Portable missile simulation launching device

Abstract

The invention relates to a portable missile simulation launching device applied to the field of missile simulation launching, the missile simulation launching device has a night vision function and a signal flare launching simulation function, the ability of a launcher to search, aim, capture and track a target and simulate missile launching and hit the target is improved, the frequency of actual installation during training is reduced, and the training efficiency is improved. In addition, through cooperation of a reversing arc strip, an abutting plate, a hydraulic cavity and a circulation pipe, axial and radial recoil dispersion of a signal flare launching barrel can be achieved, and through cooperation of the dispersion design of a buffering cavity and the design of an adapter ring and an elastic block, the signal flare launching barrel can be more stable. When a signal detonator is launched, the distance between a signal detonator launching barrel and the body surface of a launcher is increased, and then the damage of recoil force is comprehensively reduced.

Description

Technical Field

[0001] The invention relates to a missile simulation launching device, in particular to a portable missile simulation launching device applied in the field of missile simulation launching. Background Art

[0002] Exploring the motion state of missiles and guided rockets is a complex experimental project. In order to accurately simulate the various parameters of missiles and guided rockets during the launching process, it is necessary to simulate the mechanical environment of missiles and guided rockets during the launching process, so as to assess whether the strength, mechanical and electrical properties of the missile body and main components during the launching meet the requirements of resisting large axial overloads. Therefore, it is necessary to use a missile simulation launch device to assist in the experiment and obtain relevant parameters.

[0003] The specification of Chinese invention patent CN116793148A discloses a cannonball simulation launching device. The cannonball simulation launching device provided by the invention can enable the warhead to obtain greater kinetic energy, and the trajectory of the warhead flight is closer to the real trajectory.

[0004] When the existing missile simulation launch device is working, it is fired after aiming, but the flight trajectory of the warhead is difficult to observe with the naked eye during flight, and the missile has a strong recoil at the moment it leaves the barrel. Long-term training will cause certain damage to the shooter's shoulder. Therefore, it is necessary to improve the missile simulation launch device. Summary of the invention

[0005] In view of the above-mentioned prior art, the technical problem to be solved by the present invention is how to realize the naked eye visualization of the flight trajectory of the missile after launch, and how to reduce the recoil force on the missile barrel when the missile is launched.

[0006] In order to solve the above problems, the present invention provides a portable missile simulation launch device, comprising a launch barrel with an antenna interface installed on the surface, a front sight and a rear sight located on one side of the front sight installed on the surface of the launch barrel through an axis, a flare launch barrel installed on one side of the launch barrel, an infrared camera located on the other side of the front sight installed on the central axis of the launch barrel surface, a front amount indicator installed on the side of the launch barrel away from the flare launch barrel, the flare launch barrel includes a launch cavity and a buffer cavity, and the buffer cavity is located on the side of the launch cavity away from the infrared camera On one side, an electromagnetic striker is installed inside the launch chamber, a spring strip surrounding the surface of the electromagnetic striker is installed on the inner wall of one end of the launch chamber away from the buffer chamber, a buffer plate with a diameter larger than the diameter of the electromagnetic striker is slidably installed inside the buffer chamber, a surface of the buffer plate on one side away from the electromagnetic striker is connected to a reversing structure through a connecting rod, the reversing structure includes a transfer rod rotatably connected to the surface of the connecting rod, the tail end of the transfer rod is connected to a reversing arc bar through a hinge ball, and the diameter of the reversing arc bar is smaller than the inner diameter of the buffer chamber, an abutment plate is installed inside the buffer chamber, and the reversing arc bar is in sliding contact with the surface of the abutment plate;

[0007] The end of the flare launcher tube facing away from the infrared camera is connected with a bracket, and the tail end of the electromagnetic striker is slidably connected to the inside of the bracket, and the tail end of the bracket is used to place the flare.

[0008] The above-mentioned portable missile simulation launch device has night vision function and simulated flare launch function. In addition, it can also disperse the radial recoil of the flare launch tube through the reversing arc to reduce the damage caused by the recoil.

[0009] As a further improvement of the present application, the connection between the abutment plate and the buffer cavity is a fixed connection, an electromagnetic driver is installed at the connection between the launch cavity and the buffer cavity, and the electromagnetic driver and the electromagnetic striker attract each other.

[0010] As a further improvement of the present application, a plurality of strip grooves are provided on the surface of one end of the connecting rod close to the abutment plate, and the interior of the strip groove is connected to the transfer rod through an axial rod. A limiting ring is fixedly sleeved on the surface of the connecting rod, and the limiting ring and the end of the strip groove facing away from the abutment plate are on the same vertical axis.

[0011] As a further improvement of the present application, a software analysis system is also included, which includes a remote assistance module, a visualization module and a calculation and analysis module, wherein the remote assistance module is connected to the infrared camera signal to assist the launcher in aiming at the target point, the visualization module is used to assist the remote assistance module and the calculation and analysis module in performing visualization operations, and the calculation and analysis module is connected to the antenna interface signal to calculate the viewing angle speed of the launch barrel during the simulated launch process.

[0012] As a further improvement of the present application, the aiming process of the launch cartridge is as follows:

[0013] S1. Ensure that the launcher's infrared camera, front sight and rear sight are properly connected;

[0014] S2. Suspend the infrared source simulation target at the target distance to be trained, and control the target distance within the range of 30-300 meters;

[0015] S3. The launcher carries the launcher on his shoulder and uses the front and rear sights to determine the target according to the principle of three points and one line. He should keep aiming for 30s-60s to ensure that the image field of view obtained by the infrared camera is in a stable state.

[0016] S4. The assistant uses the remote assistant module to receive the images taken by the front sight and the rear sight, and compares the gap between the launch range of the target aimed at by the launcher and the simulated target of the infrared source through the visualization module to assist in adjusting the aiming target.

[0017] As another improvement of the present application, the connection method between the abutment plate and the inner wall of the buffer chamber is replaced by a sliding connection, a fixed plate is fixedly installed inside the buffer chamber, and the space formed between the abutment plate and the fixed plate is a hydraulic chamber filled with liquid, a flow tube is installed through the inside of the fixed plate, and the tail end of the flow tube is sealed and slidably connected with an extension block.

[0018] As another improvement of the present application, the replacement structure of the buffer chamber is composed of two chambers connected by an elastic block, wherein one chamber connected to the launching chamber is buffer chamber No. 1, and the other chamber is buffer chamber No. 2. An adapter ring is fixedly connected to the inner wall of the end of buffer chamber No. 2 close to buffer chamber No. 1, and the flow tube runs through the interior of the adapter ring, and the tail end of the extension block is connected to the side surface of the adapter ring facing away from buffer chamber No. 1.

[0019] As another improvement supplement of the present application, the cross-sectional width value of the adapter ring is greater than the cross-sectional width value of the elastic block in the initial state, and the end of the adapter ring close to the No. 1 buffer cavity is slidably connected to the inner wall of the No. 2 buffer cavity, and the adapter ring is located on the side of the fixed plate away from the abutment plate.

[0020] In summary, the missile simulation launch device has night vision function and simulated flare launch function, which improves the ability of the launch personnel to search, aim, capture, track and simulate the missile launch and hit the target, reduces the frequency of actual installation during training, strengthens the aiming training of the troops, improves training efficiency, and reduces training costs. In addition, it can also disperse the axial and radial recoil of the flare launch tube through the coordination of the reversing arc strip, the abutment plate, the hydraulic chamber and the flow tube, and cooperates with the dispersed design of the buffer chamber and the design of the adapter ring and the elastic block. When the flare is launched, the distance between the flare launch tube and the body surface of the launcher is increased, thereby comprehensively reducing the damage of the recoil. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 This is a schematic diagram of the overall appearance structure of the first implementation method of the present application;

[0022] Figure 2 This is an installation diagram of a flare launcher and a launcher barrel according to the first embodiment of the present application;

[0023] Figure 3 This is an overall side view of the first embodiment of the present application;

[0024] Figure 4 This is a diagram showing the internal structure of a flare launch tube according to the first embodiment of the present application;

[0025] Figure 5 This is an installation diagram of the abutment plate, the reversing arc ring, the connecting rod and the limit ring of the first embodiment of the present application;

[0026] Figure 6 This is a schematic diagram of the working state of the commutation arc bar of the first embodiment of the present application;

[0027] Figure 7 A visual schematic diagram of a computing and analysis module in a software system according to a first embodiment of the present application;

[0028] Figure 8 This is a schematic diagram showing that the infrared simulated target point of the infrared image in the remote assistance module of the software system in the first embodiment of the present application is not within the aiming target range;

[0029] Fig. 9 It is a schematic diagram of the infrared simulated target point of the infrared image in the remote assistance module of the software system in the first embodiment of the present application after adjustment within the aiming target range;

[0030] Fig.10 This is an installation diagram of a hydraulic chamber, a flow pipe and a fixing plate according to a second embodiment of the present application;

[0031] Fig.11 This is a schematic diagram of the working state of the second implementation mode of this application;

[0032] Fig.12 This is an installation diagram of an adapter ring and an elastic strip according to a third embodiment of the present application;

[0033] Fig.13 This is a schematic diagram of the compressed state of the elastic strip according to the third embodiment of the present application.

[0034] Description of the numbers in the figure:

[0035] 1. Launching barrel; 2. Front quantity indicator; 3. Front sight; 4. Infrared camera; 5. Rear sight; 6. Flare launching barrel; 61. Electromagnetic firing pin; 62. Spring bar; 63. Buffer plate; 64. Abutment plate; 65. Limiting ring; 66. Connecting rod; 67. Reversing arc bar; 7. Support; 8. Hydraulic chamber; 9. Flow pipe; 10. Fixing plate; 11. Elastic block; 12. Adapter ring. DETAILED DESCRIPTION

[0036] Three implementation modes of the present application are described in detail below with reference to the accompanying drawings.

[0037] The first implementation method:

[0038] Figure 1-3 A portable missile simulation launch device is shown, comprising a launch barrel 1 with an antenna interface installed on the surface, a front sight 3 and a rear sight 5 located on one side of the front sight 3 are installed on the surface of the launch barrel 1 through an axis, a flare launch barrel 6 is installed on one side of the launch barrel 1, an infrared camera 4 located on the other side of the front sight 3 is installed on the central axis of the surface of the launch barrel 1, and a front amount indicator 2 is installed on the side of the launch barrel 1 away from the flare launch barrel 6. Figure 4-5 As shown, the flare launch tube 6 includes a launch chamber and a buffer chamber, and the buffer chamber is located on the side of the launch chamber away from the infrared camera 4, an electromagnetic striker 61 is installed inside the launch chamber, and a spring bar 62 surrounding the surface of the electromagnetic striker 61 is installed on the inner wall of one end of the launch chamber away from the buffer chamber, and a buffer plate 63 with a diameter larger than the diameter of the electromagnetic striker 61 is slidably installed inside the buffer chamber, and the surface of the buffer plate 63 on the side away from the electromagnetic striker 61 is connected to a reversing structure through a connecting rod 66, and the reversing structure includes a switching rod rotatably connected to the surface of the connecting rod 66, and the tail end of the switching rod is connected to a reversing arc bar 67 through a hinge ball, and the diameter of the reversing arc bar 67 is smaller than the inner diameter of the buffer chamber, and an abutment plate 64 is installed inside the buffer chamber, and the reversing arc bar 67 is in sliding contact with the surface of the abutment plate 64;

[0039] The end of the flare launch tube 6 facing away from the infrared camera 4 is connected to a bracket 7, and the tail end of the electromagnetic striker 61 is slidably connected to the inside of the bracket 7, and the tail end of the bracket 7 is used to place the flare.

[0040] The connection between the abutting plate 64 and the buffer cavity is a fixed connection. An electromagnetic driver is installed at the connection between the emitting cavity and the buffer cavity, and the electromagnetic driver and the electromagnetic striker 61 attract each other.

[0041] A plurality of strip grooves are formed on the surface of one end of the connecting rod 66 close to the abutment plate 64, and the interior of the strip grooves is connected to the transfer rod via an axle rod. A limit ring 65 is fixedly sleeved on the surface of the connecting rod 66, and the limit ring 65 and the end of the strip grooves facing away from the abutment plate 64 are on the same vertical axis.

[0042] Specifically, the present application uses the electromagnetic driver and the electromagnetic striker 61 to provide stable and reliable drive launch for the launch of the flare when simulating the launch of a missile. In addition, the smoke generated when the flare is launched gives a more intuitive training experience, and the missile trajectory during the simulation training process can be displayed;

[0043] The infrared camera 4 uses infrared thermal sensing to provide a clear battlefield view in low light or completely dark environments. The launch personnel can use the infrared night vision function to conduct simulated training for night combat and improve their night combat training capabilities;

[0044] During training, the shoulder-mounted launcher 1 can be used to portable track the target, and the speed of change of the azimuth angle, that is, the speed of change of the viewing angle, can be collected through the calculation and analysis module, so as to obtain training data after training (such as Figure 7 shown).

[0045] During training, the front aimer 3 and the rear aimer 5 are used for preliminary aiming. After aiming, the assistant (which may be an instructor or other personnel) uses the aiming images transmitted by the front aimer 3 and the rear aimer 5 presented by the visualization module (the image data is transmitted to the software system through the antenna interface) to compare the gap between the aiming target and the infrared source target, and assist the transmitter in adjusting the aiming target.

[0046] During the simulated launch, the electromagnetic striker 61 moves rapidly toward the bracket 7, thereby providing a driving force to enable the flare on the bracket 7 to be launched. After the flare leaves the bracket 7, the electromagnetic striker 61 moves in the opposite direction under the action of the spring bar 62 and hits the buffer plate 63, driving the connecting rod 66 to move toward the buffer cavity, thereby driving the reversing arc bar 67 originally stored together to spread outward, thereby reversing the recoil force originally horizontally rushing toward the buffer cavity to the radial direction of the flare launch tube 6, reducing the axial force of the flare launch tube 6 (such as Figure 7 shown).

[0047] The surface of the buffer plate 63 is connected with an elastic strip to prepare for the subsequent reset of the buffer plate 63 .

[0048] The software analysis system includes a remote assistance module, a visualization module and a calculation analysis module, wherein the remote assistance module is connected to the infrared camera 4 signal to assist the launcher in aiming at the target point, the visualization module is used to assist the remote assistance module and the calculation analysis module in performing visualization operations, and the calculation analysis module is connected to the antenna interface signal to calculate the viewing angle speed of the launch barrel 1 during the simulated launch process.

[0049] The aiming process of the launcher cartridge 1 is as follows:

[0050] S1. Ensure that the infrared camera 4, the front sight 3 and the rear sight 5 of the launcher are correctly connected;

[0051] S2. Suspend the infrared source simulation target at the target distance to be trained, and control the target distance within the range of 30-300 meters;

[0052] S3, the launcher carries the launcher cartridge 1 on his shoulder, uses the front sight 3 and the rear sight 5 to determine the aiming target according to the principle of three points in one line, and maintains aiming for 30s-60s to make the image field of view obtained by the infrared camera 4 in a stable state;

[0053] S4. The assistant uses the remote assistant module to receive the images taken by the front aimer 3 and the rear aimer 5, and compares the gap between the launch range of the launcher's aiming target and the infrared source simulation target through the visualization module to assist in adjusting the aiming target.

[0054] Specifically, the assistant checks the infrared image presented by the visualization module to see whether the infrared simulated target aimed by the launcher is within the center of the red circle (e.g. Figure 8 If it is not there, the assistant double-clicks the infrared simulated target point on the image with the left button of the mouse, and the red circle will be found to be shifted (moving towards the infrared simulated target point), and the simulated target point becomes the center of the red circle (as shown in the figure). Fig. 9 to adjust the aiming target.

[0055] The second implementation method:

[0056] Fig.10 It is shown that the connection mode between the abutment plate 64 and the inner wall of the buffer chamber is replaced by a sliding connection, a fixed plate 10 is fixedly installed inside the buffer chamber, and the space formed between the abutment plate 64 and the fixed plate 10 is a hydraulic chamber 8 filled with liquid, a flow tube 9 is installed through the inside of the fixed plate 10, and the tail end of the flow tube 9 is sealed and slidably connected with an extension block.

[0057] Different from the first embodiment, in this embodiment, the connection between the abutment plate 64 and the inner wall of the buffer cavity is a sliding connection, and a hydraulic cavity 8 is designed to provide resistance in the opposite direction of the recoil force to buffer the axial recoil force when the flare launcher 6 is launched.

[0058] Specifically, when the buffer plate 63 is impacted, the abutment plate 64 squeezes the hydraulic chamber 8. At this time, part of the liquid in the hydraulic chamber 8 is transferred and diffused through the circulation tube 9 to drive the extension block to extend outward. The movement direction of the extension block is opposite to the direction of the recoil force, thereby providing an abutment effect on the fixed plate 10, and playing a counteracting role against the recoil force of the hydraulic chamber 8, reducing the recoil force in the axial direction. In conjunction with the reversing arc strip 67 in the first embodiment, the recoil force can be comprehensively reduced through operations in the axial and radial directions (such as Fig.11 shown).

[0059] The third implementation method:

[0060] Fig.12 The replacement structure of the buffer chamber is shown to be composed of two chambers connected by an elastic block 11, wherein one chamber connected to the launch chamber is buffer chamber No. 1, and the other chamber is buffer chamber No. 2. An adapter ring 12 is fixedly connected to the inner wall of the end of buffer chamber No. 2 close to buffer chamber No. 1, and the flow tube 9 passes through the interior of the adapter ring 12, and the tail end of the extension block is connected to the side surface of the adapter ring 12 facing away from the buffer chamber No. 1.

[0061] The cross-sectional width of the adapter ring 12 is greater than the cross-sectional width of the elastic block 11 in the initial state, and one end of the adapter ring 12 close to the No. 1 buffer cavity is slidably connected to the inner wall of the No. 2 buffer cavity. The adapter ring 12 is located on the side of the fixed plate 10 away from the abutment plate 64.

[0062] Different from the second embodiment, the buffer chamber in this embodiment is not an integrated design. By moving inward, the contact distance between the isolation flare launch tube 6 and the body surface of the launcher is increased, thereby reducing the impact damage of the recoil force on the body surface of the launcher.

[0063] Specifically, when the flare is launched, the recoil forces the hydraulic chamber 8 to be squeezed, and at this time, the extension block moves in the opposite direction to drive the adapter ring 12 to move in the opposite direction of the recoil, so that the adapter ring 12 can drive the second cavity fixedly connected thereto to move synchronously, and by squeezing the elastic block 11, the end of the flare launch tube 6 that is away from the infrared camera 4 is driven away from the body surface of the launcher, thereby reducing the damage caused by the recoil (such as Fig.13 shown).

[0064] In summary, the missile simulation launch device has night vision function and simulated flare launch function, which improves the ability of the launch personnel to search, aim, capture, track and simulate missile launch and hit the target, reduces the frequency of actual installation during training, strengthens the aiming training of the troops, improves training efficiency, and reduces training costs. In addition, through the coordination of the reversing arc bar 67, the abutment plate 64, the hydraulic chamber 8 and the flow tube 9, the axial and radial recoil force of the flare launch tube 6 can be dispersed, and the dispersed design of the buffer chamber and the design of the adapter ring 12 and the elastic block 11 can be used to increase the distance between the flare launch tube 6 and the body surface of the launcher when the flare is launched, thereby comprehensively reducing the damage caused by the recoil.

[0065] In view of current practical needs, the above-mentioned implementation mode adopted in this application is not limited to the scope of protection. Various changes made within the knowledge scope of technical personnel in this field without departing from the concept of this application still fall within the scope of protection of the present invention.

Claims

1. A portable missile simulation launch device, comprising a launch barrel (1) with an antenna interface mounted on the surface, characterized in that: The surface of the launch barrel (1) is provided with a front sight (3) and a rear sight (5) located on one side of the front sight (3) via an axis, a flare launch barrel (6) is provided on one side of the launch barrel (1), an infrared camera (4) located on the other side of the front sight (3) is provided on the central axis of the surface of the launch barrel (1), a lead quantity indicator (2) is provided on the surface of the launch barrel (1) on the side away from the flare launch barrel (6), the flare launch barrel (6) comprises a launch chamber and a buffer chamber, and the buffer chamber is provided on the side of the launch chamber away from the infrared camera (4), an electromagnetic striker (61) is provided inside the launch chamber, and the launch chamber away from the infrared camera (4) A spring strip (62) surrounding the surface of the electromagnetic striker (61) is installed on the inner wall of one end of the buffer cavity, a buffer plate (63) having a diameter greater than that of the electromagnetic striker (61) is slidably installed inside the buffer cavity, a surface of the buffer plate (63) on one side facing away from the electromagnetic striker (61) is connected to a reversing structure via a connecting rod (66), the reversing structure comprises a transfer rod rotatably connected to the surface of the connecting rod (66), the tail end of the transfer rod is connected to a reversing arc strip (67) via a hinge ball, and the diameter of the reversing arc strip (67) is smaller than the inner diameter of the buffer cavity, an abutment plate (64) is installed inside the buffer cavity, and the reversing arc strip (67) is in sliding contact with the surface of the abutment plate (64); The end of the flare launch tube (6) facing away from the infrared camera (4) is connected to a bracket (7), and the tail end of the electromagnetic striker (61) is slidably connected to the inside of the bracket (7), and the tail end of the bracket (7) is used to place the flare.

2. A portable missile simulation launch device according to claim 1, characterized in that: The connection mode between the abutment plate (64) and the buffer chamber is a fixed connection, an electromagnetic driver is installed at the connection between the emission chamber and the buffer chamber, and the electromagnetic driver and the electromagnetic striker (61) attract each other.

3. A portable missile simulation launch device according to claim 1, characterized in that: A plurality of strip grooves are formed on the surface of one end of the connecting rod (66) close to the abutment plate (64), and the interior of the strip grooves is connected to the transfer rod via an axle rod. A limiting ring (65) is fixedly sleeved on the surface of the connecting rod (66), and the limiting ring (65) and the end of the strip groove facing away from the abutment plate (64) are on the same vertical axis.

4. A portable missile simulation launch device according to claim 1, characterized in that: The software analysis system also includes a remote assistance module, a visualization module and a calculation analysis module, wherein the remote assistance module is connected to the infrared camera (4) signal and is used to assist the launcher in aiming at the target point, the visualization module is used to assist the remote assistance module and the calculation analysis module in performing visualization operations, and the calculation analysis module is connected to the antenna interface signal and is used to calculate the visual angle speed of the launch barrel (1) during the simulated launch process.

5. A portable missile simulation launch device according to claim 4, characterized in that: The aiming process of the launching cartridge (1) is as follows: S1. Ensure that the launcher infrared camera (4), front sight (3) and rear sight (5) are properly connected; S2. Suspend the infrared source simulation target at the target distance to be trained, and control the target distance within the range of 30-300 meters; S3, the launcher carries the launch tube (1) on his shoulder, uses the front sight (3) and the rear sight (5) to determine the aiming target according to the principle of three points in one line, and maintains aiming for 30s-60s to ensure that the image field of view obtained by the infrared camera (4) is in a stable state; S4. The assistant uses the remote assistant module to receive the images taken by the front aimer (3) and the rear aimer (5), and compares the gap between the launch range of the target aimed at by the launcher and the simulated target of the infrared source through the visualization module, and assists in adjusting the aiming target.

6. A portable missile simulation launch device according to claim 5, characterized in that: The connection mode between the abutment plate (64) and the inner wall of the buffer chamber is replaced by a sliding connection, a fixed plate (10) is fixedly installed inside the buffer chamber, and the space formed between the abutment plate (64) and the fixed plate (10) is a hydraulic chamber (8) filled with liquid, a flow tube (9) is installed through the inside of the fixed plate (10), and the tail end of the flow tube (9) is sealed and slidably connected with an extension block.

7. A portable missile simulation launch device according to claim 6, characterized in that: The replacement structure of the buffer cavity is composed of two cavities connected by an elastic block (11), wherein one cavity connected to the launch cavity is a No. 1 buffer cavity, and the other cavity is a No. 2 buffer cavity. An adapter ring (12) is fixedly connected to the inner wall of the end of the No. 2 buffer cavity close to the No. 1 buffer cavity, and the flow tube (9) passes through the interior of the adapter ring (12). The tail end of the extension block is connected to the side surface of the adapter ring (12) facing away from the No. 1 buffer cavity.

8. A portable missile simulation launch device according to claim 7, characterized in that: The cross-sectional width of the adapter ring (12) is greater than the cross-sectional width of the elastic block (11) in the initial state, and one end of the adapter ring (12) close to the No. 1 buffer cavity is slidably connected to the inner wall of the No. 2 buffer cavity, and the adapter ring (12) is located on a side of the fixed plate (10) facing away from the abutment plate (64).

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