阅读说明：本技术 战斗机导弹电磁炮 (Electromagnetic gun for missile of fighter ) 是由 朱幕松 于 2019-11-01 设计创作，主要内容包括：一种战斗机导弹电磁炮,由战斗机、螺旋炮管、电磁驱动器、导弹连发盒、滑轮导弹组成,螺旋炮管展开后的长度超过现有的电磁炮,滑轮导弹在较长的螺旋炮膛内经过多个电磁驱动器长时间的接力加速,实现用锂电将滑轮导弹的速度提高到极限,战斗机导弹电磁炮体积小、重量轻、载弹量大,适用于装备在战斗机上,滑轮导弹的摄像机根据目标的图像信息,红外传感器根据目标的热源信息,左激光雷达、右激光雷达根据目标的反射信息,控制垂直翼改变导弹左右飞行方向,控制左水平翼和右水平翼改变导弹上下飞行方向,使滑轮导弹自动跟踪打击目标,滑轮导弹质量大,动能杀伤力大、穿透力强、命中率高,能连续发射,适用于打击空中、海上或者陆地上的目标。(A fighter missile electromagnetic gun is composed of fighters, a spiral gun barrel, electromagnetic drivers, a missile repeating box and a pulley missile, wherein the length of the unfolded spiral gun barrel exceeds that of the existing electromagnetic gun, the pulley missile is subjected to long-time relay acceleration by the electromagnetic drivers in a long spiral gun bore to realize the purpose that the speed of the pulley missile is increased to the limit by lithium electricity, the fighter missile guiding electromagnetic gun is small in size, light in weight and large in missile loading capacity and is suitable for being arranged on the fighters, a camera of the pulley missile automatically tracks and hits a target by an infrared sensor according to heat source information of the target, a left laser radar and a right laser radar control a vertical wing to change the left and right flying directions of the missile according to reflection information of the target, a left horizontal wing and a right horizontal wing to change the up-down flying direction of the missile, and the missile pulley has large mass and large kinetic energy killing capacity, The penetration is strong, the hit rate is high, can continuously transmit, and is suitable for hitting targets in the air, on the sea or on the land.)

1. The utility model provides a fighter plane guided missile electromagnetism big gun, by fighter plane, spiral gun barrel, guided missile continuous firing box, pulley guided missile, guided missile launch button, intelligent control ware and lithium cell constitute its characterized in that: the electromagnetic gun of the fighter missile is provided with a fighter, the fighter is a manned fighter or an unmanned fighter, the middle part of the body (1) of the fighter is provided with a cabin, a barrel-shaped bracket (2) is arranged in the cabin, the outer circle of the barrel-shaped bracket is provided with a spiral gun barrel (3), the lower end of the barrel-shaped bracket is provided with a left connecting plate (4) and a right connecting plate (5), the lower end of the cabin is provided with a mounting port (6), the left connecting plate and the right connecting plate are fixed at the left end and the right end of the mounting port, the lower end part of the spiral gun barrel is positioned outside the mounting port, the space of the inner circle of the barrel-shaped bracket is provided with an intelligent controller (7), an electromagnetic drive control module, a missile speed sensing conversion module and a speed reduction motor control module are arranged inside the intelligent controller, the lower end of the intelligent controller is provided, a radar detector for detecting a target is arranged in front of the outer side of the fighter aircraft cab; the device is characterized in that the spiral gun barrel is provided with a plurality of circles of spiral gun barrels (9), the right lower end of each circle of spiral gun barrel is connected with a horizontal gun barrel outlet (10), the left upper end of each circle of spiral gun barrel is connected with a vertical gun barrel inlet (11), the upper end of each vertical gun barrel inlet is connected with a missile repeating box (12), the missile repeating box is filled with a plurality of pulley missiles (13), the horizontal gun barrel outlet is positioned at the lower end of the machine body and is parallel to the machine body, and the horizontal gun barrel outlet points to the front; the multi-circle spiral gun barrel, the horizontal gun barrel outlet and the vertical gun barrel inlet are made into an integral spiral gun barrel by an oblate non-magnetic conductive copper pipe, the inner circle of the spiral gun barrel is the spiral gun bore of a fighter missile electromagnetic gun, the pulley missile is used for loading, driving, accelerating and launching in the spiral gun bore, the pulley missile is made of magnetic conductive iron materials and is provided with a cuboid missile body (14), the front end and the rear end of the cuboid missile body are both semicircular, the center of the cuboid missile body is provided with a square hole, a square pipe (15) is tightly matched in the square hole, the square pipe and the cuboid missile body are both provided with a coaxial front shaft hole and a coaxial rear shaft hole, a front wheel shaft (16) is tightly matched in the front shaft hole, a rear wheel shaft (17) is tightly matched in the rear shaft hole, the front end and the rear end of the cuboid missile body are both provided with a left wheel groove and a right wheel groove, the left end and the right end of the front wheel shaft are respectively loosely matched with, the 4 pulleys (18) are respectively positioned in the 4 wheel grooves (19), the outer end planes of the 4 pulleys are respectively consistent with the planes of the left end and the right end of the cuboid bullet body, the circumferences of the 4 pulleys are respectively consistent with the semi-circles of the front end and the rear end of the cuboid bullet body, the left end and the right end of the front wheel shaft and the rear wheel shaft are respectively provided with an outer snap spring (20), the center of the right end of the front wheel shaft is provided with a circular groove, and permanent magnetic particles (21) are arranged in the circular grooves; the multi-circle spiral gun barrel is provided with a plurality of identical electromagnetic drivers, each electromagnetic driver comprises an electromagnetic coil, a Hall sensor switch and a bistable switch circuit, in the multi-circle spiral gun barrel, the periphery of each circle of spiral gun barrel is provided with 8 electromagnetic coils, the distance between the 8 electromagnetic coils is divided equally, the right side of each circle of spiral pipe is provided with 16 sensing holes, the Hall sensor switches (22) are arranged in the sensing holes in the middle positions among the 8 electromagnetic coils, the distance between the 8 Hall sensor switches is divided equally, the Hall sensor switches (23) are arranged in the sensing holes in the inner positions of the 8 electromagnetic coils, the distance between the 8 Hall sensor switches is divided equally, and the excircle of the barrel-shaped support is connected to the shells of the electromagnetic coils; 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 (24) and a switch triode (25), and the circuit connection of each electromagnetic driver is as follows: the upper input end (26) of the bistable trigger is connected with a Hall sensor switch, the lower input end (27) of the bistable trigger is connected with a Hall sensor switch, the output end of a switch triode is connected with an electromagnetic coil (28), the grounding end of a bistable switch circuit is connected with the cathode of a lithium battery, the power end (29) of the bistable switch circuit is connected with the anode of the lithium battery, the lithium battery is a small-volume and light-weight missile electromagnetic cannon power supply carried by a fighter, when the permanent magnet particles of the pulley missile aim at the Hall sensor switch in motion, the bistable trigger is triggered to be conducted with the switch triode, when the permanent magnetic particles are aligned with the Hall sensor to be closed, the bistable trigger is triggered to be cut off with the switch triode, and when the pulley missile passes through each electromagnetic coil, the pulley missile can obtain electromagnetic force and lose the electromagnetic force at the same optimal position, so that the pulley missile obtains the maximum continuous electromagnetic driving force; the section of the excircle and the interior circle of spiral barrel is oblate, the section of spiral barrel is interior circle of oblate (30), the left side and the right of the interior circle of oblate are arc, the interior circle of oblate is equipped with straight flange (31) and lower straight flange (32), solenoid's shell is equipped with magnetic conduction section of thick bamboo (33), is equipped with coil skeleton (34) in the magnetic conduction section of thick bamboo, and coiling enameled wire in the coil skeleton, magnetic conduction section of thick bamboo are equipped with annular magnetic conduction lid (35), and the interior circle of annular magnetic conduction lid is unanimous with coil skeleton's interior circle, and the central circle of magnetic conduction section of thick bamboo bottom is unanimous with coil skeleton's interior circle, and the three becomes solenoid's interior circle jointly, accomplishes holistic solenoid (28), and solenoid's interior circle is oblate, and the cover is installed in the oblate excircle tight fit of many circles spiral barrel, the spiral barrel is, The lower straight edge is an inner circular track, the pulley missile is loaded into the spiral barrel from the vertical barrel inlet, 4 pulleys of the pulley missile roll between the outer circular track and the inner circular track of the spiral barrel, when the permanent magnet particles are aligned with the Hall sensor, the Hall sensor is switched on to trigger the intelligent controller to supply power to the front end electromagnetic coil of the pulley missile, the electromagnetic coil generates an electromagnetic field to attract the pulley missile to advance, the length of the cuboid missile body is equal to that of the electromagnetic coil, when the cuboid missile body moves to the center of the electromagnetic coil, the front end and the rear end of the cuboid 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, the Hall sensor is switched off to trigger the intelligent controller to cut off the power of the electromagnetic coil, the pulley missile continues to advance by means of inertia after the cuboid missile body moves away from the magnetic force, the, the centrifugal force generated in the rotating process enables 4 pulleys of the pulley guided missile to roll along the excircle track of the multi-circle spiral gun bore, the rolling resistance of the 4 pulleys is small, so that the rotating speed of the pulley guided missile on the excircle track is quickly improved, and finally the wheel guided missile is launched out of the horizontal gun barrel outlet and is shot forward; the missile speed sensing conversion module is connected with a signal generated by a first Hall sensor of the multi-circle spiral gun barrel at an input end I, a signal generated by a last Hall sensor of the multi-circle spiral gun barrel at an input end II and a data information display at an output end, and converts the speed of the pulley missile when the pulley missile is discharged from a gun bore according to the time difference of the pulley missile when the pulley missile enters and exits the multi-circle spiral gun barrel and the length of the multi-circle spiral gun barrel and displays the speed on the data information display.

2. The fighter missile electromagnetic gun of claim 1, wherein: the pulley missile is characterized in that a left horizontal wing motor (36) is arranged at the rear end of the inner side of the square tube of the pulley missile, a left driving shaft (37) is arranged at the center of the left horizontal wing motor, a left shaft hole is formed in the square tube, the left driving shaft penetrates into the left shaft hole, a left horizontal wing (38) is installed on the left driving shaft, a right horizontal wing motor (39) is arranged at the rear end of the inner side of the square tube, a right driving shaft (40) is arranged at the center of the right horizontal wing motor, the square tube is provided with a right shaft hole, the right driving shaft penetrates into the right shaft hole, a right horizontal wing (41) is installed on the right driving shaft, the left horizontal wing and the right horizontal wing are the same in size and are bilaterally symmetrical, the left horizontal wing motor and the right horizontal wing motor are the same in model and are bilaterally symmetrical, a vertical wing motor (42) is arranged at the rear, The length of the right horizontal wing, the left horizontal wing motor, the right horizontal wing motor and the vertical wing motor are both harmonic reducer motors, the harmonic reducer motor is a low-rotation-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 and the right horizontal wing motor rotate positively and negatively, the vertical wing is driven to turn left and right when the vertical wing motor rotates positively and negatively, an intelligent control box (45) is arranged in a square pipe, a gyro horizontal sensor, a brushless motor control module and an intelligent control module are arranged in the intelligent control box, a storage battery (46) is arranged at the rear end of the intelligent control box, an arc-shaped cover plate (47) is arranged at the front end of the square pipe, the arc-shaped cover plate is consistent with the semicircle at the front end of the cuboid bullet body, a camera hole is arranged in the center of the arc-shaped cover plate, a, a left laser radar sensor (50) is installed in a sensor hole at the left end of a camera shooting hole, a right laser radar sensor (51) is installed in a sensor hole at the right end of the camera shooting hole, a starting indicator lamp (52) is installed in the sensor hole at the lower end of the camera shooting hole, a steel bar hole (53) is formed in the upper rear end of a cuboid missile body, the steel bar hole penetrates through the wall of a square tube and is directly communicated into the square tube, a Hall sensor (54) is arranged in the square tube close to the steel bar hole, a starting steel bar (55) is arranged on the pulley missile, a permanent magnet (56) is arranged at the lower end of the starting steel bar, the Hall sensor is triggered to be in a switching-on or switching-off state when the permanent magnet is close to the Hall sensor, so as to control a power switch of the pulley missile, the, The output lines of 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.

3. The fighter missile electromagnetic gun of claim 1, wherein: the electromagnetic gun for the missile of the fighter is provided with a missile repeating box, the front end in the missile repeating box is provided with a missile pushing vehicle, the missile pushing vehicle is provided with a square frame (57), the front end of the square frame is provided with a missile bin, a plurality of pulley missiles are stored in the missile bin, the height in the missile repeating box is equal to the length of the pulley missiles, the width in the missile repeating box is equal to the width of the pulley missiles, the length in the missile repeating box is equal to the sum of the length of the arrangement of the pulley missiles and the length of the square frame, the upper end of the missile repeating box is provided with a plurality of pulley missile inlets, the rear end of the bottom plate of the missile repeating box is provided with a single pulley missile inlet (58), the lower end of the square frame is provided with a front wheel shaft (59) and a rear wheel shaft (60), the left and right wheels (61) are arranged at the left and right ends of the front wheel shaft, the left and right, the missile continuous-launching box is characterized in that a linear groove (64) is formed in the right end of the missile continuous-launching box, the upper end of an L-shaped motor frame is located in the linear groove, a speed reducing motor (65) is arranged at the lower end of the L-shaped motor frame, a driving gear (66) is arranged at the left end of the speed reducing motor, a rack (67) is arranged at the lower end of a bottom plate of the missile continuous-launching box, driving gears are matched with the racks, strip-shaped grooves (68) are formed in the left end and the right end of the missile continuous-launching box, steel plate springs (69) are arranged in the left strip-shaped groove and the right strip-shaped groove, the left steel plate spring and the right steel plate spring are equal in size and are bilaterally symmetrical, the rear ends of the left steel plate spring and the right steel plate spring are clamped at the left end and the right end of a second pulley missile at the rear ends of the plurality of the pulley missiles, The missile launching button and the backing button are respectively connected with the relevant input end of the control module of the speed reducing motor, the output end of the control module of the speed reducing motor is connected with the speed reducing motor, the power end of the control module of the speed reducing motor is connected with the lithium battery, the backing button is triggered by pressing the backing button to control the speed reducing motor to rotate anticlockwise, the backing button is released after the bullet pushing vehicle is driven to move forwards to the bottom, the bullet pushing vehicle stops, a plurality of powered pulley missiles are stored in a bullet cabin at the front end of the bullet pushing vehicle, the control module of the speed reducing motor is triggered by pressing the missile launching button, the speed reducing motor rotates clockwise, the bullet pushing vehicle pushes a plurality of pulley missiles backwards, when the permanent magnet particles of the second pulley missile are stopped and aligned with the Hall sensor, the Hall sensor stops outputting a pulse signal to trigger the control module of the speed reducing motor, the, the missile is launched by a single pulley missile after being fed into a plurality of circles of spiral gun bores through a single pulley missile inlet, the pulley missile is launched after being subjected to relay acceleration by a plurality of electromagnetic coils, the single pulley missile is launched after being released by pressing a missile launching button, and the multiple pulley missiles are continuously launched without being released by pressing the missile launching button.

4. The fighter missile electromagnetic gun of claim 1, wherein: the existing electromagnetic gun is a linear gun barrel, the length of the linear gun barrel is limited, the speed of the cannonball is difficult to improve, the length of the unfolded spiral gun barrel exceeds that of the existing electromagnetic gun, the pulley missile is subjected to long-time relay acceleration in a longer spiral gun bore through a plurality of electromagnetic drivers, the speed of the pulley missile is improved to the limit by the power of a lithium battery, therefore, the size, the weight, the energy consumption and the loading capacity of the electromagnetic gun for the missile of the fighter are small, the electromagnetic gun for the missile is light, the energy consumption is small, the missile loading capacity is large, the electromagnetic gun for the missile is suitable for being arranged on the fighter, a target discovered by an airborne radar of the fighter is displayed on a data information display, the posture of the fighter is adjusted, the electromagnetic gun for the missile of the fighter can aim at the target to shoot, the initial speed of the pulley missile flying out from an outlet is equal to the linear speed accelerated in a plurality of, the intelligent control box receives an instruction of the gyro level sensor to drive the left horizontal wing and the right horizontal wing, so that the pulley missile flies in a horizontal state, the camera of the pulley missile can search and lock the target together according to the image information of the target, the infrared sensor can change the left flying direction and the right flying direction of the missile according to the heat source information of the target, and the left laser radar and the right laser radar can search and lock the target according to the reflection information of the target, so that a control signal of the flying direction is sent to the intelligent control box, the vertical wing is controlled to change the left flying direction and the right flying direction of the missile, and the left horizontal wing and the right horizontal wing are controlled to change the up-and-down flying direction of the missile, so that the pulley missile can automatically track and strike the target.

Technical Field

The invention relates to the technical field of electromagnetic coil cannons, in particular to a fighter missile electromagnetic cannon.

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 arc generated at the outlet of the electrified guide rail, the electromagnetic cannonball does not have the electric brush, the problems are solved, however, the electromagnetic cannonball has the defect that the driving force of the electromagnetic coil is insufficient, the electromagnetic cannonball moves in the limited length of the cannon chamber, and the electromagnetic cannonball is accelerated for a short time and is high.

The existing electromagnetic cannon can only be equipped on a military warship for experiment due to long cannon pipe and cannot be equipped on a fighter, the scheme for carrying the electromagnetic cannon on the fighter is still under exploration, and the significance of carrying the electromagnetic cannon on the fighter lies in that: the mission load of the fighter is reduced, the number of missiles is increased, and the cost of the missiles is reduced.

Disclosure of Invention

The invention discloses a missile electromagnetic cannon of a fighter, aiming at overcoming the defects of the existing electromagnetic rail cannon and electromagnetic coil cannon and realizing the loading of the electromagnetic cannon on the fighter.

The electromagnetic gun for the fighter missile is mainly composed of a fighter, a spiral gun barrel, an electromagnetic driver, a missile repeating box, a pulley missile, a missile launching button, an intelligent controller and a lithium battery, and is characterized in that: the electromagnetic gun of the fighter missile is provided with a fighter, the fighter is a manned fighter or an unmanned fighter, the middle part of the body of the fighter is provided with a cabin, a barrel-shaped bracket is arranged in the cabin, the excircle of the barrel-shaped bracket is provided with a spiral gun barrel, the lower end of the barrel-shaped bracket is provided with a left connecting plate and a right connecting plate, the lower end of the cabin is provided with a mounting opening, the left connecting plate and the right connecting plate are fixed at the left end and the right end of the mounting opening, the lower end part of the spiral gun barrel is positioned outside the, an intelligent controller is arranged in the space of the inner circle of the barrel-shaped support, an electromagnetic drive control module, a missile speed sensing conversion module and a speed reduction motor control module are arranged in the intelligent controller, a lithium battery is arranged at the lower end of the intelligent controller, a data information display and a missile launching button are arranged in a fighter cab, and a radar detector for detecting a target is arranged in front of the fighter cab; the device comprises a machine body, a plurality of circles of spiral gun barrels, a horizontal gun barrel outlet, a vertical gun barrel inlet, a missile repeating box, a plurality of pulley missiles, a horizontal gun barrel outlet and a vertical gun barrel outlet, wherein the spiral gun barrel is provided with the circles of spiral gun barrels; the multi-circle spiral gun barrel, the horizontal gun barrel outlet and the vertical gun barrel inlet are made into an integral spiral gun barrel by an oblate non-magnetic conductive copper pipe, the inner circle of the spiral gun barrel is the spiral gun chamber of a fighter missile electromagnetic gun, a pulley missile is used for loading, driving, accelerating and launching in the spiral gun chamber, the pulley missile is made of magnetic conductive iron materials and is provided with a cuboid missile body, the front end and the rear end of the cuboid missile body are semicircular, the center of the cuboid missile body is provided with a square hole, the square hole is internally provided with a square pipe in close fit, the square pipe and the cuboid missile body are respectively provided with a coaxial front shaft hole and a coaxial rear shaft hole, a front wheel shaft is internally provided with a front wheel shaft in close fit, a rear wheel shaft is installed in close fit, the front end and the rear end of the cuboid missile body are respectively provided with a left wheel groove and a right wheel groove, the left end and the right end of the front wheel shaft are respectively provided with a left, the 4 pulleys are respectively positioned in the 4 wheel grooves, the outer end planes of the 4 pulleys are respectively consistent with the planes of the left end and the right end of the cuboid bullet body, the circumferences of the 4 pulleys are respectively consistent with the semi-circles of the front end and the rear end of the cuboid bullet body, the left end and the right end of the front wheel shaft and the rear wheel shaft are respectively provided with an outer snap spring, the center of the right end of the front wheel shaft is provided with a circular groove, and permanent magnetic particles are arranged in the circular grooves; the multi-circle spiral gun barrel is provided with a plurality of identical electromagnetic drivers, each electromagnetic driver comprises an electromagnetic coil, a Hall sensor switch and a bistable switch circuit, 8 electromagnetic coils are arranged on the periphery of each circle of spiral gun barrel in the multi-circle spiral gun barrel, the distance between the 8 electromagnetic coils is divided equally, the right side of each circle of spiral pipe is provided with 16 sensing holes, the Hall sensor switches are arranged in the sensing holes in the middle positions among the 8 electromagnetic coils, the distance between the 8 Hall sensor switches is divided equally, the Hall sensor switches are arranged in the sensing holes in the inner positions of the 8 electromagnetic coils, the distance between the 8 Hall sensor switches is divided equally, and the excircle of the barrel-shaped support is connected to the shells of the electromagnetic coils; the electromagnetic drive control module is provided with a plurality of same bistable switch circuits, each bistable switch circuit consists of a bistable trigger and a switch triode, and the circuit connection of each electromagnetic driver is as follows: 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 an electromagnetic coil, the grounding end of the bistable switch circuit is connected with the negative electrode of a lithium battery, the power end of the bistable switch circuit is connected with the positive electrode of the lithium battery, the lithium battery is a small-size and light-weight missile electromagnetic cannon power supply carried by a fighter, when the permanent magnetic particles of the pulley missile are aligned with the Hall sensor switch in motion, the bistable trigger and the switch triode are switched on, when the permanent magnetic particles are aligned with the Hall sensor switch, the bistable trigger and the switch triode are switched off, and when the pulley missile passes through each electromagnetic coil, the pulley missile can obtain electromagnetic force and lose the electromagnetic force at the; the cross sections of the outer circle and the inner circle of the spiral gun barrel are oblate, the spiral gun bore is an oblate inner circle, the left side and the right side of the oblate inner circle are arc-shaped, the oblate inner circle is provided with an upper straight edge and a lower straight edge, the shell of the electromagnetic coil is provided with a magnetic conduction cylinder, a coil framework is arranged in the magnetic conduction cylinder, an enameled wire is wound in the coil framework to form an iron-attracting coil, the magnetic conduction cylinder is provided with an annular magnetic conduction cover, the inner circle of the annular magnetic conduction cover is consistent with the inner circle of the coil framework, the central circle at the bottom of the magnetic conduction cylinder is consistent with the inner circle of the coil framework, the three parts are jointly formed into the inner circle of the electromagnetic coil to complete the integral electromagnetic coil, the inner circle of the electromagnetic coil is oblate, the oblate outer circle of the multi-circle spiral gun barrel is sleeved with the obla, the pulley guided missile is loaded into the spiral barrel from a vertical barrel inlet, 4 pulleys of the pulley guided missile roll between an excircle track and an inner circle track of the spiral barrel, when the permanent magnet particles are aligned with the Hall sensor, the Hall sensor is switched on to trigger the intelligent controller to supply power to a front end electromagnetic coil of the pulley guided missile, the electromagnetic coil generates an electromagnetic field to attract the pulley guided missile to advance, the length of a cuboid missile body is equal to that of the electromagnetic coil, when the cuboid missile body moves to the center of the electromagnetic coil and the front end and the rear end of the cuboid missile body are consistent with those of the front end and the rear end of the electromagnetic coil, the permanent magnet particles are aligned with the Hall sensor, the Hall sensor is switched off to trigger the intelligent controller to cut off the power of the electromagnetic coil, the pulley guided missile continues to advance by means of inertia after being separated from the magnetic force, the pulley guided, the centrifugal force generated in the rotating process enables 4 pulleys of the pulley guided missile to roll along the excircle track of the multi-circle spiral gun bore, the rolling resistance of the 4 pulleys is small, so that the rotating speed of the pulley guided missile on the excircle track is quickly improved, and finally the wheel guided missile is launched out of the horizontal gun barrel outlet and is shot forward; the missile speed sensing conversion module is connected with a signal generated by a first Hall sensor of the multi-circle spiral gun barrel at an input end I, a signal generated by a last Hall sensor of the multi-circle spiral gun barrel at an input end II and a data information display at an output end, and converts the speed of the pulley missile when the pulley missile is discharged from a gun bore according to the time difference of the pulley missile when the pulley missile enters and exits the multi-circle spiral gun barrel and the length of the multi-circle spiral gun barrel and displays the speed on the data information display.

The pulley missile is characterized in that a left horizontal wing motor is arranged at the rear end of the inner part of a square tube of the pulley missile, a left driving shaft is arranged in the center of the left horizontal wing motor, a left shaft hole is formed in the square tube, the left driving shaft penetrates into the left shaft hole, the left driving shaft is provided with a left horizontal wing, a right horizontal wing motor is arranged at the rear end of the inner part of the square tube, a right driving shaft is arranged in the center of the right horizontal wing motor, the square tube is provided with a right shaft hole, the right driving shaft penetrates into the right shaft hole, the right driving shaft is provided with a right horizontal wing, the left horizontal wing and the right horizontal wing are identical in size and are symmetrical in left-right mode, the left horizontal wing motor and the right horizontal wing are identical in model and symmetrical in left-right mode, 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, the harmonic reducer motor is a low-rotation-speed motor integrating a harmonic reducer with a permanent magnet brushless motor, a left horizontal wing and a right horizontal wing are driven to respectively turn up and down when a left horizontal wing motor and a right horizontal wing motor rotate forwards and backwards, a vertical wing is driven to turn left and right when a vertical wing motor rotates forwards and backwards, an intelligent control box is arranged in a square tube, a gyro horizontal sensor, a brushless motor control module and an intelligent control module are arranged in the intelligent control box, a storage battery is arranged at the rear end of the intelligent control box, an arc-shaped cover plate is arranged at the front end of the square tube and is consistent with the semicircle at the front end of a cuboid projectile body, a camera is arranged in the center of the arc-shaped cover plate, a camera is arranged in the camera hole, 4 sensor holes are arranged on the arc-shaped cover plate around the camera hole, an infrared sensor is arranged in the sensor hole at the upper end, a starting indicator lamp is arranged in a sensor hole at the lower end of the camera hole, a steel bar hole is arranged at the rear upper end of the cuboid missile body, the steel bar hole penetrates through the wall of a square pipe and is directly communicated into the square pipe, a Hall sensor is arranged in the square pipe close to the steel bar hole, a starting steel bar is arranged on the pulley missile, a permanent magnet is arranged at the lower end of the starting steel bar, the Hall sensor is triggered to be in a switching state of being switched on or switched off when the permanent magnet is close to the Hall sensor, so that a power switch of the pulley missile is controlled, the steel bar penetrates into a lock hole of the pulley missile to trigger the Hall sensor, a power supply of the pulley missile is switched on, the starting indicator lamp of the pulley missile is on, a plurality of pulley missiles are started and then enter into a missile continuous launching box, output lines of the Hall sensor, a camera, the horizontal wing motor in right side and perpendicular wing motor, brushless motor control module input and start indicator are connected respectively to a plurality of outputs of intelligent control module.

The electromagnetic missile cannon of the fighter is provided with a missile repeating box, the front end in the missile repeating box is provided with a missile pushing vehicle, the missile pushing vehicle is provided with a square frame, the front end of the square frame is provided with a missile bin, a plurality of pulley missiles are stored in the missile bin, the height in the missile repeating box is equal to the length of the pulley missiles, the width in the missile repeating box is equal to the width of the pulley missiles, the length in the missile repeating box is equal to the sum of the length of the arrangement of the pulley missiles and the length of the square frame, the upper end of the missile repeating box is provided with a plurality of pulley missile inlets, the rear end of the bottom plate of the missile repeating box is provided with a single pulley missile inlet, the lower end of the square frame is provided with a front wheel shaft and a rear wheel shaft, the left and right wheels are arranged at the left and right ends of the front wheel shaft, the left and right ends of the rear wheel shaft are arranged at the left and right wheels, an, the lower end of an L-shaped motor frame is provided with a speed reducing motor, the left end of the speed reducing motor is provided with a driving gear, the lower end of a bottom plate of the missile repeating box is provided with a rack, the driving gear is matched with the rack, the left end and the right end of the missile repeating box are respectively provided with a strip groove, the left strip groove and the right strip groove are respectively provided with a steel plate spring, the left steel plate spring and the right steel plate spring are equal in size and are symmetrical left and right, the rear ends of the left steel plate spring and the right steel plate spring are clamped at the left end and the right end of a second pulley missile at the rear ends of a plurality of pulley missiles, so that the plurality of pulley missiles can be stably fixed in a missile silo no matter in a moving or static state, the rear right end of the missile repeating box is provided with a sensor hole, a Hall sensor stop is arranged in the sensor hole, a reversing button is, the power end of the control module of the speed reducing motor is connected with a lithium battery, the control module of the speed reducing motor is triggered by pressing a reversing button, the speed reducing motor is controlled to rotate anticlockwise to drive the bullet pushing vehicle to move forwards to the bottom and then release the reversing button, the bullet pushing vehicle stops, a plurality of pulley missiles with power on are stored in a bullet cabin at the front end of the bullet pushing vehicle, the control module of the speed reducing motor is triggered by pressing a missile launching button, the speed reducing motor rotates clockwise, the bullet pushing vehicle pushes the pulley missiles backwards, when the permanent magnet particles of the second pulley missile are stopped and aligned with the Hall sensor, the Hall sensor stops outputting a pulse signal to trigger the control module of the speed reducing motor, the speed reducing motor automatically stops, the first pulley missile at the rear ends of the pulley missiles falls down by virtue of gravity and passes through a single pulley missile inlet to fall into a plurality of spiral gun bores, after the missile launching button is pressed to be released, the missile is launched by a single pulley, and when the missile launching button is not pressed, the missile is launched by a plurality of pulleys continuously.

The electromagnetic gun for the missile of the fighter has the beneficial effects that: the existing electromagnetic gun is a linear gun barrel, the length of the linear gun barrel is limited, the speed of the cannonball is difficult to improve, the length of the unfolded spiral gun barrel exceeds that of the existing electromagnetic gun, the pulley missile is subjected to long-time relay acceleration in a longer spiral gun bore through a plurality of electromagnetic drivers, the speed of the pulley missile is improved to the limit by the power of a lithium battery, therefore, the size, the weight, the energy consumption and the loading capacity of the electromagnetic gun for the missile of the fighter are small, the electromagnetic gun for the missile is light, the energy consumption is small, the missile loading capacity is large, the electromagnetic gun for the missile is suitable for being arranged on the fighter, a target discovered by an airborne radar of the fighter is displayed on a data information display, the posture of the fighter is adjusted, the electromagnetic gun for the missile of the fighter can aim at the target to shoot, the initial speed of the pulley missile flying out from an outlet is equal to the linear speed accelerated in a plurality of, the intelligent control box receives an instruction of the gyro level sensor to drive the left horizontal wing and the right horizontal wing, so that the pulley missile flies in a horizontal state, the camera of the pulley missile can search and lock the target together according to the image information of the target, the infrared sensor can change the left flying direction and the right flying direction of the missile according to the heat source information of the target, and the left laser radar and the right laser radar can search and lock the target according to the reflection information of the target, so that a control signal of the flying direction is sent to the intelligent control box, the vertical wing is controlled to change the left flying direction and the right flying direction of the missile, and the left horizontal wing and the right horizontal wing are controlled to change the up-and-down flying direction of the missile, so that the pulley missile can automatically track and strike the target.

Drawings

Fig. 1 is a schematic diagram of the right-view overall structure of a missile electromagnetic gun of a fighter.

Fig. 2 is a front sectional structural schematic diagram of a fighter missile electromagnetic gun.

Fig. 3 is a schematic diagram of a right-view structure of the pulley missile.

Fig. 4 is an electrical schematic of an electromagnetic drive.

Fig. 5 is a rear view schematic diagram of the pulley missile and the electromagnetic driver.

FIG. 6 is a front view of the pulley missile and electromagnetic drive.

Fig. 7 is a schematic structural diagram of a pulley missile in a right-side sectional view.

FIG. 8 is a schematic diagram of a pulley missile disengaging magnetic force inertial advancing right view structure.

Fig. 9 is a structural schematic diagram of the electromagnetic coil attraction pulley missile in the right-hand direction.

Fig. 10 is a right-side structural schematic diagram of the pulley missile before the pulley missile is discharged from the gun bore.

Detailed Description

In the figures 1-10, the fighter missile electromagnetic gun is provided with a fighter which is a manned fighter or unmanned fighter, the middle part of the body 1 of the fighter is provided with a cabin, a barrel-shaped bracket 2 is arranged in the cabin, the excircle of the barrel-shaped bracket is provided with a spiral gun barrel 3, the lower end of the barrel-shaped bracket is provided with a left connecting plate 4 and a right connecting plate 5, the lower end of the cabin is provided with a mounting opening 6, the left connecting plate and the right connecting plate are fixed at the left end and the right end of the mounting opening, the lower end part of the spiral gun barrel is positioned outside the mounting opening, an intelligent controller 7 is arranged in the space of the inner circle of the barrel-shaped support, an electromagnetic drive control module, a missile speed sensing conversion module and a speed reduction motor control module are arranged in the intelligent controller, a lithium battery 8 is arranged at the lower end of the intelligent controller, a data information display and a missile launching button are arranged in a fighter cab, and a radar detector for detecting a target is arranged in front of the fighter cab; the spiral gun barrel is provided with a plurality of circles of spiral gun barrels 9, the right lower ends of the plurality of circles of spiral gun barrels are connected with a horizontal gun barrel outlet 10, the left upper ends of the plurality of circles of spiral gun barrels are connected with a vertical gun barrel inlet 11, the upper ends of the vertical gun barrel inlets are connected with a missile repeating box 12, the missile repeating box is filled with a plurality of pulley missiles 13, the horizontal gun barrel outlet is positioned at the lower end of the machine body and is parallel to the machine body, and the horizontal gun barrel outlet points to the front; the multi-circle spiral gun barrel, the horizontal gun barrel outlet and the vertical gun barrel inlet are made into an integral spiral gun barrel by an oblate non-magnetic conductive copper pipe, the inner circle of the spiral gun barrel is the spiral gun chamber of a fighter missile electromagnetic gun, the pulley missile is used for loading, driving, accelerating and launching in the spiral gun chamber, the pulley missile is made of magnetic conductive iron materials, the pulley missile is provided with a cuboid missile body 14, the front end and the rear end of the cuboid missile body are both semicircular, the center of the cuboid missile body is provided with a square hole, a square pipe 15 is tightly matched in the square hole, the cuboid missile body and the pulley missile body are both provided with a coaxial front shaft hole and a coaxial rear shaft hole, a front wheel shaft 16 is tightly matched and installed in the front shaft hole, a rear wheel shaft 17 is tightly matched and installed in the rear shaft hole, the front end and the rear end of the cuboid missile body are both provided with a left wheel groove and a right wheel groove, the left end and the right end of the front wheel shaft, the 4 pulleys 18 are respectively positioned in the 4 wheel grooves 19, the outer end planes of the 4 pulleys are respectively consistent with the planes of the left end and the right end of the cuboid bullet body, the circumferences of the 4 pulleys are respectively consistent with the semi-circles of the front end and the rear end of the cuboid bullet body, the left end and the right end of the front wheel shaft and the rear wheel shaft are respectively provided with an outer snap spring 20, the center of the right end of the front wheel shaft is provided with a circular groove, and permanent magnetic particles 21 are arranged in the circular grooves; the multi-circle spiral gun barrel is provided with a plurality of same electromagnetic drivers, each electromagnetic driver comprises an electromagnetic coil, a Hall sensor switch and a bistable switch circuit, in the multi-circle spiral gun barrel, the periphery of each circle of spiral gun barrel is provided with 8 electromagnetic coils, the distance between the 8 electromagnetic coils is divided equally, the right side of each circle of spiral pipe is provided with 16 sensing holes, Hall sensor switches 22 are arranged in the sensing holes in the middle positions among the 8 electromagnetic coils, the distance between the 8 Hall sensor switches is divided equally, Hall sensor switches 23 are arranged in the sensing holes in the inner positions of the 8 electromagnetic coils, the distance between the 8 Hall sensor switches is divided equally, and the excircle of the barrel-shaped support is connected to the shells of the electromagnetic coils; 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 24 and a switch triode 25, and the circuit connection of each electromagnetic driver is as follows: the upper input end 26 of the bistable trigger is connected with a Hall sensor switch, the lower input end 27 of the bistable trigger is connected with a Hall sensor switch, the output end of a switch triode is connected with an electromagnetic coil 28, the grounding end of the bistable switch circuit is connected with the negative electrode of a lithium battery, the power end 29 of the bistable switch circuit is connected with the positive electrode of the lithium battery, the lithium battery is a small-size and light-weight missile electromagnetic cannon power supply carried by a fighter, when the permanent magnetic particles of the pulley missile aim at the Hall sensor switch in motion, the bistable trigger and the switch triode are switched on, when the permanent magnetic particles aim at the Hall sensor switch, the bistable trigger and the switch triode are switched off, and when the pulley missile passes through each electromagnetic coil, the pulley missile can obtain electromagnetic force and lose the electromagnetic force at the same optimal; the cross sections of the outer circle and the inner circle of the spiral gun barrel are oblate, the cross section of the spiral gun bore is an oblate inner circle 30, the left side and the right side of the oblate inner circle are arc-shaped, the oblate inner circle is provided with an upper straight edge 31 and a lower straight edge 32, the shell of the electromagnetic coil is provided with a magnetic conduction cylinder 33, a coil framework 34 is arranged in the magnetic conduction cylinder, enameled wires are wound in the coil framework, the magnetic conduction cylinder is provided with an annular magnetic conduction cover 35, the inner circle of the annular magnetic conduction cover is consistent with the inner circle of the coil framework, the central circle at the bottom of the magnetic conduction cylinder is consistent with the inner circle of the coil framework, the three parts are jointly formed into the inner circle of the electromagnetic coil, the integral electromagnetic coil 28 is completed, the inner circle of the electromagnetic coil is oblate, the oblate outer circle sleeved on a plurality of spiral gun barrels is tightly matched and installed, the pulley guided missile is loaded into the spiral barrel from a vertical barrel inlet, 4 pulleys of the pulley guided missile roll between an excircle track and an inner circle track of the spiral barrel, when the permanent magnet particles are aligned with the Hall sensor, the Hall sensor is switched on to trigger the intelligent controller to supply power to a front end electromagnetic coil of the pulley guided missile, the electromagnetic coil generates an electromagnetic field to attract the pulley guided missile to advance, the length of a cuboid missile body is equal to that of the electromagnetic coil, when the cuboid missile body moves to the center of the electromagnetic coil and the front end and the rear end of the cuboid missile body are consistent with those of the front end and the rear end of the electromagnetic coil, the permanent magnet particles are aligned with the Hall sensor, the Hall sensor is switched off to trigger the intelligent controller to cut off the power of the electromagnetic coil, the pulley guided missile continues to advance by means of inertia after being separated from the magnetic force, the pulley guided, the centrifugal force generated in the rotating process enables 4 pulleys of the pulley guided missile to roll along the excircle track of the multi-circle spiral gun bore, the rolling resistance of the 4 pulleys is small, so that the rotating speed of the pulley guided missile on the excircle track is quickly improved, and finally the wheel guided missile is launched out of the horizontal gun barrel outlet and is shot forward; the missile speed sensing conversion module is connected with a signal generated by a first Hall sensor of the multi-circle spiral gun barrel at an input end I, a signal generated by a last Hall sensor of the multi-circle spiral gun barrel at an input end II and a data information display at an output end, and converts the speed of the pulley missile when the pulley missile is discharged from a gun bore according to the time difference of the pulley missile when the pulley missile enters and exits the multi-circle spiral gun barrel and the length of the multi-circle spiral gun barrel and displays the speed on the data information display.

The pulley missile is characterized in that a left horizontal wing motor 36 is arranged at the rear end of the inner side of the square tube of the pulley missile, a left driving shaft 37 is arranged at the center of the left horizontal wing motor, a left shaft hole is formed in the square tube, the left driving shaft penetrates into the left shaft hole, a left horizontal wing 38 is installed on the left driving shaft, a right horizontal wing motor 39 is arranged at the rear end of the inner side of the square tube, a right driving shaft 40 is arranged at the center of the right horizontal wing motor, a right shaft hole is formed in the square tube, a right driving shaft penetrates into the right shaft hole, a right horizontal wing 41 is installed on the right driving shaft, the left horizontal wing and the right horizontal wing are identical in size and are bilaterally symmetrical, the left horizontal wing motor and the right horizontal wing motor are identical in model and are bilaterally symmetrical, a vertical wing motor 42 is arranged at the rear end of the left horizontal wing motor, a vertical driving shaft 43 is arranged, The right horizontal wing motor and the vertical wing motor are both harmonic reducer motors, the harmonic reducer motor is a low-rotation-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 and the right horizontal wing motor rotate positively and reversely, the vertical wing motor is driven to turn left and right when the vertical wing motor rotates positively and reversely, an intelligent control box 45 is arranged in a square tube, a gyro horizontal sensor, a brushless motor control module and an intelligent control module are arranged in the intelligent control box, a storage battery 46 is arranged at the rear end of the intelligent control box, an arc-shaped cover plate 47 is arranged at the front end of the square tube, the arc-shaped cover plate is consistent with a semicircle at the front end of the cuboid missile body, a camera 48 is arranged in the center of the arc-shaped cover plate, 4 sensor holes are arranged on the, a left laser radar sensor 50 is arranged in a sensor hole at the left end of a camera shooting hole, a right laser radar sensor 51 is arranged in a sensor hole at the right end of the camera shooting hole, a starting indicator lamp 52 is arranged in the sensor hole at the lower end of the camera shooting hole, a steel bar hole 53 is arranged at the upper rear end of a cuboid missile body, the steel bar hole penetrates through the wall of a square tube and is directly communicated into the square tube, a Hall sensor 54 is arranged in the square tube close to the steel bar hole, a starting steel bar 55 is arranged on the pulley missile, a permanent magnet 56 is arranged at the lower end of the starting steel bar, the Hall sensor is triggered to be in a switching-on or switching-off state when the permanent magnet is close to the Hall sensor, so that a power switch of the pulley missile is controlled, the steel bar penetrates into a lock hole of the pulley missile to trigger the Hall, The output lines of 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 ends of the brushless motor control module and the start indicator lamp.

The electromagnetic gun of the missile of the fighter is provided with a missile repeating box, the front end in the missile repeating box is provided with a missile pushing vehicle, the missile pushing vehicle is provided with a square frame 57, the front end of the square frame is provided with a missile bin, a plurality of pulley missiles are stored in the missile bin, the height in the missile repeating box is equal to the length of the pulley missiles, the width in the missile repeating box is equal to the width of the pulley missiles, the length in the missile repeating box is equal to the sum of the length of the arrangement of the pulley missiles and the length of the square frame, the upper end of the missile repeating box is provided with a plurality of pulley missile inlets, the rear end of the bottom plate of the missile repeating box is provided with a single pulley missile inlet 58, the lower end of the square frame is provided with a front wheel shaft 59 and a rear wheel shaft 60, the left and right wheels 61 are arranged at the left and right ends of the front wheel shaft, the left and right wheels 62 are arranged at the left and right ends, the upper end of an L-shaped motor frame is positioned in a line groove, the lower end of the L-shaped motor frame is provided with a speed reducing motor 65, the left end of the speed reducing motor is provided with a driving gear 66, the lower end of the bottom plate of the missile repeating box is provided with a rack 67, the driving gear is matched with the rack, the left end and the right end of the missile repeating box are provided with bar grooves 68, the left bar groove and the right bar groove are respectively provided with a steel plate spring 69, the left steel plate spring and the right steel plate spring are equal in size and are symmetrical left and right, the rear ends of the left steel plate spring and the right steel plate spring are clamped at the left end and the right end of a second pulley missile at the rear ends of a plurality of pulley missiles, so that the plurality of pulley missiles can be stably fixed in a missile magazine no matter in a moving or static state, the rear right end of the missile repeating box is provided with a sensor hole, a Hall sensor, the output end of the control module of the deceleration motor is connected with the deceleration motor, the power end of the control module of the deceleration motor is connected with the lithium battery, the control module of the deceleration motor is triggered by pressing a reversing button, the deceleration motor is controlled to rotate anticlockwise to drive the bullet pusher to move forwards to the bottom and then release the reversing button, the bullet pusher stops, a plurality of pulley missiles with power supply opened are stored in a bullet cabin at the front end of the bullet pusher, the control module of the deceleration motor is triggered by pressing a missile launching button, the deceleration motor rotates clockwise, the bullet pusher pushes a plurality of pulley missiles backwards, when the permanent magnet particles of the second pulley missile are stopped and aligned with the Hall sensor, the Hall sensor stops outputting a pulse signal to trigger the control module of the deceleration motor, the deceleration motor automatically stops, the first pulley missile at the rear ends of the plurality of pulley missiles falls down by virtue of gravity and passes through the inlet of a single pulley missile to fall into a plurality of, after the missile launching button is pressed to be released, the missile is launched by a single pulley, and when the missile launching button is not pressed, the missile is launched by a plurality of pulleys continuously.

The existing electromagnetic gun is a linear gun barrel, the length of the linear gun barrel is limited, the speed of the cannonball is difficult to improve, the length of the unfolded spiral gun barrel exceeds that of the existing electromagnetic gun, the pulley missile is subjected to long-time relay acceleration in a longer spiral gun bore through a plurality of electromagnetic drivers, the speed of the pulley missile is improved to the limit by the power of a lithium battery, therefore, the size, the weight, the energy consumption and the loading capacity of the electromagnetic gun for the missile of the fighter are small, the electromagnetic gun for the missile is light, the energy consumption is small, the missile loading capacity is large, the electromagnetic gun for the missile is suitable for being arranged on the fighter, a target discovered by an airborne radar of the fighter is displayed on a data information display, the posture of the fighter is adjusted, the electromagnetic gun for the missile of the fighter can aim at the target to shoot, the initial speed of the pulley missile flying out from an outlet is equal to the linear speed accelerated in a plurality of, the intelligent control box receives an instruction of the gyro level sensor to drive the left horizontal wing and the right horizontal wing, so that the pulley missile flies in a horizontal state, the camera of the pulley missile can search and lock the target together according to the image information of the target, the infrared sensor can change the left flying direction and the right flying direction of the missile according to the heat source information of the target, and the left laser radar and the right laser radar can search and lock the target according to the reflection information of the target, so that a control signal of the flying direction is sent to the intelligent control box, the vertical wing is controlled to change the left flying direction and the right flying direction of the missile, and the left horizontal wing and the right horizontal wing are controlled to change the up-and-down flying direction of the missile, so that the pulley missile can automatically track and strike the target.