Method of tracking aerial target and telescopic sight having tracking range finder for implementing said method

FIELD: physics, optics.

SUBSTANCE: invention relates to telescopic sights of guidance systems of controlled objects and can be used in air defence fire control systems. The method comprises detecting an aerial target; selecting angular aiming speed of an electro-optical module (EOM) by superimposing the cross on a monitor screen with the target; turning the EOM into an automatic target tracking mode by inputting an image of the target into a tracking gate and issuing a Capture command; measuring the current range to the target by emitting laser radiation towards the target and receiving the radiation reflected from the target; controlling the spatial position of the laser radiation towards the target by issuing control commands, which correspond to angular coordinates of the target, to a two-dimensional acoustooptical deflector; converting the digital code of the range into a video signal; display thereof on a monitor in the form of a digital inscription; determining angular velocities of the aerial target and the drive of the EOM; determining the value and direction of the necessary changes of the angular velocities of the drive of the EOM by comparing angular velocities of the target and the drive of the EOM; issuing a recommendation to the pointer of a portable system on the required value and direction of changing angular velocity of the drive of the EOM.

EFFECT: high reliability of tracking high-speed and manoeuvring targets.

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The invention relates to optical sights guidance systems of managed objects and can be used in fire control systems for air defense.

A method of track air targets, which consists in combining the gunner reticle (crosshairs) of the reticle channel optical sight with the objective and the measurement range of the distance-measuring channel (RF patent No. 2224206, from 22.07.2002 G., IPC:7 F41G 7/26).

Known optical sight, which in its composition contains two channels - sighting and distance measuring. Target channel comprises a television or thermal imaging systems (TS), consisting of the appropriate probe (HP) and monitor to monitor the situation of the flight. The use in the composition of the sight of the CU provides compatibility of sight with automatic target tracking (patent RF № 2224206, from 22.07.2002 G., IPC:7 F41G 7/26).

The disadvantages of this method and the optical sight is to increase the angular pointing errors of the aiming mark a target channel at a target in the implementation guidance for maneuvering target, which does not allow to perform measurements of the target range.

For example, for anti-aircraft self-propelled vehicles Gepard (Germany) pointing errors when shooting make 3-4 mrad. For combat vehicles complexes "Tunguska", where we have introduced more complex algoritmizirovannoe signals drive control this error depends on the skill of the gunner and is in semi-skilled gunner of 0.4-0.6 and 0.2 mrad to 0.3 mrad at high qualification (patent RF № 2217681, from 19.07.2001 G., IPC: 7F41G 7/20).

In some modern scopes of control systems with cameras sighting channel used machines target tracking (ASC), in which, after the detection of a target by a gunner on the monitor on the target is superimposed on the strobe and ASN automatically according to a given algorithm accompanies the goal gate and produces signals of the error - target coordinates relative to the line of sight (V. V. Molebny. Optical radar system. M.: Mashinostroenie, 1981, Chapter 4).

The output signals of the ASC are fed to the actuators of the optical sight which expand scope to reduce the error signals, and thus the automatic tracking of the target.

Such automated systems tracking also have angular tracking error that is associated with an angular error of actuator while tracking the targets, especially in terms of tracking moving maneuvering target and when in motion. The magnitude of this error, depending on the design of the scope and conditions of use, may be 0.3 to 1.5 mrad.

To increase the range of the measurement target, the rangefinder needs to have a small arc�most importantly, the divergence of a laser beam. A number of modern rangefinders is the angular divergence of the laser radiation is about 0.6 mrad.

Therefore, in some cases, error tracking of the target exceeds the angular divergence of a laser beam rangefinders and measuring current range to the target in real time is impossible.

Closest to the invention is a method of air support the goal of detection of air targets by gunner portable complex, the choice of the angular velocity homing opto-electronic module (OEM) by aligning the crosshairs on the monitor screen for the purpose, the translation of the poem in the mode of automatic tracking of the target by entering the target inside the gate tracking and issue the command "Capture", the current measurement of distance to a target by emitting laser radiation in the direction of the target and receive reflected radiation from the target, ensure the control of the spatial position of the laser beam in the direction of the target by issuing control commands, the corresponding angular coordinates of the target on a two-coordinate acousto-optic deflector, the conversion of the digital code range in the video signal, the display on the monitor in the form of digital labels (patent RF № 2410629, on 27.01.2010 G., IPC F41G 7/26 (2006.01), G01C 3/08 (2006.01).

Closest to the invention is an optical sight, containing the opto-electric�the electronic module (OEM), in which is placed optically conjugate probe and a target channel and a ranging channel. Ranging channel is composed of a transmission device, comprising serially connected to the laser emitter and the output optical system, and a receiving device, comprising series-connected receiving optical system, the photodetector device and the transmitter of the target range. And optical sight includes an actuator guidance and stabilization, the power conversion control signals, automatic target tracking, sensor control commands for actuators and ASN and monitor. Moreover, the output of the probe and a target channel connected to the first input of the automatic target tracking, a second input connected to the output of the transmitter of the target range, the video output of the video probe sighting channel is connected to the input of the monitor and the digital output signals of the angular tracking errors for the purpose connected to the first input of the conversion unit of the control signals, the output of which is connected to the inputs of the actuator pointing and stabilization, the outputs of which are mechanically connected to the opto-electronic module. The outputs of the sensors control actuators and ASN is connected to the second input of the conversion unit of the control signals, the third control input of the automatic target tracking and the control input of the laser radiation�'el ranging channel.

Thus in the composition of the optical sight is entered serially connected to the scaling unit and the control unit of an acousto-optical deflector, comprising serially connected to the temperature compensation unit, the adder, two-channel frequency synthesizer, and a two-coordinate acousto-optic deflector, mounted optically coupled between the laser emitter and the output optical system of the transmission device of the distance-measuring channel, wherein the input of the two-coordinate acousto-optic deflector is connected to the output of the laser emitter, and the output of a two-coordinate acousto-optic deflector is connected to the input of the output optical system. The digital output signals of the angular errors of the automatic target tracking is connected to the input of the scaling unit. The outputs of the control unit of the deflector are connected to the inputs of a two-coordinate acousto-optic deflector. Moreover, the diameter d of the sensitive pad of the photodiode photodetector devices ranging channel satisfies the condition: d>2F·fmwhere F is the focal length of a reception optical system of the distance-measuring channel; fm- maximum angular tracking error objective optical sight (patent RF № 2410629, on 27.01.2010 G., IPC F41G 7/26 (2006.01), G01C 3/08 (2006.01).

A disadvantage of the optical sight is the low reliability of soprano�Denia high-speed maneuvering target due to the lack of information for the gunner portable complex of the required magnitude and direction of change (decrease or increase) the angular velocity of the actuator optoelectronic module.

The technical result of the invention is to improve the reliability of maintenance shafts and maneuvering targets due to the issuance of recommendations to the gunner portable complex of the required magnitude and direction of variation of the angular speed of the drive opto-electronic module.

The technical result is achieved in the way of air support the goal of detection of air targets, the choice of the angular velocity homing opto-electronic module (OEM) by aligning the crosshairs on the monitor screen for the purpose, the translation of the poem in the mode of automatic tracking of the target by entering the target inside the gate tracking and issue the command "Capture", the current measurement of distance to a target by emitting laser radiation in the direction of the target and receive reflected radiation from the target, ensure the control of the spatial position of the laser beam in the direction of the target by issuing control commands corresponding to the angular coordinates of the target, on a two-coordinate acousto-optic deflector, the conversion of the digital code range in the video signal, the display on the monitor in the form of digital labels, additionallydetermine the angular speed air targets and drive poem, determine the magnitude and direction�the necessary changes in the angular velocities of the drive poem by comparing the angular velocities of the target and drive poem, present recommendations to the gunner portable complex of the required magnitude and direction of change of the angular velocity of the movement of the actuator poem.

The method is implemented in the optical sight, containing the opto-electronic module (OEM), which houses the probe and a target channel and a ranging channel is composed of a transmission device, which includes United laser emitter and an output optical system, and a receiving device, comprising series-connected receiving optical system, the photodetector device and the transmitter of the target range, and the actuator pointing and stabilization, the power conversion control signals, automatic target tracking, sensor control commands to the actuators and monitor, and output video probe sighting channel connected to the first input of the automatic target tracking, a second input connected to the output of the transmitter of the target range, the video output of the automatic target tracking is connected to the input of the monitor and the digital output signals of the angular errors of the automatic target tracking is connected to the first input of the conversion unit of the control signals, the output of which is connected to the inputs of the actuator pointing and stabilization, the outputs of which are mechanically connected to the opto-electronic module, the outputs of the sensors control actuators connected to each of toringdon block conversion of control signals, the third control input of the automatic target tracking and the control input of the laser transmitter distance measuring channel, serially connected to the scaling unit, the electronic control of an acousto-optical deflector, comprising serially connected to the temperature compensation unit, the adder, two-channel frequency synthesizer, and a two-coordinate acousto-optic deflector mounted between the laser emitter and the output optical system of the transmission device of the distance-measuring channel, wherein the input of the two-coordinate acousto-optic deflector is connected to the output of the laser emitter, and the output of a two-coordinate acousto-optic deflector is connected to the input of the output optical system, the digital output signals of the angular errors of the automatic target tracking is connected to the input of the scaling unit, the outputs of the electronic control unit of an acousto-optical deflector are connected to the inputs of a two-coordinate acousto-optic deflector, and the diameter d of the sensitive pad of the photodiode photodetector devices ranging channel satisfies the condition d>2F·fmwhere F is the focal length of a reception optical system of the distance-measuring channel; fm- maximum angular tracking error objective optical sight, additionallyentered block analyseplugin the velocity of the target, the first and second inputs of which are connected respectively with the first output of the sensor control commands to the actuators and the first output of the automatic target tracking, and first, second and third outputs are connected with the second, third and fourth inputs of the monitor, the unit of analysis is the angular velocity of the target unit consists of determining the angular speed of rotation of the actuator and the block determining the angular velocity of the target, subtractive device, the first and second diodes, the first and second inputs of the unit of analysis is the angular velocity of the target are respectively the inputs of the block determine the angular velocity of the actuator and the block determining the angular speed of target movement, the outputs are connected respectively with the first and second inputs of subtractive device, the output of which is connected to the inputs of the first and second diodes, the output of subtractive device, the outputs of the first and second diodes are respectively first, second and third outputs of the unit of analysis is the angular velocity of the target, the unit determining the angular velocity of the actuator (goals) consists of first and second n elements, the first and n second threshold devices, the setpoint signals, subtractive device, a differentiating circuit, the first and second elements OR, shift register, signal generator, n elemento� And, n counters n keys, the divider, and the input unit of determining the angular velocity of the target, is the first inputs of the first and n second threshold devices, the second inputs of which are connected respectively with the first and n second outputs setpoint signal, the output of the first threshold device is connected to the input of the first element, the input of the differentiating circuit and the first input of subtractive device, the outputs of the n second threshold devices are connected to the inputs of the first element OR the output of which is connected to a first input shift register and a second input of subtractive device, the output of the differentiating circuit is connected with the second inputs of the shift register and n counters the output of the pulse generator is connected to third inputs of the shift register and n elements, And the output of the first element is NOT connected with the first inputs of n elements And the outputs of the shift register after n second elements connected with the second inputs of n elements And whose outputs are connected to first inputs of counters, whose outputs are connected with inputs of the second element OR the output of which is connected to a first input of the divider, the second inputs of which are connected to the outputs of n keys, the first and second inputs which are connected respectively with the output of subtractive device and outputs shift register, the output of the divider is the output of the block about�for determining the angular velocity of the actuator (goals).

Fig.1 shows a block diagram of an optical sight with a tracking rangefinder, where 1 opto-electronic module (OEM), 2 - probe and a target channel, 3 - distance-measuring channel 4 - transmitter 5 to the receiver unit, 6 - actuator guidance and stabilization of the poem, 7 - unit conversion of control signals, 8 - automatic target tracking (ASC), 9 - sensors control actuators, 10 - monitor, 11 - block scale, 12 - electronic control unit of an acousto-optical deflector, a 13 - block analysis, the angular velocity of target movement, 14 - dual channel frequency synthesizer 15, and the adder, 16 - unit temperature compensation, 17 - laser emitter 18 - two-coordinate acousto-optic deflector, 19 - output optical system 20 to the transmitter of the target range, 21 - photodetector, 22 - reception optical system 23 - gunner.

Fig.2 shows a block diagram of the analysis unit 13 to the angular velocity of target movement, where the 24 - unit determining the angular speed of rotation, the 25 - unit determining the angular velocity of the target, 26-subtractive device, the 27 - first and 28 second diodes, in addition, shows the structural diagram of the block 24 determining the angular speed of the gear 29 of the first and 30 second n elements, 31 in the first and 32 - n second threshold devices, the 33 - preselection signals, 34-subtractive device, the 35 - differential�th circuit, 36 - 37 of the first and second elements OR, the 38 - shift register, a 39 - signal generator, 40 - n elements And, 41 - n counters, 42 - n the keys 43 - divisor.

Optical sight with a tracking rangefinder contains opto-electronic module (OEM) 1, which is placed optically conjugate to the image of the reticle 2 channel and range channel 3 comprising a transmitting device 4 and receiving device 5, the actuator 6 of the guidance and stabilization of the poem, the block 7 signal conversion control, automatic 8 target tracking (ASC), sensors 9 control commands (MFIs) drives, monitor (monitor device) 10, block 11 zoom (BM), block 12 electronic control acousto-optic deflector, block 13 determine the angular velocity of target movement.

Transmitting the distance measuring device 4 of the channel 3 consists of series-connected laser emitter 17, a two-coordinate acousto-optic deflector 18 and the output optical system 19.

The receiving device 5 of the distance-measuring channel 3 consists of series-connected reception optical system 22, a receiving device 21 and the transmitter of the target range of 20.

The electronic control acousto-optic deflector 12, consists of a two-channel frequency synthesizer 14, the adder 15 and the temperature compensation unit 16.

The analysis unit 13 to the angular velocity of target movement �will win the block 24 determining the angular velocity of the actuator 25 determining the angular speed of target movement, subtractive device 26, the first 27 and second 28 diodes, wherein the blocks 24 (25) determining the angular velocity of the actuator and objectives consist of the first 29, n 30 second elements, the first 31 and n-32 second threshold devices, the Adjuster 33 signals, subtractive device 34, a differentiating circuit 35, the first 36 and second 37 elements OR shift register 38, the generator 39 signals, n elements And 40, n counters 41, n keys 42, a divider 43.

The analysis unit 13 to the angular velocity of target movement allows the gunner to perform a reliable support maneuverable targets due to the issuance of the additional information about the magnitude and direction (increase or decrease) of the error in angular velocity between the target and drives.

The telescope operates as follows.

Gunner 23, finding a target image on the screen 10 by moving knuppel drive control DKU 9, sets the speed of aiming a poem by angular coordinates and, by controlling the actuators AMS 1, tries to combine the crosshair on the screen of the monitor 10 for the purpose (Fig.1). On the screen there is a picture of the gate to engage a target, which in the initial state, without auto-tracking purposes, periodically changes the brightness. When entering the target inside the gate tracking the gunner presses the "Capture" DKU 9 sight and enters the automatic tracking TSE�new York, trying to combine the crosshairs (line of sight) for the purpose. In auto-tracking mode, the image of the gate lock on the monitor screen brightness does not change.

The purpose is inside the strobe, but because of the mistakes she drives is offset relative to the aiming line at a certain angle. Digital codes of the angular coordinates of the target from the ASC receives at a first input of the conversion unit of the control signals 7 and is input to the BM 11. Unit conversion control signals 7 converts them into signals to control commands the actuator guidance and stabilization of the OM 6, thereby ensuring retention targets inside the gate lock.

When the sight is in the automatic target tracking can be used to measure the current target range. The gunner presses the button "Current range" DKU 9, wherein the laser emitter 17 of the transmission device 4 of the distance-measuring channel 3 generates laser pulses with a predetermined repetition frequency. Digital codes of the signals of the angular coordinates of the target from the ASC received on the input of the scaling unit 11, converts the latter, taking into account the required for the operation of the transform coefficients, the digital control codes baffles and fed to the inputs of the motor controls the deflectors 12. Therein digital input control codes baffles of preobrazuetsya high frequency control signals (f zand fyserved on a two-coordinate acousto-optic deflector 18 of the transmission device 4 of the distance-measuring channel 3, causing angular displacement of the laser beam by an amount proportional to the measured angular coordinates of the target. Thus, despite the angular displacement of the target relative to the optical axis of the sight, the laser beam transmission device 4 of the distance-measuring channel 3 is aimed at the target.

Reflected from the target, the laser radiation passes through the entrance pupil reception optical system 22 receptor 5 distance-measuring channel 3 and focused onto the photodiode of a receiving device 21, causing the appearance at its output an electrical pulse, delayed relative to the emitted laser pulse in time proportional to the target range.

The transmitter of the target range 20 receptor 5 rangefinder channel 3 measures this time interval and generates a digital code range that ASC can be converted into a video signal and displayed on the monitor 10 in the form of digital inscriptions (Fig.1). Digital code range may be supplied to the transmitter of the fire control system for appropriate action.

The scaling block 11 provides an interface measured angular coordinates of the target and values of digital codes control baffles, to provide�Ekiti the equality of the angular displacement of the laser radiation ranging channel and the magnitude of the measured angular coordinates of the target. Let the value of the vector of the angular coordinates of the target relative to the crosshair, measured ASC equal toφC. Its projections on the coordinate axes x and y in TC is equal to fxand fI.

The module of the vector of the angular coordinates of the target can be written in the form:

ϕC=h0F0,where h0the amount of displacement of the target in the focal plane of the input lens of the probe and a target channel having a focal length Fo. Otherwise, linking the magnitude of the angular displacement of the target in the focal plane of the input lens of the probe and a target channel and the value of the digital code of the angular coordinates of the target at the output of the ASC, we can write: fC·K0=DC, where K0- coefficient of proportionality ASC, DC- a numeric code for the target position that is offset at an angle of fCrelative to the aiming line.

Code DCis formed at the output of the ASC and therefore it is equal toDC=h0F0K0 .

The electronic control acousto-optic deflector 12 in the simplest case consists of a two-channel frequency synthesizer 14. When performing a two-coordinate acousto-optic deflector 18 from a single crystal paratellurite the scan angle of the deflector may be 3 degrees when changing the high frequency control signals (fzand fyin the frequency range of 64 to 96 MHz. Center frequency frequency equal to 80 MHz. At this frequency the direction of the laser beam at the output of the distance-measuring channel 3 collinear to the optical axis of the sight. The switching time of the laser beam deflector from one angular position to another arbitrary is not more than 20 microseconds.

The electronic control acousto-optic deflector 12 may be implemented, for example, two digital chip frequency synthesizer AD9851. When using 13-bit control input for each channel synthesizer deflector provides angular deflection of the laser beam at its output equal to 1.35 seconds of arc per unit control commands are applied to the input of the control unit.

The angle of deflection γdlaser beam at the output of the transmitter 4 of the distance-measuring channel 3 can be represented by the expression:γD=ToDDandGp,where Kd - joint proportionality factor for the frequency synthesizer and the acousto-optic deflector; Gpis the angular magnification of the output optical system 18; Da- the value of the control code fed to the input of the frequency synthesizer.

In the present invention the angular magnification of the output optical system may amount to 1/2 to 1/8, depending on the tasks. To ensure equal angular displacement of the laser radiation ranging channel and the magnitude of the measured angular coordinates of the target, i.e., fC=γDthe transfer ratio of the scaling unit 11 is defined as: KBM=Da/DC= 1/(KdKoGp).

The dependence of the deflection angleγDlaser beam at the output of the transmitter 4 of the distance-measuring channel 3 more fully, taking into account the working temperature Ttthe optical sight can be represented by the expression:

γD=ToDDandGP+ Kt·ΔT·Gn

where Kt- temperature coefficient equal to approximately 10-3;

ΔT =(Tt-25°C).

When the sight in a wide temperature range, especially with a very narrow laser beam of the distance-measuring channel is taken into account the effect of temperature.

The electronic control acousto-d�lektorem 12 consists in this case of two-channel frequency synthesizer 14, the adder 15 and the temperature compensation unit 16. The temperature compensation unit 16 generates the output digital signal DT=- Kt·ΔT·Gp. After the addition in the adder 15 from Dtand Dathe effect of temperature on the scan angle is eliminated. The function is a summation codes and signal DTeasily implemented on the basis of modern microprocessor and temperature sensors, for example AD22100 ST.

The diameter d of the sensitive pad of the photodiode photoreceiver distance-measuring channel must match the value of d > 2F·fmwhere F is the focal length of a reception optical system of the distance-measuring channel, fm- maximum angular tracking error objective riflescope. This is necessary for the reception of the reflected from the target laser pulses at an angular displacement of the target relative to the optical axis of the sight. The diameter of the photodiode for the conditions: F=200 mm, fm=5 arcmin. min is equal to 0.58 mm, commercially available photodiodes designed for the reception of short laser pulses, for example HAMAMATSU, have a range of diameters of photosensitive sites, including 0.5 and 1.0 mm.

The analysis unit 13 to the angular velocity of the target allows on the basis of a comparison of the angular velocity of the actuator and the angular velocity of target movement, in addition to give information�Yu gunner about the value and direction of the required angular velocity of the movement of the actuator to prevent failure of the support and high-speed maneuvering target (Fig.1).

Consider determining the angular velocity of the actuator (the angular speed of the target is determined in the same way).

From the output of the sensors 9 teams drive control signal proportional to angular position of the actuator, is fed to the input unit 24 determining the angular velocity of the actuator, respectively, to first inputs of the first 31 and n-32 second threshold devices, the second inputs of which receives signals respectively from the first and n second outputs of the Adjuster 33 signals (Fig.2).

In the process of tracking, at the moment of exceeding the signal corresponding to the current angular position of the actuator 6 above the first threshold value supplied from the first output of the Adjuster 33, the output signal of the first threshold device 31 is supplied to the first input 29 of the item, and also to the input of the differentiating circuit 35 and the first input of subtractive device 34 (Fig.2).

From the output of the differentiating circuit 35 signal is supplied to second inputs of the shift register 38 and n counters 41, providing them with a "reset", in addition, since the output of the generator 39 pulses of the signals received on the third input of the shift register 38, ensuring its functioning.

The signal input to the first input of subtractive device 34 corresponds to the first setpoint angular position φ1drive.

In the process of further with�of avoidany the purpose by the movement of the actuator relative to n predetermined angular positions of the actuator, when this occurs the tripping of one of the n second threshold 32 devices, at the moment of exceeding the current angular position of the actuator of one of the n predetermined angular positions, the signal from one of the n outputs of the second threshold 32 devices is supplied to one of inputs of the first element 36 OR the output of which a signal is supplied to a first input of shift register 38 and the second input of subtractive device 34.

At the output of subtractive device 34 to generate a signal Δφ= φ1- φ2iproportional to the difference between the first predetermined angular value and the second predetermined angular values of the drive.

The time interval Δtimovement of the actuator corresponding to the speed of movement of the actuator relative to predetermined angular positions, defined as follows.

After the passage of the wheel 6 of the first predetermined angular position signal output from the first element 29 is NOT supplied to the first inputs of n elements And 40, the second inputs of which are periodically received signals after the passage of the drive other predetermined angular positions, with one of the outputs of the shift register 38 through one of the n second elements 30, thereby ensuring the passage of pulses from the output of the generator 39 pulses through third inputs of n elements And 40 to first inputs of one of n counters 41.

Thus, during the movement of the actuator� 6, the n outputs of the counters 41 recorded time intervals Atj relative to predetermined angular positions that correspond to the current values of the angle-ing the speed of movement of the actuator 6.

During the movement of the actuator 6 signals Δtifrom the outputs of the counters 41 through the inputs of the second element OR 37 receives the first input of the divider 43, the second inputs of which through the n keys 42 receives signals proportional to Δφ from the output of subtractive device 34.

Thus, the output of the divider 43 is formed the signal

VPref.= Δφ /Δt, corresponding to the angular speed of the drive.

From the output of the divider 43, the signal is supplied to a first input of subtractive device 26, to the second input of which receives the signal corresponding to the angular velocity of the target Vö.= Δφ /Δt from the output of block 25 (Fig.1).

Unit 25 on the basis of processing the signal from the first output of the machine 8 target tracking, in accordance with the above algorithm block 24 determines the angular velocity of the moving target.

The signal output of subtractive device 26 is supplied to the inputs of the first 27 and second 28 of diodes, which define the direction (increase or decrease) the dynamics of change in the speed of the drives.

The signals from the output of subtractive device 26, the outputs of the first 27 and second diodes 28 is received in the second third and fourth inputs of the monitor 10.

The gunner on the basis of information about the required magnitude and direction of variation of the angular speed of the drive adjusts the speed of the actuator, thereby improving the reliability of maintenance and high-speed maneuvering target.

1. Way to track air targets, consisting in the detection of aerial targets to the gunner portable complex, the choice of the angular velocity homing opto-electronic module (OEM) by aligning the crosshairs on the monitor screen for the purpose, the translation of the poem in the mode of automatic tracking of the target by entering the target inside the gate tracking and issue the command "Capture", the current measurement of distance to a target by emitting laser radiation in the direction of the target and receive reflected radiation from the target, ensuring the control of the spatial position of the laser beam in the direction of the target by issuing control commands corresponding to the angular coordinates of the target, on a two-coordinate acousto-optic deflector, the conversion of the digital code range in the video signal, the display on the monitor in the form of digital labels, characterized in that the determined angular speed air targets and drive poem, determine the magnitude and direction of the necessary changes the angular velocities of the drive OE� by comparing the angular velocities of the target and drive poem, present recommendations to the gunner portable complex of the required magnitude and direction of change of the angular velocity of the movement of the actuator poem.

2. Optical sight with a tracking rangefinder, contains the opto-electronic module, which houses the probe and a target channel, a ranging channel and the receiving device, and the actuator pointing and stabilization, the power conversion control signals, automatic target tracking, sensor control commands for actuators and automatic target tracking, the monitor, serially connected to the scaling unit and the electronic control of an acousto-optical deflector, which consists of series-connected temperature compensation unit, the adder, two-channel frequency synthesizer, the ranging channel comprises a transmitting device consisting of series-connected laser transmitter, two-coordinate acousto-optic deflector and an output optical system, the receptor consists of series-connected reception optical system, the photodetector device and the transmitter of the target range, the yield of probe and target channel connected to the first input of the automatic target tracking, a second input connected to the output of the transmitter of the target range, the second output of the automatic target tracking, which� is the output, is connected to the input of the monitor and the first output of the automatic target tracking, which is the digital output signals of the angular error, connected to the first input of the conversion unit of the control signals, the output of which is connected to the inputs of the actuator pointing and stabilization, the outputs of which are mechanically connected to the opto-electronic module, the first and second outputs of the sensors control actuators are connected respectively to the second input of the conversion unit of the control signals and the control input of automatic target tracking, in addition, when clicking the gunner of a button "current range" of the sensor control commands to the actuators, laser transmitter of the transmitting device generates laser pulses with a predetermined repetition frequency, the first output of the automatic target tracking, which is the digital output signal of the angular error, is connected to the input of the scaling unit, the outputs of the electronic control unit of an acousto-optical deflector is connected with the second inputs of two-coordinate acousto-optic deflector, and the diameter d of the sensitive pad of the photodiode photodetector devices ranging channel satisfies the condition d ≥2F·fmwhere F is the focal length of a reception optical system of the distance-measuring channel; fm- the maximum angular error tracking on�optical sight, characterized in that it introduced the unit of analysis is the angular velocity of the target, the first and second inputs of which are connected respectively with the first output of the sensor control commands to the actuators and the output of the automatic target tracking, and first, second and third outputs are connected with the second, third and fourth inputs of the monitor, the unit of analysis is the angular velocity of the target unit consists of determining the angular speed of rotation of the actuator and the block determining the angular velocity of the target, subtractive device, the first and second diodes, the first and second inputs of the unit of analysis is the angular velocity of the target are respectively the inputs of the block determine the angular velocity of the actuator and the block determining the angular speed of target movement, the outputs of which are connected respectively with the first and second inputs of subtractive device, the output of which is connected to the inputs of the first and second diodes, the output of subtractive device, the outputs of the first and second diodes are respectively first, second and third outputs of the unit of analysis is the angular velocity of the target, the unit determining the angular velocity of the actuator (goals) consists of first and second n elements, the first and n second threshold devices, setpoint signals, subtractive device, a differentiating circuit, the first and Vtorov� elements OR, shift register, a signal generator, n elements And n counters n keys, the divider, and the input unit of determining the angular velocity of the actuator (goals) is the first n inputs of the first and second threshold devices, the second inputs of which are connected respectively with the first and n second outputs setpoint signal, the output of the first threshold device is connected to the input of the first element, the input of the differentiating circuit and the first input of subtractive device, the outputs of the n second threshold devices are connected to the inputs of the first element OR the output of which is connected to a first input shift register and a second input of subtractive device, the output of the differentiating circuit is connected with the second inputs of the shift register and n counters, the output of the pulse generator is connected to third inputs of the shift register and n elements, And the output of the first element is NOT connected with the first inputs of n elements And the outputs of the shift register after n second elements connected with the second inputs of n elements And whose outputs are connected to first inputs of counters, whose outputs are connected with inputs of the second element OR the output of which is connected to a first input of the divider, the second inputs of which are connected to the outputs of n keys first and second inputs which are connected respectively with the output of subtractive device and the output�mi shift register, the divider output is the output unit determining the angular velocity of the drive (target).



 

Same patents:

FIELD: military hardware.

SUBSTANCE: data are retrieved from the route navigation system of survey control and orientation (RNSSCO) from the self-propelled launcher (SPL) assembly and results of measurements of angular mismatches between axes of the inertial navigation system (INS) of the missile and RNSSCO. The angular route mismatches between a longitudinal axis of the missile INS and RNSSCO longitudinal axis and the subsequent use of results of the taken measurements during pre-starting procedure for determination of a true azimuthal angle of the missile by estimation of correction to the azimuthal angle measured by RNSSCO. The array of angular corrections measured by INS, missiles and SPL manufacturers is saved in permanent memory units.

EFFECT: higher accuracy.

3 dwg, 1 tbl

FIELD: physics, optics.

SUBSTANCE: invention relates to optical instrument-making and a device for simulating infrared radiation of ground objects. The device includes a micromirror matrix scanning unit, an infrared radiator, a set of lenses and mirrors, objective lenses, objective lens drives, an objective lens switch and a guidance system. The device also includes input registers, units for estimating empirical coefficients, units for estimating the atmospheric transmission coefficient, delay elements, multiplier units, OR elements, groups of multiplier units, a group of exponentiation units, a group of registers, a unit for estimating radiance, a unit for issuing switching commands, a display unit, a streaming pulse generator and a pulse distributor.

EFFECT: high efficiency of conducting tests.

3 dwg

FIELD: weapons and ammunition.

SUBSTANCE: proposed method comprises target ranging and input of measured magnitude to surface control system. Beam axis initial elevation Y0 is set relative to target point direction to launch the guided missile. Beam axis maximum elevation Ymax is set relative to target point direction. Missile flies at maximum elevation till the time set at surface control system in compliance with measured range to target, beam axis being aligned with target point direction. Note here that the elevation is serially changed in time interval from rocket launch moment to moment t1=2,53,5ωcutoff, where ωcut-off is missile control system frequency cut-off, rad/s while initial elevation Y0 is kept variable. Note here that its magnitude is set by relationship Y0=Yminp+(0,5÷1,0)Rb, where Yminp is minimum possible vertical deviation of the missile from target point direction at this flight path section, m; Rb is beam radius, m, while during period from moment t1 to moment t2=t1+YmaxY0Ve, where Ve is the maximum tolerable beam elevation rate, m/s, elevation is increased to Ymax.

EFFECT: higher accuracy of fire.

2 dwg

FIELD: weapons and ammunition.

SUBSTANCE: it is proposed to direct or rotate beam (12) of laser rays relative to centre (13) of the current specified heading of shell (1) so that shell (1) can determine by itself a data set and then perform automatic correction. For that purpose, the first laser ray (11) is supplied through certain area (15) relative to the specified heading of shell (1), which at the same time can cause the beginning of time reckoning. For example, at the same time, other rotating laser ray (12) with constant rotation frequency (Q) is located around area (15). By means of the second laser ray (12) the shell determines the data set relative to the specified heading and initiates correction based on the established data set. Size of the established data set is used to begin corrections. For that purpose, delays are implemented in shell (1).

EFFECT: improving correction efficiency of flight trajectory.

16 cl, 4 dwg

FIELD: instrument making.

SUBSTANCE: device includes serially connected laser and optic-electronic scanning system, comprising two crossed anisotropic acoustooptic deflectors and an output optic system, and also a unit of deflector control, outputs of which are connected to inputs of deflector control, and external signals of controlled item start-up and lift-off are sent to its control inputs, a unit of mode selection, to the input of which the external signal is supplied to permit distance measurement, a generator of sync pulses, a unit of modulator control, an optical modulator of resonator good quality, the control input of which is connected with the output of the modulator control unit, an output optical system of a range channel and a polarisation prism unit installed between the first and second acoustooptic deflectors, the second output of which is connected with the input of the optical system of the range channel. The receiving range channel includes serially connected receiving optical system, a photodetecting device and a unit of accumulation of echo signals and range calculation.

EFFECT: reduction of weight and dimension characteristics of an optic electronic instrument with preservation of possibility to measure distance and to observe background and target environment.

2 cl, 2 dwg

FIELD: weapons and ammunition.

SUBSTANCE: topographical control of a target finder and a launching plant is carried out in the method to the area, the target is found with the target finder, target coordinates are defined and sent to the fire position station. The single time is set in the scout station and the fire position station, firing settings and flight task of the missile are calculated in the fire position station. Missile launching from the fire position station is prepared along a digital communication channel via an automatics unit of the launching plant. At the same time voltage is supplied to the selected missile, the missile is initialised, firing interlocks are removed from the missile, and power is supplied. Firing is carried out by means of sending a launching command from the commander's station to the launching plant, the time of firing is fixed automatically by means of interrogation of missile availability contacts in the plant. The time of start-up of the target finder laser radiation is sent along the channel of the satellite communication to the scout station, and whenever it is achieved, a signal of radiation start-up and sent from the scout station to the target finder, and the missile is aimed at the target. Fire unit condition indication is carried out on the fire position station.

EFFECT: provision of the possibility to realise remote preparation of missile launching.

2 dwg

FIELD: weapons and ammunition.

SUBSTANCE: versions of methods for simultaneous homing of missiles teleoriented in a beam include generation of a control beam, matching of its optical axis with a line of target sighting, narrowing of the control beam with provision of permanence of its diameter at the range of missiles flight, generation of signals proportionate to deviation of missiles from the optical axis of the control beam and generation of commands of missiles control. In the first version of the method the value of missiles separation in flight is maintained as permanent within the entire flight time, thus preserving mutual spacing of missiles before target damage. In the second version at first the distance to the target is measured, and time of missile flight to the target is forecasted, and in the final section of homing at the moment determined by the difference of the forecasted value of missile flight time to the target and the time of transition process of the missile control circuit, the signals of spacing are reduced by absolute value to the value corresponding to the residual mutual spacing of missiles that is not lower than maximum dimensions of the missile in the plane perpendicular to its longitudinal axis.

EFFECT: higher efficiency of target damage when firing with a salvo of controlled missiles with reduction of probability of missiles collision in flight due to their spacing from each other in the cross section of a control beam with provision of high energy of a beam for salvo missiles.

3 cl, 3 dwg

FIELD: weapons and ammunition.

SUBSTANCE: air target is detected, angular speed of optoelectronic module guidance rate is selected by aligning cross at display with target, said module is switched into automatic tracking mode, actual range to target is computed to convert range digital code into video signal to be displayed as digital inscription. Additionally defined the following parameters: target motion angular speed by measuring time intervals of target displacement relative to preset angular points, target angular acceleration by estimating dynamics of angular speed variations, dynamics of target acceleration variation by subtracting the last and previous angular accelerations, target tracking is defined. In case dynamics of target angular acceleration variation is smaller than preset value, tracking of IR trap is defined. In case dynamics of target angular acceleration variation is greater than preset value, portable complex operator is notified about IF trap lock-in.

EFFECT: higher noise immunity.

2 cl, 2 dwg

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

FIELD: weapons and ammunition.

SUBSTANCE: proposed sight may be used in controlled weapons guidance systems. It comprises opto-electronic unit accommodating finder channel video transducer and range finder channel, guidance and stabilisation drive, control signal conversion unit, target tracking automatic device, transducers of control signals from drives and aforesaid automatic device, and monitor. Additionally, sight comprises scaling unit, acoustic-optical deflector electronic control unit including thermal compensation unit, adder, two-channel frequency synthesizer, and two-coordinate acoustic-optical deflector arranged between laser radiator and output optical system of range finder channel transmitter. Diametre d of range finder photo receiver LED sensitive sire satisfies the condition d≥2F·φm, where F is focal distance of range finder receiving optical system; φm is maximum angular error of target tracking by optical sight.

EFFECT: accurate range finding for flying high-speed maneuvering targets thanks to target tracking error compensation in rage finder channel.

1 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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