Method of data computing system operation of missile and device for its implementation |
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IPC classes for russian patent Method of data computing system operation of missile and device for its implementation (RU 2325306):
                                                  
 Guided shell launch method and the guided shell / 2324142
Shell contains leading cumulative charge, main payload, steering drive unit, placed between them, steer opening mechanism with electroignitor, stabiliser blades. Steer opening mechanism and electroignitor are located in the steering drive unit base, at that, electroignitor is done with powder hinge, which provides steer opening delay after stabiliser blades are opened, equal to 0.25-0.35 sec.
 Anti-aircraft short range guided missile guidance system / 2324139
AA guided missile guidance system comprises target detection radar station, computer, navigation equipment, video monitor, control console, elevating-and-traversing platform with targeting drives and tracking radar station, equipped with phased antenna array, control command transmission channels and target/missile direction finding channels. Each missile contains radio receiving set, transponder, control equipment, whose output is connected to input of steering gear. The command centre additionally contains ray control unit and optoelectronic system, which comprises missile direction finding device, thermophotovisual scope, target tracking automatic system, synchronisation and coding unit.
 Method for warhead action mode switching of guided missile and warhead / 2317513
The methods consists in determination of the presence of the signal of electromagnetic lighting on the target surface at the instant of missile approach to the target and production of the command for warhead action in the required mode according to the presence or absence of the signal of electromagnetic light on the target surface. the warhead has an explosive device, the main explosive charge and a system of initiation of the main charge and an additional charge with a device of its initiation located on its opposite sides, the explosive device is provided with a non-contact pickup for detection of the signal of electromagnetic lighting on the target surface, and the additional charge is separated from the main charge by a damper preventing the transfer of detonation to the main charge.
 Method and device for conservation of energy and data in guided missile / 2316892
According to the invention, the energy and the mission data for the guided missile are transmitted from the missile erector via an induction interface. The guided missile has a capacitor member for reception and storage of electric power transmitted via the induction interface, member for reception and storage of the data transmitted via the interface simultaneously with the electric power in the combination signal of electric power and data. The missile has also a flight battery and a time stabilization system fed from the capacitor member of electric power and the flight battery. The time stabilization system is fed from the capacitor member of electric power storage during loading and salvo, and the flight battery is activated after the missile launch.
 Method for cocking of guided missile on-board system and device for its realization / 2315944
At development, test of guided missiles, as well as in combat conditions in case of an incorrect exit to operation of the homing head the flight of the guided missile in the terminal trajectory leg will proceed without homing guidance, as a result, the fall point will be poorly predicted. Such a situation will result in an enhanced danger of the guided missile, since at tests the guided missile may come out of the zone of authorized operations, as well as in a destruction of awn objectives in combat conditions. According to the invention, at a missile take-off the clockwork mechanism of the missile control system is started, the an-board equipment power supply battery is cocked, the inertial gyroscope is uncaged. On expiration of time t1 set in the clockwork mechanism the homing head power supply batteries are cocked. At an exit to the operating mode of one of the homing head power supply batteries the nose unit is jettisoned, thereby opening the entrance pupil of the homing head on expiration of time t2 set in the clockwork mechanism. The parameters of the homing head are registered, compared with the preset values, at a negative result of the comparison of the registered parameters the control signal of reduction in the vertical coordinate of the control actuator is normalized, which provides an urgent bringing of the guided missile to the ground surface, time t2 is set as a time sufficient for bringing the homing head to the operating condition and yield of its parameters to the preset made after cocking of the homing head power supply batteries, but less than the time of the expected target lock-on.
 Method for modulation of relay control signals or rolling missile and device for its realization / 2315938
Three-position reference periodic missile rolling modulating signals are normalized that are shafted relative to one another by angle π/2. The relay control signals are multiplied by three-position reference periodic missile rolling modulating signals corresponding to them. The device has a gyroscopic sensor of modulating signals containing a commutator consisting of four conducting sector insulated from one another.
 Method for guidance of spin-stabilized missile with relay control actuator and system for its realization / 2310151
According to the invention, forming of modulated radiation on the launcher, reception of the radiation on the missile and generation of control signals in the vertical and horizontal planes, modulation of these signals by signals periodic in missile roll angle are accomplished. Linearization signal, cophased with the signals periodic in roll angle, are formed on condition n=3, with n=ω0/γ where ω0 - the frequency of the linearization signals, γ - spinning speed of missile in rolling. The modulated control signals and the linearization signal are summed up. Forming of the relay two-position signal is performed by determination of the sign of this sum and transduction of the obtained relay control signal to the deflection of the control actuator. The linearization signal up to the moment of the missile sustainer engine starting and after its starting is formed on condition n=3, and during operation of the sustainer engine - on condition n=2.
 Air dynamic package of controllable flying vehicle control actuator / 2309084
Proposed air dynamic package consists of two servo units assembled in rocker arm configuration and kinematically linked with control surfaces; they are provided with distributing devices each of which is additionally provided with second plunger electromagnet. Magnetic circuits of electromagnets are connected by means of common flange fitted with armature common for electromagnets. Armature side surface has two circular grooves which are engageable with holes in flange during operation of actuator. These holes are used for communication of working chambers of servo unit depending on position of armature with high-pressure or low-pressure chamber. Armature and flange form three-way two-position plunger-type air distributor practically excluding the load on plunger caused by pressure of air being distributed.
 Device for launching of guided missile or projectile / 2303235
The device for launching of a guided missile or projectile has a clock mechanism, AND gate, starting component of the launching equipment and single-action components of the missile or projectile in the form of a power supply battery, gyroscope. The device has also a monitoring unit of the parameters of the single-action components of the missile or projectile and a series-connected power source and a contactor. The contactor output is connected to the inputs of the single-action components and the input of the clock mechanism, whose output is connected to the first input of the AND gate, whose second input is connected to the output of the monitoring unit of the parameters of the single-action components of the missile or projectile, and the output of the AND gate is connected to the starting component of the launching equipment. Automatically controlled cyclograms of missile or projectile launching are realized in the device due to the employment of ground-based and on-board single-action systems before launching of the missile or projectile, monitoring of their readiness to functioning, launching of the missile or projectile at a positive result of the monitoring, otherwise repetition of the launching cyclogram from the second missile or projectile.
 Electrohydraulic drive of control system of rockets and armament installations / 2295699
The drive has an adder, whose first input serves as the drive input, and, series-connected to it, a power amplifier, electromechanical converter, hydraulic actuator, throttle gas distributor and a hydraulic motor, whose output serves as the output of the drive kinematically linked with the control object coupled via a feedback element to the second input of the adder, which includes series-connected first correcting filter, first relay element, additional adder, second correcting filter, second relay element and a series-connected current transducer and an inverter, the input of the first correcting filter is connected to the output of the adder, and the output of the second relay element to the input of the power amplifier, whose output via the current transducer and the inverter is connected to the second input of the additional adder.
 Method for fire by guided projectiles with laser semi-active homing head at several targets / 2317504
The method consists in numbering of the guns, determination of the quantity and order of destruction of targets for each target beginning from the first one, measurement of the distance from the target indicator to the target, and of the target azimuth relative to the target indicator. Surveying of each target to the terrain in the reconnaissance console by computation according to the data o target indicator surveying, conversion of the co-ordinates of the targets in the reconnaissance console to a sequence of binary codes and transmission of them through the digital radio communication to the firing position console. Fire-mission setting for each gun is computed in the firing position console according to the co-ordinates of the respective targets and surveying of the respective gun at a computer time common with the reconnaissance console, realization of the fire-mission setting on the gun with the respective number. The shots are accomplished in the order of gun numbering, the command for fire by the next gun is produced by the firing position console according to the following relationship: Тfire i+1=Тshot i+ΔТflight i+ΔTH-Тd.lm. i+1, i=1, 2, ...n, where: Tfire i+1-time of output of fire command at the next target: Тshot i - the instant of shot time at the i-th target; ΔТflight i-the projectile light time to the i-th target; ΔТH-the of target indicator reaming to the next target; ΔТd.lm. i+1-the delay of engagement of target indicator to lighting mode at the i+1-th target; n-the quantity of destructed target. Each shot is fixed in the firing position console, the target indicator after aiming of the projectile on the previous target is transferred to the next rated, and laser emission on each is engaged and disengaged by a signal from the reconnaissance console at attainment of the respective time preset the firing position console.
 Method for normalization of guidance signal of spin-stabilized adjustable artillery projectile with the use of linear-acceleration transducers / 2316711
Linear-acceleration transducers are installed in the longitudinal axis of the adjustable artillery projectile, the apparent projectile accelerations in axes X, Y, Z in the body-axis coordinate system are measured with the aid of them, then, the angles of attack and the slip angles are determined in the on-board computer. The guidance signal of the adjustable artillery projectile is normalized, and the presence of action of g-loads on the adjustable artillery projectile is being monitored at correction of the trajectory with the aid of the linear-acceleration transducers.
 Method of remote control of movable objects / 2315346
Method comprises generating a series of pulses by means of at least one radiation emitter and receiving and filtering reflected pulses in a single timing system.
 Object signing system / 2315255
The system has an image transducer positioned on a stabilized platform installed on a movable base, video-signal processing unit including an analog-to-digital converter and the first memory unit connected to the read-record synchronizing mechanism, platform stabilizing system including a platform angular-rate sensor, differential amplifier, power amplifier and a stabilized platform drive motor, in additional, the system has the first digital filter, addressing unit providing for a shift of signal of the image transducer in the first digital filter, the second digital filter, integrating filter, the second memory unit and digital to-analog converter, the first memory unit is made with the number of cells exceeding the number of resolution elements of the imager transducer.
 Active radar homing head / 2313054
The active radar homing head has a gyrostabilized aerial drive with a monopulse slot aerial installed on it three-channel receiving device, transmitter, three-channel analog-to-digital converter, programmed signal processor, synchronizer, reference oscillator and a digital computer. An the process of processing of the received signals a high resolution of ground targets and a high precision of determination of their co-ordinates (range, speed and target elevation and azimuth) are realized.
 Method for formation of stabilization and homing signal of movable carrier and on-board homing system for its realization / 2303229
Signals are formed that are proportional to the projections of the vector of the phantom linear acceleration and the projections of the vector of the absolute turning speed of the vector (line) of target sighting to the respective co-ordinate axes of the base antenna co-ordinate system. with the aid of the obtained signals with regard to the original information of assignment of the target or/and object of sighting and initial conditions of alignment of the inertial measurement of the parameters of the sighting vector determined are the signals proportional to the current values of the target sighting vector, i.e. the projections of the vector of the absolute linear speed of closure of the movable carrier with the target to the respective co-ordinate axes of the base antenna co-ordinate system, slant range of closure of the movable carrier to the target, components of the space angular target co-ordinate in the base antenna co-ordinate system, guide cosines of the mutual attitude of the base antenna co-ordinate system and the reference geocentric co-ordinate system linked by its, co-ordinate axis to the stationary target of/and to the sighting object located, for example, on the earth surface. At an absence of the location contact with the target or/and with the sighting object the obtained signals are converted to the stabilization signals of the movable carrier from its oscillations relative to its center of masses in the horizontal plane, in the vertical plane and in rolling, as well as to the homing signals of the movable carrier to the target proportional to the g-loads. At a search of the sighting object and at its tracking signals are formed in the main or built-in short-wave wave radiation chamber that are proportional to the components of the space angular co-ordinate of the sighting object and the slant range to the sighting object in the antenna co-ordinate system. An this case signals are determined that are proportional to the parameters of the trajectory fluctuations and the deforming actions of the movable carrier body an the spatial attitude of the antenna phase center relative to the target or/and the sighting object. With the use of these signals a signal is formed that is proportional to the phase of the reference function being the function of the module of the target sighting or/and object sighting vector in the shifted co-ordinate system, i.e. the slant range to the target or/and sighting object. An this case the position of the shifted co-ordinate system is determined by the shift vector of the antenna phase center or/and of the center of radiation of antenna sounding signals relative to the center of intersection of the axes of sensitivity of measurement of the projections of the phantom linear acceleration and the projections of the vector of the absolute angular turning speed of the target (line) sighting and/or sighting object vector in the process of the inertia measurement of the parameters of the target sighting vector, and/or sighting object vector. With the use of the obtained signal that is proportional to the phase of the reference function the signal is determined that is proportional to the phase correction compensating in the received signals reflected from the radiated sighting object for the trajectory instability of the antenna phase center and the deforming actions of the movable carrier body. At an automatic tracking of the sighting object in the direction and range compared are the formed signals proportional to the current parameters of the target sighting vector in the base antenna co-ordinate system in accordance with the identical signals of automatic tracking of the sighting object in the direction and in the range in thus co-ordinate system. Then, accomplished is the optimal adaptive jamproof filtration of the respective comparison signals, and signals proportional to the precise estimations of the respective comparison signals are formed. The signals proportional to the precise estimation are used for correction of the signals proportional to the respective current values of the target sighting vector parameters. These signals are used for turning the vector of sighting in the tilt angle and azimuth relative to movable carrier body up to its matching with the direction to the sighting object, and at an automatic tracking of the sighting object signals are formed that are proportional to the slant range and the rate of closure of the movable carrier to the sighting object. Besides, simultaneously formed are signals that are proportional to the rate of change respectively of the sighting angles of the sighting object in the horizontal and vertical planes in the horizontal co-ordinate system. With the use of the obtained data formed are the signals of stabilization of the movable carrier against its oscillations relative to the center of masses in the horizontal plane, vertical plane and rolling, as well as the homing signals of the movable carrier proportional to the g-loads respectively in the horizontal and vertical planes.
 Method for fire by guided missile with laser semi-active homing head / 2300726
The method consists in the fact that after calculation of the fire settings in the gun azimuth angle, elevation angle and homing head orientation angle up to their realization on the gun on the firing position modeling of the missile flight, comparison of values a(x) and b(x) and generation of the clearance of gun fire at exceeding of a(x) over b(x) arte performed. At b(X)≥a(X) adjustment of the fire settings in the gun elevation angle and homing head orientation angle is performed directly proportional to the gear ratios of K1 and K2 of the missile model and of the difference of b(X') and a(X'). A(x) - the height of the extreme lower trajectory of the missile flight model with due regard for the dispersion at calculated fire settings for horizontal range X from the gun, b(x) - the height of the terrain profile according to the data of the electronic chart for horizontal range x from the gun, X'- the value of horizontal range x at which the value of the difference of a(x) and b(x) would be minimum. K1, K2 - gear ratios of the missile model at range X' for the gun elevation angle and homing head orientation angle respectively.
 Method for formation of descent paths of aeroballistic vehicle of required configuration at guidance to preset point of earth surface / 2296940
The method consists in formation of spiral descent path of the flight vehicle of various configuration. An the process of control of the flight vehicle descent programmed rotation of the required direction of the vector of the flight vehicle terminal velocity in the generating line of the right circular cone with the peak in the target point in the direct or reversed direction with a constant or variable period of rotation is accomplished.
 Passive object range measurement system in guided ammunition / 2295103
A semiactive laser illumination radiator and a photodetective device are positioned on the guided missile. For range measurement on the basis of the stereoscopic base method at a guidance of guided ammunition with a semiactive guidance system on objects use is made of two matrices of the instruments of charge coupling of the receiver of the guidance system that are inclined at an angle of 90 deg. to the "photodetector-object" sighting line.
 Guidance system of guided ammunition by laser radiation reflected from object to be hit / 2293942
The guidance system uses a panoramic lens, which represents a set of fiber-optic bundles of multichannel light-emitting diodes of the anamorphote of focon type, matrix photodetector on instrument with a charge coupling, and an information processing device. The accuracy of direction finding is enhanced with the increase of the quantity of fiber-optic bundles in the panoramic lens, which allows to expand the range of angular displacements of the guided ammunition relative to the "launcher-target" axis in the initial flight leg and enhance the accuracy of guidance to the target in the terminal guidance leg.
 Helmet-carried target designation, sighting and indication system / 2321813
The helmet-carried target designation, sighting and indication system has a device for display of video information, collimator, assembly for output of the video information image to the pilot's field of view, housing with reference mark radiators positioned on the helmet, the helmet is provided with a panel-filter installed for displacement. The system also has optical-location units optically conjugate to the reference mark radiators, and an electronic unit with a computing device. The system is provided with an additional housing placed in which are the device for display of video information made in the form of a microdisplay, and a collimator, the assembly for output of the video information image is rigidly coupled to the additional housing, the additional housing is installed for turning and fixing relative to the housing with reference mark radiators and conjugation of its profiled surface to the edge of the panel-filter.
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FIELD: engines and pumps. SUBSTANCE: essence of the invention comprises in preparing a missile on board launcher-aircraft to an autonomous operation by means of a voltage supply from apparatus of a fighter, also by means of measurement of a target and missile movement parameters, by means of evaluating assessment of required parameters of a relative target and absolute missile movements, by means of a choice of aiming the missile based on the best of one of the criteria under given conditions of application, of computing of mismatch parameters for the chosen method, characterizing the degree of mismatch between actual parameters of missile movement and their required values, of generating a signal for preparation and control of radio proximity fuse. Also emanation and reception of the electromagnetic oscillations are achieved by means of a narrow band scanning in a specified sector against the axis of a missile. Upon missile approaching a target at a distance when a target is becoming dimensional, frequency bands corresponding to oscillation frequencies of target structure components are selected out of spectrum of the signal reflected from the target, then the values of maximum amplitude of the reflected signal are identified in this frequencies band. Then the emission and reception of electromagnetic oscillation in the direction specified against the axis of the missile are fixed, and the component of the target structure with maximum amplitude of vibration is recognized. At a combination of a fixed ray of electro magnetic oscillations with a given structure component a signal is generated to explode an operational portion of the missile upon receiving the signal on the target location against the missile axis and receiving the signal of identification. EFFECT: upgrading of self-descriptiveness. 2 dwg, 7 cl
The invention relates to the field of aircraft guided missiles and can be used to provide information on the functioning of military equipment aircraft guided missile. The known method of functioning of the computer information system (CIS) missiles, which consists in the preparation of missiles on Board the aircraft carrier to the Autonomous operation by feeding the supply voltage of the equipment of the fighter, the configuration of the synchronization and the reflected signal at the frequency of the target illumination, the exercise test all the equipment missiles, determining the readiness of the computer information system of the rocket to work on special control signals supplied to the apparatus fighter in the feedback circuit, the configuration of the datalogger and transmitter to support the goals selected for the defeat of the command target, you can set datalogger and transmitter-to-target tracking, selected to defeat the teams of the target by turning the antenna homing head in the direction of the goal, or to pre-empt point, which will be the purpose at the time of taking it to the auto tracking, implementation teams targeting range DCCand the speed of convergence of VCCthe implementation teams celeo is asani range D CCdetermine methods of targeting and signal illumination purposes, if the radar homing head is used, a continuous signal of the target illumination is the command target speed of convergence of VCC(Doppler frequency), in accordance with which will selectrebates radio signals only that purpose, the rate of convergence which corresponds to the speed of target acquisition, if the radar homing head is used as a pulse signal, illumination purpose, the processing module receives the command target range, in accordance with which the receiver of the reflected signal will be give only on the arrival time of the signals reflected from the target, separated from fighter to a range of DCCwhen a quasi-continuous signal, illumination purposes are served commands for target designation and range and speed, in addition, the command target range, speed of convergence and the angular velocity of the line of sight act as initial conditions in the solvers extraprise parameters relative motion of the missile and the target in offline computing system rockets prior to the target on the trajectory, and in the case of exposure to interference in the measurement of motion parameters of purpose and self-degeneracy, the formation of the assessment of the required parameters relative target motion and absolute motion of the rocket, the choice of method to aim the missile at the target, the best according to some criterion for data applications, the calculation for the selected method parameters mismatch Δ1,2characterizing the degree of mismatch of the actual motion parameters missiles to their desired values, the analysis of the jamming environment and the inclusion of appropriate tools and anti-jamming and nerdythechicken meters, retargeting missiles at the jammer, the analysis of the jamming environment is energy and frequency differences of the signals emitted by the jammer and reflected from the ground or from the goal, when deciding on the membership of the analyzed signal to the intercepted target measures RGS move to its automatic maintenance Doppler frequency performed by autoselection speed and direction, carried out by the goniometer, and radar homing head is translated in the homing mode and signal preparation and management for radio controlled fuses (V.I. Merkulov, Lepin NR. Aircraft radio control system. - M.: Radio and communication, 1997 - s). It is known device, which consists of serial connected antenna and the receiver of the synchronization signal, antenna and receiver of the reflected signal, the module information processing and computer settings mismatch and system for Autonomous sensors, power amplifier and drive the antenna, where the module information processing device consists of search, discovery, selection and analysis of signals, channel estimation of range and speed of convergence, the control channel antenna, and output it mechanically connected to the antenna of the reflected signal, the output of the receiver of the reflected signal is connected to the first input of the module information processing, second, third, fourth, fifth, sixth, seventh inputs of which are respectively connected with the first output of the receiver of the synchronization signals, the first and second the output of the system is Autonomous sensors, with the release of the teams training and designation of the equipment of the fighter, which simultaneously connected to the third input evaluator parameter mismatch with the output of the transmitter of the Autonomous system, the first output of the power amplifier and drive the antenna, the second output of which is mechanically connected to the antenna of the reflected signal, the first, second third, the module outputs information processing are connected respectively to the input control signals and feedback apparatus of the fighter, the first and second input evaluator parameter mismatch, in addition, a second output the receiver synchronization is connected with the second input of the receiver of the reflected signal (V.I. Merkulov, Lepin NR. Aircraft radio control system. - M.: Radio and communication 1997 - s). The disadvantage of these methods and devices is the implementation of the detonation of a missile without regard to the location of one of the affected compartments air targets - propulsion. An object of the invention is to increase the effectiveness of the combat employment of the rocket due to the implementation of the detonation of a missile relative to power plant air targets. The solution of the technical problem is achieved in that in the method of functioning of the information system of the rocket consists in preparing missiles aboard the aircraft carrier to the Autonomous operation by feeding the supply voltage of the equipment of the fighter, the configuration of the synchronization and the reflected signal at the frequency of the target illumination, the exercise test all the equipment missiles, determining the readiness of the computer information system of the rocket to work on special control signals supplied to the apparatus fighter in the feedback circuit, the configuration of the datalogger and transmitter-to-target tracking is selected for destruction by teams of target by turning the antenna homing head in the direction of purpose, or to pre-empt the point at which h is to remain objective in the moment of taking her to the automatic tracking, implementation teams targeting range DCCand the speed of convergence of VCCis determined that the methods used are targeting and signal illumination purposes, if the radar homing head is used, a continuous signal of the target illumination is the command target speed of convergence of VCC(Doppler frequency), in accordance with which will selectrebates radio signals only that purpose, the rate of convergence which corresponds to the speed of target acquisition, if the radar homing head is used as a pulse signal, illumination purpose, the processing module receives the command target range, in accordance with which the receiver of the reflected signal will be give only on the arrival time of the signals reflected from the target, separated from fighter to a range of DCCwhen a quasi-continuous signal, illumination purposes are served commands for target designation and range and speed, in addition, the command target range, speed of convergence and the angular velocity of the line of sight act as initial conditions in the solvers extraprise parameters relative motion of the missile and the target in offline computing system rockets prior to the target on the trajectory, and if the impact is of major on her radio, the analysis of the jamming environment and the inclusion of appropriate tools and anti-jamming and nerdythechicken measures, analysis jamming environment is energy and frequency differences of the signals emitted by the jammer and reflected from the ground or from the goal, when deciding on the membership of the analyzed signal to the intercepted target gauges radar homing head pass to his automatic maintenance Doppler frequency performed by autoselection speed and direction, carried out by the goniometer, and radar homing head is translated in the homing mode, the measurement of motion parameters of the purpose and proper motion of the rocket, the formation of the assessment of the required parameters relative target motion and absolute motion of the rocket, the choice of method to aim the missile at the target, the best according to some criterion for data applications, the calculation for the selected method parameters mismatch Δ1,2characterizing the degree of mismatch of the actual motion parameters missiles to their desired values, the signal processing for the preparation and management of radio controlled fuses, additionally produce radiation and reception of electromagnetic waves by scanning a narrow beam in the set with store relative to the axis of the rocket when approaching missiles to their targets at a distance, when it gets long, separated from the spectrum reflected from a target signal band of frequencies corresponding to the frequencies of the elements of design goals, define in this frequency band the maximum amplitude of the reflected signal, and recording the radiation and reception of electromagnetic waves in a specified relative to the axis of the missile direction, recognize the design element goals, with a maximum amplitude of vibration, the combination of a fixed beam of electromagnetic waves with a given structural element, form the signal at undermining the warhead missiles. The proposed method is implemented in the device for operation of the computing system missiles containing consistently connected the antenna and the receiver of the synchronization signal, the antenna and the receiver of the reflected signal, the module information processing and computer settings mismatch, as well as a system of Autonomous sensors, power amplifier and drive the antenna, where the module information processing device consists of search, discovery, selection and analysis of signals, channel estimation of range and speed of convergence, the control channel antenna, and output it mechanically connected to the antenna of the reflected signal, the output of the receiver of the reflected signal is connected to the first input of the processing information is, the second, third, fourth, fifth, sixth, seventh inputs of which are respectively connected with the first output of the receiver of the synchronization signals, the first and second system output Autonomous sensors, with the release of the teams training and designation of the equipment of the fighter, which simultaneously connected to the third input evaluator parameter mismatch with the output of the transmitter of the Autonomous system, the first output of the power amplifier and drive the antenna, the second output of which is mechanically connected to the antenna of the reflected signal, the first, second third, the module outputs information processing are connected respectively to the input control signals and feedback apparatus of the fighter, the first and second input evaluator parameter mismatch, in addition, the second output of receiver synchronization connected with the second input of the receiver of the reflected signal, characterized in that it has consistently connected to the third antenna and the processing unit, an input connected to the second output of the module information processing, and the output is the output commands to the undermining of a missile. In addition, the processing unit consists of a transceiver unit of the scanning device, a digital to analogue Converter, counter, pulse generator, the first and second element And the first t is higher, the first threshold device, the first unit signals, a differentiating circuit, filter, n second threshold devices, n second trigger, the first n keys, a summing device, the second key, the third threshold device, the second setpoint signal and the second output module information processing connected to the first input of the first threshold device, the second input of which is connected with the first unit signals, and the output of the threshold device is connected both to the input of a differentiating circuit and a second input of the first element And the second input of which is connected with the second trigger output and the third input is connected to the output of the pulse generator, the output of the first element And connected with the second input of the counter, a first input connected with the first trigger output, and a group of outputs connected to the group of inputs of the digital to analogue Converter, the output of which is connected to the input of the scanning device, the first input of which is connected to the third antenna and the second input is connected to the input of the transceiver unit, the output of which is connected to the input filter, the output of which is connected with the first inputs of n second threshold devices, the second inputs of which are connected to the first outputs of the second unit signals, and the outputs from the first to the n inputs of the triggers, the second inputs of which are connected with the output of diff is rancorously circuit, the output of which is connected with the third input of the counter and a second input of the first flip-flop, the outputs of the n first trigger is connected with the first n inputs of the first key, the second outputs of which are connected with the second output of the second combination signal, and outputs through the adder with a first input of the second key, a second input connected to the trigger output and the output with the first input of the second threshold device, a second input connected to the output of the filter, and the output is the output of the shaping unit command to undermine the warhead missiles. New features with significant differences according to the method is the following set of actions. 1. Produce radiation and reception of electromagnetic waves by scanning a narrow beam in a given sector relative to the axis of the rocket when approaching missiles to their targets at a distance, when it becomes long. 2. Highlight of the spectrum reflected from a target signal band of frequencies corresponding to the frequencies of the elements of design goals. 3. Determine in this frequency band the maximum amplitude of the reflected signal. 4. Record the radiation and reception of electromagnetic waves in a specified relative to the axis of the rocket direction. 5. Recognize the design element goals, with a maximum amplitude of vibration, the reconciliation fix the one beam of electromagnetic waves with this design element. 6. Form the signal at undermining the warhead missiles. The essential elements of the device are connected in series, the third antenna and the processing unit, which consists of a transceiver unit of the scanning device, a digital to analogue Converter, counter, pulse generator, the first and second element And the first trigger, the first threshold device, the first unit signals, a differentiating circuit, filter, n second threshold devices, n second trigger, the first n keys, a summing device, the second key, the third threshold device, the second unit signals and connections between known and new elements. Figure 1 shows the structural diagram of the computing system missiles, figure 2 - block processing. Device for operation of the computing system missiles, includes serially connected first 1 antenna and the receiver 2 of the synchronization signal, the second 3 the antenna and the receiver 4 of the reflected signal, module 5 information processing and computer 6 parameters of the error, and system 7 offline sensors, power 8 power and drive the antenna, where the module 5 of the information processing device consists of 9 search, detection, selection and analysis of signals, channel 10 evaluation of the range and the standard deviation is the spine of convergence, channel 11 control antenna, connected in series to the third antenna 12 and unit 13 of the information processing, which consists of a transceiver unit 14 unit 15 scans, digital to analogue Converter 16, a counter 17, the generator 18 pulse, the first 19 and second 20 element And the first 21 of the trigger, the first threshold device 22, the first 23 of the generator signal, a differentiating circuit 24, filter 25, n second threshold device 26, n second trigger 27, the first n keys 28, summing device 29, the second key 30, the third threshold device 31, the second unit signals 32 and the output of the channel 11 of the antenna control mechanically connected with the antenna 3 of the reflected signal, the output of the receiver 4 of the reflected signal connected to the first input module 5 information processing, second, third, fourth, fifth, sixth, seventh inputs of which are respectively connected with the first output of the receiver 2 of the synchronization signals, the first and second system output 7 auxiliary sensors with output commands training and designation of the equipment of the fighter, which simultaneously connected to the third input of the transmitter 6 parameters mismatch, with the output of the transmitter of the Autonomous system, the first amplifier output 8 power and drive the antenna, the second output of which mechanically connected to the antenna 3 of the reflected signal, if e is ω first, the second third, the outputs of module 5 information processing are connected respectively to the input control signals and feedback apparatus of the fighter, the first and the second input of the transmitter 6 parameters mismatch, in addition, the second output of the receiver 3 synchronization connected with the second input of the receiver 4 of the reflected signal, in addition, the second output module 5 information processing connected to the first input of the first threshold device 22, the second input of which is connected to the output of the first 23 of the generator signal, and the output of the threshold device 22 is connected both to the input of the differentiating circuit 24 and a second input of the first 19 And second input which is connected to the second output of the first 21 of the trigger, and the third input is connected to the output of the generator 18 pulses, the output of the first 19 of the element And is connected to a second input of the counter 17, the first input of which is connected to the first output of the first 21 of the trigger, and a group of outputs connected to the group of inputs of the digital to analogue Converter 16, the output of which is connected to the input of the scanning device 15, the first output of which is connected to the third antenna 12, and a second output connected to the input of the transmitting-receiving unit 14, the output of which is connected to the input of the filter 25, the output of which is connected with the first inputs of n 26 second threshold device, second input which is connected with the first output and the second knob 32 signals, and the outputs from the first to the n inputs of the second 27 triggers, second input which is connected to the output of the differentiating circuit 24, the output of which is connected with the third input of the counter 17 and a second input of the first 21 of the trigger, the outputs of the n second 27 triggers connected with the first inputs of the first n 28 keys, the second outputs of which are connected with the second output of the second 32 knobs signals, and outputs through the adder 29 is connected to the first input of the second 30 key, a second input connected to the output of the first 21 of the trigger, and the output from the first input of the second threshold device 31, the second input is connected to the output of the filter 24, and the output is the output of the unit 13 of the information processing. The device operates as follows. The operation of the IVS missiles "in-in" is performed in the following modes: targeting, search and target detection when capturing it on trajectory formation parameter mismatch and the formation of a team to undermine the warhead missiles. The first two modes are preparatory, and actually homing and the formation of a team of undermining of a missile is in the third mode. Mode designation (CC) of the apparatus fighter in module 5 processing information received team training missiles to work, and commands CC (1). Command training serves as the supply voltage is TDF, configure the receivers 2, 4 synchronization channel and the reflected signal at the frequency of the signal of the target illumination (SOC) and tested the efficiency of the entire equipment of the rocket. Command HQ meters and flow computers are prepared to support the goals selected for destruction. In accordance with these teams antenna 3 homing head turns in the direction of the goal, or to pre-empt point, which will be the purpose at the time of taking it to the auto tracking. Teams targeting range DCCand the speed of convergence of VCCdetermined by the method of targeting and signal illumination of target. If the radar homing head (RGS) is continuous SOC, command HQ on the speed of convergence of VCC(Doppler frequency), in accordance with which will selectrebates radio signals only that purpose, the rate of convergence which corresponds to the speed of target acquisition. If CSG is used the pulse of the SOC, the processing module 5 receives the command HQ in range, in accordance with which the receiver of the reflected signal will be give only on the arrival time of the signals reflected from the target, separated from the fighter to the desired range of DCC. When quasi SOC serves the team HQ and in range and speed. In addition to t the th, command HQ in range, speed of convergence and the angular velocity of the line of sight act as initial conditions in the solvers extraprise parameters relative motion of the missile and target in offline mode IVS prior to the target on the trajectory, and in the case of exposure to radio interference. The willingness of the IVS to the work is controlled by a special control signal received in the apparatus fighter in the feedback circuit (figure 1). It should be noted that depending on the type of signal, illumination of the target (SOC) search and selection of the signal reflected from the intercepted goals are different. After convergence in time tracking Polustrovo rangefinder and pulse uCreflected from the target, the search stops and the task of detection. In the process of solving this problem is the accumulation of signals, with the objective to increase the probability of correct detection. If the decision is made to set the detected signal intercepted goal, then the measure of the IVS go into automatic target tracking in range and direction, and IVS into the mode of formation parameter mismatch (homing) and team formation to undermine the warhead missiles. In this mode, in the ranging channel 10 are formed assessment of the Evaluation Evaluation If the rocket is induced by the algorithm in the form of an expression:
where D0value range at start of homing, Dto- range end of the homing Knowledge evaluation The starting point for the evaluation of range set the pulses of theology, received by the receiver 2 of the synchronization signals via the antenna 1. In space (direction) purpose selectively due to the directional properties of the antenna 3 by its rotation in the direction determined by the estimated angles When continuous SOC for selection of signals reflected from the target, is used Doppler frequency FDCproportional to the velocity of approach of the missile with the target. In semi-active RGS frequency FDCstands out as the difference between the frequencies of the two signals. One of them, reflected from the target adopted by the antenna 3 AndOSand amplified in the receiver 4 of the reflected signal contains a Doppler shift frequency due to the speed of convergence of the fighter with the purpose and objectives of the missile. The second signal ucadopted by the antenna 1 and enhanced receiver 2, contains the Doppler frequency offset, caused by the speed of removal of the missiles from fighter. After subtraction of the frequencies of the signals in receivers 4, 2 reflected and synchronizing signals, a signal is generated, the search and selection which is performed in the processing module 5. When the distance Dp≤DCsearch this signal is relative to the frequency FCC=2VCC/λ, which is set by the command targeting VCCspeed, measured in radar fighter. If Dp>DCthe search is performed with respect to the frequency When deciding on the membership of the analyzed signal to the intercepted target measures RGS move to its automatic maintenance Doppler frequency performed by autoselection speed (channel 10 evaluation of Vsat), and in the direction undertaken by the goniometer, and RGS is translated in the homing mode. The assessment generated by autoselection speed by measuring the Doppler frequency FDCcomes in the transmitter 6 parameters mismatch for implementing the methods of guidance. Angular channel 11 in continuous SOC functions in the same way as when a pulse signal with businesswomen awards. When using quasi-CW signal search and selection of goals is made as range and Doppler frequency. After switching to automatic target tracking in range, speed and direction of device evaluation D and Vsatform of assessment range When quasi SOC necessary to resolve the ambiguity of the reference range, since the delay time of the reflected signal may be greater than the pulse repetition period of the SOC. If you cannot provide unambiguous reference range is not evaluated and the tracking on it is not implemented. In this situation, the reflected signal selectively not in range, and the repetition period that also allows you to provide Gating of the receiver on the arrival time of the reflected pulses. The feasibility of this method due to the fact that when calculating the parameters of the error does not require knowledge of the current range. The principle of operation of the angular channel 11 remains the same as when using the SOC of other types. Included in the system 7 offline sensors measuring parameters of self-motion (see figure 1), which include first of all the accelerometers and gyroscopes that provide information about the longitudinal and transverse accelerations jxand j1,2and the corners of the pitch ϑ and yaw ψ. Based on measurements of the longitudinal jxand transverse j1,2accelerations in the Autonomous computer systems are modelled estimates The definition of the power unit on the body of the target is performed based on the scan target narrow electromagnetic beam at the approach of the missile to the target at a specified distance. From the second output module 5 information processing signal proportional to range, is fed to the first input of the first threshold device 22, to the second input of which receives the output signal of the first 23 of the unit signals. In the case of reducing the signal level to the specified level of output of the threshold device 22 is removed signal and the output element AND-NOT there is a signal, which is supplied simultaneously to the input of the differentiating circuit 24 and the first input of the first 19 item I. From the output of the differentiating circuit 24, the signal "reset" is supplied to the third input of the counter 17, the second input of the first 21 of the trigger, the second inputs of the n - second 27 triggers, ensuring the readiness of data elements to work. On the second and third input element And receives signals respectively from the second output of the first 21 trigger generator 18 pulses. With the release of their first 19 element And the signal at the second input of the counter 17, at the first input of which receives the signal from the first output of the first 21 of the trigger. With a group of outputs of the counter 17 via the d / a Converter 16, peroyvind scanning device 15, the signal received at the input of the third antenna 12, which provides the radiation of electromagnetic energy into space through the second output of the scanning device output transceiver unit 14. Reflected from the target signal through a third antenna, scanning device, the transceiver device, the filter 25 is supplied to the first input n - 26 second threshold device, the second input of which receives the signal from the first output of the second knob 32 signals. In case of exceeding the level of the reflected signal is triggered n - 27 second trigger, outputs n - 27 second trigger signal at the first input n - 28 keys, the second outputs of which receives the signal from outputs of the second knob 32 signals, outputs the key signal through the adder 29 is supplied to the first input of the second 30 key to the second input of which receives the output signal of the first 21 of the trigger from the output of the key signal is supplied to the first input of the second threshold device 31, the second input of which receives the signal from the output of the filter 24, and the output is the output unit 13 of the information processing. Thus, along with guided missiles at the target provides the location on the body of the target propulsion units and formed a team for the undermining of a missile relative to the vital unit. Sources of information 1. Merkulov, V.I., Lepin NR. And ezinye radio control system. M.: Radio and communication, 1997 - c.201 (prototype). 1. The method of functioning of the information system of the rocket, including the preparation of missiles on Board the aircraft carrier to work, the measurement of motion parameters of the purpose and proper motion of the rocket, the formation of the assessment of the required parameters relative target motion and absolute motion of the rocket, the choice of method to aim the missile at the target, the best according to some criterion for data applications, the calculation for the selected method parameters mismatch, characterizing the degree of mismatch of the actual motion parameters missiles to their desired values, the signal processing for the preparation and management of radio controlled fuses, characterized in that produce radiation and reception of electromagnetic waves by scanning a narrow beam in a predetermined sector relative to the axis of the rocket, when approaching missiles to their targets at a distance, when it becomes dimensional, isolated from the spectrum reflected from a target signal band of frequencies corresponding to the frequencies of the elements of design goals, define in this frequency band the maximum amplitude of the reflected signal, and recording the radiation and reception of electromagnetic waves in a specified relative to the axis of the missile direction, recognize the element of design goals with maximum whom he amplitude of the vibration, and when combined fixed beam of electromagnetic waves with this element of the design form the signal at undermining the warhead missiles. 2. The method according to claim 1, characterized in that the preparation of missiles for operation aboard the aircraft carrier is carried out by feeding the supply voltage of the equipment of the fighter, configuration synchronization, and the reflected signal at the frequency of illumination of target, testing the efficiency of the equipment missiles, determining the readiness of the computer information system of the missile to control signals received at the apparatus fighter on circuits feedback, training measures and an evaluator to support the goals selected for the defeat of the command target. 3. The method according to claim 2, characterized in that the preparation of the datalogger and transmitter to support the goals selected for the defeat of the command target, carried out by turning the antenna homing head in the direction of the goal is either to pre-empt point, which will be the purpose at the time of taking it to the auto tracking, executing commands, targeting range and speed of convergence. 4. The method according to claim 3, characterized in that the command target range form depending on the method of targeting and signal illumination purposes, in this case, if the radar homing head use continuous signal target illumination, then form a team of targeting on the speed of convergence, according to which selectrow radio signals only that purpose, the rate of convergence which corresponds to the speed of target acquisition, if the radar homing head using a pulse signal, illumination purpose, the processing module serves the command target range, in accordance with which the receiver of the reflected signal will be give only on the arrival time of the signals reflected from the target, separated from the carrier aircraft at a range of targeting, with a quasi-continuous signal target illumination create teams for target designation and range, and speed, this command target range, speed of convergence and angular velocity of the line of sight serves as initial conditions in the solvers extraprise parameters relative motion of the missile and the target in offline computing system rockets prior to the target on the trajectory, and in the case of exposure to radio interference. 5. The method according to claim 1, characterized in that when making decisions about facilities of the reflected signal to the intercepted target gauges radar homing head pass to his automatic maintenance Doppler frequency performed by autoselection speed IPO direction, performed by a goniometer, and radar homing head is transferred to the homing mode. 6. Device for operation of the computing system missiles containing consistently connected the antenna and the receiver of the synchronization signal, the antenna and the receiver of the reflected signal, the module information processing and computer settings mismatch, as well as a system of Autonomous sensors, power amplifier and drive the antenna and the module information processing device consists of search, discovery, selection and analysis of signals, channel estimation of range and speed of convergence, the control channel antenna, the output of which is mechanically connected with the antenna of the reflected signal, the output of the receiver of the reflected signal is connected to the first input of the module information processing, second, third, fourth, fifth, sixth, the seventh, the inputs of which are respectively connected with the first output of the receiver of the synchronization signals, the first and second system output Autonomous sensors, with the release of the teams training and designation of the equipment of the fighter, which simultaneously connected to the third input evaluator parameter mismatch with the output of the transmitter of the Autonomous system, the first output of the power amplifier and drive the antenna, the second output of which is mechanically connected to the antenna is Draginovo signal, the first, second, and third outputs of the module information processing are connected respectively to the input control signals and feedback apparatus of the fighter, the first and second input evaluator parameter mismatch, while the second output of receiver synchronization connected with the second input of the receiver of the reflected signal, characterized in that it is provided with a series-connected to a third antenna and a processing unit, an input connected to the second output of the module information processing, and the output is output to the formation of the team at undermining the warhead missiles. 7. The device according to claim 6, characterized in that the processing unit consists of a transceiver unit of the scanning device, a digital to analogue Converter, counter, pulse generator, the first and second elements And the first trigger, the first threshold device, element or NOT, the first unit signals, a differentiating circuit, the filter, the second threshold devices, the second trigger, the first keys, a summing device, the second key, the third threshold device, the second setpoint signal and the second input module data processing connected to the first input of the first threshold device, a second input connected to the first unit signals and the output of the first threshold at which trojstva through the element AND IS NOT connected both to the input of the differentiating circuit and the first input of the first element And the second input is connected with the second trigger output and the third input is connected to the output of the pulse generator, the output of the first element And is connected to a second input of the counter, a first input connected to the first trigger output, and a group of outputs of the counter are connected with a group of inputs of the digital to analogue Converter, the output of which is connected to the first input of the scanning device, the second input/output of which is connected to the third antenna, and the third input/output connected to the first input/output transceiver unit, the second output of which is connected to the input of the filter, the output of which is connected with the first inputs of the second threshold device, the second the inputs of which are connected to the first outputs of the second setpoint signal, and outputs the first input of the second trigger, the second inputs of which are connected with the output of the differentiating circuit, the output of which is connected with the third input of the counter and a second input of the first trigger, outputs the second trigger is connected with the first inputs of the first key, the second outputs of which are connected with the second output of the second unit signals, and outputs the first key through the adder connected to the first input of the second key, a second input connected to the first trigger output and the output with the first input of the third threshold device, a second input connected to the output filter is a, and the output of the third threshold device is an input unit of the formation team at undermining the warhead missiles.
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