CN218994189U - Rocket engine igniter and fuze integrated structure - Google Patents
Rocket engine igniter and fuze integrated structure Download PDFInfo
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- CN218994189U CN218994189U CN202222376270.5U CN202222376270U CN218994189U CN 218994189 U CN218994189 U CN 218994189U CN 202222376270 U CN202222376270 U CN 202222376270U CN 218994189 U CN218994189 U CN 218994189U
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- fuse
- fuze
- rocket engine
- rotor
- fuse body
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Abstract
The utility model relates to a rocket engine igniter and fuze integrated structure, which comprises a front fuze body and a rear fuze body which are combined together, wherein a rotor seat is arranged in a cavity formed by the front fuze body and the rear fuze body, a rotor is arranged on the rotor seat, a connecting screw is arranged on the rear fuze body, an electric ignition tube is arranged on the connecting screw, a safety mechanism is connected on the rear fuze body and the connecting screw in a penetrating way, and the safety mechanism is used for limiting the rotation of the rotor. The utility model combines the ignition tool and the fuze of the rocket projectile into a whole, is integrally arranged on the rocket projectile body, has the functions of ignition and fuze, and has the advantages of small whole volume, simple structure and low production cost.
Description
Technical Field
The utility model relates to a rocket engine fuze, in particular to a rocket engine igniter and fuze integrated structure.
Background
The existing rocket projectile is generally composed of a rocket engine, a warhead and a stabilizing device. The warhead includes a fuze, rocket hull, explosive or other charge. Rocket engines include igniter systems, propellants, combustion chambers, nozzles, and the like. The igniter and the fuze are two independent parts and are divided into two parts, so that the rocket projectile has a complex structure, high manufacturing cost and low safety and reliability.
Disclosure of Invention
The utility model aims to provide a rocket engine igniter and fuze integrated structure, which aims to solve the problems of complex rocket structure and high cost caused by the fact that the igniter and the fuze of the existing rocket are two independent components.
The utility model is realized in the following way: the utility model provides a rocket engine ignition utensil and fuse integral structure, includes the front fuse body and the back fuse body that are in the same place the front fuse body with be provided with the rotor seat in the cavity that the back fuse body formed be provided with the rotor on the rotor seat be provided with on the back fuse body and connect the spiral shell on be provided with electric ignition tube the back fuse body with connect the spiral shell on the cross-under have safety mechanism, safety mechanism is used for restricting the rotation of rotor.
The safety mechanism comprises a guide pipe, a safety pin is arranged in the guide pipe, an air taking cylinder is arranged at the lower end of the guide pipe, one end of the air taking cylinder is in sealing connection with the rear fuse body, the other end of the air taking cylinder is in sealing connection with the connecting screw, a piston is arranged in the air taking cylinder, an air guide hole is formed in the connecting screw, and the air guide hole is communicated with a port of the air taking cylinder.
And a sealing ring is sleeved on the piston.
And a push rod is arranged at the end part of the piston.
The rotor seat is provided with a rotating shaft, the rotor is installed on the rotating shaft, and a torsion spring is sleeved on the rotating shaft.
The connecting screw is connected to the rear fuze body through a bolt.
And an external thread is arranged at the end part of the connecting screw.
The front fuze body is connected with the rear fuze body through threads.
The control circuit board is arranged in a cavity formed by the front fuze body and the rear fuze body, a wire connected to the control circuit board passes through the rear fuze body and the connecting screw, and the control circuit board is connected with the electric ignition tube through the wire.
The utility model integrates the fuze and the igniter of the rocket projectile, after the fuze part is arranged on the rocket body through the connecting screw, the electric ignitron on the connecting screw is arranged at the same time, the electric ignitron is communicated with the engine of the rocket, the rocket engine is ignited after the electric ignitron is ignited, the rocket projectile is launched out of the chamber, and the high-pressure gas generated after the rocket engine is ignited pushes the safety mechanism to release the safety of the fuze, so that the fuze function starts to work.
The utility model combines the ignition tool and the fuze of the rocket projectile into a whole, is integrally arranged on the rocket projectile body, has the functions of ignition and fuze, and has the advantages of small whole volume, simple structure and low production cost.
Drawings
Fig. 1 is a structural diagram of the present utility model.
Fig. 2 is a bottom view of fig. 1.
Fig. 3 is A-A view of fig. 2.
In the figure: 1. a front fuze body; 2. a rear fuze body; 3. a rotor seat; 4. a rotor; 5. connecting with a screw; 6. an electric ignition tube; 7. a conduit; 8. a safety pin; 9. taking an inflator; 10. a piston; 11. an air guide hole; 12. a partition plate; 13. a seal ring; 14. a push rod; 15. a rotating shaft; 16. a torsion spring; 17. a bolt; 18. a gasket; 19. an external thread; 20. a control circuit board; 21. a wire; 22. and a through hole.
Detailed Description
As shown in fig. 1 and 2, the utility model comprises a front fuse body 1 and a rear fuse body 2 which are combined together, a cavity is formed between the front fuse body 1 and the rear fuse body 2 after the combination, a rotor seat 3 is arranged in the cavity, a rotor 4 is arranged on the rotor seat 3, a connecting screw 5 is arranged on the rear fuse body 2, an electric ignition tube 6 is arranged on the connecting screw 5, and a safety mechanism is connected on the rear fuse body 2 and the connecting screw 5 in a penetrating way and is used for limiting the rotation of the rotor 4.
The fuse and the electric ignition tube 6 are integrated together and are fixedly arranged on the rocket projectile through the connecting screw 5, the electric ignition tube 6 is used for igniting and starting the rocket engine, the safety mechanism is used for limiting the rotation of the rotor 4 in an initial state, after the rocket is launched, the fuse rotor 4 is limited by the safety mechanism, and after the rotor 4 rotates, the fuse function starts to work.
Wherein, the safety mechanism includes pipe 7, and pipe 7 is fixed in the cavity that forms between the front fuse body 1 and the back fuse body 2, is provided with the safety pin 8 in pipe 7, and safety pin 8 can follow pipe 7 and remove. The lower end of the guide pipe 7 is provided with an air taking cylinder 9, one end of the air taking cylinder 9 is in sealing connection with the rear fuze body 2, the other end of the air taking cylinder 9 is in sealing connection with the connecting screw 5, a piston 10 is arranged in the air taking cylinder 9, the connecting screw 5 is provided with an air guide hole 11, and the air guide hole 11 is communicated with a port of the air taking cylinder 9.
A partition plate 12 is arranged between the guide pipe 7 and the air taking cylinder 9, in an initial state, the safety pin 8 is positioned at the lowest end, the upper end of the safety pin 8 and the rotor 4 are released to limit the rotation of the rotor 4, gas generated after the rocket engine is ignited enters the air taking cylinder 9 through the air guide hole 11, the high-pressure gas pushes the piston 10 to move upwards, the impact force enables the piston 10 to pass through the partition plate 12, then the piston 10 pushes the safety pin 8 to move upwards, the end part of the safety pin 8 enters into a notch on the side wall of the rotor 4, so that the limitation on the rotation of the rotor 4 is released, the rotor 4 rotates to enter into a working state, and a fuze function is started.
Wherein a sealing ring 13 is sleeved on the piston 10. The sealing performance between the piston 10 and the inner wall of the air taking cylinder 9 is ensured by the sealing ring 13.
The upper end of the piston 10 is provided with a mandril 14, the diameter of the mandril 14 is smaller than that of the guide pipe 7, the mandril 14 is inserted into the guide pipe 7 after the piston 10 moves upwards, and the mandril 14 pushes the safety pin 8 to move upwards.
The rotor seat 3 is provided with a rotating shaft 15, the rotor 4 is arranged on the rotating shaft 15, the rotating shaft 15 is sleeved with a torsion spring 16, the rotation of the rotor 4 is realized by the driving of the torsion spring 16, the rotor 4 is in a preparation state in an initial state, and after fuse safety is relieved, the torsion spring 16 drives the rotor 4 to rotate to enable the rotor 4 to enter a working state.
The connecting screw 5 is connected to the rear fuse body 2 through bolts 17, a plurality of bolts 17 are arranged in the circumferential direction of the connecting screw 5, and a gasket 18 is arranged between the connecting screw 5 and the rear fuse body 2.
An external thread 19 is provided at the end of the coupling screw 5, and the present utility model can be integrally attached to the rocket body by the external thread 19.
The front fuse body 1 and the rear fuse body 2 are connected through threads, so that the firmness and the tightness of connection between the front fuse body 1 and the rear fuse body 2 can be ensured.
A control circuit board 20 is arranged in a cavity formed by the front fuze body 1 and the rear fuze body 2, a lead 21 connected to the control circuit board 20 passes through the rear fuze body 2 and the connecting screw 5, and the fuze circuit board is connected with the electric ignition tube 6 through the lead 21. The lead 21 connects the control circuit board 20 with the rocket body controller, and the rocket body controller supplies power to the control circuit of the fuze and sends control signals.
As shown in fig. 3, the electric squib 6 is screwed into a through hole 22 on the coupling screw 5, the through hole 22 is communicated with the rocket engine, and the electric squib 6 is detonated after receiving an ignition signal, thereby igniting the rocket engine.
The fuze and the igniter are integrated into a whole, and after the fuze part is arranged on a rocket body through the connecting screw 5, the electric ignitron 6 on the connecting screw 5 is arranged at the same time. When the rocket engine is in operation, the rocket engine is ignited after the electric ignition tube 6 is ignited, the rocket is launched out of the chamber, and high-pressure gas generated after the rocket engine is ignited pushes the safety mechanism to release the safety of the fuse, so that the fuse function starts to operate.
The utility model combines the igniter and the fuze of the rocket projectile into a whole, is integrally arranged on the rocket projectile body, has the functions of ignition and fuze, simplifies the design of the rocket projectile, has small integral volume, reduces the manufacturing and using cost, and increases the safety.
Claims (9)
1. The utility model provides a rocket engine ignition utensil and fuse integral structure, its characterized in that includes the front fuse body and the back fuse body that are in the same place the front fuse body with be provided with the rotor seat in the cavity that the back fuse body formed be provided with the rotor on the rotor seat be provided with on the back fuse body and connect the spiral shell be provided with electric ignition tube connect the spiral shell to go up the cross-under has safety mechanism, safety mechanism is used for restricting the rotation of rotor.
2. A rocket engine igniter and fuse integrated structure according to claim 1, wherein said safety mechanism comprises a conduit, a safety pin is arranged in said conduit, a gas taking cylinder is arranged at the lower end of said conduit, one end of said gas taking cylinder is in sealing connection with said rear fuse body, the other end of said gas taking cylinder is in sealing connection with said gas receiving cylinder, a piston is arranged in said gas taking cylinder, a gas guiding hole is arranged on said gas receiving cylinder, and said gas guiding hole is communicated with a port of said gas taking cylinder.
3. A rocket engine igniter and fuse integrated structure according to claim 2 wherein a sealing ring is sleeved on said piston.
4. A rocket engine igniter and fuse integrated structure according to claim 2 wherein a ram is provided at the end of said piston.
5. A rocket engine igniter and fuze integrated structure as defined in claim 1 wherein a rotating shaft is provided on said rotor mount, said rotor is mounted on said rotating shaft, and a torsion spring is sleeved on said rotating shaft.
6. A rocket engine igniter and fuse integrated structure as defined in claim 1 wherein said connector screw is bolted to said rear fuse body.
7. A rocket engine igniter and fuse integrated structure according to claim 1, wherein external threads are provided at the ends of said coupling screws.
8. A rocket engine igniter and fuse integrated structure according to claim 1, wherein said front fuse body and said rear fuse body are threadably connected.
9. A rocket engine igniter and fuse integrated structure according to claim 1, wherein a control circuit board is disposed in a cavity formed by said front fuse body and said rear fuse body, a wire connected to said control circuit board passes through said rear fuse body and said connecting screw, and said control circuit board is connected to said electric squib through a wire.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222376270.5U CN218994189U (en) | 2022-09-07 | 2022-09-07 | Rocket engine igniter and fuze integrated structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222376270.5U CN218994189U (en) | 2022-09-07 | 2022-09-07 | Rocket engine igniter and fuze integrated structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218994189U true CN218994189U (en) | 2023-05-09 |
Family
ID=86192736
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222376270.5U Active CN218994189U (en) | 2022-09-07 | 2022-09-07 | Rocket engine igniter and fuze integrated structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218994189U (en) |
-
2022
- 2022-09-07 CN CN202222376270.5U patent/CN218994189U/en active Active
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