CN219694431U - Comprehensive test bed for oxygen cylinder of aircraft - Google Patents
Comprehensive test bed for oxygen cylinder of aircraft Download PDFInfo
- Publication number
- CN219694431U CN219694431U CN202321003261.XU CN202321003261U CN219694431U CN 219694431 U CN219694431 U CN 219694431U CN 202321003261 U CN202321003261 U CN 202321003261U CN 219694431 U CN219694431 U CN 219694431U
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- CN
- China
- Prior art keywords
- bottle
- ring
- bottle cover
- base
- aircraft
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- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 title claims abstract description 45
- 239000001301 oxygen Substances 0.000 title claims abstract description 45
- 229910052760 oxygen Inorganic materials 0.000 title claims abstract description 45
- 238000001514 detection method Methods 0.000 claims abstract description 34
- 230000007246 mechanism Effects 0.000 claims abstract description 24
- 238000000034 method Methods 0.000 claims abstract description 9
- 238000009434 installation Methods 0.000 claims abstract description 4
- 238000007789 sealing Methods 0.000 claims description 15
- 238000003466 welding Methods 0.000 claims description 5
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 abstract description 9
- 239000007789 gas Substances 0.000 abstract description 8
- 238000000926 separation method Methods 0.000 abstract 1
- 230000008569 process Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 210000001503 joint Anatomy 0.000 description 3
- 238000003032 molecular docking Methods 0.000 description 2
- 238000010998 test method Methods 0.000 description 2
- 238000009423 ventilation Methods 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 229910000746 Structural steel Inorganic materials 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
Abstract
The utility model provides an aircraft oxygen bottle comprehensive test platform, includes the board, still includes detection mechanism, detection mechanism that carries out aircraft oxygen bottle test is installed to board one side, detection mechanism includes base, bottle cover, bottom ring, screw hole, bolt, go-between, pneumatic cylinder and end ring, and the supporting bottle cover that carries out the outer survey method of aircraft oxygen bottle detects of installing in base top, when installing or taking out the gas cylinder, firstly with the inside water of bottle cover discharge, control the jack-up of pneumatic cylinder power end can be through go-between with the whole jack-up of bottle cover and base separation, and then conveniently take out or install the gas cylinder that awaits measuring that is located the bottle cover inside, reset the bottle cover after the installation is put in place and screw in the fixed of bottle cover can be accomplished at junction screw in the bolt, make things convenient for follow-up detection operation, compare in traditional oxygen bottle detection test platform, need not handling equipment, greatly reduced the occupation space of test bench, the location and the taking out of convenient gas cylinder.
Description
Technical Field
The utility model relates to the technical field of aviation accessory detection, in particular to an aircraft oxygen cylinder comprehensive test bed.
Background
The oxygen bottle is a high-pressure container for storing and transporting oxygen, is generally formed by hot stamping and pressing alloy structural steel, is cylindrical, is applied to places such as hospitals, emergency stations, sanatories and the like, is marked with steel marks of working pressure, test pressure, volume, weight and other information on the shoulder of the gas bottle, and in the field of aircrafts, an oxygen accessory for aviation mainly comprises an oxygen bottle, an oxygen generator and an oxygen mask, is provided with an oxygen bottle structure for storing oxygen in a matching way no matter civil aviation or other aviation systems, and needs to be subjected to various tests during maintenance, repair and detection.
The existing aircraft oxygen cylinder detection operation process has the following defects: the main offline detection method of the aircraft oxygen cylinder is external detection, the position accessory of the detection equipment is usually provided with lifting equipment such as a balance crane or a gantry crane in a matched manner to lift the air cylinder, so that the whole of the lifting equipment is conveniently inserted into the detection cylinder sleeve, the whole occupation space of the lifting equipment is large, particularly when a plurality of groups of air cylinders are continuously detected, the space of a detection chamber is very occupied, the auxiliary movement alignment is also needed manually in the operation process, and the aircraft oxygen cylinder comprehensive test bed is very inconvenient.
Disclosure of Invention
The utility model mainly aims to provide an aircraft oxygen cylinder comprehensive test bed, which can conveniently realize the installation and positioning of an air cylinder to be tested by a detection mechanism installed on one side of the machine, and can effectively solve the problems in the background technology.
In order to achieve the above purpose, the technical scheme adopted by the utility model is as follows:
the utility model provides an aircraft oxygen bottle comprehensive test platform, includes the board, still includes detection mechanism, detection mechanism that carries out aircraft oxygen bottle test is installed to board one side, detection mechanism includes base, bottle cover, bottom ring, screw hole, bolt, go-between, pneumatic cylinder and end ring, and the supporting bottle cover that carries out the outer survey method of aircraft oxygen bottle and detect of installing in base top, bottle cover bottom welding has the bottom ring that corresponds with the base position, and bottle cover periphery welding has the go-between and the pneumatic cylinder power take off end is connected with the go-between bottom.
Further, the bottle cover comprises a sealing mechanism, wherein the sealing mechanism is arranged between the bottle cover and the base, the sealing mechanism comprises an insert ring, an annular groove and a rubber cushion, the insert ring is welded at the top of the base, and the annular groove corresponding to the insert ring is formed in the bottom end inside the bottle cover; the ring is fixed with at the base top, and the annular has been seted up to bottle cover bottom, when docking bottle cover bottom with the base, aligns annular with inserting the ring earlier, moves down bottle cover in-process and makes to insert the ring to the annular inside, is located the cushion of inserting the ring surface and hugs closely the annular internal surface, and then plays fine sealed effect in the bottle cover bottom after connecting, avoids the problem of water leakage and pressure release.
Further, threaded holes are formed in the corresponding positions of the base and the inside of the bottom ring, and bolts are detachably connected between the threaded holes; after the bottle sleeve is installed in place, the threaded holes are aligned and screwed with bolts, so that the bottle sleeve and the base can be fixed together.
Further, an end ring which is butted with the opening end of the oxygen cylinder of the aircraft to be tested is arranged at the top end inside the cylinder sleeve; the end ring can be in butt joint with the opening end of the oxygen cylinder of the aircraft to be tested and is connected with the platform ventilation equipment.
Further, rubber gaskets for improving the sealing performance of the joint are adhered to the inner surface and the outer surface of the insert ring, and the insert ring corresponds to the ring groove in position and is inserted into the ring groove; the tightness of the joint at the bottom of the bottle sleeve is ensured by the rubber cushion.
Compared with the prior art, the utility model has the following beneficial effects: the bottle sleeve is arranged at the top of the base, the oxygen bottle of the aircraft to be detected is arranged in the bottle sleeve during detection, water is injected after the interior of the bottle sleeve is completely sealed, then the bottle is pressurized, and then the gas bottle is subjected to an external detection test, when the gas bottle is installed or taken out, the water in the bottle sleeve is firstly discharged, then the power end of the hydraulic cylinder is controlled to jack up, the whole bottle sleeve can be jacked up through the connecting ring and separated from the base, and then the gas bottle to be detected in the bottle sleeve is conveniently taken out or installed, the bottle sleeve is reset after the installation is in place, and the bottle sleeve can be fixed by screwing bolts into the connecting position, so that the subsequent detection operation is convenient, compared with the traditional oxygen bottle detection test stand, the lifting equipment is not needed, the occupied space of the test stand is greatly reduced, and the gas bottle is conveniently positioned and taken out; the ring is fixed with at the base top, and the annular has been seted up to bottle cover bottom, when docking bottle cover bottom with the base, aligns annular with inserting the ring earlier, moves down bottle cover in-process and makes to insert the ring to the annular inside, is located the cushion of inserting the ring surface and hugs closely the annular internal surface, and then plays fine sealed effect in the bottle cover bottom after connecting, avoids the problem of water leakage and pressure release.
Drawings
Fig. 1 is a schematic diagram of the overall structure of an aircraft oxygen cylinder comprehensive test stand.
Fig. 2 is a schematic diagram of a structure of an aircraft oxygen cylinder comprehensive test stand after the jacking of a cylinder cover.
Fig. 3 is a schematic diagram of the structure of the joint between the bottom of the bottle cover and the base of the comprehensive test stand for the oxygen bottle of the aircraft.
In the figure: 1. a machine table; 2. a detection mechanism; 201. a base; 202. a bottle sleeve; 203. a bottom ring; 204. a threaded hole; 205. a bolt; 206. a connecting ring; 207. a hydraulic cylinder; 208. an end ring; 3. a sealing mechanism; 301. inserting a ring; 302. a ring groove; 303. rubber cushion.
Detailed Description
The utility model is further described in connection with the following detailed description, in order to make the technical means, the creation characteristics, the achievement of the purpose and the effect of the utility model easy to understand.
As shown in fig. 1-3, the comprehensive test stand for the oxygen cylinder of the aircraft comprises a machine 1 and further comprises a detection mechanism 2, wherein the detection mechanism 2 for performing the oxygen cylinder test of the aircraft is arranged on one side of the machine 1, the detection mechanism 2 comprises a base 201, a cylinder sleeve 202, a bottom ring 203, a threaded hole 204, bolts 205, a connecting ring 206, a hydraulic cylinder 207 and an end ring 208, the cylinder sleeve 202 for performing the external test method detection of the oxygen cylinder of the aircraft is arranged on the top of the base 201 in a matched mode, a bottom ring 203 corresponding to the position of the base 201 is welded at the bottom of the cylinder sleeve 202, a connecting ring 206 is welded at the periphery of the cylinder sleeve 202, and a power output end of the hydraulic cylinder 207 is connected with the bottom of the connecting ring 206.
The bottle cover comprises a bottle cover 202, a base 201 and a sealing mechanism 3, wherein the sealing mechanism 3 is arranged between the bottle cover 202 and the base 201, the sealing mechanism 3 comprises an insert ring 301, a ring groove 302 and a rubber pad 303, the insert ring 301 is welded at the top of the base 201, and the ring groove 302 corresponding to the insert ring 301 is arranged at the bottom end inside the bottle cover 202; the top of the base 201 is fixed with the insert ring 301, the bottom end of the bottle sleeve 202 is provided with the annular groove 302, when the bottom of the bottle sleeve 202 is in butt joint with the base 201, the annular groove 302 is aligned with the insert ring 301, the insert ring 301 is inserted into the annular groove 302 in the process of downwards moving the bottle sleeve 202, the rubber pad 303 positioned on the surface of the insert ring 301 is tightly attached to the inner surface of the annular groove 302, and then the bottom of the connected bottle sleeve 202 plays a good sealing role, so that the problems of water leakage and pressure relief are avoided.
Screw holes 204 are formed in corresponding positions in the base 201 and the bottom ring 203, bolts 205 are detachably connected between the screw holes 204, and an end ring 208 butted with the opening end of an oxygen cylinder of the aircraft to be tested is mounted at the top end in the cylinder sleeve 202; after the bottle sleeve 202 is installed in place, the bottle sleeve 202 and the base 201 can be fixed together by aligning the threaded holes 204 and screwing in bolts 205, and the end ring 208 can be abutted with the opening end of the oxygen bottle of the aircraft to be tested and connected with the ventilation equipment of the machine 1.
Wherein, rubber pads 303 for improving the sealing performance of the joint are adhered to the inner surface and the outer surface of the insert ring 301, and the insert ring 301 corresponds to the ring groove 302 in position and is inserted into the ring groove 302; the tightness of the bottom connection part of the bottle sleeve 202 is ensured by the rubber cushion 303.
It should be noted that, when the comprehensive test stand for the aircraft oxygen bottle is used, the bottle sleeve 202 is installed at the top of the base 201, the aircraft oxygen bottle to be tested is placed in the bottle sleeve 202 during detection, the bottle sleeve 202 is completely sealed and then filled with water and then pressurized into the bottle, and then the external test method detection test is carried out on the air bottle, when the air bottle is installed or taken out, the water in the bottle sleeve 202 is firstly discharged, then the power end of the hydraulic cylinder 207 is controlled to lift up the whole bottle sleeve 202 and separate from the base 201 through the connecting ring 206, so that the air bottle to be tested positioned in the bottle sleeve 202 is conveniently taken out or installed, the bottle sleeve 202 is reset after being installed in place, and the fixing of the bottle sleeve 202 can be completed at the connecting position by screwing in the bolt 205, so that the subsequent detection operation is convenient, compared with the traditional oxygen bottle detection test stand, no lifting equipment is needed, the occupied space of the test stand is greatly reduced, and the positioning and the taking out of the air bottle are convenient; the top of the base 201 is fixed with the insert ring 301, the bottom end of the bottle sleeve 202 is provided with the annular groove 302, when the bottom of the bottle sleeve 202 is in butt joint with the base 201, the annular groove 302 is aligned with the insert ring 301, the insert ring 301 is inserted into the annular groove 302 in the process of downwards moving the bottle sleeve 202, the rubber pad 303 positioned on the surface of the insert ring 301 is tightly attached to the inner surface of the annular groove 302, and then the bottom of the connected bottle sleeve 202 plays a good sealing role, so that the problems of water leakage and pressure relief are avoided.
The foregoing has shown and described the basic principles and main features of the present utility model and the advantages of the present utility model. It will be understood by those skilled in the art that the present utility model is not limited to the embodiments described above, and that the above embodiments and descriptions are merely illustrative of the principles of the present utility model, and various changes and modifications may be made without departing from the spirit and scope of the utility model, which is defined in the appended claims. The scope of the utility model is defined by the appended claims and equivalents thereof.
Claims (5)
1. The utility model provides an aircraft oxygen bottle comprehensive test platform, includes board (1), its characterized in that still includes detection mechanism (2), detection mechanism (2) that carry out aircraft oxygen bottle test are installed to board (1) one side, detection mechanism (2) are including base (201), bottle cover (202), bottom ring (203), screw hole (204), bolt (205), go-between (206), pneumatic cylinder (207) and end ring (208), and bottle cover (202) that carries out the outer survey method detection of aircraft oxygen bottle are installed in supporting the installation in base (201) top, bottle cover (202) bottom welding has bottom ring (203) that corresponds with base (201) position, and bottle cover (202) periphery welding has go-between (206) and pneumatic cylinder (207) power take off end is connected with go-between (206) bottom.
2. The aircraft oxygen cylinder combination test stand of claim 1, wherein: still include sealing mechanism (3), install sealing mechanism (3) between bottle cover (202) and base (201), sealing mechanism (3) are including inserting ring (301), annular (302) and cushion (303), and the welding of base (201) top has inserts ring (301) and bottle cover (202) inside bottom has seted up and has inserted ring (301) position and correspond annular (302).
3. The aircraft oxygen cylinder combination test stand of claim 1, wherein: screw holes (204) are formed in corresponding positions inside the base (201) and the bottom ring (203), and bolts (205) are detachably connected between the screw holes (204).
4. The aircraft oxygen cylinder combination test stand of claim 1, wherein: an end ring (208) butted with the opening end of the oxygen cylinder of the aircraft to be tested is arranged at the top end inside the cylinder sleeve (202).
5. The aircraft oxygen cylinder combination test stand of claim 2, wherein: rubber pads (303) for improving the sealing performance of the joint are adhered to the inner surface and the outer surface of the insert ring (301), and the insert ring (301) corresponds to the ring groove (302) in position and is inserted into the ring groove (302).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321003261.XU CN219694431U (en) | 2023-04-28 | 2023-04-28 | Comprehensive test bed for oxygen cylinder of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321003261.XU CN219694431U (en) | 2023-04-28 | 2023-04-28 | Comprehensive test bed for oxygen cylinder of aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219694431U true CN219694431U (en) | 2023-09-15 |
Family
ID=87963477
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321003261.XU Active CN219694431U (en) | 2023-04-28 | 2023-04-28 | Comprehensive test bed for oxygen cylinder of aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219694431U (en) |
-
2023
- 2023-04-28 CN CN202321003261.XU patent/CN219694431U/en active Active
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