CN214397193U - Low-height light airfoil leading edge structure - Google Patents
Low-height light airfoil leading edge structure Download PDFInfo
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- CN214397193U CN214397193U CN202022891793.4U CN202022891793U CN214397193U CN 214397193 U CN214397193 U CN 214397193U CN 202022891793 U CN202022891793 U CN 202022891793U CN 214397193 U CN214397193 U CN 214397193U
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Abstract
The utility model discloses a low high light airfoil leading edge structure, its characterized in that is formed by pressing from both sides core covering subassembly (1) and rib (2) assembly, wherein press from both sides core covering subassembly (1) and include outer covering (3), interior covering (4) and honeycomb core (5), honeycomb core (5) are located between outer covering (3) and interior covering (4), and the shape of interior covering (4) is similar with outer covering (3). The utility model discloses a low height light airfoil leading edge structure wing section height is low, can improve bulk strength and rigidity, satisfies the flight load requirement.
Description
Technical Field
The utility model belongs to the technical field of the aircraft design, concretely relates to low high light airfoil leading edge structure.
Background
With the development of high-altitude long-endurance drone technology, conventional airfoil leading edge structural layouts (single-beam, multi-rib (see fig. 1), and full-height sandwich structures (see fig. 2)) have failed to meet structural requirements. The reason for this is that unmanned aerial vehicle requires the wing section to be thin during high altitude long voyage, and the aspect ratio is big to the wing leading edge height is low, and the structure slenderness ratio is big. If the full-height sandwich structure is adopted, the front edge of the airfoil surface is low, pressure cannot be applied to the foremost end, the gluing quality of the full-height sandwich structure cannot be guaranteed, the front edge of the single-beam structure cannot meet the requirement on structural stability, and the multi-rib structure cannot meet the requirement on light weight. There is a strong need for a lightweight, high efficiency, low profile airfoil structure.
SUMMERY OF THE UTILITY MODEL
In view of the above-mentioned problem of prior art, the utility model aims at coping with the high altitude long time unmanned aerial vehicle's when navigating development trend, provide a low high light airfoil leading edge structure to satisfy light efficient structural requirement.
The above object of the present invention is achieved by the following technical solutions:
a low height, lightweight airfoil leading edge structure is characterized by being assembled from a sandwich skin assembly and ribs, wherein the sandwich skin assembly comprises an outer skin, an inner skin and a honeycomb core, the honeycomb core is positioned between the outer skin and the inner skin, and the shape of the inner skin is similar to (follows) the profile of the airfoil leading edge (i.e., the profile of the outer skin).
Further, the honeycomb core at the foremost end of the leading edge (also the place with the smallest airfoil height) is replaced by the foaming glue, so that the problem that the honeycomb is difficult to form at the foremost end of the leading edge can be effectively solved, and the bonding problem of the honeycomb cores of the upper airfoil surface and the lower airfoil surface is realized.
The rib, the outer skin and the inner skin can be made of high-bearing carbon fiber composite materials respectively, and medium-temperature epoxy carbon fiber composite materials are preferably selected, so that the weight can be reduced, and the forming is facilitated. In addition, the honeycomb core is a light paper honeycomb, and the foaming adhesive is medium-temperature foaming adhesive.
Furthermore, the honeycomb core adopts a block form, which is beneficial to improving the molding quality, reducing the manufacturing defects of parts and improving the working efficiency.
The utility model discloses a low height light airfoil leading edge structure wing section height is low, can improve bulk strength and rigidity, satisfies the flight load requirement.
Drawings
FIG. 1 is a schematic view of a prior art multi-ribbed leading edge structure.
FIG. 2 is a schematic diagram of a conventional full-height sandwich front edge structure.
Fig. 3 is a schematic structural view of the low height and light weight leading edge structure of the airfoil of the present invention.
Figure 4 is an exploded view of the sandwich skin assembly.
FIG. 5 is a schematic view of a sandwich skin assembly.
Fig. 6 is a schematic sectional view taken along line a-a of fig. 5.
Fig. 7 is a schematic sectional view B-B of fig. 5.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings in conjunction with specific embodiments.
Fig. 3 is a schematic structural view of the low height and light weight leading edge structure of the airfoil of the present invention. As shown in the figure, the utility model discloses a low high light airfoil leading edge structure is formed by pressing from both sides core covering subassembly 1 and the assembly of rib 2, has effectively solved part shaping and assembly problem, is applicable to low high unmanned aerial vehicle leading edge structure, presss from both sides core covering subassembly 1 and rib 2 and can improve leading edge structure bulk strength and rigidity, satisfies the flight load requirement.
The sandwich skin assembly 1 comprises an outer skin 3, an inner skin 4 and a honeycomb core 5 (see fig. 4 and 5). The honeycomb core 5 is located between the outer skin 3 and the inner skin 4. The shape of the inner skin 4 is similar to the airfoil leading edge profile, i.e. the outer skin 3 profile (conformal), see fig. 6. In addition, as shown in fig. 6, the honeycomb core 5 at the foremost end of the leading edge (i.e., where the airfoil height is the smallest) can be replaced with the foamed rubber 6, so that the problem that the honeycomb is difficult to form at the foremost end of the leading edge can be effectively solved, and the problem of bonding the honeycomb cores of the upper and lower wing surfaces is realized. The outer skin 3, the inner skin 4, the honeycomb core 5 and the optional foaming glue 6 are glued to form the sandwich skin assembly 1, specifically, the sandwich skin assembly 1 is formed by co-curing the glue films cured at the medium temperature, so that the overall rigidity and strength of the sandwich skin assembly are effectively improved, and the sandwich skin assembly is easy to form. Fig. 7 shows a cross section of the attachment area of the sandwich skin assembly (i.e., the area where the ribs 2 are provided).
The ribs 2, the outer skin 3 and the inner skin 4 can be made of high-bearing carbon fiber composite materials, preferably medium-temperature epoxy carbon fibers. In addition, the honeycomb core 5 can be a light paper honeycomb, and the foaming adhesive 6 can be medium-temperature foaming adhesive.
In addition, the honeycomb core 5 can adopt a block form, which is beneficial to improving the forming quality, reducing the manufacturing defects of parts and improving the working efficiency.
The utility model discloses a leading edge structure can effectively satisfy the design requirement of leading edge structure that the leading edge height is low, intensity and rigidity require highly.
Claims (7)
1. The low-height light-weight airfoil leading edge structure is characterized by being formed by assembling a sandwich skin assembly (1) and ribs (2), wherein the sandwich skin assembly (1) comprises an outer skin (3), an inner skin (4) and a honeycomb core (5), the honeycomb core (5) is positioned between the outer skin (3) and the inner skin (4), and the shape of the inner skin (4) is similar to that of the outer skin (3).
2. A low profile, lightweight airfoil leading edge structure as claimed in claim 1 wherein the honeycomb core (5) at the forwardmost end of the leading edge is replaced by foam (6).
3. A low height lightweight airfoil leading edge structure in accordance with claim 2 wherein said foam (6) is a medium temperature foam.
4. A low height lightweight airfoil leading edge structure as claimed in claim 1 wherein said rib (2), outer skin (3) and inner skin (4) are each of a high load bearing carbon fibre composite material.
5. A low height lightweight airfoil leading edge structure as set forth in claim 4 wherein said carbon fiber composite is a medium temperature epoxy carbon fiber composite.
6. A low height lightweight airfoil leading edge structure in accordance with claim 1 wherein said honeycomb core (5) is a lightweight paper honeycomb.
7. A low height lightweight airfoil leading edge structure as claimed in claim 1 or 6 wherein said honeycomb core (5) is in the form of segments.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022891793.4U CN214397193U (en) | 2020-12-04 | 2020-12-04 | Low-height light airfoil leading edge structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022891793.4U CN214397193U (en) | 2020-12-04 | 2020-12-04 | Low-height light airfoil leading edge structure |
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| Publication Number | Publication Date |
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| CN214397193U true CN214397193U (en) | 2021-10-15 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202022891793.4U Active CN214397193U (en) | 2020-12-04 | 2020-12-04 | Low-height light airfoil leading edge structure |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115071954A (en) * | 2022-08-22 | 2022-09-20 | 中国空气动力研究与发展中心空天技术研究所 | Hypersonic heat-proof bearing integrated light tail wing |
-
2020
- 2020-12-04 CN CN202022891793.4U patent/CN214397193U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115071954A (en) * | 2022-08-22 | 2022-09-20 | 中国空气动力研究与发展中心空天技术研究所 | Hypersonic heat-proof bearing integrated light tail wing |
| CN115071954B (en) * | 2022-08-22 | 2022-11-08 | 中国空气动力研究与发展中心空天技术研究所 | Hypersonic heat-proof bearing integrated light tail wing |
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