Self-propelled launcher-based cruise missile alignment method
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
The invention relates to military technology, namely the technique of aiming cruise missiles, medium-range, and can be used on cruise missiles placed on mobile land-based launchers.
Currently almost all of the cruise missiles are equipped with systems final guidance, which uses as primary information sensor homing (radar, infrared, etc.). However, for a correct choice appointed to defeat the target, the missile must with a minimum error out design point for subsequent homing. One of the determining factors of the error output design point is the error of determining the initial azimuthal angle of the rocket.
The task of determining the initial azimuthal angle of the rocket decides sighting system. The method of implementation of this system depends on the accuracy of determining the initial azimuthal angle of the rocket.
Currently in wide use in schemes targeting systems of self-propelled launchers (forth - ICS) finds using route-navigation systems for topographic location and orientation (hereinafter MNST). This is especially prevalent in tanks, rocket launchers, etc. To implement such a scheme aiming first measure angular RA�approval at the exchange rate between instrument axis MSTO and the longitudinal axis of the barrel (tank), guides (for systems of volley fire), etc. In Fig.1 is a diagram of the angular misalignment in the exchange rate between the longitudinal axis MNST Sigma 30 and the longitudinal axis of the barrel self-propelled howitzers. According to the manual on MEITO Sigma-30 (paper No. NTA14/Sigma30-011, pp. 3-11), the measurement of the angle of misalignment in the exchange rate between instrument axis MNST 1 and the longitudinal axis of the barrel 2 self-propelled howitzer is carried out by means of two theodolites 3 and 4 with the optical control element (hereinafter ECE) 5, mounted on the housing MSTO and materialismus instrument axis MNST, and special tools with JCMS 6, mounted on the muzzle of the self-propelled howitzers and materialismus longitudinal axis of the muzzle. Mounting theodolites 3 and 4 perpendicular to the optical control elements 5 and 6, respectively, and then, spending autocollimation binding theodolites 3 and 4 to each other, measure the angles Ψ1and Ψ2. Using the values of Ψ1and Ψ2determine the angular misalignment ΔΨ at the exchange rate between the longitudinal axis MNST 1 and the longitudinal axis of the barrel self-propelled howitzer 2. The value of ΔΨ is stored in read only memory (hereinafter ROM) MNST 1 and subsequently used for targeting, self-propelled howitzers.
The solution to the technical nature closest to the proposed Fig�structure and therefore taken by the authors for the closest analogue.
It should be noted that the technical solution can be considered optimal in accuracy only for the tanks and rocket launchers, shells and shots which are composed of inertial navigation systems (hereinafter IRB).
As for cruise missiles, based on SLEEP and having in its composition the management system, the main element of which is an inertial navigation system, this method is rough and requires improvement.
This is due to the following circumstances.
First, the range of cruise missiles is ten times more range of the projectile, which in turn results in a proportional increase of the deviation from the plane of fire.
Secondly, self-propelled launchers with cruise missiles may have, unlike tanks, several individual missiles, the longitudinal axis which, unlike systems of volley fire, because of design features non-parallel to each other.
Thirdly, every missile, unlike unguided shells of tanks and gunfire volley fire, is composed of ince with individual values of passport data.
With the aim of increasing the accuracy and adaptation of the considered method of aiming application in rocket technology, the authors offer�Xia measurements of angular misalignment in the exchange rate between ince missiles and MNST SPU in several stages with regard to the design of the rocket, and how to install MSTO and missiles on the SPU.
The essence of the proposed method consists in measuring the angular misalignments in the exchange rate between the structural elements of the rocket and the SPU for the purpose of obtaining the total angular misalignments in the exchange rate between ince missiles and MNST SPU and the subsequent use of the results of the measurements during prelaunch processing for determining the true azimuth angle of the rocket by calculating corrections to the azimuthal angle measured MSTO.
Fig.2 shows a block diagram of the precision parameters, measurements which are needed in the manufacturing process ince, rockets and SPU. Symbols, names, measurement and storage of the parameters a1- 5shown in the table.
Fig.3, for example, one rocket out of ammunition, was appointed to conduct the shooting, schematically shows the storage of the parameters a1- 5and data communication for the transmission parameters of the a1and2and the azimuthal angle AndMNSTmeasured MSTO 4, the weapons control system (FCS) SPU 3 to calculate the initial azimuthal angle of Ajduring pre-launch.
Before pre-launch parameter a1is transmitted from the ROM ince 1 OBC 2, and thence, together with the parameter and in the MSA SPU 3. At the same time from MSTO 4 in FCS SPU 3 is transmitted to the azimuthal angle, measured MSTO 4. In the MSA SPU 3 with respect to the parameters a3- 5stored in the ROM suo SPU, are calculated:
- amendment to the azimuthal angle measured MSTO, according to the formula:
where j is the number of rocket-space;
- the azimuthal angle for each missile assigned to fire:
where j is the number of rocket-space.
Calculated by the formula (2) the azimuthal angle (Ajtransmitted in OBC 2 rockets, and then to ins 1. After running a prelaunch and launch.
This method allows for the operation of aiming for any rocket that is located on any rocket-any SPU.
To assess the accuracy of the proposed method of aiming was calculated, which showed that the total error in determining the initial azimuthal angle ince missiles satisfies requirements for missiles of this class requirements.
Thus, it can be stated that the invention makes it possible to create a fully automatic method of aiming that meet the accuracy requirements for medium-range missiles. It appears that this method can be used both in newly developed missile complexes and modernization of existing�existing missile weapon complexes.
|METHOD of AIMING CRUISE MISSILES, BASED ON a self-PROPELLED LAUNCHER|
|Parameter name||Symbol||The measurement point||Storage|
|1.||Angular misalignment in the exchange rate between the axes of the ins and seats under ince||a1||The manufacturer ince||ROM|
|2.||Angular misalignment in the exchange rate between the seats under ince of the product and the external docking ports TPN||a2||The manufacturer of the rocket||ROM|
|3.||Angular misalignment in the exchange rate between the longitudinal axis of the TPN and the baseline, about�odama through the centers of the cradle SPU||and3||The manufacturer SPU||ROM|
|4.||Angular misalignment in the exchange rate between the base line passing through the centers of lodgement of the SPU and the longitudinal axis of the chassis SPU||a4||The manufacturer SPU||ROM|
|5.||Angular misalignment in the exchange rate between the longitudinal axis MSTO and the longitudinal axis of the chassis SPU||and5||The manufacturer SPU||ROM|
Method of aiming cruise missiles, based on a self-propelled launcher, including definition of the azimuthal angle of an inertial navigation system of the missile in a known azimuthal corner route-navigation system, topographic location and orientation of self-propelled launchers, distinguishing�I, in the process of making missiles perform preliminary measurement of the angular misalignments between the elements of the design of rockets and self-propelled launchers with subsequent calculation of the total angular misalignment in the exchange rate between the inertial navigation system of the missile and route-navigation system, topographic location and orientation and use of the results of the measurements to automatically calculate the corrections to the azimuthal angle measured route-the navigation system, topographic location and orientation.
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.
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
EFFECT: higher accuracy of fire.
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.
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.
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: 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.
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
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.
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.
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.
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.