CN221238588U - Solid rocket engine air tightness detection device - Google Patents
Solid rocket engine air tightness detection device Download PDFInfo
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- CN221238588U CN221238588U CN202323023562.1U CN202323023562U CN221238588U CN 221238588 U CN221238588 U CN 221238588U CN 202323023562 U CN202323023562 U CN 202323023562U CN 221238588 U CN221238588 U CN 221238588U
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- 238000001514 detection method Methods 0.000 title claims abstract description 30
- 239000007787 solid Substances 0.000 title claims abstract description 27
- 238000003780 insertion Methods 0.000 claims abstract description 18
- 230000037431 insertion Effects 0.000 claims abstract description 12
- 230000001105 regulatory effect Effects 0.000 claims description 18
- 238000012360 testing method Methods 0.000 abstract description 7
- 238000000034 method Methods 0.000 description 5
- 238000013461 design Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
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Abstract
The utility model relates to the technical field of solid engine detection, and particularly discloses a solid rocket engine air tightness detection device. The solid rocket engine air tightness detection device comprises a vacuum pump, a first pneumatic straight-through pipe joint, an air pipe, a second pneumatic straight-through pipe joint, a first chuck type pipe insertion joint, an adjusting valve, a clamp type tee joint, a second chuck type pipe insertion joint, a vacuum gauge, a third chuck type pipe insertion joint and an engine connection tool. The device is small and exquisite, the connected mode is simple, can unpack apart and carry and deposit, and is little to the requirement in place, the device commonality is good, only needs to change engine connection frock and can carry out the air tightness test of different products.
Description
Technical Field
The utility model relates to the technical field of solid engine detection, and particularly discloses a solid rocket engine air tightness detection device.
Background
When the solid rocket engine works, the inner cavity is filled with high-temperature high-pressure gas, and the solid rocket engine is in a dynamic gas flow condition, so that the working condition is extremely bad. In order to ensure high reliability of the engine, the engine is required to be subjected to an air tightness detection test at the time of assembly. Common methods for detecting the air tightness of the engine are a positive pressure method and a negative pressure method. The positive pressure method is to detect whether the air tightness is perfect by the condition that the gas medium filled into the engine leaks out of the engine. The negative pressure method is to establish negative pressure through vacuumizing and detect whether the air tightness is perfect according to the change condition of the vacuum degree.
Since the currently used air tightness detection device is a device configured in the 90 th century, there are a plurality of technical difficulties:
1) The air tightness detection device is originally configured in the 90 s, the system of the device is huge and is fixed in a special workshop to provide air tightness detection for specific engine products, and the device has poor adaptability to other products.
2) As the types of engine products increase and the caliber becomes larger, the universal design requirement of the airtight detection device is very urgent;
3) The existing device is too huge and can not meet the use requirements of carrying and multiple sites.
In order to solve the problems, the invention designs an air tightness detection method, and the air tightness detection of the solid rocket engine is realized through the design of two sets of air tightness detection devices.
Disclosure of utility model
The utility model is realized by the following technical scheme:
The solid rocket engine air tightness detection device comprises a vacuum pump 1, a first pneumatic straight-through pipe joint 2, an air pipe 3, a second pneumatic straight-through pipe joint 5, a first chuck type pipe insertion joint 6, an adjusting valve 8, a clamp type tee joint 9, a second chuck type pipe insertion joint 10, a vacuum gauge 11, a third chuck type pipe insertion joint 12 and an engine connecting tool 13;
The vacuum pump 1 is used for vacuumizing an engine, and an air suction hole of the vacuum pump 1 is connected with the head end of the air pipe 3 through a first pneumatic straight-through pipe joint 2; the tail end of the air pipe 3 is connected to one end of a first chuck type cannula connector 6 through a second pneumatic straight-through pipe connector 5, and the other end of the first chuck type cannula connector 6 is connected to the inlet of an adjusting valve 8; the outlet of the regulating valve 8 is connected with the inlet of the clamp tee 9, the first outlet of the clamp tee 9 is connected with a second chuck type cannula connector 10, and the second chuck type cannula connector 10 is connected with a vacuum gauge 11; the second outlet of the clamp tee 9 is connected to one end of an engine connecting tool 13 through a third chuck type cannula joint 12; the other end of the engine connecting tool 13 is connected with a solid rocket engine interface in a matching way.
Preferably, when the number of the air pipes 3 is not less than two, each air pipe 3 is connected through the PU air pipe straight-through quick-insertion pipe connector 4, so that the air tightness is ensured.
Preferably, the connection interface of the air pipe 3, the regulating valve 8, the quick-assembly clamp tee 9, the vacuum gauge 11 and the engine connection tool 13 is provided with a quick-assembly clamp 7 for clamping, so that the tightness is ensured.
Further, a first quick-mounting clamp 7-1 is arranged between the air pipe 3 and the regulating valve 8 and is clamped on the first chuck type cannula joint 6; a second quick-mounting clamp 7-2 is arranged between the outlet of the regulating valve 8 and the inlet of the clamp type tee 9; the first outlet of the clamp tee 9 and the vacuum gauge 11 are provided with a third quick-mounting clamp 7-3 which is clamped on the second chuck type cannula joint 10; the second outlet of the clamp tee 9 is provided with a fourth quick-assembly clamp 7-4 clamped on a third chuck type cannula joint 12.
Preferably, the first pneumatic straight pipe joint 2 and the second pneumatic straight pipe joint 5 are pneumatic threaded straight quick-insertion pipe joints.
Preferably, the first, second and third chuck type cannula fittings 6, 10 and 12 are all chuck type quick-fit cannula fittings.
Preferably, the clamp tee 9 is a quick-assembly clamp tee.
Preferably, the measuring range of the vacuum gauge 11 is not less than 2MPa.
Preferably, the engine connecting tool 13 is detachable and matches with different engines.
Preferably, the air pipe 3 adopts a high-pressure resistant PU pipe, the outer diameter is 10mm, the inner diameter is 6.5mm, and the working pressure is 10kgdf/cm 2 at normal temperature.
The beneficial effects of the utility model are as follows:
The utility model provides a solid rocket engine air tightness detection device which is small in size, simple in connection mode, capable of being detached, carried and stored, small in requirements on places, good in universality and capable of performing air tightness tests of different products only by replacing engine connection tools.
Drawings
Fig. 1 is a schematic structural diagram of an airtight detection apparatus for a solid rocket engine according to embodiment 1 of the present utility model.
Detailed Description
For a better description of the objects, technical solutions and advantages of the present utility model, reference is made to the following description with reference to the accompanying drawings and examples. It should be understood that the examples are only for illustrating technical effects of the present utility model and are not intended to limit the scope of the present utility model.
Example 1
The solid rocket engine air tightness detection device comprises a vacuum pump 1, a first pneumatic straight-through pipe joint 2, an air pipe 3, a second pneumatic straight-through pipe joint 5, a first chuck type pipe insertion joint 6, an adjusting valve 8, a clamp type tee joint 9, a second chuck type pipe insertion joint 10, a vacuum gauge 11, a third chuck type pipe insertion joint 12 and an engine connecting tool 13;
The vacuum pump 1 is used for vacuumizing an engine, and an air suction hole of the vacuum pump 1 is connected with the head end of the air pipe 3 through a first pneumatic straight-through pipe joint 2; the tail end of the air pipe 3 is connected to one end of a first chuck type cannula connector 6 through a second pneumatic straight-through pipe connector 5, and the other end of the first chuck type cannula connector 6 is connected to the inlet of an adjusting valve 8; the outlet of the regulating valve 8 is connected with the inlet of the clamp tee 9, the first outlet of the clamp tee 9 is connected with a second chuck type cannula connector 10, and the second chuck type cannula connector 10 is connected with a vacuum gauge 11; the second outlet of the clamp tee 9 is connected to one end of an engine connecting tool 13 through a third chuck type cannula joint 12; the other end of the engine connecting tool 13 is connected with a solid rocket engine interface in a matching way. The two sections of the air pipes 3 are connected through the PU air pipe straight-through quick-insertion pipe connector 4, so that air tightness is guaranteed. The air pipe 3 adopts a high pressure resistant PU pipe, the outer diameter is 10mm, the inner diameter is 6.5mm, and the working pressure is 10kgdf/cm 2 at normal temperature.
The air pipe 3, the regulating valve 8, the quick-mounting clamp tee joint 9, the vacuum gauge 11 and the connecting interface of the engine connecting tool 13 are provided with the quick-mounting clamp 7 for clamping, so that the tightness is ensured. A first quick-mounting clamp 7-1 is arranged between the air pipe 3 and the regulating valve 8 and is clamped on the first chuck type cannula joint 6; a second quick-mounting clamp 7-2 is arranged between the outlet of the regulating valve 8 and the inlet of the clamp type tee 9; the first outlet of the clamp tee 9 and the vacuum gauge 11 are provided with a third quick-mounting clamp 7-3 which is clamped on the second chuck type cannula joint 10; the second outlet of the clamp tee 9 is provided with a fourth quick-assembly clamp 7-4 clamped on a third chuck type cannula joint 12.
The first pneumatic straight-through pipe joint 2 and the second pneumatic straight-through pipe joint 5 are pneumatic threaded straight-through quick-insertion pipe joints; the first chuck type cannula connector 6, the second chuck type cannula connector 10 and the third chuck type cannula connector 12 are all chuck type quick-assembling cannula connectors; the clamp type tee joint 9 is a quick-mounting clamp type tee joint.
The measuring range of the vacuum gauge 11 is not less than 2MPa; the engine connecting tool 13 is detachable and is matched with different engines.
When in use, the utility model is characterized in that:
The detection device is connected first, and then the engine connection tool 13 is connected with the engine. The regulating valve 8 is opened, the vacuum pump 1 is started, the display of the vacuum gauge 11 is observed, when the vacuum degree reaches a specified value or is slightly higher than the specified value, the regulating valve 8 is screwed up, the air pipe 3 is pulled out, the vacuum pump 1 is closed, and then the regulating valve 8 is regulated to enable the vacuum degree to reach the specified requirement. The test piece is kept for a predetermined time as required, and the change in vacuum degree is observed to determine the air tightness. After the test is completed, the regulating valve 8 is slowly opened, so that the internal cavity of the engine is restored to normal pressure.
The engine was tested with a vacuum gauge requirement of 0.72Mpa and a holding time of 30min, and the results are shown in table 1:
table 1 record of air pressure during vacuum tightness test
| Test item | After vacuumizing | After 30 minutes | Qualification determination |
| Air pressure Mpa | 0.72 | 0.72 | Qualified product |
Claims (10)
1. The solid rocket engine air tightness detection device is characterized by comprising a vacuum pump (1), a first pneumatic straight-through pipe joint (2), an air pipe (3), a second pneumatic straight-through pipe joint (5), a first chuck type pipe insertion joint (6), an adjusting valve (8), a clamp type tee joint (9), a second chuck type pipe insertion joint (10), a vacuum gauge (11), a third chuck type pipe insertion joint (12) and an engine connection tool (13);
The vacuum pump (1) is used for vacuumizing the engine, and an air suction hole of the vacuum pump (1) is connected with the head end of the air pipe (3) through a first pneumatic straight-through pipe joint (2); the tail end of the air pipe (3) is connected to one end of a first chuck type cannula connector (6) through a second pneumatic straight-through pipe connector (5), and the other end of the first chuck type cannula connector (6) is connected to the inlet of the regulating valve (8); the outlet of the regulating valve (8) is connected with the inlet of the clamp tee (9), the first outlet of the clamp tee (9) is connected with the second chuck type cannula connector (10), and the second chuck type cannula connector (10) is connected with the vacuum gauge (11); the second outlet of the clamp tee (9) is connected to one end of an engine connecting tool (13) through a third chuck type cannula joint (12); the other end of the engine connecting tool (13) is connected with a solid rocket engine interface in a matching way.
2. The solid rocket engine air tightness detection device according to claim 1, wherein when the number of the air pipes (3) is not less than two, each air pipe (3) is connected through a PU air pipe straight-through quick-insertion pipe joint (4), so that air tightness is ensured.
3. The solid rocket engine air tightness detection device according to claim 1, wherein the connection interface of the air pipe (3), the regulating valve (8), the fast-assembling clamp tee joint (9), the vacuum meter (11) and the engine connection tool (13) is provided with a fast-assembling clamp (7) for clamping, so that the tightness is ensured.
4. A solid rocket engine tightness detection device according to claim 3, wherein a first quick-mounting clamp (7-1) is arranged between the air pipe (3) and the regulating valve (8) and is clamped on the first chuck type cannula joint (6); a second quick-mounting clamp (7-2) is arranged between the outlet of the regulating valve (8) and the inlet of the clamp type tee joint (9); a first outlet of the clamp tee joint (9) and the vacuum gauge (11) are provided with a third quick-mounting clamp (7-3) which is clamped on the second chuck type cannula joint (10); the second outlet of the clamp tee (9) is provided with a fourth quick-assembly clamp (7-4) which is clamped on the third chuck type cannula joint (12).
5. The solid rocket engine tightness detection device according to claim 1, wherein the first pneumatic straight-through pipe joint (2) and the second pneumatic straight-through pipe joint (5) are pneumatic threaded straight-through quick-insertion pipe joints.
6. The solid rocket engine tightness detection device according to claim 1, wherein the first chuck type cannula connector (6), the second chuck type cannula connector (10) and the third chuck type cannula connector (12) are chuck type quick-assembling cannula connectors.
7. The tightness detection device of a solid rocket engine according to claim 1, wherein the clamp tee (9) is a quick-assembly clamp tee.
8. The solid rocket engine tightness detection device according to claim 1, wherein the measuring range of the vacuum gauge (11) is not less than 2MPa.
9. The solid rocket engine tightness detection device according to claim 1, wherein the engine connecting tool (13) is detachable and is matched with different engines.
10. The solid rocket engine tightness detection device according to claim 1, wherein the air pipe (3) adopts a high-pressure-resistant PU pipe, the outer diameter is 10mm, the inner diameter is 6.5mm, and the working pressure is 10kgdf/cm 2 at normal temperature.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202323023562.1U CN221238588U (en) | 2023-11-09 | 2023-11-09 | Solid rocket engine air tightness detection device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202323023562.1U CN221238588U (en) | 2023-11-09 | 2023-11-09 | Solid rocket engine air tightness detection device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN221238588U true CN221238588U (en) | 2024-06-28 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202323023562.1U Active CN221238588U (en) | 2023-11-09 | 2023-11-09 | Solid rocket engine air tightness detection device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN221238588U (en) |
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- 2023-11-09 CN CN202323023562.1U patent/CN221238588U/en active Active
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