CN218431765U - Aircraft fuel oil discharging tool - Google Patents
Aircraft fuel oil discharging tool Download PDFInfo
- Publication number
- CN218431765U CN218431765U CN202222997045.3U CN202222997045U CN218431765U CN 218431765 U CN218431765 U CN 218431765U CN 202222997045 U CN202222997045 U CN 202222997045U CN 218431765 U CN218431765 U CN 218431765U
- Authority
- CN
- China
- Prior art keywords
- sleeve
- pipe
- sleeve pipe
- funnel
- ejector
- 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.)
- Active
Links
Images
Landscapes
- Loading And Unloading Of Fuel Tanks Or Ships (AREA)
Abstract
The utility model provides an aircraft fuel discharges instrument, includes a funnel, a spiro union at the first sleeve pipe of funnel lower extreme, a activity cup joints the second sleeve pipe at first sleeve pipe lower extreme, one set establishes reset spring on first sleeve pipe and second cover, and a setting is at the intraductal ejector pin subassembly of funnel, first sleeve pipe and second sleeve. This first sleeve pipe lower extreme is provided with the first spacing ring of evagination, and second sleeve pipe upper end is provided with the second spacing ring of evagination, and first spacing ring cooperates with the second spacing ring for first sleeve pipe can be flexible in the second sleeve pipe. The ejector rod component comprises an ejector cone and an ejector pipe; the outer diameter of the tip cone is smaller than the inner diameter of the ejector rod, a cross connecting frame is arranged at an opening at the upper end in the ejector pipe, and the bottom of the tip cone is fixedly connected with the ejector pipe into a whole through the cross connecting frame. The aircraft fuel oil discharging tool of present case, stable in structure, easy operation, convenient to use can aim at the last fuel drain valve of aircraft fast, and not only the oil drain is efficient, still can effectively prevent to counterpoint and inaccurate fuel overflow that leads to.
Description
Technical Field
The utility model relates to an aircraft fuel discharging equipment field especially relates to an aircraft fuel discharging tool.
Background
At present, civil aviation airliners can carry out maintenance work regularly in order to ensure the functionality, reliability and safety of the systems. The fuel tank is used as an important part of a civil aircraft, and can be regularly checked and maintained, otherwise, microorganisms are easily bred at the junction of water and fuel oil after the water and crystal are deposited on the fuel tank, so that the structure of the fuel tank is corroded, oil leakage is caused, or the structure of a large wing of an airplane of the whole fuel tank is corroded, microorganisms can enter an engine along a fuel pipeline, and the engine is damaged. The fuel tank sediment discharge and fuel sampling detection work are two basic works in a course and a fixed inspection. The aircraft fuel emission tools commonly used in many aircraft maintenance bases today have the following disadvantages:
1) The oil discharge funnel is immovable, so that the oil discharge valve is blocked, the tip cone of the oil discharge tool cannot be aligned to the oil discharge valve on the airplane, the tip cone of the oil discharge tool is easy to contact the skin of the airplane in a staggered manner, and the potential safety hazard of damaging the skin of the airplane is caused;
2) Oil drain funnel and aircraft covering can not laminate completely, lead to the fuel to spill over, spill over on the fuel spatters maintainer's eyes or skin, can injure eyes, long term contact fuel can lead to the skin damage, and the fuel that spills over can pollute the airport apron, has the hidden danger of catching fire.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an aircraft fuel discharges instrument to overcome the shortcoming and not enough among the prior art.
In order to achieve the purpose, the scheme is realized through the following technical scheme:
the utility model provides an aircraft fuel discharges instrument, includes a funnel, a spiro union at the first sleeve pipe of funnel lower extreme, a activity cup joints at the second sleeve pipe of first sleeve pipe lower extreme, the reset spring of establishing on first sleeve pipe and second cover, and a setting is at the intraductal ejector pin subassembly of funnel, first sleeve pipe and second cover, and is further:
the lower end of the first sleeve is provided with a convex first limiting ring, the upper end of the second sleeve is provided with a convex second limiting ring, and the first limiting ring is matched with the second limiting ring, so that the first sleeve sleeved in the second sleeve can extend and retract in the second sleeve;
the ejector rod assembly comprises an ejector cone arranged at the upper part and an ejector pipe arranged at the lower part; the outer diameter of the tip cone is smaller than the inner diameter of the ejector rod, a cross connecting frame is integrally arranged at the upper end opening in the ejector pipe, and the bottom of the tip cone is fixedly connected with the ejector pipe into a whole through the cross connecting frame.
Furthermore, still radial even protrusion is provided with a plurality of guide blocks on the inner wall of first sleeve upper end, and each guide block all cooperates with the outer wall contact of tip cone.
Preferably, the upper end of the return spring is connected with the lower end of the funnel and is connected with the top pipe.
Preferably, the top opening edge of the funnel is provided with an elastic sealing ring.
Preferably, the lower end of the funnel is provided with a first internal thread matched with a first external thread arranged at the upper end of the first sleeve.
Preferably, a second internal thread is arranged on the inner wall of the top pipe and above the cross-shaped connecting frame, and the second internal thread is matched with a second external thread arranged on the outer wall of the lower end of the second sleeve.
Preferably, the outer diameter of the top pipe is larger than that of the second casing pipe, so that a step is formed at the joint of the bottom end of the second casing pipe and the top end of the top pipe.
Preferably, the outer diameter of the first limiting ring on the first sleeve is equal to the inner diameter of the second sleeve, and the inner diameter of the second limiting ring on the second sleeve is equal to the outer diameter of the first sleeve.
Preferably, the outer diameter of the tip cone is smaller than the inner diameter of the first casing.
Compared with the prior art, the beneficial effects of the utility model are that:
1) Make spiro union integrative funnel and first sleeve move backward together through reset spring, in first sleeve contracts into the second sleeve, outside the tip cone stretches out the funnel, aim at the tip cone more easily and back open the fuel outlet valve on the aircraft in sight range, can prevent effectively that the counterpoint is inaccurate to lead to the fuel overflow, also avoids because the tip cone is counterpointed and is inaccurate to damage aircraft skin.
2) Through set up the guide block at first sleeve intraductal interval, set up the cross link of fretwork in the second sleeve pipe for the oil circuit is unblocked, and simple structure is practical.
3) Through set up elasticity sealing washer at funnel opening edge, can make funnel and aircraft skin laminate completely sealed, avoid the fuel overflow to cause extravagant and potential safety hazard.
4) The aircraft fuel oil discharging tool has the advantages of being stable in structure, simple to operate, convenient to use, capable of being quickly aligned to an oil discharging valve on an aircraft, and high in oil discharging efficiency.
In order to clearly understand the present invention, preferred embodiments of the present invention will be described below with reference to the accompanying drawings.
Drawings
Figure 1 is a cross-sectional view of the present invention along a central axis;
fig. 2 is a schematic structural view of the ejector rod assembly of the present invention;
fig. 3 is a schematic structural diagram of the first sleeve of the present invention;
fig. 4 is a schematic structural diagram of a second sleeve according to the present invention;
fig. 5 is an assembly diagram of the first sleeve and the second sleeve of the present invention;
fig. 6 is a schematic top view of the present invention;
fig. 7 is a reference diagram of the usage status of the present invention.
Detailed Description
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are used merely for convenience of description and for simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention. In the description of the present invention, "a plurality" means two or more unless otherwise specified.
Furthermore, the terms "first," "second," and the like, if any, are used for descriptive purposes only and are used primarily for distinguishing different devices, elements, or components (the specific types and configurations may be the same or different), and are not used for indicating or implying relative importance among the indicated devices, elements, or components, but are not to be construed as indicating or implying relative importance.
Referring to fig. 1-7, an aircraft fuel oil discharging tool includes a funnel 1, a first sleeve 2 screwed to the lower end of the funnel 1, a second sleeve 3 movably sleeved to the lower end of the first sleeve 2, a return spring 4 sleeved on the first sleeve 2 and the second sleeve 3, and a push rod assembly disposed in the funnel 1, the first sleeve 2 and the second sleeve 3. A first internal thread is arranged at the lower end of the funnel 1 and matched with a first external thread arranged at the upper end of the first sleeve 2; the lower end of the first sleeve 2 is provided with a convex first limiting ring 21, the upper end of the second sleeve 3 is provided with a convex second limiting ring 31, the outer diameter of the first limiting ring 21 on the first sleeve 2 is equal to the inner diameter of the second sleeve 3, the inner diameter of the second limiting ring 31 on the second sleeve 3 is equal to the outer diameter of the first sleeve 2, the first limiting ring 21 is matched with the second limiting ring 31, so that the first sleeve 2 sleeved in the second sleeve 3 can stretch up and down in the second sleeve 3, and the funnel 1 and the first sleeve 2 which are screwed together move up and down integrally under the action of the reset spring 4.
The ejector rod assembly comprises an ejector cone 51 arranged at the upper part and an ejector pipe 52 arranged at the lower part; the outer diameter of the tip cone 51 is smaller than the inner diameter of the ejector rod, a cross connecting frame 521 is integrally arranged at an opening at the upper end in the top pipe 52, the bottom of the tip cone 51 is fixedly connected with the top pipe 52 into a whole through the cross connecting frame 521, and an oil discharge channel formed by the outer wall of the tip cone 51 is communicated into the top pipe 52 due to the hollow arrangement of the cross connecting frame 521.
Further, the outer diameter of the tip cone 51 is smaller than the inner diameter of the first casing 2, so that the tip cone 51 is sleeved in the funnel 1, the first casing 2 and the second casing 3;
further, the outer diameter of the top pipe 52 is larger than that of the second sleeve 3, so that a step is formed at the joint of the bottom end of the second sleeve 3 and the top end of the top pipe 52; furthermore, a second internal thread is further arranged on the inner wall of the top pipe 52 and above the cross-shaped connecting frame 521, the second internal thread is matched with a second external thread arranged on the outer wall of the lower end of the second sleeve 3, so that the second sleeve 3 can be screwed with the top pipe 52, the upper end of the return spring 4 is connected to the bottom of the funnel 1, the lower end of the return spring 4 is connected to the top of the top pipe 52, and the funnel 1 and the first sleeve 2 which are screwed together move up and down integrally under the action of the return spring 4.
Further, in order to guarantee the stability of the integrated funnel 1 and the first sleeve 2 in the up-and-down movement, a plurality of guide blocks 22 are radially and uniformly protruded on the inner wall of the upper end of the first sleeve 2, and each guide block 22 is in contact fit with the outer wall of the tip cone 51, so that the integrated funnel 1 and the first sleeve 2 are guaranteed to be coaxial with the tip cone 51 in the up-and-down movement process.
Furthermore, funnel 1, its top opening edge is provided with elasticity sealing washer 11, and elasticity sealing washer 11 avoids oil drain in-process fish tail aircraft skin, also plays sealed oil drain's effect.
When the funnel is used specifically, the funnel 1 is pulled by a hand, the funnel 1 and the first sleeve 2 which are screwed into a whole move downwards against the elastic force of the reset spring 4, the first sleeve 2 retracts into the second sleeve 3, when the tip cone 51 exposes out of the funnel 1, the tip cone 514a is aligned and slightly props against an oil drain valve on an airplane, then the funnel 1 is loosened, and the funnel 1 moves upwards under the elastic force action of the reset spring 4 until the elastic sealing ring 11 of the funnel 1 props against the airplane skin. The oil discharge valve is opened through the tip cone 514a, meanwhile, as the guide blocks 22 in the first sleeve 2 are arranged at intervals, discharged aircraft fuel oil sequentially flows through the first sleeve 2 and the second sleeve 3 from the gap of the guide blocks 22 after passing through the funnel 1, flows into the jacking pipe 52 through the hollowed-out cross connecting frame 521, and finally flows into the oil receiving barrel 6 connected to the jacking pipe 52.
Compared with the prior art, the beneficial effects of the utility model are that: the aircraft fuel oil discharging tool of present case, stable in structure, easy operation, convenient to use can aim at the last fuel drain valve of aircraft fast, and not only the oil drain is efficient, still can effectively prevent to counterpoint and inaccurate fuel overflow that leads to.
The above-mentioned embodiments only represent some embodiments of the present invention, and the description thereof is specific and detailed, but not to be construed as limiting the scope of the present invention. It should be noted that, for those skilled in the art, without departing from the spirit of the present invention, several variations and modifications can be made, which are within the scope of the present invention.
Claims (9)
1. The utility model provides an aircraft fuel discharges instrument, includes a funnel, a spiro union at the first sleeve pipe of funnel lower extreme, a activity cup joints at the second sleeve pipe of first sleeve pipe lower extreme, the reset spring of establishing on first sleeve pipe and second cover, and a setting is at the intraductal ejector pin subassembly of funnel, first sleeve pipe and second cover, its characterized in that:
the lower end of the first sleeve is provided with a convex first limiting ring, the upper end of the second sleeve is provided with a convex second limiting ring, and the first limiting ring is matched with the second limiting ring, so that the first sleeve sleeved in the second sleeve can extend and retract in the second sleeve;
the ejector rod assembly comprises an ejector cone arranged at the upper part and an ejector pipe arranged at the lower part; the outer diameter of the tip cone is smaller than the inner diameter of the ejector rod, a cross connecting frame is integrally arranged at the upper end opening in the ejector pipe, and the bottom of the tip cone is fixedly connected with the ejector pipe into a whole through the cross connecting frame.
2. An aircraft fuel discharge tool according to claim 1 wherein: still radially evenly the protrusion is provided with a plurality of guide blocks on the inner wall of first sleeve pipe upper end, each guide block all with the outer wall contact cooperation of tip cone.
3. An aircraft fuel discharge tool according to claim 1 wherein: the upper end of the reset spring is connected with the lower end of the funnel and is connected with the top pipe.
4. An aircraft fuel discharge tool according to claim 1 wherein: the top opening edge of the funnel is provided with an elastic sealing ring.
5. An aircraft fuel discharge tool according to claim 1 wherein: the funnel lower extreme is provided with first internal thread and the first external screw thread cooperation that first sleeve pipe upper end set up.
6. An aircraft fuel discharge tool according to claim 1 wherein: and a second internal thread is arranged on the inner wall of the jacking pipe and above the cross connecting frame, and the second internal thread is matched with a second external thread arranged on the outer wall of the lower end of the second sleeve.
7. An aircraft fuel discharge tool according to claim 1 wherein: the outer diameter of the top pipe is larger than that of the second sleeve pipe, so that a step is formed at the joint of the bottom end of the second sleeve pipe and the top end of the top pipe.
8. An aircraft fuel discharge tool according to claim 1 wherein: the outer diameter of the first limiting ring on the first sleeve is equal to the inner diameter of the second sleeve, and the inner diameter of the second limiting ring on the second sleeve is equal to the outer diameter of the first sleeve.
9. An aircraft fuel discharge tool according to claim 1 wherein: the outer diameter of the tip cone is smaller than the inner diameter of the first casing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222997045.3U CN218431765U (en) | 2022-11-10 | 2022-11-10 | Aircraft fuel oil discharging tool |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222997045.3U CN218431765U (en) | 2022-11-10 | 2022-11-10 | Aircraft fuel oil discharging tool |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218431765U true CN218431765U (en) | 2023-02-03 |
Family
ID=85073949
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222997045.3U Active CN218431765U (en) | 2022-11-10 | 2022-11-10 | Aircraft fuel oil discharging tool |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218431765U (en) |
-
2022
- 2022-11-10 CN CN202222997045.3U patent/CN218431765U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN218431765U (en) | Aircraft fuel oil discharging tool | |
| CN210987486U (en) | Agricultural micro-sprinkling irrigation device | |
| CN210450021U (en) | Compressor cleaning tool of turbofan engine | |
| CN209646761U (en) | A kind of pressure-type atomizer automatic block clearing device | |
| CN110463579A (en) | A kind of sparge pipe mechanism with filter device | |
| CN211174512U (en) | Blowdown collection device for air compressor unit | |
| CN208845931U (en) | A kind of external screw thread jack catchs type connector | |
| CN209247532U (en) | A kind of nozzle tube hydraulic pressure tooling | |
| CN209277854U (en) | A kind of sucker rod paraffin scraper free of cleaning | |
| CN220270894U (en) | Underground sampling device | |
| CN209403371U (en) | Integrated form hangs spraying device | |
| CN214690221U (en) | Aircraft fuel deposits drainage instrument | |
| CN214002067U (en) | Deposition equipment is put to big aircraft tank | |
| CN215479691U (en) | Aircraft fuel deposits discharges instrument | |
| CN221559230U (en) | Quick clamping device of aviation pipeline cleaning machine | |
| CN210519694U (en) | Automatic anti-blocking water spraying device for water-saving irrigation | |
| CN208705301U (en) | A kind of exterior decoration engineering-environment pollution monitoring device | |
| CN205562053U (en) | Protection device for integration warm -pressing changer | |
| CN214882409U (en) | Dual-purpose water nozzle joint | |
| CN217466315U (en) | Novel coal slurry sampler | |
| CN213269849U (en) | Combined well site dosing funnel | |
| CN218717212U (en) | Visual oil collecting device | |
| CN219613922U (en) | Diarrhea sampler | |
| CN221465498U (en) | Digital display type water quality detector | |
| US20230024940A1 (en) | Two-stroke pumping method and oil production device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |