies in the form of short professional courses, software development, mathematical modelling for Mikoyan and Sukhoi Design Companies, Flight Research Institute, Russia, (1972--1992), ShenYang Aircraft Design and Research Institute, the P.R.China (1992--1993), Aeronautical Development Agency (ADA), India (1994--1996), Defence Evaluation Research Agency (DERA) UK, 1993-2001, QinetiQ Ltd (2002 -2004), National Aerospace Laboratories, CSIR-NAL, India (2010-2013).

Current research students

International PhD programme (part time):

Bommanahal, Mallesh Vithappa, NAL, India (1st supervisor)

Pudi, Venkata Satyanarayana Murthy, NAL, India (1st supervisor)

Gurevich, Alexander, AMAG Inc., Canada (1st supervisor)

Liu, Jianming, NUAA, Nanjing, China (1st supervisor)

Zheng, Gong, NUAA, Nanjing, China (1st supervisor)

Full time:

Bailey, Richard (2nd supervisor)

Externally funded research grants information

EU 7th Framework Programme research project SUPRA (2009-2012) (www.supra.aero).

National Aerospace Laboratories CSIR-NAL, Bangalore, India (2010-2013) (www.nal.res.in).

Russian Ministry of Higher Education and Science, International Grant (2012-2013) jointly with TsAGI (www.tsagi.com).

Professional esteem indicators

Member of Editorial body of Journal Nonlinear Studies (http://nonlinearstudies.com).

Reviewer for AIAA Journal of Aircraft, Journal Guidance, Control and Dynamics, the RAeS Aeronautical Journal, TsAGI’s Visualization of Mechanical Processes, Beggell House Inc, USA.

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