CN216207797U - Aircraft fuel sampling device - Google Patents
Aircraft fuel sampling device Download PDFInfo
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- CN216207797U CN216207797U CN202122634820.4U CN202122634820U CN216207797U CN 216207797 U CN216207797 U CN 216207797U CN 202122634820 U CN202122634820 U CN 202122634820U CN 216207797 U CN216207797 U CN 216207797U
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- funnel
- aircraft fuel
- sampling device
- ejector rod
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Abstract
The utility model discloses an aircraft fuel sampling device, and belongs to the technical field of sampling devices. The aircraft fuel sampling device comprises a mandril, a sampling funnel and a sampling bottle; the sampling funnel is internally provided with a connecting part which is detachably connected with the ejector rod; the lower extreme and the sample bottle detachably sealing connection of sample funnel. The sampling device provided by the utility model has the advantages of simple structure, small volume and convenience in use, can effectively improve the sampling efficiency, reduces the sampling pollution risk, and is suitable for various types of fuel oil sampling interfaces.
Description
Technical Field
The utility model relates to the technical field of sampling devices, in particular to an aircraft fuel sampling device.
Background
In order to ensure the safety of the airplane and passengers, in the airplane assembly process in the field of aviation, before the airplane is put into use and before the airplane takes off, working personnel can strictly detect various functional parameters of the airplane, wherein the functional parameters comprise airplane fuel sampling detection, and the conditions of whether a complete machine oil supply system is intact, can normally work and the like are judged according to factors such as the pollution degree or the water content of the fuel. Impurities in aviation fuel oil can not only cause corrosion of system metal parts, but also pollute the atmosphere, and are easy to be oxidized and condensed into colloids and precipitates in the fuel to cause blockage of a combustion system and the like, which has very important influence on the normal flight of an airplane in the air.
Present aircraft fuel sampling device usually adopts to go on like traditional fuel sedimentation pipe etc. deposit the frock, but in fact aircraft fuel's sample oil mass is very little, and traditional fuel sedimentation pipe volume is great, is not convenient for on the one hand to be connected with the sampling bottle, increases the sample pollution risk of fuel easily, and on the other hand leads to using inconvenience, the sample inefficiency because bulky.
SUMMERY OF THE UTILITY MODEL
In order to overcome the defects of the prior art, the utility model aims to provide the aircraft fuel sampling device which is simple in structure, small in size and convenient to use, can effectively improve sampling efficiency, reduces sampling pollution risks, and is suitable for fuel sampling interfaces of various models.
In order to solve the problems, the technical scheme adopted by the utility model is as follows:
an aircraft fuel sampling device comprises a mandril, a sampling funnel and a sampling bottle; the sampling funnel is internally provided with a connecting part which is detachably connected with the ejector rod; the lower extreme and the sample bottle detachably sealing connection of sample funnel.
As a preferred embodiment of the present invention, the connection portion includes a connection ring disposed on a central axis of the sampling funnel and a plurality of supporting angle pieces uniformly distributed along a radial direction of the sampling funnel, one end of each supporting angle piece is connected to an inner wall of the sampling funnel, and the other end of each supporting angle piece is connected to an outer wall of the connection ring.
As a preferred embodiment of the present invention, the inner wall of the connection ring is provided with an internal thread, and the lower end of the ejector rod is provided with an external thread; the ejector rod is in threaded connection with the connecting ring.
In a preferred embodiment of the present invention, the connection portion is connected to the inner wall of the sampling funnel by welding or insertion.
As a preferred embodiment of the utility model, the supporting angle sheet and the connecting ring are integrally formed with the sampling funnel.
As a preferable embodiment of the utility model, the upper end part of the ejector rod is of a round head or a cross head structure.
In a preferred embodiment of the present invention, the ejector pin is provided with a protrusion.
As a preferred embodiment of the utility model, the lower end of the sampling funnel is screwed or clamped with the sampling bottle.
Compared with the prior art, the utility model has the beneficial effects that:
the aircraft fuel sampling device provided by the utility model comprises the replaceable ejector rod, the sampling funnel and the sampling bottle, wherein the sampling funnel and the sampling bottle are detachably and hermetically connected, so that the convenient and fast quick connection is realized, and the sampling pollution risk can be effectively reduced; the ejector rod and the sampling funnel are detachably connected in a screw connection mode and the like, so that the ejector rod can be quickly replaced, and the device can be suitable for precipitation valves or sampling interfaces of different airplanes in various models. Therefore, the fuel sampling connector is simple in structure, small in size, convenient to use, capable of effectively improving sampling efficiency and reducing sampling pollution risks, and applicable to fuel sampling connectors of various models.
Drawings
FIG. 1 is a perspective view of an aircraft fuel sampling assembly in accordance with the present invention;
FIG. 2 is a front view of an aircraft fuel sampling assembly in accordance with the present invention;
FIG. 3 is a cross-sectional view taken along line A-A of FIG. 2 in accordance with the present invention;
FIG. 4 is a top view of an aircraft fuel sampling assembly in accordance with the present invention;
the reference numbers illustrate: 1. a top rod; 11. a protrusion; 2. a sampling funnel; 21. a connecting portion; 22. a connecting ring; 23. a support corner piece; 3. and (6) sampling a bottle.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
As shown in fig. 1 to 4, the aircraft fuel sampling device of the present invention includes a push rod 1 for pushing open a one-way fuel sampling valve on an aircraft fuel sampling interface, a sampling funnel 2 for guiding the fuel, and a sampling bottle 3 for collecting the sampled fuel. The sampling funnel 2 is internally provided with a connecting part 21 for mounting the ejector rod 1, the connecting part 21 is detachably connected with the ejector rod 1, and the ejector rod 1 can be conveniently replaced while the aircraft fuel oil deposit valve can be quickly jacked open so as to be suitable for aircraft fuel oil sampling interfaces of different models; the lower extreme and the 3 detachably sealing connection of sampling bottle of sampling funnel 2 not only realize convenient and fast's high-speed joint, can also effectively reduce the sample and pollute the risk.
Specifically, as shown in fig. 1, 3-4, the external contour of the sampling funnel 2 is similar to that of a general funnel in the prior art, except that a connecting part 21 for installing the push rod 1 is provided inside the sampling funnel 2. Specifically, the connecting portion 21 includes a connecting ring 22 and a plurality of supporting angle pieces 23, wherein the connecting ring 22 is disposed on the central axis of the sampling funnel 2 and is used for mounting the carrier rod 1, the plurality of supporting angle pieces 23 are uniformly distributed along the radial direction of the sampling funnel 2, and one end of each supporting angle piece 23 is connected with the inner wall of the sampling funnel 2, and the other end is connected with the outer wall of the connecting ring 22. A hollow structure is formed between the supporting angle piece 23 and the inner wall of the sampling funnel 2 and the outer wall of the connecting ring 22, so that the fuel can smoothly flow into the sampling bottle 3. In order to improve the structural stability and ensure the smoothness of sampling, the number of the supporting angle pieces 23 is 3-5. The supporting angle sheet 23 can be connected with the inner wall of the sampling funnel 2 and the outer wall of the connecting ring 22 by welding or adopting a groove splicing mode and the like; the connecting part 21 can be made by integral molding and then welded or inserted with the inner wall of the sampling funnel 2. Similarly, the supporting angle piece 23, the connection ring 22 and the sampling funnel 2 may be integrally formed.
The ejector rod 1 is arranged in the connecting ring 22, so that the ejector rod 1 is positioned on the central axis of the sampling funnel 2, and the function of preventing fuel oil from leaking is achieved. Specifically, the inner wall of the connecting ring 22 is provided with an internal thread, and the lower end of the ejector rod 1 is provided with an external thread; the ejector rod 1 is in threaded connection with the connecting ring 22, and the ejector rod 1 is more easily detached from the sampling funnel 2 in a threaded connection mode and is replaced quickly. Through changing ejector pin 1 of different tip structures such as button head, cross, can make sampling device can be applicable to putting of different aircraft and deposit the valve, consequently the upper end tip of ejector pin 1 is button head or cross structure. Further, be provided with the arch 11 that plays limiting displacement on the ejector pin 1 to guarantee that the tip of ejector pin 1 is higher than the terminal surface of sampling funnel 2 all the time.
As shown in FIGS. 1 to 4, the lower end of the sampling funnel 2 is screwed or engaged with the sampling bottle 3. Sampling bottle 3's structure is similar with current fuel container bottle, and current fuel container bottle generally is equipped with the lid, lid and fuel container bottle bottleneck screwed connection, and there is the external screw thread in current fuel container bottle bottleneck promptly, consequently, if choose for use current fuel container bottle as sampling bottle 3, then the connected mode of preferred spiro union, be provided with the internal thread on sampling funnel 2 lower extreme promptly, through the cooperation of internal and external screw thread, can ensure that the fuel does not leak outward, and the pollution risk is little in the sample link.
When the sampling device is used, the corresponding ejector rod 1 is installed according to the interface form of the aircraft deposit valve, the clean sampling bottle 3 is screwed into the threaded interface of the sampling funnel 2, and then the deposit valve of the fuel tank is jacked open for sampling.
In conclusion, the aircraft fuel sampling device is simple in structure, small in size and convenient to use, can effectively improve sampling efficiency, reduces sampling pollution risks, and is suitable for fuel sampling interfaces of various models.
The above embodiments are only preferred embodiments of the present invention, and the protection scope of the present invention is not limited thereby, and any insubstantial changes and substitutions made by those skilled in the art based on the present invention are within the protection scope of the present invention.
Claims (8)
1. An aircraft fuel sampling device which characterized in that: comprises a mandril, a sampling funnel and a sampling bottle; the sampling funnel is internally provided with a connecting part which is detachably connected with the ejector rod; the lower extreme and the sample bottle detachably sealing connection of sample funnel.
2. An aircraft fuel sampling device according to claim 1, wherein: connecting portion are including setting up go-between and several along the radial evenly distributed's of sample funnel support angle piece on the axis of sample funnel, the one end of supporting the angle piece with the interior wall connection of sample funnel, the other end with the outer wall connection of go-between.
3. An aircraft fuel sampling device according to claim 2, wherein: the inner wall of the connecting ring is provided with internal threads, and the lower end of the ejector rod is provided with external threads; the ejector rod is in threaded connection with the connecting ring.
4. An aircraft fuel sampling device according to claim 2 or claim 3, wherein: the connecting part is connected with the inner wall of the sampling funnel through welding or splicing.
5. An aircraft fuel sampling device according to claim 2 or claim 3, wherein: the supporting angle sheet, the connecting ring and the sampling funnel are integrally formed.
6. An aircraft fuel sampling device according to claim 1, wherein: the upper end part of the ejector rod is of a round head or cross head structure.
7. An aircraft fuel sampling device according to claim 1 or claim 6, wherein: the ejector rod is provided with a bulge.
8. An aircraft fuel sampling device according to claim 1, wherein: the lower extreme of sampling funnel and sampling bottle spiro union or joint.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122634820.4U CN216207797U (en) | 2021-10-29 | 2021-10-29 | Aircraft fuel sampling device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122634820.4U CN216207797U (en) | 2021-10-29 | 2021-10-29 | Aircraft fuel sampling device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216207797U true CN216207797U (en) | 2022-04-05 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122634820.4U Active CN216207797U (en) | 2021-10-29 | 2021-10-29 | Aircraft fuel sampling device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216207797U (en) |
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2021
- 2021-10-29 CN CN202122634820.4U patent/CN216207797U/en active Active
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