A magnetoresistive mover and magnetoresistive cruise missile launching device

Abstract

The present application provides a magnetoresistive mover and a magnetoresistive cruise missile launcher. The magnetoresistive cruise missile launcher includes a barrel, a magnetoresistive mover, multiple coils, and multiple sensors. Through the arrangement of multiple soft magnets, during a launch process, the sensor detects the soft magnet multiple times, and the corresponding coil generates a constant magnetic field multiple times, applying electromagnetic attraction toward the launch end to the magnetoresistive mover multiple times, thereby shortening the launch device length and saving costs. By designing the length and distribution distance of each component, the sum of the length of the coil and the spacing length of adjacent coils is equal to the spacing length of adjacent soft magnets, which is equal to the sum of the lengths of all soft magnets. In this way, during the launch process, the magnetoresistive mover is continuously subjected to the electromagnetic attraction toward the launch end, so that the magnetoresistive mover continuously accelerates and pushes the cruise missile, avoiding multiple collisions and impacts on the cruise missile and reducing damage to the cruise missile.

Description

Technical Field

[0001] The present application belongs to the field of electromagnetic catapult technology, and in particular relates to a magnetoresistive mover and a magnetoresistive cruise missile launcher. Background Art

[0002] A loitering munition is a device deployed via ground-based acceleration equipment and capable of patrolling a target area. It can perform single or multiple missions, including surveillance, reconnaissance, combat damage assessment, aerial wireless relay, and target attack. It can be a single projectile or comprise a warhead, guidance system, propulsion system, control system (including wings), and stabilization system (including tail fins or parachutes). It can carry active cruise propulsion or passive cruise capabilities. It has a broad market application space, encompassing military, industrial, and civilian applications.

[0003] There are two types of cruise missiles: projectile type and non-projectile type. For projectile cruise missiles, the main methods of projection currently used include slingshot ejection, high-pressure air bag type, fire attack type, and liquid and gas pressure reciprocating piston type. However, some of the above projection methods have low ejection speed, low ejection energy, slow loading speed, complicated operation, political restrictions, high operational risks, large space occupation, loud noise, easy to be discovered, and other defects, which cannot meet the requirements of high frequency, multiple times, strong concealment, safety, convenience, and volume in specific occasions.

[0004] Today, the launch device that uses the electromagnetic principle, for the step-by-step acceleration coil gun, achieves intermittent acceleration of the projectile by a single electric current applied to the projectile by the electromagnet during the intermittent process. Under the influence of a series of factors such as residual magnetism, wind resistance, and friction, the projectile actually decelerates, resulting in the projectile being in a continuous acceleration → weak deceleration → acceleration cycle throughout the launch process in the barrel. This places very high demands on the impact resistance and stability of the projectile, especially when used for the launch of cruise missiles. Since there is no fixed rigid connection between the cruise missile and the accelerator, the continuous acceleration and deceleration cycle will bring great impact to the cruise missile and cause great damage to the cruise missile. Summary of the Invention

[0005] The embodiments of the present application provide a magnetoresistive mover and a magnetoresistive cruise missile launcher. By repeatedly energizing the coil, the magnetoresistive mover is continuously accelerated, so that the cruise missile can be safely accelerated to the required muzzle velocity in a very short time, shortening the launch time and reducing the length of the launcher. The magnetoresistive mover continuously accelerates and pushes the cruise missile, avoiding multiple collisions and impacts on the cruise missile, reducing damage to the cruise missile, and solving the problem of existing electromagnetic launch devices in which the accelerator is constantly accelerating and decelerating, causing large collisions and impacts on the cruise missile and causing large damage to the cruise missile.

[0006] In a first aspect, embodiments of the present application provide a reluctance mover configured to move in a magnetic field under electromagnetic attraction to propel a cruise missile at high speed. The reluctance mover includes a plurality of soft magnets, a plurality of support members, and a cruise missile seat.

[0007] A plurality of the soft magnets are distributed equidistantly, and the soft magnets are configured to be subjected to electromagnetic attraction in a magnetic field, driving the magnetic induction type mover to move. A first pressure relief hole is provided on the soft magnet. The soft magnet is a magnetic body that is easily demagnetized. The soft magnet is subjected to electromagnetic attraction in a constant magnetic field. The soft magnet is configured to be subjected to electromagnetic attraction in a magnetic field, driving the magnetic resistance type mover to move. Several of the support members are alternately distributed with the plurality of the soft magnets, and both ends of the axis direction of each support member are fixedly connected to the soft magnet. A second pressure relief hole is provided in the support member. The cruise missile seat is connected to the outermost soft magnet. The cruise missile seat is configured to connect a cruise missile, and a third pressure relief hole is provided on the cruise missile seat.

[0008] In a feasible implementation, a placement position is provided on the side of the cruise missile seat facing away from the soft magnetic body, the placement position is connected to the third pressure relief hole, and the cruise missile is inserted into the placement position.

[0009] In a feasible implementation, a protection position is provided on the side of the loitering bomb mount facing the soft magnetic 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 connected in sequence.

[0011] In a second aspect, an embodiment of the present application provides a magnetoresistive cruise missile launcher, comprising a barrel, the magnetoresistive mover, a plurality of coils, and a plurality of sensors;

[0012] The barrel has a filling end and a launching end, the filling end and the launching end are respectively located on both sides of the barrel axis direction, the loitering missile is placed in the barrel, and the reluctance mover is plugged into the barrel;

[0013] The plurality of coils are equidistantly arranged on the bore tube, the coils surrounding the circumference of the bore tube, the plurality of coils being electrically connected to an external DC power supply, the coils being supplied with DC power to generate a constant magnetic field, the sum of the length of the coil and the length of the spacing between adjacent coils being equal to the length of the spacing between adjacent soft magnetic bodies, and being equal to the sum of the lengths of all the soft magnetic bodies;

[0014] The multiple sensors correspond one-to-one to the multiple coils, and the multiple sensors are alternately distributed with the multiple coils. The sensors are configured to detect the soft magnetic bodies, and when any soft magnetic body is detected, the corresponding coils are controlled to be connected to the external DC power supply according to the position of the soft magnetic body, and the other energized coils are controlled to be disconnected from the external DC power supply.

[0015] In a feasible implementation, the distance between the sensing end of the sensor and the corresponding coil facing the filling end is a trigger threshold, and the percentage of the trigger threshold to the length of the soft magnetic body is 0 to 15%;

[0016] When the length of any of the soft magnetic bodies inserted toward the transmitting end side and toward the filling end side of the coil reaches a trigger threshold, it can be detected by the sensor corresponding to the coil. When any of the sensors detects any of the soft magnetic bodies, the sensor controls the corresponding coil to be connected to the external DC power supply, and controls the other energized coils to be disconnected from the external DC power supply.

[0017] In a feasible implementation, when the coil is connected to an external DC power supply, the coil generates a constant magnetic field, and the soft magnetic body is subjected to an electromagnetic attraction force in the direction of the coil in the constant magnetic field.

[0018] In a feasible implementation, the number of the soft magnetic bodies is greater than or equal to 2.

[0019] In a feasible implementation, the soft magnet, the support sleeve, and the outer wall of the cruise missile seat are all rings with equal outer diameters, and the outer wall of the reluctance mover is gap-fitted with the inner wall of the bore.

[0020] In a feasible implementation, a buffering and limiting mechanism is provided at the launching end of the barrel, the cruise missile passes through the buffering and limiting mechanism, and the buffering and limiting mechanism is engaged with the magnetic resistance mover.

[0021] The embodiments of the present application provide a magnetoresistive mover and a magnetoresistive cruise missile launcher. The magnetoresistive mover is inserted into a barrel. The magnetoresistive mover has multiple soft magnets. The soft magnets are easily demagnetized magnetic bodies and are subjected to electromagnetic attraction in a constant magnetic field. Multiple coils are equidistantly arranged on the barrel. The coils are electrically connected to an external DC power supply. DC power is passed through to generate a constant magnetic field. Multiple sensors corresponding to the multiple coils are provided. When the sensor detects any of the soft magnets, the sensor controls the corresponding coil to be connected to the external DC power supply and controls the other energized coils to be disconnected from the external DC power supply, so that the soft magnets are subjected to electromagnetic attraction toward the launch end in the constant magnetic field of the coils, thereby causing the magnetoresistive mover to push the cruise missile to launch.

[0022] Through the design of multiple soft magnets, the sensor detects the soft magnets multiple times during a launch, and the corresponding coil generates a constant magnetic field multiple times, applying electromagnetic attraction to the reluctance mover multiple times toward the launch end. This allows the reluctance mover and the cruise missile to quickly reach the required launch speed, shortening the launch time, reducing the length of the launch device, and saving costs.

[0023] By designing the length and distribution distance of each component, the sum of the length of the coil and the spacing lengths of adjacent coils is equal to the spacing lengths of adjacent soft magnetic bodies, which is equal to the sum of the lengths of all soft magnetic bodies. This allows the magnetoresistive mover to be continuously subjected to electromagnetic attraction toward the launch end during the launch process, allowing the magnetoresistive mover to continuously accelerate and propel the cruise missile, avoiding multiple collisions and impacts on the cruise missile and reducing damage to the cruise missile. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is a structural schematic diagram of the reluctance mover provided by this application;

[0025] Figure 2 This is a schematic structural diagram of the magnetoresistive cruise missile launcher provided by this application;

[0026] Figure 3 It is a schematic diagram of the state at the first moment during the launch process;

[0027] Figure 4 This is a schematic diagram of the state at the second moment during the launch process;

[0028] Figure 5 This is a schematic diagram of the state at the third moment during the launch process;

[0029] Figure 6 This is a schematic diagram of the fourth moment of the launch process.

[0030] Description of reference numerals:

[0031] 100-bore tube; 200-coil; 300-sensor; 400-magnetic resistance mover;

[0032] 410-soft magnet; 420-support sleeve; 430-cruise bomb seat;

[0033] 411 - first pressure relief hole; 421 - second pressure relief hole; 431 - placement position; 432 - protection position; 433 - third pressure relief hole. DETAILED DESCRIPTION

[0034] In order to enable those skilled in the art to better understand the technical solutions in this application, the technical solutions in the embodiments of this application will be clearly and completely described below in conjunction with the drawings in the embodiments of this application. Obviously, the described embodiments are only part of the embodiments of this application, not all of the embodiments. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative efforts should fall within the scope of protection of this application.

[0035] Existing methods for launching cruise missiles primarily include slingshots, high-pressure airbags, incendiary devices, and hydraulic or pneumatic reciprocating pistons. However, these various methods suffer from several drawbacks, including low launch speeds, low energy, slow reload times, complex operations, government restrictions, high operational risks, large space requirements, high noise levels, and high detectability. These drawbacks make them unable to meet the demands for high frequency, multiple launches, high concealment, safety, convenience, and compact size required for specific scenarios.

[0036] Current electromagnetic launchers, such as progressively accelerating coil guns, achieve intermittent acceleration of the projectile by applying a single electrical current to the projectile through an electromagnet. During this intermittent period, the projectile is actually decelerated due to a series of factors such as residual magnetism, windage, and friction. This causes the projectile to cycle through acceleration, weak deceleration, and acceleration throughout the launch process within the barrel. This places high demands on the projectile's impact resistance and stability, especially when used for launching cruise missiles. Because there is no fixed rigid connection between the cruise missile and the accelerator, the continuous acceleration and deceleration cycle will cause significant impact and damage to the cruise missile.

[0037] Furthermore, the existing coil gun structure can only be energized once per coil, which results in a long launch time, an excessively long launch device, high cost, and inconvenience in use.

[0038] The present application realizes continuous acceleration of the reluctance mover by repeatedly energizing the coil, thereby enabling the cruise missile to safely accelerate to the required muzzle velocity in a very short time, shortening the launch time, and reducing the length of the launch device. The reluctance mover 400 continuously accelerates and pushes the cruise missile, avoiding multiple collisions and impacts on the cruise missile, and reducing damage to the cruise missile.

[0039] The specific structure of the magnetoresistive cruise missile launcher provided in this application is described in detail below with reference to the accompanying drawings.

[0040] Example 1:

[0041] Reference Figure 1As shown, an embodiment of the present application provides a magnetoresistive mover, which is applied to a magnetoresistive cruise missile launcher. The magnetoresistive mover is configured to move under electromagnetic attraction in a constant magnetic field, thereby accelerating the cruise missile until it is ejected at high speed. The magnetoresistive mover includes a plurality of soft magnets 410, a plurality of support members 420, and a cruise missile seat 430.

[0042] The soft magnet 410 can be an annular body. The soft magnet 410 is a magnetic body that is easily demagnetized. The material used for the soft magnet 410 is pure iron, steel, or other ferromagnetic materials that are easily demagnetized. The soft magnet 410 is subjected to electromagnetic attraction in a constant magnetic field. Multiple soft magnets 410 are equidistantly distributed. Multiple soft magnets 410 are all subjected to electromagnetic attraction in a constant magnetic field, and can provide power for the movement of the reluctance mover, thereby increasing the acceleration of the reluctance mover, shortening the time required for the cruise missile to reach the launch speed, and facilitating short-time and multiple launches. A first pressure relief hole 411 is provided on the soft magnet 410. The first pressure relief hole 411 can be a circular hole or a square hole, and a plurality of the first pressure relief holes 411 can be provided.

[0043] The support member 420 is a support sleeve. The material of the support sleeve is preferably an insulating material or a poorly conductive non-magnetic metal material. The purpose is to avoid the reverse repulsion of the accelerator due to the induced eddy current when the coil is energized or de-energized. The support sleeve can be an overall circular ring or one or more cylindrical structures. Several support members 420 are alternately distributed with multiple soft magnets 410. The number of support members 420 is one less than the number of soft magnets 410. Both ends of the axial direction of each support member 420 are fixedly connected to the soft magnet 410. A second pressure relief hole 421 is provided in the support member 420. The second pressure relief hole 421 can be a circular hole or a square hole, and several of them can be provided.

[0044] The cruise missile seat 430 may be a cylindrical structure that matches the cruise missile. The cruise missile seat 430 is connected to the outermost soft magnetic body 410. The cruise missile seat 430 is configured to connect to 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 may be a circular hole or a square hole, and a plurality of third pressure relief holes 433 may be provided.

[0045] To facilitate air flow, 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 extension direction of the axis is consistent with the movement direction of the magnetoresistive mover. When the magnetoresistive mover 400 is driven by electromagnetic attraction 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 magnetoresistive mover 400. At the same time, it can also eliminate the influence of the negative pressure generated at the tail end of the magnetoresistive mover 400 on the acceleration when it is accelerated at a high speed in the barrel, so that the magnetoresistive mover 400 and the cruise missile reach the launching speed faster, thereby shortening the time required for launching and improving the exit velocity.

[0046] The present application provides a reluctance mover. Multiple soft magnets 410 are disposed within the reluctance mover 400. Each of the multiple soft magnets 410 is subjected to electromagnetic attraction in a constant magnetic field, providing power for the reluctance mover to move. This increases the acceleration of the reluctance mover, shortens the time required for a cruise missile to reach launch speed, and facilitates short-term, multiple launches.

[0047] By setting a first pressure relief hole 411 on the soft magnetic body 410, a second pressure relief hole 421 in 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 extension direction of the axis is consistent with the movement direction of the magnetoresistive mover. When the magnetoresistive mover 400 is driven by electromagnetic attraction 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 magnetoresistive mover 400. At the same time, it can also eliminate the influence of the negative pressure generated at the tail end of the magnetoresistive mover 400 on the acceleration when it is extremely accelerated in the barrel, so that the magnetoresistive mover 400 and the cruise missile reach the launching speed faster, thereby shortening the time required for launching and improving the muzzle velocity.

[0048] Example 2:

[0049] Reference Figure 2 As shown, the embodiment of the present application provides a magnetoresistive cruise missile launcher, comprising a barrel 100, the magnetoresistive mover 400, a plurality of coils 200, and a plurality of sensors 300;

[0050] The barrel 100 is a tube with a certain strength. The barrel 100 has a filling end and a launching end, which are respectively located on both sides of the barrel 100 in the axial direction. The cruise missile and the magnetoresistive mover 400 are placed in the barrel 100 and are plugged into the barrel 100. During actual launch, the cruise missile and the magnetoresistive 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 magnetoresistive mover 400 are moved to the barrel 100 near the filling end, and then an external DC power supply is connected to prepare for launch.

[0051] Multiple coils 200 are equidistantly disposed on the bore tube 100. The coils 200 surround the circumference of the bore tube 100. The multiple coils 200 are electrically connected to an external DC power supply. When DC power is supplied to the coils 200, a constant magnetic field is generated. The sum of the length of a coil 200 and the spacing between adjacent coils 200 is equal to the spacing between adjacent soft magnetic bodies 410, which is equal to the sum of the lengths of all soft magnetic bodies 410.

[0052] The plurality of sensors 300 correspond to the plurality of coils 200 one by one, and the plurality of sensors 300 and the plurality of coils 200 are alternately distributed. The sensors 300 are configured to detect any soft magnetic object 410 and, upon detecting any soft magnetic object 410, control the corresponding coil 200 to be connected to the external DC power supply and control the other energized coils 200 to be disconnected from the external DC power supply.

[0053] The sensor 300 is used to detect the position of the soft magnetic body 410. The sensor may be a photoelectric sensor, and the sensing end of the sensor just passes through the barrel 100. The sensor 300 may also be other sensors, which will not be described in detail here.

[0054] The sensor 300 can control the corresponding coil 200 to be connected to the external DC power supply through other components, and control the other energized coils 200 to be disconnected from the external DC power supply; in one embodiment, the sensor 300 controls the corresponding coil 200 to be connected or disconnected with the external DC power supply through the first driving board, and the output end of the sensor 300 is connected to the control interface of the driving board, and the external DC power supply, the first driving board and the corresponding coil 200 are connected in series in sequence, so that the sensor 300 controls the corresponding coil 200 to be energized. Similarly, the sensor 300 can control the other coils 200 to be disconnected from the external DC power supply through the second driving board; the sensor 300 can also use other methods to control the corresponding coil 200 to be energized and the other coils 200 to be deenergized, which will not be repeated here.

[0055] When the sensor 300 detects any soft magnetic object 410 , the sensor 300 controls the corresponding coil 200 to be connected to the external DC power supply, and controls the other coils 200 to be disconnected from the external DC power supply.

[0056] The embodiment of the present application provides a magnetoresistive cruise missile launcher. A magnetoresistive mover 400 is inserted into a barrel 100. The magnetoresistive mover 400 has a plurality of soft magnetic bodies 410. The soft magnetic bodies are easily demagnetized and are subjected to electromagnetic attraction in a constant magnetic field. A plurality of coils 200 are equidistantly arranged on the barrel 100. The coils are electrically connected to an external DC power supply. DC power is passed through to generate a constant magnetic field. A plurality of sensors 300 are provided corresponding to the plurality of coils 200. When the sensor 300 detects any soft magnetic body 410, the sensor 300 controls the corresponding coil 200 to be connected to the external DC power supply and controls the other coils 200 to be disconnected from the external DC power supply. This causes the soft magnetic body 410 to be subjected to electromagnetic attraction toward the launch end in the magnetic field of the coil 200, thereby causing the magnetoresistive mover 400 to propel the cruise missile to launch.

[0057] By providing multiple soft magnetic bodies 410, during a launch process, the sensor 300 detects the soft magnetic body 410 multiple times, and the corresponding coil 200 generates a constant magnetic field multiple times, applying electromagnetic attraction to the reluctance mover 400 multiple times in the direction of the launch end, thereby enabling the reluctance mover 400 and the cruise missile to quickly reach the required launch speed, shortening the launch time, reducing the length of the launch device, and saving costs.

[0058] By designing the length and distribution distance of each component, the sum of the length of the coil 200 and the spacing lengths of adjacent coils 200 is equal to the spacing lengths of adjacent soft magnetic bodies 410, which is equal to the sum of the lengths of all soft magnetic bodies 410. This allows the reluctance mover 400 to be continuously subjected to electromagnetic attraction toward the launch end during the launch process, allowing the reluctance mover 400 to continuously accelerate and push the cruise missile, avoiding multiple collisions and impacts on the cruise missile and reducing damage to the cruise missile.

[0059] In some embodiments, the distance between the sensing end of the sensor 300 and the corresponding coil 200 facing the filling end is β, β is the trigger threshold, β ≥ 0, and the percentage of the trigger threshold to the length of the soft magnetic body 410 is 0-15%;

[0060] When the length of any soft magnetic body 410 inserted toward the transmitting end side and the filling end side of the coil 200 reaches the trigger threshold, it can be detected by the sensor 300 corresponding to the coil 200. When any sensor 300 detects any soft magnetic body 410, the sensor 300 controls the corresponding coil 200 to be connected to the external DC power supply, and controls the other energized coils 200 to be disconnected from the external DC power supply.

[0061] When the sensor 300 detects any soft magnetic object 410, the sensor 300 controls the corresponding coil 200 to connect to the external DC power supply, and controls the other energized coils 200 to disconnect from the external DC power supply. That is, at any time during the entire launch process, in this magnetic induction cruise missile launcher, only one coil 200 is energized to generate an alternating magnetic field.

[0062] In some embodiments, when the coil 200 is connected to an external DC power supply, the coil 200 generates a constant magnetic field, and the soft magnetic body 410 is subjected to an electromagnetic attraction force toward the coil 200 in the constant magnetic field, and is subjected to an electromagnetic attraction force toward the launch end, thereby pushing the cruise missile acceleration toward the launch end.

[0063] Reference Figure 2 and Figure 5 As shown, in some embodiments, the number of the soft magnetic bodies 410 is greater than or equal to 2, and in the optimal solution, the number of the magnetic induction bodies 410 is greater than or equal to 3 and less than or equal to 5;

[0064] When the number of soft magnetic bodies is greater than or equal to 3, due to the distribution characteristics of the magnetic field, the magnetoresistive cruise missile accelerator 5 will be in the maximum range of the magnetic force area during the full acceleration motion, which can enable the accelerator to obtain the greatest possible kinetic energy effect within the same acceleration length. Considering that increasing the number of soft magnetic bodies will also increase the weight and length of the cruise missile accelerator accordingly, which will have a negative impact on the rigidity of the structure, it is generally best to have the number of soft magnetic bodies less than or equal to 5.

[0065] When the number of soft magnets is greater than or equal to 3, the projectile can be kept in the maximum electromagnetic force range throughout the entire acceleration process, thereby achieving the optimal stroke speed ratio. Because the actual electromagnetic force exerted on the soft magnet varies greatly depending on the insertion depth of the coil relative to the soft magnet within the energized coil, Ansys analysis and testing results show that when the soft magnet and the energized coil are equal in length, the maximum electromagnetic force is exerted when the depth of the soft magnet inserted into the coil is within the range of 20% to 80%. Beyond this range, the electromagnetic force will drop sharply. When the number of soft magnets is greater than or equal to 3, the energized coil can be switched at an insertion depth of 20% to 80% throughout the entire acceleration process, thus ensuring the optimal acceleration effect.

[0066] Reference Figure 2 As shown, in some embodiments, the outer walls of the soft magnet 410, the support member 420 and the cruise bomb seat 430 are all rings with equal outer diameters, and the outer wall of the magnetoresistive mover 400 is gap-fitted with the inner wall of the barrel 10; and, during the entire launch process, the noise is very small due to the non-contact state of the magnetoresistive mover 400 and the coil.

[0067] Based on the above technical features, the working principle of the magnetoresistive cruise missile launcher provided by this application in actual application scenarios is as follows:

[0068] like Figure 3-6 As shown in the figure, the left end of the barrel 100 is the transmitting end, and the right end is the filling end. There are n coils 200, which are L1, L2, L3, L4...Ln from right to left. There are n sensors 300, which are T1, T2, T3, T4...Tn from right to left. The magnetoresistive mover 400 includes two soft magnets 410, which are C1 and C2 from right to left. A is a cruise missile, and the cruise missile A is located on the left side of the magnetoresistive mover 400.

[0069] Assuming the trigger threshold is 0, that is, the sensing end of the sensor 300 and the side of the corresponding coil 200 facing the filling end are located in the same plane, when the side of any soft magnetic object 410 facing the transmitting end is parallel to the side of the coil 200 facing the filling end, the soft magnetic object 410 is detected by the sensor 300 corresponding to the coil 200;

[0070] exist Figure 3 In the first moment shown, the left end of the soft magnet C2 is parallel to the right end of the coil L2. Sensor T2 in the soft magnet C2 detects this, and then sensor T2 controls the coil L2 to connect to the external DC power supply. The coil L2 generates a constant magnetic field, and the soft magnet C2 receives a leftward electromagnetic attraction in the constant magnetic field of the coil L2. The reluctance mover 400 pushes the cruise missile A to accelerate to the left.

[0071] When arriving Figure 4 At the second moment shown, the right end of the soft magnetic body C2 is parallel to the right end of the coil L2. Since the sum of the length of the coil 200 and the spacing between adjacent coils 200 is equal to the spacing between adjacent soft magnetic bodies 410, which is equal to the sum of the lengths of all soft magnetic bodies 410, the left end of the soft magnetic body C1 is exactly parallel to the right end of the coil L1. The soft magnetic body C1 is detected by the sensor T1. The sensor T1 controls the coil L1 to connect to the external DC power supply and the control coil L2 to disconnect from the external DC power supply. The coil L1 generates a constant magnetic field. The soft magnetic body C1 receives a leftward electromagnetic attraction in the constant magnetic field of the coil L1, and the reluctance mover 400 continues to push the cruise missile A to accelerate to the left.

[0072] When arriving Figure 5At the third moment shown, the right end of the soft magnetic body C1 is parallel to the right end of the coil L1. Since the sum of the length of the coil 200 and the spacing between adjacent coils 200 is equal to the spacing between adjacent soft magnetic bodies 410, which is equal to the sum of the lengths of all soft magnetic bodies 410, the left end of the soft magnetic body C2 is parallel to the right end of the opposite coil L3. The soft magnetic body C2 is detected by the sensor T3. The sensor T3 controls the coil L3 to connect to the external DC power supply and disconnects the control coil L1 from the external DC power supply. The coil L3 generates a constant magnetic field. The soft magnetic body C2 receives a leftward electromagnetic attraction in the constant magnetic field of the coil L3, and the reluctance mover 400 continues to push the cruise missile A to accelerate to the left.

[0073] When arriving Figure 6 At the fourth moment shown, the right end of the soft magnetic body C2 is parallel to the right end of the opposite coil L3. Since the sum of the length of the coil 200 and the spacing lengths of adjacent coils 200 is equal to the spacing lengths of adjacent soft magnetic bodies 410, which is equal to the sum of the lengths of all soft magnetic bodies 410, the left end of the soft magnetic body C1 is parallel to the right end of the opposite coil L2. The soft magnetic body C1 is detected by the sensor T2. The sensor T2 controls the coil L2 to connect to the external DC power supply and the control coil L3 to disconnect from the external DC power supply. The coil L2 generates a constant magnetic field. The soft magnetic body C1 receives a leftward electromagnetic attraction in the constant magnetic field of the coil L2, and the reluctance mover 400 continues to push the cruise missile A to accelerate to the left.

[0074] The cycle is repeated multiple times in sequence, so that the reluctance mover 5 and the cruise missile reach the required launch speed and the launch operation is completed. During the launch process, the coil is alternately switched on and off to ensure that the reluctance mover 5 is stably subjected to the electromagnetic attraction toward the launch end, so that it always accelerates and pushes the cruise missile, so that the cruise missile is always subjected to nearly equal pressure in the barrel 100, which greatly improves the acceleration environment of the cruise missile and reduces the failure rate of the cruise missile.

[0075] It is easy to understand that those skilled in the art can combine, split, reorganize, etc. the embodiments of the present application based on the several embodiments provided in the present application to obtain other embodiments, and these embodiments do not exceed the scope of protection of the present application.

[0076] The above specific implementation methods further explain in detail the purpose, technical solutions and beneficial effects of the embodiments of the present application. It should be understood that the above are only specific implementation methods of the embodiments of the present application and are not intended to limit the scope of protection 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 should be included in the scope of protection of the embodiments of the present application.

Claims

1. A reluctance mover configured to move in a magnetic field under electromagnetic attraction to propel a loitering missile at high speed, characterized by: The reluctance mover comprises: A plurality of soft magnetic bodies (410), wherein the plurality of soft magnetic bodies (410) are distributed at equal intervals, wherein a first pressure relief hole (411) is provided on the soft magnetic body (410), wherein the soft magnetic body (410) is a magnetic body that is easily demagnetized, wherein the soft magnetic body (410) is subjected to electromagnetic attraction in a constant magnetic field, and wherein the soft magnetic body (410) is configured to be subjected to electromagnetic attraction in the magnetic field, thereby driving the reluctance type mover to move; A plurality of support members (420), wherein the plurality of support members (420) and the plurality of soft magnetic bodies (410) are alternately distributed, both ends of the axis direction of each support member (420) are fixedly connected to the soft magnetic body (410), and a second pressure relief hole (421) is provided in the support member (420); A cruise missile seat (430) is connected to the outermost soft magnetic body (410), a third pressure relief hole (433) is provided on the cruise missile seat (430), and the cruise missile seat (430) is configured to connect to a cruise missile.

2. The reluctance mover according to claim 1, characterized in that: A placement position (431) is provided on the side of the cruise missile seat (430) facing away from the soft magnetic body (410), the placement position (431) is connected to the third pressure relief hole (433), and the cruise missile is inserted into the placement position (431).

3. The reluctance mover according to claim 2, characterized in that: The side of the cruise bomb seat (430) facing the soft magnetic body (410) is provided with a protection position (432); 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 connected in sequence.

4. A magnetoresistive loitering missile launcher, characterized in that: include: A barrel (100), the barrel (100) having a filling end and a launching end, the filling end and the launching end being respectively located on both sides of the barrel (100) in an axial direction, and the loitering missile being placed in the barrel (100); The reluctance mover (400) according to any one of claims 1 to 3, wherein the reluctance mover (400) is plugged into the bore tube (100); A plurality of coils (200), wherein the plurality of coils (200) are equidistantly arranged on the bore tube (100), the coils (200) surround the circumference of the bore tube (100), the plurality of coils (200) are electrically connected to an external DC power supply, the coils (200) are supplied with DC power to generate a constant magnetic field, and the sum of the length of the coils (200) and the spacing lengths between adjacent coils (200) is equal to the spacing lengths between adjacent soft magnetic bodies (410), which is equal to the sum of the lengths of all the soft magnetic bodies (410); A plurality of sensors (300), wherein the plurality of sensors (300) correspond to the plurality of coils (200) one by one, and the plurality of sensors (300) and the plurality of coils (200) are alternately distributed, and the sensors (300) are configured to detect any of the soft magnetic bodies (410), and when any of the soft magnetic bodies (410) is detected, the corresponding coils (200) are controlled to be connected to an external DC power supply, and the other energized coils (200) are controlled to be disconnected from the external DC power supply.

5. The magnetoresistive loitering missile launcher according to claim 4, characterized in that: The distance between the sensing end of the sensor (300) and the corresponding side of the coil (200) facing the filling end is a trigger threshold, and the percentage of the trigger threshold to the length of the soft magnetic body (410) is 0 to 15%; When the length of any of the soft magnetic bodies (410) inserted toward the transmitting end side into the filling end side of the coil (200) reaches a trigger threshold, it can be detected by the sensor (300) corresponding to the coil (200). When any of the sensors (300) detects any of the soft magnetic bodies (410), the sensor (300) controls the corresponding coil (200) to be connected to an external DC power supply, and controls the other energized coils (200) to be disconnected from the external DC power supply.

6. The magnetoresistive loitering missile launcher according to claim 4, characterized in that: When the coil (200) is connected to an external DC power supply, the coil (200) generates a constant magnetic field, and the soft magnetic body (410) is subjected to an electromagnetic attraction in the direction of the coil (200) in the constant magnetic field.

7. The magnetoresistive loitering missile launcher according to claim 4, characterized in that: The number of the soft magnetic bodies (410) is greater than or equal to 2.

8. The magnetoresistive loitering missile launcher according to claim 4, characterized in that: The outer walls of the soft magnet (410), the support member (420) and the cruise bomb seat (430) are all ring-shaped with equal outer diameters, and the outer wall of the reluctance mover (400) is gap-matched with the inner wall of the bore tube (100).

9. The magnetoresistive loitering missile launcher according to claim 4, characterized in that: The launch end of the barrel (100) is provided with a buffering and limiting mechanism, the cruise missile passes through the buffering and limiting mechanism, and the buffering and limiting mechanism is engaged with the magnetic resistance mover (400).

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