Method of moving object homing basing on information on fact of target sighting and device for its implementation (versions)

FIELD: data processing.

SUBSTANCE: object trajectory is formed as cyclically repeating arched sections, along which the object moves with a preset (maximum) angular speed equal in magnitude but opposite in sign. Every two sections are combined into a cycle, which begins and ends with the fact of coincidence of the object speed vector direction with the target line of sight, and the angular speed sign is changed inside the cycle as per the fact of coincidence of inclination angles relative to an inertial coordinate system of lines connecting the object and the target at the beginning of the cycle and at the given moment. Also proposed are devices implementing the above said method.

EFFECT: proposed is a method of a moving object homing basing on information on the fact of a target sighting in case of coincidence of the radar axis direction with the object speed vector direction.

4 cl, 4 dwg

 



 

Same patents:

FIELD: physics; control.

SUBSTANCE: invention relates to rocket engineering and can be used to control rocket flight during flight tests. The method includes constantly inspecting, during the entire period of time from mounting the rocket on the launching pad until launching the rocket, using an on-board radar system for remote probing the Earth, the standard and predicted destruction sites of the rocket as a result of possible accidental change in the flight trajectory; detecting, at both sites, the appearance of unauthorised objects whose existence is endangered during self-destruction of the rocket; detecting and identifying the unauthorised objects; simultaneously entering into the programmed flight control system a command to delay the self-destruction; transmitting a command to delay self-destruction of the rocket or guiding the rocket to a safe place if, at the time of launching the rocket, the unauthorised objects are still located at one of the rocket destruction sites; launching the rocket; determining current coordinates and motion parameters of the rocket; calculating the probable trajectory; generating and transmitting to the rocket commands to change the flight trajectory; constantly transmitting to the command centre data on the state of the environment on the route of test flights; predicting possible accidental changes in the flight trajectory which lead to contamination of the Earth's surface, water bodies and air; transmitting to the rocket commands to either continue flight towards the target or deviate from the trajectory and destroy the rocket in an area with minimal damage to the environment.

EFFECT: invention ensures safety for unauthorised objects located at a predicted rocket destruction site.

3 dwg

FIELD: aviation.

SUBSTANCE: in the method of linearised signal shaping, the rotation period of missile is divided into time intervals on the missile rotating by bank angle, their durations are measured and stored in a certain way. Signal lineariser comprises digital integrator, calculator, tilt signal shaper, step-signal shaper, register and clock-pulse driver. Switchable signal lineariser comprises digital integrator, two calculators, tilt signal shaper, step-signal shaper, tilt sensor, register, control unit, switchboard, clock-pulse driver. In the process of integration, the amplitude of clock pulses is integrated on the missile rotating by bank angle in order to shape the linearised signal, bit-by-bit summing of bitwise binary parallel numbers for each rising edge of clock pulses is carried out. Duration of integration interval is set of corresponding duration of angular spacing of 90 degrees. Then, the integration process is repeated, by changing the discrete quantity in a certain way before starting. Digital integrator comprises series-connected single-bit digital cells. Cell contains D-flip-flop and adder connected in a certain way.

EFFECT: high precision of control command shaping by missile.

11 cl, 7 dwg

Adjustment shield // 2548690

FIELD: radio engineering, communication.

SUBSTANCE: adjustment shield simulates forward radio signals and radio signals specularly reflected from the earth, propagating from a missile and a target to a final homing area. The adjustment shield is located in the far zone of a radio direction-finding antenna and comprises laser and infrared emitters. To simulate signals from a missile transponder and signals reflected from a target, the shield is provided with a radio pulse generator with a frequency synthesiser.

EFFECT: high accuracy of adjustment.

3 dwg

FIELD: weapons and ammunition.

SUBSTANCE: tank-type container of warhead includes fairing, thin-walled tank body, front and rear bottoms, filler dispersion and ignition device. Buffer cavity where container weight compensators is made between the fairing and front bottom. Container fairing is designed as reinforced flat bottom with rounded edges attached to the container shell by screw connection. Front bottom of the container has a conical deflector shape. Deflector cone angle is 120-140°. Tank body features centring bulge at a distance of 3.6-3.8 of the calibre from the fairing. Filler dispersion and ignition device is positioned along longitudinal axis of the container and shifted inside the buffer cavity by 0.010-0.015 of its length and attached to a cross-shaped support.

EFFECT: enhanced efficiency of missile or ammunition with such container.

1 dwg

FIELD: weapons and ammunition.

SUBSTANCE: rolling missile is accelerated to cruising speed by means of a detachable solid-fuel launching accelerator, cruising speed is maintained with thrust of a small-size disposable turbo-jet engine, twisted and a mode of rotation about the roll axis is maintained by means of aft stabilisers that are slanted relative to the longitudinal axis and/or a gas-dynamic nozzle on the turbo-jet engine, aerodynamic lifting force is formed in the rotation mode by means of n pairs of small-size foldable wings.

EFFECT: invention allows increasing flight distance of a cruise missile.

2 dwg

FIELD: weapons and ammunition.

SUBSTANCE: shell with gas hanger includes a smooth cylindrical part, in which there is a feed cavity connected to the outer cylindrical surface through feed devices. The feed cavity is intended to create pressure in a carrying gas layer. The feed cavity is filled with substance having high combustion speed. The feed cavity is connected to the rear part of the shell through a thermite wick. The latter is made in the form of a gasket arranged on the inner wall of the feed cavity and pressed to this wall with a spring-loaded shoe.

EFFECT: reduction of the shell size and increase of firing distance.

3 dwg

Guided missile // 2542692

FIELD: weapons and ammunition.

SUBSTANCE: guided missile is made based on canard configuration. The missile with a single-channel control system and rotating in roll direction. The missile contains a main propulsion system, a steering wheel in one plane and a stabiliser with the location of fixed bearing surfaces by X-shaped pattern relating to the plane of the steering wheel console. At the head part of the housing of the guided missile in a plane perpendicular to the plane of the steering wheel console, the pylons are mounted. The fixed consoles of the pylons in a transverse plane are located at an angle of 45-60 degrees relative the consoles of the stabiliser. The consoles of the pylon on the geometric shape in the plan are made like consoles of the steering wheel with the ratio of areas of the pylon and the steering wheel as 0.5-1.0. The ratio of areas of the console of the pylon and the console of the stabiliser are made as 0.05-0.1.

EFFECT: improved control efficiency, improved ballistic and dynamic properties of the missile.

2 dwg

FIELD: weapons and ammunition.

SUBSTANCE: unit of control system of rocket projectile comprises a housing with ogive part, aerodynamic controllers folding-out in flight with actuators and a control unit, mounted on the ogive part. Each controller is equipped with abutment. The abutment is located in front of the front edge of the controller coaxially with the axis of folding-out. The profile of the front part of the abutment is congruent to the profile of the ogive part of the housing. The diameter of the maximum circumscribed circle of the abutments of all the controllers does not exceed the unit gauge. Folding-out axes of the controllers are biased to the axis of the unit relative to its gauge by an amount at least 0.5 of the maximum thickness of the controller at the root chord of its folding-out part.

EFFECT: improvement of accuracy of projectile shooting.

4 cl, 2 dwg

Controlled missile // 2539709

FIELD: weapons and ammunition.

SUBSTANCE: invention relates to missile engineering, namely to controlled missiles. A controlled missile includes a housing with the main control elements symmetrically arranged on it - aerodynamic surfaces and rudders, as well as a wire duct. The latter is arranged along the housing in the incline of rudders. An aerodynamic surface is additionally installed on the housing, on the side opposite to the wire duct.

EFFECT: improvement of aerodynamics of missile flight and improvement of its target guidance accuracy.

2 cl, 1 dwg

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.

FIELD: measurement equipment.

SUBSTANCE: method is based on use of information on fact of target localisation with a locator, the sensitivity axis of which coincides with direction of speed vector of the object. Trajectory of the object is formed in the form of cycles that begin and end by the fact of target localisation. Inside each cycle an arc-like movement is performed at maximum possible angular speed that is constant in the cycle, the sign of which is changed after achievement of the value of the average angle of advance of the object trajectory relative to a line of sighting, which is calculated for the current cycles as a product of difference of the value of this angle in the previous cycle and increase rate of the inclination angle of the object trajectory in the current cycle relative to the previous one multiplied by a coefficient depending on approach conditions, and a fraction, in the numerator of which there is difference of values of the average angle of advance in the previous cycle and rate of increase of the inclination angle of the object trajectory in the current cycle relative to the previous one, and in the denominator there is a sum of the specified values.

EFFECT: possible approach at opposite self-guidance when linear speed of the target exceeds speed of the object.

5 dwg

FIELD: physics, navigation.

SUBSTANCE: disclosed is a method of guiding aircraft to ground facilities. In the method, guidance to ground facilities is controlled simultaneously in an inclined plane whose position is determined by the flight path direction of the aircraft, and in a vertical plane, based on a condition for providing and stabilising the required resolution of radar images of ground facilities, using a proportional navigation technique with offset of the line of sight rate of the ground facility in both aircraft control planes. Offset values are generated such that the direction of the velocity vector of the aircraft in the vertical plane at moment in time matches the direction towards the point of intersection of the perpendicular to the projection of the line of sight of the ground facility on the horizontal plane, which coincides with the ground surface, passing through the ground facility and belonging to said horizontal plane, with the vertical plane in which the velocity vector of the aircraft is located.

EFFECT: high accuracy of guiding aircraft to ground facilities.

10 dwg

FIELD: physics, navigation.

SUBSTANCE: invention relates to autonomous aircraft navigation systems, particularly aircraft navigation systems comprising on-board radar equipment which guides the aircraft to ground objects. Guiding an aircraft to a ground object includes measuring the viewing angle of the ground object in the horizontal plane relative to the direction of the ground velocity of the aircraft, the angular velocity of the line of vision of the ground object in the horizontal plane, the distance from the aircraft to the ground object, the flight velocity of the aircraft and acceleration thereof in the horizontal plane. The method also includes measuring the current value of the deviation angle of the line of vision of the ground object from the direction of the velocity vector of the aircraft, the current value of the viewing angle of the ground object in the vertical plane, the current value of the inclination angle of the velocity vector of the aircraft in the vertical plane, the current value of the angular velocity of the line of vision of the ground object in the vertical plane and the current value of acceleration of the aircraft in the vertical plane. The method includes calculating the current value of the deviation angle of the projection of the line of vision of the ground object on the horizontal plane from the projection of the direction of the velocity vector of the aircraft on the same plane. The obtained results are used to control flight in the horizontal and vertical planes to enable stabilisation of the linear azimuthal resolution of the radar image of the ground object generated by on-board synthetic aperture radar, stabilisation of resolution of said radar image on the horizontal range, and such that the direction of the velocity vector of the aircraft in the vertical plane at each moment in time matches the direction towards the point of intersection of the perpendicular to the horizontal projection of the line of vision of the ground object, passing through said object and belonging to the horizontal plane, with the vertical plane to which the velocity vector of the aircraft belongs. The value of deviations (discrepancies) of current angle measurements, as well as the current inclination angle of the line of vision of the ground object from the required values is estimated and trajectory control signals for the aircraft in the horizontal and vertical planes, which enable to eliminate said deviations, are generated.

EFFECT: high accuracy of guiding an aircraft to given ground objects using on-board synthetic aperture radar.

11 dwg

FIELD: instrument engineering.

SUBSTANCE: during the final preparation for launch mobile carrier, the signals are defined and set proportional to the initial coordinates on the slant range, on the angle of slope, on the azimuth of mutual position of the mobile carrier and originally specified object of viewing (OV) relative to the base of the integrated antenna device in the coordinate system connected to the center of mass of the mobile carrier. At that the operational signals are made in the form of a package of consecutive words that are proportional to the parameters of initial setting of the inertial measurement of parameters of viewing vector of the set OV in the local horizontal coordinate system. These signals convert the parallel form and the signals are formed according to them, proportional to the initial conditions of the setting of inertial direction finding of the set OV in the base antenna coordinate system.

EFFECT: increased accuracy.

2 cl, 8 dwg

FIELD: aircraft engineering.

SUBSTANCE: stabilised sight line is consecutively aligned with every viewing object. Distance to objects and their angular coordinates relative to finder system are defined and memorised. After launching the aircraft toward short-range viewing object and its interception by control system, time of flight abeam flight path is measured. Data on aircraft hitting the preset viewing zone or miss is defined and fed to finder system field of vision. In the case of miss and possibility of re-aiming, instruction for flight above sight line is sent to aircraft. Sight line is switched to the next range viewing object and, at approach thereto, aforesaid instruction is cancelled to move the aircraft to sight line. In further misses, elevation instruction is fed with changing sight line to the nest viewing objects. Said elevation instruction is fed to aircraft when it flies over immediate object.

EFFECT: higher accuracy of control.

FIELD: weapons and ammunition.

SUBSTANCE: engineering anti-aircraft mine comprises a contactless target sensor and a directional fragmentation warhead. The method to damage low-flying targets consists in the fact that the mine warhead is actuated using a bistatic radar target sensor. The device for damage of low-flying targets is made in the form of a bistatic radar system made of a spaced radar transmitter and an autonomous Doppler radar receiver. The radar transmitter is installed on the secured object. The autonomous Doppler radar receiver is installed on the area surrounding the object, together with the fragmentation warhead. In another version of design the device warhead is made in the form of an electromagnetic missile. The electromagnetic missile comprises ready fragments of a ferromagnetic material. The area of fragmentation warhead damage is matched with the zone of detection of the autonomous Doppler radar receiver.

EFFECT: higher reliability of damage of various air targets under any meteorological conditions.

4 cl, 1 dwg

FIELD: weapons and ammunition.

SUBSTANCE: complex homing head comprises an optical and infrared digital photo cameras, a passive or an active radiolocator, an automatic pilot, a unit of threshold passage of a signal of an optical photo camera, a unit of switching off of infrared pixels, an electronic key, a delay line and a night vision device. The signal from the night vision device or from the infrared camera arrives to a specialised computer of a control system, where with the specified extent of validity it is compared with all-aspect images of all known airplanes available in the computer memory. After identification of the airplane type the computer determines the predetermined resolution or prohibition for target damage. A pre-programmed most vulnerable area is selected on the target, and further homing is carried out to the same area by readings from the night vision device or infrared camera.

EFFECT: improved accuracy.

9 cl, 1 dwg

FIELD: weapons and ammunition.

SUBSTANCE: method of generation of a signal of control of a shell rotating by list angle consists in detection of an amplitude modulated signal with a tracking gyroscopic head of homing, proportional to angular speed of a target sighting line, conversion of a signal into a width-modulated signal that arrives to an inlet of a steering drive of the shell. At the same time the sum of the amplitude-modulated signal and the signal of the sensor of angular speed of the shell filtered with a filter of noise components and a filter of a permanent component is converted into the width-modulated signal.

EFFECT: provision of possibility to increase probability of shell hitting a target.

1 cl, 6 dwg

FIELD: physics.

SUBSTANCE: method of striking a target producing coherent interference by launching and guiding missiles fitted with an active radar seeker involves emitting a probe signal and receiving the signal reflected by the target, wherein two missiles are simultaneously directed onto the target, and emission of the probe signal and reception of the signal reflected by the target are reassigned between the missiles alternately; before launching missiles, the intervals for emitting probe signals and receiving reflected signals are synchronised such that intervals for emitting the signal of one missile match intervals for receiving the signal reflected from the target of the other missile. Switching intervals for emitting the signal and receiving the reflected signal is carried out with frequency higher than the bandwidth of the guidance system, and the frequency of switching emission and reception intervals is set primarily alternating. The missiles are guided into the target on "pliers" type maximally divergent trajectories.

EFFECT: improved method.

4 cl, 2 dwg

FIELD: weapons and ammunition.

SUBSTANCE: topographical lock-on of launcher is effected with the help of satellite navigation system prior to setting the fire parameters. Fire control board with digital radio communication means is located 50-100 metres from launcher. Lock-on errors may not exceed 50 metres. Fire control parameters are transmitted in binary code to launcher ACS and, further, to missile. Launcher is turned to azimuth and elevation to launch the missile by command from control board.

EFFECT: increased range of fire, higher safety.

1 dwg

FIELD: weapon and ammunition.

SUBSTANCE: method of automatic armaments homing at moving target according to which the periodic image of the field of military operations is formed with a frame frequency, and after target detection, determination of its range, speed of movement and an altitude the lead angles of the weapon for the subsequent shot, differs by that, for the purpose of increase of probability of target destruction and safety of a shooter, after detection of the target the shooter by means of remote control moves the target image to such area of the field of vision of the optical-electronic system (OES) of the sight which would allow at stable position of the line of vision (LV) of OES to observe the target during the time sufficient for the first aiming operation; at this operation the position of LV OES is stabilised spatially; the marker is placed over the image of OES target; the sight operating mode is switched to automatic one at which OES marker moves together with the target, and OES at the beginning of each shot transfers the data (an azimuth and a angle of a place) of the target angular coordinates to the range finder; the range finder is automatically rotated towards the coordinates supplied by OES and as the target enters the sight of the range finder marker it sends an impulse of radiation and determined the range of the target which it transmits to the sight, providing the first triad of data (location angle, an azimuth and range of the target) which are saved in the sight memory; after the time Δt0, multiple to the period of OES frame sweep, the range finder again measures the target range and again transfers the information on the target range to memory of the sight which automatically forms the second triad of data on the target position with reference to the sight; the calculator of the sight using both triads of data and the known time interval Δt0, predicts the target position at the given moment TP; and at calculation of TP the following is taken into account: target speed; range and angle of the target altitude; time of shell flight taking into account the target altitude; dynamic parameters of the sight drive (time of rotation of the sight to the rated point); size of differential coordinates of the second and first triads of data; ambient temperature; wind direction and speed; then LV OES stabilisation is removed and the sight with the weapon stock is rotated towards the direction of the predicted position; after installation of the sight into the rated position at the given time TP the shot is made automatically.

EFFECT: improvement of aiming accuracy taking into account parameters and target motion conditions, homing of the weapon to the rated direction with automatic providing the required lead angle, and the shot at the rated moment without participation of the shooter.

1 cl, 5 dwg

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