FIELD: weapons and ammunition, physics.
SUBSTANCE: novelty of invention consists in preparing the missile aboard the carrier aircraft for operation, measuring the parameters of the target and missile motion, estimating the required parameters of the target relative motion and the rocket absolute motion and selecting the method of guiding the rocket to the target. The signal to prepare and control the radio detonator is generated. Proceeding from the current values of angular position, distance to the target and the speed at which the rocket approaches the target, the rocket miss module, the target geometrical sizes and aspect ratio. Allowing for the above data and initial speed of fragmentation scatter, the instruction for the rocket explosive firing is generated. The rocket explosive hitting field is controlled depending upon the target position relative to the rocket lengthwise axis.
EFFECT: higher efficiency of aircraft guided missiles due to control over spatial and power characteristics of hitting field depending upon target position relative to rocket lengthwise axis.
21 cl, 14 dwg
