Push rod type travel switch for missile fuse and working method thereof

Abstract

The invention provides an ejector rod type travel switch for a missile fuse and a working method thereof, and relates to the technical field of missile fuse switches. Comprising a fuse body, a firing pin rod, a detonator base and a pin shaft, a spring groove is formed in the fuse body, the bottom end in the spring groove is fixedly connected with a second supporting spring, the firing pin rod is arranged in the second supporting spring in a sleeved mode, one end of the firing pin rod is fixedly connected with a pin head, and the bottom end of the pin head abuts against an igniter cap. A detonator is arranged at the bottom end of the igniter cap and is in a lateral T shape, gunpowder is arranged at the bottom end of the detonator, and a detonator base is arranged on the outer side of the gunpowder in a sleeving mode. The fuse body and the detonator seat are in threaded connection through external threads, so that mounting, dismounting and overhauling operation is facilitated, a pin shaft and a through hole are matched in an inserted mode, a side plate is inserted into the top end of the fuse body, then the side plate is clamped and fixed through a clamping block, a bottom protruding block of the side plate is clamped and fixed through the clamping block, and the side plate is clamped and limited through a pull rod.

Description

Technical Field

[0001] The invention relates to the technical field of missile fuze switches, in particular to a push rod type travel switch for a missile fuze and a working method thereof. Background Art

[0002] The missile fuze is a control system that uses environmental information and target information to control the warhead to detonate or detonate the warhead charge at the most favorable position or time relative to the target under predetermined conditions. It must have four basic functions: safety control, release of insurance, target sensing, and detonation control. The missile fuze system consists of a sensor for detecting the target, an ignition mechanism for making the warhead explode, and a safety mechanism to ensure safety. The dynamic, instantaneous, and one-time nature of its working process constitutes its main characteristics that distinguish it from other missile systems. A missile fuze with good performance can not only ensure the safety of the warhead and even the entire missile, but also enable the warhead to fully exert its power to destroy the target.

[0003] The missile fuze in the prior art plays a vital role in the use of missiles and can control the detonation of missiles. Traditional missiles also have a latch structure that can control the switch function of the travel. When applying for the present invention, the applicant found through search that a Chinese patent discloses a "rod-type travel switch for missile fuze and its working method", and its application number is "202410385241.6". The patent mainly compresses and releases the compression force of the compression spring by plugging and pulling out the latch, and then drives the short-circuit board assembly to move up and down through the combination mode of the ejector rod, the limit rod and the lower ejector rod, so as to realize the switching of multiple upper and lower signals. The operation is time-saving and labor-saving, and the correctness of the working state of the fuze module is ensured, which reliably and effectively provides the first safety guarantee for the missile. However, the lateral penetration of the latch structure may affect the installation and the launch of the missile during use. Therefore, according to the invention of the applicant, a rod-type travel switch for missile fuze is invented, which solves the problem that the existing latch structure affects the use and launch of the missile. Summary of the invention

[0004] 1. Technical issues to be resolved

[0005] In view of the deficiencies of the prior art, the present invention provides a push rod type travel switch for a missile fuze and a working method thereof, which solves the problem that the existing latch structure affects the use and launch of the missile.

[0006] (II) Technical solution

[0007] To achieve the above objectives, the present invention is implemented through the following technical solutions: a push rod type travel switch for missile fuze, comprising: a fuze body, a firing pin rod, a detonator seat and a pin shaft, a spring groove is provided inside the fuze body, a second supporting spring is fixedly connected to the inner bottom end of the spring groove, a firing pin rod is sleeved inside the second supporting spring, a needle is fixedly connected to one end of the firing pin rod, a primer is abutted at the bottom end of the needle, a detonator is provided at the bottom end of the primer, the detonator is in a lateral T-shape, gunpowder is provided at the bottom end of the detonator, a detonator seat is sleeved on the outer side of the gunpowder, an external thread is provided at the top of the detonator seat, an internal thread is provided at the bottom end of the fuze body, the fuze body and the detonator seat are threadedly connected, an infrared sensor unit is fixedly connected to one side of the upper interior of the fuze body, and a laser radar sensor unit is fixedly connected to the other side of the upper interior of the fuze body;

[0008] Slide rods are fixedly connected to both sides of the inner top of the fuze body, blocks are slidably fitted to both sides of the middle of the slide rod, side plates are arranged on the inner side of the blocks, protrusions are fixedly connected to both ends of the bottom of the side plates, and the protrusions and the blocks are in contact with each other.

[0009] Preferably, the top end of the firing pin rod is fixedly connected to a metal block, and a through hole is opened in the middle of the metal block.

[0010] Preferably, a pin shaft passes through the interior of the through hole, and a slot is provided inside the side plate, and the slot and the pin shaft are slidably matched.

[0011] Preferably, an igniter is provided on one side of the detonator, and a plurality of drainage plates are fixedly connected to the outer side of the fuze body.

[0012] Preferably, an extension block is fixedly connected to the middle portion of the firing pin rod, and the extension block and the first support spring are in abutment with each other.

[0013] Preferably, a fixing block is fixedly connected between the sliding rods, and the fixing block is fixedly connected to the fuse body.

[0014] Preferably, a pull rod is inserted into the outer side of the block, and a latch rod passes through the pull rod and the fuse body.

[0015] A method for operating a push rod type travel switch for a missile fuze comprises the following specific steps:

[0016] Step S1: The fuze body and the detonator seat are threadedly connected by external threads to facilitate installation, disassembly and maintenance operations, and the pin shaft and the through hole are plugged and matched, and the side plate is plugged into the top of the fuze body, and then fixed by a clamping block, and the bottom protrusion of the side plate is clamped and fixed, and the pull rod is clamped and limited;

[0017] Step S2: When the control switch operation is required, the latch rod is separated from the fuze body and the pull rod, and then the pull rod can be pulled outward. After being pulled out, the second support spring elastically supports and bounces the block outward, and the bottom spring of the side plate bounces upward and detaches, and the disassembly operation is completed. Then, the fuze body follows the launch of the missile, and the metal block can be brought into contact with the ground. By impacting the firing pin rod, the first support spring is compressed, and the needle head completes the impact ignition operation on the primer, and the gunpowder is detonated by the action of the detonator to complete the detonation work;

[0018] Step S3: At the same time, the infrared sensor unit can also be used to complete the induction detonation of the fuze body. First, the infrared sensor unit detects the infrared radiation energy and spatial distribution of the target to obtain the target's position and movement information, and controls the missile to fly to the target through the control system. When the missile approaches the target, the fuze system starts working; the fuze system usually includes a laser device, which continuously detects the distance data between the target and the target after launch, and transmits this data back to the missile. When the distance reaches the preset value, the fuze system will detonate the missile; and by setting a laser radar sensor unit on the other side of the fuze body, the laser radar can be launched to complete precise positioning in foggy and rainy weather;

[0019] Step S4: Due to changes in weather conditions, the infrared sensor unit and the lidar sensor unit work independently. The two sensor units monitor the distance. When one of them reaches a predetermined distance, it can send a signal to the controller. After receiving the signal, the controller sends a signal to the igniter. The igniter can ignite the detonator structure to detonate the gunpowder, thereby achieving precise distance control and completing the ignition operation.

[0020] (III) Beneficial effects

[0021] The present invention provides a push rod type travel switch for missile fuze and a working method thereof. It has the following beneficial effects:

[0022] 1. The present invention is provided with: external threads, pin shafts, side plates, latch rods and second supporting springs. The fuze body and the detonator seat are threadedly connected by external threads, which is convenient for installation, disassembly and maintenance operations. The pin shaft and the through hole are plugged and matched, and the side plate is plugged into the top of the fuze body, and then fixed by a clamping block, and the bottom protrusion of the side plate is clamped and fixed. The pull rod is clamped and limited. When it is necessary to control the switch operation, the latch rod is separated from the fuze body and the pull rod, and then the pull rod can be pulled outward. After being pulled out, the second supporting spring elastically supports and bounces the clamping block outward. The bottom spring of the side plate bounces up and detaches, and the disassembly operation can be completed. The structure is used to complete the travel switch control of the fuze top rod in the missile, reduce the traditional space occupation, and achieve the storage effect.

[0023] 2. The present invention is provided with: an infrared sensing unit, through which the induction detonation of the fuze body is completed. First, the infrared sensing unit obtains the position and movement information of the target by detecting the infrared radiation energy and spatial distribution of the target, and controls the missile to fly to the target through the control system. When the missile approaches the target, the fuze system starts to work; and by arranging a laser radar sensing unit on the other side of the fuze body, the laser radar can be emitted to complete precise positioning in foggy and rainy weather.

[0024] 3. The present invention is provided with: an infrared sensor unit and a laser radar sensor unit. The infrared sensor unit and the laser radar sensor unit work independently. The two sensor units monitor the distance. When one of them reaches a predetermined distance, it can send a signal to the controller. After receiving the signal, the controller sends a signal to the igniter. The igniter can ignite the detonator structure to detonate the gunpowder, thereby realizing precise distance control and completing the ignition operation. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 It is a schematic cross-sectional front view of the present invention;

[0026] Figure 2 It is a schematic diagram of the controller flow of the present invention;

[0027] Figure 3 It is a schematic front view of a cross section of a side plate structure of the present invention;

[0028] Figure 4 It is a schematic diagram of the three-dimensional structure of the present invention;

[0029] Figure 5 For the present invention Figure 1 A is an enlarged schematic diagram;

[0030] Figure 6 It is a schematic diagram of the disassembly of the pin shaft and the side plate of the present invention.

[0031] Among them, 1. fuse body; 2. extension block; 3. infrared sensor unit; 4. metal block; 5. laser radar sensor unit; 6. firing pin rod; 7. first support spring; 8. igniter; 9. gunpowder; 10. detonator seat; 11. block; 12. slide rod; 13. fixed block; 14. second support spring; 15. latch rod; 16. pull rod; 17. drain plate; 18. through hole; 19. primer; 20. needle; 21. external thread; 22. detonator; 23. side plate; 24. slot; 25. pin shaft. DETAILED DESCRIPTION

[0032] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0033] Example:

[0034] like Figure 1-6 As shown, the embodiment of the present invention provides a push rod type travel switch for missile fuze, including: a fuze body 1, a firing pin rod 6, a detonator seat 10 and a pin shaft 25. A spring groove is provided inside the fuze body 1, and a second support spring 14 is fixedly connected to the inner bottom end of the spring groove. The firing pin rod 6 is sleeved inside the second support spring 14. A needle 20 is fixedly connected to one end of the firing pin rod 6. The bottom end of the needle 20 abuts against a primer 19. A detonator 22 is provided at the bottom end of the primer 19. The gunpowder 9 is detonated by the action of the detonator 22 to complete the detonation work. The detonator 22 is in a lateral T-shape, and the bottom end of the detonator 22 is provided with a A gunpowder 9 is arranged, and a detonator seat 10 is sleeved on the outer side of the gunpowder 9. An external thread 21 is provided on the top of the detonator seat 10. The fuze body 1 and the detonator seat 10 are threadedly connected through the external thread 21, which is convenient for installation and disassembly and maintenance operations. An internal thread is provided on the bottom end of the fuze body 1. The fuze body 1 and the detonator seat 10 are threadedly connected. An infrared sensor unit 3 is fixedly connected to one side of the upper part of the interior of the fuze body 1. The induction detonation work of the fuze body 1 is completed by the infrared sensor unit 3. First, the infrared sensor unit 3 obtains the position and movement of the target by detecting the infrared radiation energy and spatial distribution of the target. The fuze system starts to work when the missile approaches the target. A laser radar sensor unit 5 is fixedly connected to the other side of the upper part of the fuze body 1. The laser radar sensor unit 5 can accurately locate the laser radar in foggy and rainy weather. The top of the firing pin rod 6 is fixedly connected to a metal block 4. The fuze body 1 follows the launch of the missile and can bring the metal block 4 into contact with the ground. By impacting the firing pin rod 6, the first support spring 7 is compressed, and the needle 20 completes the impact ignition operation on the primer 19. The middle part of the metal block 4 is provided with a Through hole 18, a pin 25 is passed through the interior of through hole 18, the pin 25 and the through hole 18 are plugged and matched, the side plate 23 is plugged into the top of the fuze body 1, and then fixed by the clamping block 11, a clamping slot 24 is provided inside the side plate 23, the clamping slot 24 and the pin 25 are slidably matched, an igniter 8 is provided on one side of the detonator 22, the igniter 8 can ignite the detonator 22 structure to detonate the gunpowder 9, can achieve precise distance control, and complete the ignition operation, the outer side of the fuze body 1 is fixedly connected with a plurality of drainage pieces 17, and the drainage pieces 17 can maintain stable operation during the missile launch process;

[0035] The top of the fuze body 1 is fixedly connected to the two sides of the inner top, and the fixed block 13 is fixedly connected between the slide bars 12. The fixed block 13 is fixedly connected to the fuze body 1. The middle of the slide bar 12 is slidably matched with the clamping block 11 on both sides. The inner side of the clamping block 11 is provided with a side plate 23. The bottom end spring of the side plate 23 is ejected upward to complete the disassembly operation. The bottom ends of the side plate 23 are fixedly connected with a protrusion. The bottom protrusion of the side plate 23 is clamped and fixed. 16 is engaged and limited to complete the locking and fixing. The protrusion and the block 11 are in contact with each other. The middle part of the firing pin rod 6 is fixedly connected with the extension block 2. The extension block 2 and the first support spring 7 are in contact with each other. A pull rod 16 is inserted into the outer side of the block 11 to separate the latch rod 15 from the fuze body 1 and the pull rod 16. Then the pull rod 16 can be pulled outward. After being pulled out, the second support spring 14 elastically supports and bounces the block 11 outward. The latch rod 15 runs through the pull rod 16 and the fuze body 1.

[0036] A method for operating a push rod type travel switch for a missile fuze comprises the following specific steps:

[0037] Step S1: The fuze body 1 and the detonator seat 10 are threadedly connected through the external thread 21, which is convenient for installation, disassembly and maintenance operations, and the pin shaft 25 and the through hole 18 are plugged and matched, and the side plate 23 is plugged into the top inner part of the fuze body 1, and then fixed by the clamping block 11, and the bottom protrusion of the side plate 23 is clamped and fixed, and the pull rod 16 is clamped and limited;

[0038] Step S2: When the switch operation needs to be controlled, the latch rod 15 is separated from the fuze body 1 and the pull rod 16, and then the pull rod 16 can be pulled outward. After being pulled out, the second support spring 14 elastically supports and bounces the block 11 outward, and the bottom spring of the side plate 23 bounces upward and detaches, and the disassembly operation is completed. Then, the fuze body 1 follows the launch of the missile, and can make the metal block 4 contact with the ground. By impacting the firing pin rod 6, the first support spring 7 is compressed, and the needle head 20 completes the impact ignition operation on the primer 19, and the gunpowder 9 is detonated by the action of the detonator 22, completing the detonation work;

[0039] Step S3: At the same time, the infrared sensor unit 3 can also complete the induction detonation of the fuze body 1. First, the infrared sensor unit 3 detects the infrared radiation energy and spatial distribution of the target to obtain the position and movement information of the target, and controls the missile to fly to the target through the control system. When the missile approaches the target, the fuze system starts to work; the fuze system usually includes a laser device, which continuously detects the distance data between the target and the target after launch, and transmits this data back to the inside of the missile. When the distance reaches the preset value, the fuze system will detonate the missile; and by setting the laser radar sensor unit 5 on the other side of the fuze body 1, the laser radar can be launched to complete precise positioning in foggy and rainy weather;

[0040] Step S4: Due to changes in weather conditions, the infrared sensor unit 3 and the lidar sensor unit 5 work independently. The two sensor units monitor the distance. When one of them reaches a predetermined distance, both can send a signal to the controller. After receiving the signal, the controller sends a signal to the igniter 8. The igniter 8 can ignite the detonator 22 structure to detonate the gunpowder 9, thereby achieving precise distance control and completing the ignition operation.

[0041] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A push rod type travel switch for missile fuze, comprising: A fuze body (1), a firing pin rod (6), a detonator seat (10) and a pin shaft (25), characterized in that: a spring groove is provided inside the fuze body (1), a second support spring (14) is fixedly connected to the inner bottom end of the spring groove, a firing pin rod (6) is sleeved inside the second support spring (14), a needle head (20) is fixedly connected to one end of the firing pin rod (6), a bottom end of the needle head (20) abuts against a primer (19), a detonator (22) is provided at the bottom end of the primer (19), and the detonator (22) ) is in a lateral T-shape, the bottom end of the detonator (22) is provided with gunpowder (9), the outer side of the gunpowder (9) is provided with a detonator seat (10), the top end of the detonator seat (10) is provided with an external thread (21), the bottom end of the fuze body (1) is provided with an internal thread, the fuze body (1) and the detonator seat (10) are threadedly connected, the upper side of the interior of the fuze body (1) is fixedly connected with an infrared sensor unit (3), and the other upper side of the interior of the fuze body (1) is fixedly connected with a laser radar sensor unit (5); Both sides of the inner top of the fuze body (1) are fixedly connected with a slide bar (12), both sides of the middle of the slide bar (12) are slidably matched with a clamping block (11), a side plate (23) is arranged on the inner side of the clamping block (11), and both ends of the bottom of the side plate (23) are fixedly connected with a protrusion, and the protrusion and the clamping block (11) are in abutment with each other.

2. A push rod type travel switch for missile fuze according to claim 1, characterized in that: The top end of the firing pin rod (6) is fixedly connected to a metal block (4), and a through hole (18) is provided in the middle of the metal block (4).

3. A push rod type travel switch for missile fuze according to claim 2, characterized in that: A pin shaft (25) passes through the through hole (18), and a slot (24) is provided inside the side plate (23). The slot (24) and the pin shaft (25) are slidably matched.

4. A push rod type travel switch for missile fuze according to claim 1, characterized in that: An igniter (8) is provided on one side of the detonator (22), and a plurality of drainage plates (17) are fixedly connected to the outer side of the fuze body (1).

5. A push rod type travel switch for missile fuze according to claim 1, characterized in that: An extension block (2) is fixedly connected to the middle of the firing pin rod (6), and the extension block (2) and the first support spring (7) are in abutment with each other.

6. A push rod type travel switch for missile fuze according to claim 1, characterized in that: A fixing block (13) is fixedly connected between the sliding rods (12), and the fixing block (13) and the fuse body (1) are fixedly connected.

7. A push rod type travel switch for missile fuze according to claim 1, characterized in that: A pull rod (16) is inserted into the outer side of the clamping block (11), and a latch rod (15) passes through between the pull rod (16) and the fuse body (1).

8. A method for operating a push rod type travel switch for a missile fuze, based on a push rod type travel switch for a missile fuze according to any one of claims 1 to 7, characterized in that: The specific steps include: Step S1: The fuze body (1) and the detonator seat (10) are threadedly connected via an external thread (21) to facilitate installation, disassembly and maintenance operations, and the pin shaft (25) and the through hole (18) are plugged and matched, and the side plate (23) is plugged into the top of the fuze body (1), and then fixed by the clamping block (11), and fixed by the bottom protrusion of the side plate (23), and the pull rod (16) is clamped and limited; Step S2: When the switch operation needs to be controlled, the latch rod (15) is separated from the fuze body (1) and the pull rod (16), and then the pull rod (16) can be pulled outward. After being pulled out, the second support spring (14) elastically supports and bounces the block (11) outward, and the bottom spring of the side plate (23) bounces upward and separates, and the disassembly operation is completed. Then, the fuze body (1) follows the launch of the missile and can make the metal block (4) contact the ground. By impacting the firing pin rod (6), the first support spring (7) is compressed, and the needle head (20) completes the impact ignition operation on the primer (19), and the gunpowder (9) is detonated by the action of the detonator (22), completing the detonation work; Step S3: At the same time, the infrared sensor unit (3) can also complete the induction detonation of the fuze body (1). First, the infrared sensor unit (3) detects the infrared radiation energy and spatial distribution of the target to obtain the position and movement information of the target, and controls the missile to fly to the target through the control system. When the missile approaches the target, the fuze system starts to work; the fuze system usually includes a laser device, which continuously detects the distance data between the missile and the target after launch, and transmits the data back to the inside of the missile; when the distance reaches a preset value, the fuze system will detonate the missile; and by arranging a laser radar sensor unit (5) on the other side of the fuze body (1), the laser radar can be launched to complete accurate positioning in foggy and rainy weather; Step S4: Due to the change of weather conditions, the infrared sensor unit (3) and the laser radar sensor unit (5) work independently. The two sensor units monitor the distance. When one of them reaches a predetermined distance, it can send a signal to the controller. After receiving the signal, the controller sends a signal to the igniter (8). The igniter (8) can ignite the detonator (22) structure to detonate the gunpowder (9), thereby realizing precise distance control and completing the ignition operation.

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