Wing leading edge structure and aircraft wing

Abstract

The utility model belongs to the technical field of aircraft wings, and discloses a wing leading edge structure and an aircraft wing. The wing leading edge structure comprises an outer skin, a heating film and a honeycomb supporting assembly, the outer skin is located on the outer side of the wing leading edge structure, the heating film is laid on the inner side of the outer skin, the heating film is configured to heat the outer skin, and the honeycomb supporting assembly is arranged on the side, away from the outer skin, of the heating film. Due to the arrangement of the wing leading edge structure, the wing leading edge structure can be uniformly heated, a heating film is protected from being eroded by the external environment, the anti-icing and deicing effects of the wing leading edge structure are improved, the wing section is not influenced, meanwhile, the bird impact resistance is improved, and the weight reduction of the wing leading edge structure is facilitated. According to the aircraft wing provided by the utility model, by applying the wing leading edge structure, the anti-icing and deicing effects of the aircraft wing can be improved, the wing section cannot be influenced, the bird impact resistance is improved, and the lightweight of the aircraft wing is facilitated.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of aircraft wing, especially to a wing leading edge structure and aircraft wing. BACKGROUND

[0002] For the wing leading edge structure of the aircraft, there is a risk from the environment during cruising, mainly wing leading edge icing and bird strike.

[0003] The prior art has been able to realize the anti-icing and deicing function of the wing leading edge structure, but usually takes the metal skin of the wing leading edge structure as a heating carrier to carry out anti-icing and deicing, which leads to the outermost metal skin being eroded by the external environment during the cruising of the aircraft, the heating effect being poor, the anti-icing and deicing effect being poor, and the heating area being uneven, thereby causing the ice on the wing leading edge structure not to be completely removed to affect the wing profile.

[0004] In addition, bird strike is also an important factor threatening the flight safety of the aircraft during the cruising of the aircraft, and the prior art usually adds a support assembly inside the wing leading edge structure to improve the bird strike resistance of the wing leading edge structure, but the setting of the support assembly leads to the increase of the weight of the wing leading edge structure, affecting the flight safety. UTILITY MODEL CONTENTS

[0005] The utility model aims at providing a wing leading edge structure and aircraft wing, which can prevent the heating film from being eroded by the external environment, improve the protection of the heating film, make the outer skin be uniformly heated, improve the deicing and anti-icing effect, ensure the stability of the wing profile, reduce the weight of the wing leading edge structure while improving the bird strike resistance of the wing leading edge structure, and make the wing leading edge structure lightweight.

[0006] To achieve this purpose, the utility model adopts the following technical solutions:

[0007] The wing leading edge structure comprises:

[0008] an outer skin;

[0009] a heating film, which is laid on the inner side of the outer skin and is configured to heat the outer skin; and

[0010] a honeycomb support assembly, which is arranged on the side of the heating film away from the outer skin.

[0011] Preferably, the honeycomb support assembly comprises:

[0012] an inner panel, which is arranged on the side of the heating film away from the outer skin;

[0013] An outer panel is connected with the inner panel and forms a cavity with the inner panel; and

[0014] A honeycomb structure is accommodated in the cavity.

[0015] Preferably, the outer skin comprises a connected laying area and a connecting area, the connecting area is arranged around the periphery of the laying area, the inner side of the laying area is laid with the heating film, and the inner panel is fixedly connected with the inner side of the connecting area.

[0016] Preferably, the area of the honeycomb structure is smaller than the area of the heating film, and the interval between the outer edge of the honeycomb structure projected on the inner panel and the outer edge of the heating film projected on the inner panel is H1.

[0017] Preferably, the inner panel is made of carbon fiber material; and / or, the outer panel is made of carbon fiber material.

[0018] Preferably, a through hole is arranged on the honeycomb support assembly, the through hole penetrates the inner panel and the outer panel;

[0019] The heating film is an electric heating film, the wing leading edge structure further comprises an electrode, the electrode is accommodated in the through hole, and the electrode is electrically connected with the heating film.

[0020] Preferably, along the chord direction of the wing leading edge structure, the distance d between the edge of the through hole and the edge of the inner panel is 10mm-50mm.

[0021] Preferably, the outer skin, the heating film and the honeycomb support assembly are integrally formed.

[0022] Preferably, the outer skin is made of metal material.

[0023] An aircraft wing comprises a wing main body and a wing leading edge structure as described above, and the wing leading edge structure is detachably mounted on the wing main body.

[0024] The beneficial effects of the present application are as follows:

[0025] The utility model provides a kind of wing leading edge structure.The wing leading edge structure includes outer skin, heating film and honeycomb support component, heating film is laid in the inside of outer skin, heating film is configured as heating outer skin, honeycomb support component is located in the side of heating film away from outer skin.By heating film is laid in the inside of outer skin, and heating film can heat outer skin, to ensure that outer skin can be fully received heat from heating film, so that heat is evenly distributed on outer skin, so that outer skin can be evenly heated, improve the deicing and anti-icing effect of wing leading edge structure, ensure the normal work of wing leading edge structure;In addition, since heating film is laid in the inside of outer skin, it can effectively prevent heating film from being eroded by external environment, improve the protection of heating film;In addition, honeycomb support component is arranged at the side of heating film away from outer skin, can make the structure of honeycomb support component support outer skin, honeycomb support component can disperse and absorb impact when being bird-striking, improve the bird-striking performance, and facilitate the light weight of wing leading edge structure.

[0026] The utility model also provides an airplane wing, which applies the wing leading edge structure, can improve the bird-striking performance of the airplane wing, facilitate the light weight of the airplane wing, and can heat the outer skin evenly, prevent the heating film from being eroded by external environment, and not affect the airfoil. ACCOUNT OF DRAWINGS

[0027] Figure 1 It is the schematic diagram of wing leading edge structure provided by the utility model embodiment;

[0028] Figure 2 It is the sectional view of wing leading edge structure provided by the utility model embodiment;

[0029] Figure 3 It is Figure 2 The enlarged view of A in the middle;

[0030] Figure 4 It is the schematic diagram of honeycomb structure of wing leading edge structure provided in the utility model embodiment;

[0031] Figure 5 It is the schematic diagram of partial structure of outer skin of wing leading edge structure provided in the utility model embodiment;

[0032] Figure 6 It is the schematic diagram of partial structure of wing leading edge structure provided in the utility model embodiment.

[0033] In the drawing:

[0034] 10, wing leading edge structure;

[0035] 1, outer skin;11, laying area;12, connecting area;

[0036] 2. heating film;

[0037] 3. honeycomb support assembly; 31, inner panel; 311, through hole; 32, outer panel; 33, honeycomb structure. DETAILED DESCRIPTION

[0038] The utility model will be described in further detail below in connection with the drawings and embodiments. It can be understood that the specific embodiments described herein are only used to explain the utility model, and not to limit the utility model. In addition, it should be noted that, in order to facilitate the description, only the part related to the utility model is shown in the drawings, not all structures.

[0039] In the description of the utility model, unless otherwise explicitly specified and limited, the terms "connected", "connected", "fixed" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or it can be integrated, it can be mechanically connected, or it can be electrically connected, it can be directly connected, or it can be indirectly connected through an intermediate medium, it can be the internal communication of two elements or the interaction relationship of two elements. For ordinary skilled in the art, the specific meaning of the above terms in the utility model can be understood according to the specific circumstances.

[0040] In the utility model, unless otherwise explicitly specified and limited, the first feature "on" or "below" the second feature can include that the first and second features are in direct contact, or the first and second features are not in direct contact but are in contact through another feature between them. Moreover, the first feature "on", "above" and "above" the second feature includes that the first feature is directly above and obliquely above the second feature, or only indicates that the horizontal height of the first feature is higher than that of the second feature. The first feature "below", "below" and "below" the second feature includes that the first feature is directly below and obliquely below the second feature, or only indicates that the horizontal height of the first feature is less than that of the second feature.

[0041] In the description of the embodiment, the terms "up", "down", "right", etc. orientation or position relationship is based on the orientation or position relationship shown in the drawings, only for the convenience of description and simplification of operation, and does not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, therefore it cannot be understood as a limitation on the utility model. In addition, the terms "first", "second" are only used to distinguish in the description, and have no special meaning.

[0042] As Figures 1-3As shown, the embodiment provides a wing leading edge structure 10, which comprises an outer skin 1, a heating film 2 and a honeycomb support assembly 3. The heating film 2 is arranged on the inner side of the outer skin 1 and configured to heat the outer skin 1. The honeycomb support assembly 3 is arranged on the side of the heating film 2 away from the outer skin 1. By arranging the heating film 2 on the inner side of the outer skin 1 and enabling the heating film 2 to heat the outer skin 1, the outer skin 1 can fully receive heat from the heating film 2, and the heat is evenly distributed on the outer skin 1, so that the wing leading edge structure 10 is evenly heated when deicing and icing prevention, the deicing and icing prevention effect of the wing leading edge structure 10 is improved, and the appearance of the wing leading edge structure 10 is not changed, so that the stability of the airfoil is ensured. In addition, since the heating film 2 is arranged on the inner side of the outer skin 1, the heating film 2 is prevented from being eroded by the external environment, and the protection of the heating film 2 is improved. In addition, the honeycomb support assembly 3 is arranged on the side of the heating film 2 away from the outer skin 1, so that the honeycomb support assembly 3 can support the structure of the outer skin 1, and the honeycomb support assembly 3 can disperse and absorb the impact when being hit by a bird, so that the anti-bird performance is improved, and the weight of the wing leading edge structure 10 is reduced, which is beneficial to the lightweight of the wing leading edge structure 10.

[0043] Further, the outer skin 1 is made of a metal material. The metal material has excellent strength and corrosion resistance, can effectively protect the internal structure, and has good thermal conductivity, can quickly dissipate the heat generated by the heating film 2, and accelerate the deicing and icing prevention speed of the wing leading edge structure 10. Optionally, in the embodiment, the metal material can be corrosion-resistant steel, aluminum alloy or titanium alloy, etc. The embodiment preferably uses aluminum alloy, which has light weight and forms a protective film on the outer surface, has good corrosion resistance, and can ensure the normal work of the heating film 2.

[0044] Further, as shown in Figure 2 and Figure 3 , the honeycomb support assembly 3 comprises an inner panel 31, an outer panel 32 and a honeycomb structure 33. The inner panel 31 is arranged on the side of the heating film 2 away from the outer skin 1. The outer panel 32 is connected with the inner panel 31 and forms a cavity between the inner panel 31 and the outer panel 32. The honeycomb structure 33 is accommodated in the cavity. The above arrangement provides accommodation space for the honeycomb structure 33, and the honeycomb structure 33 can be placed in the cavity, so that the whole honeycomb support assembly 3 has excellent strength and stability. In addition, the porous characteristics of the honeycomb structure 33 not only reduce the overall weight, but also can disperse the impact kinetic energy when being impacted, and protect the structure of the outer skin 1. In addition, the inner panel 31 and the outer panel 32 can protect the honeycomb structure 33 from being damaged by the external environment. Optionally, in the embodiment, the profiles of the inner panel 31 and the outer panel 32 are the same as the profile of the outer skin 1, so that they can be tightly connected and ensure the consistency of the overall structure.

[0045] Alternatively, as Figure 4 As shown, in this embodiment, the honeycomb structure 33 is an overstretched honeycomb. Overstretched honeycombs can produce large bending deformation in a certain direction, which is suitable for the situation of this embodiment. In other embodiments, the honeycomb structure 33 can be a common hexagonal honeycomb. As long as it is a honeycomb structure 33, there is no limitation here.

[0046] Further, if Figure 5 As shown, the outer skin 1 includes a connected laying area 11 and a connecting area 12. The connecting area 12 is arranged around the outer periphery of the laying area 11. The heating film 2 is laid on the inner side of the laying area 11, and the inner panel 31 is fixedly connected to the inner side of the connecting area 12. This design not only ensures the maximum heating area of ​​the heating film 2 in the laying area 11, achieving the effect of overall heating stability, but also ensures the stable connection between the inner panel 31 and the outer skin 1, ensuring that when the inner panel 31 and the inner side of the connecting area 12 are fixed, the heating film 2 will not extend beyond the laying area 11, thereby preventing the heating film 2 from being damaged. It should be noted that in this embodiment, the gap between the outer edge of the laying area 11 and the outer edge of the connecting area 12 is H2, thereby ensuring that the area of ​​the connection between each position of the inner panel 31 in the circumferential direction and the connecting area 12 is consistent, ensuring the stability and reliability of the connection between the inner panel 31 and the connecting area 12.

[0047] Further, if Figure 5 and Figure 6 As shown, the area of ​​the honeycomb structure 33 is smaller than that of the heating film 2, and the distance H1 between the outer edge of the honeycomb structure 33 projected onto the inner panel 31 and the outer edge of the heating film 2 projected onto the inner panel 31 is . Because the heating film 2 is not sandwiched between the inner panel 31 and the connection area 12, during the lamination process of the wing leading edge structure 10, the lack of heating film 2 causes the inner panel 31 in the connection area 12 to be slightly recessed relative to the inner panel 31 in the laying area 11 in the lamination direction. However, the above arrangement allows the honeycomb structure 33 to overlap only with the laying area 11, preventing the honeycomb structure 33 from overlapping the recessed area, thereby preventing breakage and damage to the honeycomb structure 33 during subsequent lamination. Furthermore, the honeycomb structure 33 serves as the central support for the heating film 2, ensuring stability and reliability during the heating process.

[0048] Optionally, in the embodiment, the inner panel 31 and the outer panel 32 are both made of carbon fiber material, preferably carbon fiber fabric. The carbon fiber fabric has excellent mechanical properties, can provide good firmness and stability for the honeycomb support assembly 3, can further improve the impact resistance of the honeycomb support assembly 3, can also make the honeycomb support assembly 3 more lightweight, and the carbon fiber fabric can protect the honeycomb structure 33 from high temperature. In other embodiments, the inner panel 31 or the outer panel 32 can also be made of carbon fiber material.

[0049] Further, the honeycomb support assembly 3 is provided with a through hole 311 penetrating the inner panel 31 and the outer panel 32. The heating film 2 is an electric heating film, and the wing leading edge structure 10 further comprises an electrode (not shown in the figure) accommodated in the through hole 311, and the electrode is electrically connected with the heating film 2. The electric heating film has high heating performance, which improves the heating efficiency of the outer skin 1. In addition, by accommodating the electrode in the through hole 311, it is ensured that the current can be stably transmitted to the heating film 2, so that the heating film 2 can be rapidly heated, and the anti-icing and de-icing functions of the wing leading edge structure 10 are realized. It should be noted that the through holes 311 are uniformly distributed along the wingspan direction of the wing leading edge structure 10, and one electrode is arranged in each through hole 311, so that the electrodes are uniformly distributed, and the heating speed of the heating film 2 is more uniform.

[0050] Optionally, in the embodiment, there are three through holes 311 along the wingspan direction of the wing leading edge structure 10, which can improve the heating power of the heating film 2. In other embodiments, the number of through holes 311 is designed according to the number of electrodes to meet the power requirement of the electric heating film. It should be noted that the opening size of the through hole 311 is designed according to the size of the electrode.

[0051] Further, along the chord direction of the wing leading edge structure 10, the distance d between the edge of the through hole 311 and the edge of the inner panel 31 is 10mm-50mm. Optionally, the distance d between the edge of the through hole 311 and the edge of the inner panel 31 can be 10mm, 20mm, 30mm, 40mm or 50mm. The above numerical limitation makes the distance d between the edge of the through hole 311 and the edge of the inner panel 31 not too large to cause the through hole 311 to be arranged in the honeycomb structure 33, so that the honeycomb structure 33 is incomplete, and the bird impact resistance of the honeycomb support assembly 3 is reduced, and the distance d between the edge of the through hole 311 and the edge of the inner panel 31 is not too small to cause the through hole 311 to be arranged at the edge of the inner panel 31, so that during the cruising of the aircraft, water vapor enters the honeycomb, the performance of the honeycomb material gradually decreases, the strength and stiffness are reduced, and the overall stability and safety of the aircraft structure are affected.

[0052] Optionally, in other embodiments, after the electrode is placed in the through hole 311 and is electrically connected with the heating film 2, the through hole 311 can be subjected to a potting operation, so that the potting glue is clamped between the inner panel 31 and the outer panel 32 and surrounds the outer periphery of the through hole 311. The above arrangement can play a sealing role, preventing external water vapor from entering the inside of the through hole 311 and then entering the inside of the honeycomb structure 33, thereby improving the reliability and service life of the entire device. It should be noted that when the through hole 311 is subjected to the potting operation, the distance d between the edge of the through hole 311 and the edge of the inner panel 31 can be appropriately reduced. Specifically, the potting operation can be performed along the inner peripheral walls of the through hole 311.

[0053] Further, the outer skin 1, the heating film 2 and the honeycomb support assembly 3 are integrally formed, greatly improving the strength and stability of the wing leading edge structure 10 and being able to better withstand external impact. At the same time, this design makes the heat transfer more uniform and efficient, and the heat of the heating film 2 can be rapidly and uniformly conducted to the outer skin 1, thereby achieving a faster, more stable and more uniform heating effect. It should be noted that the present embodiment adopts a co-curing molding technology, and in other embodiments, other integral molding technologies can also be used, such as stamping integral molding or hot pressing integral molding, etc., which can realize the close connection between the outer skin 1, the heating film 2 and the honeycomb support assembly 3.

[0054] The present embodiment also provides an aircraft wing, which comprises a wing body and the wing leading edge structure 10 described above, and the wing leading edge structure 10 is detachably mounted on the aircraft wing. This makes it more convenient and efficient to operate when the wing leading edge structure 10 is damaged or needs to be maintained or replaced.

[0055] Obviously, the above embodiments of the present application are only examples for clearly illustrating the present application, and are not intended to limit the implementation modes of the present application. For those skilled in the art, various obvious changes, readjustments and replacements can be made without departing from the protection scope of the present application. Here, it is not necessary and impossible to exhaust all the implementation modes. Any modification, equivalent replacement and improvement made within the spirit and principle of the present application shall be included in the protection scope of the claims of the present application.

Claims

1. Wing leading edge structure, characterized in that The wing leading edge structure (10) comprises: an outer skin (1); a heating film (2) laid on the inner side of the outer skin (1), the heating film (2) being configured to heat the outer skin (1); and a honeycomb support assembly (3) arranged on the side of the heating film (2) away from the outer skin (1).

2. The wing leading edge structure according to claim 1, characterized in that The honeycomb support assembly (3) comprises: an inner panel (31) arranged on the side of the heating film (2) away from the outer skin (1); an outer panel (32) connected with the inner panel (31) and forming a cavity with the inner panel (31); and a honeycomb structure (33) accommodated in the cavity.

3. The wing leading edge structure according to claim 2, characterized in that The outer skin (1) comprises a laying area (11) and a connecting area (12) connected with each other, the connecting area (12) being arranged around the periphery of the laying area (11), the inner side of the laying area (11) being provided with the heating film (2), and the inner panel (31) being fixedly connected with the inner side of the connecting area (12).

4. The wing leading edge structure according to claim 2, characterized in that The area of the honeycomb structure (33) is smaller than the area of the heating film (2), and the interval between the outer edge of the honeycomb structure (33) projected on the inner panel (31) and the outer edge of the heating film (2) projected on the inner panel (31) is H1.

5. The wing leading edge structure of claim 2, wherein The inner panel (31) is made of carbon fiber material; and / or, the outer panel (32) is made of carbon fiber material.

6. The wing leading edge structure according to claim 2, characterized in that The honeycomb support assembly (3) is provided with a through hole (311) penetrating the inner panel (31) and the outer panel (32); The heating film (2) is an electric heating film, and the wing leading edge structure (10) further comprises an electrode accommodated in the through hole (311) and electrically connected with the heating film (2).

7. The wing leading edge structure according to claim 6, characterized in that In the chord direction of the wing leading edge structure, the distance d between the edge of the through hole (311) and the edge of the inner panel (31) is 10-50 mm.

8. The wing leading edge structure according to any one of claims 1 to 7, characterized in that The outer skin (1), the heating film (2) and the honeycomb support assembly (3) are integrally formed.

9. The wing leading edge structure according to any one of claims 1 to 7, characterized in that The outer skin (1) is made of metal material.

10. An aircraft wing, characterised in that The wing leading edge structure (10) is detachably mounted on the wing body.

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