An open magnetic resistance cruise missile launcher

Abstract

The present application provides an open reluctance cruise missile launcher, comprising a mounting frame, an electromagnet group disposed in the mounting frame, and a reluctance mover disposed in the electromagnet group. The launcher adopts the principle of electromagnetic induction for launch, and the cruise missile is pushed by the reluctance mover, which is disposed in the electromagnet group, which is disposed in the mounting frame. The mounting frame is an open structure, and is provided with multiple external air channels. The electromagnet group is an open structure, and is composed of multiple electromagnets and a number of guide rods. Internal air channels are formed between adjacent electromagnets. The air inside and outside the launcher can be quickly circulated through the multiple internal air channels and the multiple external air channels, which can effectively reduce the air resistance encountered by the cruise missile during launch, and can obtain the required muzzle velocity in a very short time. In addition, the noise during launch is greatly reduced, and the concealment is improved.

Description

Technical Field

[0001] The present application belongs to the field of electromagnetic catapult technology, and in particular relates to an open magnetic resistance cruise missile launch device. 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] The launch devices currently used for cruise missiles all fire from the barrel. Because the barrel is relatively narrow and air circulation is inconvenient, the air in the head space of the cruise missile is instantly compressed during the acceleration process in the barrel, causing obstructive pressure on the cruise missile. The air in the tail space of the cruise missile is instantly vacuumed, causing obstructive suction on the cruise missile, making it difficult for the cruise missile to obtain the required exit velocity in a short period of time. Summary of the Invention

[0004] An embodiment of the present application provides an open reluctance cruise missile launcher, which adopts the principle of electromagnetic induction for launch. The cruise missile is propelled by a reluctance mover and ejected from an electromagnetic cylinder composed of an electromagnet and a guide rod. The electromagnetic cylinder has an open structure, which is conducive to air circulation inside and outside the cylinder, and can effectively reduce the air resistance encountered by the cruise missile during launch, and can obtain the required muzzle velocity in a very short time. This solves the problem of existing barrel-type launchers, in which air circulation in the barrel is inconvenient, the cruise missile will encounter great air resistance during launch, and it is difficult to obtain the required muzzle velocity in a short time.

[0005] The embodiment of the present application provides an open-type magnetoresistive cruise missile launcher, comprising a mounting frame, an electromagnet group disposed in the mounting frame, and a magnetoresistive mover disposed in the electromagnet group;

[0006] The mounting frame includes a frame body and a plurality of acceleration sensors arranged in the frame body, a fixed position is provided in the frame body, the fixed position has a relative filling end and a launching end along its length direction, a plurality of acceleration sensors are equidistantly arranged in the fixed position along the length direction of the fixed position, the electromagnet group is arranged in the fixed position, the electromagnet group includes a plurality of accelerating electromagnets and a plurality of guide rods for fixing the plurality of accelerating electromagnets, the accelerating electromagnets are annular electromagnets, a plurality of accelerating electromagnets are equidistantly distributed along the length direction of the fixed position, and the axes of the plurality of accelerating electromagnets are located in the same straight line, a plurality of guide rods are plugged into all the accelerating electromagnets, and are embedded in the accelerating electromagnets, so that the plurality of accelerating electromagnets constitute an accelerating electromagnetic cylinder, the reluctance type mover is plugged into the accelerating electromagnetic cylinder, the reluctance type mover includes a soft magnet, the soft magnet is located in the electromagnet group, and the launching end of the soft magnet is connected to the cruise missile;

[0007] The plurality of accelerating electromagnets correspond one-to-one to the plurality of acceleration sensors. The acceleration sensors are configured to detect the soft magnetic bodies and, upon detecting any of the magnetic induction bodies, control the corresponding accelerating electromagnets to be connected to an external DC power supply and control the other energized accelerating electromagnets to be disconnected from the external AC power supply.

[0008] In a feasible implementation, the mounting bracket further includes a plurality of deceleration sensors, which are equidistantly arranged in the fixing position along the length direction of the fixing position, a plurality of the deceleration sensors are arranged on the side of the fixing position close to the emission end, and a plurality of the acceleration sensors are arranged on the side of the fixing position close to the filling end;

[0009] The electromagnet group further includes a plurality of deceleration electromagnets, each of which is an annular electromagnet. The plurality of deceleration electromagnets are equidistantly distributed along the length direction of the fixed position. The plurality of guide rods are plugged into all of the deceleration electromagnets and embedded in the deceleration electromagnets, so that the plurality of deceleration electromagnets constitute a deceleration electromagnetic cylinder. The deceleration electromagnetic cylinder is located on the side of the plurality of guide rods close to the emission end, and the acceleration electromagnetic cylinder is located on the side of the plurality of guide rods close to the filling end.

[0010] The plurality of deceleration electromagnets correspond one to one with the plurality of deceleration sensors, and the deceleration sensors are configured to detect the soft magnetic body, and when the magnetic induction body is detected, the corresponding deceleration electromagnet is controlled to be connected to the external AC power supply, and the other energized deceleration electromagnets are controlled to be disconnected from the external AC power supply.

[0011] In a feasible implementation, the mounting frame further includes a mounting base and a plurality of hoops provided on the mounting base, and the mounting base and the plurality of hoops constitute the frame body;

[0012] The mounting base is provided with the fixing position, and the plurality of hoops are arranged on the side of the mounting base provided with the fixing position. The plurality of hoops correspond one-to-one to the plurality of electromagnets, and the plurality of hoops and the mounting base clamp the corresponding electromagnets so that the electromagnet group is fixed in the fixing position.

[0013] In a feasible implementation, the electromagnet group further includes a plurality of isolation blocks;

[0014] A plurality of isolation blocks are provided between adjacent electromagnets. The length of the isolation blocks is adjustable, and both ends of the isolation blocks in the length direction are fixedly connected to the opposite surfaces of two adjacent electromagnets respectively.

[0015] In a feasible implementation, the electromagnet group further includes two connecting rings;

[0016] The two connecting rings are respectively arranged at the two ends of the guide rod, and the guide rods connect the two connecting rings, the multiple electromagnets and the multiple isolation blocks into one.

[0017] In a feasible implementation, the reluctance type mover further includes a sliding bearing;

[0018] The sliding bearing is arranged on the outer wall of the soft magnetic body, and the outer wall of the sliding bearing is slidably connected with the inner wall of the electromagnet, and the two are clearance-matched.

[0019] In a feasible implementation, the reluctance type mover further includes a loitering missile mounting seat;

[0020] The cruise missile mounting seat is arranged on the side of the soft magnetic body facing the launch end, and a cruise missile placement position is provided on the side of the cruise missile mounting seat facing the launch end, and the cruise missile is plugged into the cruise missile placement position.

[0021] In a feasible implementation, a protection position is provided on the side of the cruise missile mounting seat facing the filling end, and the soft magnetic body completely seals the protection position to form a protection cavity.

[0022] In a feasible implementation, the cruise missile mounting seat is provided with a first pressure relief hole, and the soft magnetic body is provided with a second pressure relief hole, and the first pressure relief hole and the second pressure relief hole are located on the same axis;

[0023] The cruise missile placement position, the first pressure relief hole, the protection position and the second pressure relief hole are connected in sequence.

[0024] An open reluctance cruise missile launcher provided in an embodiment of the present application adopts the principle of electromagnetic induction for launch. The cruise missile is propelled by a reluctance mover, which is arranged in an electromagnet group. The electromagnet group is arranged in a mounting frame. The mounting frame is an open structure. A plurality of external air channels are provided on the mounting frame. The electromagnet group is an open structure. The electromagnet group is composed of a plurality of electromagnets and a plurality of guide rods. An internal air channel is formed between adjacent electromagnets. The air inside and outside the launcher can be quickly circulated through the plurality of internal air channels and the plurality of external air channels, which can effectively reduce the air resistance encountered during the launch of the cruise missile and obtain the required muzzle velocity in a very short time. In addition, the noise during launch is greatly reduced, the concealment is improved, and the problem of the existing barrel-type launcher, that the air circulation in the barrel is inconvenient, the cruise missile will be encountered with great air resistance during launch, and it is difficult to obtain the required muzzle velocity in a short time, is solved. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 This is a schematic structural diagram of the open-type magnetoresistive cruise missile launcher provided by the present application;

[0026] Figure 2 yes Figure 1 Side view of

[0027] Figure 3 1. It is a structural diagram of the mounting frame;

[0028] Figure 4 It is a structural diagram of the electromagnet group;

[0029] Figure 5 yes Figure 4 sectional view of

[0030] Figure 6 It is a structural diagram of the magnetoresistive mover;

[0031] Figure 7 yes Figure 6 sectional view of

[0032] Figure 8 It is a structural diagram of the cruise missile in the launch state.

[0033] Description of reference numerals:

[0034] 100-electromagnet assembly; 200-reluctance type mover; 300-mounting frame;

[0035] 110 - acceleration electromagnet; 120 - guide rod; 130 - deceleration electromagnet; 140 - isolation block; 150 - connecting ring; 210 - soft magnet; 220 - sliding bearing; 230 - cruise missile mounting base; 310 - acceleration sensor; 320 - deceleration sensor; 330 - mounting base; 340 - clamp;

[0036] 211-Second pressure relief hole; 231-Cruise missile placement position; 232-Protection position; 233-First pressure relief hole. DETAILED DESCRIPTION

[0037] 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.

[0038] Existing cruise missile launchers all fire cruise missiles from within the barrel. This creates significant air resistance during launch, making it difficult to achieve the desired muzzle velocity in a short period of time. Furthermore, the launch produces a high level of noise, resulting in poor concealment. The open reluctance cruise missile launcher provided in this application features an open electromagnetic cylinder, facilitating air circulation inside and outside the cylinder. This effectively reduces the air resistance encountered during launch, enabling the desired muzzle velocity to be achieved in a very short period of time. Furthermore, this significantly reduces noise during launch, improving concealment.

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

[0040] Reference Figure 1-7 As shown, the embodiment of the present application provides an open reluctance cruise missile launcher, comprising a mounting frame 300, an electromagnet group 100 disposed in the mounting frame 300, and a reluctance mover 200 disposed in the electromagnet group 100;

[0041] The mounting frame 300 is an open cylindrical structure. It includes a frame body and a plurality of acceleration sensors 310 disposed within the frame body. The frame body is provided with a plurality of external air passages through which air can quickly circulate between the frame body and the outside. The frame body is provided with a fixed position, which is a cylindrical position having an opposed filling end and a transmitting end along its length. The plurality of acceleration sensors 310 are equidistantly disposed within the fixed position along its length.

[0042] The electromagnet group 100 is an open-ended cylindrical structure. The electromagnet group 100 is arranged in a fixed position. The electromagnet group 100 includes a plurality of accelerating electromagnets 110 and a plurality of guide rods 120 for fixing the plurality of accelerating electromagnets 110. The accelerating electromagnets 110 are annular electromagnets. The plurality of accelerating electromagnets 110 are equidistantly distributed along the length direction of the fixed position, and the axes of the plurality of accelerating electromagnets 110 are located on the same straight line. The plurality of guide rods 120 are connected to all of the accelerating electromagnets 110 to form an accelerating electromagnetic cylinder. A first inner air channel is formed between adjacent accelerating electromagnets 110. Air inside and outside the accelerating electromagnetic cylinder can be quickly circulated through the plurality of first inner air channels. The plurality of accelerating electromagnets 110 are respectively electrically connected to an external DC power supply. DC power is supplied to the accelerating electromagnets 110 to generate a constant magnetic field.

[0043] The reluctance type mover 200 is plugged into the accelerating electromagnetic cylinder, and the two are gap-fitted. The reluctance type mover 200 includes a soft magnetic body 210. There are multiple magnetic induction bodies 210, and the multiple magnetic induction bodies 210 are evenly distributed. The soft magnetic body 210 is located in the electromagnet group 100. The soft magnetic body 210 is a magnetic body that is easily demagnetized. The material used for the soft magnetic body 210 is pure iron, steel or other ferromagnetic materials that are easily demagnetized. The soft magnetic body 210 is subjected to electromagnetic attraction in a constant magnetic field. The soft magnetic body 210 is subjected to electromagnetic attraction in a constant magnetic field, thereby driving the magnetic induction type mover 200 to move.

[0044] The plurality of accelerating electromagnets 110 correspond one to one with the plurality of acceleration sensors 310. The acceleration sensor 310 is configured to detect the soft magnetic body 210 and, upon detecting any magnetic induction body 210, control the corresponding accelerating electromagnet 110 to be connected to the external AC power supply and control the other energized accelerating electromagnets 110 to be disconnected from the external AC power supply.

[0045] The acceleration sensor 310 is used to detect the position of the soft magnetic body 210. The sensor may be a photoelectric sensor, and the sensing end of the sensor just passes through the barrel 100. The acceleration sensor 310 may also be other sensors, which will not be described in detail here.

[0046] The acceleration sensor 310 can control the connection or disconnection of the acceleration electromagnet 110 with the external DC power supply through other components. In one embodiment, the acceleration sensor 310 controls the connection or disconnection of the corresponding acceleration electromagnet 110 with the external DC power supply through the first driver board. The output end of the acceleration sensor 310 is connected to the control interface of the driver board. The external DC power supply, the first driver board, and the corresponding acceleration electromagnet 110 are connected in series in sequence, thereby enabling the acceleration sensor 310 to control the power on and off of the corresponding acceleration electromagnet 110. Similarly, the sensor 310 can control the disconnection of other acceleration electromagnets 110 from the external AC power supply through the second driver board. The acceleration sensor 310 can also use other methods to control the power on and off of the corresponding acceleration electromagnet 110, which will not be repeated here.

[0047] The distance between the sensing end of the acceleration sensor 310 and the corresponding acceleration electromagnet 110 facing the filling end is β, where β is the acceleration trigger threshold, β≥0, and the percentage of the acceleration trigger threshold to the length of the magnetic induction body 210 is 0-15%;

[0048] When the distance between the side of any magnetic induction body 210 facing the launch end and the side of the accelerating electromagnet 110 facing the filling end reaches the acceleration trigger threshold, it can be detected by the acceleration sensor 310 corresponding to the accelerating electromagnet 110. When any acceleration sensor 310 detects any magnetic induction body 210, the acceleration sensor 310 controls the corresponding accelerating electromagnet 110 to be connected to the external AC power supply, and controls the other energized accelerating electromagnets 110 to be disconnected from the external AC power supply. The corresponding accelerating electromagnet 110 generates an alternating magnetic field. The magnetic induction body 210 is attracted by the accelerating electromagnet 110 in the alternating magnetic field and is subjected to a force toward the launch end, thereby pushing the cruise missile to accelerate toward the launch end.

[0049] Multiple magnetic induction bodies 210 are evenly distributed, and multiple accelerating electromagnets 110 are equidistantly distributed along the fixed length direction. The sum of the length of each accelerating electromagnet 110 and the spacing length between adjacent accelerating electromagnets 110 is equal to the spacing length between adjacent magnetic induction bodies 210, which is equal to the sum of the lengths of all magnetic induction bodies 210. This enables all accelerating electromagnets 110 to be alternately switched on with power at zero intervals, so that during the launch process, the reluctance mover is continuously subjected to electromagnetic attraction toward the launch end, causing the reluctance mover to continuously accelerate and push the cruise missile, avoiding multiple collisions and impacts on the cruise missile, and reducing damage to the cruise missile.

[0050] An open reluctance cruise missile launcher provided in an embodiment of the present application adopts the principle of electromagnetic induction for launch. The cruise missile is pushed by a reluctance mover 200, which is arranged in an electromagnet group 100. The electromagnet group 100 is arranged in a mounting frame 300. The mounting frame 300 is an open structure. A plurality of external air channels are provided on the mounting frame 300. The electromagnet group 100 is an open structure. The electromagnet group 100 is composed of a plurality of electromagnets and a plurality of guide rods. An internal air channel is formed between adjacent electromagnets. The air inside and outside the launcher can be quickly circulated through the plurality of internal air channels and the plurality of external air channels, which can effectively reduce the air resistance encountered during the launch of the cruise missile and obtain the required muzzle velocity in a very short time. In addition, the noise during launch is greatly reduced, the concealment is improved, and the problem of the existing barrel-type launcher, that the air circulation in the barrel is inconvenient, the cruise missile will encounter great air resistance during launch, and it is difficult to obtain the required muzzle velocity in a short time is solved.

[0051] Reference Figure 1-7As shown, in some embodiments, the mounting bracket 300 further includes a plurality of deceleration sensors 320, which are equidistantly arranged in the fixed position along the length direction of the fixed position. The plurality of deceleration sensors 320 are all arranged on the fixed position near the transmitting end, and the plurality of acceleration sensors 310 are all arranged on the fixed position near the filling end.

[0052] The electromagnet group 100 also includes a plurality of deceleration electromagnets 130, which are annular electromagnets. The plurality of deceleration electromagnets 130 are equidistantly distributed along the length direction of the fixed position, and a second inner air channel is formed between adjacent deceleration electromagnets 130. A plurality of guide rods 120 are connected to all of the deceleration electromagnets 130 to form a deceleration electromagnetic cylinder. The reluctance type mover 200 is plugged into the deceleration electromagnetic cylinder. The deceleration electromagnetic cylinder is located on the side of the plurality of guide rods 120 close to the emission end, and the acceleration electromagnetic cylinder is located on the side of the plurality of guide rods 120 close to the filling end. The plurality of deceleration electromagnets 130 are respectively electrically connected to an external DC power supply, and DC power is passed through the deceleration electromagnets 130 to generate a constant magnetic field.

[0053] The plurality of deceleration electromagnets 130 correspond one to one with the plurality of deceleration sensors 320. The deceleration sensor 320 is configured to detect the soft magnetic body 210 and, upon detecting any magnetic induction body 210, control the corresponding deceleration electromagnet 130 to be connected to the external DC power supply and control the other energized deceleration electromagnets 130 to be disconnected from the external AC power supply.

[0054] The multiple deceleration electromagnets 130 have the same structure, principle, fixing method and arrangement as the multiple acceleration electromagnets 110. The multiple deceleration sensors 320 have the same structure and principle as the multiple acceleration sensors 310, but their positions relative to the electromagnets are different. The multiple acceleration electromagnets 110 and the multiple acceleration sensors 310 are used to accelerate the magnetoresistive mover 200 in the early stage of launch so that the magnetoresistive mover 200 pushes the cruise missile to be launched. The multiple deceleration electromagnets 130 and the multiple deceleration sensors 320 are used to decelerate the magnetoresistive mover 200 that has been separated from the cruise missile and is moving at high speed in the later stage of launch to prevent the magnetoresistive mover 200 from being launched with the cruise missile.

[0055] The distance between the sensing end of the deceleration sensor 320 and the corresponding deceleration electromagnet 130 facing the transmitting end is α, where α is the deceleration trigger threshold, and α is equal to β;

[0056] When the length of the deceleration electromagnet 130 extending toward the transmitting end of any magnetic induction body 210 reaches the deceleration trigger threshold, it can be detected by the deceleration sensor 320 corresponding to the deceleration electromagnet 130. When any deceleration sensor 320 detects any magnetic induction body 210, the deceleration sensor 320 controls the corresponding deceleration electromagnet 130 to be connected to the external AC power supply, and controls the other energized deceleration electromagnets 130 to be disconnected from the external AC power supply. The corresponding deceleration electromagnet 130 generates an alternating magnetic field. The magnetic induction body 210 is attracted by the corresponding deceleration electromagnet 130 in the alternating magnetic field and is subjected to a force toward the filling end, thereby decelerating the magnetic induction type mover 200 moving toward the transmitting end. By setting multiple deceleration electromagnets 130, the speed of the magnetic induction type mover 200 is reduced to zero or to a predetermined speed, thereby preventing the magnetic induction type mover 200 from being ejected.

[0057] Reference Figure 3 As shown, in some embodiments, the frame includes a mounting base 330 and a plurality of clamps 340 disposed on the mounting base 330;

[0058] A fixed position is set on the upper surface of the mounting base 330, and the fixed position can be a semicircular mounting position. The clamp 340 is a semicircular shape matching the fixed position. Multiple clamps 340 are set on the side of the mounting base 330 with the fixed position. One end of the clamp 340 is hinged to one side of the mounting base 330, and the other end is clamped to the other side of the mounting base 330, thereby forming an open cylindrical structure. An external air channel is formed between adjacent clamps 340. Multiple clamps 340 correspond to multiple electromagnets one by one, and multiple external air channels correspond to multiple internal air channels. Multiple clamps 340 and the mounting base 330 clamp the corresponding electromagnets so that the electromagnet group 100 is fixed in the fixed position.

[0059] Reference Figure 1 As shown, in some embodiments, the electromagnet assembly 100 further includes a plurality of isolation blocks 140;

[0060] A plurality of isolation blocks 140 are provided between adjacent electromagnets. The isolation blocks 140 are cylindrical and have adjustable lengths. Both ends of the isolation blocks 140 in the length direction are fixedly connected to the opposite surfaces of two adjacent electromagnets.

[0061] Reference Figure 4 and Figure 5 As shown, in some embodiments, the electromagnet assembly 100 further includes two connecting rings 150;

[0062] The side wall of the electromagnet is provided with a plurality of grooves, and a plurality of guide rods 20 pass through the plurality of grooves, and the inner wall of the inner end of the guide rod 20 is located in the same plane as the inner wall of the electromagnet, and a plurality of isolation blocks 140 are provided between two adjacent electromagnets. Two connecting rings 150 are respectively provided at both ends of the guide rod 120, and a plurality of connecting holes are provided on the connecting ring 150. The guide rod 120 is plugged into the connecting holes. Nuts are provided at both ends of the guide rod 120. Tighten the nuts so that the nuts clamp the two connecting rings 150, the plurality of electromagnets and the plurality of isolation blocks 140, so that the various components of the electromagnet group 100 can be connected as one.

[0063] Reference Figure 6 and Figure 7 As shown, in some embodiments, the reluctance mover 200 further includes a sliding bearing 220, which is disposed on the outer wall of the soft magnetic body 210. The outer wall of the sliding bearing 220 is slidably connected to the inner wall of the electromagnet or the outer wall of the guide rod 120, and the two are clearance-matched to ensure that the reluctance mover 200 reliably follows the direction of the guide rod 120 when accelerating.

[0064] The sliding bearing 25 is not limited to being disposed only on the soft magnetic body 210 , and can be disposed at any position on the reluctance mover 200 close to the guide rod or the electromagnet as required.

[0065] In some embodiments, the reluctance mover 200 further includes a cruise missile mounting seat 230;

[0066] The cruise missile mounting seat 230 is arranged on the side of the soft magnetic body 210 facing the launch end. The cruise missile mounting seat 230 is provided with a cruise missile placement position 231 on the side facing the launch end. The cruise missile is plugged into the cruise missile placement position 231. For cruise missiles with electromagnetic shielding requirements, the placement area of the cruise missile mounting seat 230 can use electromagnetic shielding materials, such as aluminum, copper, stainless steel or other materials or alloy materials.

[0067] In some embodiments, a protection portion 232 is provided on the side of the cruise missile mounting seat 230 facing the filling end, and the soft magnetic body 210 completely seals the protection portion 232 to form a protection cavity;

[0068] The protection position 432 can also be 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.

[0069] In some embodiments, the cruise missile mounting seat 230 is provided with a first pressure relief hole 233. When the cruise missile is placed in the cruise missile mounting seat 230, the cruise missile does not block the first pressure relief hole 233. The soft magnetic body 210 is provided with a second pressure relief hole 211. The first pressure relief hole 233 and the second pressure relief hole 211 are located on the same axis.

[0070] The cruise missile placement position 231, the first pressure relief hole 233, the protection position 232 and the second pressure relief hole 211 are connected in sequence, thereby releasing the wind pressure resistance generated by the high-speed operation of the magnetoresistive mover 200, thereby reducing the influence of wind resistance on the speed of the magnetoresistive mover 200. At the same time, it can also eliminate the influence of the negative pressure generated at the tail end of the magnetoresistive mover 200 on the acceleration when the magnetoresistive mover 200 is accelerated at a high speed in the barrel, so that the magnetoresistive mover 200 and the cruise missile reach the launch speed faster, thereby shortening the time required for launch and improving the exit speed.

[0071] Based on the above technical features, the working principle of the open reluctance cruise missile launcher provided by this application in actual application scenarios is as follows:

[0072] Reference Figure 8 As shown, Figure 8 This is a schematic diagram of the structure of a cruise missile in the launch state. In the figure, A is a cruise missile. The left end of the mounting frame 300 is the launch end, and the right end is the filling end. The left side of the electromagnet group 100 is the deceleration electromagnetic cylinder, and the right side is the acceleration electromagnetic cylinder. The deceleration electromagnetic cylinder and the acceleration electromagnetic cylinder are an integrated structure. The reluctance type mover 200 is set in the electromagnet group 100 and can move left and right.

[0073] When the reluctance mover 200 moves from right to left in the accelerating electromagnetic cylinder, if any acceleration sensor 310 detects the soft magnetic element 210, the acceleration sensor 310 controls the corresponding accelerating electromagnet 110 to connect to the external DC power supply and controls the other energized accelerating electromagnets 110 to disconnect from the external AC power supply. The corresponding accelerating electromagnet 110 generates a constant magnetic field, and the soft magnetic element 210 is subjected to a force toward the launch end in the constant magnetic field, thereby causing the reluctance mover 200 to push the cruise missile and accelerate it toward the launch end.

[0074] Because the multiple magnetic induction bodies 210 are evenly distributed, the multiple accelerating electromagnets 110 are equidistantly distributed along the fixed length direction, and the sum of the length of the accelerating electromagnet 110 and the length of the spacing between adjacent accelerating electromagnets 110 is equal to the length of the spacing between adjacent magnetic induction bodies 210, which is equal to the sum of the lengths of all magnetic induction bodies 210. This allows all accelerating electromagnets 110 to be alternately switched on with zero intervals, so that the magnetic induction mover 200 is always subjected to a leftward electromagnetic attraction in the accelerating electromagnetic cylinder and is always in accelerated motion.

[0075] By setting the current intensity or the number of accelerating electromagnets 110, when the cruise missile reaches the launch speed, the reluctance type mover 200 just passes the leftmost accelerating electromagnet 110 and enters the deceleration electromagnetic cylinder;

[0076] When the reluctance type mover 200 moves in the deceleration electromagnetic cylinder, when any deceleration sensor 320 detects the soft magnetic material 210, the deceleration sensor 320 controls the corresponding deceleration electromagnet 130 to connect to the external DC power supply, and controls the energized deceleration electromagnet 130 to disconnect from the external AC power supply. The corresponding deceleration electromagnet 130 generates a constant magnetic field. After the soft magnetic material 210 moves toward the emission end due to inertia, it is subjected to a force toward the filling end in the constant magnetic field, thereby decelerating the reluctance type mover 200.

[0077] By setting the current intensity or the number of deceleration electromagnets 130 , after the reluctance mover 200 passes through all the deceleration electromagnets 130 , the speed of the reluctance mover 200 is reduced to zero or a predetermined speed, thereby preventing the reluctance mover 200 from being ejected.

[0078] 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.

[0079] 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. An open-type magnetoresistive loitering missile launcher, characterized by: It comprises a mounting frame (300), an electromagnet group (100) arranged in the mounting frame (300), and a reluctance type mover (200) arranged in the electromagnet group (100); The mounting frame (300) comprises a frame body and a plurality of acceleration sensors (310) arranged in the frame body, the frame body is provided with a plurality of external air channels, a fixing position is provided in the frame body, the fixing position has a relative filling end and a transmitting end along its length direction, and the plurality of acceleration sensors (310) are equidistantly arranged in the fixing position along the length direction of the fixing position; The electromagnet group (100) is arranged in the fixed position, and the electromagnet group (100) includes a plurality of accelerating electromagnets (110) and a plurality of guide rods (120) for fixing the plurality of accelerating electromagnets (110). The plurality of accelerating electromagnets (110) are equidistantly distributed along the length direction of the fixed position, and a first inner air channel is formed between adjacent accelerating electromagnets (110). The plurality of guide rods (120) are connected to all the accelerating electromagnets (110) to form an accelerating electromagnetic cylinder. The plurality of accelerating electromagnets (110) are electrically connected to an external DC power supply respectively, and the accelerating electromagnets (110) are supplied with DC power to generate a constant magnetic field. The reluctance type mover (200) is plugged into the acceleration electromagnetic cylinder. The reluctance type mover (200) includes a soft magnetic body (210) and a cruise missile mounting seat (230). The number of the soft magnetic bodies (210) is greater than 2. The soft magnetic bodies (210) are located in the electromagnet group (100). The soft magnetic bodies (210) are magnetic bodies that are easily demagnetized. The soft magnetic bodies (210) are subjected to electromagnetic attraction in a constant magnetic field. The soft magnetic bodies (210) are configured to be subjected to electromagnetic attraction in a constant magnetic field, thereby driving the magnetic induction type mover (200) to move. The cruise missile mounting seat (230) is provided with a first pressure relief hole (233). The soft magnetic body (210) is provided with a second pressure relief hole (211). The first pressure relief hole (233) is communicated with the second pressure relief hole (211). The plurality of accelerating electromagnets (110) correspond one to one with the plurality of accelerating sensors (310), and the accelerating sensors (310) are configured to detect any of the soft magnetic bodies (210), and when any of the soft magnetic bodies (210) is detected, control the corresponding accelerating electromagnet (110) to be connected to an external DC power supply, and control the other accelerating electromagnets (110) that have been powered on to be disconnected from the external DC power supply.

2. The open reluctance loitering missile launcher according to claim 1, characterized in that: The mounting frame (300) further comprises a plurality of deceleration sensors (320), the plurality of deceleration sensors (320) being equidistantly arranged in the fixed position along the length direction of the fixed position, the plurality of deceleration sensors (320) being all arranged on the side of the fixed position close to the emission end, and the plurality of acceleration sensors (310) being all arranged on the side of the fixed position close to the filling end; The electromagnet group (100) further comprises a plurality of deceleration electromagnets (130), wherein the plurality of deceleration electromagnets (130) are equidistantly distributed along the length direction of the fixed position, and a second inner air channel is formed between adjacent deceleration electromagnets (130). The plurality of guide rods (120) are connected to all the deceleration electromagnets (130) to form a deceleration electromagnet cylinder. The reluctance type mover (200) is plugged into the deceleration electromagnet cylinder. The deceleration electromagnet cylinder is located on the side close to the emission end of the plurality of guide rods (120), and the acceleration electromagnet cylinder is located on the side close to the filling end of the plurality of guide rods (120). The plurality of deceleration electromagnets (130) are respectively electrically connected to an external DC power supply, and the deceleration electromagnets (130) are supplied with DC power to generate a constant magnetic field. The plurality of deceleration electromagnets (130) correspond to the plurality of deceleration sensors (320) in a one-to-one manner. The deceleration sensor (320) is configured to detect the position of any of the soft magnetic bodies (210), and when the soft magnetic body (210) is detected, the corresponding deceleration electromagnet (130) is controlled to be connected to an external DC power supply, and the other energized deceleration electromagnets (130) are controlled to be disconnected from the external DC power supply. When the deceleration sensor (320) detects that the side of the soft magnetic body (210) facing the emission end and the side of the corresponding deceleration electromagnet (130) facing the emission end are located in the same plane, the deceleration sensor (320) controls the corresponding deceleration electromagnet (130) to be connected to the external DC power supply; when the deceleration sensor (320) detects that the side of the soft magnetic body (210) facing the filling end and the side of the corresponding deceleration electromagnet (130) facing the emission end are located in the same plane, the deceleration sensor (320) controls the corresponding deceleration electromagnet (130) to be disconnected from the external DC power supply.

3. The open-type magnetoresistive loitering missile launcher according to claim 2, characterized in that: The frame includes a mounting base (330) and a plurality of hoops (340) arranged on the mounting base (330); The fixing position is arranged on the mounting base (330), and the plurality of clamps (340) are all arranged on the side of the mounting base (330) where the fixing position is arranged, and the external air channel is formed between adjacent clamps (340). The plurality of clamps (340) correspond to the plurality of electromagnets one by one, and the plurality of external air channels correspond to the plurality of internal air channels. The plurality of clamps (340) and the mounting base (330) clamp the corresponding electromagnets, so that the electromagnet group (100) is fixed in the fixing position.

4. The open-type magnetoresistive loitering missile launcher according to claim 2, characterized in that: The electromagnet assembly (100) further includes a plurality of isolation blocks (140); A plurality of isolation blocks (140) are provided between adjacent electromagnets, and both ends of the isolation blocks (140) in the length direction are fixedly connected to the opposite surfaces of two adjacent electromagnets respectively.

5. The open reluctance loitering missile launcher according to claim 4, characterized in that: The electromagnet assembly (100) further includes two connecting rings (150); The two connecting rings (150) are respectively arranged at both ends of the guide rod (120), and the guide rods (120) connect the two connecting rings (150), a plurality of electromagnets and a plurality of isolation blocks (140) into one body.

6. The open-type magnetoresistive loitering missile launcher according to claim 2, characterized in that: The reluctance type mover (200) further includes a sliding bearing (220); The sliding bearing (220) is arranged on the outer wall of the soft magnetic body (210), and the outer wall of the sliding bearing (220) is slidably connected to the inner wall of the electromagnet, and the two are clearance-matched.

7. The open-type magnetoresistive loitering missile launcher according to claim 6, characterized in that: The cruise missile mounting seat (230) is arranged on the side of the soft magnetic body (210) facing the launch end, and a cruise missile placement position (231) is provided on the side of the cruise missile mounting seat (230) facing the launch end, and the cruise missile is plugged into the cruise missile placement position (231).

8. The open reluctance loitering missile launcher according to claim 7, characterized in that: The cruise missile mounting seat (230) is provided with a protection position (232) on the side facing the filling end, and the soft magnetic body (210) completely seals the protection position (232) to form a protection cavity.

9. The open reluctance loitering missile launcher according to claim 8, characterized in that: The cruise missile placement position (231), the first pressure relief hole (233), the protection position (232), and the second pressure relief hole (211) are connected in sequence.

Images