CN219734630U - A spray tube sealing closure for rocket engine gas tightness detects - Google Patents
A spray tube sealing closure for rocket engine gas tightness detects Download PDFInfo
- Publication number
- CN219734630U CN219734630U CN202222883304.XU CN202222883304U CN219734630U CN 219734630 U CN219734630 U CN 219734630U CN 202222883304 U CN202222883304 U CN 202222883304U CN 219734630 U CN219734630 U CN 219734630U
- Authority
- CN
- China
- Prior art keywords
- spray pipe
- engine
- cover body
- blanking cover
- circular plate
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- 239000007921 spray Substances 0.000 title claims abstract description 27
- 238000007789 sealing Methods 0.000 title claims abstract description 20
- 238000001514 detection method Methods 0.000 claims abstract description 15
- 238000000748 compression moulding Methods 0.000 claims abstract description 4
- 239000000463 material Substances 0.000 claims abstract description 4
- 238000004519 manufacturing process Methods 0.000 abstract description 4
- 238000012360 testing method Methods 0.000 description 5
- 238000009530 blood pressure measurement Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000004806 packaging method and process Methods 0.000 description 2
- 238000004200 deflagration Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
Landscapes
- Examining Or Testing Airtightness (AREA)
- Testing Of Engines (AREA)
Abstract
The utility model discloses a spray pipe sealing plug for rocket engine air tightness detection, which comprises a plug body and an inflation interface arranged on the plug body; the middle part of the blanking cover body is a circular plate with the diameter matched with the diameter of the throat part of the spray pipe, the outer edge of the circular plate extends forwards in the axial direction to form a conical limiting surface, and the taper of the conical limiting surface is matched with the taper of the inner wall of the front section of the spray pipe; the inflation interface is arranged in the middle of the circular plate of the blanking cover body; the spray pipe sealing cover is adhered to the rear end of the inner wall of the front section of the spray pipe through the conical limiting surface. The blanking cover body with the interface of aerifing adopts rubber material integrated compression moulding. The inflation interface adopts a male head of a pneumatic C-type quick connector. The sealing cover for the spray pipe simplifies the manufacturing process of engine parts, eliminates the hidden danger of sealing the engine caused by an inflation interface, and can realize the air tightness detection of the engine in a whole-bullet state.
Description
Technical Field
The utility model relates to a spray pipe sealing cover for rocket engine air tightness detection, and belongs to the technical field of engine quality detection.
Background
The tightness of the rocket engine plays a decisive role for the normal operation of the engine, and if the good tightness of the engine cannot be ensured, catastrophic accidents such as burning-through, deflagration and the like can occur in the operation process of the engine. Therefore, after the engine is assembled, an air tightness detection test is required, and the traditional test method is as follows: sealing and packaging two ends of the engine shell, arranging an inflation interface on a packaging cover at the front end of the engine shell, filling a gas medium with certain pressure into an inner cavity of the engine through the inflation interface on the engine, testing the gas pressure drop of the inner cavity of the engine after maintaining the pressure for a certain time, and if the gas pressure drop meets a qualified criterion, indicating that the air tightness of the engine is good. The above-mentioned gas tightness detects structure has the problem: 1) After the top cover is processed, the inflatable interface is welded on the top cover, and then the vent hole is drilled, so that the manufacturing process is complex; 2) After the air tightness of the engine is detected, the engine can be put into use after the air charging interface is plugged by adopting a tool, 100% tightness cannot be ensured by matching the air charging interface with the tool, and the air tightness of the engine plugged by the tool cannot be detected, so that potential tightness hazards exist in the engine; 3) Under the whole bullet state, the engine head has been connected with other cabin sections on the bullet, and the interface of aerifing is located the projectile body inside, can't carry out the gas tightness to the engine at this moment and detect. In general, for a whole bullet stored for a long time, in order to ensure the normal operation of an engine, the air tightness of the engine needs to be detected and confirmed before the engine is launched, and the detection work cannot be realized by the structure at present.
Disclosure of Invention
The utility model aims to solve the problems that an engine part is complex in manufacturing process, hidden danger exists in an engine and the air tightness of the engine cannot be detected in a full-bullet state due to an inflation structure in a traditional air tightness detection test, and provides a jet pipe sealing cover for rocket engine air tightness detection.
The utility model aims at realizing the following technical scheme:
the utility model relates to a spray pipe sealing plug for rocket engine air tightness detection, which comprises a plug body and an inflation interface arranged on the plug body;
the middle part of the blanking cover body is a circular plate with the diameter matched with the diameter of the throat part of the spray pipe, the outer edge of the circular plate extends forwards in the axial direction to form a conical limiting surface, and the taper of the conical limiting surface is matched with the taper of the inner wall of the front section of the spray pipe; the inflation interface is arranged in the middle of the circular plate of the blanking cover body; the spray pipe sealing cover is adhered to the rear end of the inner wall of the front section of the spray pipe through the conical limiting surface.
The blanking cover body with the interface of aerifing adopts rubber material integrated compression moulding.
The inflation interface adopts a male head of a pneumatic C-type quick connector.
Working process
When the rocket engine air tightness detection test is carried out, the inflation interface of the jet pipe sealing plug is connected with the air pipe provided with the pneumatic C-shaped quick connector female head, so that the pressurization and the pressure measurement of the engine air cavity can be realized.
Advantageous effects
According to the sealing cover of the spray pipe, an inflatable connector is omitted from being arranged on the top cover, so that the manufacturing process of engine parts is simplified; secondly, as the sealing plug is broken by flame after the engine is ignited, the hidden danger of sealing the engine caused by the inflation interface is eliminated; in addition, because the inflation interface is positioned at the spray pipe, the spray pipe is still exposed to the outside in the whole bullet state, so that the air tightness detection of the engine in the whole bullet state can be realized.
Drawings
FIG. 1 is a schematic illustration of the installation of a spout seal closure of the present utility model;
in the figure, a 1-blanking cover body and a 2-inflation interface are arranged.
Detailed Description
The utility model is further described below with reference to the drawings and examples:
examples
The utility model relates to a spray pipe sealing plug for rocket engine air tightness detection, which comprises a plug body 1 and an inflation interface 2 arranged on the plug body;
the middle part of the blanking cover body 1 is a circular plate with the diameter matched with the diameter of the throat part of the spray pipe, the outer edge of the circular plate is axially extended forward to form a conical limit surface, and the taper of the conical limit surface is matched with the taper of the inner wall of the front section of the spray pipe; the inflation interface is arranged in the middle of the circular plate of the blanking cover body; the spray pipe sealing cover is adhered to the rear end of the inner wall of the front section of the spray pipe through the conical limiting surface.
The blanking cover body 1 and the inflation interface 2 are integrally formed by compression molding of rubber materials.
The inflation interface 2 adopts a male head of a pneumatic C-type quick connector.
When the rocket engine air tightness detection test is carried out, the inflation interface 2 of the jet pipe sealing plug cover is connected with an air pipe provided with a pneumatic C-type quick connector female head, so that the pressurization and the pressure measurement of an engine air cavity can be realized.
Claims (3)
1. A spray tube sealing cap for rocket engine gas tightness detects, characterized by: comprises a blanking cover body and an inflation interface arranged on the blanking cover body;
the middle part of the blanking cover body is a circular plate with the diameter matched with the diameter of the throat part of the spray pipe, the outer edge of the circular plate extends forwards in the axial direction to form a conical limiting surface, and the taper of the conical limiting surface is matched with the taper of the inner wall of the front section of the spray pipe; the inflation interface is arranged in the middle of the circular plate of the blanking cover body; the spray pipe sealing cover is adhered to the rear end of the inner wall of the front section of the spray pipe through the conical limiting surface.
2. A nozzle seal cap for rocket motor air tightness detection as recited in claim 1, wherein: the blanking cover body with the interface of aerifing adopts rubber material integrated compression moulding.
3. A nozzle seal cap for rocket motor air tightness detection as claimed in claim 1 or 2, wherein: the inflation interface adopts a male head of a pneumatic C-type quick connector.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222883304.XU CN219734630U (en) | 2022-10-31 | 2022-10-31 | A spray tube sealing closure for rocket engine gas tightness detects |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222883304.XU CN219734630U (en) | 2022-10-31 | 2022-10-31 | A spray tube sealing closure for rocket engine gas tightness detects |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219734630U true CN219734630U (en) | 2023-09-22 |
Family
ID=88026499
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222883304.XU Active CN219734630U (en) | 2022-10-31 | 2022-10-31 | A spray tube sealing closure for rocket engine gas tightness detects |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219734630U (en) |
-
2022
- 2022-10-31 CN CN202222883304.XU patent/CN219734630U/en active Active
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