Guidance method to optic beam of missile launching from mobile carrier, and guidance system for its implementation

FIELD: weapons and ammunition.

SUBSTANCE: method involves formation of two beams in the form of sequence of short light pulses projected in the form of strips of constant width, which are perpendicular to each other, subsequent orthogonal scanning of beams as to heading and pitch relative to strip length, transmission to the missile of information on spatial position of beam and generation of guidance command in missile equipment. In addition, variation of carrier roll angle α is measured after missile launching; components of coordinates Yb·cos(α) and Yb·sin(α) of the beam scanned as to pitch and Zb·cos(α) and Zb·sin(α) of the beam scanned as to heading are determined and transmitted to missile in sequence of light pulses, and its coordinates are determined in missile equipment as per the following ratios: Zm=Zb·cos(α)+Yb·sin(α), Ym=Yb·cos(α)-Zb·sin(α), where Zm, Ym - current missile coordinates. To the carrier equipment there introduced is in-series connected roll angle sensor of carrier and sine-cosine functional converter, as well as product unit. The first and the second summation units are added to the missile equipment.

EFFECT: improving guidance accuracy and maintaining stability of missile control circuit due to compensation of turn of coordinate system of movable carrier relative to missile coordinate system after its launching.

2 cl, 6 dwg

 

The proposed method homing missiles optical beam and a device for its implementation relate to the field of weapons and can be used in anti-tank missile complexes ATGW placed on mobile devices such as aviation.

Currently, the guidance systems of missiles at the target optical beam are widely used in domestic complexes guided weapons, such as "brass Knuckles", "Bastion", "SWIR", "Reflex", as well as foreign, such as "SPEAR" (firm Diehl, Germany) (Weebie, Web, Avignon, Arilou. The basics of the operation of artillery and guided missiles, Tula: ed. Tula state University, 2003, p.75 [1]).

There is a method of guidance, namely, that in the place of launch is directed to goal three of the laser beam (clock and scanned in vertical and horizontal directions relative to the target), and the optical axis of the synchronizing beam is combined with line of sight (U.S. patent No. 4111385 from 16.04.1976,, CL 244/3 .13). The laser beam performing the scanning in the horizontal plane, is elongated in the vertical direction of the radiation pattern and directivity of the laser beam scanned in the vertical plane, elongated in the horizontal direction. In the process of homing missiles is the settlement of adulterine scanning rays. The position of the missile in a raster scan (control field) is determined by the time interval between the reception of rocket signals upon irradiation her scanned and synchronizing rays, and the synchronizing beam radiates the signal in the point of intersection of the scanned beam center control field (line of sight) and has a size equal to field management.

In the patent of the Russian Federation 2382315 from 20.02.2010, taken as the closest analogue, presents the implementation of how the controller uses two beams, comprising the following operations. On the control station 1 (figure 1) towards the target send two flat scanned beam. Luminous flux from the first pulsed radiation source II 2 block form a flat orthogonal beams WAS 4 concentrated in a narrow beam that is elongated in the vertical direction, and the light flux from the second pulsed radiation source II 5 block formation are concentrated in a narrow beam that is elongated in the horizontal direction. The total cross beam of the unit 4 is directed to the scanning unit BS 7 made in the form of optical wedge driven in rotary motion by the drive. The scanning unit implements a consistent swing beams. When this beam, the beam which is elongated vertically, scan rate and beam chart, the latter is the Uta horizontally, scan pitch. Synchronously with the scanning unit rotates the sensor of angular position of the rays DUP 8, the output of which produces signals on the spatial position of the beams relative to the mean coincident with the line of aim.

Signal light from the scanning unit to send optical zoom optical system OPS 9, which continuously during flight of the projectile produces a scaled image of the scanned beams is inversely proportional to the distance to the rocket, thereby providing a constant size field of the control trajectory.

The electrical signals of the position of each of the scanned beam in the control field of the sensor 8 is directed to the input of pulse shaper code FIC 3.

Shaper pulse code generates code sequences, which contain information about the current position of the scanned beams at the rate and yaw control field (information about the coordinates of the projectile during its irradiation).

The digital signal with a sensor of angular position about the spatial position of the beam in the pulse shaper code transform in the time interval τToin the channel rate and τ in the channel pitch between literal and coordinate impulses.

Pulse channel code rate shaper pulse code served on the first source and the radiation, and channel pitch - the second radiation source. Sources of radiation under the action of control signals from the pulse shaper code produce short light pulses.

Flat optical beams sequentially scanned one at the rate of the second pitch, and sequentially emit signals in the direction of the goal. The vertical beam at the time of scan rate modulate a code sequence which provides information about its position relative to the line of sight and the beam is scanned across the pitch, modulate a code sequence containing information about its spatial position.

On-Board equipment of the projectile 12 receives the optical signal and converts it to a radiation detector into an electrical signal. The signal occurs only at the intersection of the scanned rays of the light receiver 13. At the time of irradiation missiles beam is scanned across the course (pitch), the onboard apparatus from a sequence of light pulses produce information about the position of the strip beam coordinate course (pitch), coincident with the coordinates of the missile in the field of management. In accordance with the selected coordinates to produce control commands rocket, resulting in its line of sight.

Thus, the entity known way to aim the missile Zack is udaetsya the following:

in the formation of two scanned optical beams with a narrow radiation pattern in cross section and modulated by the sequence of short light pulses;

in the calculation of the carrier current coordinates of the bands rays at the rate and pitch;

in the transfer of the missile in the sequence of light pulses calculated components of the coordinates of the rays;

in the allocation of rocket components of the coordinates of the rays and the formation of teams aiming for known dependencies.

Hover missiles optical beam with the rolling of the carrier there is a mutual rotation (twist) of a rectangular coordinate systems media (measuring system) and rockets (Executive system)arising from the roll media. The carrier mobility can be an aircraft (airplane, helicopter), marine (boat), or land (war machine).

At the time of launch the rocket with the help of the gyroscopic unit commands memorized the position of Executive coordinate system coinciding with the measuring coordinate system of the carrier associated with the field of management created the scanned beam. After the launch aircraft carrier shall, as a rule, maneuver out of the killing zone, this raises the roll media and, consequently, rotation of the measuring coordinate system information for the I control relative to the Executive coordinate system of the rocket. The angular speed of the spread of a modern airplane or helicopter to roll when the maneuver can reach 40°/s

This leads to rotation ("twist") of the coordinate systems associated with the carrier and missile.

Rotation of coordinate systems will result in a known way to aim the missile to the distortion of selection coordinates of the beam and, consequently, distortion of the coordinates of the missile and command guidance, which will cause deterioration of the stability of the control loop and the loss of precision targeting. Feature-guided missiles on a narrow scanned beam is the fact that at each moment of time in the apparatus rocket information is received by only one of the coordinates of the beam YLor ZLand the media is no information about the coordinates of the missile in the field of management. This feature does not allow media by the beam to pass to the missile, the guidance commands Zpand Yptaking into account the change in the angle of roll media. If the roll media after launch does not change (land holders), then the moments of the radiation missiles are scanned by the beam of its coordinates in the Executive system of coordinates coincide with the coordinates of the stripe beam control field (in the measuring coordinate system). If the roll media after the launch of change (aircraft carriers), the coordinates of the rocket in the Executive system CCW is dint do not match the moments of the radiation missiles with coordinates of the scanned beam, so in the guidance systems of missiles by scanning a narrow beam cannot transfer directly command guidance missile Zp, Yphow this is done in the command telecontrol systems.

Known methods compensate for the twisting coordinate systems after launch missiles guidance systems for optical beam (beam systems telecontrol):

the introduction of the compensating prisms in the optical system forming the beam (optical method);

- the introduction of amendments to the change of the angle of roll media after launch (a transfer method by the beam on the missile roll angle of the carrier).

Optical compensation of the rotation axes of the coordinate after launch based on a combination of measuring and Executive coordinate systems using optical plates and prisms (Dov, Pehan) in the device (equipment) carrier, rotating the image control field.

The optical compensation "twisting" of the instrument coordinate system of the carrier relative to the coordinate system of the rocket has a number of disadvantages, the main of which are:

technological complexity of manufacturing and alignment of the prisms, plates and servo drives, and low accuracy compensation "twisting" of the coordinate systems

- the complexity of the optical circuit device of the media, especially when large light aperture is x prisms.

Error of fabrication and alignment of the prisms and plates lead to withdrawal (beating) of the center of the field of missile guidance and mainly due to:

- inclination of the reflecting face of the prism to the axis of its rotation due to the presence of the radial beating bearings, in which is installed prism

- tilt the axis of rotation of the plate or prism to the axis of movement of the zoom lens;

- pyramidal manufacturing prisms and clinoid shape of wafer production. Calculations show that these errors lead to an overall shift of the optical axis of the beam relative to the target at distances of 5-7 km on the value of 0.6-0.8 m, which reduces the accuracy of missile guidance. In addition, the introduction of optical compensators and their controls significantly increase the size, weight and complexity of manufacturing unit media.

The task of the invention is to increase the precision pointing optical beam missiles, starting with the rolling carrier, in the presence of "twisting" of the coordinate systems while simplifying the equipment carrier and missiles.

The problem is solved as follows. The known method of guided optical beam missiles, starting with the rolling media, including the formation of two beams in a sequence of short light impulse is, projected into space in the form of strips of constant width, with strips perpendicular to each other, a sequential scan of the rays in the space of one course, a different pitch relative to the target orthogonal to the length of the strip, the transfer of the missile position information of the beam in space and allocation of equipment missile command guidance, the measured change of the roll angle of the carrier of α after launch, determine and transmit a rocket in the sequence of light pulses constituting the coordinate YL·cos(α) and YL·sin(α) of the beam is scanned across the pitch and ZL·cos(α) and ZL·sin(α) of the beam scanned on the course and in the equipment of the rocket its coordinates determined by the dependencies:

,

where ZP, YP- the current coordinates of the beam (missiles), converted into an execution system of coordinates missiles;

ZL, YP- the current coordinates of the beam in the measuring coordinate system of the carrier.

Calculation of the components of ZL·cos(α), ZL·sin(α), YL·cos(α) and YL·sin(α) in the claimed method is performed with high accuracy in the instrument carrier with the help of computers. Components of the coordinates of the beam transmitted to the missile in the sequence of pulses. In the on-Board device of the rocket at the moment exposed the Oia beam, the scanning rate, extracted from the code sequence of light pulses of the components of ZL·cos(α) and ZL·sin(α), and the irradiation beam, the scanning pitch, allocate the components of YL·cos(α) and YL·sin(α), which are summed in accordance with the expression (1) and under which generates control commands.

Therefore, in the proposed method of guided missiles optical beam compensation "twisting" of the coordinate systems when roll media is carried out without the use of complex optical devices in the equipment carrier and without complicated operations in the apparatus of missiles on the formation of the functions sin(α) and cos(α) and multiplying them by the coordinates of the missile in the field of management that cannot be performed with high accuracy on the rocket.

The proposed guidance method is illustrated in figure 2...5, where figure 2 shows the structural block diagram of the proposed system controller figure 3 denote: ZL, YL- axis of the measurement coordinate system of the carrier; ZP, YP- axis of the Executive coordinate system of the rocket; α - angle "twisting" of the coordinate system when the roll carrier; 23, 24-scanned strip of optical beams; 25 - information field of missile guidance; 26 - rocket. Figure 4 presents the structure of the hardware of the proposed method guidance, where 27-devices is ur media 28 - optic line, 29 - apparatus missiles.

Figure 5 presents the view code sequence of light pulses: - the reference pulse; LTo, LT- lettered pulses; Zn • cos(α), ZL·sin(α),YL·cos(α) and YL·sin(α) - pulses carrying information about the coordinates of the rays (missiles) taking into account the reversal of the coordinate systems; τltoτlt- lettered intervals; τtoτt- coordinate intervals; τin- timeline coding coordinates; τand- the duration of one sequence of pulses, τABOUT- duration exposure missiles are scanned by the beam.

The essence of the proposed method of guided optical beam missiles, starting with the rolling media, is the following. From the media towards the target after launch send two flat optical (laser) beam, sequentially (serially) scanned orthogonal to the length of the strip at the rate and pitch relative to the target (figure 3). The laser beam, the scanning rate is elongated in the vertical direction of the pattern 23, and the beam scanning pitch, has a radiation pattern that is elongated in the horizontal direction 24. The beams are scanned sequentially in the control box 25 with a constant frequency.

The dimensions of the raster scanning beams in the process namegenerally software reduces inversely proportional to the distance to the rocket using a zoom optical system, that provides constant size strips rays and field control rocket. The center of the field of management combined with the line of sight targets.

Measure the current scanning angle of the beam relative to the center of the field of management, which is proportional to the coordinates of the runway beam. The measured coordinates of the beam is converted into a coded sequence of pulses which modulate the radiation of semiconductor lasers.

When the scan rate of the beam modulate the pulse sequence presented in figure 5,a, a scanning pitch sequence presented on figure 5,b. The duration of one pulse sequence is equal to τAnd.

Lettered intervals τLToτLTperform coding of the transmitted information when scanning beams at the rate and pitch, respectively. Are these intervals are the same for instruments missiles and carrier that provides a clear separation of coordinates through appropriate channels.

In the proposed method of guided missiles optical beam in contrast to the known introduced a new operation to compensate for the rotation ("curl") coordinate systems arising from the roll media after the launch. When the scanning beam on the course in the time interval τK1pass to rocket coordinated the ATU band beam at the rate multiplied by the function sin(α) changing the angle of roll media after the launch, and in the time interval τK2- coordinate beam at the rate multiplied by cos(α). When the scanning beam pitch in the time intervals τT1and τT2in the sequence of pulses transmitted to the missile coordinate of the beam pitch multiplied by sin(α) and cos(α), respectively.

Thus, in the code sequence of radiation pulses are transmitted to the missile components are the coordinates of the beam ZL·cos(α) and ZL·sin(α) when scanning its course, and the components of YL·cos(α) and YL·sin(α) when the scanning beam pitch in the control field (see figure 5).

In the apparatus of missiles in times of irradiation of the scanned strip is received and decrypted the code sequence of pulses of laser radiation. When exposed strip is scanned across the course, stand out and be remembered for the components of ZL·cos(α) and ZL·sin(α), and the irradiation of the strip is scanned across the pitch stand out and be remembered in the apparatus of the rocket components of the coordinates of the beam YL·cos(α), YL·sin(α).

To compensate for the "twisting" of the coordinate systems in the apparatus rockets 29 (figure 4) is the operation of summing the components of the coordinates of the beam and generates the guidance commands in accordance with the dependencies (1).

In accordance with the tvii with computed command-guided missile with the help of the steering actuator is driven to the line of sight. Therefore, the essence of the proposed method of guided missiles is as follows:

in the formation of two scanned optical beams with a narrow radiation pattern in cross section and modulated by the sequence of short light pulses;

- in the calculation of the carrier current coordinates of the bands rays at the rate and pitch multiplied by sin(α) and cos(α) changing the angle of roll media after launch;

- on the rocket in the sequence of light pulses calculated components of the coordinates of the rays;

in the allocation of rocket components of the coordinates of the beam and the formation of teams aiming for known dependencies (1).

The difference of the proposed method guidance from well-known is the following:

is the separation between instruments media and rockets sequence of operations compensation "twisting" of the measurement coordinate system of the carrier relative to the Executive coordinate system of the rocket;

- in the introduction of new transfer operations on the rocket in the sequence of light pulses of current components of the coordinates of the beam YL·cos(α) and YL·sin(α) when the scanning beam pitch and ZL·cos(α) and ZL·sin(α) at the scan rate and the accumulation operation on the rocket selected components of the coordinates of the rays and vyrabotki the related commands to aim the missile at the target.

Technical implementation of the proposed method guidance provided in the proposed device, the guidance systems of missiles.

As a prototype of the proposed device is the selected device in the missile guidance system, as claimed in the patent of the Russian Federation 2382315, a block diagram is presented in figure 1, where 1 - control, 2 - first pulsed radiation source, 3 - shaper pulse-code, 4 - unit beam forming, 5 - second pulsed radiation source 6 to the first synchronizer 7 is a block scan, 8 - sensor angular position of the rays, 9 - optical zoom optical system, 10-optical reticle, 11 - block lettering, 12 - rocket, 13 - a radiation receiver, 14 - the block Gating signal, a 15 - block Gating pulses, 16 - second synchronizer 17 is a pulse - code analyzer. The problem is solved as follows. In the known guidance systems of missiles, starting with mobile media containing installed in the equipment carrier of the first and second pulsed radiation sources, the block forming two planar orthogonal beams mounted between the radiation source and the scanning unit, kinematically connected with a sensor of angular position, and is connected with the output unit of the scanning optical zoom optical system, Shusterman with an optical sight, consistently soy is yennie block lettering and the pulse shaper code and the first synchronizer, the output of which is connected to the clock inputs of the block lettering and shaper pulse code, the first and second outputs of which are connected with inputs respectively of the first and second sources of pulsed radiation, and also located in the equipment missiles connected in series radiation detector, optically connected with the output end of the optical zoom system, the power Gating signal and the pulse-code analyzer, connected in series, the second synchronizer and block Gating pulses, the output of which is connected with the second input of the Gating signal, and the output of the radiation detector is connected to the second input of the Gating pulses, the output of the second synchronizer is connected to the clock input analyzer pulse code entered in the equipment carrier connected in series sensor roll angle of the carrier and the sine-cosine functional Converter, and the AC works, the first and second inputs of which are connected with the first and second outputs of the sine-cosine functional inverter, a third input connected to the output of the sensor of angular position, and the output is connected to the third input of the shaper pulse code, and hardware missiles entered the first and second summation blocks, the inputs to the pairs that are connected with the corresponding outputs of the pulse-code analyzer. The guidance systems of missiles, starting with mobile media allows you to compensate for the rotation (twist) of the coordinate system of the carrier relative to the coordinate system of the rocket that occur after launch. Moreover, compensation is made without the use of optical prisms, and without the use of information processing on the rocket.

Figure 2 presents a structural diagram of the guidance system of the missile, where the available blocks added: 18 - block works, 19 - sine-cosine functional Converter, 20 - gauge roll angle of the carrier 21 and 22 - the summation blocks.

The proposed device operates as follows. On the carrier 1 in the direction of the target send flat sequentially scanned at the rate and pitch of the laser beams. Luminous flux from the first pulsed radiation source (laser) channel rate 2 beam forming unit 4 is concentrated in a narrow beam that is elongated in the horizontal direction, and the light flux from the second pulsed radiation source (laser) channel pitch 5 unit 4 is concentrated in a narrow beam that is elongated in the horizontal direction. The scanning unit 7 performs a sequential scan of the beams, and the beam, an elongated vertically scans on the course and the beam, an elongated horizontally scans pitch relative what about the center of the raster scan (control field).

Signal light from the scanning unit is supplied to the zoom optical system 9, which continuously during the flight of the rocket produces zoom images of the scanned beam is inversely proportional to the distance to the rocket, thereby providing a permanent band sizes of the beam and control field in the plane of the missile. Rigidly from the optical system associated optical aiming device 10, the aiming mark which coincides with the center of the field of rocket control.

The signal proportional to the rotation angle of the measuring coordinate system, relative to the Executive coordinate system, is produced in the sensor roll angle of the carrier 20 and is served in a sine-cosine functional Converter 19, which are produced by the function cos(α) sin(α) changing the angle of roll media after the launch. To the sync input of the shaper pulse code receives clock pulses from the first synchronizer 6.

Electrical signals from the sensor 8, is proportional to the coordinates of the beam ZLand YLin the control box, proceed to the third input of the block pieces 18, the first and second inputs which serves the function sin(a) and cos(a) changing the angle of roll media.

Shaper pulse code continuously generates code pulse sequence duration τandwhich contain the information about the lettering and the coordinates of the scanned beam, multiplied by sin(α) and cos(α).

View the sequence of pulses generated by the block 7 when the scanning beam on the course, presented in figure 5,a, a scanning pitch sequence presented on figure 5,δ. Lettered intervals τLToτlTperforming encoding information transmitted by the beam directional and pitch, are set to launch the same for instruments missiles and carrier that provides a clear separation of coordinates through appropriate channels. The output of block works when the scanning beam at the rate of produced components of ZL·cos(α) and ZL·sin(α), and when the scanning beam pitch components coordinates UD · cos(α) and YL·sin(α), served on the third input of the shaper pulse code 3.

The signals from the unit works 18 proportional to the coordinates of the beam multiplied by the function sin(α) and cos(α), in the imaging unit 3 are converted into time intervals τK1τK2τK1τT2between literal and coordinate pulses. Is the time-pulse modulation in the time scales τinsignal components of the coordinates of the scanned beam. The code pulse sequence (figure 5,a) scanning the beam in the course of the imaging unit 3 is supplied to the laser 2, Akopova the pulse sequence (figure 5,b) when the scanning beam pitch - the laser 5.

Flat laser beams sequentially scan rate and yaw control field with a time interval τABOUT.When the scan rate of the beam is modulated by a sequence of pulses, which contain information about the lettering and the components of ZL·cos(α) and ZL· sin(α) (figure 5,a), and when the scanning pitch beam is modulated by a sequence of pulses, which incorporated information about lettering and the components of YL· cos(α) and YL·sin(α) (figure 5,b). Raster scanning beams through the work of the zoom lens optical system 9 is constant along the trajectory of the missile and field equal control.

On-Board equipment of the missile 12 in moments of exposure are scanned by the beam receiving laser pulses, converts them to light receiver 13 into electrical signals. The signal from the radiation detector is fed to a second input of the Gating signal 14, to the first input of which receives the signal from the block Gating pulses 15.

The block Gating signal 14 passes signals from the receiver only during the gate pulse. Block the gate pulse 15 runs from the synchronizer 16 at the time of arrival of the reference pulse from the receiver. After the arrival of the reference pulse unit 15 generates the gate pulses through time, p the ate literal interval τ Land then the gate pulses of duration τinover time, equal to the minimum interval τToand τT. To ensure the synchronism generation time interval lettering τLand conditions of time scales τinon the missile and the carrier synchronizers 6 and 16 are made identical.

The signal from block gate 14 is supplied to the second input of the pulse-code analyzer 17, where the selection and memorization at time τABOUTcomponents of the coordinates of the beam Z1=ZL·cos(α), Z2=ZL·sin(α) in the scan period of his course and the components of Y1=YL·cos(α), Y2=YL·sin(α) between the scanning beam pitch. Selected components of ZL·cos(α) and YL·sin(α) are fed to the inputs of the first summation block 21, and the components of YL-cos(α) and ZL-sin(α) are fed to the inputs of the second summation block 22. The outputs of summation blocks are produced, the guidance commands YPand Zpunder the action of which the bodies of steering control lead rocket to the line of sight targets.

The proposed guidance method for an optical beam missiles, starting with the rolling carrier, and a device for its implementation in comparison with the known have high precision missile guidance when the angle of roll media with simultaneous UE is emeniem instruments media and rockets through the following technical solutions:

- with the exception of the equipment carrier of complex optical compensators (prisms, plates, servo drives, and equipment missile complex functional converters, which are used in known devices to compensate for the "twisting" of the coordinate systems;

to ensure high accuracy compensation "twisting" of the coordinate systems by forming components of the coordinates of the scanned beam electronically on the media, the transfer of these components by the beam on the rocket and summarize them in the equipment missiles, i.e. doing rocket simple operation to generate control commands.

The proposed guidance system can be performed as follows. Work package 18 can be performed, for example, the type of integrated analog multiplier products (see "Analog and digital integrated circuits."/ Edited Vakomovskogo, - M: Owls. Radio, 1979, s). Functional Converter 19 may be made on the principle of analog electronic computing machine (see Eightys and Eaaou "Analog-to-digital converters". - M.: Energoizdat, 1981). Sensor roll angle of the carrier can be made on the basis of a static gyro (Upominki, Viewnov, Gospelof, Automation-controlled missiles. - M.: Barongis, 1963, s-171).

Pulsed radiation sources, the block forms the of the rays, the scanning unit, the pulse shaper code, synchronizers, block lettering, block Gating signal, the Gating block pulses, the pulse analyzer code executed in the same manner as in the prototype. The proposed method and device targeting missiles optical beam, their technical implementation of laboratory confirmed and firing trials of anti-tank guided weapons "Whirlwind".

1. Guidance method for an optical beam missiles, starting with the rolling media, including the formation of two beams in a sequence of short light pulses projected into space in the form of strips of constant width, with strips perpendicular to each other, a sequential scan of the rays in space - one course, a different pitch relative to the target orthogonal to the length of the strip, the transfer of the missile position information of rays in space and allocation of equipment missile command guidance, characterized in that the measured change of the roll angle of the carrier of α after launch, determine and transmit a rocket in the sequence of light pulses constituting the Y coordinateL·cos(α) and YL·sin(α) of the beam is scanned across the pitch, and ZL·cos(α) and YL·sin(α) of the beam scanned on the course and in the equipment of the rocket its coordinates ZPand YPdetermine what the dependencies:
ZP=ZL·cos(α)+YL·sin(α),
YP=YL·cos(α)-ZL·sin(α).

2. The guidance system on the optical beam missiles, starting with mobile media containing installed in the equipment carrier of the first and second pulsed radiation sources, the block forming two planar orthogonal beams mounted between the radiation source and the scanning unit, kinematically connected with a sensor of angular position, and is connected with the output unit of the scanning optical zoom optical system, Shusterman with an optical sight, connected in series block lettering and the pulse shaper code, and the first synchronizer, the output of which is connected to the clock inputs of the block lettering and shaper pulse code, the first and second outputs of which are connected with inputs respectively of the first and second sources of pulsed radiation, and also located in the equipment missiles connected in series radiation detector, optically connected with the output end of the optical zoom system, the power Gating signal and the pulse-code analyzer, connected in series, the second synchronizer and block Gating pulses, the output of which is connected with the second input of the Gating signal, and the output of the radiation receiver, Saedinenie the second input of the Gating pulses, the output of the second synchronizer is connected to the clock input of the pulse-code analyzer, characterized in that the introduced hardware media connected in series sensor roll angle of the carrier and the sine-cosine functional Converter, and the AC works, the first and second inputs of which are connected with the first and second outputs of the sine-cosine functional inverter, a third input connected to the output of the sensor of angular position, and the output is connected to the third input of the shaper pulse code, and hardware missiles entered the first and second summation blocks, the inputs of which are paired with the corresponding outputs of the pulse-code analyzer.



 

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SUBSTANCE: invention relates to trainers. Proposed system comprises gunner-operator and commander trainers connected in common circuit. Note here that gunner-operator trainer comprises acoustic communication unit, visual conditions simulator control unit, unit to generate and receive target-hitting indicator and control unit. Commander trainer comprises acoustic communication unit, control unit to cut in visual conditions simulator control unit for gunner-operator, unit to generate and receive target-hitting indicator and unit to control gunner-operator actions. Note here that all outputs of the units to generate and receive target-hitting indicator of all trainers are interconnected to transmit target-hitting indicator into gunner-operator and commander units designed to generate and receive target-hitting indicators for the latter to be displayed ion appropriate visual conditions simulators of trainer. Commander acoustic communication unit has two-way communication with acoustic communication unit of every gunner-operator trainer. Output of the unit that controls visual conditions simulators of commander trainer is connected with inputs of the units that control visual conditions simulators of gunner-operator trainers.

EFFECT: possibility to train groups of gunners-operators.

3 cl, 1 dwg

FIELD: physics.

SUBSTANCE: system can be used in mechanisms for guiding guided missiles to a target using a laser beam. The system includes an input window of the laser modulation device, first pancratic system and first objective lens placed lying on the first axis, second pancratic system, second objective lens and optical compensator lying on the second axis, parallel the first axis. The first reflector is placed at an angle to the first axis in front of the first pancratic system with possibility of coming out of the beam path. The second reflector is placed in front of the second pancratic system parallel the first reflector. In the initial position of the first reflector on the axis of the first pancratic system, mobile components of the second pancratic system move, thereby reducing angle of divergence α of the laser radiation in the near control area to a value αd. When the first reflector moves out of the beam path, mobile components of the first pancratic system move, thereby reducing angle of divergence of laser radiation in the far control area from value αd to a minimal value. Each pancratic system includes at least two mobile components.

EFFECT: reduced length of the pancratic system, prevention of defocusing of the system in the entire movement range of lenses of the pancratic system.

4 cl, 1 dwg

FIELD: physics, optics.

SUBSTANCE: device comprises lens, mesh with transparent diaphragm and check marks on its working surface, which is installed with the possibility of displacement in direction that is perpendicular to lens axis, system for illumination of mesh check marks, the first photodetector device, which is optically connected to mesh, and electronic device for control, processing and generation of measurement information. The following components are introduced and installed on optical axis of lens: spectrum divider, attenuator of laser radiation, the second photodetector device, and also electric drive for mesh displacement, detector of mesh position and video observation device. The first and second inlets of electronic device are connected to the outlets of the first and second photodetector devices, the third inlet - to detector of mesh position, the fourth inlet has possibility of connection to outlet, and the first outlet - to the inlet of laser control channel of controlled device, the second outlet - to electric drive of mesh displacement, and the third outlet - to video observation device.

EFFECT: expansion of functional resources by provision of control over time cyclogram of laser control channel operation and power of laser radiation, improved efficiency and accuracy of control by automation of performed operations and processing of measurement results.

2 dwg

FIELD: FOR TELEORIENTATION OF GUIDED OBJECTIVES, OPTICAL SIGHT OF GUIDED MISSILE GUIDANCE SYSTEM AND PULSE SHAPER.

FIELD: remote control of flight vehicles.

SUBSTANCE: the invention consists in bringing the searchlight emission in the sighting channel, formation of elision only at the moments when the time intervals between the pulses are equal to the reference values, visualization of the emission that has passed through the sighting channel. Besides, defection of the emission that has passed through the sighting channel. Besides, deflection of the searchlight optical flux in two mutually perpendicular directions is accomplished, which provides for alignment of the sight optical axis and the searchlight information axis. A rotary prism is introduced in the guidance optical sight, and the sighting channel is made on the basis of a TV camera, monitor, sighting mark forming unit, and a sighting mark position control panel. Two AMD circuits and a series-connected decoder and an OR circuit with respective couplings are introduced in the pulse shaper.

EFFECT: enhanced accuracy of guidance of the controlled objective.

4 cl, 4 dwg, 1 ex

FIELD: the invention refers to optics-electron arrangements designed for detection the sources of optical radiation and diagnostics the optical characteristics of these sources.

SUBSTANCE: the proposed arrangements have a panoramic mirror objective with a numerical aperture more then 0,5, an angular field of vision 3600 along the horizon and no less then -50 +250 along the vertical line, negative distortion no less then 50%, a photo receiving arrangement, a signals analysis block which is fulfilled with possibility to execute measuring of amplitudes, duration and periods of signals radiated by sources of optical radiation. The technical result is in simplification of the optical tract, in increasing the working spectral range, in increasing sensitiveness, in providing possibility to gain information about optical sources of radiation in the angular field of vision 3600 along the horizon and no less(-5 +25)0 along the vertical line, in providing possibility of gaining temporary information from the channels.

EFFECT: provides diagnostics of spectral characteristics of the sources of optical radiation.

2 cl, 5 dwg

FIELD: optical guidance systems of guided missiles, applicable in guided weapon systems with teleorientation in laser beam.

SUBSTANCE: the guided missile guidance system has a missile starting system and an optical sight including a target sighting channel and a guidance channel containing series-connected laser radiation source, modulator and an optical system with a variable focal length, whose input is connected to the output of the optical system control circuit, in addition use is made of a control bus-bar, and a OR gate, AND gate, NAND gate are introduced in the optical sight. The first input of the control bus-bar is connected to the input of the NAND gate, whose output is connected to the first input of the AND gate, whose second input is connected to the output of the OR gate, whose first input is connected to the output of the missile starting system, and the second input - to the second input of the control bus-bar, and the output of the AND gate is connected to the input of the optical system control circuit.

EFFECT: enhanced quality of control of the guidance system characteristics in service.

2 dwg

FIELD: development of missile guidance systems, applicable in anti-tank and aircraft missile complexes.

SUBSTANCE: the known method for guidance consists in formation of modulated laser radiation with variation of the beam angular dimension according to a program, shooting of the missile in the beam, reception by the missile control equipment of radiation and transformation of it to an electric signal of control of the control surfaces, additional operations are introduced: after a definite time interval the second missile is shot in the beam, and the program of variation of the beam angular dimension is started at the instant of launch of the second missile, the time interval between the launches of missiles is determined from the condition determined by the preset mathematical expression. The guidance system realizing this method differs from the known one, which has a sight consisting of series-connected source of modulated laser radiation and optical system with a variable focal distance, missile launching system, the sight is made for connection by optical communication to the first input of the control equipment of the first missile, the output of the missile launching system is connected to the second input of the control equipment of the first missile by the fact that it is provided with a delay unit, whose input is connected to the output of the missile launching system, and the output is connected to the second input of the control system of the second guided missile and to the second input of the optical system with a variable focal distance. The sight is made for connection by optical communication to the first input of the control equipment of the second missile.

EFFECT: provided simultaneous guidance of two missiles in one beam, which enhancer the efficiency of the complexes at destruction of an extra-important target.

3 cl, 1 dwg

FIELD: optical systems of guided missile guidance systems, applicable in weapons control systems with teleorientation in the laser beam.

SUBSTANCE: the optical sight of the guided missile guidance system has an aligned sight and a searchlight including two injection lasers, whose radiating areas are located perpendicularly to the axes of the measured coordinates, radiation output system of the lasers to a single optical axis, an optical scanner in the form of a rotating prism and a pancreatic objective successively installed on this axis, the prism axis of rotation is matched with the objective optical axis, as well as a an opaque shutter installed on the mount of the rotating prism, two optron sensors fixed in parallel with one of the measured coordinates. In the plane perpendicular to the optical axis of the searchlight, the angle between the line connecting each sensor with the axis of rotation of the prism makes up 90 deg, the outputs of the first and second optron sensors are connected respectively to the inputs of the first and second delay circuits, whose outputs are connected respectively to the first and second inputs of the pulse shaper. Introduced are the temperature-sensitive element, first and second voltage switches, the first control inputs of the first and second voltage switches are connected respectively to the first and second outputs of the pulse shaper, and the second inputs - respectively to the outputs of the first and second controlled voltage sources, whose control inputs are connected to the output of the temperature - sensitive element, and the outputs of the first and second voltage switches are connected respectively to the inputs of the first and second lasers.

EFFECT: enhanced reliability of sight operation due to stabilized power of lasers within the whole range operating temperatures.

4 dwg

FIELD: means of monitoring of sights-guidance instruments (sights) of controlled armament, designed for production of an optical beam of flight vehicle control and using lasers as a source of radiation, in particular, sights of the teleorientation system with radiating channels on injection lasers.

SUBSTANCE: the method includes the registration of the signal, separation of coordinates and estimation of the signal parameters. Formed in addition is a pilot beam by picking from the full section of the laser beam formed by the sight of the teleorientation system of a normalized portion of power with a preset value K of this portion. The pilot beam signal is registered, the information parameters of the pilot beam signal are estimated as identical to the parameters of the pilot beam signal, and the control beam power is estimated as a ratio of the measured value of the pilot beam signal power to the K value. The method is realized in the device including light filters, a photodetector and an electronic unit for measuring the signal parameters connected to its output. In addition the device uses an optical adapter containing a base member with an inlet hole, first and second outlet holes, plane-parallel plate made of optical material possessing properties of passage and reflection of laser radiation and overlapping the first outlet hole, and a holder for installation of light filters, positioned between the plano-parallel plate and the second outlet hole. The base member in the area of the inlet and second holes is equipped by mounting places for installation of the optical adapter on the sight and attachment of the photodetector to it, providing for intersection of the optical axes of the objectives of the sight information channel and photodetector on the surface of the plano-parallel plate located perpendicularly to the plane formed by these axes, and forming equal in value angles with each of them.

EFFECT: provided monitoring of the control beam signal parameters in the process of control by the flight vehicle.

3 cl, 1 dwg

FIELD: weapons.

SUBSTANCE: optical sight comprises axially aligned sight and light source that is made of two injection lasers whose emitting zones are perpendicular to the co-ordinates to be measured, system for adjusting the laser beams to single optical axis, and scanner made of rotating prism and objective lens mounted at the optical axis in series. The axis of rotation of the prism is in coincident with the optical axis of the objective lens. The nontransparent shield is mounted on the mandrel of the rotating prism. Two optronic pickups are immovably mounted parallel to the coordinate to be measured. In the plane perpendicular to the optical axis of the light source, the angle between the lines that connect pickups with the axis of rotation of the prism is 90º. The outputs of the first and second optronic pickups are connected, respectively, with the inputs of the first and second delay circuit whose outputs are connected, respectively, to the first and second inputs of the OR circuit and first and second inputs of the permanent memory. The output of the OR circuit is connected with the first inputs of the timer and channel commutator. The output of the timer is connected with the third input of the permanent memory whose second input is connected with the output of the generator and second input of the timer. The output of the code-time converter is connected with the second input of the channel commutator whose outputs are connected, respectively, to the inputs of the first and second lasers. The sight is provided with the windage calculator, pickup system, and multiplexer. First and second recorders whose outputs are connected with the first and second inputs of the multiplexer whose third input is connected with the output of the OR circuit and output is connected with the fourth input of the permanent memory. The inputs of the first and second recorders are connected with the first and second outputs of the windage calculator whose inputs are connected with the pickup system.

EFFECT: enhanced accuracy of sighting.

3 dwg

FIELD: weapons.

SUBSTANCE: optical sight comprises axially aligned sight and light source that is made of two injection lasers whose emitting zones are perpendicular to the axes of co-ordinates to be measured, system for adjusting the laser beams to single optical axis, and scanner made of rotating prism and objective lens mounted at the optical axis in series. The axis of rotation of the prism is in coincident with the optical axis of the objective lens. The nontransparent shield is mounted on the mandrel of the rotating prism. Two optronic pickups are immovably mounted parallel to the coordinate to be measured. In the plane perpendicular to the optical axis of the light source, the angle between the lines that connect pickups with the axis of rotation of the prism is 90º. The outputs of the first and second optronic pickups are connected, respectively, with the inputs of the first and second delay circuit whose outputs are connected, respectively, to the first and second inputs of the OR circuit and first and second inputs of the permanent memory. The output of the OR circuit is connected with the first inputs of the timer and channel commutator. The output of the timer is connected with the third input of the permanent memory whose second input is connected with the output of the reference generator and second input of the timer. The output of the code-time converter is connected with the second input of the channel commutator whose outputs are connected, respectively, to the inputs of the first and second lasers. The sight is provided with the counter of scanning cycles whose output is connected with the forth input of the permanent memory. The counting input is connected with the output of the second dely circuit.

EFFECT: enhanced precision of sighting.

4 dwg

FIELD: optical and radar devices.

SUBSTANCE: laser-location station can be used at high-precision radar assemblies for guiding laser radiation onto movable air and space objects to determine parameters (coordinates) of motion of remote objects. Laser-location station has optical radio-engineering transceiver unit placed onto support-rotating device. The unit has optical transmitting-receiving aerial, optical receiving aerial, transmitting-receiving radio aerial, Drive for α axis and α axis coordinate detector are mounted onto α axis of support-rotating unit. Drive for β axis and β axis coordinate detector are mounted onto β axis of support-rotating unit. Laser transmitter, optical signal receiver, diagram-forming circuit, laser transmitter power and control unit, received optical signal primary processing unit, transmitting unit set, receiving units set, radio- and optical receiving-transmitting channel control unit, rotating contact device, control-adjusting aerial, receiving-transmitting control unit, received optical signal secondary processing unit, station control unit, operator interface unit, station information representation unit, outer consumer data transmission system, outer target designator interface unit, units for controlling drives along α and β axes and secondary electric supply unit are mounted onto rotary-supporting unit. Station is used for detecting, capturing and escorting targets as well as for laser location of moving target to provide high precision of measurement of coordinates of different flying and moving targets and to reduce time for preliminary target designation for laser channel.

EFFECT: improved efficiency of operation.

4 cl, 9 dwg

FIELD: projectile guidance systems, in particular, by laser beam.

SUBSTANCE: the transmitting channel of the guidance device is made in the form of a double-mode pulsed-periodic laser. The laser operates in the mode of free oscillation for beam guidance and in the monopulse mode for laser target indication and range finding. A polarized box is introduced between the optical system with a variable focus distance and the excess mechanism.

EFFECT: enhanced noise immunity of the projectile due to an independent use of the channels of beam guidance and laser target indication.

2 cl, 2 dwg

FIELD: control of moving objects with tele-orientation in the laser beam.

SUBSTANCE: the system has a laser, optoelectronic scanning system, output optical system and a control unit of deflectors. The control unit of deflectors has a formation unit of sync signals and raster parameters, driver of raster codes, driver of shift codes, adder and a double-channel frequency synthesizer. Raster codes Zs and Yt from the outputs of the raster code driver and shift code Kφ from the output of the shift code driver are fed the inputs of the adder connected to the inputs of the double-channel frequency synthesizer, codes Zs=Zt, Ys=Yt+Kφ or Zs=Zt+Kφ, Ys=Yt or Zt+Kφ, Ys=Yt+Kφ are formed. The control inputs of the shift code driver are connected to the control outputs of the formation unit of sync signals and raster parameters and the driver of raster-codes. The laser system of tele-orientation is made for input of the "DESCENT" command to the input of the formation unit of sync signals and raster parameters.

EFFECT: enhanced noise immunity of the system and enhanced methods of control of objects.

2 cl, 5 dwg

FIELD: guided missile optical guidance systems, applicable in guided weapon systems with teleorientation in a laser beam.

SUBSTANCE: the optical sight of the guided missile guidance system has a coaxially installed sight and a projector including two injection lasers, whose emitting areas are positioned perpendicularly to the axes of the measured co-ordinates, system of laser emission ejection to a single optical axis, an optical scanner in the form of a rotating prism and a zoom lens installed in succession in this axis. The axis of prism rotation is matched with the lens optical axis. The sight has also a nontransparent shutter installed on the cell of the rotating prism, two optronic sensors fixed in parallel with one of the measured co-ordinates in the plane perpendicular to the projector optical axis, the angle between the lines connecting each sensor to the axis of rotation of the prism makes up 90 deg. The outputs of the first and second optronic sensors are connected respectively to the inputs of the first and second delay circuits, whose outputs are connected respectively to the first and second inputs of the exclusive OR circuit, as well as to the first and second inputs of the permanent storage, the output of the exclusive OR circuit is connected to the first inputs of the time counter of the channel switch. The output of the time counter is connected to the third input of the permanent storage, whose output is connected to the first input of the code-to-time converter, whose second input is connected to the output of the frequency standard and the second input of the time counter. The output of the code-to-time converter is connected to the second input of the channels switch, whose outputs are connected respectively to the inputs of the first and second lasers, use is made of the first and second pulse counters, whose first clock inputs are connected to the output of the frequency standard, the carry output of the first pulse counter is connected to the clearance input of the second pulse counter, whose information outputs are connected to the fourth input of the permanent storage.

EFFECT: enhanced range of guidance of the guided missile.

3 dwg

FIELD: optoelectronic engineering, in particular, devices for focusing, optical filtration and conversion of received optical radiation to an electric signal.

SUBSTANCE: the optical system additionally has an edge filter of infra-red and ultra-violet radiation bands with a shutter and photodetector. The elements of the catadioptic lens are positioned on the gyroscope. The shutter is made of a disk of heat-resistant, nontransparent, nonmagnetic material with cut-outs of larger dimensions of the edge filters and positioned in the open position opposite them. The edge filter is made of a disk of heat-resistant, nontransparent, nonmagnetic material with inserts of materials conducting radiation in spectral regions within 0.019 to 0.022 μm and 2 to 3 μm located in an L-shaped manner. The wide-band photodetector represents an open-type photodiode with a sensitivity in the spectral region within 0.015 to 4 μm.

EFFECT: enhanced accuracy of processing of the optical signal at ranges to the target of less than 7000 m due to enhanced resolution of signal reception in the ultra-violet band.

4 dwg

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