Wing with foam sandwich structure

Abstract

The utility model belongs to the field of wings, and particularly relates to a wing with a foam sandwich structure, which comprises a fuselage framework, a foam sandwich, a skin and two side wing boxes, the two side wing boxes are symmetrically arranged on the two sides of the fuselage framework, and the skin covers the outer sides of the fuselage framework and the side wing boxes; gaps are formed between the side faces and the end faces of the side wing boxes and the skin, and foam sandwiches are arranged in the gaps; a plurality of grooves are formed in the machine body framework, and foam sandwiches are arranged in the grooves. According to the wing with the foam sandwich structure provided by the utility model, the fuselage framework and the side wing boxes are used as the integral framework of the wing, the skin is used as the outer skin of the wing, and the foam sandwich is filled between the outer skin and the framework, so that the structural strength can be ensured, and the lightweight design can be carried out as much as possible; the design of the side wing box can enhance the structural strength of the side wing, improve the bending resistance and reduce the maximum deformation of the tip of the side wing.

Description

Technical Field

[0001] The utility model belongs to the field of wings, and particularly relates to a wing with a foam sandwich structure. Background Art

[0002] With the continuous development of unmanned aerial vehicle (UAV) technology, the requirements for lightweight and structural strength of UAVs at the present stage are also increasing. The traditional wing structures include pure metal structure wings and traditional composite material wings. The pure metal structure wing is formed by curing aluminum alloy and welding an aluminum alloy skin. After forming, the wing has high structural strength, but the overall structure is heavy, resulting in low effective utilization rate of the overall structure weight of the aircraft, and gradually unable to meet the lightweight design requirements at the present stage. The traditional composite material wing is prepared by using a carbon fiber skin and a sandwich structure. The advantage of this formed wing compared with the metal structure wing is that the overall structure is lighter, but the overall structural strength is not high, it is difficult to meet the use under large load conditions, and the wing deforms greatly during flight and is prone to damage under extreme conditions. Content of the Utility Model

[0003] The technical problem to be solved by the utility model is to provide a wing with a foam sandwich structure that can improve the anti-deformation ability of the wing on the basis of meeting the lightweight requirements.

[0004] The utility model provides a wing with a foam sandwich structure, which includes a fuselage frame, a foam sandwich, a skin and two wingtip boxes;

[0005] One end of the wingtip box is fixedly arranged on the side of the fuselage frame, and the two wingtip boxes are symmetrically arranged on both sides of the fuselage frame. The skin covers the outside of the fuselage frame and the wingtip boxes;

[0006] There is a gap between the side surface and the end surface of the wingtip box and the skin, and the foam sandwich is arranged in the gap. The wingtip box, the skin outside the wingtip box and the foam sandwich in the gap form a wingtip;

[0007] A number of grooves are arranged on the fuselage frame, and the foam sandwich is arranged in the grooves. The fuselage frame, the skin outside the fuselage frame and the foam sandwich in the grooves form a wing body.

[0008] Furthermore, the upper and lower ends of the wingtip box are attached to the skin.

[0009] Furthermore, the wing with the foam sandwich structure of the present invention further includes an aileron and an aileron drive mechanism;

[0010] There is a notch at the downstream of the wingtip, and the aileron is rotatably arranged at the notch;

[0011] The aileron drive mechanism includes a rotary drive mechanism disposed on the fuselage frame and a drive rod connecting the output end of the rotary drive mechanism and the aileron. The side wing box is hollow with openings at both ends, and the drive rod is disposed through the hollow of the side wing box.

[0012] Furthermore, a foam sandwich is disposed in the hollow of the side wing box, and a receiving groove is provided in the foam sandwich at this location. The drive rod is rotatably disposed in the receiving groove.

[0013] Furthermore, the aileron drive mechanism further includes a carbon tube disposed outside the drive rod.

[0014] Furthermore, both ends of the aileron are rotatably disposed on both sides of the notch through bushings.

[0015] Furthermore, a concave cavity is provided on the fuselage frame. The aileron drive mechanism further includes a mounting plate detachably disposed on the concave cavity, and the rotary drive mechanism is detachably disposed on the mounting plate.

[0016] Furthermore, the drive rod is a variable cross-section rod, which is successively a large end of a cone, a small end of a cone, and a flat rod from the rotary drive mechanism to the aileron direction.

[0017] Furthermore, the groove is a groove and / or a through groove.

[0018] Furthermore, several of the grooves are adjacently arranged, and a reinforcing rib structure is formed between two adjacent grooves.

[0019] The beneficial effects of the present invention are that the wing with a foam sandwich structure provided by the present invention uses the fuselage frame and the side wing box as the overall frame of the wing, and the skin as the outer skin of the wing. A foam sandwich is filled between the outer skin and the frame, which can not only ensure the structural strength but also carry out a lightweight design as much as possible. The design of the side wing box can enhance the structural strength of the side wing, improve the bending resistance, and reduce the maximum deformation of the side wing tip. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Attached Figure 1 is a schematic structural diagram of the present invention;

[0021] Attached Figure 2 is a schematic structural diagram of the present invention after hiding the skin;

[0022] Attached Figure 3 is a schematic structural diagram of the present invention after hiding the foam sandwich;

[0023] Attached Figure 4 is a front view of the present invention;

[0024] Attached Figure 5 is attached Figure 4Cross-sectional view taken along line A-A

[0025] In the figure, 100 - wing-body; 200 - side wing; 300 - aileron; 1 - fuselage frame; 11 - groove; 12 - cavity; 2 - side wing box; 3 - foam sandwich; 4 - skin; 5 - notch; 6 - fastener; 7 - aileron drive mechanism; 71 - rotary drive mechanism; 72 - drive rod; 73 - mounting plate; 74 - carbon tube. Detailed implementation manners

[0026] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0027] It should be noted that all directional indications (such as up, down, left, right, front, back...) in the embodiments of the present invention are only used to explain the relative position relationship and movement conditions between components in a specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indications will also change accordingly.

[0028] In addition, in the present invention, descriptions such as "first" and "second" are only for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the quantity of the indicated technical features. Thus, features defined with "first" and "second" may explicitly or implicitly include at least one of such features. In the description of the present invention, "a plurality" means at least two, such as two, three, etc., unless otherwise specifically defined.

[0029] In the present invention, unless otherwise clearly defined and limited, terms such as "connection" and "fixation" should be understood in a broad sense. For example, "fixation" can be a fixed connection, a detachable connection, or integrated; it can be a mechanical connection, an electrical connection, a physical connection or a wireless communication connection; it can be directly connected, or indirectly connected through an intermediate medium, and can be the internal communication of two components or the interaction relationship between two components, unless otherwise clearly limited. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0030] In addition, the technical solutions between the various embodiments of the present invention can be combined with each other, but it must be based on the fact that those of ordinary skill in the art can implement it. When the combination of technical solutions is contradictory or cannot be implemented, it should be considered that such a combination of technical solutions does not exist and is not within the protection scope required by the present invention.

[0031] As shown in the attached Figure 1 - attachment Figure 5 As shown, the present utility model provides a wing with a foam sandwich structure, including a fuselage skeleton 1, a foam sandwich 3, a skin 4, and two wing boxes 2. The fuselage skeleton 1 is preferably made of aluminum alloy material to ensure the overall strength and stiffness. The wing box 2 is preferably made of carbon fiber material to ensure the bending resistance. The foam sandwich 3 is made of PMI material, and the skin 4 is preferably made of aluminum alloy plate;

[0032] One end of the wing box 2 is fixedly arranged on the side of the fuselage skeleton 1. Preferably, the wing box 2 is detachably installed on the side of the fuselage skeleton 1 through fasteners to facilitate the processing of the fuselage skeleton 1 and the wing box 2. The two wing boxes 2 are symmetrically arranged on both sides of the fuselage skeleton 1. The skin 4 is covered on the outside of the fuselage skeleton 1 and the wing box 2. The skin 4 can be a whole piece or assembled by multiple plates, which can be specifically selected according to needs;

[0033] There is a gap between the side surface and the end surface of the wing box 2 and the skin 4. The skin 4 located outside the wing box 2 is in the configuration of the wing flank. The foam sandwich 3 is arranged in the gap. The foam sandwich 3 can improve the structural strength of the skin 4, while the skin 4 can ensure the smoothness of the outer wall surface of the wing, reduce air resistance, and at the same time prevent external dust and rain from entering the foam sandwich 3, causing changes in the physical and chemical properties of the foam sandwich 3. The wing box 2, the skin 4 outside the wing box 2, and the foam sandwich 3 in the gap form the wing flank 200;

[0034] A number of grooves 11 are arranged on the fuselage skeleton 1, and the foam sandwich 3 is arranged in the grooves 11. Arranging the grooves 11 can, on the one hand, reduce the weight of the fuselage skeleton 1, thereby ensuring the light weight of the wing. On the other hand, the space between the grooves 11 and the skin 4 can be used to fill the foam sandwich 3, providing an installation space for the foam sandwich 3. The foam sandwich 3 here can fill the space in the grooves 11 to support the skin 4 and improve the structural strength of the skin 4. The fuselage skeleton 1, the skin 4 outside the fuselage skeleton 1, and the foam sandwich 3 in the grooves 11 form the wing-body 100.

[0035] Preferably, the middle part of the skin 4 at the wing-body 100 is a planar structure, which can be used to connect the fuel tank compartment, and the outside is a curved surface structure that smoothly transitions with the planar structure. On the one hand, it can reduce stress concentration, and on the other hand, it can meet the requirements of the aerodynamic shape. Preferably, threaded mounting holes for external devices are also arranged at the corresponding positions of the fuselage skeleton 1 and the skin 4.

[0036] The wing with a foam sandwich structure provided by the present utility model uses the fuselage frame 1 and the wing side box 2 as the overall frame of the wing, and the skin 4 as the outer skin of the wing. A foam sandwich 3 is filled between the outer skin and the frame, which can not only ensure the structural strength but also conduct lightweight design as much as possible. The design of the wing side box 2 can enhance the structural strength of the wing side 200, improve the bending resistance performance, and reduce the maximum deformation of the wing tip of the wing side 200.

[0037] In one embodiment, refer to the attached Figure 5 , the upper and lower ends of the wing side box 2 are arranged in fit with the skin 4. Such an arrangement enables the wing side box 2 to support and fix the skin 4 and shape the skins 4 on both sides.

[0038] In one embodiment, the wing with the foam sandwich structure further includes ailerons 300 and an aileron drive mechanism 7;

[0039] A notch 5 is arranged downstream of the wing side 200, and the ailerons 300 are rotatably arranged at the notch 5. Preferably, the structural shape of the ailerons 300 is adapted to the shape of the notch 5;

[0040] The aileron drive mechanism 7 includes a rotary drive mechanism 71 arranged on the fuselage frame 1 and a drive rod 72 connecting the output end of the rotary drive mechanism 71 and the ailerons 300. The inside of the wing side box 2 is hollow and open at both ends. The drive rod 72 is arranged through the hollow of the wing side box 2. In this embodiment, the wing side box 2 can also be used to install the drive rod 72, allowing the drive rod 72 to rotate inside the wing side 200, facilitating the transmission of the driving force from the rotary drive mechanism 71 located on the fuselage frame 1 to the ailerons 300 located on the wing side 200. Among them, the rotary drive mechanism 71 preferably uses a rotary servo.

[0041] In one embodiment, a foam sandwich 3 is arranged in the hollow of the wing side box 2, and a receiving groove 31 is arranged on the foam sandwich 3 at this position. The drive rod 72 is rotatably arranged in the receiving groove 31, thereby improving the structural strength of the wing side box 2 and, to a certain extent, restricting the moving range of the drive rod 72 and improving the limiting ability.

[0042] In one embodiment, the aileron drive mechanism 7 further includes a carbon tube 74 arranged outside the drive rod 72. By arranging the carbon tube 74, the structural strength of the drive rod 72 can be improved on the premise of ensuring lightweight.

[0043] In one embodiment, both ends of the aileron 300 are rotatably arranged on both sides of the notch 5 through a bushing 8. The bushing 8 is preferably a nylon bushing, which can not only limit the lateral movement of the aileron 300 along the axial direction, but also improve its rotation effect, meet the use requirements of the aileron 300 under a large aerodynamic load, and at the same time prevent its rotation from damaging the drive rod 72.

[0044] In one embodiment, a concave cavity 12 is provided on the fuselage frame 1. The aileron drive mechanism 7 further includes a mounting plate 73 detachably arranged on the concave cavity 12, and the rotary drive mechanism 71 is detachably arranged on the mounting plate 73. Preferably, the mounting plate 73 is detachably fixed on the concave cavity 12 through a fastener 6, and the rotary drive mechanism 71 is detachably fixed on the mounting plate 73 through a fastener 6, so as to simplify the difficulty of fixing the rotary drive mechanism 71 on the fuselage frame 1.

[0045] In one embodiment, the drive rod 72 is a variable cross-section rod, which is successively a large end of a cone, a small end of a cone and a flat rod from the rotary drive mechanism 71 to the aileron 300 direction. Therefore, the drive rod 72 needs to bear a certain torsional stress. However, due to the limited local space reserved at the aileron 300, a combined form of a conical structure and a flat structure is adopted for the drive rod 72, and a flattened rod body structure is adopted near the aileron 300, so as to achieve the lightest weight while meeting its torsional performance requirements.

[0046] In one embodiment, the groove 11 is a groove and / or a through groove. Preferably, a groove structure is adopted in the middle of the fuselage frame 1 to make it have a bottom plate to ensure the structural strength, while through groove structures are adopted on the front and rear sides of the fuselage frame 1, so as to realize the lightweight design.

[0047] In one embodiment, several of the grooves 11 are arranged adjacent to each other, and a reinforcing rib structure is formed between two adjacent grooves 11, that is, a raised reinforcing rib is formed between two adjacent grooves 11 to ensure the structural strength and bending resistance.

[0048] The above is only this embodiment and does not impose any limitation on the present utility model. Any person skilled in the art can, without departing from the scope of the technical solution of the present utility model, make many possible changes, modifications or equivalents to equivalent embodiments by using the technical content disclosed above. Therefore, any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present utility model without departing from the content of the technical solution of the present utility model shall fall within the scope of the protection of the technical solution of the present utility model.

Claims

1. An aircraft wing with a foam sandwich structure, characterized in that, It includes a fuselage frame (1), a foam sandwich (3), a skin (4) and two wing boxes (2); The two wing boxes (2) are symmetrically arranged on both sides of the fuselage frame (1), and the skin (4) is wrapped on the outside of the fuselage frame (1) and the wing boxes (2); There is a gap between the side and end faces of the wing box (2) and the skin (4), and the foam sandwich (3) is arranged in the gap. The wing box (2), the skin (4) outside the wing box (2) and the foam sandwich (3) in the gap form a wing (200); A number of grooves (11) are arranged on the fuselage frame (1), and the foam sandwich (3) is arranged in the grooves (11). The fuselage frame (1), the skin (4) outside the fuselage frame (1) and the foam sandwich (3) in the grooves (11) form a wing-body (100).

2. The wing with a foam sandwich structure according to claim 1, characterized in that, The upper and lower ends of the wing box (2) are fitted with the skin (4).

3. The wing with a foam sandwich structure according to claim 1, characterized in that, It further includes ailerons (300) and an aileron drive mechanism (7); There is a notch (5) downstream of the wing (200), and the ailerons (300) are rotatably arranged at the notch (5); The aileron drive mechanism (7) includes a rotary drive mechanism (71) arranged on the fuselage frame (1) and a drive rod (72) connecting the output end of the rotary drive mechanism (71) and the ailerons (300). The inside of the wing box (2) is hollow and open at both ends, and the drive rod (72) passes through the hollow of the wing box (2).

4. The wing with a foam sandwich structure as claimed in claim 3, wherein, The foam sandwich (3) is arranged in the hollow of the wing box (2), and a receiving groove (31) is arranged on the foam sandwich (3) at this position. The drive rod (72) is rotatably arranged in the receiving groove (31).

5. The wing with a foam sandwich structure according to claim 4, characterized in that, The aileron drive mechanism (7) further includes a carbon tube (74) arranged outside the drive rod (72).

6. The wing with a foam sandwich structure as described in claim 3, characterized in that, Both ends of the ailerons (300) are rotatably arranged on both sides of the notch (5) through bushings (8).

7. The wing with a foam sandwich structure as claimed in claim 3, characterized in that, A concave cavity (12) is arranged on the fuselage frame (1). The aileron drive mechanism (7) further includes a mounting plate (73) detachably arranged on the concave cavity (12), and the rotary drive mechanism (71) is detachably arranged on the mounting plate (73).

8. The wing with a foam sandwich structure according to claim 3, characterized in that, The drive rod (72) is a variable cross-section rod, which is successively a large end of a cone, a small end of a cone and a flat rod from the rotary drive mechanism (71) to the ailerons (300).

9. The wing with a foam sandwich structure according to any one of claims 1-8, characterized in that, The groove (11) is a groove and / or a through groove.

10. The wing with a foam sandwich structure according to any one of claims 1-8, characterized in that, A number of the grooves (11) are arranged adjacent to each other, and a rib structure is formed between two adjacent grooves (11).

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