Patent EA-002202-B1 (EA)
Title: A guidance system for a short-range anti-aircraft missile unit
Inventor: EFREMOV VENIAMIN PAVLOVICH
IPC: F41G7/30
Filed: 1998-10-19
Abstract: 1. A guidance system for a short-range anti-aircraft missile unit, comprising mounted on a single self-propelled carrier, or in a conveyance container, detection means 2 having an all-round looking radar; radar-based identification interrogator 4; means 10 for tracking and precision-measurement of the target and missile coordinates; means 22 for displaying an information; devices 6 for the missile pre-launch preparation and launch execution; transponder 18; missile autopilot 19; computation control means, including evaluator 7 for evaluating the time a target enters the launch area, and evaluator 14 for evaluating the angle misalignment, characterized in further comprising: means 1 for partial controlling of antenna beams of the all-round looking radar, having a phase-shift device; means 3 for the range and azimuth tracking; system 8 for controlling the beam of a radar of means 10 for tracking and precision-measurement of coordinates, the antenna of which radar is implemented in the form of a phased array; programmable search device 9; system 11 for simultaneous tracking basing on four coordinates (azimuth, elevation, range and Doppler frequency) of a number of objects using the radar of means 10 for tracking and precision-measurement of coordinates; device 17 for controlling the pattern width; missile beacon 21; tracking radar 20 of missile beacon 21; switching device 15; device 13 for identification of the target class and adapting the modes of operation of the missile control systems, including a signal spectral analysis unit; evaluator 16 for evaluating the pre-launch command information and missile deviation angles after the vertical launch; device 12 for analysing the launch results; and the computation control means further comprises second evaluator 5 for evaluating the time a target enters the launch area; the pattern of antenna of radar-based identification interrogator 4 being deployed in azimuth relative to the antenna of the all-round looking radar of detection means 2 in the direction opposite to that of rotation of the latter; a transmitter of the all-round looking radar of detection means 2 being connected to the phase-shift device of means 1 for controlling the antenna beams of the all-round looking radar of detection means 2, which phase-shift device is connected to antenna emitters of the all-round looking radar of detection means 2; output of a receiving system of the all-round looking radar of detection means 2, which system is of the "n-channel" type, being coupled to radar-based identification interrogator 4 and to a first input of range and azimuth tracking device 3, a second input of which being connected to output of radar-based identification interrogator 4; output of range and azimuth tracking device 3 being coupled to second evaluator 5 for evaluating the time a target enters the launch area, and to system 11 for simultaneous tracking basing on four coordinates; programmable search device 9, via beam control system 8, being connected to antenna of the radar of means 10 for tracking and precision-measurement of coordinates, whose receiver outputs being connected to system 11 for simultaneous tracking basing on four coordinates; evaluator 16 for evaluating the pre-launch command information and the missile deviation angles, via its input, being connected to system 11 for simultaneous tracking basing on four coordinates, and via its output - to missile autopilot 19; tracking radar 20 of missile beacon 21 being connected, via device 17 for controlling the pattern width, to antenna of the transponder tracking radar of means 10 for tracking and precision-measurement of coordinates; switching device 15, via its inputs, being coupled to output of the transponder tracking radar receiver of means 10 for tracking and precision-measurement of coordinates, to tracking radar 20 of beacon 21 and to output of evaluator 14 for evaluating the angle misalignment, and via its output being coupled to the transponder tracking system of means 10 for tracking and precision-measurement of coordinates; inputs of evaluator 14 for evaluating the angle misalignment being coupled to system 11 for simultaneous tracking basing on four coordinates and to tracking radar 20 of beacon 21; device 13 for the target class identification and adapting the modes of operation of the missile control systems, via its inputs, being connected to system 11 for simultaneous tracking basing on four coordinates and to the radar receiver of means for tracking and precision-measurement of coordinates, and via its output - to a device for transmitting the control information to missiles, which device belongs to means 10 for tracking and precision-measurement of coordinates; launch result analysis device 12, via its input, being connected to system 11 for simultaneous tracking basing on four coordinates, and via its output - to information display means 22; input of evaluator 7 for evaluating the time a target enters the launch area being connected to system 11 for simultaneous tracking basing on four coordinates; and outputs of both evaluators 5 and 7 for evaluating the time a target enters the launch area being connected to devices 6 for the missile pre-start preparation and launch execution.