Наукові статті кафедри аерокосмічних систем управління

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ADAPTIVE SUBOPTIMAL CONTROL OF INPUT CONSTRAINED PLANTS
(Національний авіаційний університет, 2011) Valerii N., Azarskov; Leonid N., Blokhin; Leonid S., Zhytetskyi
This paper deals with adaptive regulation of a discrete-time linear time-invariant plant with arbitrary bounded disturbances whose control input is constrained to lie within certain limits. The adaptive control algorithm exploits the one-step-ahead control strategy and the gradient projection type estimation procedure using the modified dead zone. The convergence property of the estimation algorithm is shown to be ensured. The sufficient conditions guaranteeing the global asymptotical stability and simultaneously the suboptimality of the closed-loop systems are derived. Numerical examples and simulations are presented to support the theoretical results
OPTIMAL FILTRATION OF DETERMINISTIC INFORMATION IN MULTIVARIATE MEASURING ROUTE
(ВД "Освіта України", 2013) Blokhin, L. N.; Prokofieva, I. Yu.; Novitska, N. D.
The new methodology of optimal filtering is represented for deterministic components of measured information in on-board multivariate measuring route. Two variants of the mentioned problem are considered, where first is for measuring route with physically realizable (stable) elements, and the second one takes into account possibility of unstable elements in a system.
СИСТЕМА СТАБИЛИЗАЦИИ АМПЛИТУДЫ КОЛЕБАНИЙ РЕЗОНАТОРА КОРИОЛИСОВОГО ВИБРАЦИОННОГО ГИРОСКОПА
(Національний Авіаційний Університет, 2013) Чіковані, Валерій Валеріанович; Цирук, Ганна; Маляров, Сергій; Кохан, Юрій
При изменении параметров резонатора в широком диапазоне их значений запасы устойчивости по фазе и амплитуде системы стабилизации амплитуды колебаний резонатора с ПИ регулятором существенно не изменяются и имеют вполне удовлетворительные значения.
ADAPTIVE ROBUST CONTROL OF MULTIVARIABLE STATIC PLANTS WITH POSSIBLY SINGULAR TRANSFER MATRIX
(ВД "Освіта України", 2013) Azarskov, V. N.; Zhiteckii, L. S.; Solovchuk, K. Yu.
A new problem of the adaptive robust control of linear discrete-time multivariable static plants with the singular transfer matrices in the presence of bounded disturbances is stated and solved. The asymptotical properties of the adaptive robust feedback control systems designed via the proposed method are established
BIAS COMPENSATION IN DIFFERENTIAL CORIOLIS VIBRATORY GYRO
(ВД "Освіта України", 2013) V. V. Chikovani; H. V. Tsiruk
This work presets one of the ways to compensate for the bias in differential mode of Coriolis vibratory gyro operation. To compensate for the bias it is necessary to know both channels scale factors, SFx and SFy of differential Coriolis vibratory gyro, which, as a rule, are known by the results of calibration procedure and elastic wave angle  relative to one of the two drive axes which can be established in advance. This paper presents the different variants of bias compensation algorithms which can be applied to compensate for initial gyro bias and bias drift in motion. Experimental results on differential Coriolis vibratory gyro key parameters temperature influence are also presented.
DESIGN OF ROBUST CONTROLLER FOR UAV INFORMATION-MEASURING DEVICES STABILIZATION SYSTEM
(Kyiv, "Osvita Ukrainy", 2013) O. A. Sushchenko
The design problems of the information-measuring devices operated on the unmanned aerial vehicles in difficult conditions of the considerable parametric and vigorous external disturbances are considered. The mathematical model of the system is developed. The problem statement and basic stages of the robust controllers design are analyzed. The results of the synthesized system simulation in the modes of the preliminary and precision stabilization are given
FLIGHT CONTROL SYSTEM DESIGN VIA LMI-APPROACH
(Kyiv, "Osvita Ukrainy", 2013) M. M. Komnatska
A contemporary approach of flight control system design via static output feedback design is proposed. The static output feedback is formulated in terms of linear matrix inequalities. The obtained solution guarantees stabilization of unmanned aerial vehicle during flight mission. During flight envelope the unmanned aerial vehicle is subjected to the external stochastic disturbances. The efficiency of the proposed approach is illustrated by a case study of unmanned aerial vehicle longitudinal motion.
SEQUENTIAL LEARNING PROCESSES IN NEURAL NETWORKS APPLIED AS MODELS OF NONLINEAR SYSTEMS
(ВД "Освіта України", 2013-10) Azarskov, V. N.; Zhiteckii, L. S.; Nikolaienko, S. A.
Asymptotic properties of the online gradient algorithm with a constant step size employed for learning in neural network models of nonlinear systems having one hidden layer are examined. Some conditions guaranteeing the convergence of this algorithm are established.
FEATURES OF COMPUTER-AIDED DESIGN OF ROBUST DISCRETE CONTROLLERS FOR INFORMATION-MEASURING DEVICES STABILIZATION SYSTEMS
(Kyiv, "Osvita Ukrainy", 2013-11) O. A. Sushchenko
The paper deals with problems of computer-aided design of controllers for systems of stabilization of information-measuring devices operated on vehicles of the wide class in difficult conditions of disturbances action. Algorithms of the robust parametrical optimization and robust structural synthesis are suggested. The simulation results are represented
ON STRUCTURES OF COMBINED UAV FLIGHT CONTROL SYSTEMS WITH ELEMENTS OF FUZZY LOGICS
(Kyiv, "Osvita Ukrainy", 2014) Tunik, A. A.
The paper deals with flight control system development in a form of successive loop control that involves “crisp” and fuzzy contours. The paper explores peculiarities of sharing the control functions between “crisp” and fuzzy parts of the developed autopilot. The division of the autopilot structure into “crisp” and fuzzy parts is performed by applying the Hinfinity -robust stability theory of fuzzy systems and the describing function approach. The design procedure is illustrated by a case study of unmanned aerial ve- hicle lateral channel control. It was proved that application of the fuzzy control is expedient for outermost contour in the successive loop structure of flight control system.
VIBRATION DAMPING FOR THE PROBLEMS OF AIRCRAFT MOTION
(ВД "Освіта України", 2014) Azarskov, V. N.; Gristchak, D. D.
Two-step hybrid asymptotic method based on perturbation methods and phase integrals (me- thod WKB) is used to obtain approximate analytical solutions of the nonlinear problem of the vibrations of the aircraft near the rough surface, which reduces the need for the integration of singular nonlinear dif- ferential equation with time-variable periodic coefficients for given initial conditions. This solution is not limited to the value of the dimensionless amplitude of perturbations and the nature of the order non-linear restoring force. The resulting solution has the form of the sum, where each term consists of two functions according to the method of perturbation (in scalar parameter when the nonlinear component of the original equation) and the WKB-approximation, effective in the integration of singular differential equations with variable coefficients. For specific numerical results, a comparison with the data of direct numerical inte- gration of the equations of the original problem
SHOCK RESISTANCE OF DIFFERENTIAL TYPE RING-LIKE RESONATOR VIBRATORY GYROSCOPE
(ВД "Освіта України", 2014) V. V. Chikovani; H. V.Tsiruk
This work presents investigation of differential Coriolis vibratory gyroscope ability to external shock suppression. First of all pulse amplitude in voltage caused by external mechanical shock of 100 g is estimated for the two sensor designs. Then, using differential Coriolis vibratory gyroscope Simulink model, output signals of two measurement channels are analyzed. It is shown that differential Coriolis vibratory gyroscope damps amplitude of erroneous angle rate caused by shock directed along sensing axis of no less than 3 times in comparison with non differential Coriolis vibratory gyroscope. Influence of lateral shock is also analyzed
STRUCTURE IDENTIFICATION OF NON-LINEAR SYSTEM “MOVING OBJECT AND SERVO DRIVE” UNDER STOCHASTIC DISTURBANCES
(Національний авіаційний університет, 2015) Valerii, Azarskov; Leonid, Blokhin; Olga, Ermolaeva
The article represents an algorithm for dynamics models identification of nonlinear system “moving object and servo drive”, taking into account that the stochastic disturbances presented in the real operating mode are acting on it
FEATURES OF POINTING IN SYSTEMS OF STABILIZATION BY GROUND VEHICLE OBSERVATION EQUIPMENT
(Kyiv, "Osvita Ukrainy", 2015) O. A. Sushchenko
The paper deals with features of pointing and tracking modes in systems of control by location of lines-of-sights of observation devices operated at the ground vehicles. The structural scheme of the studied control system is suggested. Features of two possible approaches to control pointing modes in the studied systems are considered. Analysis of the methods of pointing and their equations is carried out. The choice of the method of the proportional method of pointing or proportional navigation is grounded. Advantages of the chosen method are analyzed
ON ONE APPROACH OF OBSERVER-BASED FLIGHT CONTROL SYSTEM DESIGN
(Kyiv, "Osvita Ukrainy", 2015) Komnatska, M. M.; Klipa, A. M.; Berezanskyi, Y. A.; Kiliian, I. V.
This paper presents a novel approach of observer design for aircraft motion control. The novelty of design procedure is based on the application of linear matrix inequality technique. The design procedure treats the design of both observer and controller by solving the set of linear inequalities simultaneously. The proposed approach is free of observer poles placement location. Simulation results demonstrate the validity and effectiveness of the proposed design approach
ESTIMATION ALGORITHM OF ARBITRARY DYNAMICS OBJECT STATE UNDER RANDOM ACTIONS AND INCOMPLETE MEASURING BY UNSTABLE SYSTEM
(Kyiv, “Osvita Ukrainy”, 2015) Azarskov, V.N.; Kurganskyi, А. U.; Rudyuk, G. I.
The article proposes estimation algorithm of linear time-invariant systems with arbitrary dy- namic behavior of control object and measuring system subject to real operating conditions.
OBSERVER-BASED FLIGHT CONTROL SYSTEM DESIGN UNDER LINEAR MATRIX INEQUALITIES APPROACH
(Kyiv, "Osvita Ukrainy", 2015) M. M. Komnatska
The paper examines a problem of observer-based flight control system design. The design procedure allows deriving both the observer and the controller simultaneously. The peculiarity of the proposed approach is that there is no need not need to choose the observer poles. The proposed design procedure is based on linear matrix inequalities technique. To demonstrate the efficiency of the proposed approach a longitudinal motion of unmanned aerial vehicle is used as a case study.
OPTIMAL GUARANTEED COST CONTROL OF AIRCRAFT MOTION
(Kyiv, “Osvita Ukrainy”, 2015) Komnatska, M. M.
The problem of optimal state feedback controller design in terms of quadratic performance index is considered. The problem is formulated in the form of linear matrix inequalities (LMIs). The obtained solution guarantees stabilization of the aircraft during flight mission. During flight envelope the aircraft is subjected to the external stochastic disturbances. The efficiency of the proposed approach is illustrated by a case study of airplane longitudinal motion.
OPTIMAL OBSERVER-BASED CONTROL DESIGN FOR AIRCRAFT LATERAL MOTION
(Національний авіаційний університет, 2015-10-08) Komnatska M.M.
The paper presents an alternative approach of observer-based flight control system design. This approach is based on the application of linear matrix inequality technique. The design procedure treats the design of both observer and controller by solving the set of linear inequalities simultaneously. The proposed approach is free of observer poles placement location. Simulation results demonstrate the validity and effectiveness of the proposed design approach
H2/H∞ OPTIMIZATION OF INERTIALLY STABILIZIED PLATFORMS
(Kyiv, "Osvita Ukrainy", 2016) O. A. Sushchenko; O. V. Shirokii
The paper deals with H2/H∞-approach to design of the inertially stabilized platforms operated at vehicles of the different types including unmanned aerial ones. The formulation of the vector optimization problem is represented. The robust optimization algorithm and results of the synthesied system simulation are shown. Comparative analysis of the results of the parametrical optimization using the Nelder-Mead method and genetic algorithm are given. Proposed approach ensures functioning of the inertially stabilized platforms in the difficult conditions of real operation.

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