CN210971500U - Composite material airplane outer wing spar - Google Patents
Composite material airplane outer wing spar Download PDFInfo
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- CN210971500U CN210971500U CN201921973582.6U CN201921973582U CN210971500U CN 210971500 U CN210971500 U CN 210971500U CN 201921973582 U CN201921973582 U CN 201921973582U CN 210971500 U CN210971500 U CN 210971500U
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- web
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Abstract
The utility model discloses a composite material airplane outer wing spar, which comprises a flange strip, a rectangular web plate and a 1-shaped web plate, wherein the rectangular web plate is positioned at a wing root, the 1-shaped web plate is connected with the rectangular web plate and extends towards the wing tip direction, the two flange strips are respectively arranged above and below the rectangular web plate and the 1-shaped web plate, the periphery of the rectangular web plate is wound with first glass fiber cloth, and the first glass fiber cloth surrounds the flange strip above and below the rectangular web plate; and second glass fiber cloth is laid on the inner sides of the beam edge strips above and below the support plate and the 1-shaped web plate. Compared with a metal material, the wing beam made of the composite material can obviously reduce weight and has no corrosion and fatigue problems. The structural form is not limited by the capacity of a machining process, and the number and the direction of the layers can be adjusted according to the size of the load, so that the load transfer is more reasonable and efficient. The section form of the wing beam is gradually changed from a rectangular shape to an I-shaped shape, and the structural efficiency is high.
Description
Technical Field
The utility model relates to an aerospace technical field, concretely relates to wing of aircraft.
Background
Conventional outer wing spars for aircraft are generally of metal construction and are relatively heavy. The combined metal structure is mainly adopted, the combined metal structure comprises independent edge strips and webs which are connected through fasteners, and the combined metal structure has more parts and standard parts and is complex to assemble; or the integral metal wing beam is machined by adopting a forged piece or a thick plate, so that the material utilization rate is low and the cost is high. The metal structure is susceptible to corrosion and fatigue.
SUMMERY OF THE UTILITY MODEL
The utility model solves the technical problem that: the outer wing beam of the airplane is light in weight, not easy to corrode and free of fatigue.
In order to solve the technical problem, the utility model provides a following technical scheme: a composite material airplane outer wing spar comprises beam edge strips, a rectangular web plate and a 1-shaped web plate, wherein the rectangular web plate is located at a wing root, the 1-shaped web plate is connected with the rectangular web plate and extends towards a wing tip direction, the beam edge strip positioned above the two beam edge strips is arranged above the rectangular web plate and the 1-shaped web plate, the beam edge strip positioned below the two beam edge strips is arranged below the rectangular web plate and the 1-shaped web plate, first glass fiber cloth is wound on the periphery of the rectangular web plate, and the first glass fiber cloth surrounds the beam edge strips positioned above and below the rectangular web plate; and second glass fiber cloth is laid on the inner sides of the beam edge strips above and below the 1-shaped web plate and the 1-shaped web plate.
The loads are greater at the root of the wing, i.e. the wing root, and less at the tip of the wing, i.e. the wing tip. Therefore, the wing beam of the utility model adopts the rectangular web with the rectangular cross section at the wing root, and the part which is connected with the rectangular web and extends towards the wing tip direction adopts the 1-shaped web. The periphery of the rectangular web is wound with first glass fiber cloth, and the first glass fiber cloth surrounds the beam flange strips above and below the rectangular web so as to improve the bearing capacity of the rectangular web. 1 font web constitutes the structure that the cross-section is the I-shaped with the roof beam reason strip of its top, below, from this, spar cross-sectional form becomes the I-shaped from the rectangle gradually.
The utility model discloses a combined material wing spar compares in metal material, can be obvious subtract heavy, and do not corrode and fatigue problem.
The utility model discloses a composite material wing spar from wing root to wing tip, adopts variable cross section structure, from bearing high wing root to the relatively less wing tip of load, and the cross sectional form becomes the I-shaped (the transversal I-shaped that personally submits of the structure that upper and lower beam flange and 1 font web constitute) gradually from rectangle (the transversal rectangle of personally submitting of rectangular web), and its weight is lighter. As an improvement, the height of the whole web body formed by the rectangular web plate and the 1-shaped web plate is slightly reduced from the wing root to the wing, wherein the height is the height of the whole web plate when the spar is installed on the fuselage.
The utility model discloses a combined material wing spar not only can reduce the discontinuous state of fastener quantity and structure, improves the whole function of structure, reduces manufacturing procedure and assembly cycle moreover to reduce cost.
Drawings
The invention will be further explained with reference to the drawings:
FIG. 1 is a full cross-sectional view of an outer wing spar of a composite aircraft;
FIG. 2 is a cross-sectional view taken along line A-A of FIG. 1;
fig. 3 is a sectional view taken along line B-B in fig. 1.
The symbols in the drawings illustrate that:
1. a flange strip;
2. a first C-web;
3. a second C-web;
4. a first glass fiber cloth;
5. 1-shaped web plate;
6. and a second glass fiber cloth.
Detailed Description
With reference to fig. 1 to 3, a composite material airplane outer wing spar comprises a flange strip 1, a rectangular web and a 1-shaped web 5, wherein the rectangular web is located at a wing root, the 1-shaped web is connected with the rectangular web and extends towards a wing tip direction, the upper flange strip of the two flange strips is arranged above the rectangular web and the 1-shaped web, the lower flange strip of the two flange strips is arranged below the rectangular web and the 1-shaped web, a first glass fiber cloth 4 is wound on the periphery of the rectangular web, and the first glass fiber cloth surrounds the flange strips above and below the rectangular web; and second glass fiber cloth 6 is laid on the inner sides of the beam edge strips above and below the 1-shaped web plate and the 1-shaped web plate.
The wing beam is a frame structure of an outer wing (a part of the wing outside a fuselage) of the airplane, is a main stress component in the wing and bears shearing force and bending moment of the wing. The root of the wing refers to one end of the wing close to the fuselage, and is called the wing root for short; the tail end of the wing refers to one end of the wing far away from the fuselage, and is called a wing tip for short.
1 font web and rectangular web link up, indicate that 1 font web and rectangular web end to end link up, the junction between the two, 1 font web bonds with rectangular web. According to the actual load distribution condition of the wing beam, at the joint, the rectangular web plates are thinned, then inwards folded from two sides, gradually transited and glued with the 1-shaped web plates to form a Y shape, as shown in figure 1.
As shown in fig. 2, the two beam edge strips are respectively located above and below the rectangular web, so that the first glass fiber cloth 4 wound around the periphery of the rectangular web specifically passes through the left side wall of the rectangular web, the part of the beam edge strip located above the rectangular web, the right side wall of the rectangular web, and the part of the beam edge strip located below the rectangular web. The first glass fiber cloth 4 can fasten the matching of the beam flange strip 1 and the rectangular web, and the strength, namely the bearing capacity, of the spar at the wing root is improved. Alternatively, the first glass cloth 4 has a multi-layer structure, each layer having a thickness of 4 mm.
As shown in FIG. 2, the rectangular web is a rectangular hollow structure and is formed by overlapping a first C-shaped web 2 and a second C-shaped web 3 left and right, namely, the first C-shaped web is positioned on the left side, and the second C-shaped web is positioned on the right side. Wherein, the lapping specifically means: each end of the two ends of the first C-shaped web plate is provided with a first connecting part, each end of the two ends of the second C-shaped web plate is provided with a second connecting part, when the first C-shaped web plate and the second C-shaped web plate are spliced together, the upper end of the first C-shaped web plate is butted with the upper end of the second C-shaped web plate, and the first connecting part at the upper end of the first C-shaped web plate and the second connecting part at the upper end of the second C-shaped web plate are overlapped together up and down; the lower end of the first C-shaped web plate is in butt joint with the lower end of the second C-shaped web plate, and the first connecting part at the lower end of the first C-shaped web plate and the second connecting part at the lower end of the second C-shaped web plate are vertically overlapped together.
The first C-web 2 and the second C-web 3 are both of a glass fibre foam sandwich structure, i.e. the glass fibres sandwich the foam, alternatively either C-web is 12mm thick, wherein the total thickness of the foam is 8mm and the thickness of the glass fibres is 4 mm.
Alternatively, the beam flange strip 1 is a carbon fiber unidirectional tape with the thickness of 6 mm.
As shown in fig. 3, a second glass fiber cloth 6 is laid on the inner side (the opposite side of the upper and lower beam flanges) of the beam flange 1 above and below the 1-shaped web 5 and the left and right sides of the 1-shaped web 5, wherein the upper end of the 1-shaped web is connected with the upper beam flange by bonding or connecting pieces; the lower end of the 1-shaped web plate is connected with the lower beam edge strip. Alternatively, the 1-shaped web 5 is a glass fiber foam sandwich structure, i.e. the glass fibers sandwich the foam, and alternatively the total thickness of the foam is 6mm, the thickness of the glass fibers is 1mm, and the total thickness is 7 mm. Alternatively, the second glass cloth 6 has a multi-layer structure, and the thickness of each layer is 1 mm.
The above description is only for the preferred embodiment of the present invention, and for those skilled in the art, there are variations on the detailed description and the application scope according to the idea of the present invention, and the content of the description should not be construed as a limitation to the present invention.
Claims (5)
1. The utility model provides a composite material aircraft outer wing spar, includes cap strip (1), rectangle web, 1 font web (5), its characterized in that: the rectangular web is located at the wing root, the 1-shaped web is connected with the rectangular web and extends towards the wing tip direction, the upper beam edge strip of the two beam edge strips is arranged above the rectangular web and the 1-shaped web, the lower beam edge strip of the two beam edge strips is arranged below the rectangular web and the 1-shaped web, first glass fiber cloth (4) is wound on the periphery of the rectangular web, and the first glass fiber cloth surrounds the beam edge strips above and below the rectangular web; and second glass fiber cloth (6) is laid on the inner sides of the beam edge strips above and below the 1-shaped web plate and the support plate.
2. An aircraft outer wing spar according to claim 1, wherein: the rectangular web is of a rectangular hollow structure and is formed by left and right lap joint of a first C-shaped web (2) and a second C-shaped web (3); the 1-shaped web plate and the beam edge strips above and below the web plate form an I shape.
3. An aircraft outer wing spar according to claim 2, wherein: the first C-shaped web plate (2) and the second C-shaped web plate (3) are both of glass fiber foam sandwich structures.
4. An aircraft outer wing spar according to claim 1, wherein: the beam edge strip (1) is a carbon fiber unidirectional tape.
5. An aircraft outer wing spar according to claim 1, wherein: the 1-shaped web plate (5) is of a glass fiber foam sandwich structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921973582.6U CN210971500U (en) | 2019-11-15 | 2019-11-15 | Composite material airplane outer wing spar |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921973582.6U CN210971500U (en) | 2019-11-15 | 2019-11-15 | Composite material airplane outer wing spar |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210971500U true CN210971500U (en) | 2020-07-10 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921973582.6U Active CN210971500U (en) | 2019-11-15 | 2019-11-15 | Composite material airplane outer wing spar |
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|---|---|
| CN (1) | CN210971500U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112572762A (en) * | 2020-12-04 | 2021-03-30 | 中国航空工业集团公司成都飞机设计研究所 | Composite material beam joint |
-
2019
- 2019-11-15 CN CN201921973582.6U patent/CN210971500U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112572762A (en) * | 2020-12-04 | 2021-03-30 | 中国航空工业集团公司成都飞机设计研究所 | Composite material beam joint |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20220221 Address after: 312500 No.1-3 (building 1-5), Aofeng Road, Wozhou Town, Xinchang County, Shaoxing City, Zhejiang Province Patentee after: Zhejiang Wanfeng Aircraft Manufacturing Co.,Ltd. Address before: 312500, No.1, Aofeng Road, Xinchang Industrial Park, Shaoxing City, Zhejiang Province Patentee before: Wanfeng Aircraft Industry Co.,Ltd. |
|
| TR01 | Transfer of patent right |