Wing with high aspect ratio and wing wallboard thereof

Abstract

The invention discloses a high aspect ratio wing and a wing wallboard thereof, and relates to the technical field of aircrafts, the wing wallboard comprises an integral upper wallboard and an integral lower wallboard, the integral upper wallboard comprises an integral oil tank area and a non-integral oil tank area which are integrally formed, and the integral oil tank area and the integral lower wallboard are cap-shaped rib foam sandwich wallboards; the non-integral fuel tank areas are honeycomb sandwich wall plates, and the thicknesses of the non-integral fuel tank areas of the integral upper wall plate and the integral lower wall plate are gradually reduced from one end close to a wing root to one end close to a wing tip in the spanwise direction of the wing. The overall upper wall plate is of a composite structure of the cap-shaped rib foam sandwich wall plate and the honeycomb sandwich wall plate, the overall lower wall plate is the cap-shaped rib foam sandwich wall plate, the requirements for sealing and structural stability of an overall oil tank area are met, and the mass of the wing wall plate is remarkably reduced.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft technology, and more particularly to a wing panel. BACKGROUND

[0002] The existing large medium-altitude long-endurance unmanned aerial vehicles all adopt a high-aspect-ratio wing configuration to improve the lift-drag ratio and ensure the endurance requirement. The load condition of the high-aspect-ratio wing is complex, and as a load transmission component, the mass ratio of the high-aspect-ratio wing in the aircraft structure generally exceeds 50%. The wing panel, as the main component of the wing, generally accounts for more than 40% of the total mass of the wing.

[0003] In addition to load transmission, the high-aspect-ratio wing often also carries an integral fuel tank to maximize space utilization and improve endurance. In order to ensure the sealing of the integral fuel tank and prevent fuel leakage, the wing panel needs to meet the size design requirement of a minimum thickness of 1.6 mm in the integral fuel tank area. However, due to the gradual decrease of wing load from the wing root to the wing tip, the wing panel at the wing tip and other parts with smaller load does not need to be excessively thick.

[0004] In summary, how to reduce the mass of the wing panel while meeting the size design requirement of the integral fuel tank area is a problem that needs to be solved by the technical personnel in the field. SUMMARY

[0005] Therefore, the purpose of the present application is to provide a wing panel, which is a composite structure of a hat-shaped rib foam sandwich panel and a honeycomb sandwich panel on the whole upper panel and a hat-shaped rib foam sandwich panel on the whole lower panel, thereby meeting the sealing and structural stability requirements of the integral fuel tank area and significantly reducing the mass of the wing panel.

[0006] In addition, the present application also provides a high-aspect-ratio wing comprising the above-mentioned wing panel.

[0007] In order to achieve the above-mentioned purpose, the present application provides the following technical solutions:

[0008] A wing panel, comprising a whole upper panel and a whole lower panel, the whole upper panel comprising an integral fuel tank area and a non-integral fuel tank area, the integral fuel tank area and the whole lower panel being a hat-shaped rib foam sandwich panel, and the non-integral fuel tank area being a honeycomb sandwich panel, the non-integral fuel tank area of the whole upper and lower panels gradually decreasing in thickness from one end close to the wing root to the other end close to the wing tip along the spanwise direction of the wing.

[0009] Preferably, a moisture-proof adhesive film is provided between the outer surface of the inner skin of the whole upper panel and the honeycomb core, and the outer edge of the moisture-proof adhesive film protrudes beyond the outer edge of the honeycomb core.

[0010] Preferably, the hat-shaped rib of the integral lower wall panel is provided with an end rib notch for mounting an end rib of the oil tank, and the oil tank side of the end rib notch is provided with an end rib connecting rib, which is arranged perpendicularly to the hat-shaped rib.

[0011] Preferably, the inner and outer skins of both the integral upper wall panel and the integral lower wall panel comprise a hybrid layup, which is formed by spacing and laying up unidirectional tape layers and fabric woven cloth layers.

[0012] Preferably, the outermost layer of the hybrid layup is a fabric woven cloth layer, the fibers of the unidirectional tape layer extend along the spanwise direction of the wing, and the fiber direction of the fabric woven cloth layer forms an angle of 45° with the spanwise direction of the wing.

[0013] A high-aspect-ratio wing comprises a leading edge skin, a trailing edge skin and the wing panel of any one of the above.

[0014] Preferably, both the integral upper wall panel and the integral lower wall panel are provided with an inwardly recessed lap joint edge, so that the leading edge skin is lapped on the lap joint edge, and the lap joint edge is provided with a wedge-shaped block for sealing contact with the outer edge of the leading edge skin.

[0015] Preferably, the wedge-shaped block is integrally laid up and cured with the integral upper wall panel or the integral lower wall panel.

[0016] Preferably, a sealing gap is provided between the lap joint edge and the leading edge skin, and the sealing gap is filled with a waterproof sealing member.

[0017] Preferably, the integral upper wall panel, the integral lower wall panel and the trailing edge skin are integrally formed.

[0018] The wing panel provided by the present application adopts a hat-shaped rib foam core sandwich panel for the integral oil tank area of the integral upper wall panel and the integral lower wall panel, and the closed-cell foam core of the hat-shaped rib can avoid the risk of oil leakage caused by the internal gap of the hat-shaped rib, has better sealing performance, can meet the sealing requirement and structural stability requirement of the main wing surface integral oil tank area of the wing, and compared with the traditional ribbed panel, the mass of the hat-shaped rib foam core sandwich panel is significantly reduced, effectively reducing the mass of the wing panel.

[0019] In addition, the integral oil tank area and the non-integral oil tank area of the integral upper wall panel are integrally formed, which is beneficial to reducing the number of connecting members, and further reduces the mass of the wing panel.

[0020] In addition, the present application also provides a high-aspect-ratio wing comprising the above-mentioned wing panel. BRIEF DESCRIPTION OF DRAWINGS

[0021] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the accompanying drawings needed to be used in the embodiments or the prior art description will be briefly introduced. Obviously, the accompanying drawings in the following description only aim to explain the embodiments of the present application, and for those skilled in the art, other drawings can be obtained without creative effort based on the provided drawings.

[0022] Figure 1 The structural schematic diagram of the overall upper wall plate of the wing wall plate provided by the present application is shown in the figure.

[0023] Figure 2 The sectional view schematic diagram of the A-A section is shown in the figure.

[0024] Figure 3 The sectional view schematic diagram of the B-B section is shown in the figure.

[0025] Figure 4 The structural schematic diagram of the overall lower wall plate of the wing wall plate provided by the present application is shown in the figure.

[0026] Figure 5 The sectional view schematic diagram of the C-C section is shown in the figure.

[0027] Figure 6 The partition schematic diagram of the wing provided by the present application is shown in the figure.

[0028] Figure 7 The skeleton structure schematic diagram of the wing is shown in the figure.

[0029] Figure 8 The connection schematic diagram of the leading edge skin and the overall upper and lower wall plates of the wing is shown in the figure.

[0030] Figure 9 The sectional view schematic diagram of the A-A section is shown in the figure. Figure 8 The enlarged view of the figure is shown in the figure.

[0031] Figures 1-9 The sectional view schematic diagram of the B-B section is shown in the figure.

[0032] 1 - leading edge skin; 2 - overall upper wall plate; 21 - overall fuel tank area; 22 - non- overall fuel tank area; 3 - trailing edge skin; 4 - overall lower wall plate; 41 - wedge-shaped block; 5 - front beam; 6 - rear beam; 7 - fuel tank root rib; 8 - fuel tank end rib. DETAILED DESCRIPTION

[0033] The technical solutions in the embodiments of the present application will be clearly and completely described below with the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative effort belong to the scope of protection of the present application.

[0034] The core of the present application is to provide a wing panel, the overall upper panel is a composite structure of a hat-shaped rib foam sandwich panel and a honeycomb sandwich panel, and the overall lower panel is a hat-shaped rib foam sandwich panel, which not only meets the sealing and structural stability requirements of the overall fuel tank area, but also significantly reduces the weight of the wing panel.

[0035] In addition, the present application also provides a high-aspect-ratio wing comprising the wing panel.

[0036] The wing panel provided by the present application comprises an overall upper panel 2 and an overall lower panel 4, the overall upper panel 2 comprises an integral overall fuel tank area 21 and a non-integral overall fuel tank area 22, the overall fuel tank area 21 and the overall lower panel 4 are both hat-shaped rib foam sandwich panels, and the non-integral overall fuel tank area 22 is a honeycomb sandwich panel, and the thickness of the non-integral overall fuel tank area 22 of the overall upper and lower panels gradually decreases from one end close to the wing root to the other end close to the wing tip along the spanwise direction of the wing.

[0037] Please refer to Figure 7 , the front beam 5 and the rear beam 6 extend along the spanwise direction of the wing, the front beam 5 and the rear beam 6 are longitudinal load-bearing members of the wing, the main wing surface between the front beam 5 and the rear beam 6 is the core load-bearing area of the wing, and is also the layout area of the overall fuel tank; the fuel tank root rib 7 and the fuel tank end rib 8 extend along the heading direction of the wing, and are used to separate the main wing surface overall fuel tank area and the main wing surface non-integral overall fuel tank area of the wing; and the overall upper panel 2 and the overall lower panel 4 are used to cover the upper and lower surfaces of the wing.

[0038] Please refer to Figure 1 , the overall upper panel 2 comprises an integral overall fuel tank area 21 and a non-integral overall fuel tank area 22, the overall fuel tank area 21 corresponds to the main wing surface overall fuel tank area of the wing, and the non-integral overall fuel tank area 22 corresponds to the main wing surface non-integral overall fuel tank area of the wing, as shown in Figure 6 , the overall fuel tank area 21 is a hat-shaped rib foam sandwich panel, as shown in Figure 2 , the hat-shaped rib foam sandwich panel is provided with a hat-shaped rib along the spanwise direction of the wing, and a closed-cell foam core is arranged inside the hat-shaped rib, which can not only be used as a forming mold for the inner skin of the panel during forming to reduce the tooling cost of the panel, but also avoid the risk of oil leakage caused by the existence of gaps inside the hat-shaped rib.

[0039] In addition, since the hat-shaped rib is arranged only along the spanwise direction, and the foam core is only filled in the inner cavity of the hat-shaped rib with a low filling rate, the mass of the hat-shaped rib foam sandwich panel is not only significantly lower than that of the conventional ribbed panel, but also slightly lower than that of the foam sandwich panel, effectively reducing the mass of the overall upper panel 2.

[0040] The non-integral overall fuel tank area 22 is a honeycomb sandwich panel, as shown in Figure 3As shown, the honeycomb sandwich panel is filled with honeycomb clips. The overall strength of the honeycomb sandwich panel is more uniform and the flatness is higher. It is suitable for the middle section and wingtip of the wing where the load distribution of the wing is relatively accurate and the aerodynamic accuracy is high, that is, the non-integral fuel tank area 22 of the wing. At the same time, the mass of the honeycomb sandwich panel is significantly lower than that of the traditional stiffened panel, which effectively reduces the mass of the wing panel.

[0041] Preferably, to prevent the internal honeycomb core from absorbing moisture, a moisture-proof film can be provided between the outer surface of the inner skin of the overall upper wall panel 2 and the honeycomb core. The outer edge of the moisture-proof film protrudes from the outer edge of the honeycomb core so that the moisture-proof film can adhere to the side of the honeycomb core structure, thereby forming a continuous sealing surface of honeycomb core-film-inner skin.

[0042] Moisture-proof film can be set as fluororubber-based hot melt sealant film, polyimide-based high temperature resistant sealant film, etc. The specific material and size of the moisture-proof film are determined by referring to the existing honeycomb sandwich wall panels according to the actual moisture-proof performance requirements of production.

[0043] During processing, the outer skin of the integral upper wall panel 2 is first laid, and a copper mesh is laid on the inner surface of the outer skin to meet the lightning protection performance requirements of the wing. Then, according to the integral fuel tank area 21 and the non-integral fuel tank area 22, cap-shaped ribs and honeycomb cores are laid on the inner side of the copper mesh, and foam cores are filled into the inner cavity of the cap-shaped ribs. The cap-shaped ribs and honeycomb cores are then conformally processed according to the design shape of the inner skin. Finally, the inner skin is covered on the inner surface of the cap-shaped ribs and honeycomb cores and hot-pressed to solidify the integral upper wall panel 2 into a single structure.

[0044] Please refer to Figure 4 and Figure 5 The overall lower wall panel 4 is a cap-shaped rib foam sandwich panel, with the cap-shaped ribs extending along the spanwise direction of the wing. To facilitate the installation of the overall fuel tank, the cap-shaped ribs of the overall lower wall panel 4 are preferably provided with end rib notches for installing the fuel tank end ribs 8, and the fuel tank side of the end rib notch is provided with end rib connecting ribs. The end rib connecting ribs are set perpendicular to the cap-shaped ribs in order to compensate for the sudden change in stiffness of the cap-shaped ribs caused by the end rib notches.

[0045] The processing method of the integral lower wall panel 4 can refer to the processing method of the integral oil tank area 21 of the integral upper wall panel 2.

[0046] Considering that the wing load gradually decreases from the wing root to the wingtip, and the integral fuel tank area 21 needs to meet the design size requirement of a minimum thickness of 1.6mm, in order to reduce the overall weight of the wing panels, the thickness of the non-integral fuel tank area 22 of the integral upper panel 2 and the non-integral fuel tank area of ​​the integral lower panel 4 can be adjusted according to the design load strength in actual production, so that the non-integral fuel tank areas of both gradually decrease along the wing span direction, from the end closer to the wing root to the end closer to the wingtip.

[0047] In this embodiment, both the integral fuel tank area 21 of the integral upper panel 2 and the integral lower panel 4 adopt cap-shaped rib foam sandwich panels. The closed-cell foam core of the cap-shaped ribs can avoid the risk of oil leakage caused by the gaps between the cap-shaped ribs, and the sealing performance is better. It meets the sealing requirements and structural stability requirements of the integral fuel tank area of ​​the main wing surface. Compared with the traditional ribbed panel, the mass of the cap-shaped rib foam sandwich panel is significantly reduced, which effectively reduces the mass of the wing panel. The non-integral fuel tank area 22 adopts a honeycomb sandwich panel, which has good compressive stability. It not only meets the overall stability and local stability of the integral upper panel 2, but also significantly reduces the mass of the integral upper panel 2 through the size reduction design.

[0048] In addition, the integral fuel tank area 21 and the non-integral fuel tank area 22 of the overall panel 2 are integrally formed, which helps to reduce the number of connecting parts and further reduce the weight of the wing panel.

[0049] In the above embodiments, both the inner and outer skins of the overall upper wall panel 2 and the overall lower wall panel 4 may include a mixed lay-up, which is formed by alternating layers of unidirectional tape and woven fabric.

[0050] The fibers of the unidirectional tape layer are neatly arranged in a single direction, which can withstand large tensile and compressive loads in the fiber extension direction. Considering the tensile and compressive load direction of the wing, it is preferable to set the fibers of the unidirectional tape layer to extend along the spanwise direction of the wing. The woven fabric layer is formed by vertically weaving fibers in orthogonal directions, which can withstand large shear loads. Considering the shear load direction of the wing, it is preferable to set the fiber direction of the woven fabric layer to be at a 45° angle to the spanwise direction of the wing.

[0051] In this embodiment, the unidirectional fiber structure of the unidirectional tape layer can effectively withstand the tensile and compressive loads of the wing, and the orthogonal fiber structure of the woven fabric layer can effectively withstand the shear loads and aerodynamic impact loads of the wing, and can prevent interlayer cracking of the unidirectional tape layer. Therefore, it can achieve the lightest weight design while achieving balanced stress in the spanwise and yaw directions of the wing panel.

[0052] Considering that the woven fabric layer has stronger impact load resistance, it is preferable to set the outermost layer of the mixed layup as a woven fabric layer in order to improve the impact load resistance of the wing panel. In addition, the woven fabric layer has stronger conformability, which is beneficial to improving the surface flatness of the wing panel.

[0053] In addition to the aforementioned wing panel, the present invention also provides a high aspect ratio wing including the wing panel disclosed in the above embodiments. The high aspect ratio wing includes a leading edge skin 1, a trailing edge skin 3, and the wing panel disclosed in the above embodiments. For the specific structure of the leading edge skin 1 and the trailing edge skin 3, please refer to the prior art.

[0054] To reduce the overall weight of the wing, both the upper integral panel 2 and the lower integral panel 4 are provided with inwardly recessed overlapping edges, such as... Figure 8 As shown, the leading edge skin 1 overlaps on the overlapping edge, and the overlapping edge is provided with a wedge block 41 for contacting and sealing with the outer edge of the leading edge skin 1.

[0055] Compared to frame connections, lap joints effectively reduce wing mass and improve wing structural efficiency. Furthermore, the wedge block 41 and the lap joint form a continuous surface seal with the leading edge skin 1, which, compared to the line seal of frame connections, improves the sealing reliability of the joint and reduces the risk of fuel or water vapor leakage. In addition, the lap joint structure is simple to construct, facilitates construction, avoids stress concentration issues associated with frame connections, and extends service life.

[0056] Please refer to Figure 9 The wedge block 41 is used to fill the sunken area of ​​the wing panel and to achieve the transition of the thickness difference of the wing panel. Therefore, the size of the wedge block 41, such as the length of the wedge block 41, needs to be determined according to the actual sunken depth of the wing panel in production. Usually, the length of the wedge block 41 is set to 5 times the sunken depth of the panel. For example, in a specific embodiment, the length of the alkali-free glass cloth covering area on the surface of the wing panel is 30mm.

[0057] Considering that the wedge block 41 is usually laid out independently, in order to ensure that the wedge block 41 can be stably and reliably connected with the wing panel and to ensure the sealing performance of the joint, it is preferable that the wedge block 41 be laid out and cured integrally with the overall upper panel 2 or the overall lower panel 4.

[0058] For example, in a specific embodiment, alkali-free glass cloth is used to lay the wedge block 41 and the wing panel into an integral structure. The alkali-free glass cloth can eliminate the gap between the wedge block 41 and the wing panel, enhance the bonding strength of the overlapping area, and ensure the surface flatness of the structure after laying. The alkali-free glass cloth can also be replaced by composite materials such as fiberglass felt and fiberglass unidirectional tape.

[0059] In addition, a sealing gap is provided between the overlapping edge and the front edge skin 1, and the sealing gap is filled with a waterproof sealant, which can be specifically set as a sealing strip, sealant, etc.

[0060] To reduce the overall weight of the wing, preferably, the upper panel 2, the lower panel 4, and the trailing edge skin 3 can be made into a single integrated structure. This can reduce the number of connecting parts, thereby reducing the overall weight of the wing, and also increase the number of seams on the wing surface, thus improving its aerodynamic performance.

[0061] The upper wall panel 2, the rear edge skin 3, and the lower wall panel 4 are integrally formed. Either the rear edge flanges of the upper and lower wall panels can be fused together by adhesive bonding and co-curing to form the rear edge skin 3, or the upper wall panel 2, the rear edge skin 3, and the lower wall panel 4 can be integrally hot-pressed after layup.

[0062] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0063] The high aspect ratio wing and its wing panels provided by this invention have been described in detail above. Specific examples have been used to illustrate the principles and implementation methods of this invention. The descriptions of the embodiments above are merely for the purpose of helping to understand the method and core ideas of this invention. It should be noted that those skilled in the art can make various improvements and modifications to this invention without departing from its principles, and these improvements and modifications also fall within the protection scope of the claims of this invention.

Claims

1. A wing panel, characterized in that, The system includes an integral upper wall panel (2) and an integral lower wall panel (4). The integral upper wall panel (2) includes an integrally formed fuel tank area (21) and a non-integral fuel tank area (22). The integral fuel tank area (21) and the integral lower wall panel (4) are both cap-shaped ribbed foam sandwich panels. The non-integral fuel tank area (22) is a honeycomb sandwich panel. The thickness of the non-integral fuel tank area (22) of the integral upper and lower walls gradually decreases along the spanwise direction of the wing, from the end near the wing root to the end near the wingtip.

2. The wing panel according to claim 1, characterized in that, A moisture-proof adhesive film is provided between the outer surface of the inner skin of the overall upper wall panel (2) and the inner honeycomb core, and the outer edge of the moisture-proof adhesive film protrudes from the outer edge of the honeycomb core.

3. The wing panel according to claim 1, characterized in that, The cap-shaped rib of the overall lower wall panel (4) is provided with an end rib notch for installing the oil tank end rib (8), and the oil tank side of the end rib notch is provided with an end rib connecting rib, which is set perpendicular to the cap-shaped rib.

4. The wing panel according to any one of claims 1-3, characterized in that, Both the inner and outer skins of the integral upper wall panel (2) and the integral lower wall panel (4) include a mixed lay-up, which is formed by alternating layers of unidirectional tape and woven fabric.

5. The wing panel according to claim 4, characterized in that, The outermost layer of the hybrid layup is a woven fabric layer, and the fibers of the unidirectional tape layer extend along the spanwise direction of the wing. The fiber direction of the woven fabric layer forms a 45° angle with the spanwise direction of the wing.

6. A high aspect ratio airfoil, characterized in that, It includes the leading edge skin, the trailing edge skin, and the wing panel as described in any one of claims 1-5.

7. The high aspect ratio wing according to claim 6, characterized in that, Both the overall upper wall panel (2) and the overall lower wall panel (4) are provided with inwardly recessed overlapping edges so that the front edge skin (1) overlaps on the overlapping edges. The overlapping edges are provided with wedge-shaped blocks (41) for contacting and sealing with the outer edge of the front edge skin (1).

8. The high aspect ratio wing according to claim 7, characterized in that, The wedge-shaped block (41) is integrally laid and cured with the overall upper wall panel (2) or the overall lower wall panel (4).

9. The high aspect ratio wing according to claim 7, characterized in that, A sealing gap is provided between the overlapping edge and the front edge skin (1), and the sealing gap is filled with a waterproof sealant.

10. The high aspect ratio wing according to claim 6, characterized in that, The integral upper wall panel (2), the integral lower wall panel (4), and the rear edge skin (3) are integrally formed structures.

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