CN110686561A

CN110686561A - Warship missile electromagnetic gun

Info

Publication number: CN110686561A
Application number: CN201911125538.4A
Authority: CN
Inventors: 朱幕松
Original assignee: Individual
Current assignee: Zhuhai Tongmi Technology Co ltd
Priority date: 2019-11-18
Filing date: 2019-11-18
Publication date: 2020-01-14
Anticipated expiration: 2039-11-18
Also published as: CN110686561B

Abstract

A warship missile electromagnetic gun is characterized in that a gliding missile is driven in a long and thin multi-coil gun barrel and is accelerated in a long stroke and time through the relay of a plurality of electromagnetic coils, the speed of the gliding missile can be increased to the limit without large electric power, the advancing direction of a warship and the elevation angle of the multi-coil gun barrel are adjusted, the warship missile electromagnetic gun can aim at and shoot a target, the highest speed of the gliding missile, which is emitted out of a gun barrel, is ultrahigh sound speed and is the initial speed of the gliding missile, the gliding missile hits the target by virtue of inertial motion and gliding flight with controllable direction, a camera of the gliding missile searches and locks the target together according to the image information of the target, an infrared sensor according to the heat source information of the target, a left laser radar and a right laser radar according to the reflection information of the target, an intelligent missile control box controls a vertical wing to change the flight direction of the left horizontal wing and a right horizontal wing to change the up-down flight direction, the gliding missile can automatically track and strike the target.

Description

Warship missile electromagnetic gun

Technical Field

The invention relates to the technical field of electromagnetic coil guns, in particular to a warship missile electromagnetic gun.

Background

Compared with the traditional gunpowder cannon, the electromagnetic cannon has the advantages of high projectile speed and long shooting range, the electromagnetic cannon technology is divided into an electromagnetic orbit cannon and an electromagnetic coil cannon, the electromagnetic orbit cannon technology in China is at the world leading level at present, the electromagnetic orbit cannon is encouraged to be equipped on a military warship in China to be tested successfully, the electromagnetic orbit cannon is not equipped on the military warship in some military strong countries including the United states at present and is only in the research and experiment stage, and the electromagnetic orbit cannon has the defects that: the electromagnetic cannonball has the advantages that the electric brush is arranged between the electromagnetic cannonball and the electrified guide rail, when the electromagnetic cannonball is popped out of the cannon, the electrified guide rail is easily burnt by electric arcs generated at the outlet of the electrified guide rail, the electromagnetic coil cannonball does not have the electric brush, the problems are solved, however, the electromagnetic coil cannonball has the defects that the electromagnetic cannonball does not generate a magnetic field, the driving force generated in the electromagnetic coil is insufficient, and if the electromagnetic cannonball is accelerated in a short length of the cannon, the.

Disclosure of Invention

The invention discloses a warship missile electromagnetic gun, aiming at overcoming the defects of the existing electromagnetic orbit gun and the existing electromagnetic coil gun. The warship missile electromagnetic gun mainly comprises a warship, a multi-coil gun barrel, a gliding missile, a missile storage box, an intelligent controller, a missile control keyboard and a storage battery pack, and is characterized in that: a gun bin is arranged on the right rear side of a warship of the warship missile electromagnetic gun, a triangular support is arranged at the bottom of the gun bin, a hydraulic rack is arranged in front of the bottom of the gun bin, an electric hydraulic pump is arranged in front of the hydraulic rack, a hydraulic pipe is arranged between the hydraulic rack and the electric hydraulic pump, an electromagnetic valve is arranged on the hydraulic pipe, a multi-coil gun tube is arranged at the upper ends of the triangular support and the hydraulic rack, a cab is arranged on the left side of the multi-coil gun tube, an intelligent controller, a data information display, an electromagnetic gun control keyboard and a storage battery are arranged in the cab, and a radar detector for detecting; the multi-coil gun barrel is provided with a gun barrel pipe, the gun barrel pipe is a non-magnetic-conductivity copper pipe, the cross section figures of the inner circle and the outer circle of the gun barrel pipe are both in a segmental shape, the outer circle of the gun barrel pipe is provided with a plurality of coil frameworks, enameled wires are wound in the coil frameworks to manufacture electromagnetic coils, the cross section figures of the inner circle and the outer circle of each electromagnetic coil are both in a segmental shape, the distances among the electromagnetic coils are equal to the lengths of the electromagnetic coils, the outer circles of the electromagnetic coils are provided with gun barrels, each gun barrel is a magnetic-conductivity steel pipe, the cross section figures of the inner circle and the outer circle of each gun barrel are both in a segmental shape, the front ends of the electromagnetic coils are consistent with the front ends of the gun barrel pipe and the gun barrel, the rear ends of the electromagnetic coils are consistent with the rear end of the gun barrel, the electromagnetic coils are installed with the gun barrel and the gun barrel in a close fit, a magnetic flow loop is formed between each electromagnetic coil, the intelligent control device comprises an intelligent controller, a sensor hole, a Hall sensor switch, a plurality of bistable switch circuits, an electromagnetic driver, a Hall sensor switch and a Hall sensor switch, wherein the sensor hole at the rear end of a first electromagnetic coil at the rear end of a gun bore tube is provided with the Hall sensor switch, the Hall sensor switch is arranged in a sensing hole at the middle position between the electromagnetic coils, the distance between the Hall sensor switches is divided equally, the electromagnetic driver control module, the missile speed sensing conversion module and the motor control module are arranged in the intelligent controller, the electromagnetic driving control module is provided with a plurality of same bistable switch circuits, each bistable switch circuit comprises a bistable trigger and a switch triode, each bistable switch circuit comprises the electromagnetic driver and the electromagnetic coils as well as the Hall sensor switches, and the circuit connection of the electromagnetic driver is as: the upper input end of the bistable trigger is connected with a Hall sensor switch, the lower input end of the bistable trigger is connected with a Hall sensor switch, the output end of a switch triode is connected with the lower end of an electromagnetic coil, the grounding end of a bistable switch circuit is connected with the negative electrode of a storage battery pack, the power supply end of the bistable switch circuit and the upper end of the electromagnetic coil are connected with the positive electrode of the storage battery pack, the storage battery pack is an electromagnetic gun power supply carried by a warship, the storage battery pack is charged by a ship-borne generator, and a plurality of identical electromagnetic drivers are connected; the rear end of a gun bore tube is connected with a missile storage box, a plurality of gliding missiles are stored in the missile storage box, a single gliding missile falls to the bottom of a missile cabin for loading, driving, accelerating and launching, a triangular plate support is welded at the rear lower end of the gun bore, a front connection lug and a rear connection lug are welded at the lower end of the triangular plate support, the front connection lug is provided with a front joint shaft, the front joint shaft is connected with the upper end of a hydraulic frame, the rear connection lug is provided with a rear joint shaft, the rear joint shaft is connected with the upper end of the triangular support, a connection lug is arranged at the bottom of the gun bore, the connection lug is provided with a joint shaft, the joint shaft is connected with the lower end of the hydraulic frame, the hydraulic frame is provided with a hydraulic cylinder, a plunger is arranged in the hydraulic cylinder, an; the gliding missile is made of magnetic conductive iron materials and is provided with a cylindrical missile body, the cross section of the missile body is in a segmental shape, the cylindrical missile body is in loose fit and sliding fit with the inner circle of a gun bore tube, the gliding missile realizes the circumferential positioning of the missile body by means of the segmental shape, the front end and the rear end of the cylindrical missile body are both in a hemispherical shape, the center of the cylindrical missile body is provided with a square hole, a square tube is installed in the square hole in a close fit manner, the right end of the cylindrical missile body is provided with a circular groove, permanent magnetic particles are installed in the circular groove, the rear end in the inner direction of the square tube is provided with a left horizontal wing motor, the center of the left horizontal wing motor is provided with a left driving shaft, the square tube is provided with a left shaft hole, the left driving shaft is penetrated into the left shaft hole, the left driving shaft is provided with a left horizontal wing, the rear end in the inner direction of the square tube is provided with a right horizontal wing, the left horizontal wing and the right horizontal wing have the same size, are bilaterally symmetrical, have the same model and are bilaterally symmetrical, a vertical wing motor is arranged at the rear end of the left horizontal wing motor and the right horizontal wing motor, a vertical driving shaft is arranged at the upper end of the vertical wing motor, an upper shaft hole is arranged on a square tube, the vertical driving shaft penetrates into the upper shaft hole, the vertical wing is arranged at the upper end of the vertical driving shaft, the length of the vertical wing is longer than that of the left horizontal wing and the right horizontal wing, the left horizontal wing motor, the right horizontal wing motor and the vertical wing motor are harmonic reducer motors, the harmonic reducer motor is a low-rotating-speed motor integrating a harmonic reducer and a permanent magnet brushless motor, the left horizontal wing and the right horizontal wing are driven to respectively turn up and down when the left horizontal wing motor rotates in positive and negative directions, the vertical wing is driven to turn left and right when the vertical wing motor rotates in positive and, the rear end of the intelligent control box is provided with a dry battery, the front end of the square tube is provided with a spherical cover plate, the spherical cover plate is consistent with the spherical surface of the front end of the cylinder missile body, the center of the spherical cover plate is provided with a camera hole, a camera is arranged in the camera hole, the spherical cover plate around the camera hole is provided with 4 sensor holes, an infrared sensor is arranged in the sensor hole at the upper end of the camera hole, a left laser radar sensor is arranged in the sensor hole at the left end of the camera hole, a right laser radar sensor is arranged in the sensor hole at the right end of the camera hole, a starting indicator lamp is arranged in the sensor hole at the lower end of the camera hole, the upper end of the cylinder missile body is provided with a steel bar hole, the steel bar hole penetrates through the wall of the square tube to be directly communicated with the square tube, the power switch of the gliding missile is controlled, the steel bar penetrates into a lock hole of the gliding missile to trigger the Hall sensor, the pulley missile power supply is turned on, the starting indicator light of the gliding missile is on, a plurality of gliding missiles are started and then are put into a missile storage box, the output lines of the Hall sensor, the camera, the infrared sensor, the left laser radar, the right laser radar and the gyro level sensor are respectively connected with the relevant input ends of the intelligent control module, a plurality of output ends of the brushless motor control module are respectively connected with the left horizontal wing motor, the right horizontal wing motor and the vertical wing motor, and a plurality of output ends of the intelligent control module are respectively connected with the input end of the brushless motor control module and the starting indicator light; the gliding missile moves forwards in the bore, when the permanent magnet particles are aligned with the Hall sensor, the Hall sensor is opened to trigger the bistable trigger to enable the switch triode to be switched on to supply power to the front end electromagnetic coil of the gliding missile, the electromagnetic coil generates an electromagnetic field to attract the gliding missile to move forwards, the length of the cylinder missile body is equal to that of the electromagnetic coil, when the cylinder missile body is attracted to the center of the electromagnetic coil, the front end and the rear end of the cylinder missile body are consistent with the front end and the rear end of the electromagnetic coil, the permanent magnet particles are aligned with the Hall sensor to be switched off, the Hall sensor is switched off to trigger the bistable trigger to enable the switch triode to be switched off, the electromagnetic coil is powered off, the gliding missile continues to move forwards by means of inertia after being separated from the magnetic force, the gliding missile can obtain the electromagnetic force and lose the electromagnetic force, the gliding missile is attracted by a plurality of electromagnetic coils in front to be relayed and accelerated, the speed is rapidly increased, and finally the gliding missile is taken out of the chamber and shot towards a front target; the missile speed sensing conversion module is connected with a signal that a first Hall sensor at the front end of a gun bore tube is opened at the input end, a signal that a third Hall sensor at the front end of the gun bore tube is opened at the input end, and the output end of the missile speed sensing conversion module is connected with a data information display.

The electromagnetic gun of the warship missile is provided with a missile storage box, the upper end in the missile storage box is provided with a missile pushing vehicle, the missile pushing vehicle is provided with a square frame vehicle frame, the lower end of the square frame vehicle frame is provided with a missile cabin, a plurality of gliding missiles are stored in the missile cabin, the width in the missile storage box is equal to the length of the gliding missiles, the thickness in the missile storage box is equal to the width of the gliding missiles, the height in the missile storage box is equal to the sum of the height of the gliding missiles and the height of the square frame vehicle frame, the front end of the bottom of the missile cabin is connected with a gun barrel pipe, the front end of the square frame vehicle frame is provided with an upper vehicle shaft and a lower vehicle shaft, the left and right front ends of the upper and lower vehicle shafts are respectively provided with an upper and right front wheel and a lower left and right wheel, the left and right ends of the upper and lower vehicle shafts are respectively provided with an upper and right, the front end of the missile storage box is provided with a linear groove, the connecting plate is positioned in the linear groove, the front end of the connecting plate is provided with a speed reducing motor, the right end of the speed reducing motor is provided with a driving gear, the front end of the missile storage box is provided with a rack, the driving gear is meshed with the rack, when the speed reducing motor rotates forwards and backwards, the missile pushing vehicle is driven up and down, the four wheels are supported at the front end and the rear end in the missile storage box, the meshing clearance between the driving gear and the rack is stabilized, the left end and the right end of the missile storage box are both provided with a strip-shaped groove, the left strip-shaped groove and the right strip-shaped groove are both provided with steel plate springs, the left steel plate spring and the right steel plate spring are equal in size and are bilaterally symmetrical, the lower ends of the left steel plate spring and the right steel plate spring are provided with elastic grippers, the left end and the right end of a first gliding, a Hall sensor stop is arranged in an upper sensor hole, a Hall switch sensor is arranged in a lower sensor hole, a cylindrical permanent magnet is arranged at the right end of a connecting plate, a sensor hole is arranged at the right end of a missile repeating box, a Hall stop sensor is arranged in the sensor hole, output lines of the Hall sensor stop, the Hall switch sensor, the Hall stop sensor and a missile control keyboard are respectively connected with relevant input ends of a motor control module, the output end of the motor control module is respectively connected with a speed reducing motor, an electric hydraulic pump and an electromagnetic valve, the power end of the motor control module is connected with a storage battery, the electromagnetic gun control keyboard is provided with an elevation angle upward button, an elevation angle downward button, a reversing button, a missile single-launching button and a missile continuous launching button, the reversing button is pressed to trigger the motor control module, the speed reducing motor is controlled to, the Hall stop sensor triggers a generator control module, the power supply of a speed reducing motor is turned off, a missile pusher stops, a magazine is arranged in the space below the missile pusher, a magazine door is arranged at the rear end of a missile repeating box, the magazine door is opened, a plurality of gliding missiles with the power supply opened are loaded into the magazine, the generator control module is triggered by pressing a single missile launching button, the speed reducing motor rotates clockwise, the missile pusher pushes down a plurality of gliding missiles to push a first gliding missile out of an elastic gripper, when the permanent magnetic particles of a second gliding missile at the lower ends of the plurality of gliding missiles are aligned with the Hall switch sensor, the Hall switch sensor outputs pulse signals to trigger the generator control module, the speed reducing motor automatically stops, the elastic gripper grabs the left end and the right end of the second gliding missile, the first gliding missile falls into the bottom of the magazine by separating from the grabbing force of left and right steel plate springs, the permanent magnetic particles of the first gliding missile are aligned with the Hall sensor, the Hall sensor starts to trigger the intelligent controller to supply power to a first electromagnetic coil at the rear end, the electromagnetic coil generates an electromagnetic field to attract the gliding missile to move forwards, the pulley gliding missile is accelerated by the relay of a plurality of electromagnetic coils and then is launched out of a chamber, a trigger pulse is generated by pressing a single launching button of the missile once to launch a gliding missile, a plurality of trigger pulses are generated by pressing a continuous launching button of the missile, a plurality of gliding missiles are launched continuously, when the last gliding missile falls into the bottom of a missile cabin, the missile pusher moves downwards to a cylindrical permanent magnet to be aligned with the Hall sensor to stop, the Hall sensor stops to trigger a motor control module to turn off a speed reducing motor power supply, the missile pusher stops, an elevation angle upward button is pressed, the electric hydraulic pump and the electromagnetic valve are turned on by the trigger motor control module, the elevation angle of the multi-coil gun barrel is adjusted upwards, the elevation angle of the multi-coil gun barrel is adjusted downwards, the solenoid valve of the button is released to be closed after the elevation angle of the multi-coil gun barrel is determined, and the elevation angle of the multi-coil gun barrel is fixed.

The warship missile electromagnetic gun has the beneficial effects that: the length of the multi-coil gun barrel is slightly less than that of a warship and is greater than that of the existing electromagnetic gun barrel, the multi-coil gun barrel belongs to a long and thin type gun barrel, a triangular plate support at the lower end of the multi-coil gun barrel is used for enhancing the strength of the long and thin type gun barrel, a gliding missile moves in the long and thin type gun barrel and can be accelerated in a long time and in a long stroke through the relay of a plurality of electromagnetic coils, so that the speed of the gliding missile can be improved to the limit without needing large electric power, the electromagnetic gun of the warship missile is simple in structure, light in weight and small in energy consumption, and is suitable for being arranged on the warship, targets found by radar of the warship are displayed on a data information display, the advancing direction of the warship and the elevation angle of the multi-coil gun barrel are adjusted, the electromagnetic gun of the warship missile can aim at the targets, the highest speed of the gliding missile, which is the initial speed of the gliding missile, and the gliding missile can hit the targets by means of inertial motion, the intelligent control box of the gliding missile receives the instruction of the gyro level sensor to drive the left horizontal wing and the right horizontal wing, so that the left horizontal wing and the right horizontal wing can slide to keep a horizontal state, the camera of the gliding missile can search and lock the target together according to the image information of the target, the infrared sensor can control the heat source information of the target, and the left laser radar and the right laser radar can search and lock the target together according to the reflection information of the target, so that a control signal of the flight direction can be sent to the intelligent control box, the vertical wing can be controlled to change the left and right flight directions of the missile, and the left horizontal wing and the right horizontal wing can be controlled to change the up and down flight directions of the missile, so that the gliding missile can automatically track the target.

Drawings

Fig. 1 is a schematic diagram of a right-view integral structure of a warship missile electromagnetic gun in a horizontal collection state.

Fig. 2 is a schematic diagram of the integral structure of a warship missile in a high-altitude launching state from the bottom.

Fig. 3 is an electrical schematic of an electromagnetic drive.

Fig. 4 is a right view structure schematic diagram of a gliding missile.

Figure 5 is a schematic rear sectional view of a multi-coil barrel.

FIG. 6 is a right view of the missile storage box.

Detailed Description

In fig. 1-6, a gun bin 2 is arranged at the right rear side of a warship 1 of the warship missile electromagnetic gun, a triangular support 3 is arranged at the bottom of the gun bin, a hydraulic frame 4 is arranged in front of the bottom of the gun bin, an electric hydraulic pump 5 is arranged in front of the hydraulic frame, a hydraulic pipe 6 is arranged between the hydraulic frame and the electric hydraulic pump, an electromagnetic valve 7 is arranged on the hydraulic pipe, a multi-coil gun barrel 8 is arranged at the upper ends of the triangular support and the hydraulic frame, a cab 9 is arranged at the left side of the multi-coil gun barrel, an intelligent controller 10, a data information display 11, an electromagnetic gun control keyboard 12 and a storage battery pack 13 are arranged in the cab, and a radar detector for; the multi-coil gun barrel is provided with a gun barrel 14, the gun barrel is a non-magnetic-conductivity copper pipe, the cross section figures of the inner circle and the outer circle of the gun barrel are both in a segmental shape, the outer circle of the gun barrel is provided with a plurality of coil frameworks 15, enameled wires are wound in the coil frameworks to manufacture electromagnetic coils 16, the cross section figures of the inner circle and the outer circle of each electromagnetic coil are both in a segmental shape, the equal distance among the electromagnetic coils is equal to the length of each electromagnetic coil, the outer circles of the electromagnetic coils are provided with gun barrels 17, each gun barrel is a magnetic-conductivity steel pipe, the cross section figures of the inner circle and the outer circle of each gun barrel are both in a segmental shape, the front ends of the electromagnetic coils are consistent with the front ends of the gun barrel and the gun barrel, the rear ends of the electromagnetic coils are consistent with the rear end of the gun barrel, the electromagnetic coils are installed in close fit with the gun barrel and the gun barrel, a magnetic flow loop is formed between each electromagnetic coil and the gun barrel and is positioned, the intelligent control device is characterized in that a Hall sensor switch 18 is arranged in a sensor hole at the rear end of a first electromagnetic coil at the rear end of a gun bore tube, Hall sensor switches are arranged in sensing holes at the middle positions among the electromagnetic coils, the distance among the Hall sensor switches is divided equally, Hall sensor switches 19 are arranged in sensing holes at the inner positions of the electromagnetic coils, the distance among the Hall sensor switches is divided equally, an electromagnetic drive control module, a missile speed sensing conversion module and a motor control module are arranged in the intelligent controller, the electromagnetic drive control module is provided with a plurality of same bistable switch circuits, each bistable switch circuit is composed of a bistable trigger 20 and a switch triode 21, each bistable switch circuit, the electromagnetic coils 16, the Hall sensor switches 18 and the Hall sensor switches 19 form an electromagnetic driver, and the electromagnetic driver is connected with the circuits as follows: the upper input end of the bistable trigger is connected with a Hall sensor switch 18, the lower input end of the bistable trigger is connected with a Hall sensor switch 19, the output end of a switch triode is connected with the lower end of an electromagnetic coil, the grounding end of a bistable switch circuit is connected with the negative electrode of a storage battery pack, the power supply end of the bistable switch circuit and the upper end of the electromagnetic coil are connected with the positive electrode of a storage battery pack 13, the storage battery pack is an electromagnetic gun power supply carried by a warship, the storage battery pack is charged by a ship-borne generator, and a plurality of identical electromagnetic drivers are connected; the rear end of a gun bore tube is connected with a missile storage box 22, a plurality of gliding missiles 23 are stored in the missile storage box, a single gliding missile falls to the bottom of a missile cabin for loading, driving, accelerating and launching, the rear lower end of the gun bore is welded with a triangular plate support 24, the lower end of the triangular plate support is welded with a front connecting lug 25 and a rear connecting lug 26, the front connecting lug is provided with a front joint shaft 27, the front joint shaft is connected with the upper end of a hydraulic rack, the rear connecting lug is provided with a rear joint shaft 28, the rear joint shaft is connected with the upper end of the triangular support, the bottom of the gun cabin is provided with a connecting lug 29, the connecting lug is provided with a joint shaft 30, the joint shaft is connected with the lower end of the hydraulic rack, the hydraulic rack is provided with a hydraulic cylinder 31, a plunger 32 is arranged in the hydraulic cylinder, and a controllable; the gliding missile is made of magnetic conductive iron materials, the gliding missile is provided with a cylindrical missile body 33, the cross section figure of the missile body is in a segmental shape, the cylindrical missile body is in loose fit sliding fit with the inner circle of a gun bore tube, the gliding missile realizes the positioning of the circumferential position of the missile body by means of the segmental shape, the front end and the rear end of the cylindrical missile body are both in a hemispherical shape, the center of the cylindrical missile body is provided with a square hole, a square tube 34 is installed in the square hole in a close fit manner, the right end of the cylindrical missile body is provided with a circular groove, permanent magnetic particles 35 are installed in the circular groove, the rear end of the inner square of the square tube is provided with a left horizontal wing motor 36, the center of the left horizontal wing motor is provided with a left driving shaft 37, the square tube is provided with a left shaft hole, the left driving shaft penetrates into the left shaft hole, the left driving shaft is provided with a left horizontal wing 38, the rear end of the inner square tube is, the right driving shaft is provided with a right horizontal wing 41, the left horizontal wing and the right horizontal wing have the same size and are bilaterally symmetrical, the left horizontal wing and the right horizontal wing have the same motor model and are bilaterally symmetrical, the rear ends of the left horizontal wing motor and the right horizontal wing motor are provided with a vertical driving shaft 43, the square tube is provided with an upper shaft hole, the vertical driving shaft penetrates into the upper shaft hole, the upper end of the vertical driving shaft is provided with a vertical wing 44, the length of the vertical wing is greater than that of the left horizontal wing and the right horizontal wing, the left horizontal wing motor, the right horizontal wing motor and the vertical wing motor are harmonic reducer motors, the harmonic reducer motor is a low-rotating-speed motor with a harmonic reducer and a permanent magnet brushless motor integrated, the left horizontal wing and the right horizontal wing are driven to respectively turn up and down when the left horizontal wing motor rotates forwards and reversely, the vertical wing motor drives the vertical wing to turn left and right when, The intelligent control box comprises a brushless motor control module and an intelligent control module, wherein a dry battery 46 is arranged at the rear end of the intelligent control box, a spherical cover plate 47 is arranged at the front end of a square pipe, the spherical cover plate is consistent with the spherical surface of the front end of a cylinder missile body, a camera hole is formed in the center of the spherical cover plate, a camera 48 is installed in the camera hole, 4 sensor holes are formed in the spherical cover plate around the camera hole, an infrared sensor 49 is installed in a sensor hole at the upper end of the camera hole, a left laser radar sensor is installed in a sensor hole at the left end of the camera hole, a right laser radar sensor is installed in a sensor hole at the right end of the camera hole, a starting indicator lamp 50 is installed in a sensor hole at the lower end of the camera hole, a steel bar hole 51 is formed in the upper end of the cylinder missile body, the steel bar hole penetrates through the wall of the square pipe to be directly communicated, the power switch of the gliding missile is controlled, the steel bar penetrates into a lock hole of the gliding missile to trigger the Hall sensor, the pulley missile power supply is turned on, the starting indicator light of the gliding missile is on, a plurality of gliding missiles are started and then are loaded into the missile continuous launching box, the output lines of the Hall sensor, the camera, the infrared sensor, the left laser radar, the right laser radar and the gyro level sensor are respectively connected with the relevant input ends of the intelligent control module, a plurality of output ends of the brushless motor control module are respectively connected with the left horizontal wing motor, the right horizontal wing motor and the vertical wing motor, and a plurality of output ends of the intelligent control module are respectively connected with the input end of the brushless motor control module and the starting indicator light; the gliding missile moves forwards in the bore, when the permanent magnet particles are aligned with the Hall sensor, the Hall sensor is opened to trigger the bistable trigger to enable the switch triode to be switched on to supply power to the front end electromagnetic coil of the gliding missile, the electromagnetic coil generates an electromagnetic field to attract the gliding missile to move forwards, the length of the cylinder missile body is equal to that of the electromagnetic coil, when the cylinder missile body is attracted to the center of the electromagnetic coil, the front end and the rear end of the cylinder missile body are consistent with the front end and the rear end of the electromagnetic coil, the permanent magnet particles are aligned with the Hall sensor to be switched off, the Hall sensor is switched off to trigger the bistable trigger to enable the switch triode to be switched off, the electromagnetic coil is powered off, the gliding missile continues to move forwards by means of inertia after being separated from the magnetic force, the gliding missile can obtain the electromagnetic force and lose the electromagnetic force, the gliding missile is attracted by a plurality of electromagnetic coils in front to be relayed and accelerated, the speed is rapidly increased, and finally the gliding missile is taken out of the chamber and shot towards a front target; the missile speed sensing conversion module is connected with a signal that a first Hall sensor at the front end of a gun bore tube is opened at the input end, a signal that a third Hall sensor at the front end of the gun bore tube is opened at the input end, and the output end of the missile speed sensing conversion module is connected with a data information display.

The electromagnetic gun of the warship missile is provided with a missile storage box 22, the upper end in the missile storage box is provided with a missile pushing vehicle, the missile pushing vehicle is provided with a square frame 55, the lower end of the square frame is provided with a missile bin 56, a plurality of gliding missiles are stored in the missile bin, the width in the missile storage box is equal to the length of the gliding missiles, the thickness in the missile storage box is equal to the width of the gliding missiles, the height in the missile storage box is equal to the sum of the height of the plurality of gliding missiles and the height of the square frame, the front end of the bottom of the missile bin is connected with a gun barrel, the front end of the square frame is provided with an upper wheel shaft 57 and a lower wheel shaft 58, the left and right ends of an upper wheel shaft and a lower wheel shaft are respectively provided with a front upper left wheel 59 and a right wheel 60, the rear end of the square frame is provided with an upper wheel shaft 61 and a lower wheel shaft 62, the left and right ends of the, the front end of the missile storage box is provided with a line groove 66, the connecting plate is positioned in the line groove, the front end of the connecting plate is provided with a speed reducing motor 67, the right end of the speed reducing motor is provided with a driving gear 68, the front end of the missile storage box is provided with a rack 69, the driving gear is meshed with the rack, the missile pusher is driven to move up and down when the speed reducing motor rotates forwards and backwards, the four wheels are supported at the front end and the rear end of the inner wall of the missile repeating box to stabilize the meshing clearance between the driving gear and the rack, the left end and the right end of the missile box are both provided with a strip groove 70, the left strip groove and the right strip groove are both provided with a steel plate spring 71, the left steel plate spring and the right steel plate spring are equal in size and are bilaterally symmetrical, the lower ends of the left steel plate spring and the right steel plate spring are provided with elastic grippers, the left end and the right end of a first gliding missile at the lower ends, a Hall sensor stop 72 is arranged in an upper sensor hole, a Hall off sensor 73 is arranged in a lower sensor hole, a cylindrical permanent magnet 74 is arranged at the right end of a connecting plate, a sensor hole is arranged at the right end of a missile storage box, a Hall stop sensor 75 is arranged in the sensor hole, output lines of the Hall sensor stop, the Hall off sensor, the Hall stop sensor and a missile control keyboard are respectively connected with relevant input ends of a motor control module, the output end of the motor control module is respectively connected with a speed reducing motor, an electric hydraulic pump and an electromagnetic valve, a power supply end of the motor control module is connected with the anode of a storage battery, the electromagnetic gun control keyboard is provided with an elevation angle upward button, an elevation angle downward button, a backing button, a missile single-launching button and a missile continuous launching button, a backing button is pressed to contact the, the cylindrical permanent magnet is aligned with the Hall stop sensor, the Hall stop sensor triggers the generator control module to turn off the power supply of the speed reducing motor, the missile pusher stops, the space below the missile pusher is a missile bin, the rear end of the missile repeating box is provided with a missile bin door 76, the missile bin door is opened, a plurality of gliding missiles with the power supply opened are loaded into the missile bin, the generator control module is triggered by pressing a single missile launching button, the speed reducing motor rotates clockwise, the missile pusher pushes down a plurality of gliding missiles, a first gliding missile at the lower end is pushed out of an elastic gripper, when the permanent magnet particles of a second gliding missile at the lower ends of the plurality of gliding missiles are aligned with the Hall off sensor, the Hall off sensor outputs a pulse signal to trigger the generator control module, the speed reducing motor automatically stops, the elastic gripper grabs the left end and the right end of the second gliding missile, and the first gliding missile falls into the bottom of the missile bin by separating from, the permanent magnetic particles of a first gliding missile are aligned with a Hall sensor switch, the Hall sensor switch triggers an intelligent controller to supply power to a first electromagnetic coil at the rear end, the electromagnetic coil generates an electromagnetic field to attract the gliding missile to move forwards, a pulley gliding missile is accelerated by the relay of a plurality of electromagnetic coils and then is launched into a chamber, a single launching button of the missile is pressed once to be a triggering pulse, a gliding missile is launched, a plurality of triggering pulses are formed when the continuous launching button of the missile is pressed, a plurality of gliding missiles are launched continuously, when the last gliding missile falls into the bottom of a missile cabin, a missile pusher moves downwards to a cylindrical permanent magnet to be aligned with the Hall sensor to stop, the Hall sensor stops triggering a motor control module to turn off a power supply of a speed reducing motor, the missile pusher stops, an elevation angle up button is pressed, the triggering motor control module turns on an electric hydraulic pump and an electromagnetic valve, and, pressing an elevation downward button to trigger a generator control module to close the electric hydraulic pump, adjusting the elevation of the multi-coil gun barrel downward, loosening an upward or downward button to close an electromagnetic valve after the elevation of the multi-coil gun barrel is determined, and fixing the elevation of the multi-coil gun barrel.

The length of the multi-coil gun barrel is slightly less than that of a warship and is greater than that of the existing electromagnetic gun barrel, the multi-coil gun barrel belongs to a long and thin type gun barrel, a triangular plate support at the lower end of the multi-coil gun barrel is used for enhancing the supporting strength of the long and thin type gun barrel, a gliding missile moves in the long and thin type gun barrel and can be accelerated in a long stroke and time through the relay of a plurality of electromagnetic coils, so that the speed of the gliding missile can be improved to the limit without needing large electric power, the electromagnetic gun of the warship missile is simple in structure, light in weight and small in energy consumption, and is suitable for being arranged on the warship, a target discovered by a radar of the warship is displayed on a data information display, the advancing direction of the warship and the elevation angle of the multi-coil gun barrel are adjusted, the electromagnetic gun of the warship can aim at the target, the highest speed of the gliding missile, which is the ultrahigh sonic speed, is the initial, the intelligent control box of the gliding missile receives the instruction of the gyro level sensor to drive the left horizontal wing and the right horizontal wing, so that the left horizontal wing and the right horizontal wing are glidingly kept in a horizontal state, the camera of the gliding missile searches and locks the target together according to the heat source information of the target and the reflection information of the target by the left laser radar and the right laser radar according to the image information of the target, a control signal of the flight direction is sent to the intelligent control box, the vertical wing is controlled to change the left flight direction and the right flight direction of the missile, the left horizontal wing and the right horizontal wing are controlled to change the up-and-down flight direction of the missile, so that the gliding missile automatically tracks the target and hits the target, the gliding missile has large mass, large kinetic energy killing force and strong penetrating force, and the gliding missile is suitable for hitting the target in the air, on the sea or on the land.

Claims

1. The utility model provides a warship guided missile electromagnetic gun, comprises warship, multicoil gun barrel, gliding missile, guided missile bin, intelligent control ware, guided missile control keyboard and storage battery, its characterized in that: a gun bin (2) is arranged on the right rear side of a warship (1) of the warship missile electromagnetic gun, a triangular support (3) is arranged at the bottom of the gun bin, a hydraulic rack (4) is arranged in front of the bottom of the gun bin, an electric hydraulic pump (5) is arranged in front of the hydraulic rack, a hydraulic pipe (6) is arranged between the hydraulic rack and the electric hydraulic pump, an electromagnetic valve (7) is arranged on the hydraulic pipe, a multi-coil gun tube (8) is arranged at the upper ends of the triangular support and the hydraulic rack, a cab (9) is arranged on the left side of the multi-coil gun tube, an intelligent controller (10), a data information display (11), an electromagnetic gun control keyboard (12) and a storage battery (13) are arranged in; the multi-coil gun barrel is provided with a gun barrel pipe (14), the gun barrel pipe is a non-magnetic-conductivity copper pipe, the cross section figures of the inner circle and the outer circle of the gun barrel pipe are both in a segmental shape, the outer circle of the gun barrel pipe is provided with a plurality of coil frameworks (15) which are equally divided, enameled wires are wound in the coil frameworks to form an electromagnetic coil (16), the cross section figures of the inner circle and the outer circle of the electromagnetic coil are both in a segmental shape, the equally divided distances among the electromagnetic coils are equal to the length of the electromagnetic coil, the outer circle of the electromagnetic coils is provided with a gun barrel (17), the gun barrel is a magnetic-conductivity steel pipe, the cross section figures of the inner circle and the outer circle of the gun barrel are both in a segmental shape, the front end of the electromagnetic coil is consistent with the front end of the gun barrel pipe and the front end of the gun barrel, the rear end of the electromagnetic coil is consistent with the rear end of the gun barrel, the electromagnetic coils are, the intelligent controller is characterized in that the intelligent controller is positioned at the right end of a bore tube, a plurality of sensor holes are formed in a straight line on the diameter position of the bore tube, Hall sensor switches (18) are installed in the sensor holes at the rear end of a first electromagnetic coil at the rear end of the bore tube, Hall sensor switches are installed in the sensor holes at the middle positions among the electromagnetic coils, the distance between the Hall sensor switches is divided equally, an electromagnetic driving control module, a missile speed sensing conversion module and a motor control module are installed in the intelligent controller, the electromagnetic driving control module is provided with a plurality of identical bistable switch circuits, each bistable switch circuit is composed of a bistable trigger (20) and a switch triode (21), and the bistable switch circuits, the electromagnetic coils (16), the Hall sensor switches (18) and the Hall sensor switches (19) form an electromagnetic driver, the circuit connections of the electromagnetic driver are: the upper input end of the bistable trigger is connected with a Hall sensor switch (18), the lower input end of the bistable trigger is connected with a Hall sensor switch (19), the output end of a switch triode is connected with the lower end of an electromagnetic coil, the grounding end of the bistable switch circuit is connected with the negative electrode of a storage battery pack, the power end of the bistable switch circuit and the upper end of the electromagnetic coil are connected with the positive electrode of the storage battery pack (13), the storage battery pack is an electromagnetic gun power supply carried by a warship, the storage battery pack is charged by a ship-borne generator, and a plurality of identical electromagnetic drivers are connected in parallel; the rear end of a gun bore tube is connected with a missile storage box (22), a plurality of gliding missiles (23) are stored in the missile storage box, a single gliding missile falls to the bottom of a missile cabin for loading, driving, accelerating and launching, a triangular plate support (24) is welded at the rear lower end of the gun bore, a front connecting lug (25) and a rear connecting lug (26) are welded at the lower end of the triangular plate support, the front connecting lug is provided with a front joint shaft (27), the front joint shaft is connected with the upper end of a hydraulic rack, the rear connecting lug is provided with a rear joint shaft (28), the rear joint shaft is connected with the upper end of the triangular support, the bottom of the gun cabin is provided with a connecting lug (29), the connecting lug is provided with a joint shaft (30), the joint shaft is connected with the lower end of the hydraulic rack, the hydraulic rack is provided with a hydraulic cylinder (31), a plunger (, adjusting the elevation angle of the gun barrel up and down; the gliding missile is made of magnetic conductive iron materials, the gliding missile is provided with a cylindrical missile body (33), the cross section of the cylindrical missile body is in a segmental shape, the excircle of the cylindrical missile body is in loose fit sliding fit with the inner circle of a bore tube, the gliding missile realizes the positioning of the circumferential position of the cylindrical missile body by means of the segmental shape, the front end and the rear end of the cylindrical missile body are both in a hemispherical shape, the center of the cylindrical missile body is provided with a square hole, a square tube (34) is tightly installed in the square hole, the right end of the cylindrical missile body is provided with a round groove, permanent magnetic particles (35) are installed in the round groove, the rear end of the inner square of the square tube is provided with a left horizontal wing motor (36), the center of the left horizontal wing motor is provided with a left driving shaft hole (37), the square tube is provided with a left shaft hole, the left driving shaft penetrates into the left shaft hole, the left horizontal wing (38) is installed on the left driving shaft, the, the square tube is provided with a right shaft hole, a right driving shaft penetrates into the right shaft hole, the right driving shaft is provided with a right horizontal wing (41), the left horizontal wing and the right horizontal wing have the same size and are bilaterally symmetrical, the models of the left horizontal wing motor and the right horizontal wing motor are the same and are bilaterally symmetrical, the rear ends of the left horizontal wing motor and the right horizontal wing motor are provided with a vertical wing motor (42), the upper end of the vertical wing motor is provided with a vertical driving shaft (43), the square tube is provided with an upper shaft hole, the vertical driving shaft penetrates into the upper shaft hole, the upper end of the vertical driving shaft is provided with a vertical wing (44), the length of the vertical wing is greater than that of the left horizontal wing and the right horizontal wing, the left horizontal wing motor, the right horizontal wing motor and the vertical wing motor are harmonic reducer motors, the harmonic reducer motor is a low-speed motor with a harmonic reducer and a permanent magnet brushless motor, an intelligent control box (45) is arranged in the square tube, a gyro level sensor, a brushless motor control module and an intelligent control module are arranged in the intelligent control box, a dry battery (46) is arranged at the rear end of the intelligent control box, a spherical cover plate (47) is arranged at the front end of the square tube, the spherical cover plate is consistent with the spherical surface at the front end of the cylinder body, a camera hole is arranged at the center of the spherical cover plate, a camera (48) is arranged in the camera hole, 4 sensor holes are arranged on the spherical cover plate around the camera hole, an infrared sensor (49) is arranged in the sensor hole at the upper end of the camera hole, a left laser radar sensor is arranged in the sensor hole at the left end of the camera hole, a right laser radar sensor is arranged in the sensor hole at the right end of the camera hole, a starting indicator lamp (50) is, a Hall sensor (52) is arranged in the square tube close to the steel bar hole, the gliding missile is provided with a starting steel bar (53), the lower end of the starting steel bar is provided with a permanent magnet (54), the Hall sensor is triggered to be in a switch state of switching on or off when the permanent magnet is close to the Hall sensor, thereby controlling a power switch of the gliding missile, leading the steel bar to penetrate into a lock hole of the gliding missile to trigger the Hall sensor, turning on a pulley missile power supply, leading the starting indicator lamp of the gliding missile to be bright, leading a plurality of gliding missiles to be loaded into a missile storage box from a missile cabin door after being started, the output lines of the Hall sensor, the camera, the infrared sensor, the left laser radar, the right laser radar and the gyro level sensor are respectively connected with the relevant input ends of the intelligent control module, a plurality of output ends of the brushless motor control module are respectively connected with the left horizontal wing motor, the right horizontal wing motor and the vertical wing motor, and a plurality of output ends of the intelligent control module are respectively connected with the input end of the brushless motor control module and the start indicator lamp; the gliding missile moves forwards in the bore, when the permanent magnet particles are aligned with the Hall sensor, the Hall sensor is opened to trigger the bistable trigger to enable the switch triode to be switched on to supply power to the front end electromagnetic coil of the gliding missile, the electromagnetic coil generates an electromagnetic field to attract the gliding missile to move forwards, the length of the cylinder missile body is equal to that of the electromagnetic coil, when the cylinder missile body is attracted to the center of the electromagnetic coil, the front end and the rear end of the cylinder missile body are consistent with the front end and the rear end of the electromagnetic coil, the permanent magnet particles are aligned with the Hall sensor to be switched off, the Hall sensor is switched off to trigger the bistable trigger to enable the switch triode to be switched off, the electromagnetic coil is powered off, the gliding missile continues to move forwards by means of inertia after being separated from the magnetic force, the gliding missile can obtain the electromagnetic force and lose the electromagnetic force, the gliding missile is attracted by a plurality of electromagnetic coils in front to be relayed and accelerated, the speed is rapidly increased, and finally the gliding missile is taken out of the chamber and shot towards a front target; the missile speed sensing conversion module is connected with a signal that a first Hall sensor at the front end of a gun bore tube is opened at the input end, a signal that a third Hall sensor at the front end of the gun bore tube is opened at the input end, and the output end of the missile speed sensing conversion module is connected with a data information display.

2. The warship missile electromagnetic gun of claim 1, wherein: the electromagnetic gun of the warship missile is provided with a missile storage box (22), the upper end in the missile storage box is provided with a missile pushing vehicle, the missile pushing vehicle is provided with a square frame (55), the lower end of the square frame is provided with a missile bin (56), a plurality of gliding missiles (23) are stored in the missile bin, the width in the missile storage box is equal to the length of the gliding missiles, the thickness in the missile storage box is equal to the width of the gliding missiles, the height in the missile storage box is equal to the sum of the height of the gliding missiles and the height of the square frame, the front end of the bottom of the missile bin is connected with a gun barrel pipe, the front end of the square frame is provided with an upper vehicle wheel shaft (57) and a lower vehicle wheel shaft (58), the left end and the right end of the upper vehicle wheel shaft and the lower vehicle wheel shaft are respectively provided with a front upper left wheel, a right wheel (59), a front lower left wheel, a right wheel, The missile launching vehicle comprises a right wheel (63), a lower rear left wheel (64), a rear lower right wheel (64), a square frame front end welding connecting plate (65), a line groove (66) is formed in the front end of a missile storage box, the connecting plate is located in the line groove, a speed reducing motor (67) is arranged at the front end of the connecting plate, a driving gear (68) is arranged at the right end of the speed reducing motor, a rack (69) is arranged at the front end of the missile storage box, driving gears and the rack are meshed, the missile pushing vehicle is driven to move up and down when the speed reducing motor rotates forwards and backwards, the four wheels are supported at the front end and the rear end of the inner wall of the missile storage box, meshing gaps between the driving gears and the rack are stabilized, strip grooves (70) are formed in the left end and the right end of a magazine, steel plate springs (71) are arranged in the left strip grooves and the right strip grooves, the left steel, The right end of the missile hopper is firmly grasped by the elastic gripper, so that a plurality of gliding missiles are firmly fixed in the middle of the missile hopper under the static state of the missile pusher, the right end of the missile hopper is provided with an upper sensor hole and a lower sensor hole, a Hall sensor stop (72) is installed in the upper sensor hole, a Hall off sensor (73) is installed in the lower sensor hole, a cylindrical permanent magnet (74) is arranged at the right end of the connecting plate, a sensor hole is arranged at the right end of the missile hopper, a Hall stop sensor (75) is installed in the sensor hole, output lines of the Hall sensor stop, the Hall off sensor, the Hall stop sensor and the missile control keyboard are respectively connected with relevant input ends of the motor control module, the output end of the motor control module is respectively connected with output lines of a speed reducing motor, an electric hydraulic pump and an, An elevation angle downward button, a backing button, a missile single-launching button and a missile continuous-launching button, when the backing button is pressed, a trigger motor control module controls a speed reducing motor to rotate anticlockwise to drive a missile pushing vehicle to move upwards to the top, a cylindrical permanent magnet is aligned with a Hall parking sensor, the Hall parking sensor triggers a generator control module to turn off a power supply of the speed reducing motor, the missile pushing vehicle stops, a space below the missile pushing vehicle is a missile cabin, the rear end of a missile storage box is provided with a missile cabin door (76), the missile cabin door is opened, a plurality of gliding missiles with the power supply on are loaded into the missile cabin, when the missile single-launching button is pressed, the trigger motor control module controls the speed reducing motor to rotate clockwise, the missile pushing vehicle pushes a plurality of gliding missiles downwards to push an elastic gripper from the first lower end, when the permanent magnet particles of the second gliding missiles at the lower ends of the plurality of gliding missiles are aligned with the Hall closing sensor, the speed reducing motor stops automatically, the elastic gripper catches the left end and the right end of the second gliding missile, the first gliding missile falls into the bottom of the missile cabin by separating from the gripping force of the left steel plate spring and the right steel plate spring, the permanent magnetic particles of the first gliding missile are aligned with the Hall sensor switch, the Hall sensor switch triggers the intelligent controller to supply power to the first electromagnetic coil at the rear end, the electromagnetic coil generates an electromagnetic field to attract the gliding missiles to move forwards, the pulley gliding missiles are accelerated by the relay of a plurality of electromagnetic coils and then are launched into the chamber, one gliding missile is launched by pressing a single missile launching button to be a trigger pulse, a plurality of trigger pulses are pressed by pressing a missile continuous launching button, a plurality of gliding missiles are launched continuously, when the last gliding missile falls into the bottom of the missile cabin, the missile pusher moves downwards to be aligned with the cylindrical permanent magnet and stops, the Hall sensor stop triggering motor control module turns off the power supply of, the bullet pushing vehicle stops, the elevation angle up button is pressed, the motor control module is triggered to open the electric hydraulic pump and the electromagnetic valve, the elevation angle of the multi-coil gun barrel is adjusted upwards, the elevation angle down button is pressed to trigger the motor control module to close the electric hydraulic pump, the elevation angle of the multi-coil gun barrel is adjusted downwards, after the elevation angle of the multi-coil gun barrel is determined, the upward or downward button electromagnetic valve is loosened to close, and the elevation angle of the multi-coil gun barrel is fixed.

3. The warship missile electromagnetic gun of claim 1, wherein: the length of the multi-coil gun barrel is slightly less than that of a warship and is greater than that of the existing electromagnetic gun barrel, the multi-coil gun barrel belongs to a long and thin type gun barrel, a triangular plate support at the lower end of the multi-coil gun barrel is used for enhancing the supporting strength of the long and thin type gun barrel, a gliding missile moves in the long and thin type gun barrel and can be accelerated in a relay way through a plurality of electromagnetic coils within a long stroke and a long time, so that the speed of the gliding missile can be improved to the limit without needing large electric power, the electromagnetic gun of the gliding missile is simple in structure, light in weight and small in energy consumption, and is suitable for being arranged on the warship, a target found by a radar of the warship is displayed on a data information display, the advancing direction of the warship and the elevation angle of the multi-coil gun barrel are adjusted, the electromagnetic gun of the warship can aim at the target, the highest speed of the gliding missile, which is emitted out of a gun bore, the intelligent control box of the gliding missile receives the instruction of the gyro level sensor to drive the left horizontal wing and the right horizontal wing, so that the left horizontal wing and the right horizontal wing are glidingly kept in a horizontal state, the camera of the gliding missile searches and locks the target together according to the heat source information of the target and the reflection information of the target by the left laser radar and the right laser radar according to the image information of the target, a control signal of the flight direction is sent to the intelligent control box, the vertical wing is controlled to change the left flight direction and the right flight direction of the missile, the left horizontal wing and the right horizontal wing are controlled to change the up-and-down flight direction of the missile, so that the gliding missile automatically tracks the target and hits the target, the gliding missile has large mass, large kinetic energy killing force and strong penetrating force, and the gliding missile is suitable for hitting the target in the air, on the sea or on the land.