Guided missile firing method

FIELD: weapons and ammunition.

SUBSTANCE: performed is topographic control of target indicator and launching facility to the terrain by ground satellite receiver, determined are coordinates of launching facility and location and ephemeris for each space vehicle of satellite positioning system, detected and measured are target coordinates, the coordinates are transmitted to artillery position control station, set is universal computer time in reconnaissanceman's console and artillery position control station, calculated and transmitted are shooting settings to launching facility automatic control unit, performed is missile launching procedure, the missile is launched from transporter-launcher container along the preset ballistic course, the missile is oriented by on-board navigation satellite receiver, when the missile approaches the target it is oriented by laser emitter.

EFFECT: providing higher probability of guided missile hitting the target.

 

The invention relates to the field of control and regulation, and more specifically to a managed service.

The invention is intended to control the firing guided missiles with launchers.

There is a method of shooting [Patent RU No. 2468327 from 27.11.2012, MPK7 F41G 5/00, 7/22 - the Way of firing a guided missile with semi-active laser homing head], which consists in the following. The firing position (launcher) is located at a great distance from the line of contact with the enemy. To the line of battle of contact sent a scout with laser designator - rangefinder (LCD), satellite navigation equipment, digital radio and the remote scout, and outputs LCD, satellite navigation equipment and digital radio stations via the connectors connected to the remote reconnaissance, the commander of the firing position has a remote control firing position with satellite navigation equipment and digital radio. Using satellite navigation equipment are determined by the coordinates of the LCD and are entered into the console scout. In the remote control firing position with satellite navigation equipment are entered coordinates launchers. Scout with LCD produces measurement target range, azimuth and elevation angle of the target relative to the target designator. The results of measurements n is Reduta in remote scout, converted to a rectangular coordinate system, are displayed on the screen of the remote scout and transmitted to the remote control firing position on digital radio channel. In the remote control firing position using the received radio coordinates of targets, the measured coordinates launchers are calculated installation of fire for guided missiles and launchers. Designed installation for digital communication channel is transmitted to the automation unit launchers and later in electronic equipment guided missile. Provide guidance launchers on the azimuth angle and elevation angle. The operator control position issues on the launcher command on the start, where there is a missile launch.

At the time of launch on the remote control firing position is read starting time on timers hours single time. The message about the fact of shots and time on LCD mode target illumination is transmitted through a digital channel radio remote control firing position on the panel of the scout, where when the required time is given in LCD signal to switch on the laser radiation that is used for guidance of the guided missile on the target.

The disadvantage of the prototype is that in this way pointing missiles at the target for implementation through the Xia only signals with laser homing head when the illumination of target laser target designator, that happens only in the terminal phase of flight path of the missiles, and up to this point, the missile can withstand the direction towards the goal only under the control of the gyroscopic system that when firing at long ranges may not provide an output missiles in the target area and cause a miss.

The task of the invention is to improve the reliability of hitting a target by implementing a three-step method of controlling the rocket.

This object is achieved due to the fact that in the known method of firing guided missile, including topographic binding designator and launchers to the terrain, the detection of a target designator, the dimension designator target coordinates and transfer them to the remote control firing position, setting a single computer time in the cockpit of the scout and the remote control firing position, the remote control firing position units firing guided missiles and launchers, the transmission of the firing settings on the launcher and the rocket in the automation unit launchers and missile guidance missile launchers, serve with remote control firing position in the automatic block launcher commands on start-up and production start with fixing the moment of its production, transmission from the remote control firing position on the panel of the scout is on the digital communication channel on-time laser target designator, automatic sending of remote spy in the designator of the enable signal of laser radiation for achieving the required time, the guidance of the guided missile on the target, illuminated laser target designator, what's new is that topprivate launchers perform ground satellite receiver with simultaneous determination of location coordinates launchers and ephemeris for each space unit satellite positioning system, when the transmission of the firing settings in guided missile additionally pass target coordinates and the ephemerides of the satellite constellation, the guidance of the guided missile on the target is carried out in three stages: in the first phase after start-up and release of the missile from the transport-launch container, the missile flies in a given ballistic trajectory, the second stage guidance control rocket trajectory is carried out under control of the onboard navigation satellite receiver in the third phase when approaching the target, the guidance is on target, illuminated laser target designator on signals from laser homing head, and the first step guidance on-Board navigation satellite receiver rocket begins to determine position coordinates of the rocket on the ephemeris entered before uscom.

Firing control guided missile with launcher on the proposed method is as follows.

Using satellite navigation equipment cockpit firing position determine location coordinates launchers and ephemeris for each space unit satellite positioning system.

To the remote control firing position, for example, via interface GOST R 520070-2003 connects the automation unit launchers. Launcher is charged with her missiles can be at a distance of 100 m from the remote control firing position. In addition, the remote control firing position connects a set of communication tools, which provides a digital communication channel with the scout while they are on the command-observation post at a considerable distance from the firing position to the target area. The scout has a remote scout connects to the designator and a set of communication tools. Spy remote spy determines location coordinates, using the pointer detects a target and enters the target coordinates in the polar coordinate system in the remote agent. The target information is transmitted through a digital communication channel to the remote control firing position. In the remote control firing position, the upper margin of the installation are stated shooting targets for launchers and guided missiles.

On command from a remote control firing position on a digital communication channel with automatic block launcher is remote training guided missile launch, which includes the following operations: applying voltage to the selected guided missile, transmission and recording in electronic equipment missiles designed installations of fire.

When the transmission of the firing settings in guided missile additionally pass target coordinates and the ephemerides of the satellite constellation. Information about the ephemeris of the satellite constellation of electronic equipment guided missile is passed to the onboard navigation satellite receiver, who immediately when power goes out in the mode of determining location coordinates of the rocket without losing time searching for satellites.

Formed the permission to start and the team to start automatically start the guided missile.

At the time of launch on the remote control firing position automatically and remotely recorded start time by polling the corresponding contacts of the presence of the rocket on the launcher. With the remote control firing position on a digital communication channel to a remote scout is transferred on-time laser target designator.

Targeting guided missile at the target is carried out in three stages.In the first phase after start-up and release of the missile from the transport-launch container, the missile flies in a given ballistic trajectory, while onboard navigation satellite receiver begins to determine the current location of the missile in a few seconds after exiting the container through commissioning before starting the rocket information about ephemeris for each space unit satellite positioning system.

In the second stage guidance control rocket trajectory is carried out under the control of the onboard navigation satellite receiver. When this adjustment of the trajectory of the rocket based on the current location of the rocket and entered before the start of the information about the coordinates of the target.

The designator is automatically enabled in the mode of the target illumination by laser radiation at a given point in time, while the missile is in the target area. Begins the third stage pointing missiles at the target, illuminated laser target designator, the signals from the laser semi-active homing head.

To implement the described method can be used with apparatus described in the patent [Patent RU No. 2468327 from 27.11.2012, MPK7 F41G 5/00, 7/22 - the Way of firing a guided missile with semi-active laser homing head].

The use of the present invention will allow aiming of the missile into the target not only signals the laser semi-active homing head, but the signal is m onboard navigation satellite receiver, that will increase the likelihood of hitting a target. The effectiveness of the method is tested on the mock-up sample of the guided missile.

The way of firing a guided missile, including topographic binding designator and launchers to the terrain, the detection of a target designator, the dimension designator target coordinates and transfer them to the remote control firing position, setting a single computer time in the cockpit of the scout and the remote control firing position, the remote control firing position units firing guided missiles and launchers, the transmission of the firing settings on the launcher and the rocket in the automation unit launchers and missile guidance missile launchers, serve with remote control firing position in the automatic block launcher commands on start-up and production start with fixing the moment of its production, transmission from the remote control firing position on the panel of the scout on the digital communication channel on-time laser target designator, the automatic sending of remote spy in the designator of the enable signal of laser radiation for achieving the required time, the guidance of the guided missile on the target, illuminated laser target designator, wherein topprivate starting ustanavlivaetsya terrestrial satellite receiver with simultaneous determination of location coordinates launchers and ephemeris for each space unit satellite positioning system, when the transmission of the firing settings in guided missile additionally pass target coordinates and the ephemerides of the satellite constellation, and the guidance of the guided missile on the target is carried out in three stages: in the first phase after start-up and release of the missile from the transport-launch container pointing perform on a given ballistic trajectory, the second stage guidance control rocket trajectory is realized under control of the onboard navigation satellite receiver, at the third stage when approaching goals provide guidance on the purpose, illuminated laser target designator on signals from laser homing head, and the first step guidance using the on-Board navigation satellite receiver missiles begin to determine location coordinates of the rocket on the ephemeris, entered before you start.



 

Same patents:

Guided shell // 2537357

FIELD: weapons and ammunition.

SUBSTANCE: shell is made based on the canard configuration. The shell comprises an air-dynamic steering gear in the front section of the shell housing and aerodynamic control elements - steering wheels with pylons mounted in front of them. The air-intake devices of the air-dynamic steering gear are incorporated in the pylons and made in the form of bi-plane U-shaped plates with converting into the monoplane along the rear edge. In the front edge of the pylon the U-shaped hole is made and the hole in the shell housing is made.

EFFECT: increase in efficiency of the shell operation.

2 cl, 6 dwg

FIELD: transport.

SUBSTANCE: proposed set of inventions relates to military equipment, namely to method and means for parachute and fastened to it container packing. Method for packing parachute and fastened to it container with useful equipment into grenade body head includes packing of parachute canopy, shroud lines and metal extension (if present) into grenade body head. When parachute canopy is packed it is used to form dome in the grenade body head by means of special appliance. The major portion of canopy material is placed at side wall of dome. Portion of shroud lines of parachute adjacent to its canopy is wound as spiral onto the rod placed in concavity of dome. Appliance for packing parachute and fastened to it container with useful equipment into grenade body head is formed by body which consists of two coaxial and installed one inside the other bushings and by rod freely accommodated in the channel of inner bushing. On the outer bushing, at its front butt end on the outside fascia is made which centres it in grenade body head. On the inner bushing, at the side of its front butt end, outer diametrical lowering is made on which radial-longitudinal grooves are made which are symmetric to end slots of outer bushing and spaced from front butt end of inner bushing by minimum distance.

EFFECT: higher reliability of parachute deployment.

3 cl, 4 dwg

FIELD: weapons and ammunition.

SUBSTANCE: invention refers to military equipment and may be used for development of missile take-off from container. Onboard command device includes power source, electrically connected to catapult device, first-stage engine, servo units through normally closed switches, switch interacting with dummy outcome sensor, unit of engine start time delay relative to the moment of outcome sensor action, two parallel chains with inverter for supply of electric signal of required polarity to servo units.

EFFECT: providing non-use of control system for take-off and dummy displacement from take-off position.

2 dwg

FIELD: weapons and ammunition.

SUBSTANCE: invention relates to methods for hitting of underwater targets. The method to hit underwater targets consists in delivery of a detachable warhead of underwater action to a target location area, separation of a warhead in the end section of flight trajectory and its actuation after landing on water. The detachable warhead is delivered by the first missile. Prior to delivery of the warhead to the target location area, they deliver one radio hydroacoustic buoy. The buoy is delivered by the second missile. After buoy landing on water, as the first missile gets closer to the area of target location, by means of equipment placed on it, they provide for reception of information from the buoy on location of the target, and the point of warhead landing on water is corrected. Cruise missiles are used for delivery of the warhead and buoy to the area of target location. The cruise missile is equipped with a sustainer power plant with an air jet engine. The speed of acceleration of each missile by a speeding device in the initial section of the trajectory is limited by the value sufficient for development of an aerodynamic lifting force that sustains the flight and to start the sustainer engine, afterwards they provide for its separation from the speeding device, start of the sustainer engine and further flight to the area of target location in the atmosphere. Correction of the point of warhead landing on water is carried out due to correction of the trajectory of the first missile flight by confirmed coordinates of the target and separation of the warhead closer to the target.

EFFECT: invention provides for reduced mass of a missile complex.

4 cl, 2 dwg

FIELD: weapons and ammunition.

SUBSTANCE: underwater target hitting method consists in supply to a target location area of an underwater action separated warhead and one hydroacoustic buoy by means of a missile using an acceleration device, separation of the warhead in the final section of the flight trajectory and its involvement after splashdown. Before the underwater action warhead is separated, one hydroacoustic buoy is separated, and after its splashdown, by means of equipment arranged on the missile there provided is a reception via a radio channel of information from the hydroacoustic buoy on a target location. A point of splashdown of the underwater action warhead is corrected as per the received information. In order to deliver the separated underwater action warhead and one hydroacoustic buoy to the target location area, a cruise missile is used. The missile is provided with a propulsion power plant with an air-jet engine. The missile acceleration velocity in the initial section of the trajectory is restricted by a value sufficient for the creation of an aerodynamic lift supporting the flight and for the start of a cruise engine, after which there provided is its separation from the acceleration device, the start of the cruise engine and further flight to the location area of the target in the atmosphere.

EFFECT: reduction of the weight of an underwater target hitting device.

3 cl, 1 dwg

Munition // 2529236

FIELD: weapons and ammunition.

SUBSTANCE: munition comprises body with tail part, drop-out supports of stabilising fins and articulation of supports with body tail part. Said tail part is shaped to truncated cone with radial lengthwise grooves. Said drop-out supports of stabilising fins are made of rolled sheet are partially fitted in said radial lengthwise grooves and having holes on body bottom side. Said grooves are open on body bottom side. Elements of articulation of supports with body tail part are composed of circular groove made at body tail nearby its bottom and split ring made of round spring rolled steel. Ring is fitted in both circular groove and holes of supports. Supports feature rolled sheet bend-off made along its extreme chord. Body tail part material nearby circular ring is locally strained to split ring generatrix.

EFFECT: simplified design.

2 cl, 2 dwg

FIELD: transport.

SUBSTANCE: invention relates to control over the flight path of bodies flying at high speeds including orbital velocities. In compliance with proposed method, this system can be used as a backup (standby) path correction system for missiles with failed guidance system. Besides, it can be used at minor bodies whereat installation of standard self-guidance system causes problems. Proposed method comprises application of silicon strips 5, 6, 7, 8 on body side surface alloyed to different degree that provides for different resonance frequency of laser absorption. Laser radiation 3 getting on strip with resonance frequency of radiation absorption causes its evaporation and occurrence of appropriate correcting reactive force. By varying the radiation frequency 3, to get correction pulses in required directions.

EFFECT: possibility to control flight path in two directions across the vector of its current velocity.

1 dwg

FIELD: weapons and ammunition.

SUBSTANCE: guided artillery round comprises body, automatic control unit, steering unit, unit of braking devices, warhead, combined exploder, stabiliser and base gas generator. ACU comprises robot pilot, set of inertial transducers, GPS receiver, passive radar homing head with broadband receiver and receiver frequency tuner module. Unit of braking devices changes projectile drag at final section of trajectory. Said passive radar homing head responds to radio signal emitted by target and can operated in intermittent mode of target signal receipt.

EFFECT: higher accuracy of hitting.

1 dwg

FIELD: weapons and ammunition.

SUBSTANCE: invention relates to antitank and antiaircraft missile guidance systems. In compliance with this method, control signal is generated for astable drive of aerodynamic rudders with feedback and vibratory linearisation as well as appropriate deflection of rudder drive. Locked time moment is set prior to rocket launch. From the moment of launch to fixed time moment drive control signal is shaped as relay two-position width-modulation signal. Note here that drive is operated in relay mode with deactivated feedback and vibratory linearisation. Missile control system comprises appropriate control hardware (1). It comprises device (2) to measure mismatch of missile with preset guidance line and device (3) to generate control signals. Aerodynamic rudder drive (4) comprises adding amplifier (5), power amplifier (6), relay element (7), actuator (8), rudder deflection transducer (13) and generator (14) of linearisation oscillations. Additionally, it incorporates first and second switches (11, 12), time signal source (9) and logical device (10).

EFFECT: higher accuracy of guidance for rudder drive rockets.

2 cl, 2 dwg

FIELD: physics.

SUBSTANCE: method employs information on the Earth's magnetic field (EMF) vector measured by an EMF sensor in a coordinate system associated with a banking aircraft. The signal measured by a banking angle sensor is summed with the correction signal of said angle which is calculated based on the inclination angle of the EMF intensity vector, magnetic heading angle and pitch angle of the aircraft. The sensitivity function of the correction signal of the banking angle is determined depending on the sensitivity function of the measurement error of the banking angle of the aircraft by an EMF sensor to errors in determining the pitch and yaw angles of the aircraft, calculated based on the inclination of the EMF intensity. The pitch and heading angles of the aircraft are selected such that the sensitivity function of the correction signal of the banking angle does not exceed a value of said angle which is allowable on calculation accuracy.

EFFECT: higher accuracy of determination.

3 cl, 2 tbl, 8 dwg

Guided missile // 2244897

FIELD: armament, in particular, guided missiles.

SUBSTANCE: the guided missile has a body with on-board systems, frame with drive shafts made with journals, with air vanes hinge-installed in their end face grooves for folding in the body and fixation in the unfolded position. The guided missile is provided with control-surface deflection transducers and a printed circuit board secured through an insulator on the front end face of the frame and connected by means of a bundled conductor to the on-board systems of the guided missile.

EFFECT: reduced spread in the value of the sweep angle of the air vanes in the process of manufacture.

2 dwg

FIELD: guided missiles, in particular, their control actuators.

SUBSTANCE: the control surfaces are connected by means of a half-axle, in which a central hole is made along the missile longitudinal axis, alkane holes are made perpendicularly to the longitudinal axis for installation of the axles of the control surfaces. The half-axle has components for coupling to the actuation cylinders.

EFFECT: enhanced efficiency of armor-piercing capacity of the missile.

4 cl, 2 dwg

FIELD: defense engineering; production of guided missiles and projectiles.

SUBSTANCE: the invention is pertinent to the field of defense engineering, in particular, to production of guided missiles and projectiles. The technical result of the invention is simplification of testing, increased accuracy, decreased labor input and cost of the testing. The method of testing of a developed torque of an electro-pneumatic steering gear of guided missiles and projectiles is based on a torque measurement of the steering gear with the help of a reference load and an easily removable balance lever put on a rudder. Then the steering gear with a detector of the rudders motion are installed on a customizing table. The detector of the rudders motion is made in the form of a separate contact or non-contact sensor or for the purpose they use an available in the steering gear as a feedback gauge - the gauge of a piston linear motion or a gauge of angular motion of rudders. The rudders turning at a maximum angle in one side is made using application of a torque of the corresponding sign by a reference load with the weight on a definite length of an arm of a placement of the load on the lever in respect to the axis of rotation of the rudders equal to a developed torque of the steering gear at the given pressure of the feeding. Switch on the power of the gauge, measure the voltage on the gauge output by a voltmeter, remove a torque by removal of the reference load, turn the rudders at a maximum angle in other side using application of a torque of an opposite sign equal to a maximum torque of a hinged load on the rudders in respect to the rudders turning angle and an angle of attack of a missile or a projectile. Switch on power supply of the booster of the steering gear and feed onto an input of the steering gear compressed air under pressure of P =1.5Pgvn., feed onto the input of the steering gear a maximum control signal of management corresponding to the motion of the rudders at a maximum angle, measure the voltage on the output of the gauge, which should meet the first given ratio. By a smooth reduction of pressure of the feeding in the pneumo-circuit) of the steering gear and according to reduction of voltage on the output of the gauge determine pressureP

+1
at which the voltage will meet the second given ratio. At that the pressure P+1
should be no more than Pgvn ,remove a pneumatic feeding and the power supply of the booster of the steering gear and switch off the control signal and the power of the gauge. After that using an analogous method they measure voltages and determine the pressure at application of the corresponding torques and a control signal of an opposite sign and determine a developed torque of the steering gear according to the mathematical formula.

EFFECT: the invention ensures simplification of testing, increased accuracy, decreased labor input and cost of the testing.

5 cl, 1 dwg

FIELD: methods for missile radar guidance on air targets in radar guidance systems.

SUBSTANCE: guidance of missiles on an air target moving in the direction to the protected object, including the detection of the air target, evaluation of the parameters of its trajectory, missile launching, missile-to-target approach to the distance of actuation of the missile warhead blasting device, correction of the missile heading in the process of approach, blasting of the charge of the missile warhead at a distance from the protected object not less than the preset one, is accomplished in the trajectory coinciding, in the terminal leg with the predicted missile trajectory. In the terminal leg the speed of the missile is set lower than that of the air target. The result is also attained by the fact that the guidance of the missile on the air target moving in the direction to the protected object, including the detection of the air target, evaluation of the parameters of its trajectory, missile launching, missile-to-target approach to the distance of actuation of the missile warhead blasting device, correction of the missile heading in the process of approach, blasting of the charge of the missile warhead at a distance from the protected object not less than the preset one, is accomplished in the trajectory of the missile displaced in the direction to the protected object. In the terminal leg the speed of the missile is set higher than that of the air target. The result is also attained by the fact that the radar set for guidance of the missile on the air target has a missile control point and an on-board radar equipment. The missile control point includes a detection radar, a guidance radar, a computer, a servo drive, a transmitting device and an antenna device, the missile on-board equipment has a missile antenna, radio-receiving device of the missile guidance channel, actuating device, selector switch, transmitting device, radio-receiving device of the detection channel, computer.

EFFECT: reduced dynamic errors of missile guidance on an air target, and enhanced time of radio contact of the missile warhead fuse: with the air target.

5 cl, 6 dwg

Control actuator // 2254267

FIELD: flying vehicle control systems, mainly small-sized guided projectiles.

SUBSTANCE: proposed control actuator includes adder whose first input is used as actuator input and correcting filter connected to adder output. Actuator includes also relay element, power amplifier and servo unit connected in series. Servo unit output is used as actuator output and is connected with second input of adder through feedback element. Circuit is additionally provided with harmonic signal generator and second adder. First input of adder is connected with correcting filter output and second input is connected with output of harmonic signal generator and output is connected with relay element input. Such arrangement makes it possible to change and to select parameters of correcting filter and gain factor of circuit.

EFFECT: enhanced operational accuracy and noise immunity.

1 dwg

FIELD: aeronautical engineering; control systems of unmanned flying vehicles provided with target coordinator and passive homing system.

SUBSTANCE: proposed method consists in selection of tracking point inside target loop and measurement of parameters of motion of flying vehicle relative to this point. During autonomous flight of flying vehicle, its selective guidance is ensured by forming limited tracking zone around selected tracking point with many threshold magnitudes and respective time intervals. When tracking point gets beyond these thresholds, its position is restored by forced correction. In case tracking within this zone is unstable after several correction cycles, guidance in target loop is performed instead of selective guidance by making several correction cycles of tracking point. In case tracking is unstable again, target is considered to be lost. Homing is replaced by forced motion of flying vehicle in way of reference tracking point over rectilinear trajectory and fixing the axis of target coordinator in direction towards selected tracking point. Attempts are made for locking-on new tracking point inside target loop. In case of successful attempt, homing of flying vehicle to new tracking point is performed. In case of unstable tracking, target lock-on is considered to absent and fixed position of target coordinator axis is restored positively. As target range reduces, approximate linear deviation of tracking point is maintained constant inside target loop.

EFFECT: enhanced efficiency of flying vehicle due to selective guidance and retaining controllability in case of loss of target.

6 cl, 6 dwg

FIELD: defense equipment, in particular, projectiles and missiles.

SUBSTANCE: the preliminarily cooled to the maximum preset negative temperature of the control drive is checked in a thermal vacuum chamber, when it is fed with air of a raised humidity. After the check a technical inspection of the drive (assemblies and parts) is carried out and the quality of coatings and insulation of the current-conducting circuits, strength, stability and serviceability are estimated. According to the results of the comparative estimate of the obtained values of the measured parameters with the preset ones in the selected conditions and technical inspection, a decision is taken on the quality of functioning of the air-dynamic control actuator cooled to the negative temperature at a compressed aid of a raised humidity. The stand for quality control of functioning of the air-dynamic control actuator of guided missile is provided with a thermal vacuum chamber with a vacuum pump, humidity chamber and a pneumatic cock with a connecting hose. The outlet of the humidity chamber is connected to the pneumatic cock and connecting hose to the inlet of the receiver. The base with the unit fastened on it and the receiver with the measuring pressure gauge and the relief valve are installed in the thermal vacuum chamber.

EFFECT: expanded potentialities of use of the stand and enhanced quality of control of functioning of air-dynamic control actuators and autopilots of guided projectiles and missiles.

2 cl, 1 dwg

FIELD: armament, in particularly, rocketry, applicable in development of missile-weapon complexes with beam-rider guidance systems, in which the missile flight trajectory, for example, close to and parallel with the ground surface, or water surface.

SUBSTANCE: from the moment of start a program-changed pitch command is formed on the missile, and at an entry of the missile in the beam area control is effected by the TV guidance system. In the horizontal plane the directions of the missile start line and beam are matched with the zero value of command messages. In the vertical plane the direction of the missile start line is adjusted in angle above the beam direction with the zero values of the command messages, and the beam-rider guidance system is controlled by the guidance system from the moment of getting of the missile to the beam area with zero values of command messages in the vertical plane, the missile is twisted in bank angle. Described are two modifications of the complex of the missile telecontrolled in beam. The first modification has a missile that includes components of missile electromechanical joining, autopilot, and a series-connected receiver and a coordinate separation unit, as well as a control station that includes a sight-guidance instrument and a start control device, which is connected via the device of the electromechanical joining of the launcher to the components of the missile electromechanical joining, the receiver is coupled by electromagnetic radiation to the sight-guidance instrument; installed on the missile are a delay unit and series-connected starting pulse shaper, variable command shaper and an adder, the heading and pitch outputs of the coordinates separation unit are connected, respectively, to the first and second inputs of the delay unit, the heading output of the delay unit is connected to the first input of the autopilot, the pitch output of the delay unit is connected to the second input of the adder, the adder output is connected to the second input of the autopilot, and the third input of the delay unit is connected to the output of the starting pulse shape, whose input is connected to the components of the missile electromechanical joining. The second modification differs from the first one by the fact, that the receiver output is connected to the first input of the delay unit, whose output is connected to the input of the coordinates separation unit, the pitch output of the coordinates separation unit is connected to the output of the starting pulse shaper, whose input is connected to the components of the missile electromechanical joining.

EFFECT: enhanced efficiency.

4 cl, 6 dwg

FIELD: armament, in particular, rocketry spinning in bank angle, applicable in missile guidance systems, in which beam-rider guidance systems are used, for example.

SUBSTANCE: the electromagnetic radiation from the control station is converted on the missile into the components of the command signal, corrected and a command signal is formed from the corrected values. A bank signal is generated on the missile in the form of electric pulses, whose durations are formed to be equal in value to angular intervals, formed at missile bank spinning, the duration of each pulse is transformed into a binary number, whose value corrects the values of the components of the command signal. Introduction in the missile guidance system of a connected-in-series roll-angle pick-off and a "duration-code" converter has enhanced the reliability due to the use of the missile of roll rate for correction of the value of the command signal on the missile.

EFFECT: enhanced reliability due to the use of the missile roll rate as a regulating value, that corrects the command signal on the rolling missile.

5 cl

FIELD: armament, in particular, rocketry.

SUBSTANCE: at this method a spatial structure of electromagnetic field is produced at the control station, in which the field parameter is functionally coupled with the coordinates of the respective points of the space. A beam with zero values of the command messages is laid on the target or above the target, and the parameter of the electromagnetic field is measured on the missile, the value of coordinates is determined and the heading and pitch control commands are formed; N devices are positioned in the area of beam propagation, each of the devices transforms the field parameter to the pitch and heading coordinate signals, and then are registered from the missile start, and the position of the missile relative to the target is fixed in the flight trajectory. The process of registration and fixation in time is synchronized according to the value of the registered coordinate signals and fixed missile deviation from the target in heading and pitch, and a conclusion is made on the condition of the beam telecontrol system and its components. The method is realized by the beam telecontrol monitoring system, having a control station, coupled with the missile by electromagnetic radiation, and a telemetering system, use is made of a device for fixation of the missile flight trajectory, and the telemetering system is made in the form of N chains, in each of which connected in series are a receiver and a coordinate separation unit, the heading and pitch outputs of the coordinate separation units from the N chains are connected to a registering device, the receiver from each chain is coupled by an electromagnetic radiation to the control station, and the device fixing the missile flight trajectory is optically coupled with the missile.

EFFECT: a spatial structure of the electromagnetic field is produced at the control station, in which the parameter of the field is functionally coupled with the coordinates of the respective points of the space.

3 cl, 1 dwg

Up!