| 摘要 |
FIELD: rocket armament, in particular, methods of fire by guided missiles from infantry fighting vehicles and tanks. ^ SUBSTANCE: after launching of the missile from the bore the sustainer engine is started in the trajectory of its flight by the preset start-up time, and the missile is controlled in the active and passive sections of the trajectory up to the end of the missile flight. The sustainer engine is started by a device with an electronic delay, the delay time is determined from the condition: where: - delay time of sustainer engine starting; - missile flight speed at the instant of sustainer engine starting; V0(m/s) - missile muzzle velocity; m(sq.kgf/m) - missile mass at the instant of sustainer engine starting; cx - missile drag coefficient; Smid(sq.m) - missile maximum cross-section area; - air density. ^ EFFECT: enhanced efficiency of fire due to the increase of the maximum flying range at a simultaneous reduction of spread and reduction of dispersion in the initial trajectory section. ^ 3 dwg |
