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69
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1,135
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Introduction
Skills and Expertise
Additional affiliations
October 1997 - present
August 1972 - July 2001
Central Aerohydrodynamic Institute (TsAGI), Russia
Position
- Researcher, Head of sector
Publications
Publications (69)
Although there have been many proposed methods to model unsteady aerodynamic effects in the stall and post-stall region, little work has been done to directly assess the impact of unsteady aerodynamic models on stability and control characteristics. In this paper, we combine the state-space method for unsteady aerodynamic modelling with bifurcation...
Although quasi-steady aerodynamic modelling is a widely used technique, its shortcomings in representing the stall and post-stall dynamics have been noted in the literature. Various methods to model the unsteady aerodynamics effects have been proposed as a result, but their direct implications on the aircraft's flight dynamics characteristics have...
Wind tunnel oscillatory testing is a technique conventionally used for the measurement of dynamic aerodynamic loads on subscale aircraft models. Oscillatory testing is commonly used for identification of dynamic stability derivatives for flight mechanics models. Model oscillation is normally driven by a rig drive mechanism, or with the use of its c...
The paper presents computational prediction of aerodynamic hysteresis loops in static conditions for a two-dimensional aerofoil that was used as a cross-section profile for a rectangular wing with an aspect ratio of five, tested in the TsAGI T-106 wind tunnel at a Reynolds number of Re=6×106 and a Mach number of M=0.15. Tests in the wind tunnel sho...
The principles of aerodynamic modeling in the extended flight envelope, which is characterized by the development of separated flow, are outlined and illustrated for a generic transport airplane. The importance of different test techniques for generating wind-tunnel data and the procedure for blending the obtained experimental data for aerodynamic...
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...
Computational simulations of aerodynamic characteristics of the Common Research Model (CRM), representing a typical transport airliner are con-ducted 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...
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...
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 diff...
p>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 pres...
p>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-depen...
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 control...
A five-degree-of-freedom dynamic wind-tunnel rig is used in the observation of large-amplitude, stall-related and self-sustaining, pitch oscillations of a model aircraft. These oscillations are investigated on the dynamic wind-tunnel rig during a quasi-steady ramp input to the aircraft model’s elevator surfaces in one-degree-of-freedom pitch mode a...
The applications of the adaptive Runge-Kutta discontinuous Galerkin method are discussed for arbitrarily complex geometries on Cartesian grid. To simulate flows over complex configurations, a ghost cell immersed boundary method is adopted. The method is validated versus well documented test problems involving both steady and unsteady compressible f...
SUMMARYA Cartesian grid method using immersed boundary technique to simulate the impact of body in fluid has become an important research topic in computational fluid dynamics because of its simplification, automation of grid generation, and accuracy of results. In the frame of Cartesian grid, one often uses finite volume method with second order a...
This paper presents an immersed boundary method for compressible Navier–Stokes equations in irregular domains, based on a local radial basis function approximation. This approach allows one to define a reconstruction of the radial basis functions on each irregular interface cell to treat both the Dirichlet and Neumann boundary conditions accurately...
A new five-degree-of-freedom rig for the dynamic wind-tunnel testing of aircraft models has been developed. The maneuver rig enables a large set of conventional and more-extreme aircraft maneuvers to be performed in the controlled environment of a wind tunnel, allowing direct physical simulation of in-flight maneuvers and the identification of aero...
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...
The aerodynamics at high-angle-of-attack is an unsteady and nonlinear phenomena in time. In this paper, we present a phenomenological and mathematically rigorous approach to nonlinear modeling of the unsteady aerodynamics based on Volterra variational equa- tions. The model consists of differential equations of internal states corresponding to diff...
The SUPRA research project - Simulation of Upset Recovery in Aviation - has been funded by the European Union 7th Framework Program to enhance the flight simulation envelope for upset recovery simulation. Within the project an extended aerodynamic model, capturing the key aerodynamics during and beyond stall for a large category transport aircraft...
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 predi...
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 spee...
A five-degree-of-freedom dynamic wind tunnel rig is used in the observation of large amplitude self-sustaining pitch oscillations of a model aircraft. These oscillations arise during a quasi-steady ramp input to the aircraft model's elevator surfaces in one-degree-of-freedom pitch mode and in the longitudinal two-degree-of-freedom pitch and heave m...
This paper gives an overview of the European Framework Programme 7 project SUPRA-Simulation of Upset Recovery in Aviation, a European research effort involving nine partnering organizations from the Netherlands, Austria, Spain, Russia, the United Kingdom and Germany aiming at developing new concepts of ground-based upset recovery simulation for use...
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 clea...
A wind-tunnel rig to provide data from manoeuvring aircraft is developed. The "Manoeuvre rig" is a horizontal pendulum type rig that is capable of large amplitude motions in 5 degrees of freedom. This enables a large set of conventional and extreme aircraft manoeuvres to be performed in the controlled environment of a wind tunnel. A mixed different...
An active flutter suppression using linear saturated control is investigated for a 2dof wing section with nonlinear torsional stiffness and limited deflection amplitude of its single control effector. The suppression of limit cycle oscillations in the nonlinear closed-loop system is achieved through maximization of the stability region of the linea...
An active flutter suppression using linear sub-optimal control scheme is investigated for a 2dof airfoil system with nonlinear torsional stifiness and limited deflection amplitude of its single actuator. The suppression of limit cycle oscillations in the nonlinear closed-loop system is achieved through maximization of the stability region of its li...
The effect of amplitude and rate control constraints in active flutter suppression is analysed for a number of different state feedback control laws considering mathematical model of two degree-of freedom nonlinear aeroelastic airfoil system with trailing and leading edge flaps. The size of region of attraction is used as an additional metric to se...
A computational framework based on qualitative theory, parameter continuation and bifurcation analysis is outlined and illustrated by a number of examples for inertia-coupled roll maneuvers. The focus is on the accumulation of computed results in a special database and its incorporation into the investigation process. Ways to automate the investiga...
An aircraft's performance and maneuvering capabilities in steady flight conditions are usually analyzed considering the steady states of the rigid-body equations of motion. A systematic way of computation of the set of all attainable steady states for a general class of helical trajectories is presented. The proposed reconstruction of attainable eq...
This chapter presents the design and evaluation of an LPV control law for the ADMIRE model over a specified wide flight envelope,
including subsonic, transonic and supersonic regions. The design of the LPV control law is based on the parameter-dependent
Lyapunov function approach with gridding of the parameter space. It is demonstrated that by usin...
In this chapter, the manoeuvring capabilities of the ADMIRE model are analyzed using qualitative methods via computation of
attainable equilibrium sets, local stability maps and two-dimensional cross-sections of stability regions for stable equilibria
considering the velocity-vector roll manoeuvre. A nonlinear dynamic inversion control law is imple...
The problem of minimizing wind perturbations using the control on the trailing edge of the airfoil is considered for an airfoil
passing through a short wind gust. It is considered that the airfoil movement is bounded by two degrees of freedom, viz. in
pitch and height, and each channel has an elastic spring that simulates torsional and bending stif...
A traditional representation of aerodynamic characteristics based on the concept of aerodynamic derivatives becomes inadequate at high angles of attack due to significant dynamic effects generated by separated and vortical flow. The main difficulty in an application of aerodynamic derivatives at these conditions is linked with their strong dependen...
The H∞-based and classical engineering approaches to flight control law design are compared regarding a similarity between the derived controllers structure. The integrated flight and aeroelastic control laws have been designed using the H∞ synthesis. The engineering control laws for the same aeroservoelactic aircraft model and flight conditions ha...
An important issue in stabilization of unstable dynamics is connected with the size of the controllability region, which is the set of all states of the aircraft dynamics that can be stabilized by some realizable control action. This region is bounded because of nonlinear actuator constraints, and its size can be considered as a measure for allowab...
Stabilization of the unstable dynamic linear system with control constraints is considered in terms of maximizing the size of the closed-loop system stability region. A controllability region for the open-loop system is a natural limit for the stability region of the closed-loop system with any designed controller. A relation between the controllab...
Dynamics of a free-to-roll delta wing installed at high incidence in a wind tunnel is outlined using the experimental and mathematical modelling results. A simple analytical model applied allows us to simulate the multiattractor and chaotic dynamics observed in wind tunnel tests and thus to validate the used method for nonlinear and unsteady aerody...
An active control technology may significantly expand an aircraft flight envelope and improve its performance characteristics. In many cases it is attained by implementation of aerodynamically unstable configurations and flight regimes with dynamic instability, which are purposely stabilized by control system. An important issue in stabilization of...
The use of nonlinear dynamics theory for the analysis of aircraft motion and the assessment of aircraft control systems i well known. In this paper the continuation and bifurcation methods are applied to aircraft nonlinear control design problems.
The search for the recovery control from spin regimes is based on the minimization of an energy-like s...
Applications of global stability and bifurcational analysis methods are presented for different nonlinear flight dynamics problems, such as roll-coupling, stall, spin, etc. Based on the results for different real aircraft, F-4, F-14, F-15, High Incidence Research Model, (HIRM), the general methods developed by many authors are presented. The outlin...
Global stability analysis of dynamical system implies determination of all the system's attractors and their regions of asymptotic stability. Numerical methods necessary for global stability analysis are outlined: SSNE algorithm for systematic search of all the solutions of nonlinear system of equations, and two algorithms for computing cross-secti...
Mathematical modeling of unsteady aerodynamic forces and moments plays an important role in aircraft dynamics investigation and stability analysis at high angles of attack. In this article the state-space representation of aerodynamic forces and moments for unsteady aircraft motion is proposed. Consideration of separated flow about an airfoil and f...
A model for the lift force of an aircraft operating at high angles of attack is presented. In this model the unsteady aerodynamic effect is expressed as a dependence, of the lift on an internal variable for which a differential equation is postulated. The resulting model is applied to a delta wing subjected to forced pitching moment oscillations. T...
A system of ordinary differential equations for which the desired single- parameter family of solutions of finite equations is a stable phase trajectory is obtained for extending solutions of systems of finite nonlinear equations with variation in the parameter. A finite-difference algorithm for extending the solution with correction orthogonal to...
The paper examines the problem of determining stationary positions of pairs of vortices of unequal intensity in the flow behind a cylinder modeling the axisymmetric separated flow past a slender body at large angles of attack. The possible asymmetric stationary positions of two vortices are calculated, and their stability with respect to small pert...
Unsteady resonant flight regimes of a spinning vehicle with small mass and aerodynamic asymmetries as it reenters the atmosphere are investigated. A method is described that involves an asymptotic splitting of the equations of motion with respect to the center of mass into two equations describing, respectively, the low-frequency and high-frequency...
The collaborative research project SUPRA, intends to develop methodologies and advanced flight simulator concepts for teaching airline pilots to detect, and recover from adverse flight upsets that lead to unusual attitudes. The project is funded by the EU Seventh Framework Programme, in the area of Aeronautics and Air Transport. Research activities...
Projects
Projects (3)
The project aims to create an ultimate, immersive in-vehicle experience research platform by means of 6 degree-of-freedom motion system enhanced by augmented and virtual reality. Motion simulation is all about perception; presentation of visual, acoustic, vestibular and haptic information must be done in such a way that it is perceived to be highly realistic. The proposed cost-effective approach uses a 6-DOF platform to reproduce surge, sway, heave, yaw, pitch and roll motions. The platform is supplemented by driving and flight manipulators and gauges, acoustic system and a state-of-the-art head-mounted VR 3D display enabling close to reality augmented and virtual reality research.
