A magnetic induction type mover and a magnetic induction type cruise missile launching device

Abstract

The present application provides a magnetic induction type mover and a magnetic induction type loitering munition launching device. The magnetic induction type loitering munition launching device includes a barrel, a magnetic induction type mover, a plurality of coils and a plurality of sensors. Through the arrangement of a plurality of magnetic induction bodies, during a single launch process, the sensors detect the magnetic induction bodies multiple times, the corresponding coils generate magnetic fields multiple times, and an electromagnetic repulsive force in the direction of the launch end is applied to the magnetic induction type mover multiple times, thereby reducing the length of the launching device and saving costs. Through the design of the lengths and distribution distances of each component, the sum of the length of the coil and the distance between adjacent coils is equal to the distance between adjacent magnetic induction bodies, so that during the launch process, the magnetic induction type mover can continuously receive an electromagnetic repulsive force in the direction of the launch end, continuously accelerating the magnetic induction type mover to push the loitering munition, avoiding multiple impacts on the loitering munition, and reducing the damage caused to the loitering munition.

Description

Technical Field

[0001] This application belongs to the technical field of electromagnetic catapult, and particularly relates to a magnetic induction mover and a magnetic induction loitering munition launching device. Background Art

[0002] A loitering munition is a device that is launched through a ground acceleration device, can patrol and fly in the target area, and can perform single or multiple tasks such as surveillance, reconnaissance, battle damage assessment, air wireless relay, and attacking targets. It can be either a single projectile or composed of a warhead, a guidance device, a propulsion system, a control device (including wings), a stabilizing device (including tail fins or a parachute), etc. It can carry an active cruise power or achieve a passive cruise function. It has a very broad market application space and can be used in both military and industrial or civilian fields.

[0003] Loitering munitions are divided into two categories: projectile type and non-projectile type. For projectile-type loitering munitions, the current projection methods mainly include slingshot catapult type, high-pressure air bag type, pyrotechnic type, and liquid and gas pressure reciprocating piston type, etc. However, for the above various projection methods, some have low catapult speed, some have low catapult energy, some have slow loading speed, some are troublesome to operate, some have government order restrictions, some have strong operation risks, some occupy a large space, some have a large noise and are easy to be detected, etc., with one or more defects, and cannot meet the requirements of high frequency, multiple times, strong concealment, safety, convenience, volume, etc. in specific occasions.

[0004] For the current launching devices using electromagnetic principles, for step-by-step acceleration coil guns, the intermittent acceleration of the projectile is achieved by the way of single-time power-on acceleration of the projectile by an electromagnet. During the intermittent process, the projectile actually decelerates under the influence of a series of factors such as residual magnetism, air resistance, and friction. As a result, the whole process of the projectile's launch in the barrel is in a cycle of continuous acceleration → weak deceleration → acceleration, and the requirement for the impact resistance stability of the projectile is very high. Especially when used for the projection of loitering munitions, since there is no fixed rigid connection between the loitering munition and the accelerating body, the continuous acceleration and deceleration cycle will bring a great impact to the loitering munition and cause great damage to the loitering munition. Summary of the Invention

[0005] The embodiments of this application provide a magnetic induction mover and a magnetic induction loitering munition launching device, which realize the continuous acceleration of the magnetic induction mover by repeatedly powering on the coil, so that the loitering munition can be safely accelerated to the required muzzle velocity in a very short time, shorten the launch time, reduce the length of the launching device, and the magnetic induction mover continuously accelerates to push the loitering munition, avoiding multiple impacts on the loitering munition, reducing the damage to the loitering munition, and solving the problem that the existing electromagnetic launching device has a large impact on the loitering munition due to the continuous acceleration and deceleration cycle of the accelerating body and causes great damage to the loitering munition.

[0006] In a first aspect, an embodiment of the present application provides a magnetic induction mover, which is configured to move under an electromagnetic repulsive force in a magnetic field to propel a loitering munition to be ejected at high speed. The magnetic induction mover includes a plurality of magnetic induction bodies, a plurality of support members, and a loitering munition seat;

[0007] The plurality of magnetic induction bodies are equidistantly distributed. The magnetic induction bodies are configured to be subjected to an electromagnetic repulsive force in a magnetic field to drive the magnetic induction mover to move. A first pressure relief hole is provided on the magnetic induction body. The plurality of support members and the plurality of magnetic induction bodies are alternately distributed. Both ends of each support member in the axial direction are fixedly connected to the magnetic induction body. A second pressure relief hole is provided in the support member. The loitering munition seat is connected to the outermost magnetic induction body. The loitering munition seat is configured to connect to a loitering munition, and a third pressure relief hole is provided on the loitering munition seat.

[0008] In a feasible implementation manner, a placement position is provided on the side of the loitering munition seat facing away from the magnetic induction body. The placement position communicates with the third pressure relief hole, and the loitering munition is inserted into the placement position.

[0009] In a feasible implementation manner, a protection position is provided on the side of the loitering munition seat facing the magnetic induction body;

[0010] The placement position, the third pressure relief hole, the protection position, the first pressure relief hole, and the second pressure relief hole are sequentially communicated.

[0011] In a second aspect, an embodiment of the present application further provides a magnetic induction loitering munition launching device, including a barrel, the above-mentioned magnetic induction mover, a plurality of coils, and a plurality of sensors;

[0012] The barrel has a filling end and a launching end, and the filling end and the launching end are respectively located on two sides of the barrel in the axial direction. The loitering munition is placed in the barrel. The magnetic induction mover is inserted into the barrel. The plurality of coils are equidistantly arranged on the barrel. The coils surround the circumferential surface of the barrel. The sum of the length of the coil and the distance between adjacent coils is equal to the distance between adjacent magnetic induction bodies, which is equal to the sum of the lengths of all magnetic induction bodies;

[0013] The plurality of sensors correspond to the plurality of coils one by one, and the plurality of sensors and the plurality of coils are alternately distributed. The sensors are configured to detect the magnetic induction bodies, and when any magnetic induction body is detected, control the corresponding coil to be connected to an external alternating current power supply, and control the other energized coils to be disconnected from the external alternating current power supply.

[0014] In a feasible implementation manner, the distance between the sensing end of the sensor and the side of the corresponding coil facing the launching end is a trigger threshold, and the percentage of the trigger threshold to the length of the magnetic induction body is 0 to 15%;

[0015] When the length of any of the magnetic induction bodies extending towards the transmitting end side beyond the coil towards the transmitting end side reaches the trigger threshold, it can be detected by the sensor corresponding to this coil. When any sensor detects any of the magnetic induction bodies, the sensor controls the corresponding coil to be connected to the external alternating current power supply and controls the other energized coils to be disconnected from the external alternating current power supply.

[0016] In a feasible implementation manner, when the coil is connected to the external alternating current power supply, the coil generates a changing magnetic field, and the magnetic induction body is subjected to an electromagnetic repulsive force in the changing magnetic field in the direction away from the coil.

[0017] In a feasible implementation manner, the number of the magnetic induction bodies is greater than or equal to 2, and the length ratio of the magnetic induction bodies to the coil is 5 - 8:10.

[0018] In a feasible implementation manner, the magnetic induction body, the support member, and the outer wall of the cruise missile seat are all annular with equal outer diameters, and the outer wall of the magnetic induction type mover has a clearance fit with the inner wall of the barrel.

[0019] In a feasible implementation manner, a buffer limiting mechanism is provided at the transmitting end of the barrel. The cruise missile penetrates through the buffer limiting mechanism, and the buffer limiting mechanism is clamped with the magnetic induction type mover.

[0020] A magnetic induction type mover and a magnetic induction type cruise missile launching device provided by an embodiment of the present application. By inserting the magnetic induction type mover into the barrel, the magnetic induction type mover has a plurality of magnetic induction bodies. The magnetic induction bodies are non-magnetic good conductors and are subjected to an electromagnetic repulsive force in a changing magnetic field. A plurality of coils are equidistantly arranged on the barrel. The coils are electrically connected to an external alternating current power supply to introduce an alternating current to generate a changing magnetic field, and a plurality of sensors corresponding to the plurality of coils are provided. When the sensor detects any magnetic induction body, the sensor controls the corresponding coil to be connected to the external alternating current power supply and controls the other energized coils to be disconnected from the external alternating current power supply, so that the magnetic induction body is subjected to an electromagnetic repulsive force in the changing magnetic field of the coil in the direction towards the transmitting end, thereby enabling the magnetic induction type mover to push the cruise missile to be launched;

[0021] Through the design of a plurality of magnetic induction bodies, during one launching process, the sensor detects the magnetic induction bodies multiple times, the corresponding coils generate a changing magnetic field multiple times, and an electromagnetic repulsive force in the direction towards the transmitting end is applied to the magnetic induction type mover multiple times, so that the magnetic induction type mover and the cruise missile can quickly reach the required launching speed, shorten the launching time, and furthermore, the length of the launching device is reduced, and the cost is saved;

[0022] By designing the lengths of various components and the distribution distances, the sum of the length of the coil and the distance between adjacent coils is made equal to the distance between adjacent magnetic induction bodies, which is equal to the sum of the lengths of all magnetic induction bodies. In this way, during the launching process, the magnetic induction type mover can continuously receive electromagnetic repulsive force in the direction of the launching end, enabling the magnetic induction type mover to continuously accelerate and push the cruise missile, avoiding multiple impacts on the cruise missile and reducing the damage caused to the cruise missile. Description of the Drawings

[0023] Figure 1 is a schematic structural diagram of the magnetic induction type mover provided by this application;

[0024] Figure 2 is a schematic structural diagram of the magnetic induction type cruise missile launching device provided by this application;

[0025] Figure 3 is a schematic diagram of the state at the first moment during the launching process;

[0026] Figure 4 is a schematic diagram of the state at the second moment during the launching process;

[0027] Figure 5 is a schematic diagram of the state at the third moment during the launching process;

[0028] Figure 6 is a schematic diagram of the state at the fourth moment during the launching process.

[0029] Description of the Reference Numerals:

[0030] 100 - Bore tube; 200 - Coil; 300 - Sensor; 400 - Magnetic induction type mover;

[0031] 410 - Magnetic induction body; 420 - Support sleeve; 430 - Cruise missile seat;

[0032] 411 - First pressure relief hole; 421 - Second pressure relief hole; 431 - Placement position; 432 - Protection position; 433 - Third pressure relief hole. Detailed Embodiments

[0033] In order to enable those skilled in the art of this technology to better understand the technical solutions in this application, the following will clearly and completely describe the technical solutions in the embodiments of this application in conjunction with the accompanying drawings in the embodiments of this application. Obviously, the described embodiments are only a part of the embodiments of this application, rather than all of the embodiments. Based on the embodiments in this application, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of this application.

[0034] In the prior art, the main projection methods of loitering munitions include slingshot ejection, high-pressure air bag, pyrotechnic device, liquid and gas pressure reciprocating piston, etc. However, for the above various projection methods, some have low ejection speed, some have low ejection energy, some have slow loading speed, some are troublesome to operate, some have administrative restrictions, some have strong operation risks, some occupy a large space, some have high noise and are easy to be detected, etc., with one or more defects, and cannot meet the requirements of high frequency, multiple times, strong concealment, safety, convenience, small size, etc. in specific scenarios.

[0035] Currently, for the launch devices using electromagnetic principles, for step-by-step acceleration coil guns, the projectile is intermittently accelerated by applying a single electric current to the projectile through an electromagnet. During the intermittent process, the projectile actually decelerates under the influence of a series of factors such as residual magnetism, air resistance, and friction. As a result, the entire launch process of the projectile in the barrel is in a continuous cycle of acceleration → weak deceleration → acceleration, which requires a very high impact resistance stability for the projectile. Especially when used for loitering munition projection, since there is no fixed rigid connection between the loitering munition and the accelerating body, the continuous acceleration and deceleration cycle will cause a great impact on the loitering munition and cause great damage to the loitering munition.

[0036] Moreover, due to the fact that each coil of the existing coil gun structure can only be energized once, the required launch time is long, the total length of the launch device is too long, the cost is high, and it is inconvenient to use.

[0037] In this application, the continuous acceleration of the magnetic induction type mover is achieved by repeatedly energizing the coil, so that the loitering munition can be safely accelerated to the required muzzle velocity in a very short time, shortening the launch time, reducing the length of the launch device. The magnetic induction type mover 400 continuously accelerates to push the loitering munition, avoiding multiple impacts on the loitering munition and reducing the damage caused to the loitering munition.

[0038] The following will describe in detail the specific structures of the magnetic induction type mover and the magnetic induction type loitering munition launch device provided by this application with reference to the accompanying drawings.

[0039] Embodiment 1:

[0040] Referring to Figure 1 As shown, the embodiment of this application provides a magnetic induction type mover. The magnetic induction type mover is applied to a magnetic induction type loitering munition launch device. The magnetic induction type mover is configured to move under the action of electromagnetic repulsion force in a changing magnetic field, push the loitering munition to accelerate until it is ejected at a high speed. The magnetic induction type mover includes a plurality of magnetic induction bodies 410, several support members 420, and a loitering munition seat 430.

[0041] The magnetic induction body 410 can be an annular body. The magnetic induction body 410 is a non-magnetic good conductor, and the materials used are good conductors such as aluminum, copper, tin or corresponding alloys and non-magnetic materials. The magnetic induction body 410 is subject to electromagnetic repulsive force in a changing magnetic field. A plurality of magnetic induction bodies 410 are evenly distributed. A plurality of magnetic induction bodies 410 are all subject to electromagnetic repulsive force in a changing magnetic field, and can all provide power for the movement of the magnetic induction type mover, thereby increasing the acceleration of the magnetic induction type mover, shortening the time required for the cruise missile to reach the launch speed, facilitating short-time and multiple launches. The magnetic induction body 410 is provided with a first pressure relief hole 411. The first pressure relief hole 411 can be a round hole or a square hole, and a plurality of them can be provided;

[0042] The support member 420 is a support sleeve. The material preferably used for the support sleeve is an insulating material or a poor conductive non-magnetic metal material. The purpose is to avoid bringing reverse repulsive force to other accelerating bodies due to induced eddy currents when the coil is energized or de-energized instantaneously. The support sleeve can be an integral circular ring, or can be a structure of one or more columnar bodies. A plurality of support members 420 and a plurality of magnetic induction bodies 410 are alternately distributed. The number of support members 420 is one less than the number of magnetic induction bodies 410. Both ends of each support member 420 in the axial direction are fixedly connected to the magnetic induction body 410. The support member 420 is provided with a second pressure relief hole 421. The second pressure relief hole 421 can be a round hole or a square hole, and a plurality of them can be provided;

[0043] The cruise missile seat 430 can be a cylindrical structure matching the cruise missile. The cruise missile seat 430 is connected to the outermost magnetic induction body 410. The cruise missile seat 430 is configured to connect the cruise missile. The cruise missile seat 430 is provided with a third pressure relief hole 433. When the cruise missile is placed in the cruise missile seat 430, the cruise missile does not block the third pressure relief hole 433. The third pressure relief hole 433 can be a round hole or a square hole, and a plurality of them can be provided;

[0044] To facilitate air flow, the first pressure relief hole 411, the second pressure relief hole 421 and the third pressure relief hole 433 can be located on the same axis, and the extending direction of the axis is consistent with the movement direction of the magnetic induction type mover. When the magnetic induction type mover 400 is pushed by electromagnetic repulsive force to accelerate the cruise missile, the first pressure relief hole 411, the second pressure relief hole 421 and the third pressure relief hole 433 can release the wind pressure resistance generated during high-speed operation, thereby reducing the influence of wind resistance on the speed of the magnetic induction type mover 400. At the same time, it can also eliminate the influence of the negative pressure generated at the tail end on the acceleration when the magnetic induction type mover 400 is extremely accelerated in the barrel, so that the magnetic induction type mover 400 and the cruise missile can reach the launch speed faster, thereby shortening the time required for launch and increasing the muzzle velocity.

[0045] A magnetic induction type mover provided by an embodiment of the present application, by arranging a plurality of magnetic induction bodies 410 inside the magnetic induction type mover 400, the plurality of magnetic induction bodies 410 are all subject to electromagnetic repulsive forces in a changing magnetic field, and can all provide power for the movement of the magnetic induction type mover, thereby increasing the acceleration of the magnetic induction type mover, shortening the time required for the cruise missile to reach the launch speed, and facilitating short-time and multiple launches;

[0046] By arranging a first pressure relief hole 411 on the magnetic induction body 410, a second pressure relief hole 421 inside the support member 420, and a third pressure relief hole 433 on the cruise missile seat 430, the first pressure relief hole 411, the second pressure relief hole 421, and the third pressure relief hole 433 are located on the same axis, and the extending direction of the axis is consistent with the movement direction of the magnetic induction type mover. When the magnetic induction type mover 400 is pushed by the electromagnetic repulsive force to accelerate the cruise missile, the first pressure relief hole 411, the second pressure relief hole 421, and the third pressure relief hole 433 can release the wind pressure resistance generated during high-speed operation, thereby reducing the influence of wind resistance on the speed of the magnetic induction type mover 400. At the same time, it can also eliminate the influence of the negative pressure generated at the tail end on acceleration when the magnetic induction type mover 400 is extremely accelerated in the barrel, enabling the magnetic induction type mover 400 and the cruise missile to reach the launch speed faster, thereby shortening the time required for launch and increasing the muzzle velocity.

[0047] Refer to Figure 1 As shown, in some embodiments, a placement position 431 is provided on the side of the cruise missile seat 430 facing away from the magnetic induction body 410. The placement position 431 can be a cylinder matching the cruise missile. The placement position 431 is communicated with the third pressure relief hole 433. The cruise missile is inserted into the placement position 431, thereby facilitating stable connection and pushing the cruise missile. And because the bottom surface of the cruise missile is not flat, the third pressure relief hole 433 will not be blocked.

[0048] Refer to Figure 1 As shown, in some embodiments, a protection position 432 is provided on the side of the cruise missile seat 430 facing the magnetic induction body 410. The protection position 432 can be either a cavity-type structure or a solid structure. The main purpose of the protection position 432 is to ensure that when the external coil is energized, the distance between the cruise missile and the energized coil is far enough to avoid the instantaneous large current and magnetic induction gradient of the energized coil from affecting the cruise missile;

[0049] The placement position 431, the third pressure relief hole 433, the protection position 432, the first pressure relief hole 411, and the second pressure relief hole 421 are sequentially communicated, thereby releasing the wind pressure resistance generated during the high-speed operation of the magnetic induction type mover 400, thereby reducing the influence of wind resistance on the speed of the magnetic induction type mover 400. At the same time, it can also eliminate the influence of the negative pressure generated at the tail end on acceleration when the magnetic induction type mover 400 is extremely accelerated in the barrel, enabling the magnetic induction type mover 400 and the cruise missile to reach the launch speed faster, thereby shortening the time required for launch and increasing the muzzle velocity.

[0050] Embodiment 2:

[0051] Referring to Figure 2 As shown, the embodiment of the present application provides a magnetic induction type cruise missile launching device, including a barrel 100, the above-mentioned magnetic induction type mover 400, a plurality of coils 200 and a plurality of sensors 300;

[0052] The barrel 100 is a tube body with a certain strength. The barrel 100 has a filling end and a launching end, and the filling end and the launching end are respectively located on both sides of the axis direction of the barrel 100. The cruise missile and the magnetic induction type mover 400 are placed in the barrel 100 and are both inserted into the barrel 100. During actual launching, the cruise missile and the magnetic induction type mover 400 can be inserted into the barrel 100 from the launching end or from the filling end. After insertion, the cruise missile and the magnetic induction type mover 400 both move to the vicinity of the filling end of the barrel 100, and then the external alternating current power supply is connected to prepare for launching;

[0053] A plurality of coils 200 are equally spaced on the barrel 100. The coils 200 surround the circumferential surface of the barrel 100. A plurality of coils 200 are respectively electrically connected to an external alternating current power supply. The coils 200 pass through alternating current to generate a changing magnetic field. The sum of the length of the coil 200 and the spacing length between adjacent coils 200 is equal to the spacing length between adjacent magnetic induction bodies 410, and is equal to the sum of the lengths of all the magnetic induction bodies 410;

[0054] A plurality of sensors 300 correspond to a plurality of coils 200 one by one. The plurality of sensors 300 and the plurality of coils 200 are alternately distributed. The sensors 300 are configured to detect the position of the magnetic induction body 410, and control the corresponding coil 200 to be connected to the external alternating current power supply according to the position of the magnetic induction body 410, and control other energized coils 200 to be disconnected from the external alternating current power supply;

[0055] The sensor 300 is used to detect the position of the magnetic induction body 410. The sensor can be an optoelectronic sensor. The sensing end of the sensor just penetrates the barrel 100. The sensor 300 can also be other sensors, which will not be elaborated here;

[0056] The sensor 300 can control the corresponding coil 200 to be connected to an external alternating power supply through other components, and control other energized coils 200 to be disconnected from the external alternating power supply; in one embodiment, the sensor 300 controls the corresponding coil 200 to be connected to the external alternating power supply through the first drive board. The output end of the sensor 300 is connected to the control interface of the first drive board, and the external variable power supply, the first drive board, and the corresponding coil 200 are connected in series in sequence, so as to realize the sensor 300 controlling the corresponding coil 200 to be energized. Similarly, the sensor 300 can control other coils 200 to be disconnected from the external alternating power supply through the second drive board; the sensor 300 can also use other methods to control the corresponding coil 200 to be energized and other coils 200 to be de-energized, which will not be elaborated here.

[0057] A magnetic induction type cruise missile launching device provided by an embodiment of the present application inserts a magnetic induction type mover 400 into the barrel 100. The magnetic induction type mover 400 has a plurality of magnetic induction bodies 410. The magnetic induction bodies 410 are non-magnetic good conductors and are subjected to electromagnetic repulsive forces in a changing magnetic field. A plurality of coils 200 are equidistantly arranged on the barrel 100. The coils 200 are electrically connected to an external alternating power supply, and an alternating current is passed through to generate a changing magnetic field. A plurality of sensors 300 corresponding to the plurality of coils 200 are provided. When the sensor 300 detects any magnetic induction body 410, the sensor 300 controls the corresponding coil 200 to be connected to the external alternating power supply, and controls other energized coils 200 to be disconnected from the external alternating power supply, so that the magnetic induction body 410 is subjected to an electromagnetic repulsive force in the direction of the launching end in the magnetic field of the coil 200, and further enables the magnetic induction type mover 400 to push the cruise missile to be launched;

[0058] Through the arrangement of a plurality of magnetic induction bodies 410, during one launching process, the sensor 300 detects the magnetic induction bodies 410 multiple times, the corresponding coils 200 generate a changing magnetic field multiple times, and an electromagnetic repulsive force in the direction of the launching end is applied to the magnetic induction type mover 400 multiple times, so that the magnetic induction type mover 400 and the cruise missile can quickly reach the required launching speed, shorten the launching time, and also reduce the length of the launching device and save costs;

[0059] Through the design of the lengths and distribution distances of each component, the sum of the length of the coil 200 and the spacing length between adjacent coils 200 is equal to the spacing length between adjacent magnetic induction bodies 410, which is equal to the total length of all magnetic induction bodies 410. In this way, during the launching process, the magnetic induction type mover 400 can continuously receive an electromagnetic repulsive force in the direction of the launching end, enabling the magnetic induction type mover 400 to continuously accelerate and push the cruise missile, avoiding multiple impacts on the cruise missile and reducing the damage caused to the cruise missile.

[0060] In some embodiments, the distance between the sensing end of the sensor 300 and the side of the corresponding coil 200 facing the transmitting end is β, where β is the trigger threshold, β ≥ 0, and the percentage of the trigger threshold to the length of the magnetic inducer 410 is 0 to 15%.

[0061] When the length of any magnetic inducer 410 extending out of the side of the coil 200 facing the transmitting end reaches the trigger threshold, it can be detected by the sensor 300 corresponding to the coil 200. When any sensor 300 detects any magnetic inducer 410, the sensor 300 controls the corresponding coil 200 to be connected to an external alternating power source, and controls other energized coils 200 to be disconnected from the external alternating power source.

[0062] When the sensor 300 detects any magnetic inducer 410, the sensor 300 controls the corresponding coil 200 to be connected to an external alternating power source, and controls other energized coils 200 to be disconnected from the external alternating power source. That is, at any moment during the entire launching process, in this magnetic induction type cruise missile launching device, only one coil 200 is energized to generate a changing magnetic field.

[0063] In some embodiments, when the coil 200 is connected to an external alternating power source, the coil 200 generates a changing magnetic field. The magnetic inducer 410 is subjected to an electromagnetic repulsive force in the direction away from the coil 200 and an electromagnetic repulsive force in the direction towards the transmitting end in the changing magnetic field, thereby pushing the cruise missile to accelerate in the direction towards the transmitting end.

[0064] Refer to Figure 2 and Figure 5 As shown, in some embodiments, the number of magnetic inducers 410 is greater than or equal to 2. The optimal solution is that the number of magnetic inducers 410 is greater than or equal to 3 and less than or equal to 5, and the length ratio of the magnetic inducer 410 to the coil 200 is 5 - 8:10.

[0065] When the number of magnetic inducers is greater than or equal to 3, due to the distribution characteristics of the magnetic induction gradient, the magnetic induction type mover 400 can be in the region with the maximum and stable electromagnetic repulsive force during the whole - process acceleration movement, enabling the magnetic induction type mover 400 to obtain as large a kinetic energy effect as possible within the same acceleration length. Considering that when the number of magnetic inducers 410 increases, the self - weight and length of the magnetic induction type mover 400 will also increase correspondingly, which has a negative impact on the stiffness of the structure. Therefore, generally, the number of magnetic inducers is preferably less than or equal to 5.

[0066] When the number of magnetic induction bodies is greater than or equal to 3, the electromagnetic repulsive force on the magnetic induction type mover 400 can be maximized and stabilized throughout the acceleration process, achieving the optimal stroke speed ratio. This is because when the magnetic induction bodies are within the variable current coil, the actual electromagnetic repulsive force they experience varies significantly depending on their relative insertion depth into the coil. Through Ansys analysis and test results, when the ratio of the length of the magnetic induction body to the length of the energized coil is in the range of 5 - 8:10, and the front end face of the advancing side of the magnetic induction body 410 is flush with the corresponding side of the coil, when a variable current is applied, the electromagnetic repulsive force is the largest. At the same time, the stable region of the electromagnetic repulsive force is in the range where the rear end face of the magnetic induction body is 30 - 85% of the length of the coil from the rear end face of the variable current coil. When the number of magnetic induction bodies 410 is equal to 3, the rear end face of the corresponding magnetic induction body during acceleration is always at 30 - 85% of the length of the variable current coil, thus ensuring the best acceleration effect.

[0067] Referring to Figure 2 As shown, in some embodiments, the outer walls of the magnetic induction body 410, the support member 420, and the outer wall of the loitering missile seat 430 are all annular with equal outer diameters. The outer wall of the magnetic induction type mover 400 has a clearance fit with the inner wall of the barrel 10. And during the entire launch process, since the magnetic induction type mover 400 is in a non-contact state with the coil, the noise is very small.

[0068] In some embodiments, a buffer limiting mechanism is provided at the launch end of the barrel 100. The loitering missile passes through the buffer limiting mechanism, and the buffer limiting mechanism is engaged with the magnetic induction type mover 400. The buffer limiting mechanism can be an elastic limiting ring, which is detachably arranged at the launch end of the barrel 100. The loitering missile can pass through the elastic limiting ring, and the magnetic induction type mover 400 is engaged with the elastic limiting ring. The elastic limiting ring buffers and decelerates the magnetic induction type mover 400, making it convenient to use.

[0069] According to the above technical features, the working principle of the magnetic induction type loitering missile launch device provided by this application in the actual application scenario is as follows:

[0070] As Figures 3 - 6 shown, in the figure, the left end of the barrel 100 is the launch end, the right end is the filling end. There are n coils 200, which are L1, L2, L3, L4... Ln from right to left in sequence. There are n sensors 300, which are T1, T2, T3, T4... Tn from right to left in sequence. The magnetic induction type mover 400 includes two magnetic induction bodies 410, which are C1 and C2 from right to left respectively. A is the loitering missile, and the loitering missile A is located on the left side of the magnetic induction type mover 400;

[0071] Set the trigger threshold to 0, that is, the sensing end of the sensor 300 and the side of the corresponding coil 200 facing the transmitting end are in the same plane. When the side of any magnetic induction body 410 facing the transmitting end is parallel to the side of the coil 200 facing the transmitting end, the magnetic induction body is detected by the sensor 300 corresponding to the coil 200;

[0072] At Figure 3 In the state at the first moment shown, the left end of the magnetic induction body C2 is parallel to the left end of the coil L2, and the magnetic induction body C2 is detected by the sensor T2. Then the sensor T2 controls the coil L2 to be connected to the external alternating power supply, and the coil L2 generates a changing magnetic field. The magnetic induction body C2 receives an electromagnetic repulsive force to the left in the changing magnetic field of the coil L2, so the magnetic induction type mover 400 pushes the cruise missile A to accelerate to the left;

[0073] When reaching Figure 4 In the state at the second moment shown, at this time the magnetic induction body C2 just breaks away from the coil L2. Because the sum of the length of the coil 200 and the spacing length between adjacent coils 200 is equal to the spacing length between adjacent magnetic induction bodies 410, at this time the left end of the magnetic induction body C1 is just parallel to the left end of the coil L1, and the magnetic induction body C1 is detected by the sensor T1. The sensor T1 controls the coil L1 to be connected to the external alternating power supply, and the sensor T1 controls the coil L2 to be disconnected from the external alternating power supply. Then the coil L1 generates a changing magnetic field, and the magnetic induction body C1 receives an electromagnetic repulsive force to the left in the changing magnetic field of the coil L1, so the magnetic induction type mover 400 continues to push the cruise missile A to accelerate to the left;

[0074] When reaching Figure 5 In the state at the third moment shown, at this time the magnetic induction body C1 just breaks away from the coil L1. Because the sum of the length of the coil 200 and the spacing length between adjacent coils 200 is equal to the spacing length between adjacent magnetic induction bodies 410, which is equal to the sum of the lengths of all magnetic induction bodies 410, at this time the left end of the magnetic induction body C2 is parallel to the left end of the coil L3, and the magnetic induction body C2 is detected by the sensor T3. Then the sensor T3 controls the coil L3 to be connected to the external alternating power supply, controls the coil L1 to be disconnected from the external alternating power supply, and the coil L3 generates a changing magnetic field. The magnetic induction body C2 receives an electromagnetic repulsive force to the left in the changing magnetic field of the coil L3, so the magnetic induction type mover 400 continues to push the cruise missile A to accelerate to the left;

[0075] When reaching Figure 6At the state of the fourth moment shown, at this time, the magnetic induction body C2 just breaks away from the coil L3. Since the sum of the length of the coil 200 and the spacing length between adjacent coils 200 is equal to the spacing length between adjacent magnetic induction bodies 410, at this time, the left end of the magnetic induction body C1 is parallel to the left end of the coil L2, and the magnetic induction body C1 is detected by the sensor T2. Then the sensor T2 controls the coil L2 to be connected to the external alternating power supply and controls the coil L3 to be disconnected from the external alternating power supply. The coil L2 generates a changing magnetic field, and the magnetic induction body C1 receives an electromagnetic repulsive force to the left in the changing magnetic field of the coil L2. Then the magnetic induction type mover 400 continues to push the cruise missile A to accelerate to the left;

[0076] This process is cycled multiple times in sequence, so that the magnetic induction type mover 5 and the cruise missile reach the required launch speed and complete the launch operation. During the launch process, by alternately switching the on-off state of the coil, it is ensured that the magnetic induction type mover 5 stably receives an electromagnetic repulsive force towards the launch end, so that it always accelerates, pushes the cruise missile, and enables the cruise missile to always bear an approximately equal pressure in the barrel 100, greatly improving the acceleration environment of the cruise missile and reducing the failure rate of the cruise missile.

[0077] It is easy to understand that those skilled in the art can combine, split, recombine, etc. the embodiments of the present application based on several embodiments provided in the present application to obtain other embodiments, and these embodiments do not exceed the protection scope of the present application.

[0078] The above specific implementation manners further elaborate on the purpose, technical solutions, and beneficial effects of the embodiments of the present application. It should be understood that the above are only the specific implementation manners of the embodiments of the present application and are not used to limit the protection scope of the embodiments of the present application. Any modifications, equivalent replacements, improvements, etc. made on the basis of the technical solutions of the embodiments of the present application shall be included in the protection scope of the embodiments of the present application.

Claims

1. A magnetic induction mover, which is configured to move under the action of electromagnetic repulsive force in a changing magnetic field and push a cruise missile to be launched at high speed, characterized in that: The magnetic induction type mover includes: A plurality of magnetic induction bodies (410), the plurality of magnetic induction bodies (410) are equidistantly distributed, a first pressure relief hole (411) is provided on the magnetic induction body (410), the magnetic induction body (410) is a non-magnetic good conductor, the magnetic induction body (410) is subjected to an electromagnetic repulsive force in a changing magnetic field, and the magnetic induction body (410) is configured to be subjected to an electromagnetic repulsive force in a changing magnetic field to drive the magnetic induction type mover to move; A plurality of support members (420), the plurality of support members (420) and the plurality of magnetic induction bodies (410) are alternately distributed, both ends of each support member (420) in the axial direction are fixedly connected to the magnetic induction body (410), and a second pressure relief hole (421) is provided in the support member (420); A loitering missile seat (430), the loitering missile seat (430) is connected to the outermost magnetic induction body (410), a third pressure relief hole (433) is provided on the loitering missile seat (430), and the loitering missile seat (430) is configured to connect a loitering missile.

2. The magnetic induction type mover according to claim 1, wherein: A placement position (431) is provided on the side of the loitering missile seat (430) facing away from the magnetic induction body (410), the placement position (431) communicates with the third pressure relief hole (433), and the loitering missile is inserted into the placement position (431).

3. The magnetic induction type mover according to claim 2, wherein: A protection position (432) is provided on the side of the loitering missile seat (430) facing the magnetic induction body (410); The placement position (431), the third pressure relief hole (433), the protection position (432), the first pressure relief hole (411), and the second pressure relief hole (421) are sequentially communicated.

4. A magnetic induction type cruise missile launching device, characterized in that: Including; A barrel (100), the barrel (100) has a filling end and a launching end, the filling end and the launching end are respectively located on both sides of the barrel (100) in the axial direction, and the loitering missile is placed in the barrel (100); The magnetic induction type mover (400) according to any one of claims 1-3, the magnetic induction type mover (400) is inserted into the barrel (100); A plurality of coils (200), the plurality of coils (200) are evenly arranged on the barrel (100), the coils (200) surround the circumferential surface of the barrel (100), and the plurality of coils (200) are respectively electrically connected to an external alternating current power supply, An alternating current is passed through the coil (200) to generate a changing magnetic field, and the sum of the length of the coil (200) and the distance between adjacent coils (200) is equal to the distance between adjacent magnetic induction bodies (410), and is equal to the sum of the lengths of all the magnetic induction bodies (410); A plurality of sensors (300), the plurality of sensors (300) corresponding one-to-one to the plurality of coils (200), the plurality of sensors (300) and the plurality of coils (200) being alternately distributed, the sensors (300) being configured to detect the magnetic induction bodies (410), and when any of the magnetic induction bodies (410) is detected, controlling the corresponding coil (200) to be connected to an external alternating power supply and controlling the other energized coils (200) to be disconnected from the external alternating power supply.

5. The magnetic induction type cruise missile launching device according to claim 4, wherein: The distance between the induction end of the sensor (300) and the side of the corresponding coil (200) facing the launching end is a triggering threshold, and the percentage of the triggering threshold to the length of the magnetic induction body (410) is 0-15%; When the length of any magnetic induction body (410) extending out of the side of the coil (200) facing the launching end reaches the triggering threshold, it can be monitored by the sensor (300) corresponding to the coil (200). When any sensor (300) monitors any magnetic induction body (410), the sensor (300) controls the corresponding coil (200) to be connected to an external alternating power supply and controls the other energized coils (200) to be disconnected from the external alternating power supply.

6. The magnetic induction type cruise missile launching device according to claim 4, wherein: When the coil (200) is connected to an external alternating power supply, the coil (200) generates a changing magnetic field, and the magnetic induction body (410) is subjected to an electromagnetic repulsive force in the direction away from the coil (200) in the changing magnetic field.

7. The magnetic induction type cruise missile launching device according to claim 4, wherein: The number of the magnetic induction bodies (410) is greater than or equal to 2, and the length ratio of the magnetic induction bodies (410) to the coils (200) is 5-8:

10.

8. The magnetic induction type cruise missile launching device according to claim 4, wherein: The outer walls of the magnetic induction body (410), the support member (420), and the outer wall of the cruise missile seat (430) are all annular with equal outer diameters, and the outer wall of the magnetic induction type mover (400) is in clearance fit with the inner wall of the barrel (100).

9. The magnetic induction type cruise missile launching device according to claim 4, wherein: A buffer limiting mechanism is provided at the launching end of the barrel (100), the cruise missile penetrates through the buffer limiting mechanism, and the buffer limiting mechanism is engaged with the magnetic induction type mover (400).

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