CN204688426U - Wing tank - Google Patents
Wing tank Download PDFInfo
- Publication number
- CN204688426U CN204688426U CN201520377117.1U CN201520377117U CN204688426U CN 204688426 U CN204688426 U CN 204688426U CN 201520377117 U CN201520377117 U CN 201520377117U CN 204688426 U CN204688426 U CN 204688426U
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- CN
- China
- Prior art keywords
- wing
- fuel tank
- coverboard
- end plate
- downside
- 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.)
- Expired - Fee Related
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Abstract
A kind of wing tank, is made up of coverboard on the downside of coverboard, fuel tank outer end plate, fuel tank floor, fuel tank inner end plate, oil inlet, oil outlet pipe, skeleton, wing on the upside of wing; On the upside of wing, the outer of coverboard is prefabricated with convex edge, outside, and on the downside of wing, the outer of coverboard is prefabricated with convex edge, inner side, and convex edge, outside is mated with convex edge, inner side, and is connected by adhesive seal; The skeleton running through integral structure inside is provided with between coverboard on the downside of coverboard and wing on the upside of wing; The side of skeleton is provided with fuel tank outer end plate and fuel tank inner end plate, and and form seal chamber between coverboard on the downside of coverboard and wing on the upside of wing, sealing cavity internal fixtion is connected with at least two fuel tank floors, the top of fuel tank floor is provided with several airflow holes, bottom is provided with several oily discharge orifices, and downside end is provided with position, end control oilhole; Fuel tank inner end plate is provided with oil inlet and oil outlet pipe, and the inner of oil inlet is placed in the upper end of fuel tank inner end plate, and the inner port of oil outlet pipe is placed in the downside end of fuel tank inner end plate.
Description
Technical field
The utility model relates to a kind of technical field of aerospace, is specifically related to a kind of Novel aerofoil fuel tank, is applicable to use with the aircraft match of unmanned plane or other type.
Background technology
China Patent No. 201210325959.3 discloses a kind of wing tank vent layout method.This layout method sets up fuel tank 3D modelling based on CATIA software, determines fuel tank upper surface vertex, First Point, rearmost point, ultra-left point and rightest point under stopped status.By to point vertex and a First Point, determine pitching height point; Again by point pitching height point and a rightest point, determine the main vent locations of wing tank.In like manner, by point vertex and a rightest point, the secondary high point of pitching is determined; Again by the secondary high point of point pitching and ultra-left point, determine wing tank assisted ventilation mouth position.Given vent locations is rationally distributed, and tank capacity space waste is little, and can not overflow, and method is simple, easy to use, is applicable to any wing tank, highly versatile, has application value.China Patent No. 201420134216.2 discloses the improvement of adaptor union and wing floor riveted structure in a kind of wing tank pressure filling pipeline.It is characterized in that: there is a butt flange annular boss (1d) position of upper at butt flange (1b), close cylinder (1), butt flange annular boss (1d) inserts in the left port of mounting hole (2a), and the difference of the internal diameter of this mounting hole (2a) and the external diameter of butt flange annular boss (1d) is not more than 0.5mm.Ensure that the right alignment of cylinder 1 and mounting hole 2a, eliminate the connection deviation of adaptor union and left oil pipe 4 and right oil pipe 6, reduce the stress after installation, avoid and damage wing tank floor, ensure that flight safety.
Utility model content
The purpose of this utility model is to provide a kind of wing tank, effectively can utilize the inner space of wing, and Oiltank structure is firm, and the air in guarantee fuel tank and bunker oil flow unobstructed.
For achieving the above object, the utility model have employed such technical scheme: described wing tank, is made up of coverboard on the downside of coverboard, fuel tank outer end plate, fuel tank floor, fuel tank inner end plate, oil inlet, oil outlet pipe, skeleton, wing on the upside of wing; It is characterized in that, on the upside of wing, the outer of coverboard is prefabricated with convex edge, outside, and on the downside of wing, the outer of coverboard is prefabricated with convex edge, inner side, and convex edge, outside is mated with convex edge, inner side, and is connected by adhesive seal; The skeleton running through integral structure inside is provided with between coverboard on the downside of coverboard and wing on the upside of wing; The side of skeleton is provided with fuel tank outer end plate and fuel tank inner end plate, and and form seal chamber between coverboard on the downside of coverboard and wing on the upside of wing, sealing cavity internal fixtion is connected with at least two fuel tank floors, the top of fuel tank floor is provided with several airflow holes, bottom is provided with several oily discharge orifices, and downside end is provided with position, end control oilhole; Fuel tank inner end plate is provided with oil inlet and oil outlet pipe, and the inner of oil inlet is placed in the upper end of fuel tank inner end plate, and the inner port of oil outlet pipe is placed in the downside end of fuel tank inner end plate.
After adopting such structure, the side of skeleton is provided with fuel tank outer end plate and fuel tank inner end plate, and and form seal chamber between coverboard on the downside of coverboard and wing on the upside of wing, namely this cavity is whole volumes of wing tank; The fuel tank floor that sealing cavity internal fixtion connects has raising Joint strenght to coverboard on the downside of coverboard on the upside of wing and wing, increases the effect of supporting & stablizing; Several airflow holes of the top setting of fuel tank floor, object is to prevent wing tank top from occurring, and air suppresses the generation of poly-phenomenon; Position, the end control oilhole that several oily discharge orifices that bottom is arranged and downside end are arranged, its object is to, when bunker oil liquid level reduces, reduce the accumulation of bunker oil bottom wing tank as far as possible.
The beneficial effects of the utility model: the inner space effectively utilizing wing, Oiltank structure is firm, and the air in guarantee fuel tank and bunker oil flow unobstructed.
Accompanying drawing explanation
Figure 1 shows that the schematic diagram of the utility model concrete structure;
Fig. 2 is the cutaway view of A-A shown in Fig. 1.
Detailed description of the invention
Below in conjunction with accompanying drawing, wing tank described in the utility model is described in detail; As shown in Figure 1 and Figure 2, described wing tank, is made up of coverboard 15 on the downside of coverboard on the upside of wing 1, fuel tank outer end plate 2, fuel tank floor 6, fuel tank inner end plate 7, oil inlet 8, oil outlet pipe 9, skeleton 10, wing; On the upside of wing, the outer of coverboard 1 is prefabricated with convex edge 4, outside, and on the downside of wing, the outer of coverboard 15 is prefabricated with convex edge 3, inner side, and convex edge, outside 4 is mated with convex edge, inner side 3, and is connected by adhesive seal; The skeleton 10 running through integral structure inside is provided with between coverboard 15 on the downside of coverboard 1 and wing on the upside of wing; The side of skeleton 10 is provided with fuel tank outer end plate 2 and fuel tank inner end plate 7, and and form seal chamber between coverboard 15 on the downside of coverboard 1 and wing on the upside of wing, sealing cavity internal fixtion is connected with at least two fuel tank floors 6; (as shown in Figure 2) top of fuel tank floor 6 is provided with several airflow holes 5, and bottom is provided with several oily discharge orifices 13, and downside end is provided with position, end control oilhole 14;
Fuel tank inner end plate 7 is provided with oil inlet 8 and oil outlet pipe 9, and the inner 12 of oil inlet 8 is placed in the upper end of fuel tank inner end plate 7, and the inner port 11 of oil outlet pipe 9 is placed in the downside end of fuel tank inner end plate 7.
Claims (1)
1. a wing tank, is made up of coverboard (15) on the downside of coverboard on the upside of wing (1), fuel tank outer end plate (2), fuel tank floor (6), fuel tank inner end plate (7), oil inlet (8), oil outlet pipe (9), skeleton (10), wing;
It is characterized in that, on the upside of wing, the outer of coverboard (1) is prefabricated with convex edge, outside (4), on the downside of wing, the outer of coverboard (15) is prefabricated with convex edge, inner side (3), convex edge, outside (4) is mated with convex edge, inner side (3), and is connected by adhesive seal; The skeleton (10) running through integral structure inside is provided with between coverboard (15) on the downside of coverboard (1) and wing on the upside of wing; The side of skeleton (10) is provided with fuel tank outer end plate (2) and fuel tank inner end plate (7), and and form seal chamber between coverboard (15) on the downside of coverboard (1) and wing on the upside of wing, sealing cavity internal fixtion is connected with at least two fuel tank floors (6), the top of fuel tank floor (6) is provided with several airflow holes (5), bottom is provided with several oily discharge orifices (13), and downside end is provided with position, end control oilhole (14);
Fuel tank inner end plate (7) is provided with oil inlet (8) and oil outlet pipe (9), the inner (12) of oil inlet (8) is placed in the upper end of fuel tank inner end plate (7), and the inner port (11) of oil outlet pipe (9) is placed in the downside end of fuel tank inner end plate (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520377117.1U CN204688426U (en) | 2015-05-28 | 2015-05-28 | Wing tank |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520377117.1U CN204688426U (en) | 2015-05-28 | 2015-05-28 | Wing tank |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204688426U true CN204688426U (en) | 2015-10-07 |
Family
ID=54228744
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520377117.1U Expired - Fee Related CN204688426U (en) | 2015-05-28 | 2015-05-28 | Wing tank |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204688426U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104908958A (en) * | 2015-05-28 | 2015-09-16 | 河南翱翔航空科技有限公司 | Wing fuel tank |
| CN105501450A (en) * | 2015-11-30 | 2016-04-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Unmanned plane composite integral fuel tank sealing method |
-
2015
- 2015-05-28 CN CN201520377117.1U patent/CN204688426U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104908958A (en) * | 2015-05-28 | 2015-09-16 | 河南翱翔航空科技有限公司 | Wing fuel tank |
| CN105501450A (en) * | 2015-11-30 | 2016-04-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Unmanned plane composite integral fuel tank sealing method |
| CN105501450B (en) * | 2015-11-30 | 2020-09-18 | 中国航空工业集团公司沈阳飞机设计研究所 | Unmanned aerial vehicle composite material integral oil tank sealing method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20151007 Termination date: 20180528 |