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.
FIELD: weapons and ammunition.
SUBSTANCE: method of generation of a signal of control of a shell rotating by list angle consists in detection of an amplitude modulated signal with a tracking gyroscopic head of homing, proportional to angular speed of a target sighting line, conversion of a signal into a width-modulated signal that arrives to an inlet of a steering drive of the shell. At the same time the sum of the amplitude-modulated signal and the signal of the sensor of angular speed of the shell filtered with a filter of noise components and a filter of a permanent component is converted into the width-modulated signal.
EFFECT: provision of possibility to increase probability of shell hitting a target.
1 cl, 6 dwg
SUBSTANCE: method of striking a target producing coherent interference by launching and guiding missiles fitted with an active radar seeker involves emitting a probe signal and receiving the signal reflected by the target, wherein two missiles are simultaneously directed onto the target, and emission of the probe signal and reception of the signal reflected by the target are reassigned between the missiles alternately; before launching missiles, the intervals for emitting probe signals and receiving reflected signals are synchronised such that intervals for emitting the signal of one missile match intervals for receiving the signal reflected from the target of the other missile. Switching intervals for emitting the signal and receiving the reflected signal is carried out with frequency higher than the bandwidth of the guidance system, and the frequency of switching emission and reception intervals is set primarily alternating. The missiles are guided into the target on "pliers" type maximally divergent trajectories.
EFFECT: improved method.
4 cl, 2 dwg
FIELD: weapons and ammunition.
SUBSTANCE: topographical lock-on of launcher is effected with the help of satellite navigation system prior to setting the fire parameters. Fire control board with digital radio communication means is located 50-100 metres from launcher. Lock-on errors may not exceed 50 metres. Fire control parameters are transmitted in binary code to launcher ACS and, further, to missile. Launcher is turned to azimuth and elevation to launch the missile by command from control board.
EFFECT: increased range of fire, higher safety.
SUBSTANCE: optoelectronic system for an air defence missile system has an pointing head (5) mounted on a precision two-coordinate turning device (8), as well as a computing unit (13), a monitor (15) and a control unit (16). The pointing head (5) has a double-channel design with wide (6) and narrow (7) field of vision television channels. The optoelectronic system is fitted with a unit for superimposing wide and narrow field of vision images (14). The lens of the narrow field of vision channel has a mirror-lens design with central screening and includes a main concave mirror (19) and a convergent mirror (20) arranged in series, as well as annular first (21) and second (22) optical wedges placed in front of the convergent mirror (20) with possibility of independent rotation relative each other around the optical axis of the lens. The outer diameter of the optical wedges is equal to the diameter of the main concave mirror (19), and the inner diameter is equal to the diameter of the convergent mirror (20). The wide field of vision (6) channel is placed in front of the narrow field of vision (7) channel having a common optical axis with it. The diameter of each of the components wide field of vision (6) channel does not exceed the diameter of the convergent mirror (20).
EFFECT: possibility of battery launch of a missile with one air defence missile system at several targets at once.
FIELD: weapons and ammunition.
SUBSTANCE: corrected artillery projectile (CAP) containing body, nongyroscopic target indicator-coordinator, logic device, electric power supply system, jet impulse correcting engines (ICE) are actuated on end section of ballistic flight trajectory maximum during 3 s. Multiple pulse correction is performed at maximum frequency meeting the specified ratio. In order to decrease the angle of non-scheduled CAP oscillations, application points of CAP trust vectors are offset from mass centre towards tail portion through the distance of 2…3 diameters of critical cross section of CAP nozzle. In order to reduce the probability of retaliatory strike of target indication means, laser irradiation of target is performed for not more than 3.5 s. In order to shorten the time and increase the kill effectiveness, the shooting is performed with two or more guns against one target by using the fire schedule providing simultaneous approach of several CAP to obstacle (target).
EFFECT: shortening the time and increasing kill efficiency.
FIELD: weapons and ammunition.
SUBSTANCE: infrared missile seeker includes one photoreceiver located separately from photoreceivers arranged on rotating rotor of coordinator after optic diagram in the form of a slot. The above photoreceiver transmits the received pulse signal from generator of infrared pulse interference to signal amplification unit, and then to control unit of missile rudders and interrupts the signal from photoreceivers arranged on rotating rotor.
EFFECT: improving interference immunity against infrared pulse interference.
FIELD: weapons and ammunition.
SUBSTANCE: initial hypothetic rendezvous moment is pre-set, coordinates of vertexes of triangular approachability areas of missile and target in horizontal plane are calculated for that rendezvous moment from the position corresponding to missile control selection moment. Distances from vertexes of triangular approachability area of target to missile approachability area are determined, which together with hypothetic rendezvous moment are stored. Hypothetic rendezvous moment is varied within the range of the time moment at which the control is chosen to maximum allowable moment of end of orientation. For each vertex of triangular approachability area of target there found is its optimum hypothetic rendezvous moment corresponding to minimum distance between missile approachability area and this vertex. Optimum hypothetic rendezvous moments for each vertex of target approachability area and distance from that vertex to missile approachability area are stored. That vertex of target approachability area is chosen which at its optimum hypothetic rendezvous moment is located at maximum distance from missile approachability area, and as per mutual location of that vertex and missile approachability area built for the same hypothetic rendezvous moment there chosen is missile control.
EFFECT: improving missile orientation accuracy, improving usability of fighting equipment of missile during firing at high-speed and high-manoeuvrable targets.
FIELD: weapons and ammunition.
SUBSTANCE: proposed system compares signals from optical and IR digital photo cameras and radar signal to differentiate between true and false targets. System generates anticipation trajectory via feedback between rudders with movable homing head, that is, the latter turns in direction opposite the rudder deviation unless the rudders stay in neutral position. System can perform leading anticipation towards airframe via shifting rudders position transducer neutral toward the side coinciding with homing head deviation, or its additional deviation toward the same side.
EFFECT: high probability of heating maneuvering target.
4 cl, 3 dwg
FIELD: physics, navigation.
SUBSTANCE: invention relates to navigation equipment and is primarily meant for solving the problem of self-homing through constant-bearing approach of short-term interacting small aircraft. The device has an antenna, a radar set, a timer and a control device. There are two evaluators, an electronic switch, two memory units, a logic device and a control device. The antenna is connected to the first input of the radar set whose output is connected to the first inputs of the first evaluator and the first memory unit. The output of the first evaluator is connected to the first input of the second evaluator and to series-connected electronic switch and second memory unit, the output of which is connected to the second input of the first evaluator, whose output is connected through the first input of the logic device to the input of the control device. A standard one signal is transmitted to the second input of the logic device. The output of the control device is the output of the entire device. The radar set, whose second input is connected to the output of the timer, can be a range finder of a Doppler frequency measuring device.
EFFECT: simple design and broadening options for controlling kinematic motion through constant-bearing approach.
FIELD: defense technology.
SUBSTANCE: accuracy of movable targets is achieved by determination of angular speed and acceleration of target movement by means of introduction of unit for processing of information signals of angular positions of target. Unit inlet is connected to outlet of central computer via the first digital manifold, and outlet is connected to inlet of micro-central computer via the fifth digital manifold. At that unit for processing of information signals of angular positions of target consists of channel for processing of information signals of angular positions of target in horizontal plane and channel for processing of information signals of angular positions of target in vertical plane, outlets of which are connected to the first digital outlet of central computer via the first digital manifold, and outlets - to the inlet of micro-central computer along the fifth digital manifold.
EFFECT: increased accuracy of movable targets accompanying.
2 cl, 2 dwg
FIELD: armament, in particular, artillery guided missiles with a laser semi-active homing head locking on n illuminated target in the terminal trajectory leg; the invention is designed for control of fire of mortars and barrel artillery of calibers, types 120, 122, 152, 155 mm, at firing of guided ammunition, as well as of guided missiles with a homing head.
SUBSTANCE: the method consists in the following: the target is detected by a target indicator, then the distances between the target indicator and the target and the firing position and the target are measured with a topographical survey of the target, target indicator and the firing position, computation and realization of the firing settings according to the target and firing position coordinates. Then, missile guidance to the target is performed, it includes a successive gun setting and turn of the missile on target illuminated after the shot by laser radiation of the target indicator, the topographical target survey and conversion of its coordinates to a sequence of binary codes is accomplished with the aid of a reconnaissance panel, and the computation of gun settings is performed with the id of a gun control panel. A common computer time is organized in the reconnaissance panel and in the gun control panel, and after the shot up to the actuation of the target indicator transmission of the value of the time of switching of target indicator laser radiation is performed from the gun control panel to the reconnaissance panel by means of digital radio communication, and the signal of switching of target illuminance is automatically transmitted from the reconnaissance panel to the target indicator at achievement of the time of switching.
EFFECT: enhanced accuracy of fire by a guided missile at a target illuminated by a laser beam due to reduced quantity of "hand" operations and enhanced accuracy of synchronization of the moment of target illumination with the time of the shot; the last property is especially important for destruction of moving targets.
FIELD: homing systems of flight vehicles.
SUBSTANCE: the method consists in the fact that the distance from the flight vehicle to the target by the moment of beginning of homing, the current rate of closure with it, angular velocities of the sight line and the lateral accelerations of the target and guided flight vehicle in the horizontal and vertical planes are measured. After measurements the signals of flight vehicle control in the horizontal and vertical planes are formed according to the relations using the mentioned coordinates of the target and flight vehicle. The high sensitivity of the flight vehicle to the target maneuver is based on the estimation of its lateral accelerations, and the adaptation to the range of the beginning of homing is based on estimation in the procedure of suspension of its navigation parameter.
EFFECT: provided reaction to the maneuver of far located targets and adaptation to the range of the beginning of homing predetermining a more active maneuver of the guided object on a near located target.
FIELD: high-accuracy armament systems, in particular, guidance systems of tactical ballistic missiles.
SUBSTANCE: the method includes the lunching of the missile and its flight on the trajectory having a ballistic leg, on which the moment of separation of the correctable war module is determined, and the correctable war module is separated, and a homing leg. In addition the flight trajectory has a leg of intermediate correction. Prior to the missile launch, the initial conditions for computation of the predicted flight trajectory of the correctable war module are set into the on-board computer via the antenna of the communication radio set and the on-board receiver. After the launch the kinematic parameters of the missile motion are additionally determined on the ballistic leg, and after separation of the correctable war module the predicted miss of the correctable war module is computed on the leg of intermediate correction, and the impulse correction engine is started for reduction of the miss to the minimum value. Before the homing leg the correctable war head is decorated to the operating linear and angular velocity, and the beginning of the homing leg is determined by transmitting a signal from the correctable war module via the radio channel to the target indicator-range finder. At intermediate correction and homing the impulse correction engines are started when the current miss exceeds the allowable value.
EFFECT: enhanced accuracy of guidance.
FIELD: radio engineering, in particular, methods for guidance of self-moving guided projectiles to reflected laser beam, applicable in military equipment.
SUBSTANCE: use is made of several sources of illumination of the optoelectronic device located on the object of destruction. These sources operate at different frequencies, as a result of which an information field of projectile flight control is produced with a multispectral homing head, which makes it possible to reduce the requirements to the accuracy of projectile guidance to the target at the initial leg o guidance to the optoelectronic instrument, located in the most vulnerable point of the armored object.
EFFECT: enhanced accuracy of guidance of guided projectile to the most vulnerable points of position of the optoelectronic instrument, and efficiency of destruction of the armored object.
FIELD: aircraft guidance systems.
SUBSTANCE: method comprises measuring transverse acceleration of the aircraft to be guided in the horizontal plane, measuring the angle between the vector of aircraft velocity and line of sighting on the ground object, distance between the aircraft and ground object, velocity of the aircraft, and generating the control signal in the horizontal plane as the difference between the required angular velocity of the conventional sighting point multiplied by the adaptive navigation parameter and transverse acceleration of the aircraft in the horizontal plane. The adaptive navigation parameter is generated depending on the difference between the current value of the angle between the vector of the aircraft velocity and line of sighting on the ground object in the horizontal plane and required angular shift of the conventional sighting point in the horizontal plane with respect to the line of sighting on the ground object.
EFFECT: improved stabilizing of linear resolution of the guidance.
FIELD: air defense.
SUBSTANCE: system comprises housing connected with four return springs each of which is connected with the corresponding air vane, propulsion engine, four photomultiplier tubes of the guidance system which are connected in the arms of the electric bridge, four air vanes connected with the electromagnets with movable core through intermediate relay, four infrared devices for photomultiplier tubes, four vision limiters for photomultiplier tubes, four DC amplifiers for photomultiplier tubes, board power source, four tail stabilizing fins, analogue-digital converter, and control unit composed of integrator, tree-link integrating device, and inverter. The photomultiplier tubes are connected with the analogue-pulse converter, intermediate relay, integrator, inverter, and three-link integrating device through the DC amplifier.
EFFECT: accelerated missile aiming.
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.
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.
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.
SUBSTANCE: the method consists in topographical survey of the target indicator and firing position to the terrain, target detection by the target indicator, measurement of the distance from the target indicator to the target, azimuth and angle of sight relative to the target indicator under the conditions of successive target location. Topographical co-ordinates, direction and speed of target motion are calculated in the reconnaissance panel, the co-ordinates, speed and direction of target motion are transformed to a series of binary codes and transmitted to the firing position panel by the digital radio communication. On the basis of the obtained data and preliminarily preset meteorological data, ballistic corrections, time of preparation of the gun and missile to fire the predicted point of impact of the missile with the target an the ground surface is calculated, the fire settings according to the co-ordinates of the gun and the co-ordinates of the predicted point of impact of the missile with the target are calculated, the time of the shot for target destruction in the predicted point is calculated, the sole computing time is set in the reconnaissance panel and in the firing position panel, the fire settings are realized. The signal for a shot is given from the firing position panel when the time of the shot is coming. The time of switching-an of the target indicator of laser radiation is transmitted from the firing position panel to the reconnaissance panel via the digital radio communication channel. The signal for switching-on of the laser radiation target indicator is automatically given from the reconnaissance panel when the required time of switching-on is attained, and the missile is guided to the target illuminated by the laser radiation of the target indicator.
EFFECT: enhanced accuracy of fire at movable targets.
4 cl, 2 dwg