CN216240989U - Capping structure of solid rocket engine - Google Patents
Capping structure of solid rocket engine Download PDFInfo
- Publication number
- CN216240989U CN216240989U CN202122213341.5U CN202122213341U CN216240989U CN 216240989 U CN216240989 U CN 216240989U CN 202122213341 U CN202122213341 U CN 202122213341U CN 216240989 U CN216240989 U CN 216240989U
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- China
- Prior art keywords
- pressure
- cover
- spray pipe
- engine
- shearing
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Abstract
The utility model discloses a blocking cover structure of a solid rocket engine, and belongs to the field of solid rocket engines. The structure comprises a plugging cover and a spray pipe. The pressure-bearing surfaces of the plug cover are arc-shaped, the arc shape of the inner pressure is convex towards the pressure intensity direction, and the arc shape of the outer pressure surface is concave towards the pressure intensity direction; a shearing groove is reserved at the arc-shaped termination position of the inner pressure surface of the plug cover, and the diameter of the inner circle of the shearing groove is larger than that of the inner circle of the pressure-bearing surface of the spray pipe, so that the shearing ring is prevented from being damaged by stress when external pressure is applied; the depth of the shearing ring is adjusted according to the designed critical pressure, so that different charging and firing requirements are met; the blocking cover can directly bear high-pressure impact generated by launching, and parts of the blocking cover do not need to be protected, so that the scheme optimization of the mass, the mass center and the flight stability of the projectile body is facilitated; when the engine works normally, the sealed blanking cover maintains the minimum critical pressure of the engine charge, and when the preset pressure is reached, the shearing ring on the blanking cover is damaged, the blanking cover is smoothly opened, and the engine is normally ignited.
Description
Technical Field
The utility model belongs to the technical field of solid rocket engines, and particularly relates to a plug cover structure of an engine.
Background
The solid rocket engine is used as the second-stage power of the missile and is also part of the full missile structure. The bottom of the projectile body is subjected to impact from high pressure gas during firing (i.e., first stage power), and if the engine is in the form of a tail nozzle, the blanking member of the nozzle tube is subjected to a large impact force. The general missile design scheme is that a part is additionally arranged at the bottom of a missile body to protect a blocking cover part of an engine from being impacted by high-pressure gas during launching, and after the missile launches a launching barrel, the part is thrown away to create conditions for smooth opening of the blocking cover. The structure needs to additionally use a protective part, the weight of the missile body is increased, and meanwhile, the connection and the throwing-off design of the missile need to be considered.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a blocking cover structure of a solid rocket engine, which can not only bear high-pressure gas in a launching tube during launching by removing a protection component and enabling the blocking cover and the outlet end of a spray pipe to ensure the sealing property of a combustion chamber of the engine; and moreover, after the engine bears the impact of high-pressure gas during emission, the plug cover can still ensure the ignition critical pressure required during working and can be opened during normal working of the engine.
The purpose of the utility model is realized by the following technical scheme:
the utility model discloses a blocking cover structure of a solid rocket engine, which comprises a blocking cover and a spray pipe outlet end.
The pressure bearing surface of the plug cover is arc-shaped, the arc shape of the inner pressure is convex towards the pressure intensity direction, and the arc shape of the outer pressure surface is concave towards the pressure intensity direction;
a shearing groove is reserved at the arc-shaped termination position of the inner pressure surface of the plug cover, and the diameter of the inner circle of the shearing groove is larger than that of the inner circle of the pressure-bearing surface of the spray pipe, so that the shearing ring is prevented from being damaged by stress when external pressure is applied; the depth of the shearing ring is adjusted according to the designed critical pressure, and the requirements of different explosive charging and firing indexes are met.
The outlet end of the spray pipe is provided with a circular ring plane with a certain width bearing pressure;
the connection mode between blanking cover and the spray pipe is threaded connection, and the butt joint with the spray pipe and the later-stage replacement are convenient.
And coating a proper amount of sealant on the thread of the plug cover, mounting the plug cover to the outlet end of the spray pipe through the thread, completely attaching the shear ring on the plug cover to the pressure-bearing surface of the spray pipe in the assembling process to ensure that the plug cover is assembled in place, and completely sealing the plug cover through the sealant to ensure the sealing property of the combustion chamber of the engine.
The utility model discloses a working method of a blocking cover structure of a solid rocket engine, which comprises the following steps:
firstly, when in launching, the outer end surface of the blocking cover can bear the action of high-pressure gas in the launching tube, so that the sealing property of the engine combustion chamber is ensured; when the engine works, after the ignition device is triggered, the pressure in the combustion chamber is opened due to the fact that the shearing ring is damaged instantly only when the pressure in the combustion chamber reaches the critical pressure of engine charging, and normal ignition of the engine is guaranteed.
Has the advantages that:
1. the blocking cover structure of the solid rocket engine disclosed by the utility model can bear high-pressure impact generated by launching by independently depending on the blocking cover, does not need to design a part for protecting the blocking cover, and is convenient for the scheme optimization of the quality, the mass center and the flight stability of a projectile body.
2. According to the blocking cover structure of the solid rocket engine, when the engine works normally, the blocking cover maintains the minimum critical pressure of the charge of the engine, and when the design pressure is reached, a shearing ring on the blocking cover is damaged, the blocking cover is smoothly opened, and the engine is normally ignited.
Drawings
FIG. 1 is a schematic view of the closure of the present invention after installation of the outlet end of the spout.
Wherein: 1-blocking cover and 2-spraying pipe outlet end.
Fig. 2 is a schematic view of the structure of the blanking cover.
FIG. 3 is a schematic view of the nozzle outlet end configuration.
Detailed Description
For better illustrating the objects and advantages of the present invention, the following description is provided in conjunction with the accompanying drawings and examples.
As shown in figure 1, the utility model discloses a blocking cover structure of a solid rocket engine, which comprises a blocking cover 1 and a spray pipe outlet end 2.
As shown in fig. 2, the pressure-bearing surfaces of the blocking cover 1 are all arc-shaped, the arc shape of the internal pressure is convex towards the pressure intensity direction, and the arc shape of the external pressure surface is concave towards the pressure intensity direction;
as shown in fig. 2, a shearing groove is left at the circular arc-shaped end of the inner pressure surface of the blanking cap 1, and the inner circle diameter of the shearing groove is larger than that of the pressure-bearing surface of the nozzle. So as to prevent the shear ring from being damaged under external pressure. The depth of the shearing ring can be modified according to the designed critical pressure, and the requirements of different explosive charging and firing indexes can be met.
As shown in fig. 3, the outlet end of the nozzle is designed with a circular ring plane with a certain width for bearing pressure.
The connection mode between the plugging cover 1 and the spray pipe is threaded connection, and as shown in figure 1, the plugging cover is convenient to be butted with the spray pipe and replaced in the later period.
The assembly relation is as follows: the thread of the closure 1 is coated with a proper amount of sealant and then is mounted to the outlet end of the spout by means of the thread, it should be noted that during the assembly process, the shear ring of the closure 1 must be fully engaged with the bearing surface of the outlet end 2 of the spout to be assembled in place.
The utility model discloses a working method of a plug part structure of an engine, which comprises the following steps:
firstly, when in launching, the outer end surface of the blanking cover 1 can bear the action of high-pressure gas in a launching tube, so that the sealing property of a combustion chamber of an engine is ensured; when the engine works, after the ignition device is triggered, the pressure in the combustion chamber can be instantly opened (namely the shearing ring of the blanking cover 1 is damaged) only when the pressure in the combustion chamber reaches the critical pressure of engine charging, so that the normal ignition of the engine is ensured.
The above detailed description is provided to further explain the objects, technical solutions and advantages of the present invention in detail, and it should be understood that the above embodiments are merely exemplary embodiments of the present invention and are not intended to limit the scope of the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (2)
1. A blanking cover structure of a solid rocket engine is characterized in that: comprises a blanking cover (1) and a spray pipe outlet end (2);
the pressure bearing surface of the plug cover (1) is arc-shaped, the arc shape of the inner pressure is convex towards the pressure intensity direction, and the arc shape of the outer pressure surface is concave towards the pressure intensity direction;
a shearing groove is reserved at the arc-shaped termination position of the inner pressure surface of the plugging cover (1), and the diameter of the inner circle of the shearing groove is larger than that of the inner circle of the pressure-bearing surface of the spray pipe, so that the shearing ring is prevented from being damaged by stress when external pressure is applied; the depth of the shearing ring is adjusted according to the designed critical pressure, so that the requirements of different explosive charging and firing indexes are met;
the outlet end of the spray pipe is provided with a circular ring plane with a certain width bearing pressure;
coating a proper amount of sealant on the thread of the plug cover (1), and then installing the plug cover to the outlet end of the spray pipe through the thread, wherein in the assembling process, the shearing ring on the plug cover (1) is completely attached to the pressure-bearing surface of the spray pipe to ensure that the plug cover is assembled in place, and the complete sealing is realized through the sealant to ensure the sealing performance of the engine combustion chamber.
2. A solid rocket engine cap structure as recited in claim 1, wherein: the connection mode between blanking cover (1) and the spray pipe is threaded connection, and the butt joint with the spray pipe and the later-stage replacement are convenient.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122213341.5U CN216240989U (en) | 2021-09-14 | 2021-09-14 | Capping structure of solid rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122213341.5U CN216240989U (en) | 2021-09-14 | 2021-09-14 | Capping structure of solid rocket engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216240989U true CN216240989U (en) | 2022-04-08 |
Family
ID=80986397
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122213341.5U Expired - Fee Related CN216240989U (en) | 2021-09-14 | 2021-09-14 | Capping structure of solid rocket engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216240989U (en) |
-
2021
- 2021-09-14 CN CN202122213341.5U patent/CN216240989U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20220408 |
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| CF01 | Termination of patent right due to non-payment of annual fee |