Method of launching missile with laser semi-active-guidance head
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.
The invention relates to the field of armaments, in particular to the management of missile with semi-active laser homing head, exciting highlighted the purpose of the final part of the path.
The invention is intended to control the fire of mortars and cannons calibers type 120, 122, 152, 155 mm when shooting managed ammunition and guided missiles with homing head.
There is a method of firing a controlled missile with semi-active laser homing head [Patent RU No. 2247297 from 24.07.03, a Method for firing the controlled missile with semi-active laser homing head], we have chosen for the prototype.
Scout on the control and observation point detects and maintains target laser designator-rangefinder; transmits the coordinates of the targets on the firing position, where you are shooting tracked target managed projectile. After the shot guided projectile flies like a rocket, which captures the illuminated laser beam aim on the target trajectory.
Named method is the following: consistently produce topographic binding designator and a firing position to the terrain, the target detected by the target designator, and then produce a measurement of the azimuth and distance from the designator to the target and topographic p is ivascu of a target area; calculation and implementation of units firing at the target coordinates and fire position. Topographic coordinates of a target location and transform its coordinates in the sequence of binary codes using the remote scout, and the calculation of the firing settings using the remote control firing position. In remote reconnaissance and remote control firing position organized by a single computer. Next is the missile launch and guidance of missiles at the target, comprising the sequential move the launcher to aim at the corners of the firing settings, input settings shooting a rocket, then launch and spread of missiles at the target, highlighted after shot laser target designator. After the missile is launched to enable designator transfer from the remote control firing position in the remote spy on digital radio time values include laser target designator, and the enable signal highlighting automatically send from the remote control scout in the designator while achieving on-time.
The disadvantage of this method is the limited range missile or artillery shell (up to 20 km) and the need to combat the calculation launchers or guns to be near the starting condition is anouki at launch.
The task of the invention is to increase the firing range of up to 50 km and more through the use of missiles with semi-active laser homing head having a main engine unlike artillery projectile, as well as improving the safety of fighters calculate the firing position by removing the remote control firing position for a few tens of meters from the guide launchers.
To achieve the above objectives, in a known way of firing a guided missile with semi-active laser homing head, comprising the sequential detection of a target designator, the dimension designator azimuth and distance to a target, topographic binding designator and target areas, and topographic binding targets is carried out in the remote scout calculated, after which the remote scout target coordinates is converted into a sequence of binary codes and pass them on digital radio in the remote control firing position, the dimensioning of the firing of the missiles and launchers perform in the remote control firing position on the coordinates of the target and missile launchers, and remote reconnaissance and remote control firing position establishing uniform computer time, perform the production start-up, including serial hovering the s launcher at the target on the angles of shooting, the input units firing at the missile launch and guidance of missiles at the target, illuminated laser target designator, and a switch-on signal of the designator is automatically sent from the remote control scout in achieving on-time transmitted from the remote control firing position in the remote spy on digital radio, and topographic binding launchers perform using satellite navigation equipment cockpit firing position; what's new is that additional topographic binding launchers to the terrain using satellite navigation equipment cockpit firing position to perform the calculation of the firing settings and set the remote control firing position, together with the tools of digital radio at a distance of 50-100 meters from the launcher, ensure that the accuracy of the topographic location of the launcher, target designator and targets for each dimension of the geographic coordinate system did not exceed 50 meters, designed in the remote control firing position installation firing the launcher and the missile passed in binary code in the automation unit launchers and rocket deploy the launcher on the angles of azimuth and installations firing, the missile was produced by a signal from the remote control is the exercise firing position, moreover, the signal on the rocket passed to the automation unit launchers in the binary code, and the transmission delay to switch on the pointer with remote control firing position in remote scout after launch does not exceed 3-6 seconds.
Implementation of the proposed method is illustrated by the flowchart shown in the drawing, showing: 1 - laser designator-rangefinder, 2 - gyro, 3 - satellite navigation equipment, 4 - remote scout, 5 - digital radio, 6 - remote control firing position, 7 - automatic block, 8 - missile.
The proposed method of firing a missile with semi-active laser homing head is implemented as follows: the firing position 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 (LCC), satellite navigation equipment, digital radio and the remote scout, and outputs designator, satellite navigation equipment and digital radio stations through connectors and adapters connected to the processor of the remote agent.
Laser designator with the rangefinder and the target channel is used for detection and target tracking, and target coordinates, for example, range and azimuth of the target relative to the LCD.
With p the power of satellite navigation equipment are determined by the coordinates of the pointer in a rectangular geographic system and entered into the control panel of the scout.
Scout with LCD produces measurement target range and azimuth of the target. The results of the measurements are entered into the console scout, is converted, for example, in the terrestrial coordinate system topographic binding to the terrain, are displayed on the screen of the remote scout, is converted into a sequence of binary codes, for example, according to EIA standard interface RS232C and transmitted to the remote control firing position on digital radio.
In the remote control firing position perform topographic binding launchers to the terrain, for example, satellite navigation equipment, entered the latitude, longitude, and height of the launcher, keyboard enter data for ballistic calculations (the weight of the rocket, the temperature of the charge), weather information (metalbulletin or results of ground Metaoutline).
Set the remote control firing position, together with the tools of the digital radio communication at a distance of 50-100 meters from the launcher. This remote control firing position connected via cable to the automation unit launchers.
In the remote control firing position using the received radio coordinates of the target are calculated automatically install the firing launchers and missiles. The calculation of the angles of firing the launcher to perform aetsa, for example, the dependencies that are listed in the [Patent RU No. 2111437 from 20.05.98, the Method and apparatus aiming guns].
The dimensioning of the firing of the rocket may include determining the time of flight to the target and on-time seekers.
Using the gyro-compass is pointing the launcher at the target on the firing settings (azimuth angles and places).
Installation of firing missiles that define the sequence diagram of its flight, is transmitted in binary code in the automation unit launchers and forth in a storage device of the rocket.
The men of the crew firing position performs a reversal of the launcher, enter setup firing into the ship and then take cover in the trench (the dugout) in 50-100 meters from the launcher; there is a missile launch.
After that, over the voice communication channel to the control and observation point, where the Deputy commander, passes the report on the readiness of the launcher to start. With control and observation point over the voice channel connection command "start". This command on the firing line is the start of a rocket.
Before starting the automatic block launcher generates a voltage required for the implementation timeline of the launch.
At the time of launch on the remote control firing position commander button is enabled "the UIC" and automatically generated message to the remote spy on start. With timer hours single time with the remote control firing position reads the time of the shot, and sets the turn-on delay time LCD mode target illumination, taking into account the total time of flight of the rocket. The value of on-time target illumination is transmitted to the remote scout as a sequence of binary codes.
Scout via LCD continues to follow the target, to keep her in the cross hairs of the sighting channel.
In remote scout is automatically set to the switching time of the laser highlighter, based on the testimony of a single time control the firing position and the remote agent. In the corresponding time signal from the remote control scout is issued via a digital interface, such as RS232, LCD, and the laser beam illuminates the target.
After launch the missile launcher can be translated in a marching position and transported to a new position.
At approach of the missile to the target, the seeker on the missile scans the earth's surface in search of the trace of the laser beam. Upon detection of the laser spot in a controlled rocket generates commands to control surfaces, providing a spread of missiles in the center of the laser spot.
The turn-on time of the laser designator can be chosen constant and equal to, for example, 12 seconds to fly the missile to the target. When such inclusion target illumination for the FIC the new period of time before meetings to easier organize work of the rocket control system. To activate the LCD on the illumination to approach the missile to the target is established that the delay transfer signal to switch on the LCD should not exceed 3 to 6 seconds.
Transformation of coordinates in this way can be produced using the following coordinate systems.
The binding to the terrain LCD and a firing position, it is desirable to produce in a geographic coordinate system (CS) with fixing latitude, longitude and height mesostena.
LCD captures the target in polar IC measurement of distance and angles LCD. In the cockpit of the scout coordinates, introduced with LCD, converted to geographic SK. Through radio coordinates of the topographic binding targets in a geographical IC arrive in the remote control firing position.
In the remote control firing position on the coordinates of the target and firing position determine the range to the target, elevation, and calculate the firing settings in polar IC associated with the launcher; and the X-axis of the coordinate system is oriented to the North. These coordinates induce the launcher.
The rocket on the first segment when flying with the main engine moves along the path defined by the tip launchers. On the second site after the inclusion of the homing head control rocket is in the polar IC connected with the longitudinal axis of the missile.
For the realizatsii method can be applied to the following devices.
As a laser designator / rangefinder, gyrocompass, satellite navigation equipment, remote spy, digital radio and remote control firing position can be used in the devices described in the prototype [Patent RU No. 2247297 from 24.07.03, a Method for firing the controlled missile with semi-active laser homing head].
As automation unit can be used by the automation unit complex "Hermes", is described in [Multi-purpose missile system of the WTO helicopter-based Horizons KBP, No. 3, 2007, p.36-38].
As launchers can be used launcher, described on page 365 in the book [Precision-guided weapons to foreign countries. Volume 1. Anti-tank missile systems: survey and analytical reference. / KBP Tula: publishing house "Badretdinov and Co., 2008].
The missile is described on page 38 publication [Multi-purpose missile system of the WTO helicopter-based Horizons KBP, No. 3, 2007, p.36-38].
The proposed method of firing a missile with semi-active laser homing head compared to the prototype allows to increase the range of the missile and to increase job security with a launcher to fire position. The effectiveness of the proposed method for firing confirmed to complex the modeling stand.
The way of firing a guided missile with semi-active laser homing head, comprising the sequential detection of a target designator, the dimension designator azimuth and distance to a target, topographic binding designator and target areas, and topographic binding targets is carried out in the remote scout calculated, after which the remote scout target coordinates is converted into a sequence of binary codes and pass them on digital radio in the remote control firing position, the dimensioning of the firing of the missiles and launchers perform in the remote control firing position on the coordinates of the target and missile launchers, and remote reconnaissance and remote control firing position establish a single computer time, perform the production start-up, including serial hover launcher at the target on the angles of shooting, the input units firing at the missile launch and guidance of missiles at the target, illuminated laser target designator, and a switch-on signal of the designator is automatically sent from the remote control scout in achieving on-time transmitted from the remote control firing position in the remote spy on digital radio, and topographic binding launchers do with p the power of satellite navigation equipment cockpit firing position, characterized in that the topographic binding launchers to the terrain using satellite navigation equipment cockpit firing position to perform the calculation of the firing settings and set the remote control firing position, together with the tools of the digital radio communication at a distance of 50-100 m from the launcher, ensure that the accuracy of the topographic location of the launcher, target designator and targets for each dimension of the geographic coordinate system did not exceed 50 m calculated in the remote control firing position installation firing the launcher and the missile passed in binary code in the automation unit launchers and rocket deploy the launcher on the angles of azimuth and places units firing, the missile was produced by a signal from the remote control firing position, and a signal to start the rocket passed to the automation unit launchers in the binary code, and the transmission delay to switch on the pointer with remote control firing position in remote scout after launch does not exceed 3-6 C.
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.
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.
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.
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.
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
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.
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
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.
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
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
FIELD: armament, in particular, artillery guided missiles with a laser semi-active homing head locking on n illuminated target in the terminal trajectory leg; the invention is designed for control of fire of mortars and barrel artillery of calibers, types 120, 122, 152, 155 mm, at firing of guided ammunition, as well as of guided missiles with a homing head.
SUBSTANCE: the method consists in the following: the target is detected by a target indicator, then the distances between the target indicator and the target and the firing position and the target are measured with a topographical survey of the target, target indicator and the firing position, computation and realization of the firing settings according to the target and firing position coordinates. Then, missile guidance to the target is performed, it includes a successive gun setting and turn of the missile on target illuminated after the shot by laser radiation of the target indicator, the topographical target survey and conversion of its coordinates to a sequence of binary codes is accomplished with the aid of a reconnaissance panel, and the computation of gun settings is performed with the id of a gun control panel. A common computer time is organized in the reconnaissance panel and in the gun control panel, and after the shot up to the actuation of the target indicator transmission of the value of the time of switching of target indicator laser radiation is performed from the gun control panel to the reconnaissance panel by means of digital radio communication, and the signal of switching of target illuminance is automatically transmitted from the reconnaissance panel to the target indicator at achievement of the time of switching.
EFFECT: enhanced accuracy of fire by a guided missile at a target illuminated by a laser beam due to reduced quantity of "hand" operations and enhanced accuracy of synchronization of the moment of target illumination with the time of the shot; the last property is especially important for destruction of moving targets.
FIELD: homing systems of flight vehicles.
SUBSTANCE: the method consists in the fact that the distance from the flight vehicle to the target by the moment of beginning of homing, the current rate of closure with it, angular velocities of the sight line and the lateral accelerations of the target and guided flight vehicle in the horizontal and vertical planes are measured. After measurements the signals of flight vehicle control in the horizontal and vertical planes are formed according to the relations using the mentioned coordinates of the target and flight vehicle. The high sensitivity of the flight vehicle to the target maneuver is based on the estimation of its lateral accelerations, and the adaptation to the range of the beginning of homing is based on estimation in the procedure of suspension of its navigation parameter.
EFFECT: provided reaction to the maneuver of far located targets and adaptation to the range of the beginning of homing predetermining a more active maneuver of the guided object on a near located target.
FIELD: high-accuracy armament systems, in particular, guidance systems of tactical ballistic missiles.
SUBSTANCE: the method includes the lunching of the missile and its flight on the trajectory having a ballistic leg, on which the moment of separation of the correctable war module is determined, and the correctable war module is separated, and a homing leg. In addition the flight trajectory has a leg of intermediate correction. Prior to the missile launch, the initial conditions for computation of the predicted flight trajectory of the correctable war module are set into the on-board computer via the antenna of the communication radio set and the on-board receiver. After the launch the kinematic parameters of the missile motion are additionally determined on the ballistic leg, and after separation of the correctable war module the predicted miss of the correctable war module is computed on the leg of intermediate correction, and the impulse correction engine is started for reduction of the miss to the minimum value. Before the homing leg the correctable war head is decorated to the operating linear and angular velocity, and the beginning of the homing leg is determined by transmitting a signal from the correctable war module via the radio channel to the target indicator-range finder. At intermediate correction and homing the impulse correction engines are started when the current miss exceeds the allowable value.
EFFECT: enhanced accuracy of guidance.
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.
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.
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.
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.
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
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.
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