Airborne missile safety device
By designing a lane -based missile insurance device that links the missile locking circuit and the ignition circuit, the problem of safety hazards of accidental ignition during the missile testing process is solved, and higher security and stability are achieved.
Patent Information
- Application Number
- CN202311145122.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2023-09-06
- Publication Date
- 2025-01-24
AI Technical Summary
The ignition circuit of existing airborne missiles is prone to accidental ignition during the test, resulting in great safety hazards.
Design an airborne missile fuse, which controls the interlocking circuit and ignition circuit of the missile through linkage, and uses the conversion module to connect with the first conduction module and the second conduction module to form a loop to achieve system testing and launch control, and through Circuit break protection settings improve safety.
It effectively improves the safety of the missile, prevents accidental ignition and misoperation ignition, and ensures the stability and controllability of the missile during testing and launch.
Smart Images
Figure CN119353992A_ABST
Abstract
Description
Technical Field
[0001] The invention relates to the technical field of missile launch control, in particular to an airborne missile safety device. Background Art
[0002] Airborne missiles of conventional weapon systems usually have their internal engine combustion powder and pyrotechnics such as the detonating powder of the fuze controlled by an ignition circuit. The ignition circuit needs to be triggered by an electric current. To prevent accidental ignition of the missile, all ignition circuits are short-circuited by short-circuit fuses before launch. In addition, interlock circuits are usually provided in the missile to test the missile control system. During the test of the interlock circuit, abnormal test operation is prone to occur, which may cause the ignition circuit to operate and cause accidental ignition, posing a great safety hazard. Summary of the invention
[0003] The purpose of the present invention is to provide an airborne missile safety device to solve the problems existing in the above-mentioned prior art and to control the interlocking circuit and ignition circuit of the missile in a linked manner to improve safety.
[0004] To achieve the above object, the present invention provides the following solutions:
[0005] The present invention provides an airborne missile insurance device, comprising a fuse shell, a travel component and a switch component; the fuse shell is used to be arranged on a missile body; the travel component comprises a driving mechanism, and the driving mechanism is arranged on the fuse shell; the switch component is arranged on the fuse shell, and the switch component has a first conduction module, a second conduction module and a movably arranged conversion module; the first conduction module is used to access the interlocking circuit of the missile body, and the second conduction module is used to access the ignition circuit of the missile body; the conversion module can be connected to the driving mechanism, and the driving mechanism can drive the conversion module to move so that the conversion module is connected to the first conduction module or the second conduction module; when the conversion module is connected to the first conduction module, the conversion module, the first conduction module and the interlocking circuit form a loop; when the conversion module is connected to the second conduction module, the conversion module, the second conduction module and the ignition circuit form a loop.
[0006] Preferably, the conversion module includes a conversion component and a return component, the return component is connected to the conversion component, the conversion component can be connected to the driving mechanism, the driving mechanism can drive the conversion component to move until the conversion component is connected to the second conduction module, and can cause the return component to undergo elastic deformation; and the conversion component can move to and maintain connection with the first conduction module under the restoring force of the return component.
[0007] Preferably, the driving mechanism includes a driving member and a sliding member, the sliding member slides and is sealingly connected to the safety shell, the driving member is connected to both the sliding member and the safety shell, and the driving member is used to drive the sliding member to slide relative to the safety shell and drive the conversion component to move so that the conversion component is connected to the second conduction module.
[0008] Preferably, the driving member is configured as an elastic member; the sliding member can slide relative to the safety housing under the action of external pressure so that the conversion component can move under the restoring force of the return component to connect with the first conduction module, and can cause the driving member to undergo elastic deformation; and the sliding member can slide relative to the safety housing under the restoring force of the driving member so that the conversion component can move to connect with the second conduction module, and can cause the return component to undergo elastic deformation.
[0009] Preferably, the stroke assembly also includes a limiting component, which can be detachably connected to the sliding member and the safety shell and can fix the relative position of the sliding member and the safety shell so that the conversion assembly remains connected to the first conduction module; and the sliding member can also abut against the frame to fix the relative position with the safety shell so that the conversion assembly remains connected to the first conduction module.
[0010] Preferably, the sliding member includes a sliding rod and a trigger block fixedly connected from top to bottom, the trigger block is movably arranged in the safety shell, the sliding rod is slidably and sealingly connected to the safety shell, and the lower end of the sliding rod is fixedly connected to the upper side of the trigger block, and the upper end of the sliding rod can extend out of the safety shell; the driving member is arranged in the safety shell and connected to the sliding member; one end of the conversion component is arranged in the safety shell and can be connected to the trigger block; the sliding member can slide outward relative to the safety shell under the restoring force of the driving member until the upper side of the trigger block is against the inner wall of the safety shell and maintains a relative position with the safety shell, so that the conversion component can be driven by the trigger block to move to maintain connection with the second conduction module.
[0011] Preferably, the driving member is configured as a spring, a guide rod is provided in the safety shell, the sliding member is provided with a guide groove, the spring is coaxially sleeved outside the guide rod, the spring and the guide rod can extend into the guide groove, and the two ends of the spring are respectively connected to the sliding member and the inner wall of the safety shell.
[0012] Preferably, the side of the trigger block used for connecting with the conversion assembly is set as an upslope surface.
[0013] Preferably, the switch assembly includes two micro switches fixedly arranged side by side on the safety shell, each of the micro switches includes a fixed shell, a transmission rod, a reset spring, a connecting piece, and a first pin, a second pin, a third pin and a fourth pin arranged side by side; each of the fixed shells can be detachably arranged on the safety shell, the transmission rod is movably arranged in the fixed shell, and one end of the transmission rod extends out of the fixed shell and can be connected to the driving mechanism, the transmission rods and the connecting piece of the two micro switches are the conversion assembly, and the return component includes two reset springs; the first pin, the second pin, the third pin and the fourth pin are fixedly arranged on each of the fixed shells, and one end of the first pin, the second pin, the third pin and the fourth pin all extend out of the corresponding fixed shell, and the other end is arranged in the corresponding fixed shell, the third pin and the fourth pin of the two micro switches are the first pin The microswitch comprises a first microswitch and a second microswitch, wherein the first microswitch and the second microswitch are connected to each other through a first connecting module and a second connecting module, and the first microswitch and the second microswitch are connected to each other through a first connecting module and a second connecting module. The microswitch comprises a first microswitch and a second microswitch, wherein the first microswitch and the second microswitch are connected to each other through a first connecting module and a second connecting module. The microswitch comprises a first microswitch and a second microswitch, wherein the first microswitch and the second microswitch are connected to each other through a first connecting module and a second connecting module. The microswitch comprises a first microswitch and a second microswitch, wherein the first microswitch and the second microswitch are connected to each other through a first connecting module and a second connecting module.
[0014] Preferably, it further comprises a connector disposed on the fuse housing, the connector being connectable to the first conduction module and the second conduction module via cables, and the connector being further used for electrically connecting to the interlock circuit and the ignition circuit.
[0015] Compared with the prior art, the present invention has achieved the following technical effects:
[0016] The airborne missile safety device provided by the present invention is integrated and arranged on the missile body, wherein the safety shell is connected to the missile body, and the driving mechanism of the travel component is arranged on the safety shell, which can drive the conversion module of the switch component to move, so that the conversion module is connected to the first conduction module or the second conduction module; since the first conduction module is connected to the interlocking circuit of the missile body, and the second conduction module is connected to the ignition circuit of the missile body, when the conversion module is connected to the first conduction module, the conversion module, the first conduction module and the interlocking circuit form a loop, and the missile body can complete the system test at this time, and the ignition circuit is in an open circuit state, and the ignition circuit will not be triggered in any operation, and the ignition circuit will be triggered only when the conversion module is connected to the second conduction module, so that the safety is improved by the open circuit protection setting; when the conversion module is connected to the second conduction module under the action of the driving mechanism, the conversion module, the second conduction module and the ignition circuit form a loop, and the missile launch is completed; in this way, the airborne missile safety device provided by the present invention controls the connection of the interlocking circuit and the ignition circuit of the missile in a linked manner, so that the safety can be improved. BRIEF DESCRIPTION OF THE DRAWINGS
[0017] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.
[0018] Figure 1 This is an axial schematic diagram of the airborne missile safety device provided in Example 1;
[0019] Figure 2 A schematic diagram of the side cross-sectional structure of the airborne missile safety device provided in the first embodiment when the ignition circuit is turned on;
[0020] Figure 3 A partial cross-sectional schematic diagram of the airborne missile safety device provided in Example 1 when the ignition circuit is turned on;
[0021] Figure 4 A schematic diagram of the side cross-sectional structure of the airborne missile safety device provided in the first embodiment when the interlock circuit is turned on;
[0022] Figure 5 A cross-sectional schematic diagram of the micro switch provided in Example 1;
[0023] Figure 6 This is a schematic diagram of the circuit connection of the switch assembly and the connector provided in Example 1.
[0024] Icons: 1-airborne missile safety device; 10-safety shell: 11-guide rod; 12-sealing ring; 13-connecting rod; 20-stroke assembly; 21-driving mechanism; 211-driving member; 212-sliding member; 2121-sliding rod; 2122-trigger block; 2123-guide groove; 22-limiting member; 30-switch assembly; 31-first conduction module; 32-second conduction module; 33-conversion module; 331-conversion assembly; 332-return member; 34-micro switch; 341-fixed shell; 342-transmission rod; 343-reset spring; 344-connecting member; 3441-reed leaf; 3442-circlip; 345-first pin; 346-second pin; 347-third pin; 348-fourth pin; 40-connector; 41-cable; 42-clamp. DETAILED DESCRIPTION
[0025] 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.
[0026] The purpose of the present invention is to provide an airborne missile safety device to solve the problems existing in the above-mentioned prior art, to link and control the interlocking circuit and the ignition circuit of the missile to improve the safety and integration, and to facilitate the setting.
[0027] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.
[0028] Embodiment 1
[0029] This embodiment provides an airborne missile safety device 1, see Figure 1-Figure 6, including a fuse shell 10, a stroke assembly 20 and a switch assembly 30; the fuse shell 10 is used to be arranged on the missile body; the stroke assembly 20 includes a driving mechanism 21, and the driving mechanism 21 is arranged on the fuse shell 10; the switch assembly 30 is arranged on the fuse shell 10, and the switch assembly 30 has a first conduction module 31, a second conduction module 32 and a movably arranged conversion module 33; the first conduction module 31 is used to access the interlocking circuit of the missile body, and the second conduction module 32 is used to access the ignition circuit of the missile body; the conversion module 33 can be connected to the driving mechanism 21, and the driving mechanism 21 can drive the conversion module 33 to move so that the conversion module 33 is connected to the first conduction module 31 or the second conduction module 32; when the conversion module 33 is connected to the first conduction module 31, the conversion module 33, the first conduction module 31 and the interlocking circuit form a loop; when the conversion module 33 is connected to the second conduction module 32, the conversion module 33, the second conduction module 32 and the ignition circuit form a loop.
[0030] The integrated device is arranged on the missile body, wherein the fuse shell 10 is connected to the missile body, and the driving mechanism 21 of the stroke assembly 20 is arranged on the fuse shell 10, which can drive the conversion module 33 of the switch assembly 30 to move, so that the conversion module 33 is connected to the first conduction module 31 or the second conduction module 32; since the first conduction module 31 is connected to the interlocking circuit of the missile body, and the second conduction module 32 is connected to the ignition circuit of the missile body, when the conversion module 33 is connected to the first conduction module 31, the conversion module 33, the first conduction module 31 and the interlocking circuit form a loop, and the missile body can complete the system test at this time, and the ignition circuit is in an open circuit state, ensuring safety; when the conversion module 33 is connected to the second conduction module 32 under the action of the driving mechanism 21, the conversion module 33, the second conduction module 32 and the ignition circuit form a loop, and the missile ignition and launch are completed; in this way, the airborne missile safety device 1 provided by the present invention can control the connection of the interlocking circuit and the ignition circuit of the missile in a linked manner, and can improve safety.
[0031] Among the optional solutions of this embodiment, it is more preferred to refer to Figure 2 , Figure 4 and Figure 5The conversion module 33 includes a conversion component 331 and a return component 332. The return component 332 is connected to the conversion component 331. The conversion component 331 can be connected to the driving mechanism 21. The driving mechanism 21 can drive the conversion component 331 to move so that the conversion component 331 is connected to the second conduction module 32, and can cause the return component 332 to undergo elastic deformation; and the conversion component 331 can move under the restoring force of the return component 332 to maintain connection with the first conduction module 31; by setting the return component 332, the conversion component 331 can maintain connection with the first conduction module 31, forming a loop with the interlocking circuit, and the ignition circuit is in an open circuit state, thereby improving safety; the conversion component 331 can be connected to the second conduction module 31 only when driven by the driving mechanism 21.
[0032] Among the optional solutions of this embodiment, it is more preferred to refer to Figure 2 and Figure 4 The driving mechanism 21 includes a driving member 211 and a sliding member 212. The sliding member 212 slides and is sealed to the safety shell 10, and can move relatively while maintaining sealing. The driving member 211 is connected to the sliding member 212 and the safety shell 10. The driving member 211 is used to drive the sliding member 212 to slide relative to the safety shell 10, and drive the conversion component 331 to move so that the conversion component 331 is connected to the second conduction module 32. The driving member 211 is arranged to facilitate driving the sliding member 212 to slide relative to the safety shell 10 to drive the conversion component 331 to move.
[0033] Among the optional solutions of this embodiment, it is more preferred to refer to Figure 2 and Figure 4 , the driving member 211 is configured as an elastic member; the sliding member 212 can slide relative to the safety shell 10 under the action of external pressure such as pressing so that the conversion component 331 can move under the restoring force of the return component 332 to connect with the first conduction module 31, and can cause the driving member 211 to undergo elastic deformation; and the sliding member 212 can slide relative to the safety shell 10 under the restoring force of the driving member 211, so that the conversion component 331 can move to connect with the second conduction module 32, and can cause the return component 332 to undergo elastic deformation; the driving member 211 is configured as an elastic member, so that when the sliding member 212 is not restricted by external pressure, the sliding member 212 is driven to slide to drive the conversion component 331 to connect with the second conduction module 32 so that the ignition circuit is triggered for automatic firing.
[0034] In the optional scheme of this embodiment, it is more preferred that the stroke assembly 20 also includes a limiting component 22, and the limiting component 22 can be detachably connected to the sliding member 212 and the safety shell 10 and can fix the relative position of the sliding member 212 and the safety shell 10 so that the conversion assembly 331 remains connected to the first conduction module 31; and the sliding member 212 can also abut against the frame to fix the relative position with the safety shell 10 so that the conversion assembly 331 remains connected to the first conduction module 31.
[0035] Specifically, the limiting component 22 can be configured as a safety pin, which can be detachably inserted through the safety housing 10 and the sliding member 212 to fix their relative positions.
[0036] Specifically, during the loading or testing phase: the limiting component 22 is connected to the sliding member 212 and the fuse housing 10 for limiting. Figure 1 and Figure 4 The entire safety device is arranged on the missile body so that the conversion component 331 remains connected to the first conduction module 31. At this time, the ignition circuit of the airborne missile is still disconnected and the interlocking circuit is connected, which can effectively prevent the missile from being accidentally ignited or ignited by mistake without affecting the missile test items.
[0037] During the stage of aircraft carrying missiles and taking off: in this stage, the missile is mounted on the airborne missile rack, and then the limiting component 22 can be removed, and the sliding member 212 can be pressed against the missile rack. By controlling the position of the missile relative to the rack, when the sliding member 212 is pressed against the rack, the sliding member 212 has a small stroke or does not move under the restoring force of the driving member 211, and the conversion component 331 still remains connected to the first conduction module 31. At this time, the ignition circuit of the airborne missile is still disconnected, and the interlocking circuit is connected, which can effectively prevent the missile from being accidentally ignited or ignited by misoperation without affecting the missile test items.
[0038] Among the optional solutions of this embodiment, it is more preferred to refer to Figure 2 and Figure 4The sliding member 212 is vertically arranged, and the sliding member 212 includes a sliding rod 2121 and a trigger block 2122 that are fixedly connected from top to bottom. The trigger block 2122 is movably arranged in the safety shell 10. The sliding rod 2121 is slidably and sealedly connected to the safety shell 10, and the lower end of the sliding rod 2121 is fixedly connected to the upper side of the trigger block 2122, and the upper end of the sliding rod 2121 can extend out of the safety shell 10; the driving member 211 is arranged in the safety shell 10 and connected to the sliding member 212; one end of the conversion assembly 331 is arranged in the safety shell 10 and can be connected to the trigger block 2122; the sliding member 212 can slide outward relative to the safety shell 10 under the restoring force of the driving member 211 to the upper side of the trigger block 2122 and the trigger block 2122. The inner wall of the fuse shell 10 abuts against and maintains a relative position with the fuse shell 10, so that the conversion component 331 can be driven by the trigger block 2122 to move to maintain connection with the second conduction module 32; a sealing groove is provided on the inner circumferential surface of the fuse shell 10 surrounding the slide bar 2121, and a sealing ring 12 is provided in the sealing groove to ensure the sealing of the sliding connection between the slide bar 2121 and the fuse shell 10, which is waterproof and dustproof; wherein the sliding member 212 can compress the driving member 211 during the sliding process, so that the trigger block 2122 can abut against the inner wall of the fuse shell 10 under the action of the restoring force of the driving member 211, so that the conversion component 331 can move to maintain connection with the second conduction module 32, and form a loop with the ignition circuit of the missile.
[0039] Specifically, in the stage of aircraft bombing: in this stage, after the aircraft arrives at the designated area and executes the missile launch command, the missile is released from the rack. At this time, the sliding member 212 continues to bounce upward under the driving member 211 until the upper side of the trigger block 2122 abuts against the inner wall of the fuselage 10. Figure 2 and Figure 3 Under the action of the trigger block 2122, the conversion component 331 is connected to the second conduction module 32 to form a loop with the ignition circuit. The missile has the ignition and launch conditions and can be launched through the carrier aircraft.
[0040] During the aircraft unloading stage: when the aircraft is flying with bombs and returns to unload bombs without performing the bomb dropping mission, a tool is used to press the sliding member 212 to the extreme position and connect the limiting component 22. As the sliding member 212 moves downward, the conversion assembly 331 can be restored to the initial position and connected to the first conduction module 31 under the action of the restoring force of the return component 332, forming a loop with the interlocking circuit, and the missile ignition circuit is still disconnected, effectively preventing the missile from being accidentally ignited or ignited by mistake.
[0041] In the optional scheme of this embodiment, it is more preferred that the driving member 211 is configured as a spring, a guide rod 11 is provided in the safety shell 10, the sliding member 212 is provided with a guide groove 2123, the spring is coaxially sleeved outside the guide rod 11, the spring and the guide rod 11 can extend into the guide groove 2123, and the two ends of the spring are respectively fixedly connected to the sliding member 212 and the inner wall of the safety shell 10; the guide rod 11 is provided to facilitate guiding, and the driving member 211 is provided in the guide groove 2123, which can save space and facilitate layout.
[0042] In the optional scheme of this embodiment, it is more preferred that the side of the trigger block 2122 used to connect with the conversion component 331 is set as an uphill surface. By setting it as an uphill surface, the uphill surface gradually approaches the conversion component 321 from top to bottom. Therefore, the upward movement of the trigger block 2122 can squeeze the conversion component 331 to move, and the downward movement of the trigger block 2122 can pop out under the restoring force of the return component 332.
[0043] Among the optional solutions of this embodiment, it is more preferred to refer to Figure 5 The switch assembly 30 includes two micro switches 34 fixedly arranged side by side on the safety housing 10. The micro switches 34 can be set as double-circuit micro switches. Specifically, each micro switch 34 includes a fixed housing 341, a transmission rod 342, a return spring 343, a connecting piece 344, and a first pin 345, a second pin 346, a third pin 347 and a fourth pin 348 arranged side by side; each fixed housing 341 can be detachably arranged on the safety housing 10, and the transmission rod 342 is movably arranged in the fixed housing 341, and one end of the transmission rod 342 extends Out of the fixed shell 341 and capable of being connected to the driving mechanism 21, the transmission rod 342 and the connecting piece 344 of the two micro switches 34 are the conversion component 331, and the two reset springs 343 are the return component 332; the first pin 345, the second pin 346, the third pin 347 and the fourth pin 348 are fixedly arranged on the corresponding fixed shell 341, and one end of the first pin 345, the second pin 346, the third pin 347 and the fourth pin 348 are all extended out of the corresponding fixed shell 341, and the other end is all arranged in the corresponding fixed shell 341.
[0044] Among them, the third pin 347 and the fourth pin 348 of the two micro switches 34 are the first conduction module 31 and are used to access the interlocking circuit. Usually, the ignition circuit of the missile includes the engine ignition circuit and the fuze ignition circuit. Therefore, the second conduction module 32 includes the engine ignition conduction module and the fuze ignition conduction module. The first pin 345 and the fourth pin 348 of one micro switch 34 are the engine ignition conduction module and are used to access the engine ignition circuit. The first pin 345 and the fourth pin 348 of the other micro switch 34 are the fuze ignition conduction module and are used to access the fuze ignition circuit; reset spring 343 and the connecting piece 344 are arranged in the corresponding fixed shell 341, the reset spring 343 is connected to the transmission rod 342 and the fixed shell 341, and the connecting piece 344 is connected to the transmission rod 342; the driving mechanism 21 can drive the two transmission rods 342 to move relative to the corresponding fixed shell 341, so that the two ends of the corresponding connecting piece 344 are respectively connected to the corresponding second pin 346 and the third pin 347, and the corresponding reset spring 343 can be elastically deformed; and each connecting piece 344 can be connected to the corresponding first pin 345 and the fourth pin 348 at both ends under the restoring force of the corresponding reset spring 343.
[0045] Specifically, the two micro switches 34 can be embedded in the safety housing 10 and fixed by a connecting rod 13 penetrating the safety housing 10 and the fixing housing 341 .
[0046] The transmission rod 342 is slidably arranged in the fixed shell 341, and the return spring 343 is sleeved on the outside of the transmission rod 342 and fixedly connected to the transmission rod 342 and the fixed shell 341. The return spring 343 can be compressed during the inward sliding of the transmission rod 342; each connecting piece 344 includes a spring leaf 3441 and two retaining springs 3442, the transmission rod 342 is inserted in the middle of the spring leaf 3441, and the middle side edge of the spring leaf 3441 is fixedly connected to the fixed shell 341, the two retaining springs 3442 are located on both sides of the transmission rod 342, and one end of the two retaining springs 3442 is fixedly connected to the transmission rod 342, and the other end is respectively connected to the two ends of the spring leaf 3441, and contacts are provided on both sides of the two ends of the spring leaf 3441. One end of the spring 3442 is placed between the inner ends of the first pin 345 and the second pin 346, and the other end is placed between the inner ends of the third pin 347 and the fourth pin 348; in the initial state, the two ends of the spring 3442 can be connected to the inner ends of the corresponding second pin 346 and the third pin 347, and the transmission rod 342 slides inwardly under the action of the driving mechanism 21 to compress the reset spring 343, and can bend the two ends of the spring 3441 by bending the retaining spring 3442 to be connected to the inner ends of the corresponding first pin 345 and the fourth pin 348, and can extend outward under the restoring force of the reset spring 343, so that the retaining spring 3442 is restored to make the two ends of the spring 3441 reconnect with the inner ends of the corresponding second pin 346 and the third pin 347.
[0047] In the optional scheme of this embodiment, it is more preferred that the missile safety device 1 provided in this embodiment further includes a connector 40 arranged on the safety shell 10, and the connector 40 can be connected to the first conduction module 31 and the second conduction module 32 through the cable 41, and the connector 40 can also be electrically connected to the missile body through the plug connector to connect to the interlock circuit and the ignition circuit; specifically, for the circuit connection relationship between the connector 40 and the first conduction module 31 and the second conduction module 32, please refer to Figure 6 The connector 40 may be configured as a conventional wiring head having nine interfaces, which are numbered 1-9 respectively. The left micro switch 34 and the right micro switch 34 are respectively the outer ends of the first pin 345, the second pin 346, the third pin 347 and the fourth pin 348 from top to bottom, which may be represented by L1-L4 and R1-R4 respectively; Figure 6 K1-K4 indicate whether the conversion component 331 is connected to the first conduction module 31 or the second conduction module 32; L1 and L4 are respectively connected to interfaces No. 6 and No. 7 of the connector 40, and interfaces No. 6 and No. 7 are connected to the fuze ignition circuit of the missile body; R1 is connected in parallel to interfaces No. 4 and No. 5, and R4 is connected in parallel to interfaces No. 8 and No. 9, and interfaces No. 8 and No. 9 are connected to the engine ignition circuit of the missile body; L2 is connected to R2 and connected to interface No. 1, L3 is connected to R3 and connected to interface No. 2, and interfaces No. 1 and No. 2 are connected to the interlocking circuit of the missile body.
[0048] Furthermore, the cable 41 can be fixedly disposed on the outside of the fuse housing 10 by a wire clamp 42 .
[0049] In the optional scheme of this embodiment, it is more preferred that the fuse shell 10 is configured as a detachable structure, such as a detachable upper cover or lower cover, which is convenient for installation and disassembly.
[0050] The present invention uses specific examples to illustrate the principles and implementation methods of the present invention. The above examples are only used to help understand the method and core ideas of the present invention. At the same time, for those skilled in the art, according to the ideas of the present invention, there will be changes in the specific implementation methods and application scopes. In summary, the content of this specification should not be understood as limiting the present invention.
Claims
1. An airborne missile safety device, characterized in that: include: A fuse shell (10) is used to be arranged on the missile body; A travel assembly (20), the travel assembly (20) comprising a driving mechanism (21), the driving mechanism (21) being arranged on the safety housing (10); and A switch assembly (30) is arranged on the fuse housing (10), wherein the switch assembly (30) comprises a first conduction module (31), a second conduction module (32) and a movably arranged conversion module (33); the first conduction module (31) is used to connect to the interlocking circuit of the missile body, and the second conduction module (32) is used to connect to the ignition circuit of the missile body; the conversion module (33) can be connected to the driving mechanism (21), and the driving mechanism (21) can drive the conversion module (33) to move so that the conversion module (33) is connected to the first conduction module (31) or the second conduction module (32); when the conversion module (33) is connected to the first conduction module (31), the conversion module (33), the first conduction module (31) and the interlocking circuit form a loop; when the conversion module (33) is connected to the second conduction module (32), the conversion module (33), the second conduction module (32) and the ignition circuit form a loop.
2. The airborne missile safety device according to claim 1, characterized in that: The conversion module (33) comprises a conversion component (331) and a return component (332); the return component (332) is connected to the conversion component (331); the conversion component (331) can be connected to the driving mechanism (21); the driving mechanism (21) can drive the conversion component (331) to move until the conversion component (331) is connected to the second conduction module (32), and can cause the return component (332) to undergo elastic deformation; and the conversion component (331) can move under the restoring force of the return component (332) until it is connected to and maintained with the first conduction module (31).
3. The airborne missile safety device according to claim 2, characterized in that: The driving mechanism (21) comprises a driving member (211) and a sliding member (212); the sliding member (212) is slidably connected to the safety housing (10); the driving member (211) is connected to both the sliding member (212) and the safety housing (10); the driving member (211) is used to drive the sliding member (212) to slide relative to the safety housing (10) and to drive the conversion component (331) to move so that the conversion component (331) is connected to the second conduction module (32).
4. The airborne missile safety device according to claim 3 is characterized in that: The driving member (211) is configured as an elastic member; the sliding member (212) can slide relative to the safety housing (10) under the action of external pressure so that the conversion component (331) can move under the restoring force of the return component (332) to connect with the first conduction module (31), and can cause the driving member (211) to undergo elastic deformation; and the sliding member (212) can slide relative to the safety housing (10) under the restoring force of the driving member (211) so that the conversion component (331) can move to connect with the second conduction module (32), and can cause the return component (332) to undergo elastic deformation.
5. The airborne missile safety device according to claim 4, characterized in that: The stroke assembly (20) further comprises a limiting component (22), wherein the limiting component (22) is detachably connected to the sliding member (212) and the safety housing (10) and is capable of fixing the relative position of the sliding member (212) and the safety housing (10) so that the conversion assembly (331) and the first conduction module (31) remain connected; and the sliding member (212) is also capable of abutting against a frame to fix the relative position with the safety housing (10) so that the conversion assembly (331) and the first conduction module (31) remain connected.
6. The airborne missile safety device according to claim 5, characterized in that: The sliding member (212) comprises a sliding rod (2121) and a trigger block (2122) which are fixedly connected from top to bottom; the trigger block (2122) is movably arranged in the safety shell (10); the sliding rod (2121) is slidably and sealedly connected to the safety shell (10); the lower end of the sliding rod (2121) is fixedly connected to the upper side of the trigger block (2122); the upper end of the sliding rod (2121) can extend out of the safety shell (10); the driving member (211) is arranged in the safety shell (10) and is connected to the sliding member (212). ) connected; one end of the conversion component (331) is arranged in the safety shell (10) and can be connected to the trigger block (2122); the sliding member (212) can slide outward relative to the safety shell (10) under the restoring force of the driving member (211) until the upper side of the trigger block (2122) abuts against the inner wall of the safety shell (10) and maintains a relative position with the safety shell (10), so that the conversion component (331) can be driven by the trigger block (2122) to move to maintain connection with the second conduction module (32).
7. The airborne missile safety device according to claim 6, characterized in that: The driving member (211) is configured as a spring, a guide rod (11) is provided in the safety housing (10), the sliding member (212) is provided with a guide groove (2123), the spring is coaxially sleeved outside the guide rod (11), the spring and the guide rod (11) can extend into the guide groove (2123), and two ends of the spring are respectively connected to the sliding member (212) and the inner wall of the safety housing (10).
8. The airborne missile safety device according to claim 6, characterized in that: The side surface of the trigger block (2122) used for connecting with the conversion assembly (331) is arranged as an upslope surface.
9. The airborne missile safety device according to claim 2, characterized in that: The switch assembly (30) comprises two micro switches (34) fixedly arranged side by side on the safety housing (10), each of the micro switches (34) comprising a fixed housing (341), a transmission rod (342), a return spring (343), a connecting piece (344), and a first pin (345), a second pin (346), a third pin (347), and a fourth pin (348) arranged side by side; each of the fixed housings (341) is detachably arranged on the safety housing (10), and the transmission rod (342) is movably arranged in the fixed housing (341). One end of the transmission rod (342) extends out of the fixed shell (341) and can be connected to the driving mechanism (21); the transmission rods (342) and the connecting piece (344) of the two micro switches (34) are the conversion assembly (331); the return component (332) includes two reset springs (343); each of the fixed shells (341) is fixedly provided with the first pin (345), the second pin (346), the third pin (347) and the fourth pin (348); the first pin (345), the second pin (346), the third pin (347) and the fourth pin (348); One end of the second pin (346), the third pin (347) and the fourth pin (348) are all extended out of the corresponding fixed shell (341), and the other end is arranged in the corresponding fixed shell (341); the third pin (347) and the fourth pin (348) of the two micro switches (34) are the first conduction module (31) and are used to connect to the interlock circuit; the second conduction module (32) includes an engine ignition conduction module and a fuse ignition conduction module; the first pin (345) and The fourth pin (348) is the engine ignition conduction module and is used to connect to the engine ignition circuit. The first pin (345) and the fourth pin (348) of another micro switch (34) are the fuze ignition conduction module and are used to connect to the fuze ignition circuit. The reset spring (343) and the connecting piece (344) are arranged in the corresponding fixed shell (341). The reset spring (343) is connected to the transmission rod (342) and the fixed shell (341), and the connecting piece (344) is connected to the transmission rod (342). The driving mechanism (21) is capable of driving the two transmission rods (342) to move relative to the corresponding fixed shell (341) until the two ends of the corresponding connecting piece (344) are respectively connected to the corresponding second pin (346) and the third pin (347), and can cause the corresponding reset spring (343) to undergo elastic deformation; and each connecting piece (344) can move under the restoring force of the corresponding reset spring (343) until the two ends are respectively connected to the corresponding first pin (345) and the fourth pin (348).
10. The airborne missile safety device according to claim 1, characterized in that: The invention also comprises a connector (40) arranged on the fuse housing (10), wherein the connector (40) can be connected to the first conduction module (31) and the second conduction module (32) via a cable (41), and the connector (40) is also used to be electrically connected to the interlock circuit and the ignition circuit.