Browsing by Author "Filyashkin, Mykola"

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    Damped Micromechanical Hyrovertical
    (National Aviation University, 2022-09-26) Filyashkin, Mykola; Філяшкін, Микола Кирилович; Smirnov, Oleg; Смірнов, Олег Ігорович
    The article considers the methods for vertical gyro construction on rough microelectromechanical elements, such as: angular velocity sensors and accelerometers. It is proposed to improve the accuracy of the microelectromechanical vertical gyro by combining it with a satellite navigation system. The solutions proposed in the article make it possible to improve the accuracy of the integrated vertical gyro based on micromechanical technologies, by the means of complex data processing that uses a compensation scheme with the latest dynamic filter, which practically does not distort the errors of the strapdown inertial microelectromechanical vertical gyro, and thus obtain an estimate of the ground speed as close to the true speed as possible. Based on the obtained estimate, it is proposed to construct a scheme of the vertical gyro speed correction (damping scheme), which would significantly improve the accuracy of estimation of the angular orientation’s parameters.
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    Modeling Complex for Studies of Methodical and Instrumental Errors of the Strapdown Inertial Navigation System
    (National Aviation University, 2023-12-27) Filyashkin, Mykola; Філяшкін, Микола Кирилович; Smirnov, Oleg; Смірнов, Олег Ігорович
    To study the accuracy characteristics, a strapdown inertial navigation system is represented as a set of kinematic equations and equations of a mathematical model of the Earth. Based on the mathematical model in the Matlab-Simulink package, a modeling complex was created, consisting of subsystems of the reference and studied navigation system, subsystems of the reference and simplified model of the Earth and a subsystem of primary information sensors. In navigation subsystems, kinematic equations of inertial navigation algorithms are solved, and matrices of direction cosines are formed. In the subsystems of the Earth model, the parameters of the Earth's spheroid and the acceleration of gravity are calculated. The sensor models are developed based on the characteristics of low-cost microelectromechanical sensors. The purpose of the study was to assess methodological and instrumental errors as the difference in the dead reckoning signals of the flight navigation parameters of the reference and studied navigation systems. Methodological errors of the system are played up by simplifications of the parameters of the earth's spheroid, and instrumental errors are caused by errors in inertial sensors.
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    Particle filtering technique for aircraft control in highly-disturbed GPS-denied environment
    (National Aviation University, 2020-03-24) Mukhina, Maryna; Мухіна, Марина Петрівна; Filyashkin, Mykola; Філяшкін, Микола Кирилович; Kazak, Vasil; Казак, Василь Миколайович; Shevchuk, Dmytro; Шевчук, Дмитро Олегович
    The problem of aircraft control is considered for certain class of situation, namely when aircraft enters GPS-denied zone with significant disturbances of different nature which may cause the constructive damage and the loss of control. The only source of information is from inertial navigation system that need to be aided by correlation extreme navigation system, for example. In the paper the control problem is solved by using particle filtering technique for correlation extreme navigation system which outputs form the control vector. Further the structural reconfiguration is done by redistributing control or changing the control law in order to create the necessary control forces and moments, maintain acceptable control quality and return for the desired track. The lack of reliable navigation information is compensated by correlation extreme navigation system working by terrain filed of the Earth to be included into control contour. The researches have been conducted by mathematical modeling of the developed algorithms in mathematical software package MATLAB using terrain field (the part of Carpathians territory). The results proved the high accuracy of navigation solution and stability of control estimated by error of closing loop.
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    Two-circuit System of Automated Control of Low-Altitude Helicopter Flight
    (National Aviation University, 2024-03-29) Filyashkin, Mykola; Філяшкін, Микола Кирилович
    The mode of automatic control of a low-altitude flight of a helicopter over heavily rugged terrain based on information about the inclined range is considered. It is shown that at high flight speeds it is impossible to overcome strictly vertical obstacles without changing the angle of inclination of the rangefinder antenna to the horizon depending on the flight speed, or without reducing the flight speed when approaching such an obstacle. Algorithms for controlling low-altitude flight using a two-channel scheme are proposed, namely, at high speeds through the longitudinal channel of the swashplate, and at low speeds – through the channel of the general pitch of the main rotor. The problem of optimal control of low-altitude helicopter flight is formulated, which can be presented as a variational problem with restrictions on phase coordinates and control influences. Ways to optimize the process of circumventing an obstacle with forecasting the trajectory of the helicopter on a certain section of the route with subsequent stabilization of the helicopter on this trajectory are shown.