METHOD OF ANTENNA inertial drive ensures stable maneuvering INTENSIVELY SUPPORT AND HIGH-SPEED AIRCRAFT WITH HIGH adaptation to maneuver CARRIER AND SYSTEM FOR ITS IMPLEMENTATION

摘要

1. A method for controlling the inertial drive antenna, consisting in the fact that generates error signals for tracking bearing and the angular velocity target value by subtracting the estimated signal bearing tseliznacheniya estimated rotation angle signal antennyi subtracting from the value of the estimated angular velocity signal tseliznacheniya estimated angular velocity signal of antennyusilivaya koeffitsientamii constant depending on the antenna drive properties, characterized in that it additionally takes into account the signal of the angular velocity estimation inii sight, its second derivative pervoyi reinforced with different coefficients depending on the parameters of the antenna drive protractor and stack them with reinforced tracking error signals, the drive control signal forming antennygdei- estimates the rotation angle of the antenna and its angular velocity, u evaluation target and the angular bearing line of sight velocity u estimates the first and second derivatives of the line of sight angular rate, T - the time constant of the actuator protractor, b - a drive gain goniometer, P and the weighting coefficients of p- tsenki current state, k is the coefficient value for fine upravleniya.2 signal. . Goniometer control system implementing the method according to claim 1 and including the position of the antenna sensor, the inclinometer actuator position sensor antenna filter finder, subtractors, protractor filter, amplifiers, an adder; characterized in that it additionally introduced sensor position in space, the magnitude of the course filter, the values ​​of the first and second derivatives of course come reinforced with coefficients Ci Kna input of the adder 16, the values ​​of the first and second azimuth derivative