FIELD: military equipment.
SUBSTANCE: invention relates to weapons and can be used in anti-aircraft missile systems, as well as in artillery. According to the method, the range and speed of the target and the missile directed to the opposite target course are measured. Missile warhead is blasted at preset range to form circular field of striking elements moving towards target. At that, during guided missile guidance, current time of its flight is determined before warhead is blasted before target. Taking into account flight characteristics - coordinates and speed of target and guided missile. Interval of time between the moments of measurement of coordinates of the target and the guided missile, delay in the control channel of the controlled missile, missile value of the guided missile at the moment of explosion of the warhead and time after blasting of the warhead are taken into account. That is followed by determining the value of the required radius of the circular field of the striking elements by the time the target is covered with allowance for the damaging elements braking. Provided that the current time of flight of the guided missile to meet the target corresponds to the allowable value, a cocking radio command and a blasting command in the form of a binary ten-digit time code are generated and transmitted to the controlled missile via the radio line before the warhead is blasted. At the same time on the controlled missile board after receiving and decoding of the blasting command code at each exchange cycle the moment of blasting is specified. Accurate time reading is started until blasting, and when it is zeroed, warhead is blasted.
EFFECT: technical result is high probability of target striking by guided missile.
1 cl, 2 dwg
Title | Year | Author | Number |
---|---|---|---|
MISSILE MUNITION | 2020 |
|
RU2769035C1 |
METHOD FOR DETERMINATION OF PROXIMITY FUSE-RANGE AT TESTS OF GUIDED MISSILE | 2005 |
|
RU2294526C1 |
WARHEAD WITH A RADIALLY-DIRECTED LOW-VELOCITY FIELD OF A FLASK GUIDED MISSILE INTENDED FOR INTERCEPTION OF TACTICAL BALLISTIC ROCKETS | 2003 |
|
RU2249175C1 |
SPACE-AIR DEFENSE COMPLEX | 2002 |
|
RU2227892C1 |
TANDEM TYPE WARHEAD | 2003 |
|
RU2251069C1 |
HIGH-EXPLOSIVE WARHEAD | 2006 |
|
RU2301957C1 |
METHOD AND DEVICE (AMMUNITION) FOR DESTRUCTION OF GROUND AND AIR TARGETS | 1999 |
|
RU2158408C1 |
METHOD FOR LOCATION OF ROCKET IN FLIGHT TRAJECTORY | 2001 |
|
RU2241202C2 |
PROVIDING GROUND COMPLEX FOR TESTS OF COMBAT EQUIPMENT OF ANTIAIRCRAFT MISSILES AND PROJECTILES | 2001 |
|
RU2205352C2 |
HIGH-EXPLOSIVE NON-ISOTROPIC WARHEAD | 2006 |
|
RU2301958C1 |
Authors
Dates
2019-11-28—Published
2019-02-14—Filed