Wing structure

Abstract

The embodiment of the present invention discloses a wing structure, which includes: a wing body, an upper skin, a lower skin and a leading edge patch; wherein the upper skin is attached to the upper surface of the wing body, and the lower skin is attached to the lower surface of the wing body; wherein a groove is formed on the leading edge patch, and the leading edge patch is sleeved on the wing body through the groove, and the seam between the upper skin and the lower skin is located in the groove. The wing structure can reduce the probability of delamination or cracking at the joint of the upper and lower skins of the wing.

Description

Technical Field

[0001] The present invention relates to the field of aircraft, and in particular to a wing structure. Background Art

[0002] In recent years, unmanned military equipment has penetrated almost every field of the battlefield space. Drones have become an important and even critical force affecting the course of combat and have been paid attention to by more and more countries. The military departments of many countries have given priority to the development of drones.

[0003] At present, composite wing structures basically adopt the structure of upper and lower skin + frame. The joint of the upper and lower skin of the wing leading edge has the problem of delamination and cracking during use.

[0004] Therefore, it is necessary to develop a wing structure that can reduce the probability of delamination or cracking at the junction of the upper and lower skins of the wing.

[0005] The information disclosed in the background technology section of the present invention is only intended to deepen the understanding of the general background technology of the present invention, and should not be regarded as acknowledging or suggesting in any form that the information constitutes the prior art already known to those skilled in the art. Summary of the invention

[0006] The object of the present invention is to provide a wing structure which can reduce the probability of delamination or cracking at the junction of the upper and lower skins of the wing.

[0007] In order to achieve the above object, a wing structure is provided according to the present invention, the wing structure comprising: a wing body, an upper skin, a lower skin and a leading edge patch;

[0008] Wherein, the upper skin is attached to the upper surface of the wing body, and the lower skin is attached to the lower surface of the wing body;

[0009] A groove is formed on the leading edge patch, the leading edge patch is sleeved on the wing body through the groove, and the joint between the upper skin and the lower skin is located in the groove.

[0010] Preferably, the leading edge patch is an integrally formed structure, and the cross-section of the leading edge patch is V-shaped. When the leading edge patch is sleeved on the wing body, the tip of the V-shape faces away from the wing body.

[0011] Preferably, the wing body comprises a front beam, a rear wall, ribs and a load-bearing main beam;

[0012] Among them, the front beam and the rear wall are arranged opposite to each other, the load-bearing main beam is connected to the front beam and the rear wall, one end of the rib plate is connected to the rear wall, and the other end is connected to the load-bearing main beam or the front beam, and the rib plate is located between the front beam and the rear wall.

[0013] Preferably, the wing structure further comprises: tenon holes, the tenon holes are provided on the front beam and the rear wall, and the rib plate and the load-bearing main beam are mortise-jointed to the rear wall and the front beam through the tenon holes.

[0014] Preferably, the cross-section of the load-bearing main beam is an I-shape, the upper end surface of the I-shape is attached to the upper skin, and the lower end surface is attached to the lower skin.

[0015] Preferably, a first connecting surface is provided at the top of the load-bearing main beam, and a second connecting surface is provided at the bottom, the first connecting surface is attached to the upper skin, the second connecting surface is attached to the lower skin, and the first connecting surface and the second connecting surface are planes.

[0016] Preferably, the wing structure further comprises: an adhesive layer, wherein the adhesive layer is provided between the upper skin and the leading edge patch and between the lower skin and the leading edge patch.

[0017] Beneficial effects:

[0018] 1) The wing structure provided by the present invention embeds the leading edge patch on the wing body so that the joint between the upper skin and the lower skin is located in the leading edge patch, thereby protecting the joint between the upper skin and the lower skin and preventing delamination or cracking at the joint between the upper and lower skins of the wing.

[0019] 2) The wing structure provided by the present invention has an I-shaped cross section of the load-bearing main beam, which increases the contact area between the load-bearing main beam and the upper and lower skins, thereby increasing the force-bearing area and improving the stress concentration problem of the load-bearing main beam, making the operation of the drone safer. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a schematic diagram of the exploded structure of a wing structure according to an embodiment of the present invention.

[0021] Figure 2 It is a schematic structural diagram of a wing structure according to an embodiment of the present invention.

[0022] Figure 3 It is a schematic cross-sectional view of a load-bearing main beam of a wing structure according to an embodiment of the present invention.

[0023] Description of reference numerals:

[0024] 1. Upper skin; 2. Lower skin; 3. Front edge patch; 4. Front beam; 5. Rear wall; 6. Rib plate; 7. Load-bearing main beam. DETAILED DESCRIPTION

[0025] The technical solution of the present invention is described in detail below with reference to the accompanying drawings.

[0026] According to one aspect of the present invention, a wing structure is provided, the wing structure comprising: a wing body, an upper skin, a lower skin and a leading edge patch;

[0027] Wherein, the upper skin is attached to the upper surface of the wing body, and the lower skin is attached to the lower surface of the wing body;

[0028] A groove is formed on the leading edge patch, the leading edge patch is sleeved on the wing body through the groove, and the joint between the upper skin and the lower skin is located in the groove.

[0029] The wing structure provided by the present invention nests a leading edge patch on the wing body so that the joint between the upper skin and the lower skin is located within the leading edge patch, thereby protecting the joint between the upper skin and the lower skin and avoiding delamination or cracking at the joint between the upper and lower skins of the wing.

[0030] The wing structure provided by the present invention plays a role in protecting the wing body by bonding an upper skin to the upper surface of the wing body and a lower skin to the lower surface of the wing body. At the same time, it can reduce the wind resistance of the wing structure, so that a drone or aircraft equipped with the wing structure can run more smoothly and with lower energy consumption.

[0031] As a preferred solution, the leading edge patch is an integrally formed structure, the cross section of the leading edge patch is V-shaped, and when the leading edge patch is sleeved on the wing body, the tip of the V-shape faces away from the wing body.

[0032] In this technical solution, a leading edge patch structure is further provided, the leading edge patch section is V-shaped, and the tip of the V-shape is away from the wing body, so that the UAV or aircraft equipped with the wing structure can run more smoothly and consume less energy. At the same time, the leading edge patch is an integrated structure, which improves the mechanical strength of the leading edge patch and ensures the safety factor of the wing structure.

[0033] As a preferred solution, the wing body includes a front beam, a rear wall, ribs and a load-bearing main beam;

[0034] Among them, the front beam and the rear wall are arranged opposite to each other, the load-bearing main beam is connected to the front beam and the rear wall, one end of the rib plate is connected to the rear wall, and the other end is connected to the load-bearing main beam or the front beam, and the rib plate is located between the front beam and the rear wall.

[0035] In this technical solution, a wing body structure is further provided. The wing body includes a front beam, a rear wall, ribs and a load-bearing main beam, which plays the role of bearing the main stress. The strength of the wing structure is further guaranteed by the setting of the ribs.

[0036] As a preferred solution, the wing structure further comprises: tenon holes, the tenon holes are provided on the front beam and the rear wall, and the rib plate and the load-bearing main beam are mortise-jointed to the rear wall and the front beam through the tenon holes.

[0037] In this technical solution, tenon holes are further included, and the front beam, rear wall, rib plate and load-bearing main beam are connected by tenon joints. On the one hand, it is convenient for the assembled installation of the wing body, and on the other hand, it makes the wing body have stronger mechanical strength.

[0038] As a preferred solution, the cross-section of the load-bearing main beam is an I-shape, the upper end surface of the I-shape is attached to the upper skin, and the lower end surface is attached to the lower skin.

[0039] In this technical solution, the cross section of the load-bearing main beam is an I-shaped one, which increases the contact area between the load-bearing main beam and the upper and lower skins, thereby increasing the force-bearing area and improving the stress concentration problem of the load-bearing main beam, making the operation of the drone safer.

[0040] As a preferred embodiment, a first connecting surface is provided at the top of the load-bearing main beam, and a second connecting surface is provided at the bottom, the first connecting surface is attached to the upper skin, the second connecting surface is attached to the lower skin, and the first connecting surface and the second connecting surface are planes.

[0041] In this technical solution, a first connection surface is provided on the top of the load-bearing main beam, and a second connection surface is provided on the bottom, which increases the contact area between the load-bearing main beam and the upper and lower skins, thereby increasing the force-bearing area and improving the stress concentration problem of the load-bearing main beam, making the operation of the drone safer.

[0042] As a preferred solution, the wing structure further comprises: an adhesive layer, wherein the adhesive layer is arranged between the upper skin and the leading edge patch and between the lower skin and the leading edge patch.

[0043] This technical solution further includes an adhesive layer. Through the provision of the adhesive layer, the leading edge patch is more securely fixed, making the use of the wing structure safer.

[0044] Example 1

[0045] Figure 1 It is a schematic diagram of the exploded structure of a wing structure according to an embodiment of the present invention. Figure 2 It is a schematic structural diagram of a wing structure according to an embodiment of the present invention. Figure 3It is a schematic cross-sectional view of a load-bearing main beam of a wing structure according to an embodiment of the present invention.

[0046] like Figures 1 to 3 As shown, the wing structure includes: a wing body, an upper skin 1, a lower skin 2 and a leading edge patch 3;

[0047] Wherein, the upper skin 1 is attached to the upper surface of the wing body, and the lower skin 2 is attached to the lower surface of the wing body;

[0048] A groove is formed on the leading edge patch 3, and the leading edge patch 3 is sleeved on the wing body through the groove, and the joint between the upper skin 1 and the lower skin 2 is located in the groove.

[0049] The leading edge patch 3 is an integrally formed structure, and the cross section of the leading edge patch 3 is V-shaped. When the leading edge patch 3 is sleeved on the wing body, the tip of the V-shape is away from the wing body.

[0050] The wing body includes a front beam 4, a rear wall 5, a rib plate 6 and a load-bearing main beam 7;

[0051] Among them, the front beam 4 and the rear wall 5 are arranged opposite to each other, the load-bearing main beam 7 is connected to the front beam 4 and the rear wall 5, one end of the rib plate 6 is connected to the rear wall 5, and the other end is connected to the load-bearing main beam 7 or the front beam 4, and the rib plate 6 is located between the front beam 4 and the rear wall 5.

[0052] The wing structure further includes: tenon holes, which are provided on the front beam 4 and the rear wall 5, and the ribs 6 and the load-bearing main beam 7 are mortise-jointed to the rear wall 5 and the front beam 4 through the tenon holes.

[0053] The cross section of the load-bearing main beam 7 is an I-shape, the upper end surface of the I-shape is attached to the upper skin 1 , and the lower end surface is attached to the lower skin 2 .

[0054] The wing structure further includes: an adhesive layer, wherein the adhesive layer is arranged between the upper skin 1 and the leading edge patch 3 and between the lower skin 2 and the leading edge patch 3 .

[0055] like Figure 1 As shown, the present invention divides the leading edge of the wing and makes the leading edge of the wing into an integral part, namely, the leading edge patch 3; the load-bearing main beam 7 is formed by a mold at one time, and the upper and lower surfaces of the load-bearing main beam 7 are connected to the upper skin 1 and the lower skin 2. The load-bearing main beam 7, the front beam 4, and the rib plate 6 are connected through tenon holes, and after being glued to the rear wall 5, they are glued to the lower skin 2 and the upper skin 1 to form a whole, and then the leading edge patch 3 is positioned and glued to the integral wing body after the mold is closed to form a complete wing structure.

[0056] In this example, the leading edge patch 3 is integrally formed to wrap the mold line of the upper skin 1 and the lower skin 2 so that they are not affected by the outside world, so as to achieve the purpose of preventing the mold joint from delamination and cracking. Figure 3 As shown, the load-bearing main beam 7 is an "I"-shaped structure, and its upper and lower parts are in contact with the upper skin 1 and the upper skin 1 respectively, which increases the force-bearing area and improves the stress concentration problem of the load-bearing main beam 7.

[0057] Finally, it should be noted that the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or replace some of the technical features therein by equivalents. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A wing structure, characterized in that: The wing structure includes: a wing body, an upper skin, a lower skin and a leading edge patch; Wherein, the upper skin is attached to the upper surface of the wing body, and the lower skin is attached to the lower surface of the wing body; Wherein, a groove is formed on the leading edge patch, the leading edge patch is sleeved on the wing body through the groove, and the seam between the upper skin and the lower skin is located in the groove; The wing body includes a front beam, a rear wall, ribs and a load-bearing main beam; Wherein, the front beam is arranged opposite to the rear wall, the load-bearing main beam is connected to the front beam and the rear wall, one end of the rib plate is connected to the rear wall, and the other end is connected to the load-bearing main beam or the front beam, and the rib plate is located between the front beam and the rear wall; The cross section of the load-bearing main beam is an I-shaped beam, the upper end surface of the I-shaped beam is attached to the upper skin, and the lower end surface is attached to the lower skin; The leading edge patch is an integrally formed structure, and the cross section of the leading edge patch is V-shaped. When the leading edge patch is sleeved on the wing body, the tip of the V-shape is away from the wing body; An adhesive layer is provided between the upper skin and the leading edge patch and between the lower skin and the leading edge patch.

2. The wing structure according to claim 1, characterized in that: Also includes: Tenon holes are provided on the front beam and the rear wall, and the rib plate and the load-bearing main beam are mortise-jointed to the rear wall and the front beam through the tenon holes.

3. The wing structure according to claim 1, characterized in that: The top of the load-bearing main beam is provided with a first connecting surface, and the bottom is provided with a second connecting surface. The first connecting surface is attached to the upper skin, and the second connecting surface is attached to the lower skin. The first connecting surface and the second connecting surface are planes.

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