Method for simultaneous homing of missiles teleoriented in control beam (versions) and homing system for its realisation

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.

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The proposed technical solution relates to rocket technology and can be used in the complexes of guided weapons mainly air-launched to combat dangerous purposes, for example, by means of air defense, aircraft and helicopters, launchers and atomic batteries of artillery.

Currently, foreign army equipped with weapons of the new generation, characterized by an increased firing range of activities and a high survivability. Increasingly used to fight with tanks, planes, helicopters and air defenses are complexes of guided weapons with beam guidance system. Well-known domestic complexes "Bastion", "the Reflex" (Weapons and technologies of Russia, armored armament and technology, volume VII, M., 2003, the Publishing house "Weapons and technology", s-345), and foreign "Mapats" (Israel), MSS 1.2 (Brazil), ZT-35 Ingwe (South Africa), "Red Arrow" (China) (Precision-guided weapons to foreign countries. Volume 1, Anti-tank missile systems, survey and analytical reference, Tula, 2008). Complexes of this type provide shooting at ranges up to 5 km with a probability of kill of about 0.8.

Conditions the brevity of the fight and the high range fire resistance means of the opponent, for example, the most common air defense to 5-6 km, require packing list : the owls of guided weapons, posted by mobile carriers with a short strike, increased effective range of fire and the probability of hitting a target. This problem is partly solved by the use of complexes of the air base.

However, because of the speed of angular displacement of the line of sight in the process of aiming missiles at the target such complexes are characterized by a large dynamic error pointing and, as a consequence, the low efficiency of defeat, not exceeding the effectiveness of the air defense of 0.3-0.6.

A significant increase in the efficiency of the lesion may be obtained through the simultaneous targeting of multiple missiles at one target (volley fire).

The probability of hitting a target W1in this case, is determined by the expression (Wentzel Y.S., probability Theory, Nauka, M., 1964)

where i is the number of missiles in the volley,

W1- the probability of hitting a target with one rocket.

From (1) it is obvious that with increasing number of missiles increases the probability of hitting a target.

Targeting multiple missiles at one target, possibly as several independent complexes, and from one sector beam control.

There is a method of missile guidance beam, presented in the patent of the Russian Federation 2247299 IPC7F41G 7/26-based obstrelivanii two missiles in the beam control is teleriunione missiles in a single beam control by keeping them in the center of the beam control before hitting a target.

The method consists in the following. Each missile is allowed in the direction of the goal and keep the beam about its center, systemowego with line of sight. Start their produce consistently with some interval, causing the missiles are spaced from each other in distance and beam width control maintain constant range in place of the span of the last rocket.

There is a method of guidance on the information beam implemented in the guidance system, protected by the RF patent №2382315 IPC F41G 7/26, allowing simultaneous firing of several complexes at the same target, and firing two missiles from one complex in a single beam at one target. There is a method of guidance is as follows.

On the control station in the direction of the goal alternately send two flat scanned beam. When this beam chart which stretched vertically, scan rate and beam chart, an elongated horizontally scan pitch. Optical zoom optical system in the process of homing missiles constantly changes the angular size of the raster scanning beams, thereby maintaining the constancy of the width of the scanning beams in place of the flight of the rocket range. The center of the scanning field Shusterman with line of sight. In systemevolved time-pulse modulated beams with literal encoding. A vertically elongated beam is modulated code sequence of pulses, which incorporated information about lettering and its deviation from the guidelines for the course, and horizontally elongated beam is modulated code sequence containing information about lettering and its deviation in pitch. Literal interval - the interval between the literal and the reference pulses - its for each individual complex, is set to launch the same for instruments of control and rockets. In short intervals of irradiation scanned beams installed on the missile receiver of optical radiation side apparatus performs decoding of the received code sequence at its lettering, resulting in the rocket produces control signals for the missile is proportional to its coordinates in the scanning field of the rays. The method has high resistance to optical interference due to the application of the Gating time of the received signal and a literal encoding of the information about the coordinates of the rocket transmitted from the control point on the rocket on the scanned rays that ensures sustainable management of missiles while shooting several different coded complexes at one target. When firing a volley due to the simultaneous use of the project for several independent systems for shooting at one target, this method requires significantly more material and human costs compared to the costs when firing a volley from one complex.

Guidance method provides quassapaug shooting, in which missiles are produced one after another with a short time period. For the case of firing two missiles into a single beam by one goal, with some time between launches the probability of collision missiles. As a consequence, the probability of hitting a target can be even less than for the case of firing a single missile.

The time interval between launches of missiles must be greater than some minimum value to avoid collision missiles in flight if the speed of the second rocket will be better than the first speed, and less than some maximum value, which for the first rocket in the expanded beam, stops normal allocation coordinate its light receiver.

The increase in the interval between the starts of consecutive missiles increases the time of making the volley kick, holding the brand of sight on the target over a longer time, not allowing the media to maneuver, reducing the effectiveness of the fire resistance of the enemy, and consequently a decline in the survival rate of the complex, to reduce combat rate of fire, and, ultimately, to reduce the combat effectiveness of the media. The disadvantages of this method of guidance is that the first is I rocket, flying in a wider beam, uses less energy beam that can lead to loss of missiles, as well as a high level of collision probability of missile flight trajectory and, as a consequence, the low efficiency of defeats the purpose.

The described method is implemented in the guidance system shown in the patent of Russian Federation №2382315 IPC F41G 7/26 containing installed in the hardware of the control point 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 sequentially connect the installed 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 of the analyzer pulse-code.

The objective of the proposed technical solution is to increase the efficiency of hitting a target when firing a volley of guided missiles in a single beam. This object is achieved by reducing the probability of collision missiles in flight due to their removal from each other in the cross section of beam control.

In the first embodiment proposes a method of simultaneously targeting tereorieribum in the beam missiles, including the formation of beam control, the combination of its optical axis with the line of sight of the goal, narrowing the beam control to ensure consistency of its diameter in the range of the missiles, generation of signals proportional to the deviation of the missile from the optical axis of the beam control, formation control commands missiles, new is the fact that each rocket form and memorize a signal proportional to its sequence number, and form signals explode determined by dependency

where yn, znlights explode, respectively, ka is the al pitch, and of course,

n is the number of missiles

i - the number of simultaneously guided missiles,

h - diameter of a circle on which the centers of the orientation of the missile in flight, and the number of simultaneously guided missiles is determined from the condition

where a is the diameter of the beam control range missiles

σn- the deviation of the coordinates of the missile from the expected position, as defined, for example, statistical modeling, h is chosen from the condition

but the development of new control commands missiles produced in proportion to the difference between the signals of the deviation of the missile from the optical axis of the beam control signals explode in the corresponding control channel.

The second option offers a way of simultaneously targeting tereorieribum in the beam missiles, including the formation of beam control, the combination of its optical axis with the line of sight of the goal, narrowing the beam control to ensure consistency of its diameter in the range of the missiles, generation of signals proportional to the deviation of the missile from the optical axis of the beam control, formation control commands missiles, new is the fact that initially measure the range to the target, predict the time of flight of the missile to the target, each rocket f is rerout and remember the signal, proportional to its ordinal form the signal explode determined by dependency

where yn, znlights explode, respectively, in the channels of the pitch and of course,

n is the number of missiles

i - the number of simultaneously guided missiles,

h - diameter of a circle on which the centers of the orientation of the missile in flight, and the number of simultaneously guided missiles is determined from the condition

where a is the diameter of the beam control range missiles

σn- the deviation of the coordinates of the missile from the expected position,

h is chosen from the condition

but the development of new control commands missiles produced in proportion to the difference between the signals of the deviation of the missile from the optical axis of the beam control signals explode in the corresponding control channel, while the final part of the guidance at the time determined by the difference between the predicted value of the time of flight of the missile to the target and time of transient process control loop missile, reduce signals explode in absolute value to the value corresponding to the residual mutual destruction of missiles not less than the maximum dimensions of cancer is you in the plane, perpendicular to its longitudinal axis.

In the control room make the detection of a target form and send in the direction of the target, the beam control, in which streliaut clearancequeenie missiles after they start. In cross-sectional area of the beam control encode proportional to the angular deviations (coordinates) from its centre on the rate and pitch, thereby to form in the beam coordinate control field missiles, and the center beam control (start coordinate control field) combined with line of sight targets. Rockets hold the beam to hit a target by receiving radiation rocket, the selection coordinates of each of the rocket relative to the center beam control by means of the decoding control signal and output it control action, proportional to the coordinates of the missile to correct its position. To reduce the probability of collision missiles in flight, their guidance is implemented with a distance from each other, which provide as follows. Before the launch of rockets in the cross-sectional area of the beam control for each of them choose the position (orientation), remote from selected provisions of other missiles. Form and submit to the Board each rocket additional commands, encoded values of the coordinates of the selected position in the beam control of the same RA is Yety, allocate aboard each missile coordinates of the selected position by decoding additional control commands to form the rocket additional control action, proportional and opposite in sign to coordinate its selected position. In this case, the total control action on the rocket becomes zero in its selected position, which seeks to take the rocket in flight. The value of the mutual removal Δ selectable positions missiles set of conditions

where σnexperimental or calculated value of the standard deviation of the coordinates of the rocket from the expected position. Due to the fact that the characteristics of the real position of the missile random rocket cannot constantly keep in cross section of the beam in the position for which she was chosen before the start, and hovers around him. In connection with any removal of selectable positions remains some probability of collision missiles. The minimum allowable value (10 σnmutual removal of selectable positions of the missile is determined through statistical modeling volley firing guided clearanceshemale missiles.

As the criteria and the chosen level of probability of collision of R=0.02, prin is th for aircraft and rockets. The upper boundary of the deletion of Δ is limited to the width And beam control. In addition, to minimize the probability of collision missiles in flight while ensuring the sustainability of their teleobjective each rocket in the cross section of the beam control allocate the management area with a minimum width of 10 σnand select the position (orientation centers) missiles in flight have evenly spaced around the circumference with its center coincident with the center of the beam control and a diameter of h, defined by the condition (4), where i is the number of simultaneously induced in the beam missiles selected from conditions (3).

To increase the efficiency of destruction of large air slaboerodovanyh goals, and clusters of enemy forces by increasing the area affected the amount of the additional control constant support during the whole time of flight of the missile, thereby preserving the mutual destruction of the missiles to hit the target.

In the second embodiment, when firing at armoured technique to improve the efficiency of defeat by concentrating the power of the strike in the terminal phase of the missile flight drive to the center of the beam control. To do this, first measure the distance DCto target, forecast time tCflight of the missile to the target and the final part of the guidance at time t0defined what isnotu predicted time of flight of the missile to the target and time of transient process control loop rockets

shift the centers of the orientation of the missile from the originally selected provisions to the center beam control, which reduces the signals explode in absolute value to the value at which the residual mutual destruction ΔOSTthe expected average of the provisions of missiles (centers orientation) meets the condition:

where - the maximum dimensions of the rocket in the plane perpendicular to its longitudinal axis.

Suggested ways to implement guidance system of simultaneous guidance tereorieribum in the beam control missiles containing installed on the control shaper pulse-code, two pulsed radiation source and connected in series forming unit two planar orthogonal beams, the scanning unit, kinematically associated with a sensor of angular position, the output of which is connected to the first input of the pulse shaper code, and Shusterman with an optical sight optical zoom optical system, and the block lettering connected with its output to the second input of the shaper pulse code, and the first synchronizer, the output of which is connected to the clock inputs of the block lettering and shaper pulse code, with the first and second pulse sources its outputs on clucene respectively to first and second inputs of the unit beam forming, and installed on each missile is consistently connected to the radiation detector, optically connected with the optical zoom system control block Gating signal and the pulse-code analyzer and block Gating pulses, a first input connected to the output of the radiation detector, and a second synchronizer, the output of which is connected to the clock inputs of the pulse-code analyzer and block Gating pulses, the output of which is connected with the second input of the Gating signal, wherein the control point is entered, the switch connected to the first and second inputs respectively to the first and second outputs of the pulse shaper code, and first and second outputs to inputs respectively of the first and second pulsed radiation sources, connected in series rangefinder, the block detection command information, missiles, block compare, the driver gate and the switch mode controller is connected with its output to the control input of the switch, as well as stopwatch, connected to the second input of the comparison, and directional signs missiles, each missile entered sequentially connected block storage characteristic, the first adder, the first block works, sine-cosine functional change is spruce, the second work package, the first inverter, the first attenuator and the second adder, connected in series, the third work package, the second inverter, a second attenuator and a third adder, and a storage unit constants, with each output of the distributor signs of missiles is connected to the input of the storage unit characteristic corresponding to the rocket, the first and second outputs of the storage unit constants connected with the second inputs of the first adder and the first block works, respectively, and the third output of the storage unit constants connected with the second inputs of the second and third blocks of the works, the second output sine-cosine functional Converter connected to the first input of the third block works the first and second outputs of the pulse-code analyzer pitch rate is connected with the second inputs of the second and third adders, respectively, and also connected in series selector command code information, missiles, is connected with its input to the output of the radiation receiver, and a storage element that is connected with its output to the control inputs of the first and second attenuators.

Figure 1 shows the functional diagram of the guidance system for volley firing clearanceshemale missiles.

Figure 2 presents a scheme aiming when firing a salvo of two missiles, removing the cancer is t from each other in the cross section of the beam control.

Figure 3 shows the location of the missiles in the cross section of the beam when conducting volley of four missiles.

Figure 1 presents the block diagram of the proposed guidance system that implements the proposed method. Part of the guidance system on the control point 1, along with the known blocks, such as: the shaper pulse-code 2, the first and second pulsed radiation sources 3,4, block the formation of two planar orthogonal beams 5, the first synchronizer 6, the scanning unit 7, the sensor of angular position of the beams 8, optical zoom optical system 9, the optical sight 10 and the block lettering 11, includes new blocks: switch 18, a timer 19, rangefinder 20, codebrowser team information, rockets 21, switch modes aiming 22, the gate driver 23, block 24 comparison unit determining the time of filing command information 25 missiles and directional signs missiles 18, and each missile 12 to well-known blocks: the radiation receiver 13, the block Gating signal 14, the gate pulse 15, the second synchronizer 16 and the analyzer pulse code 17 added new blocks: the block of storage characteristic rockets 27, the first, second and third adders 28, 40, 41, a storage unit constants 29, the first, second and third blocks works 30, 33, 34, sine-cosine functional Converter 32, the first and second inverters 35, 36, village of the tor code team information, rockets 31, the storage element 37, the first and second attenuators 38, 39.

The proposed guidance system works in the following way. On the control station 1 with 12 missiles on launchers 42 (2) make the detection of a target 45, in the direction which send two flat scanned beam. Luminous flux from the first pulsed radiation source 3 block form a flat orthogonal beams 5 is concentrated in a narrow beam that is elongated in the vertical direction, and the light flux from the second pulsed radiation source 4 block formation is concentrated in a narrow beam that is elongated in the horizontal direction. The total cross-shaped beam with unit 5 is directed to the scanning unit 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, an elongated horizontally scans the pitch. The vertical beam in the scanning rate modulate the coded sequence, which incorporated information about lettering and its position relative to the line of sight, similar to the beam is scanned across the pitch, modulate a code sequence containing information about the lettering I position. Synchronously with the scanning unit 7 rotates the sensor of angular position of the beams 8, the output of which produces signals on the spatial position of the beam relative to the mean coincident with the line of aim. Signal light from the scanning unit enters the optical zoom optical system 9, which continuously during the flight of the rocket produces zoom images of scanned beams, thereby providing a constant coordinate control field, the rocket trajectory. Rigidly with the zoom lens system 9 is connected to the optical sight 10, the aiming mark which coincides with the center of the field of missile guidance.

The electrical signals of the position of each of the scanned beam in the control field of the sensor 8 are served on a first input of the shaper pulse-code 2, to the second input of which receives signals from the block lettering 11. The first synchronizer 6 produces clock pulses at the clock input of the driver code 2 and block lettering 11.

Shaper pulse-code 2 continuously generates a code sequence, which includes information on lettering and the position of the scanned beams at the rate and pitch (information about the coordinates of the rocket during its irradiation).

Block lettering 11 generates the reference and lettered pulses, and ferny interval between these pulses, defines a literal encoding of the transmitted rays of information. This interval is set to launch the same for ground and on-Board instruments of each individual complex ptors.

The digital signal with a sensor of angular position about the spatial position of the beam in the driver code 2 is converted into a time interval between literal and coordinate pulses in the channels of the course and pitch.

Pulse channel code rate of the imaging unit 2 is supplied to the radiation source 3 and the channel pitch is on the radiation source 4. Sources of radiation under the action of control signals from the pulse shaper code 2 produce short light pulses. On-Board equipment of the missile 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 beams of the receiver 13.

The signal from the light receiver of the missile 13 is supplied to the first input of the Gating signal 14, to the second 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 presence of the Gating pulses. Block the gate pulse 15 is started from the second synchronizer 16 at the time of arrival of the reference pulse from the receiver 13. For about the especiany synchrony generation time interval lettering and provisions timelines rocket and control both synchronizer 6 and 16 are made identical. By applying a temporal Gating of the received signal and the operation of the onboard apparatus to the reception only in moments of exposure lettered pulse code achieves increased robustness of the control system from optical interference.

The signal from block Gating 14 to the input of the analyzer pulse-code 17, which converts the coded signals to analog, by measuring the time intervals corresponding to the coordinates of the rocket at the rate Z and the pitch Y, and generates a control command that is proportional to the deviation of the missile (coordinates) at the rate and pitch from the center of the beam control.

To avoid collision and impact of gas streams adjacent missiles unmanaged flight, for example, from the time of leaving the launcher to vstraivaniya in the beam control of missiles produced, for example, diluted to the front or the height launchers (Fig 2).

After vstraivaniya missile 12 in beam 43 width And beam at the location of missile support, for example, a permanent change using the optical system of the angular size of γ(t) of the beam, for example, by a zoom lens with variable focal length. Radiation control take on each missile, convert it into an electrical signal and decode, resulting in a gain when the e signals, proportional to the coordinates of the current position of the missile relative to the center 44 of the beam control 43. Then produce a control action, proportional allocated thus coordinates, move the rocket to the center of the beam control, resulting in each missile is held in the beam control. To ensure mutual removal of the missiles in the plane of the cross section of the beam control on each missile form additional control action.

On the control form for control signals explode), encoded by the coordinate values of its selected position, pass them on Board, for example, when preparing the rocket for launch through circuit training and launch and control decode on each missile, thereby coordinate values of the selected position, and fixed in the storage unit characteristic missiles to save during the flight, and the signals explode produce proportionally fixed values of the coordinates of the selected position of the missile with the opposite sign. In addition the resulting control actions each missile is shifted to its selected position and held about him.

Recorded in block 27 of each missile characteristic, for example, in the form of a serial number of missiles comes n is the input of the first adder 28, where the number of missiles is summarized constant "-1", coming from the first output of the storage unit constants (BHC) 29. Further, the output signal of the first adder is fed to the first input of the first work package 30, the second input of which receives the constant 2π/i" from the second output of the BHC. With the release of the first block works the signal goes to the input sine-cosine functional Converter (SCFP) 32, the first output of which the signal at the first input of the second work package 33 and the second output SKFP - at the first input of the third work package 34, the second inputs of the second and third blocks works comes the constant "h/2" from the third output of the BHC. In the end, with the outlet of the second work package is the signal via inverter is supplied to the first attenuator and the second input of the second adder, where is folded pitch output pulse-code analyzer, and the output of the third work package of the signal passed through the inverter goes to the second attenuator and then to the second input of the third adder, where is folded directional output of the pulse-code analyzer. In addition for additional commands control commands coming from the block 17, the outputs of the second and third adders 40 and 41 are produced team total control, bias cancer is in its selected position.

The amount of the additional control signals explode) keep up defeats the purpose when shooting, for example, air and large goals. This allows you to save at the meeting for mutual destruction of missiles, and to provide a wide area of damage.

Figure 3 illustrates the accommodation of four missiles in the cross section of the beam. Before the launch of missiles for each of them choose their position in the cross-sectional area of the beam. For example, let σn=0.02 and selected provisions of the missiles C1, C2, C3, C4 on the circumference, for example, with a diameter of 0.5 a with coordinates

; n=1,2,3,4

; n=1,2,3,4

The minimum value of Δminis in this case

that meets the condition (4):

When firing at armoured engineering (second variant) to ensure a high concentration of power impact the value of the mutual removal of the missiles by the time of the meetings to reduce. To do this, first, for example, when the avalanche missiles with launchers, measure the distance of the goal from the control and predict the flight of the missile to the target, for example, experimental or calculated according to the time of flight of the rocket from the predetermined range, and when approaching the goal is t 0that is determined in accordance with condition (5), rocket from the control transmit command information, missiles, for which additional control actions, holding the rockets about their selected provisions decrease in absolute value, for example, to the value of the corresponding residual removal ΔOSTmissiles (8), is equal to, for example, the maximum size of the rocket In the plane perpendicular to its longitudinal axis. For the above case with four missiles in the salvo new expected position of the missiles will be on the circle with diameter h2

and to have coordinates

; n=1,2,3,4

; n=1,2,3,4

Changing K values additional control actions proportional to the change of coordinates will be

The pulsed radiation sources 3, 4, block the formation of rays 5, the pulse shaper code 2, the scanning unit 7, the angular position sensor 8, the optical zoom optical system 9 with the optical sight 10, block lettering 11, the radiation receiver 13, the block Gating signal 14, block the gate pulse 15, the pulse-code analyzer 17 and synchronizers 6, 16 are elements of the system meliorative and can be performed, for example, t is the same as in the guidance system prototype.

Rangefinder 20, for example, a laser (see RF patent №2123165, IPC F41G 3/22) before the start of the missile determines the range of 45 goals from the control station, generates and outputs at its output a digital value. The block detection command information, missiles 25 made, for example, in the form of functional Converter on permanent storage devices (ROM), in cells which are listed dependence (5). At the address equal to the digital value range goal of DCcoming from the rangefinder 20 to the address input of the ROM unit 25, is the selection of the appropriate values of t0command information of missiles. Stopwatch 19, which represents, for example, electronic digital timekeeping device (see C. A. Shpolyansky, Chronometry, M., engineering, 1974, s-255)launched the rockets, for example, at the time of their departure from the launcher makes the expense of real-time flight missiles, the value of which goes to the Comparer 24 made, for example, in the form of a digital comparator. To the second input of the comparison comes a time value t0block 25. The logic state at the output of the Comparer is replaced, for example, from "0" to "1" at the time matches the current time with a value of t0, resulting in the gate driver 23 made, for example,in the form of a one-shot, generates the gate pulse at the input of the switch mode guidance 22. Before launch, the switch 22, made for example in the form of a contact device (see Taikina, radio electronic elements, M, Owls. Radio, 1976, p.19-20), set in one of two positions: 1 - for example, when firing at armoured engineering, 2 respectively when shooting at large and laborunions technique or air targets. At the first position, the switch 22 electrically connects the control input of the switch 18 with the output of the gate driver 23, the second position - for example, a shared bus. In the first case, the gate pulse output unit 23 is supplied to the control input of switch commands 18, which produces a disconnection from entering the unit emitters of signals from the pulse shaper code control commands 2, and connected to the signal with the instruction code information of missiles from koroobrazovaniya 21. At time τpaction gate pulse beam control over the whole cross section regardless of the angular deviations of the course, and the pitch is modulated by one code - the command code information of missiles. The value of τpchoose, for example, equal to two periods of the update information of the coordinates of the missile in the beam that provides the reception of each missile at least one code consistently the tee command signal information, produced by koroobrazovaniya 21. Code sequence command information represents, for example, a group of 3-5 pulses with time intervals different from the intervals produced by the pulse shaper code 2. Codebrowser 21 can be performed, for example, similar to that shown in Reference electronics, Ed. by Was, Meters, Energy, 1967, volume 1, s, 604 [1].

Directional signs missiles 26 and the storage unit constants 29 can be made in the form of a persistent storage device (Utica, Klenk, Semiconductor circuitry, M., Mir, 1982, s-127 [2]). The storage unit characteristic rockets 27 can be performed, for example, in the form of random access memory, s-124 [2]. The adders 28, 40, 41 can be implemented, for example, according to the scheme RIS (p.137). Blocks works 30, 33, 34 can be made by the scheme (RES, s [2]). Sine-cosine functional Converter 32 can be implemented on the basis of the functional circuits of the Converter ROM (RES, s [2]).

For each channel receives on attenuators 38, 39, the transmission ratios which in the initial state is equal to one, and from the outputs of the attenuators on the corresponding adders 40, 41, made for example in the form of diagrams summing operational amplifier.

is the result of adding additional commands explode with control commands, coming from the block 17, the outputs of the adders 40 and 41 are produced team total control, bias missile to its selected position.

When the switch 22 in position I in the time interval from t0to t0pbeam control for each missile receives the command signal information, which is decoded by the selector code 31 made, for example, similar to that shown in [1], s, 605, resulting in its output produces a pulse command information of missiles, which is supplied to the storage element 37 made of, for example, in the form of R-S flip-flop, and changes its output condition, for example, from low to high, affecting the control inputs attenuators 38 and 39 made in the form, for example, managed divider.

This signal causes the reduction gear ratio of the attenuator for each channel, for example, in accordance with (8), resulting in values of additional commands at the rate and pitch of current at the input of the adders 40 and 41 are reduced. Consequently, under the action of the new total control each missile is shifted to a new position near the center of the beam control, separated from the new provisions other missiles on the value of ΔOST.

When the switch 22 is in position II when approaching targets for cancer is you don't receives a command signal information, at the meeting with the aim of selected mutual destruction remains. This ensures effective shooting as large laborunions and air targets (first option), and armored targets (the second option).

The probability of hitting a target when firing on the proposed method of targeting a salvo of two missiles, taking into account the probability of collision missiles on the trajectory Rarticleis determined by the formula

,

and taking into account (1)

.

When making salvo of two missiles with a likely defeat a missile W1=0.7 and the probability of collision of Rarticle=0.02 resulting probability will be

which is higher than the probability of hitting a target when firing a single missile. The proposed method guidance for firing a volley allows to reduce the probability of hitting each rocket to the level corresponding to firing a missile at the expense of reducing the probability of collision missiles, and a small number of missiles in the volley - the exception of their clash on the trajectory. The proposed method removes restrictions on the maximum range and the minimum interval between launches of missiles available to the prototype that allows it to be used in the complexes based the x on mobile media (airplanes and helicopters) in the conditions of firing on the promising technique of the enemy at ranges, exceeding the area of its fire resistance.

1. The method of simultaneous guidance tereorieribum in the beam missiles, including the formation of beam control, the combination of its optical axis with the line of sight of the goal, narrowing the beam control to ensure consistency of its diameter in the range of the missiles, generation of signals proportional to the deviation of the missile from the optical axis of the beam control, formation control commands missiles, characterized in that each rocket form and remember the signal, proportional to its ordinal form signals explode missiles in the beam, and the formation of management teams missiles produced in proportion to the difference between the signals of the deviation of the missile from the optical axis of the beam control signals explode in the corresponding control channel while the signals of the missiles explode in the beam is determined by the dependencies:
where yn, znlights explode, respectively, in the channels of the pitch and of course;
n is the number of missiles;
i - the number of simultaneously guided missiles;
h - diameter of a circle on which the centers of the orientation of the missile in flight,
moreover, the number of simultaneously guided missiles is determined from the condition:,
where a is the diameter l of the cha management on the flight range of the missile;
σn- the deviation of the coordinates of the missile from the expected position,
h choose from a condition:

2. The method of simultaneous guidance tereorieribum in the beam missiles, including the formation of beam control, the combination of its optical axis with the line of sight of the goal, narrowing the beam control to ensure consistency of its diameter in the range of the missiles, generation of signals proportional to the deviation of the missile from the optical axis of the beam control, formation control commands missiles, characterized in that the first measure the range to the target, predict the time of flight of the missile to the target, each rocket form and remember the signal, proportional to its ordinal form signals explode missiles in the beam, and the formation of management teams missiles produced in proportion to the difference between the deviation signals rocket from the optical axis of the beam control signals explode in the corresponding control channel, while the final part of the guidance at the time determined by the difference between the predicted value of the time of flight of the missile to the target and time of transient process control loop missile, reduce signals explode in absolute value to the value corresponding to the residual mutual destruction of missiles of at least the maximal size of the rocket in the plane perpendicular to its longitudinal axis.

3. The system of simultaneous guidance tereorieribum in the beam control missiles containing installed on the control shaper pulse-code, two pulsed radiation source and connected in series forming unit two planar orthogonal beams, the scanning unit, kinematically associated with a sensor of angular position, the output of which is connected to the first input of the pulse shaper code, and Shusterman with an optical sight optical zoom optical system, and the block lettering connected with its output to the second input of the shaper pulse code and the first synchronizer, the output of which is connected to the clock inputs of the block lettering and shaper pulse code, and the first and second pulse sources its outputs connected respectively to first and second inputs of the unit beam forming, and installed on each missile is consistently connected to the radiation detector, optically connected with the optical zoom system control block Gating signal and the pulse-code analyzer and block Gating pulses, a first input connected to the output of the radiation detector, and a second synchronizer, the output of which is connected to the clock inputs is analizator pulse code and block Gating pulses, the output of which is connected with the second input of the Gating signal, wherein the control point is entered, the switch connected to the first and second inputs respectively to the first and second outputs of the pulse shaper code, and first and second outputs to the inputs respectively of the first and second pulsed radiation sources, connected in series rangefinder, the block detection command information, missiles, block compare, the driver gate and the switch mode controller is connected with its output to the control input of the switch, as well as stopwatch, connected to the second input of the comparison, and directional signs missiles, each missile introduced sequentially connected block storage characteristic, the first adder, the first block works, sine-cosine functional Converter, the second block works, the first inverter, the first attenuator and the second adder, connected in series, the third work package, the second inverter, a second attenuator and a third adder, and a storage unit constants, with each output of the distributor signs of missiles is connected to the input of the storage unit characteristic corresponding to the rocket, the first and second outputs of the storage unit constants connected with the second inputs of the first adder and the first is Loka works, respectively, and the third output of the storage unit constants connected with the second inputs of the second and third blocks of the works, the second output sine-cosine functional Converter connected to the first input of the third work package, the first and second outputs of the pulse-code analyzer pitch rate is connected with the second inputs of the second and third adders, respectively, and also connected in series selector command code information, missiles, is connected with its input to the output of the radiation receiver, and a storage element that is connected with its output to the control inputs of the first and second attenuators.



 

Same patents:

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: weapons and ammunition.

SUBSTANCE: group of inventions relates to devices of ship air defense system with optoelectronic information means (OEIM) for detection and tracking of air and surface targets. OEIM in the form of television camera, thermal imager and laser range finder. OEIM are installed in tight vessel with protective optical windows (POW). According to the first version of invention, POW are arranged with their wedging alignment in direction that minimises angular parallax between OEIM within the limits of specified range of distances to target, and autocollimating images from tight vessel POW are used as test ones for online monitoring of angular position of photo-optical axes, threshold sensitivity and angular resolution of OEIM. In the second version tight vessel of POW is arranged with drives that are independent on the main gimbal suspension, and dynamically moving autocollimating images from POW of tight vessel are used as test ones to control parametres of driving circuit of targets tracking. Device is equipped with monolithic glass angled reflector and glass wedge, which are in optical contact and have various index of refraction. Wedge is arranged with angle, value of which provides for preservation of angular direction of passing light beam. Internal surface of tight vessel imitates photometric Ulbricht sphere, and inner surface of tight vessel cover is Lambert reflector.

EFFECT: increased distance of targets detection and increased accuracy of their coordinates measurement.

4 cl, 4 dwg

FIELD: physics.

SUBSTANCE: system has a laser rangefinder, two detection channels, one of which is television and the other is infrared, which has a second objective lens and an N-element photodetector, a scanning mirror position sensor, a switch, an analogue-to-digital converter, a unit for determining matrix elements of the resultant image, a unit for evaluating linear transformation coefficients, a criterion function calculation unit, a unit for selecting the minimum value of the criterion function and a unit for forming the matrix of the initial image.

EFFECT: more reliable identification of a the image of a target due to independence of the reference from scanning conditions.

1 dwg

FIELD: weapons.

SUBSTANCE: invention relates to guidance systems and can be incorporated with tank and antitank complexes as well as in small-size antiaircraft complexes. Control station additionally incorporates unit to generate two flat orthogonal beams, course- and pitch-scanned perpendicular to their planes, which adds to security of control process due to small instantaneous area and short duration of terrain illumination in target area. Control station also incorporates synchroniser and unit to generate codes and pulse codes transmitting, on scanned beams, the data on spatial position in the form of time-pulse modulation in preset, for given complex, level of security to increase efficiency in simultaneous fire from several complexes and provide security of control thanks to pulsed radiation mode (minor radiation power). Missile incorporates unit to gate received signal, gate pulse unit, onboard pulse code synchroniser and analyser to extract missile coordinates transmitted on their pulse code level.

EFFECT: higher noise immunity and accuracy thanks to generation and transmission of commands of dynamic error compensation.

3 dwg

FIELD: weapons.

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: 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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