novtexmechМехатроника, автоматизация, управлениеMekhatronika, Avtomatizatsiya, Upravlenie1684-64272619-1253Commercial Publisher «New Technologies»10.17587/mau.22.365-373novtexmech-1013Research ArticleДИНАМИКА, БАЛЛИСТИКА, УПРАВЛЕНИЕ ДВИЖЕНИЕМ ЛЕТАТЕЛЬНЫХ АППАРАТОВDYNAMICS, BALLISTICS AND CONTROL OF AIRCRAFTСинтез высокоточной системы самонаведения ракет с допустимым запасом устойчивости системы стабилизации нормального ускоренияSynthesis of a High-Precision Missile Homing System with an Permissible Stability Margin of the Normal Acceleration Stabilization SystemДоКуанг ТхонгDoQuang Thong

канд. техн. наук, преподаватель

Ханой

 Ph.D.

Hanoi

doquangthong@yahoo.comТехнический Университет им. Лэ Куй ДонВьетнамLe Quy Don Technical UniversityViet Nam202108072021227365373Copyright © Commercial Publisher «New Technologies», 20212021Commercial Publisher «New Technologies»Commercial Publisher «New Technologies»https://mech.novtex.ru/jour/about/submissions#copyrightNoticehttps://mech.novtex.ru/jour/article/view/1013

На практике широко используется система самонаведения ракет (ССР) с применением метода пропорционального наведения. В ней при уничтожении целей на разных высотах применяется система стабилизации нормального ускорения (ССНУ). Следовательно, система самонаведения ракет является сложной системой, и ее синтез является сложной задачей. При синтезе ССР необходимо синтезировать ССНУ. В целях упрощения процесса синтеза в первом приближении принимаем линейную модель ССНУ и стараемся макситмально использовать команды пакета Control System Toolbox (Matlab). В нем существуют команды описания передаточных функций, команда определения запаса устойчивости по амплитуде и команда определения значений переходной харктеристики линейных автоматических систем. Поэтому в работе представлены методики синтеза ССР c допустимым запасом устойчивости ССНУ по перерегулированию или по амплитуде. Они нетрудно осуществляются с помощью команд MATLAB. Синтез ССР осуществлен методом параметрической оптимизации, позволяющим получить высокоточную ССР. В работе также представлено сравнение результата синтеза ССР с применением этих методик с результатом ее синтеза c допустимым запасом устойчивости ССНУ по показателю колебательности, которое показывает, что предложенные методики синтеза дают одинаковые результаты.

В статье также проводится исследование влияния силы тяжести, продольного ускорения ракеты, ослепления головки самонаведения на точность синтезированной ССР. По результатам наших исследований они мало влияют на ее точность.

The proportional guidance method-based missile homing systems (MHS) have been widely used the real-world environments. In these systems, in order to destroy the targets at different altitudes, a normal acceleration stabilization system (NASS) is often utilized. Therefore, the MHS are complex and the synthesis of these systems are a complex task. However, it is necessary to synthesize NASS during the synthesis of the MHS. To simplify the synthesis process, a linear model of the NASS is used. In addition, we make use of the available commands in Control System Toolbox in MATLAB. Because the Toolbox has the commands to describe the transfer function, determine the stability gain margin, and the values of the transient respond of the linear automatic systems. Thus, this article presents two methods for synthesizing the missile homing systems, including (i) a method for synthesizing the MHS while ensuring the permissible stability gain margin of the NASS, and (ii) a method for synthesizing the MHS while ensuring the permissible stability margin of the NASS by overshoot. These techniques are very easy to implement using MATLAB commands. The synthesis of the proposed MHS is carried out by the parametric optimization method. To validate the performance of the proposed techniques, we compare them withthe MHS synthesized by ensuring the stability margin of the NASS bythe oscillation index. The results show that, two our proposed methods and the existing method provide the same results in terms of high-precision. Nevertheless, the proposed methods are simple and faster than the conventional method. The article also investigates the effect of gravity, longitudinal acceleration of the rocket, andblinding of the homing head on the accuracy of the synthesized MHS. The results illustrate that they have a little effect on its accuracy.

синтез системыракетасистема самонаведения ракетметод пропорционального наведенияцельsystem synthesismissilemissile homing systemproportional guidance methodtargetReferencesKanashchenkova A. I., Merkulova V. I. Aviation radio control systems. Vol. 2, Moscow, Radio Engineering, 2003, pp. 23—30 (in Russian).Kanashchenkova A. I., Merkulova V. I. Aviation radio control systems. Vol. 2, Moscow, Radio Engineering, 2003, pp. 23—30 (in Russian).Zarchan P. Tactical and Strategic Missile Guidance, third edition, Vol. 157, Progress in Astronautics and Aeronautics, published by the American Institute of Aeronautics and Astronautics, Inc., 1801 Alexander Bell Drive, Reston, VA 20191-4344, p. 14.Zarchan P. Tactical and Strategic Missile Guidance, third edition, Vol. 157, Progress in Astronautics and Aeronautics, published by the American Institute of Aeronautics and Astronautics, Inc., 1801 Alexander Bell Drive, Reston, VA 20191-4344, p. 14.George M. Siouris Missile Guidance and Control Systems, New York, Springer-Verlag, 2004, pp. 166, P. 194—196.George M. Siouris Missile Guidance and Control Systems, New York, Springer-Verlag, 2004, pp. 166, P. 194—196.Yanushevcky R. Modern missiler guidance, 2008 by Taylor & Francis Group, LLC CRC Press is an imprint of Taylor & Francis Group, an Informa business, p. 10, p. 18.Yanushevcky R. Modern missiler guidance, 2008 by Taylor & Francis Group, LLC CRC Press is an imprint of Taylor & Francis Group, an Informa business, p. 10, p. 18.Pupkov K. A., Egupov N. D., Kolesnikov L. V.et al. HighPrecision homing systems: Calculation and design. Computational experiment, Moscow, FIZMATLIT, 2011, p. 51, p. 54, p. 294 (in Russian).Pupkov K. A., Egupov N. D., Kolesnikov L. V.et al. HighPrecision homing systems: Calculation and design. Computational experiment, Moscow, FIZMATLIT, 2011, p. 51, p. 54, p. 294 (in Russian).Arkhangelsk I. I., Afanasiev P. P., Bolotov E. G., Golubev I. S., Matvienko A. M., Mizrahi V. Ya., Novikov V. N., Ostapenko S. N., Svetlov V. G. Design of anti-aircraft guided missiles, Moscow, MAI Publishing house, 2001, pp. 321—344 (in Russian).Arkhangelsk I. I., Afanasiev P. P., Bolotov E. G., Golubev I. S., Matvienko A. M., Mizrahi V. Ya., Novikov V. N., Ostapenko S. N., Svetlov V. G. Design of anti-aircraft guided missiles, Moscow, MAI Publishing house, 2001, pp. 321—344 (in Russian).Thong Do Quang.Synthesis of high-precision missile homing system using proportional guidance method, Mekhatronika, Avtomatizatsiya, Upravlenie, 2020, vol. 20, no. 4, pp. 242—248 (in Russian).Thong Do Quang.Synthesis of high-precision missile homing system using proportional guidance method, Mekhatronika, Avtomatizatsiya, Upravlenie, 2020, vol. 20, no. 4, pp. 242—248 (in Russian).Timofeev N. N., Shestun A. N. Design of non-stationary dynamic control systems of aircraft, Saint Petersburg, BSTU, 2001, pp. 9—43 (in Russian).Timofeev N. N., Shestun A. N. Design of non-stationary dynamic control systems of aircraft, Saint Petersburg, BSTU, 2001, pp. 9—43 (in Russian).Thong Do Quang.Synthesis of a missile homing system ta king into account the dynamics of measuring elements, Mekhatro nika, Avtomatizatsiya, Upravlenie, 2019, vol. 20, no. 4, pp. 251—256 (in Russian).Thong Do Quang.Synthesis of a missile homing system ta king into account the dynamics of measuring elements, Mekhatro nika, Avtomatizatsiya, Upravlenie, 2019, vol. 20, no. 4, pp. 251—256 (in Russian).Krinetsky E. I. Homing Systems, Moscow, Mashinostroenie, 1970, pp. 134—151 (in Russian).Krinetsky E. I. Homing Systems, Moscow, Mashinostroenie, 1970, pp. 134—151 (in Russian).Fedosov E. A., Bobronnikov V. T., Krasilschikov N. N.et al. Dynamic design of control systems for automatic maneuverable aircraft, Moscow, Mashinostroenie, 1997, pp. 63—65; pp. 87—88 (in Russian).Fedosov E. A., Bobronnikov V. T., Krasilschikov N. N.et al. Dynamic design of control systems for automatic maneuverable aircraft, Moscow, Mashinostroenie, 1997, pp. 63—65; pp. 87—88 (in Russian).Tolpegin O. A. Mathematical models of aircraft guidance systems, Saint Petersburg, BSTU, 1999, pp. 65—96 (in Russian).Tolpegin O. A. Mathematical models of aircraft guidance systems, Saint Petersburg, BSTU, 1999, pp. 65—96 (in Russian).Lebedev A. A., Karabanov V. A. Dynamics of f light of unmanned aerial vehicles, Moscow, Mashinostroenie, 1962,pp. 482—503 (in Russian).Lebedev A. A., Karabanov V. A. Dynamics of f light of unmanned aerial vehicles, Moscow, Mashinostroenie, 1962,pp. 482—503 (in Russian).Lebedev A. A., Karabanov V. A. Dynamics of control systems for unmanned aerial vehicles, Moscow, Mashinostroenie, 1965, pp. 249, pp. 410—442 (in Russian).Lebedev A. A., Karabanov V. A. Dynamics of control systems for unmanned aerial vehicles, Moscow, Mashinostroenie, 1965, pp. 249, pp. 410—442 (in Russian).Gane V. A. , St epanov V. L. Calculation of tracking systems, Minsk, Vysheyshaya shkola publishing house, 1990, pp. 218—228 (in Russian).Gane V. A. , St epanov V. L. Calculation of tracking systems, Minsk, Vysheyshaya shkola publishing house, 1990, pp. 218—228 (in Russian).Met vedev V. S. , Pochemk in V. G. Control System Toolbox, Moscow, ED. DIALOG MEPhI, 1999 (in Russian).Met vedev V. S. , Pochemk in V. G. Control System Toolbox, Moscow, ED. DIALOG MEPhI, 1999 (in Russian).Ogata K. Modern Control Engineering, Prentice Hall, Pear son, p. 468.Ogata K. Modern Control Engineering, Prentice Hall, Pear son, p. 468.

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