| 摘要 |
FIELD: guidance of missiles on target. ^ SUBSTANCE: the system has the first subsystem for determination of the target co-ordinates and output of the co-ordinate data. The second subsystem, using these data, computes the flight trajectory to the target with the mentioned co-ordinates. The projectile in such a system is launched and guided in flight in the trajectory to the target. The projectile is made in the form of a tungsten core, and the first subsystem has an infra-red imaging system of forward view and a laser range finder. The second subsystem has a fire control system. The fire control system has an additional inertial measuring device and precomputes the target co-ordinates. The projectile is installed in a rocket launched from the launching table, for example, of a launching machine. After burn-out of the rocket propellant in the initial stage the rocket launches the projectile in the flight to the target. The rocket is made in the form of a jet projectile with a guidance system and a propulsion system. The guidance system has a transceiver device installed on the projectile. The transceiver device has a low-power continuous radiator of the millimetric band. The system is installed on the launcher for an exchange of in formation with the projectile. The system on the launcher transmits short command signals to the projectile and measures the time of their passage to and fro for confirmation of the projectile range. Then the monopulse aerial installed and the launcher determines the azimuth and the elevation angle. As a result, the launcher system determines the projectile co-ordinates and its impact point. The launcher system generates a command to the projectile, which it receives and uses for the drive of the control surfaces so as to correct the projectile trajectory and the point of impact. ^ EFFECT: optimized operating characteristics of the guidance system and reduced cost of it. ^ 22 cl, 3 dwg, 1 tbl |
