CN214451788U - Water outlet isolating ring and airplane - Google Patents
Water outlet isolating ring and airplane Download PDFInfo
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- CN214451788U CN214451788U CN202120235531.4U CN202120235531U CN214451788U CN 214451788 U CN214451788 U CN 214451788U CN 202120235531 U CN202120235531 U CN 202120235531U CN 214451788 U CN214451788 U CN 214451788U
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- annular
- annular gasket
- water outlet
- fuselage skin
- annular boss
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Abstract
The application relates to the technical field of aircraft structures, in particular to a water outlet isolating ring and an aircraft. The water outlet isolating ring comprises an annular gasket and an annular boss which are vertically connected, and the through hole of the annular gasket is communicated with the through hole of the annular boss. The annular boss can be inserted into a water drainage port of an aircraft fuselage skin and is hermetically bonded with the side wall of the water drainage port; the annular gasket can be attached to the outer wall surface of the fuselage skin and bonded in a sealing mode, the valve body of the drain valve of the airplane can penetrate through the annular gasket and the annular boss to be installed in the drain port, and the flange of the lower end position of the valve body abuts against the annular gasket. The fuselage skin in a preset range outside the water outlet is shielded by the water outlet isolation ring, so that the condensed water at the water outlet is prevented from contacting the fuselage skin, and the erosion of the condensed water to the fuselage skin is prevented; meanwhile, the normal installation, disassembly and maintenance of the drain valve cannot be influenced by the arrangement of the drain outlet isolating ring.
Description
Technical Field
The application relates to the technical field of aircraft structures, in particular to a water outlet isolating ring and an aircraft.
Background
The fuselage skin of the commercial passenger plane mostly uses aluminum alloy metal plates as fuselage skin materials, the lower part of the fuselage is provided with a plurality of water outlets from front to back, and each water outlet is internally provided with a drain valve for draining condensed water generated by the cold and hot alternating fuselage inner wall; at present, a water outlet of a fuselage skin is only protected by a paint layer and is often corroded by liquid flowing out of the water outlet, the fuselage skin belongs to an important structure of an airplane, corrosion damage cannot exceed 10% of the thickness, the airplane exceeding the damage standard needs stopping maintenance, the stopping maintenance needs at least 72 hours, and stopping time, labor and aviation material cost are high; in recent years, temporary airplane change caused by excessive corrosion of a water outlet in inspection before flight occurs for many times.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a waterspout cage and aircraft to reduce the corruption of fuselage covering in the waterspout department to a certain extent.
The utility model provides a water outlet isolation ring which is arranged between a water outlet and a water discharge valve at the lower end of a fuselage skin of an airplane; the water outlet isolating ring comprises an annular gasket and an annular boss; the annular boss is vertically arranged on the annular gasket, and the annular gasket is communicated with the annular boss; the annular boss can be inserted into the water outlet and bonded with the side wall of the water outlet, and the annular gasket is bonded with the outer wall surface of the fuselage skin; when the drain valve is installed to in the drain port, the valve body of drain valve can pass annular gasket with annular boss, just the flange of valve body with annular gasket counterbalance leans on.
Further, the annular gasket and the annular boss are made of PBT plastic.
Furthermore, one end, far away from the annular gasket, of the annular boss extends to the inner wall surface of the fuselage skin, and the annular boss and the inner wall surface of the fuselage skin are sealed in a fillet mode through a sealant.
Furthermore, the outer side wall of the annular gasket is in fillet sealing with the outer wall surface of the fuselage skin through the sealant.
Further, the sealant is PS870B1/2 sealant or PS870B2 sealant.
Furthermore, an arc chamfer or an inclined chamfer is formed at the transition joint of the outer side wall of the annular gasket and the end face of the annular gasket, which is far away from the fuselage skin side.
Further, when the chamfer of the outer side wall of the annular gasket is an inclined chamfer, the angle of the inclined chamfer is 30-45 degrees.
Further, the included angle between the outer side wall of the annular gasket and the end face, facing the fuselage skin, of the annular gasket is 30-45 degrees.
Further, the outer diameter of the annular gasket is 34-41mm, the inner diameters of the annular gasket and the annular boss are 18-25mm, and the outer diameter of the annular boss is 21-28 mm; the thicknesses of the annular gasket and the annular boss are respectively 1.0-1.5 mm.
Further, the annular gasket and the annular boss are integrally machined.
The utility model also provides an airplane, which comprises the waterspout isolating ring; a plurality of water outlets are formed in the fuselage skin of the aircraft, and each water outlet is provided with one water outlet isolation ring.
Compared with the prior art, the beneficial effects of the utility model are that:
the utility model provides a outlet isolating ring includes annular gasket and annular boss, and annular boss sets up perpendicularly on one side face of annular gasket, and the coaxial setting of annular boss and annular gasket for the through-hole of annular gasket is linked together with the through-hole of annular boss. The annular boss is matched with the water outlet at the lower end of the fuselage skin, so that the annular boss can be inserted into the water outlet, and the contact surface of the annular boss and the water outlet is coated with sealant, so that the annular boss and the water outlet are sealed and bonded together; the annular gasket is attached to the outer wall surface of the fuselage skin facing the outer side of the fuselage, and the annular gasket is arranged around the water outlet on the fuselage skin; meanwhile, the contact surfaces of the annular gasket and the fuselage skin are bonded together in a sealing mode, so that the water outlet isolation ring is bonded at the water outlet in a sealing mode, and the outer wall surface of the fuselage skin in the preset range outside the water outlet can be shielded through the annular gasket due to the fact that the annular gasket has the preset width. Be used for installing the drain valve in the drain outlet, the valve body of drain valve can pass annular gasket and annular boss in order to stretch into the fuselage inside, and the flange of valve body lower extreme position supports and leans on the annular gasket.
Therefore, when condensed water on the inner side of the fuselage flows out of the fuselage through the drain valve, the fuselage skin in a preset range on the outer side of the drain port can be shielded through the drain port isolating ring, the condensed water cannot contact the outer wall surface of the fuselage skin, the drain port isolating ring is bonded with the fuselage skin through a sealant, the condensed water cannot enter between the drain port isolating ring and the fuselage skin, the condensed water is prevented from contacting with the fuselage skin, and the erosion of the condensed water on the fuselage skin is prevented; meanwhile, the normal installation, disassembly and maintenance of the drain valve cannot be influenced by the arrangement of the drain outlet isolating ring.
The utility model also provides an aircraft, include outlet isolating ring, therefore the aircraft also has the beneficial effect of outlet isolating ring.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the technical solutions in the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
Fig. 1 is a schematic structural view of a water outlet isolation ring according to an embodiment of the present invention;
fig. 2 is a schematic structural view of a drain opening isolating ring assembled in a drain opening according to an embodiment of the present invention.
Reference numerals:
1-a water outlet isolating ring, 11-an annular gasket, 12-an annular boss, 2-a valve body, 21-a flange, 3-a support component and 4-a fuselage skin.
Detailed Description
The technical solution of the present invention will be described clearly and completely with reference to the accompanying drawings, and obviously, the described embodiments are some, but not all embodiments of the present invention.
The components of the embodiments of the present invention, as generally described and illustrated in the figures herein, may be arranged and designed in a wide variety of different configurations. Thus, the following detailed description of the embodiments of the present invention, presented in the accompanying drawings, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention.
Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
A waterspout isolator ring and an aircraft according to some embodiments of the present application are described below with reference to fig. 1 and 2.
The application provides a water outlet isolating ring 1 which is arranged between water outlet drain valves at the lower end of a fuselage skin 4 of an aircraft; the water outlet isolating ring 1 comprises an annular gasket 11 and an annular boss 12; the annular boss 12 is vertically arranged on the annular gasket 11, and the annular gasket 11 is communicated with the annular boss 12; the annular boss 12 can be inserted into the water outlet and bonded with the side wall of the water outlet, and the annular gasket 11 is bonded with the outer wall surface of the fuselage skin 4; when the drain valve is installed in the drain port, the valve body 2 of the drain valve can pass through the annular gasket 11 and the annular boss 12, and the flange 21 of the valve body 2 abuts against the annular gasket 11.
In this embodiment, the drain isolator ring 1 is intended to be arranged at a drain at the lower end of a fuselage skin 4 of an aircraft; as shown in fig. 1, the drain opening spacer ring 1 includes an annular gasket 11 and an annular boss 12; the annular gasket 11 is a circular flat gasket, a through hole with a preset diameter is formed in the center of the annular gasket 11, and the through hole of the annular gasket 11 penetrates through two ends of the annular gasket 11 in the thickness direction; the annular boss 12 is a cylindrical sleeve, a through hole penetrating through both ends of the annular boss 12 in the length direction is also formed at the center of the annular boss 12, and the through hole of the annular boss 12 and the through hole of the annular gasket 11 have the same diameter. The annular boss 12 is vertically arranged on one side plate surface of the annular gasket 11, and the annular boss 12 and the annular gasket 11 are coaxially arranged, so that the through hole of the annular gasket 11 is communicated with the through hole of the annular boss 12.
As shown in fig. 2, the annular boss 12 is adapted to the water discharge port, so that the annular boss 12 can be inserted into the water discharge port at the lower end of the fuselage skin 4, and the outer side wall of the annular boss 12 abuts against the side wall of the water discharge port; sealing glue is coated on the contact surface of the annular boss 12 and the water outlet, so that the annular boss 12 and the water outlet are sealed and bonded together; when the annular boss 12 is bonded in the water drainage port, the annular gasket 11 is attached to the outer wall surface of the fuselage skin 4 facing the outer side of the fuselage, and the annular gasket 11 is arranged around the water drainage port on the fuselage skin 4; meanwhile, the contact surface of the annular gasket 11 and the fuselage skin 4 is coated with sealant, so that the annular gasket 11 and the fuselage skin 4 are bonded together in a sealing manner, the water outlet isolation ring 1 is bonded at the water outlet in a sealing manner, and the outer wall surface of the fuselage skin 4 in a predetermined range outside the water outlet can be shielded through the annular gasket 11 due to the fact that the annular gasket 11 has a predetermined width.
The outlet is used for installing the drain valve, and the fuselage skin 4 is installed supporting component 3 towards the inside wall of fuselage on and the position department that corresponds the outlet, and supporting component 3 is used for fixing the valve body 2 of drain valve. When the drain valve is installed, the valve body 2 of the drain valve needs to extend into the machine body from the outer side of the machine body through the drain port so as to be connected with the support component 3.
The through hole of the annular boss 12 and the through hole of the annular gasket 11 are matched with the valve body 2 of the drain valve, so that the valve body 2 of the drain valve can sequentially penetrate through the annular gasket 11 and the annular boss 12, and the upper end of the valve body 2 of the drain valve extends into the machine body to be connected with the support component 3; meanwhile, a flange 21 at the lower end of the valve body 2, which is positioned at the outer side of the machine body, is abutted against the annular gasket 11, and the size of the annular gasket 11 is larger than that of the flange 21; therefore, when condensed water on the inner side of the fuselage flows out of the fuselage through the drain valve, the fuselage skin 4 in a preset range on the outer side of the drain port can be shielded through the drain port isolation ring 1, the condensed water cannot contact the outer wall surface of the fuselage skin 4, the drain port isolation ring 1 is bonded with the fuselage skin 4 through sealant, the condensed water cannot enter between the drain port isolation ring 1 and the fuselage skin 4, the condensed water is prevented from contacting with the fuselage skin 4, and the erosion of the fuselage skin 4 by the condensed water is prevented; meanwhile, the normal installation, disassembly and maintenance of the drain valve cannot be influenced by the arrangement of the drain outlet isolating ring 1.
It should be noted that, because the water outlet on the existing fuselage skin 4 is matched with the valve body 2 of the drain valve, the space between the water outlet and the drain valve is not enough to install the annular boss 12; therefore, when installing the drain opening spacer ring 1, first, the adapted drain opening spacer ring 1 is selected according to the size of the drain valve body 2 so that the valve body 2 of the drain valve can pass through the annular gasket 11 and the annular boss 12 of the drain opening spacer ring 1. Then flaring is carried out on the water outlet according to the size of the annular boss 12, so that the annular boss 12 can be inserted into the water outlet, and the side wall of the annular boss 12 is abutted against the side wall of the water outlet; thereby completing the installation of the water outlet isolation ring 1 and enabling the water outlet isolation ring 1 to be installed with the drain valve and the water outlet in a matching way.
In an embodiment of the present application, preferably, the annular gasket 11 and the annular boss 12 are integrally formed, and the material of the annular gasket 11 and the annular boss 12 is PBT plastic.
In the embodiment, the drain port isolating ring 1 is made of PBT plastic which is the same as that of the existing drain valve; so that the drain opening isolating ring 1 has high strength and good fatigue resistance.
The annular gasket 11 and the annular boss 12 are integrally formed, the edge of the through hole of the annular gasket 11 extends upwards to form a boss with a preset height along the direction vertical to the annular gasket 11, namely, the annular boss 12 coaxially arranged with the annular gasket 11 is formed, and the through hole of the annular boss 12 and the through hole of the annular gasket 11 are positioned on the same axis and are mutually communicated.
In one embodiment of the present application, preferably, one end of the annular boss 12 remote from the annular gasket 11 extends to the inner wall surface of the fuselage skin 4 and is fillet-sealed with the inner wall surface of the fuselage skin 4 by a sealant. The outer side wall of the annular gasket 11 is in fillet sealing with the outer wall surface of the fuselage skin 4 through sealant.
In the embodiment, preferably, one end of the drain port isolation ring 1, namely the upper end of the annular boss 12, which is far away from the annular gasket 11, extends to the upper port of the drain port facing the interior of the fuselage, the upper end of the annular boss 12 is flush with the inner wall surface of the fuselage skin 4 facing the interior of the fuselage, and the upper end surface of the annular boss 12 and the inner wall surface of the fuselage skin 4 are subjected to fillet sealing through a sealant, so that point corrosion of the fuselage skin 4 in an opening area of the drain port occurs to a certain extent; and meanwhile, condensed water can be further prevented from entering between the fuselage skin 4 and the waterspout isolating ring 1.
Preferably, the other end of the water outlet isolation ring 1, which is opposite to the upper end of the annular boss 12, is the outer edge of the annular gasket 11, and the outer edge of the annular gasket 11 is subjected to fillet sealing with the outer wall surface of the fuselage skin 4 through sealant; therefore, the tightness between the annular gasket 11 and the fuselage skin 4 is ensured, condensed water is prevented from entering between the annular gasket 11 and the fuselage skin 4, the opening between the annular gasket 11 and the fuselage skin 4 is subjected to fillet sealing through sealant, and the potential corrosion between the waterspout isolating ring 1 and the fuselage sealing skin is also avoided.
In one embodiment of the present application, the sealant is preferably a PS870B1/2 sealant or a PS870B2 sealant.
In this embodiment, the sealant for sealing and bonding the joint surface of the waterspout isolating ring 1 and the fuselage skin 4 is preferably a PS870B1/2 sealant or a PS870B2 sealant; meanwhile, the fillet sealing of the drain opening isolating ring 1 and the fuselage sealing cover also adopts PS870B1/2 sealant or PS870B2 sealant.
The PS870B1/2 sealant or the PS870B2 sealant has good corrosion resistance, and can be used as fillet sealing to effectively prevent the fuselage skin 4 from generating potential corrosion; meanwhile, the sealant has higher strength and better capability of resisting structural deformation, so that the water outlet isolation ring 1 and the fuselage skin 4 are bonded more tightly.
In one embodiment of the present application, preferably, the outer side wall of the annular gasket 11 is arc-shaped; or the outer side wall of the annular gasket 11 is a slope with a preset inclination angle with the end surface of the annular gasket 11; and when the chamfer of the outer side wall of the annular gasket 11 is an inclined chamfer, the angle of the inclined chamfer is 30-45 degrees.
In this embodiment, the end face of the annular shim 11 facing away from the fuselage skin 4, i.e. the transition between the lower end face of the annular shim 11 and the outer side wall of the annular shim 11, has an arc chamfer or bevel chamfer, and when the transition is a bevel chamfer, the angle of the bevel chamfer is 30 ° to 45 °. Thereby improve the pneumatics on fuselage surface through setting up arc chamfer and inclined plane chamfer, also prevent simultaneously to a certain extent that the liquid that the fuselage outside flows down from gathering at the kneck of annular gasket 11 and fuselage skin 4 to further block the contact of comdenstion water and fuselage skin 4, avoid the corruption of fuselage skin 4 of outlet opening part.
In one embodiment of the present application, preferably, the outer diameter of the annular gasket 11 is 34-41mm, the inner diameters of the annular gasket 11 and the annular boss 12 are 18-25mm, and the outer diameter of the annular boss 12 is 21-28 mm; the thicknesses of the annular gasket 11 and the annular boss 12 are respectively 1.0-1.5 mm; so that the annular gasket 11 and the annular boss 12 are matched with the valve body 2 of the drain valve, and the fuselage skin 4 in the area near the drain port is shielded by the annular gasket 11 to avoid the erosion of the fuselage skin 4 by the condensed water.
The present application also provides an aircraft comprising a waterspout isolator ring 1 according to any of the embodiments above; a plurality of water outlets are formed on a fuselage skin 4 of the airplane, and a water outlet isolation ring 1 is respectively arranged at each water outlet.
In this embodiment, the aircraft comprises a waterspout cage 1, a plurality of waterspouts are provided on a fuselage skin 4 at the lower end of the fuselage of the aircraft, and a waterspout cage 1 is provided at each waterspout to prevent erosion of the fuselage skin 4. The aircraft thus has all the benefits of the outlet spacer 1 and will not be described in any greater detail here.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the present invention.
Claims (10)
1. A water outlet isolation ring is arranged between a water outlet and a water discharge valve at the lower end of a fuselage skin of an aircraft; the water outlet isolation ring is characterized by comprising an annular gasket and an annular boss;
the annular boss is vertically arranged on the annular gasket, and the annular gasket is communicated with the annular boss;
the annular boss can be inserted into the water outlet and bonded with the side wall of the water outlet, and the annular gasket is bonded with the outer wall surface of the fuselage skin;
when the drain valve is installed to in the drain port, the valve body of drain valve can pass annular gasket with annular boss, just the flange of valve body with annular gasket counterbalance leans on.
2. The drain opening spacer ring of claim 1, wherein the annular gasket and the annular boss are PBT plastic.
3. The drain opening isolating ring of claim 1, wherein one end of the annular boss, which is away from the annular gasket, extends to the inner wall surface of the fuselage skin and is sealed with the inner wall surface of the fuselage skin by a sealant.
4. The drain isolator ring of claim 3 wherein the outer sidewall of said annular gasket is fillet sealed to the outer wall surface of said fuselage skin by said sealant.
5. The drain opening spacer ring of claim 4 wherein said sealant is a PS870B1/2 sealant or a PS870B2 sealant.
6. The drain opening isolating ring of claim 1, wherein the transition junction between the outer side wall of the annular gasket and the end surface of the annular gasket on the side facing away from the fuselage skin is formed with an arc chamfer or a bevel chamfer.
7. The drain opening spacer ring of claim 6 wherein when the chamfer of the outer sidewall of the annular gasket is a beveled chamfer, the angle of the beveled chamfer is 30 ° -45 °.
8. The drain opening spacer ring of claim 1, wherein the annular gasket has an outer diameter of 34-41mm, the annular gasket and the annular boss have an inner diameter of 18-25mm, and the annular boss has an outer diameter of 21-28 mm;
the thicknesses of the annular gasket and the annular boss are respectively 1.0-1.5 mm.
9. The drain isolator ring of claim 1, wherein the annular gasket and the annular boss are integrally formed.
10. An aircraft comprising a waterspout spacer ring of any one of claims 1-9;
a plurality of water outlets are formed in the fuselage skin of the aircraft, and each water outlet is provided with one water outlet isolation ring.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120235531.4U CN214451788U (en) | 2021-01-26 | 2021-01-26 | Water outlet isolating ring and airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120235531.4U CN214451788U (en) | 2021-01-26 | 2021-01-26 | Water outlet isolating ring and airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214451788U true CN214451788U (en) | 2021-10-22 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120235531.4U Active CN214451788U (en) | 2021-01-26 | 2021-01-26 | Water outlet isolating ring and airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214451788U (en) |
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2021
- 2021-01-26 CN CN202120235531.4U patent/CN214451788U/en active Active
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| TR01 | Transfer of patent right |
Effective date of registration: 20230309 Address after: 510000 Room 301, 3rd floor, phase I office building, Guanhao science and Technology Park, 12 Yuyan Road, Huangpu District, Guangzhou City, Guangdong Province Patentee after: CHINA SOUTHERN AIRLINES CO.,LTD. Address before: 830000 Room 202, unit 1, building 14, No. 8, Xinyi Road, Xinshi District, Urumqi, Xinjiang Uygur Autonomous Region Patentee before: Chen He Patentee before: Wang Xingjian |