Browsing by Author "Kolesnikov, E. N."

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    Aerodynamic model of transport airplane in extended envelope for simulation of upset recovery
    (ICAS 2012 CD-ROM PROCEEDINGS, 2012-09) Abramov, Nikolay; Goman, M. (Mikhail G.); Khrabrov, A. N. (Alexander N.); Kolesnikov, E. N.; Sidoryuk, M. E. (Maria E.); Soemarwoto, B.; Smaili, H.
    The paper presents the aerodynamic model in extended flight envelope for a generic airliner with under wing engines and conventional tail developed within the EU Framework Programme (FP7) research project Simulation of Upset Recovery in Aviation (SUPRA) (www.supra.aero). The SUPRA aerodynamic model is covering angles of attack beyond stall and speeds from take-off to cruise flight. The aerodynamic model in extended flight envelope developed for piloted simulation of upset prevention and recovery has been successfully validated by a number of expert pilots.
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    Analysis of Aircraft Nonlinear Dynamics Using Non-Gradient Based Numerical Methods and Attainable Equilibrium Sets
    (2012) Kolesnikov, E. N.; Goman, M. (Mikhail G.)
    Multiple equilibrium solutions of aircraft motion equation are investigated using non-gradient based numerical methods and computation of attainable equilibrium sets. The proposed approach may be applied to realistic industrial scale aircraft aerodynamic models based on look-up data tables. Advantages of this method and its joint use with predictor-corrector techniques for continuation and bifurcation analysis of aircraft nonlinear dynamics are discussed. A number of computational examples for aircraft dynamics investigation are presented for a generic airliner aerodynamic model developed within the SUPRA research project – “Simulation of Upset Recovery in Aviation” – funded by the European Union 7th Framework Program.
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    Design and analysis of combined nonlinear dynamic inversion and H_infty-based flight contol laws
    (Zhejiang University, China, 2010-05) Sidoryuk, M. E. (Maria E.); Kolesnikov, E. N.; Fan, Y.M.; Goman, M. (Mikhail G.)
    There is a significant interest in developing flight control laws which need minimum gain scheduling across the whole flight envelope while providing required robust performance and stability properties to the closed-loop system. Dynamic inversion and/or feedback linearization technique are considered by many authors as candidates to achieve these objectives. A common feature of proposed solutions is that dynamic inversion via nonlinear control feedbacks compensates coupled nonlinear aircraft dynamics and then the desired command response is prescribed by external robust linear feedback controller. The main advantage of the method is that control laws automatically achieve decoupling of command variables and avoid extensive gain scheduling. In this paper a combined two-loop design approach is implemented. An inner loop NDI-based controller is designed to linearize the dynamics and then a outer loop feedback controller designed using H_infty-based methods is applied to the resulting system to ensure robustness to model uncertainties. To achieve a more practical design solution both stability and performance characteristics are analyzed depending on roles assigned for inner and outer loop controllers. Robustness stability analysis is performed using mu-analysis, LPV (Linear Parameter Varying) methods and classical stability margins. The ultimate goal is to achieve a relatively simple design process providing robust performance and stability guarantees.
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    Evaluation of aircraft performance and maneuverability by computation of attainable equilibrium sets.
    (American Institute of Aeronautics and Astronautics, 2008) Goman, M. (Mikhail G.); Khramtsovsky, A. V. (Andrew V.); Kolesnikov, E. N.
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    Flight Envelope Expansion via Active Control Solutions for a Generic Tailless Aircraft
    (29th ICAS Congress 2014. St. Petersburg, Russia, 2014-09-07) 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
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    Investigation of Attainable Equilibrium Sets for Clearance of Flight Control Laws
    (American Institute of Aeronautics and Astronautics, AIAA, 2010-01) Abramov, Nikolay; Goman, M. (Mikhail G.); Kolesnikov, E. N.; Sidoryuk, M. E. (Maria E.)
    A systematic investigation of aircraft equilibrium states and their local stability characteristics is used for clearance of flight control laws for a large variety of manoeuvres. The proposed approach is illustrated by clearance of the LPV control laws designed in a wide subsonic region for the F-18HARV aircraft in level flight conditions and clearance of the F-16 aircraft longitudinal and lateral-directional stability augmentation system for high range of incidence and intensive velocity roll rotation.
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    Investigation of the ADMIRE manoeuvring capabilities using qualitative methods.
    (Springer, 2007) Goman, M. (Mikhail G.); Khramtsovsky, A. V. (Andrew V.); Kolesnikov, E. N.
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    Pushing Ahead - SUPRA Airplane Model for Upset Recovery
    (American Institute of Aeronautics and Astronautics, 2012) Abramov, Nikolay; Goman, M. (Mikhail G.); Khrabrov, A. N. (Alexander N.); Kolesnikov, E. N.; Fucke, Lars; Soemarwoto, B.; Smaili, H.
    One of the primary objectives of the European Union 7th Framework Program research project SUPRA – “Simulation of Upset Recovery in Aviation” – is the development and validation of the aerodynamic model of a generic large transport airplane aimed for piloted simulation in the post-stall region and upset recovery training. Modeling methods for prediction of post-stall flight dynamics, use of the wind tunnel data from different experimental facilities complemented by CFD analysis, validation criteria, nonlinear dynamics investigation and piloted simulation results are presented in this paper. The aerodynamic model was successfully validated by a number of expert pilots and found acceptable for upset recovery training.