Patent RU-2280836-C1 (RU)
Inventor: SHIPUNOV ARKADIJ GEORGIEVICH
IPC: F41H11/02
Filed: 2004-12-08
Granted: 2006-07-27
Abstract: FIELD: armament and military equipment, in particular, protection of aircraft against attacking guided missiles, for example, with the aid of machine-gun (gun) mountings. 
     SUBSTANCE: in the known method for protection of flight vehicles against guided missiles including a search, detection and tracking of the guided missile, determination of angular corrections of the means of destruction of the guided missile for determination of its spatial attitude, the destructive action on the guided missile with regard to the determined corrections, according to the invention before the beginning of the destructive action of the means of destruction the most attack-dangerous guided missile is selected out of the attacking ones and the required miss of the separated guided missile, range to the initiation of the flight vehicle maneuver (Dinm) and the range of the destructive action are determined, the destructive action is performed at the range of the destructive action, after that at the range of the beginning of the destructive action determined from a mathematical expression the maneuver of the flight vehicle is performed with an allowable g-load up in the vertical plane up to the fly-by of the guided missile.  The raised task is solved by the fact that in the known system of fire protection against a guided missile containing the series-connected scanning-sighting system, on-board computer, power drives of the installation, destruction means, as well as the navigation, destruction means as well as the navigation system, the outputs of the navigation system are connected to the computer inputs, according to the invention additionally used are a device for selection of the maneuver and firing ranges, a comparison unit, a unit for formation of the maneuver and firing ranges, as well as a unit for formation of the flight time.  The first and the second inputs of the unit for formation of the line range are connected respectively to the second and the third outputs of the scanning-sighting system, the third input of the unit for formation of the line range is connected to the first output of the navigation system, its fourth input is connected to the output of the unit for formation of the flight time, and the fifth input of the unit for formation of the line range - to the first output of the comparison unit, whose first input is connected to the first output of the scanning - sighting system, its second and the third inputs receive signals from the selectors of the required miss value and allowable g-load of the flight vehicle.  The fourth input of the comparison unit is connected to the output of the unit for formation of the flight time, the first and the second inputs of the unit for formation of the flight time are connected to the second and the third outputs of the scanning-sighting system respectively, its third input is connected to the first output of the comparison unit, the fourth and the fifth inputs of the unit for formation of the flight time are connected respectively to the first and the second outputs of the navigation system, its sixth and seventh inputs receive signals from the selectors of the values of the ballistic coefficient and the missile initial speed respectively.  The first input of the unit for formation of the maneuver and firing ranges is connected to the first output of the navigation system, its second, third and fourth inputs are connected respectively to the second, third and first outputs of the scanning-sighting system, the fifth, sixth and seventh inputs of the unit for formation of the maneuver and firing ranges receive signals from the selectors of fire rate N, burst length and missile speed respectively, its ninth input is connected to the output of the unit for formation of the flight time, and the tenth input - to the sixth output of the navigation system, the first output of the unit for formation of the maneuver and firing ranges is connected to the input of the flight vehicle control system, and its second output - to the input of the destruction means. 
     EFFECT: enhanced survival rate of the flight vehicle due to maximum reduction of the firing range by the fire protection system and thus provision of the required systematic miss of the destructed missile due to maneuver of the flight vehicle. 
     10 cl, 8 dwg, 1 tbl