Homing guidance systems (F41G7/22)

Antenna device with bigimbal support // 2613344
FIELD: physics.SUBSTANCE: antenna device with the bigimbal support made in the form of the two gimbal supports consisting of the outer and inner frames, contains rotate drives of the outer and inner frames arranged on the fixed base, a microwave path, a mirror mounted on the inner frame of the first gimbal support, and a mobile and console-based mounted rod, on which a plug is fixed, cinematically connected with the yoke (arc), the ends of which are fixed on the drive of the inner frame. At the same time the rotation axis of the outer frame of the second gimbal support is parallel to the base plane characterized in that the inner and outer frame of the gimbal supports are respectively connected by two rods mounted symmetrically to the rotation axis of the rod mounted on the shaft of the outer frame of the second gimbal support on its outer side and on the symmetry axis of the outer frame. The axis of the yoke drive (inner frame) crosses the rotation axis of the outer frame of the second gimbal support perpendicular to the base plane, and the yoke plug shaft is movable in the symmetry plane of the rod at the angle to the symmetry axis of the outer frame of the second gimbal support, and the plug is adapted to be pivotable relative to the axis of the cross yoke section, and a torsion spring is mounted on the plug shaft, one end of which is fixed on the rod, and the other on the plug.EFFECT: increase of the arrangement density of the antenna device symmetrically to the construction rocket axis, improved balancing and increasing of the view field of the mobile antenna mirror.8 dwg

ethod of moving object homing basing on information on fact of target sighting and device for its implementation (versions) // 2607758
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

High-precision attack of radioelectronic structures (res) // 2598687
FIELD: weapons and ammunition.SUBSTANCE: hitting of the RESs operating in SHF, HF and VHF bands exploits one guided missile (GM) with two self-guidance procedures. At initial fight paths self-guidance ratio system is used for search and coarse guidance. Thereafter, at final stage, optoelectronic guidance system is used for fine guidance to the RES. This allows the increase in guidance stability, hitting range and the decrease in the GM launching preparation interval.EFFECT: higher efficiency of fire, hitting of the RESs operating in SHF, HF and VHF bands.2 dwg

ethod of forming data support aircraft flight path and device for its implementation // 2597309
FIELD: aircraft engineering.SUBSTANCE: group of inventions relates to a method and a device for forming an aircraft flight path. To form an aircraft flight path signals are transmitted to a memory unit proportional to coordinates, heading and horizontal speed of the target, they are saved for the reception moment, then a given miss value is transmitted or entered, the obtained signals are compared, the aircraft deviations by heading and range are evaluated, a correction to the current heading is received, saved in the output buffer and transmitted from the buffer to the aircraft heading automatic control system to be worked out, the aircraft movement as per the specified radius around the target is provided, a new flight path considering the target motion is formed. Device for forming a flight path comprises a switch, a memory unit, two subtractors, an output buffer, a range unit, a false target unit, an angular shift unit, a logical unit - all interconnected in a certain manner. False target unit comprises two dividers, an arcsine calculator, an arctangent calculator, a comparator, a multiplier, two arithmetic devices. Angular shift unit comprises two sinus calculators, two multipliers, a subtractor. Logical unit comprises two units of comparison with a preset value, an amplifier, two subtractors, five multipliers, two dividers, two inverters, an arctangent calculator, two adders.EFFECT: provided is automatic forming the aircraft flight path at the target movement.5 cl, 8 dwg

ethod for automatic control of homing head, installed on jet projectile, particularly on rocket // 2595309
FIELD: aviation; instrumentation.SUBSTANCE: rocket missile (1) is equipped with homing head (2) with a homing system on the basis of a gimballess navigation system, characterised by the target capture stage, during which it attempts to detect target (C), and which is characterised by direction (3) of vision, wherein said direction (3) of vision is fixed relative to rocket missile (1) and is directed along longitudinal axis (4) of the latter, and said missile (1) additionally contains control means (8) for automatic control of said missile (1) so that its longitudinal axis (4) in flight during the stage of capture by homing head (2) makes a circle whose radius is increased in time until target (C) is detected.EFFECT: higher efficiency of homing systems.5 cl, 2 dwg

ethod of generating signal to control fighter in horizontal plane in its short-range guidance at clustered air target // 2593911
FIELD: radio control. SUBSTANCE: invention relates to radio control and can be used in radio electronic systems of radio control in short-range guidance of a fighter at the best, predicted intercept point, at a clustered air target (CAT) with additional creation of a condition for providing required linear resolution of targets in the cluster in the fighter on-board radar due to the effect of radar antenna aperture synthesis. EFFECT: technical result is: in the process of guiding a fighter in the horizontal plane at a clustered air target (CAT) in the best predicted intercept point to create the conditions for providing the on-board radar system (ORS) with the required linear resolution of targets in the cluster basing on the synthesis aperture radar (SAR) effect. 1 cl, 4 dwg

ethod of striking target producing coherent interference with missiles fitted with active radar seekers // 2586819
FIELD: aviation.SUBSTANCE: invention relates to aircraft engineering and can be used in development of aircraft and surface-to-air missiles. Proposed method of striking a target-director with coherent noise comprises spatial diversity of transmitter of probe signal and receiver of signal reflected from target, which is achieved by simultaneous start of functionally related groups of at least two missiles, transmitters of which radiate at different frequencies and receivers receive frequency of transmitters of adjacent missiles . This virtually eliminates interference, because receivers are precisely tuned to frequency of emitted signal and its transmitter is located outside receiver bandwidth. This ensures high-precision missile guidance, which is necessary to launch at most divergent "pliers" type paths.EFFECT: technical result is increasing efficiency of striking a target with coherent interference by launch and guidance of missiles with active radar homing emitting probing signals at different frequencies, with receivers tuned to frequency of transmitter of adjacent missiles.3 cl, 1 dwg

ethod of target capture by laser homing head of unmanned aerial vehicle // 2583868
FIELD: aviation, weapon and ammunition.SUBSTANCE: proposed technical solution relates to drones with laser homing heads and can be used in rockets, arranged at outer suspensions carrier aircraft. Target capture by laser homing head of drone is as follows: target is illuminated by light pulse from the illumination station arranged on aircraft carrier, using photodetector placed in laser self-guidance head of drone fix glow of the atmosphere and convert into electric current. Device for generating strobing pulses generate strobe pulse opening amplifier of the laser self-guidance head of drone for the time of expecting arrival of signal reflected from a target.EFFECT: use of different carrier aircraft with different types of DRONE without additional modification of the carrier target illumination station.1 cl, 5 dwg

Self-guidance active laser head // 2573709
FIELD: weapons and ammunition.SUBSTANCE: invention can be used in control systems and self-guidance systems of, for examples, missiles. Self-guidance head incorporates optical system to allow angular deflection relative two orthogonal axes of gimbal in response to commands from two-axes system of stabilisation and tracking. Besides, it comprises detection and identification unit, target preset point locator unit and tracking control unit. Also, it exploits memory unit to store the target reference image preset as a prelaunch flight mission. Target designation laser radiator, flat inclined mirrors, spectrum divider, first and second narrow-band optical filters, first and second objective lenses, laser range finder and timing unit are additionally introduced.EFFECT: reliable high-precision operation at any time at poor illumination, visibility and well-organised counteraction and interferences.2 dwg

Guidance of aa medium range missile with active self-guidance head at guidance to group concentrated target // 2570115
FIELD: aircraft engineering.SUBSTANCE: control over AA mid-range missile with active self-guided head at guidance to the group concentrated target is based on the application of statistic characteristics of the dependence of angular interferences of radar target on its linear sizes. It consists in that the magnitudes of the target angular coordinates are subjected to adaptive filtration by α-β-γ smoothing process and correction algorithm. The magnitudes thus obtained correspond to angular coordinates of actual target of said group target, not to apparent centre which can be located beyond the limits of the location objects geometrical sizes.EFFECT: higher accuracy of missile guides at negative interference effects.4 dwg

ethod for approaching of moving object at self-guidance as per information on fact of target localisation // 2552990
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

ethod of guiding aircraft to ground facilities // 2525650
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

ethod of guiding aircraft to ground object // 2521890
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

ethod of inertial auto-tracking of specified object of viewing and system for its implementation // 2498193
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

ethod of control over aircraft flight // 2496081
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.

ethod and device to damage low-flying targets // 2490583
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

Complex homing head (versions) // 2483273
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

ethod for generation of signals for control of homer rotating by list angle // 2482426
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

ethod of striking target producing coherent interference with missiles fitted with active radar seekers // 2468381
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

ethod of launching missile with laser semi-active-guidance head // 2468327
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

Optoelectronic system for air defence missile system // 2433370
FIELD: physics.SUBSTANCE: optoelectronic system for an air defence missile system has an pointing head (5) mounted on a precision two-coordinate turning device (8), as well as a computing unit (13), a monitor (15) and a control unit (16). The pointing head (5) has a double-channel design with wide (6) and narrow (7) field of vision television channels. The optoelectronic system is fitted with a unit for superimposing wide and narrow field of vision images (14). The lens of the narrow field of vision channel has a mirror-lens design with central screening and includes a main concave mirror (19) and a convergent mirror (20) arranged in series, as well as annular first (21) and second (22) optical wedges placed in front of the convergent mirror (20) with possibility of independent rotation relative each other around the optical axis of the lens. The outer diameter of the optical wedges is equal to the diameter of the main concave mirror (19), and the inner diameter is equal to the diameter of the convergent mirror (20). The wide field of vision (6) channel is placed in front of the narrow field of vision (7) channel having a common optical axis with it. The diameter of each of the components wide field of vision (6) channel does not exceed the diameter of the convergent mirror (20).EFFECT: possibility of battery launch of a missile with one air defence missile system at several targets at once.1 dwg

ethod for shooting small-size targets with corrected artillery projectile rotating about longitudinal axis and self-guided on end flight section of ballistic trajectory // 2426970
FIELD: weapons and ammunition.SUBSTANCE: corrected artillery projectile (CAP) containing body, nongyroscopic target indicator-coordinator, logic device, electric power supply system, jet impulse correcting engines (ICE) are actuated on end section of ballistic flight trajectory maximum during 3 s. Multiple pulse correction is performed at maximum frequency meeting the specified ratio. In order to decrease the angle of non-scheduled CAP oscillations, application points of CAP trust vectors are offset from mass centre towards tail portion through the distance of 2…3 diameters of critical cross section of CAP nozzle. In order to reduce the probability of retaliatory strike of target indication means, laser irradiation of target is performed for not more than 3.5 s. In order to shorten the time and increase the kill effectiveness, the shooting is performed with two or more guns against one target by using the fire schedule providing simultaneous approach of several CAP to obstacle (target).EFFECT: shortening the time and increasing kill efficiency.4 cl

Infrared missile seeker non-sensitive to generators of infrared pulse interference // 2419060
FIELD: weapons and ammunition.SUBSTANCE: infrared missile seeker includes one photoreceiver located separately from photoreceivers arranged on rotating rotor of coordinator after optic diagram in the form of a slot. The above photoreceiver transmits the received pulse signal from generator of infrared pulse interference to signal amplification unit, and then to control unit of missile rudders and interrupts the signal from photoreceivers arranged on rotating rotor.EFFECT: improving interference immunity against infrared pulse interference.1 dwg

ethod for shaping control signal of missile during orientation at manoeuvring target // 2419057
FIELD: weapons and ammunition.SUBSTANCE: initial hypothetic rendezvous moment is pre-set, coordinates of vertexes of triangular approachability areas of missile and target in horizontal plane are calculated for that rendezvous moment from the position corresponding to missile control selection moment. Distances from vertexes of triangular approachability area of target to missile approachability area are determined, which together with hypothetic rendezvous moment are stored. Hypothetic rendezvous moment is varied within the range of the time moment at which the control is chosen to maximum allowable moment of end of orientation. For each vertex of triangular approachability area of target there found is its optimum hypothetic rendezvous moment corresponding to minimum distance between missile approachability area and this vertex. Optimum hypothetic rendezvous moments for each vertex of target approachability area and distance from that vertex to missile approachability area are stored. That vertex of target approachability area is chosen which at its optimum hypothetic rendezvous moment is located at maximum distance from missile approachability area, and as per mutual location of that vertex and missile approachability area built for the same hypothetic rendezvous moment there chosen is missile control.EFFECT: improving missile orientation accuracy, improving usability of fighting equipment of missile during firing at high-speed and high-manoeuvrable targets.2 dwg

Aa missile guidance system // 2400690
FIELD: weapons and ammunition.SUBSTANCE: proposed system compares signals from optical and IR digital photo cameras and radar signal to differentiate between true and false targets. System generates anticipation trajectory via feedback between rudders with movable homing head, that is, the latter turns in direction opposite the rudder deviation unless the rudders stay in neutral position. System can perform leading anticipation towards airframe via shifting rudders position transducer neutral toward the side coinciding with homing head deviation, or its additional deviation toward the same side.EFFECT: high probability of heating maneuvering target.4 cl, 3 dwg

Self-homing device // 2392575
FIELD: physics, navigation.SUBSTANCE: invention relates to navigation equipment and is primarily meant for solving the problem of self-homing through constant-bearing approach of short-term interacting small aircraft. The device has an antenna, a radar set, a timer and a control device. There are two evaluators, an electronic switch, two memory units, a logic device and a control device. The antenna is connected to the first input of the radar set whose output is connected to the first inputs of the first evaluator and the first memory unit. The output of the first evaluator is connected to the first input of the second evaluator and to series-connected electronic switch and second memory unit, the output of which is connected to the second input of the first evaluator, whose output is connected through the first input of the logic device to the input of the control device. A standard one signal is transmitted to the second input of the logic device. The output of the control device is the output of the entire device. The radar set, whose second input is connected to the output of the timer, can be a range finder of a Doppler frequency measuring device.EFFECT: simple design and broadening options for controlling kinematic motion through constant-bearing approach.6 dwg

Active radio-locating head of rocket homing // 2360204
FIELD: defense technology.SUBSTANCE: accuracy of movable targets is achieved by determination of angular speed and acceleration of target movement by means of introduction of unit for processing of information signals of angular positions of target. Unit inlet is connected to outlet of central computer via the first digital manifold, and outlet is connected to inlet of micro-central computer via the fifth digital manifold. At that unit for processing of information signals of angular positions of target consists of channel for processing of information signals of angular positions of target in horizontal plane and channel for processing of information signals of angular positions of target in vertical plane, outlets of which are connected to the first digital outlet of central computer via the first digital manifold, and outlets - to the inlet of micro-central computer along the fifth digital manifold.EFFECT: increased accuracy of movable targets accompanying.2 cl, 2 dwg

Aircraft navigator semi-scale table stimulator // 2338992
FIELD: weapon and ammunition.SUBSTANCE: table stimulator contains signal generator (target simulator), target seeker, analogue computer (AC). Target seeker (TS), containing "БЦВМ" is mounted on fixed base. Signal generator is mounted on fixed base so that its longitudinal axis is aligned with TS longitudinal axis. AC contains assembled aircraft (A) dynamic and motion models, target motion models, TS gyrostabilised platform motion model, TS gyrostabilised platform control models, aircraft-target unit vector calculation model. The table allows for real-time semi-scale simulation of aircraft homing system within the whole range of angular velocity of aircraft-target aiming line without system contour dynamic distortion.EFFECT: higher accuracy of simulation.1 dwg

ethod of missile command signal formation // 2335730
FIELD: weapons and ammunition.SUBSTANCE: method lies in formation of a missile command signal in a vertical plane, starting from target engagement range by the radar-tracking homing head (RHH) for tracking up to missile-target encounter and formation of a command signal by the missile in a horizontal plane from range of target resolution, defined by RHH antenna beam width (ABW) to missile-target encounter according to a method of proportional approach. Thus orienting a missile in a horizontal plane from missile-target engagement range by the RHH to range of target resolution, defined by RHH antenna beam width, is split into several consecutive stages equal on duration, defined by time necessary for an estimation of a maximum quantity resolved on Doppler frequency of air targets by the missile RHH with probability of a correct estimation, exceeding its threshold value. At each stage depending on a situation concerning quantity resolved on Doppler frequency of the targets in group in missile RHH at the previous stage of prompting of a missile the command signal is formed by it, or also according to a method of proportional approach, or according to a method of proportional approach with displacement of an angular rotation rate of a target sight line "missile-target" on a constant and not equal to zero value for maintenance of required linear resolution of the targets in a horizontal plane.EFFECT: increase in resolution by a missile homing head of elements of a group air target.1 dwg, 1 ex

ethod of autonomous development of semi-active homing system of aircrafts and device to this effect // 2333449
FIELD: weapons.SUBSTANCE: invention refers to defense enginery, in particular to the sphere of armament testing and can be used at development of weapon systems with semi-active homing of aircrafts, in particular guided missiles or projectile. The method includes setting code by the laser semi-active homing head, of illumination target by laser radiation with the preset code by means of laser designator and rangefinder, search of the laser radiation by the laser semi-active homing head reflected from the target, coordination of actions by means of communication. Depending on the tactical task, the laser designator and rangefinder, target and laser semi-active homing head are placed at the required reciprocal distances wherefor they are controlled and corrected; while searching the laser radiation the output signals of the laser semi-active homing head are registered; the output signal of the laser semi-active homing head are compared to the required target values; based on the results of the comparison the correctness of tract operation "laser designator and rangefinder - target - laser semi-active homing head" visevaluated.EFFECT: chances for testing and autonomous development of the semi-active homing system for different ranges of the relative position of elements, at different angles of target marking, properties of target reflection surfaces, external conditions; ruling out unconditional necessity of aircraft launch at development.2 cl, 1 dwg

ethod of functioning of information computation system of missile and device therefor // 2332634
FIELD: missilery.SUBSTANCE: invention is related to the field of aviation controlled missiles. Substance of invention consists in preparation of missile on board of carrier airplane for work, measurement of target movement parameters and missile own movement, generation of assessment of necessary parameters of target relative movement and missile absolute movement, selection of method of missile homing at target of the best application by any criterion for these conditions. Parameters of mismatch are calculated for selected method, the said parameters characterising extent of mismatch of actual parameters of missile movement and their required values. Analysis of jamming environment is carried out, noise protective facilities and non-radio-radar meters being switched on depending on jamming environment. Formation of preparation and control signal is carried out for radio proximity fuse. Based on current values, angle position and target range rate of missile approaching target is determined, as well as module of missile miss, geometric dimensions and target angle. On the basis of these data commands are generated for blasting of missile warhead and for initial speed of missile warhead fragments emission.EFFECT: increased efficiency of operational use.21 cl, 13 dwg

ethod of missile guidance at drag increase trajectory part // 2331839
FIELD: weapons and ammunition.SUBSTANCE: in using the method proportional navigation at the increasing drag trajectory part, the flight control can be started at a certain time. Also, velocity drop occurs at the moment of rendezvous because of inadequate distribution of control accelerations. The invention proposes using the time-variable navigation factor. The proposed method of guidance approximates, in fact, to the method of proportional navigation, but unlike it wherein the navigation factor makes a constant, the proposed method varies it depending upon known missile behavior at the drag trajectory part to maximise its velocity at the moment of rendezvous with the target.EFFECT: decreasing the near impact zone, increasing the flight velocity at the point of rendezvous at the drag increase trajectory part.

ethod of data computing system operation of missile and device for its implementation // 2325306
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

ethod for fire by guided projectiles with laser semi-active homing head at several targets // 2317504
FIELD: armament, in particular, control of artillery guided projectiles with a laser semi-active homing head locking-on the lighted target in the terminal trajectory leg and designed for fire control art a fire by guided ammunition with a homing head.SUBSTANCE: 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.EFFECT: reduced time of destruction of several targets due to a complex delivery of fire by several guns at a number of targets with employment of one target indicator.2 dwg

ethod for normalization of guidance signal of spin-stabilized adjustable artillery projectile with the use of linear-acceleration transducers // 2316711
FIELD: artillery weapon, applicable in production of Adjustable artillery projectiles.SUBSTANCE: 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.EFFECT: enhanced accuracy at simultaneous simplification.3 dwg

ethod of remote control of movable objects // 2315346
FIELD: remote control.SUBSTANCE: 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.EFFECT: enhanced reliability.2 cl, 2 ex

Object signing system // 2315255
FIELD: various branches of industry, where the observed information is processed with the aid of optoelectronic systems, in particular, aviation and naval material (on-board observation systems), industrial and ecological monitoring systems, etc.SUBSTANCE: 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.EFFECT: enhanced sensitivity and resolving power of the system.2 cl, 2 dwg

Active radar homing head // 2313054
FIELD: defense equipment, in particular, missile guidance systems.SUBSTANCE: 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.EFFECT: enhanced target tracking accuracy and enhanced resolution of targets in azimuth, as well as enhanced detection range.1 dwg

ethod for formation of stabilization and homing signal of movable carrier and on-board homing system for its realization // 2303229
FIELD: homing systems of movable carriers.SUBSTANCE: 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.EFFECT: enhanced accuracy, linear and angular resolving power, homing noise immunity, at the same time enhanced antijam capability and dynamic accuracy of tracking of the sighting object in direction and range.2 cl, 6 dwg

ethod for fire by guided missile with laser semi-active homing head // 2300726
FIELD: armament, in particular, control of artillery guided missiles with a laser semi-active homing head.SUBSTANCE: 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.EFFECT: enhanced reliability of fire at targets in the mountain conditions.2 cl, 1 dwg

ethod for formation of descent paths of aeroballistic vehicle of required configuration at guidance to preset point of earth surface // 2296940
FIELD: guidance control of flight vehicles, applicable for formation of various descent paths of the preset configuration in the process of guidance of aeroballistic vehicle to the preset point of the earth surface (target point).SUBSTANCE: 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.EFFECT: realized maneuvering capabilities of descending aeroballistic vehicles by formation of various descent paths.3 dwg

Passive object range measurement system in guided ammunition // 2295103
FIELD: methods for guidance of self-propelled reflected beam guided ammunition, applicable in military equipment.SUBSTANCE: 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.EFFECT: enhanced accuracy of guidance of a self-propelled guided ammunition and efficiency of object destruction.4 dwg

Guidance system of guided ammunition by laser radiation reflected from object to be hit // 2293942
FIELD: direction finding optoelectronic devices, applicable in guidance devices of guided ammunition by laser radiation in military equipment.SUBSTANCE: 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.EFFECT: provided a panoramic observation pattern and enhanced accuracy of determination of the direction to the laser radiation source (lighting object).6 dwg

ethod for fire of guided missile with laser semi-active homing head (modifications) // 2291371
FIELD: armament, in particular, control of artillery guided missiles with a laser semi-active homing head, locking an illuminated target in the terminal trajectory leg, applicable for control of fire of mortars and cannon artillery.SUBSTANCE: the method consists in topographical survey of the target indicator and firing position to the terrain, target detection by the target indicator, measurement of the distance from the target indicator to the target, azimuth and angle of sight relative to the target indicator under the conditions of successive target location. Topographical co-ordinates, direction and speed of target motion are calculated in the reconnaissance panel, the co-ordinates, speed and direction of target motion are transformed to a series of binary codes and transmitted to the firing position panel by the digital radio communication. On the basis of the obtained data and preliminarily preset meteorological data, ballistic corrections, time of preparation of the gun and missile to fire the predicted point of impact of the missile with the target an the ground surface is calculated, the fire settings according to the co-ordinates of the gun and the co-ordinates of the predicted point of impact of the missile with the target are calculated, the time of the shot for target destruction in the predicted point is calculated, the sole computing time is set in the reconnaissance panel and in the firing position panel, the fire settings are realized. The signal for a shot is given from the firing position panel when the time of the shot is coming. The time of switching-an of the target indicator of laser radiation is transmitted from the firing position panel to the reconnaissance panel via the digital radio communication channel. The signal for switching-on of the laser radiation target indicator is automatically given from the reconnaissance panel when the required time of switching-on is attained, and the missile is guided to the target illuminated by the laser radiation of the target indicator.EFFECT: enhanced accuracy of fire at movable targets.4 cl, 2 dwg

ethod for normalization of signal of compensation of axial acceleration influence // 2285886
FIELD: guided missile guidance systems.SUBSTANCE: before normalization of missile control signals the engine operation time is preset, a priory evaluation of the projections of the missile axial acceleration onto the input axes of the antenna co-ordinate system of the homing head is preset. On completion of engine operation the present flight time is measured, the time before impact with the target is determined, and the evaluation of miss caused by missile axial acceleration is determined. The axial acceleration compensation signal is proportional to the evaluation of miss caused by missile axial acceleration. The obtained compensation signal is summed up with the signal of missile control according to the method of proportional navigation or its modifications.EFFECT: enhanced accuracy of guidance.2 dwg

ethod for generation of launcher guidance angles for firing at underwater targets by rockets 90p // 2276317
FIELD: methods for generation of launcher guidance angles by fire control devices.SUBSTANCE: the probability of pursuit of the underwater target is determined and in addition a correcting of the launcher guidance angles is introduced in the calculation of the lead point coinciding with the center of the target pursuit area by determination of linear deflection of aiming point Δxc by formula: Δxc=l0-ln , where ln - semilength of the target pursuit area; l0 - semilength of the target lock-on area.EFFECT: enhanced probability of hitting of the underwater target at firing by rockets 90P to the target lead point.5 dwg, 2 tbl

ethod for fire by guided missile // 2275582
FIELD: rocket armament, in particular, methods of fire by guided missiles from infantry fighting vehicles and tanks. SUBSTANCE: after launching of the missile from the bore the sustainer engine is started in the trajectory of its flight by the preset start-up time, and the missile is controlled in the active and passive sections of the trajectory up to the end of the missile flight. The sustainer engine is started by a device with an electronic delay, the delay time is determined from the condition: where: - delay time of sustainer engine starting; - missile flight speed at the instant of sustainer engine starting; V0(m/s) - missile muzzle velocity; m(sq.kgf/m) - missile mass at the instant of sustainer engine starting; cx - missile drag coefficient; Smid(sq.m) - missile maximum cross-section area; - air density.EFFECT: enhanced efficiency of fire due to the increase of the maximum flying range at a simultaneous reduction of spread and reduction of dispersion in the initial trajectory section.3 dwg

Control system for self-guided missile // 2261413
FIELD: air defense.SUBSTANCE: system comprises housing connected with four return springs each of which is connected with the corresponding air vane, propulsion engine, four photomultiplier tubes of the guidance system which are connected in the arms of the electric bridge, four air vanes connected with the electromagnets with movable core through intermediate relay, four infrared devices for photomultiplier tubes, four vision limiters for photomultiplier tubes, four DC amplifiers for photomultiplier tubes, board power source, four tail stabilizing fins, analogue-digital converter, and control unit composed of integrator, tree-link integrating device, and inverter. The photomultiplier tubes are connected with the analogue-pulse converter, intermediate relay, integrator, inverter, and three-link integrating device through the DC amplifier.EFFECT: accelerated missile aiming.7 dwg

ethod of proportional guidance of aircrafts at ground targets // 2261411
FIELD: aircraft guidance systems.SUBSTANCE: method comprises measuring transverse acceleration of the aircraft to be guided in the horizontal plane, measuring the angle between the vector of aircraft velocity and line of sighting on the ground object, distance between the aircraft and ground object, velocity of the aircraft, and generating the control signal in the horizontal plane as the difference between the required angular velocity of the conventional sighting point multiplied by the adaptive navigation parameter and transverse acceleration of the aircraft in the horizontal plane. The adaptive navigation parameter is generated depending on the difference between the current value of the angle between the vector of the aircraft velocity and line of sighting on the ground object in the horizontal plane and required angular shift of the conventional sighting point in the horizontal plane with respect to the line of sighting on the ground object.EFFECT: improved stabilizing of linear resolution of the guidance.1 dwg

Guidance system of guided ammunition to the points of positioning of optoelectronic instruments // 2256871
FIELD: radio engineering, in particular, methods for guidance of self-moving guided projectiles to reflected laser beam, applicable in military equipment.SUBSTANCE: use is made of several sources of illumination of the optoelectronic device located on the object of destruction. These sources operate at different frequencies, as a result of which an information field of projectile flight control is produced with a multispectral homing head, which makes it possible to reduce the requirements to the accuracy of projectile guidance to the target at the initial leg o guidance to the optoelectronic instrument, located in the most vulnerable point of the armored object.EFFECT: enhanced accuracy of guidance of guided projectile to the most vulnerable points of position of the optoelectronic instrument, and efficiency of destruction of the armored object.3 dwg
 
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