| 摘要 |
control systems of flight vehicles, in particular guided projectiles and missiles. SUBSTANCE: the method for guidance includes two guidance phases. In the first control phase beginning from the moment of projectile lift-off and continuing to the end of the transient processes a signal that is equivalent to the zero command is formed at the output of the control equipment device. At the same time an additional torque counteracting the deflection of the control surfaces from their zero position is built up at the output shaft of the control surfaces of the control actuator. The control of the control surfaces of the projectile control actuator in accordance with the coordinates of its deflection from the sighting line is effected in the second phase before the end of the flight. The guided projectile guidance system has an auxiliary device of the guidance instrument, which accommodates a square-wave generator and a switch. The first and second information inputs of the switch are connected to the outputs of the control command formation unit and the square-wave generator respectively. The switch control input is connected to the timer output, and the output - to the input of the wire communication line. A power engine made in the form a spring, whose one end is connected to the body of the control actuator, and the other - to the axle of the control surfaces, is installed on board the projectile. EFFECT: enhanced accuracy of guidance of guided projectiles and missiles, simplified guidance system. 3 cl, 2 dwg
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