| 摘要 |
FIELD: methods for missile guidance. ^ SUBSTANCE: the direction and values of the linear lateral rate of deflection of the sight line caused by maneuvering of the carrier are determined, target range is measured and the sight line is moved towards the decrease of the deflection at an angular rate corresponding to expression omega=Vsl/Rt, where omega - angular lateral rate of the sight line, Vsl-sight linear lateral rate of sight line, Rt - target range. After launching of the guided missile for the time of its capture the increment of the linear lateral rate of the sight line is measured, and the information coordinator field of vision is deflected from the sight line towards the side opposite the increment through an angle corresponding to this increment. ^ EFFECT: enhanced accuracy of guidance at carrier maneuvering by 25 to 30 per cent, enhanced reliability of capture of the guided missile and antijamming capability of the guidance system by 18 to 20 per cent. |
