References

gyroscopy

Гироскопия и навигация

Giroskopiya i Navigatsiya

0869-70352075-0927

AO «Концерн «ЦНИИ «Электроприбор»

10.17285/0869-7035.2018.26.4.058-071

gyroscopy-295

Research Article

Статьи

Расширенное двухмерное пропорционально-дифференциальное командное наведение по линии визирования

An Expanded Two-Dimensional Proportional–Derivative Command to Line-of-Sight Guidance Law

Пенев

Б. Г.

Penev

B.G.

Пенев Борислав Г. Доктор наук, доцент факультета оптоэлектроники и лазерной техники

Софийский технический университетБолгарияTechnical University – Sofia, Branch PlovdivBulgaria

2018

21112025

2645871

2025

Пенев Б.

Penev B.

This work is licensed under a Creative Commons Attribution 4.0 License.

https://www.gyroscopy.ru/jour/article/view/295

В статье рассматривается расширенное двухмерное (2D) пропорционально-дифференциальное командное наведение по линии визирования, которое позволяет избежать возникновения спиральной траектории движения противотанковой управляемой ракеты в плоскости, перпендикулярной линии визирования, или так называемой плоскости перспективы. Предложенный метод наведения повышает качество переходного процесса при выводе ракеты на линию визирования. Закон наведения работает как классический закон пропорционально-дифференциального регулирования в пределах небольшой заданной области вокруг линии визирования, а при выходе ракеты из этой области закон регулирования задействует дополнительные нелинейные компоненты, зависящие от производных координат ракеты в плоскости, перпендикулярной линии визирования. Доказана глобальная асимптотическая устойчивость системы наведения путем введения в рассмотрение особой положительно определенной функции Ляпунова. Результаты моделирования демонстрируют эффективность предложенного подхода. Закон наведения позволяет уменьшить влияние ближних граничных условий на радиус действия ракеты.

This paper deals with an expanded two-dimensional (2D) proportional-derivative (PD) command to line-of-sight (CLOS) guidance law which fights the spiral type trajectory of an anti-tank guided missile (ATGM) in the plane perpendicular to the line-of-sight (LOS) or the so called picture plane, in order to improve the transition process performance while putting the missile onto the LOS. The guidance law acts as a classical PD control law within a small predetermined area around the LOS while at missile deviations pointing a position outside this area the control law includes additional nonlinear components connected with the derivatives of the missile position vector in the plane perpendicular to the LOS. The global asymptotic stability of the guidance loop is established by a specific positive definite Lyapunov function. The effectiveness of the proposed approach is illustrated by simulation results. The guidance law enables to decrease the near-field boundary of the missile operational range.

Управляемая ракетатрехточечное наведениенелинейное управлениеасимптотическая устойчивость.

Guided missilethree-point guidancenonlinear guidanceasymptotic stability.

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