Method for remote orientation of moving objects

FIELD: physics, instrument-making.

SUBSTANCE: method for remote orientation of moving objects includes formation of orthogonal raster by row-wise, forward and counter reverse scanning of a laser beam with duplication of forward scanning, between which given time delays during radiation extinction are maintained in each row. Given time delays are maintained in each row between scanning instances, said time delays enabling to identify row number with a defined position of an object in the information field.

EFFECT: invention increases the rate of transmitting information in remote orientation systems by reducing the amount of raster needed when forming an information field.

2 dwg

 



 

Same patents:

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: transport.

SUBSTANCE: invention relates to space engineering and may be used in approach, buzzing, hovering, docking jobs etc using robotic systems. Device comprises casing, radiation source, flat diffraction gratings and outlets. Four planes of flat diffraction gratings are perpendicular in pairs, two of them intersect at right angle to axis extending through common radiation source and parallel with passive spacecraft construction axis while remaining two make the angle of 0 to 90 degrees with the axis.

EFFECT: decreased loads at docking assemblies.

4 dwg

FIELD: instrument making.

SUBSTANCE: invention is designed for shaping of information field of laser teleorientation and navigation systems, optical connection, and can be used at control, landing and docking of airborne vehicles, escort of ships through narrow zones or bridge sections, remote control of robotic devices in zones that are dangerous for human health, etc. The proposed method is based on scanning by means of acoustooptical deflectors of the laser emission with a pencil-beam directional pattern; at that, laser beam movement trajectory provides formation both of information frames used for measurement of the controlled object coordinates, and command frames used for transfer of additional commands to the controlled object. The peculiar feature of the method is simultaneous formation of two lines of the information raster, which are displaced relative to each other by N/4 lines, by alternating formation of single cycles in the first line and then in the second line, where N is number of lines in a raster.

EFFECT: improving informativity of laser teleorientation system owing to increasing the repetition frequency of information and command rasters in information field of laser teleorientation system by reducing the duration of time delays between cycles, and owing to reducing light losses.

4 dwg

FIELD: physics.

SUBSTANCE: scanning laser beacon has a housing, a laser light source mounted in a scanning unit, a base and an axle. The device includes an anamorphic optical system mounted in the scanning unit on the same optical axis as the laser light source. The axis around which the scanning unit rotates lies at an angle of 120° to said optical axis, and the anamorphic optical system is a wide-angle lens in a section perpendicular to the scanning direction, said lens having a 90° field of view. A rotating drive, which is in mechanical connection with the scanning unit, rotates in the scanning plane.

EFFECT: possibility of detecting a passive spacecraft in half the solid angle at distances of up to 160 km when pointing an active spacecraft on said passive spacecraft.

3 dwg

FIELD: physics.

SUBSTANCE: scanning laser beacon has a housing and a laser light source mounted in a scanning unit in a gimbal suspension. The device includes an anamorphic optical system mounted in the scanning unit on the same optical axis as the laser light source. The axis of the gimbal suspension is perpendicular to said optical axis, and the anamorphic optical system is a fisheye lens in a section perpendicular to the scanning direction. A swinging drive, which is in mechanical connection with the scanning unit, swings in the scanning plane.

EFFECT: possibility of detecting a passive spacecraft in half the solid angle at distances of up to 160 km when pointing an active spacecraft on said passive spacecraft.

3 dwg

FIELD: physics, navigation.

SUBSTANCE: invention relates to instrument making and is intended for generation of data field of laser teleorientation systems (DF LTS) and navigation, optical communication, and can be used in control, landing and docking of aircraft, etc. continuous length-adjusted laser radiation band is generated as well as delay between three scanning cycles originating in object banking is generated by a certain law, the object accommodating control field generation system.

EFFECT: control over object with no zones wherein object laser control does not exist, scissors-like laser radiation directional pattern.

4 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

How teleobiettivi // 2117311
The invention relates to laser technology and is intended for the formation of the information field systems telecontrol moving objects

The invention relates to the instrument and is intended for the formation of the information field of laser systems teleobiettivi

The invention relates to the instrument and is intended for the formation of the information field of laser systems teleobiettivi and navigation, optical communication and can be used when running, landing and docking of aircraft, navigation through narrow or sections of bridges, remote control robotic devices are dangerous to humans zones, etc

FIELD: physics, optics.

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

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

2 cl, 2 dwg

FIELD: military hardware.

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

EFFECT: higher accuracy.

3 dwg, 1 tbl

FIELD: physics, optics.

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

EFFECT: high efficiency of conducting tests.

3 dwg

FIELD: weapons and ammunition.

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

EFFECT: higher accuracy of fire.

2 dwg

FIELD: weapons and ammunition.

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

EFFECT: improving correction efficiency of flight trajectory.

16 cl, 4 dwg

FIELD: instrument making.

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

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

2 cl, 2 dwg

FIELD: weapons and ammunition.

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

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

2 dwg

FIELD: weapons and ammunition.

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

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

3 cl, 3 dwg

FIELD: weapons and ammunition.

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

EFFECT: higher noise immunity.

2 cl, 2 dwg

FIELD: weapons and ammunition.

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

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

2 cl, 6 dwg

FIELD: 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

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