CN204003155U - A kind of rocket motor with decompression protection device - Google Patents
A kind of rocket motor with decompression protection device Download PDFInfo
- Publication number
- CN204003155U CN204003155U CN201420221159.1U CN201420221159U CN204003155U CN 204003155 U CN204003155 U CN 204003155U CN 201420221159 U CN201420221159 U CN 201420221159U CN 204003155 U CN204003155 U CN 204003155U
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- China
- Prior art keywords
- ring
- pressure relief
- chamber shell
- burning chamber
- jet pipe
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- Expired - Fee Related
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Abstract
The utility model relates to a kind of rocket motor with decompression protection device, belongs to rocket motor field.Rocket motor of the present utility model, comprises burning chamber shell, rear pressing cover, pressure relief ring, jet pipe; Pressure relief ring is enclosed within the rear end of jet pipe ring-type screens platform, make the axial screens of ear end face of pressure relief ring and jet pipe ring-type screens platform, the front end of jet pipe inserts the rear end of burning chamber shell, and by the grate screens forward in burning chamber shell, rear pressing cover is threaded in the rear end of burning chamber shell, and pressure relief ring is clamped between burning chamber shell ear end face and rear pressing cover ring-type positioning table, and then the ring-type screens platform of jet pipe front end is clamped between grate and pressure relief ring.The utility model, by being directly connected by pressure relief ring with burning chamber shell at jet pipe, has ensured Security in fire trial process, and the possibility of having avoided motor to blast in abnormal conditions, can be widely used in rocket motor field.
Description
Technical field
The utility model relates to a kind of rocket motor with decompression protection device, belongs to rocket motor field.
Background technique
Rocket motor is the power plant of rocket, is conventionally made up of parts such as engine chamber, powder charge, igniter, grate, jet pipes, by propellant combustion, produces high temperature and high pressure gas, through jet pipe ejection, forms rocket Driving force.Wherein, between jet pipe and burning chamber shell, be connected by link, as shown in Figure 1, the rear end of burning chamber shell is threaded with the front inner wall of link, and the annular boss of jet pipe front end is clamped between the rear end of burning chamber shell and the screens platform of link rear end.In engine ignition process of the test, because motor, powder charge design or powder column itself may exist the defect such as crackle, leakiness, the situation that can cause motor internal pressure to increase suddenly, can cause engine explosions when serious.In propellant formulation research process, when the engine test of jejune propellant formulation, more easily there is this situation.So largely increase experimentation cost, but also greatly incured loss through delay scientific research progress.Therefore, need a kind of pressure relief device, can be at engine pressure is excessive while exceeding a certain predetermined value releasing pressure automatically, play protection engine action.
Model utility content
The purpose of this utility model is, in order to solve in conventional engines fire trial process, the problem of engine explosions to occur, and a kind of rocket motor with decompression protection device is provided.
The purpose of this utility model is achieved through the following technical solutions:
A kind of rocket motor with decompression protection device of the present utility model, comprises burning chamber shell, rear pressing cover, pressure relief ring, jet pipe;
The rear end outer wall of burning chamber shell is processed with outside thread;
The front end end of jet pipe extends outward ring-type screens platform, and the external diameter of this ring-type screens platform and the internal diameter of burning chamber shell rear end match;
Rear pressing cover is cirque structure, and the front inner wall of rear pressing cover is processed with the internal thread matching with burning chamber shell rear end outside thread, the end, rear end of the rear pressing cover ring-type positioning table that extends internally out, and the internal diameter of this ring-type positioning table is greater than the internal diameter of burning chamber shell rear end;
Pressure relief ring is the ring structure that brass material processes, and the shear pressure of pressure relief ring and the safe-working pressure of motor match; The internal diameter of pressure relief ring is less than the external diameter of jet pipe ring-type screens platform, and the external diameter of pressure relief ring is greater than the internal diameter of rear pressing cover ring-type positioning table.
Pressure relief ring is enclosed within the rear end of jet pipe ring-type screens platform, make the axial screens of ear end face of pressure relief ring and jet pipe ring-type screens platform, the front end of jet pipe inserts the rear end of burning chamber shell, and by the grate screens forward in burning chamber shell, rear pressing cover is threaded in the rear end of burning chamber shell, and pressure relief ring is clamped between burning chamber shell ear end face and rear pressing cover ring-type positioning table, and then the ring-type screens platform of jet pipe front end is clamped between grate and pressure relief ring.
Working principle
When rocket motor is normally worked, the high temperature and high pressure gas that propellant combustion produces, through jet pipe ejection, for rocket provides Driving force; When in the time there are abnormal conditions, pressure jump reaches the pressure of setting, the stressed pressure relief ring that first outwards cuts off of jet pipe, makes jet pipe ejection make motor pressure release, thereby the burning chamber shell of protection motor is not destroyed, and avoids causing engine explosions.
Beneficial effect
The utility model, by being directly connected by pressure relief ring with burning chamber shell at jet pipe, has ensured Security in fire trial process, and the possibility of having avoided motor to blast in abnormal conditions, can be widely used in rocket motor field.
Brief description of the drawings
Fig. 1 is the structural representation of traditional rocket motor;
Fig. 2 is the rocket motor structure schematic diagram of the utility model band decompression protection device;
Wherein 1-burning chamber shell, 2-rear pressing cover, 3-pressure relief ring, 4-jet pipe.
Embodiment
Below in conjunction with drawings and Examples, content of the present utility model is further described.
Embodiment
A kind of rocket motor with decompression protection device of the present utility model, as shown in Figure 2, comprises burning chamber shell 1, rear pressing cover 2, pressure relief ring 3, jet pipe 4;
The rear end outer wall of burning chamber shell 1 is processed with outside thread;
The front end end of jet pipe 4 extends outward ring-type screens platform, and the internal diameter of the external diameter of this ring-type screens platform and burning chamber shell 1 rear end matches;
Rear pressing cover 2 is cirque structure, the front inner wall of rear pressing cover 2 is processed with the internal thread matching with burning chamber shell 1 rear end outside thread, the end, rear end of the rear pressing cover 2 ring-type positioning table that extends internally out, the internal diameter of this ring-type positioning table is greater than the internal diameter of burning chamber shell 1 rear end;
The ring structure that pressure relief ring 3 processes for brass material, the shear pressure of pressure relief ring 3 and the safe-working pressure of motor match; The internal diameter of pressure relief ring 3 is less than the external diameter of jet pipe 4 ring-type screens platforms, and the external diameter of pressure relief ring 3 is greater than the internal diameter of rear pressing cover 2 ring-type positioning tables.
Pressure relief ring 3 is enclosed within the rear end of jet pipe 4 ring-type screens platforms, make the axial screens of ear end face of pressure relief ring 3 and jet pipe 4 ring-type screens platforms, the front end of jet pipe 4 inserts the rear end of burning chamber shell 1, and by the grate screens forward in burning chamber shell 1, rear pressing cover 2 is threaded in the rear end of burning chamber shell 1, and pressure relief ring 3 is clamped between burning chamber shell 1 ear end face and rear pressing cover 2 ring-type positioning tables, and then the ring-type screens platform of jet pipe front end is clamped between grate and pressure relief ring 3.
Claims (2)
1. the rocket motor with decompression protection device, is characterized in that: comprise burning chamber shell, rear pressing cover, pressure relief ring, jet pipe;
The rear end outer wall of burning chamber shell is processed with outside thread;
The front end end of jet pipe extends outward ring-type screens platform, and the external diameter of this ring-type screens platform and the internal diameter of burning chamber shell rear end match;
Rear pressing cover is cirque structure, and the front inner wall of rear pressing cover is processed with the internal thread matching with burning chamber shell rear end outside thread, the end, rear end of the rear pressing cover ring-type positioning table that extends internally out, and the internal diameter of this ring-type positioning table is greater than the internal diameter of burning chamber shell rear end;
Pressure relief ring is ring structure, and the shear pressure of pressure relief ring and the safe-working pressure of motor match; The internal diameter of pressure relief ring is less than the external diameter of jet pipe ring-type screens platform, and the external diameter of pressure relief ring is greater than the internal diameter of rear pressing cover ring-type positioning table;
Pressure relief ring is enclosed within the rear end of jet pipe ring-type screens platform, make the axial screens of ear end face of pressure relief ring and jet pipe ring-type screens platform, the front end of jet pipe inserts the rear end of burning chamber shell, and by the grate screens forward in burning chamber shell, rear pressing cover is threaded in the rear end of burning chamber shell, and pressure relief ring is clamped between burning chamber shell ear end face and rear pressing cover ring-type positioning table, and then the ring-type screens platform of jet pipe front end is clamped between grate and pressure relief ring.
2. a kind of rocket motor with decompression protection device as claimed in claim 1, is characterized in that: pressure relief ring is that brass material processes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420221159.1U CN204003155U (en) | 2014-04-30 | 2014-04-30 | A kind of rocket motor with decompression protection device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420221159.1U CN204003155U (en) | 2014-04-30 | 2014-04-30 | A kind of rocket motor with decompression protection device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204003155U true CN204003155U (en) | 2014-12-10 |
Family
ID=52043168
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420221159.1U Expired - Fee Related CN204003155U (en) | 2014-04-30 | 2014-04-30 | A kind of rocket motor with decompression protection device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204003155U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104612858A (en) * | 2015-01-29 | 2015-05-13 | 南京理工大学 | Adjustable double-pulse solid rocket engine jet pipe testing device |
| CN105089853A (en) * | 2015-08-25 | 2015-11-25 | 南京理工大学 | Combined exhaust pipe for solid rocket engine |
| CN110749536A (en) * | 2019-10-16 | 2020-02-04 | 南京理工大学 | Solid rocket engine thermal protection material ablation experimental device |
| CN112324594A (en) * | 2020-11-06 | 2021-02-05 | 湖北航天技术研究院总体设计所 | Test equipment for solid rocket engine combustion |
| CN112431691A (en) * | 2020-11-12 | 2021-03-02 | 西安长峰机电研究所 | Low-damage solid rocket engine shell structure |
-
2014
- 2014-04-30 CN CN201420221159.1U patent/CN204003155U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104612858A (en) * | 2015-01-29 | 2015-05-13 | 南京理工大学 | Adjustable double-pulse solid rocket engine jet pipe testing device |
| CN105089853A (en) * | 2015-08-25 | 2015-11-25 | 南京理工大学 | Combined exhaust pipe for solid rocket engine |
| CN110749536A (en) * | 2019-10-16 | 2020-02-04 | 南京理工大学 | Solid rocket engine thermal protection material ablation experimental device |
| CN110749536B (en) * | 2019-10-16 | 2022-04-01 | 南京理工大学 | Solid rocket engine thermal protection material ablation experimental device |
| CN112324594A (en) * | 2020-11-06 | 2021-02-05 | 湖北航天技术研究院总体设计所 | Test equipment for solid rocket engine combustion |
| CN112324594B (en) * | 2020-11-06 | 2023-08-18 | 湖北航天技术研究院总体设计所 | Solid rocket engine simulated combustion test equipment |
| CN112431691A (en) * | 2020-11-12 | 2021-03-02 | 西安长峰机电研究所 | Low-damage solid rocket engine shell structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20141210 Termination date: 20170430 |