CN2835081Y - Aircraft wing structure - Google Patents
Aircraft wing structure Download PDFInfo
- Publication number
- CN2835081Y CN2835081Y CN 200520200678 CN200520200678U CN2835081Y CN 2835081 Y CN2835081 Y CN 2835081Y CN 200520200678 CN200520200678 CN 200520200678 CN 200520200678 U CN200520200678 U CN 200520200678U CN 2835081 Y CN2835081 Y CN 2835081Y
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- Prior art keywords
- wing
- aircraft wing
- aircraft
- skeleton
- filler
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Abstract
The utility model discloses a new aircraft wing structure. The structure comprises an aircraft wing skeleton which is connected with aircraft wing filling materials, and the outer surface of the aircraft wing skeleton and the outer surface of the aircraft wing filling materials are covered by aircraft wing face materials. For a large aircraft, a reinforcement beam is arranged in the middle of an aircraft wing; for a double convex wing type structure, both the upper face and the lower face of the aircraft wing skeleton are provided with the aircraft wing filling materials and the reinforcement beam. The utility model has the advantages of simple structure, quick, convenient and accurate moulding, easy remoulding operation and low cost.
Description
Technical field:
The utility model relates to a kind of structure of aircraft, particularly relates to a kind of wing structure of aircraft.
Background technology:
Why the aircraft that overweights air can liftoffly fly, and is to obtain lift by its wing.Lifting force of wings is utilized bernoulli principle and is obtained.Generally to have wing section shape flat under the epirelief be aerofoil profile to the wing profile of aircraft for this reason, and windstream was through the speed difference of aerofoil upper and lower surface when such aerofoil profile was moved in air, thereby to produce difference of pressure be lift.
Existing Airfoil complex structure, need a large amount of overhourss and numerous and diverse assembly technique, the productive costs height, the processing of Airfoil sometimes just accounts for the over half of total cost, both be unfavorable for stock production, also be unfavorable for when the test aerofoil profile, changing fast aerofoil profile.
Summary of the invention:
The purpose of this utility model is: the new construction that a kind of aircraft wing is provided, simple and practical, make and simple and easyly fast both be applicable to low-cost production aircraft wing fast, be applicable to that also the aerodynamic experiment chamber makes different aerofoil profile models fast and carry out the aerodynamic force test.
The utility model is to constitute like this: it comprises wing skeleton (3), with wing skeleton (3) bonded assembly be wing filler (2), be coated with wing lining (1) at the outside face of wing skeleton (3) and wing filler (2).
In order to obtain wing shapes accurately, wing filler (2) can be made one or a few blocks, and the thickness of every block of wing filler (2) is less, and size and shape is accurate.
For larger-size aircraft, strengthened beam (4) is set, in the middle of wing to increase wing single-piece rigidity and degree of stability.
Some aircraft is made the biconvex profile structure, and the upper and lower surface in wing skeleton (3) all is provided with wing filler (2) and is connected with it with strengthened beam (4).
Method for making of the present utility model is as follows: the first, and maker wing skeleton (3), wing skeleton (3) materials used are that cork wood plate, aluminium sheet or charcoal fiber meet plate of material etc., require the hard intensity height of texture material; The second, use polystyrene foam, polyurethane foamed plastic or other foamed materials maker stuffing with wing (2), and go up labelling machine stuffing with wing (2) at wing skeleton (3); The 3rd, at the outside coating machine aerofoil material (1) of wing skeleton (3) and wing filler (2), wing lining (1) uses the tubulose heat-shrinkable film; At last integral body is put into Oven heating, treat that certain hour shrinks the back and takes out cooling, typing.
In method for making second step, for larger-size aircraft, make strengthened beam (4) according to designing requirement, be vertically mounted on the wing skeleton (3), and be connected with wing filler (2); For the biconvex profile structure, make the wing filler (2) and the strengthened beam (4) of requirement according to design parameters, and it is separately fixed at the two sides of wing skeleton (3).
During making, wing skeleton (3) is made into writing board shape, processes easily and assembles, and also is convenient to process lightening hole and reinforced rib is installed on flat board; Wing filler (2) also is made into writing board shape, is convenient to stick on the wing skeleton (3); The foamed materials that wing filler (2) uses has bigger elasticity and compressibility, the wing lining (1) that the outside coats is for having the membraneous material of contractility, after membraneous material tightens up, then with the foam compresses that is in contact with it, can not form tangible polyline shaped surface, resulting aerofoil profile is quite slick and sly curve.
The utility model compared with prior art has simple in structure, quick accurate, the advantage easy, with low cost of retrofiting of moulding.
Description of drawings:
Fig. 1, Fig. 2: basic structure scheme drawing of the present utility model.
Fig. 3: scheme drawing of the present utility model has strengthened beam in the structure.
Fig. 4: scheme drawing of the present utility model, be the biconvex profile structure, strengthened beam is arranged in the structure.
The specific embodiment:
Embodiment of the present utility model:
Embodiment 1: as shown in Figure 1 and Figure 2, wing skeleton (3), wing filler (2) and wing lining (1) are arranged in this structure.At first, use the high cork wood plate maker wing skeleton (3) of the hard intensity of quality, make writing board shape; Secondly, use polystyrene foam to make polylith wing filler (2), also be made into writing board shape; And with it on labelling machine wing skeleton (3), paste position carries out according to the design-calculated coordinate; Then, use the tubulose heat-shrinkable film, it is packaged in outside the assembly set of the wing skeleton (3) made and wing filler (2) as wing lining (1); At last integral body is put into Oven heating, make film shrink, treat to take out cooling, typing behind the certain hour.
Embodiment 2: as shown in Figure 3, compare with embodiment 1, increased strengthened beam (4) in this structure.Use the high cork wood plate of the hard intensity of quality to make strengthened beam (4), and be fixed on the wing skeleton (3), incorporating mill stuffing with wing (2) connects into integral body; All the other are with embodiment 1.
Embodiment 3: as shown in Figure 4, this structure is the biconvex profile structure, and wing filler (2) and strengthened beam (4) all are set on the two sides of wing skeleton (3).Make the wing filler (2) and the strengthened beam (4) of requirement according to design parameters, and it is separately fixed at the two sides of wing skeleton (3), at the outer package wing lining (1) of whole assembly set; All the other together
Embodiment 1.
Claims (4)
1. aircraft wing structure, it comprises wing skeleton (3), it is characterized in that: with wing skeleton (3) bonded assembly be wing filler (2), be coated with wing lining (1) at the outside face of wing skeleton (3) and wing filler (2).
2. aircraft wing structure according to claim 1 is characterized in that: wing filler (2) is made one or a few blocks.
3. aircraft wing structure according to claim 1 is characterized in that: for larger-size aircraft, strengthened beam (4) is set in the middle of wing.
4. aircraft wing structure according to claim 1 is characterized in that: for the biconvex profile structure, the upper and lower surface in wing skeleton (3) all is provided with wing filler (2) and is connected with it with strengthened beam (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200520200678 CN2835081Y (en) | 2005-10-10 | 2005-10-10 | Aircraft wing structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200520200678 CN2835081Y (en) | 2005-10-10 | 2005-10-10 | Aircraft wing structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2835081Y true CN2835081Y (en) | 2006-11-08 |
Family
ID=37299739
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200520200678 Expired - Fee Related CN2835081Y (en) | 2005-10-10 | 2005-10-10 | Aircraft wing structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2835081Y (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102069919A (en) * | 2010-12-23 | 2011-05-25 | 江西洪都航空工业集团有限责任公司 | High-aspect-ratio wing type structure and manufacturing method thereof |
| CN104590544A (en) * | 2015-01-28 | 2015-05-06 | 梧州晟裕科技有限公司 | Aerofoil structure of fixed-wing unmanned aerial vehicle |
| CN114104326A (en) * | 2021-12-03 | 2022-03-01 | 西北工业大学 | Unmanned aerial vehicle production method |
-
2005
- 2005-10-10 CN CN 200520200678 patent/CN2835081Y/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102069919A (en) * | 2010-12-23 | 2011-05-25 | 江西洪都航空工业集团有限责任公司 | High-aspect-ratio wing type structure and manufacturing method thereof |
| CN104590544A (en) * | 2015-01-28 | 2015-05-06 | 梧州晟裕科技有限公司 | Aerofoil structure of fixed-wing unmanned aerial vehicle |
| CN114104326A (en) * | 2021-12-03 | 2022-03-01 | 西北工业大学 | Unmanned aerial vehicle production method |
| CN114104326B (en) * | 2021-12-03 | 2024-04-26 | 西北工业大学 | Unmanned aerial vehicle production method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C19 | Lapse of patent right due to non-payment of the annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |