novtexmechМехатроника, автоматизация, управлениеMekhatronika, Avtomatizatsiya, Upravlenie1684-64272619-1253Commercial Publisher «New Technologies»10.17587/mau.21.242-248novtexmech-789Research ArticleДИНАМИКА, БАЛЛИСТИКА И УПРАВЛЕНИЕ ДВИЖЕНИЕМ ЛЕТАТЕЛЬНЫХ АППАРАТОВDYNAMICS, BALLISTICS AND CONTROL OF AIRCRAFTСинтез высокоточной системы самонаведения ракеты с применением метода пропорционального наведенияSynthesis of High-Precision Missile Homing System Using Proportional Guidance MethodТхонгДо КуангThongDo Quang

Кандидат технических наук, преподаватель, Факультет техники управления

Ханой 

 

doquangthong@yahoo.comТехнический Университет им. Лэ Куй ДонВьетнамLe Quy Don Technical UniversityViet Nam202011042020214242248Copyright © Commercial Publisher «New Technologies», 20202020Commercial Publisher «New Technologies»Commercial Publisher «New Technologies»https://mech.novtex.ru/jour/about/submissions#copyrightNoticehttps://mech.novtex.ru/jour/article/view/789

Современные воздушные цели характеризуются малой заметностью, высокой маневренностью и высокой живучестью. Кроме того, для уничтожения некоторых конкретных целей, например боевых частей баллистических ракет, необходимо обеспечить прямое попадание, т. е. " hit to kill". Поэтому в настоящей работе представлена высокоточная система самонаведения ракеты с использованием пропорционального метода наведения для стрельбы по высокоманевренным целям. В частности, предложен метод параметрической оптимизации системы самонаведения ракеты для каждого динамического набора параметров ракеты. Кроме того, даны рекомендации по выбору начальных условий для синтеза системы самонаведения ракеты. По нашему опыту, мы должны выбрать малое начальное условие для синтеза системы самонаведения ракеты. Наконец, в статье также исследуется влияние систематической погрешности определения скорости, нормального ускорения ракеты и угловой скорости линии визирования ракеты и цели на точность работы системы самонаведения ракеты. Мы реализуем предложенную систему самонаведения ракеты и метод параметрической оптимизации в среде Matlab. Результаты экспериментов показывают, что с помощью предложенной системы и метода параметрической оптимизации ракета способна поражать современные воздушные цели с низкой видимостью, высокой маневренностью и высокой живучестью. 

Modern air targets are characterized by low visibility, high maneuverability and high survivability. In addition, for some specific targets, for instance ballistic missiles, in order to defeat them the missile need tobe guided and carried out direct hit, i.e. "hit to kill". Therefore, in this paper, we present a high-precision missile homing system (MHS) using the proportional guidance method for firing at the highly maneuverable targets. Specifically, we propose a parametric optimization method for choosing a set of optimal parameters of the missile homing system for each dynamic parameter set of the missile. In addition, the paper gives the recommendations of choosing the initial conditions for the synthesis of missile homing system. In our experience, we should choose the small initial condition for synthesizing the missile homing system. Finally, the article also investigates the influence of systematic error in determining the speed, normal acceleration of missiles and the angular velocity of the line of sight of the missile and target on the accuracy of the missile homing system. We implement the proposed missile homing system and the parametric optimization method in Matlab. The experimental results illustrate that, using proposed system and the parametric optimization method, the missile can defeat the modern air targets with low visibility, high maneuverability and high survivability. 

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The authors declare that there are no conflicts of interest present.