Complex homing head (versions)

FIELD: weapons and ammunition.

SUBSTANCE: complex homing head comprises an optical and infrared digital photo cameras, a passive or an active radiolocator, an automatic pilot, a unit of threshold passage of a signal of an optical photo camera, a unit of switching off of infrared pixels, an electronic key, a delay line and a night vision device. The signal from the night vision device or from the infrared camera arrives to a specialised computer of a control system, where with the specified extent of validity it is compared with all-aspect images of all known airplanes available in the computer memory. After identification of the airplane type the computer determines the predetermined resolution or prohibition for target damage. A pre-programmed most vulnerable area is selected on the target, and further homing is carried out to the same area by readings from the night vision device or infrared camera.

EFFECT: improved accuracy.

9 cl, 1 dwg

 

The invention relates to missiles "ground-to-air and air-to-air.

Known mobile homing head (hereinafter GOS)containing optical and infrared digital camera and exercising discrimination of decoys and pointing a rocket in advance of the trajectory with the transfer of the point of contact with the nozzle on the fuselage, see patent RU 2400690. The disadvantages of this GOS is that you might accidentally defeat his or civil aircraft, and that the missile hit is not in the most vulnerable place of the plane.

To address these shortcomings GOS in addition to the above elements has a night vision device, the signal of which is fed to a dedicated control computer, where with a given degree of accuracy compared with the existing in computer memory three-dimensional images of all known aircraft, and after identification of the aircraft type, the computer determines a predetermined permission or prohibition of defeats the purpose and on the objectives selected pre-programmed for the most vulnerable place, and further guidance is in this place on the testimony of a night vision device.

GOS can also be passive or active radar and/or the autopilot, the signals are transmitted to the computer.

Identification of the target radio is techico is not performed, as modern radio means the signal can be simulated, which will make the enemy aircraft newsfilm.

If the enemy are fighting some aircraft domestic production or if the opponent uses civil aircraft, removing their images from the computer memory may be blocked.

Under "aircraft" means all aircraft: helicopters, airplanes, cruise missiles, warheads of ballistic missiles, etc.

The night vision device has a range of automatic gain control (AGC), allowing to distinguish between goals and day.

To facilitate identification of targets against the background of the earth, especially the goals, with camouflage coloring, the computer has a program to compare two or more adjacent frames of a night vision device with removing image elements not matching on these frames. After this treatment, the changing image of the earth is fully or partially self-destructs and will remain almost unchanged the image plane.

To exclude the effects of coloring aircraft identification purposes only on the contour of the aircraft. There is another way - identification is carried out by personnel infrared camera (the coloring in this case is almost irrelevant), but this image will depend on the speed JG is the that is, from aerodynamic heating. Not to mention the weather.

If the target is not identified with a given accuracy, for example, with a probability of 95%, with none of the available computer memory planes, then it goes to the discharge allowed to defeat.

If the target is identified as his or civilian aircraft, the computer is instructed to change the direction of flight (up better, not to collide with the earth on low-level flight) and is independent search goal by deviation of the head (e.g., rotational movement) or redirect one of the purposes of mathematical models which are available in the computer's memory.

If the target is identified as the enemy and joined the management device night vision or infrared camera, the computer disables the transfer system point of contact with the nozzle on the fuselage (system timing), if there were any in the GOS, as the mouse is the most vulnerable point of the plane. If the goal is overcast, the system will not disabled.

The sketch shows a block diagram GOS rocket mid-range, where: OFC - optical digital camera, IFC - infrared digital camera with the same and synchronized scan, PPP - block threshold bandwidth signal, VIP - Blo is off pixels infrared camera, ECU - electronic key management, LPA - delay line, radar - radar, NVD - night vision device To the computer.

The missile range will additionally have the autopilot, but the rocket is in the middle range may not have radar, but the autopilot may have.

Works GOS: at large distances the mouse is on the radar. When approaching to the appropriate range, the target detection occurs infrared camera and the aiming is carried out by two signals, which increases the noise immunity.

When getting into the field of view of the optical chamber heat traps her bright signal overcomes the block threshold bandwidth and using a block off infrared pixels VIP "cuts" on the signal of the infrared camera is a black spot in this place. In the result, the GOS does not react to trap heat.

When the attempt of the enemy to give his plane for a false purpose, artificially increasing its optical luminosity, lost signal with the IFC and the electronic key ECU through the delay line LPA disables the block VIP. The goal again is visible in the infrared range. The process pulsating repeated that does not interfere with the mouse.

At distances reliably distinguish the contours of the target device night vision or infrared camera serves the target image in the computer, where contoural compared with the existing memory. The computer generates a control system rudder (not shown), the signal of the target steering or changing course and finding another target.

When defeat is pointing at a pre-specified of the most vulnerable point of the plane, for example in the wing center section. The system transfer point of contact with the nozzle on the fuselage (advance) will shut down the computer.

1. Comprehensive seeker containing optical and infrared digital camera, the unit threshold bandwidth of the optical signal of the camera unit off infrared pixels, the electronic key and the delay line, characterized in that it has a night vision device, the signal of which is fed to a dedicated control computer, where with a given degree of accuracy compared with the existing in computer memory three-dimensional images of all known aircraft, and after identification of the aircraft type, the computer determines a predetermined permission or prohibition of defeats the purpose and on the objectives selected pre-programmed for the most vulnerable place, and further guidance is in this place on readings night vision.

2. The head according to claim 1, wherein the night vision device has a range of automatic gain control, allowing to distinguish between C the Li and day.

3. The head according to claim 1, characterized in that the computer has a program to compare two or more adjacent frames of a night vision device with removing image elements not matching on these frames.

4. The head according to claim 1, characterized in that identification purposes only on the contour of the aircraft.

5. The head according to claim 1, characterized in that if the target is not identified with a given accuracy with any of the available computer memory planes, then it goes to the discharge allowed to defeat.

6. The head according to claim 1, characterized in that the computer has the following program: if the target is identified as his or civilian aircraft, the computer is instructed to change the direction of flight and is independent search goal by abnormalities of the head, or redirect one of the purposes of mathematical models which are available in the computer's memory.

7. The head according to claim 1, characterized in that the computer has the following program: if you have included the management of a night vision device, the computer disables the transfer system point of contact with the nozzle on the fuselage (system timing), if it was on the rocket.

8. Comprehensive seeker containing optical and infrared digital camera, the unit threshold bandwidth of the optical signal is of the second camera, block off infrared pixels, the electronic key and the delay line, wherein a signal from an infrared camera is fed to a dedicated control computer, where with a given degree of accuracy compared with the existing in computer memory three-dimensional images of all known aircraft, and after identification of the aircraft type, the computer determines a predetermined permission or prohibition of defeats the purpose and on the objectives selected pre-programmed for the most vulnerable place, and further guidance is in this place on the testimony of an infrared camera.

9. Head of claim 8, characterized in that it is passive or active radar and/or the autopilot, the signals are transmitted to the computer.



 

Same patents:

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Self-homing device // 2392575

FIELD: physics, navigation.

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2 cl, 2 dwg

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7 dwg

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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

FIELD: methods for generation of launcher guidance angles by fire control devices.

SUBSTANCE: the probability of pursuit of the underwater target is determined and in addition a correcting of the launcher guidance angles is introduced in the calculation of the lead point coinciding with the center of the target pursuit area by determination of linear deflection of aiming point Δxc by formula: Δxc=l0-ln , where ln - semilength of the target pursuit area; l0 - semilength of the target lock-on area.

EFFECT: enhanced probability of hitting of the underwater target at firing by rockets 90P to the target lead point.

5 dwg, 2 tbl

FIELD: guided missile guidance systems.

SUBSTANCE: before normalization of missile control signals the engine operation time is preset, a priory evaluation of the projections of the missile axial acceleration onto the input axes of the antenna co-ordinate system of the homing head is preset. On completion of engine operation the present flight time is measured, the time before impact with the target is determined, and the evaluation of miss caused by missile axial acceleration is determined. The axial acceleration compensation signal is proportional to the evaluation of miss caused by missile axial acceleration. The obtained compensation signal is summed up with the signal of missile control according to the method of proportional navigation or its modifications.

EFFECT: enhanced accuracy of guidance.

2 dwg

FIELD: armament, in particular, control of artillery guided missiles with a laser semi-active homing head, locking an illuminated target in the terminal trajectory leg, applicable for control of fire of mortars and cannon artillery.

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EFFECT: enhanced accuracy of fire at movable targets.

4 cl, 2 dwg

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