МЕТОДИКА РАСЧЕТА ОШИБОК ОПРЕДЕЛЕНИЯ ТРАЕКТОРИИ УПРАВЛЯЕМОЙ РАКЕТЫ И ПАРАМЕТРОВ ДВИЖЕНИЯ АКТИВНОГО ЭЛЕМЕНТА ЗАЩИТЫ

摘要

Предложена методика оценки ошибок определения угла пеленга и дальности до управляемой ракеты, а также ошибок определения параметров движения активного элемента защиты с целью обеспечения требуемой вероятности поражения ракеты на траектории сближения. Рассматривается подход, при котором снижается вероятность поражения обороняемого летательного аппарата (ЛА) за счет нейтрализации управляемой ракеты активными элементами защиты. Проведена оценка влияния ошибок определения координат ЛА на точность определения координат ракеты.%At present, the onboard aircraft defense structures for protection from "air-to-air" missiles are equipped with the systems of jamming cartridges of various calibers ejection. The existing algorithm of airborne defense systems application consists in practically continuous ejection of a series of jamming cartridges when the aircraft enters the area of the enemy's air defense. However, the existing techniques of jamming cartridges implementation do not ensure the aircraft protection from the missiles equipped with matrix photodetectors. There is a contradiction between the potential onboard defense systems implementation efficacy, and military characteristics of existing onboard defense systems. In this paper, the authors propose a technique for guided missile coordinates determination errors to ensure its neutralization on the flight trajectory. A methodology for probability estimate of aircraft skipping the hit by a guided missile while realizing the active element ejection to the trajectory of the guide missile with its subsequent detonation was developed. The probability estimate of guided missile missing its target is based on probability calculation of the active element's detonation coordinates center will appear inside the dispersion ellipse with the main axes equal to mean square deviation of the active protection element detonation coordinates from the actual position of the missile. The equations for the active protection element detonation coordinates were obtained using measuring errors theory methods on the assumption of the aircraft and missile rectilinear and steady motion, after the initial miss elaboration, with an allowance for the aircraft and missile coordinates and flight speeds measuring error, as well as current missile's angle of attack determination errors. The paper shows that the missile'sangle of attack determination errors depend on aircraft and missile current speeds determination errors, as well as missile bearing in vertical plane measured by optical radar station or specialized onboard radar station belonged to aircraft protection structure.