| 摘要 |
FIELD: high-accuracy armament systems, in particular, guidance systems of tactical ballistic missiles. ^ SUBSTANCE: the method includes the lunching of the missile and its flight on the trajectory having a ballistic leg, on which the moment of separation of the correctable war module is determined, and the correctable war module is separated, and a homing leg. In addition the flight trajectory has a leg of intermediate correction. Prior to the missile launch, the initial conditions for computation of the predicted flight trajectory of the correctable war module are set into the on-board computer via the antenna of the communication radio set and the on-board receiver. After the launch the kinematic parameters of the missile motion are additionally determined on the ballistic leg, and after separation of the correctable war module the predicted miss of the correctable war module is computed on the leg of intermediate correction, and the impulse correction engine is started for reduction of the miss to the minimum value. Before the homing leg the correctable war head is decorated to the operating linear and angular velocity, and the beginning of the homing leg is determined by transmitting a signal from the correctable war module via the radio channel to the target indicator-range finder. At intermediate correction and homing the impulse correction engines are started when the current miss exceeds the allowable value. ^ EFFECT: enhanced accuracy of guidance. ^ 1 dwg |
