A laminated hybrid composite wing structure

Abstract

The present invention discloses a laminated hybrid composite wing structure. The ribs, trusses and spars are located inside the wing skin shell, the ribs are evenly spaced on the spars along the length direction of the spars, the ribs are connected by trusses, and the outer periphery of the ribs is close to the inner side of the wing skin shell; the wing structure is installed on the fuselage of the aircraft through one end of the spar as the side wing of the aircraft. The wing structure of the present invention introduces hybrid composite materials into the optimized design of the wing, which can meet the comprehensive requirements of the cost, weight and performance of the wing structure, and can improve the strength and vibration characteristics of the wing structure without increasing the cost, and achieve the lightweight requirements, thereby improving the flight efficiency of the aircraft.

Description

Technical Field

[0001] The invention relates to a wing structure, in particular to a laminated hybrid composite material wing structure. Background Art

[0002] The wing structure is the main load-bearing component that directly bears the aerodynamic load of the aircraft. The weight and performance of the wing structure affect the efficiency of the aircraft's flight. Therefore, lightweight, high-strength, and high-efficiency optimization design is the direction of wing structure development. Reducing the weight of the wing structure and improving the strength and vibration characteristics of the wing structure are direct and effective means to improve the flight efficiency of the aircraft. Due to the complexity of the actual working conditions of the wing structure, both metal materials and single composite materials are difficult to meet the multi-objective requirements of the wing skin under complex working conditions, and the weight and performance of the wing structure cannot be taken into account at the same time. At the same time, the aerodynamic loads on various parts of the wing structure are uneven. If all parts use the same material, it will lead to redundancy or insufficiency of the weight or structural performance of the structure, and the ideal design requirements cannot be achieved. Summary of the invention

[0003] In order to solve the problems existing in the background technology, the present invention provides a laminated hybrid composite material wing structure.

[0004] The technical solution adopted by the present invention is:

[0005] The laminated hybrid composite material wing structure of the present invention includes a plurality of wing ribs, trusses, wing spars and a wing skin shell, wherein each wing rib, truss and wing spars are located inside the wing skin shell, each wing rib is evenly spaced along the length direction of the wing spars, each wing rib is connected by a truss, and the outer periphery of each wing rib is in close contact with the inner side surface of the wing skin shell; the wing structure is installed on the fuselage of the aircraft through one end of the wing spars as the side wing of the aircraft, and the aircraft can specifically be a small or medium-sized fixed-wing UAV.

[0006] The planes where the wing ribs are located are parallel to each other, the wing beam passes through the wing ribs and is perpendicular to the plane where each wing rib is located, and the wing beam is close to the leading edge of the wing structure.

[0007] The truss comprises a plurality of trusses, each of which is arranged along the length direction of the wing beam and sequentially connects each rib.

[0008] The wing skin shell is formed by connecting the first skin layer, the second skin layer, the third skin layer, the fourth skin layer, the fifth skin layer and the sixth skin layer in sequence. The first skin layer, the second skin layer, the third skin layer, the fourth skin layer, the fifth skin layer and the sixth skin layer are all long sheet structures. The length directions of the first skin layer, the second skin layer, the third skin layer, the fourth skin layer, the fifth skin layer and the sixth skin layer are all parallel to the length direction of the wing beam and the lengths are all equal to the distance between the first rib and the last rib.

[0009] The first skin layer, the second skin layer and the third skin layer are located above each wing rib, and the fourth skin layer, the fifth skin layer and the sixth skin layer are located below each wing rib; the first skin layer and the sixth skin layer are close to the leading edge of the wing structure, and the third skin layer and the fourth skin layer are close to the trailing edge of the wing structure.

[0010] The first skin layer, the second skin layer, the third skin layer, the fourth skin layer, the fifth skin layer and the sixth skin layer are all skin layers formed by stacking eight composite layers, and the eight composite layers are, from the outer side of the wing skin shell to the inner side, the first composite layer, the second composite layer, the third composite layer, the fourth composite layer, the fifth composite layer, the sixth composite layer, the seventh composite layer and the eighth composite layer, wherein the fiber directions of materials of the first composite layer and the eighth composite layer are the same, the fiber directions of materials of the second composite layer and the seventh composite layer are the same, the fiber directions of materials of the third composite layer and the sixth composite layer are the same, the fiber directions of materials of the fourth composite layer and the fifth composite layer are the same, and the fiber directions of materials of the first to fourth composite layers are all different.

[0011] When the fiber direction of the material of the first composite layer and the eighth composite layer is 0°, the fiber direction of the material of the second composite layer and the seventh composite layer is 45°, the fiber direction of the material of the third composite layer and the sixth composite layer is 90°, and the fiber direction of the material of the fourth composite layer and the fifth composite layer is -90°.

[0012] The first skin layer and the fifth skin layer are both made of carbon fiber / cyanate resin HS300 / ET223; the second skin layer and the sixth skin layer are both made of carbon fiber composite material T800H / 924C; the third skin layer is made of carbon fiber epoxy resin material HT7 / 5438; and the fourth skin layer is made of carbon / glass fiber material BT250E-6.

[0013] The wing ribs are made of high-strength carbon fiber material IM6 / 3501-6 or carbon fiber epoxy resin material HT3 / 5405.

[0014] The wing spar is made of carbon fiber pre-impregnated unidirectional tape material HTS134 / 977-2.

[0015] The beneficial effects of the present invention are:

[0016] 1. The wing ribs, spars and trusses in the wing structure skeleton of the present invention adopt different types of fiber reinforced composite materials according to the size of the aerodynamic loads on the wing structure. The wing spar parts that are subject to greater loads in the wing structure adopt fiber reinforced composite materials with relatively high strength, while the remaining ribs and spars that are subject to less loads adopt fiber reinforced composite materials with slightly lower strength, which can effectively control the weight of the wing composite structure.

[0017] 2. The wing skin shell of the present invention is designed to be divided into six areas and uses different materials. This layout can effectively reduce the weight of the wing skin shell and improve the impact resistance of the wing skin shell.

[0018] 3. The fiber laying method of the six different areas of the wing skin shell of the present invention can increase the fundamental frequency of the wing skin shell and thus increase the stiffness of the skin.

[0019] In summary, the wing structure of the present invention introduces hybrid composite materials into the optimized design of the wing, which can meet the comprehensive requirements of the weight and performance of the wing structure, improve the stiffness and strength characteristics of the wing structure, and achieve the lightweight requirements of the structure, thereby improving the flight efficiency and mechanical properties of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a schematic diagram of the internal skeleton structure of the wing structure of the present invention;

[0021] Figure 2 It is a schematic diagram of the layout of each area of ​​the wing skin shell and the laying of the skin laminated fibers of the present invention;

[0022] In the figure: 1, wing rib, 2, truss, 3, wing spar, 4, first skin layer, 5, second skin layer, 6, third skin layer, 7, fourth skin layer, 8, fifth skin layer, 9, sixth skin layer. DETAILED DESCRIPTION

[0023] The present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0024] like Figure 1As shown, the wing structure of the present invention comprises a plurality of ribs 1, trusses 2, spars 3 and wing skin shells, each rib 1, truss 2 and spars 3 are located inside the wing skin shell, each rib 1 is evenly spaced along the length direction of the spars 3 on the spars 3, each rib 1 is connected by trusses 2, and the outer periphery of each rib 1 is close to the inner side of the wing skin shell; the wing structure is installed on the fuselage of the aircraft through one end of the spars 3 as the side wing of the aircraft, and the aircraft can be a small or medium-sized fixed-wing type unmanned aerial vehicle. The planes where the ribs 1 are located are parallel to each other, the spars 3 pass through the ribs 1 and are perpendicular to the planes where each rib 1 is located, and the spars 3 are close to the leading edge of the wing structure. The ribs 1 are made of high-strength carbon fiber material IM6 / 3501-6 or carbon fiber epoxy resin material HT3 / 5405. The spars 3 are made of carbon fiber prepreg unidirectional tape material HTS134 / 977-2. The number of ribs 1 can be specifically 17. The truss 2 includes a plurality of stringers, each of which is arranged along the length direction of the spar 3 and sequentially connects the ribs 1. The material layout of the internal skeleton of the wing structure is designed according to the load conditions of the wing. The loads in different areas of the wing are different, and the required strength is also different. Under the comprehensive consideration of factors such as weight and performance, the wing spars, ribs and stringers are designed to be components of different materials, so as to reduce the weight of the structure while meeting the aerodynamic load, thereby improving the flight efficiency.

[0025] like Figure 2 As shown, the wing skin shell is formed by the first skin layer 4, the second skin layer 5, the third skin layer 6, the fourth skin layer 7, the fifth skin layer 8 and the sixth skin layer 9 which are connected in sequence. The first skin layer 4, the second skin layer 5, the third skin layer 6, the fourth skin layer 7, the fifth skin layer 8 and the sixth skin layer 9 are all long sheet structures. The length directions of the first skin layer 4, the second skin layer 5, the third skin layer 6, the fourth skin layer 7, the fifth skin layer 8 and the sixth skin layer 9 are all parallel to the length direction of the wing beam 3 and the lengths are all equal to the distance between the first rib 1 to the last rib 1.

[0026] The first skin layer 4, the second skin layer 5 and the third skin layer 6 are located above each wing rib 1, and the fourth skin layer 7, the fifth skin layer 8 and the sixth skin layer 9 are located below each wing rib 1; the first skin layer 4 and the sixth skin layer 9 are close to the leading edge of the wing structure, and the third skin layer 6 and the fourth skin layer 7 are close to the trailing edge of the wing structure. Dividing the wing skin into six areas and giving each area a different material distribution is, on the one hand, to facilitate the design and manufacture of the skin structure, and on the other hand, considering that the wing skin is a direct load-bearing component, the load on the wing skin is approximately distributed in a gradient from the wing root to the wing tip, from the chord direction to the span direction, so the force on the wing skin surface is uneven, and the bearing strength required on the wing surface is also different. Therefore, the wing skin is divided into different areas, and the area with a larger load uses a composite material with a larger strength, and the area with a smaller load uses a composite material with a slightly smaller strength. This solution can reduce the weight of the wing skin, improve the strength of the skin structure, and thus improve the flight efficiency of the aircraft.

[0027] The first skin layer 4, the second skin layer 5, the third skin layer 6, the fourth skin layer 7, the fifth skin layer 8 and the sixth skin layer 9 are all skin layers formed by stacking eight composite layers, and the eight composite layers are, from the outer side of the wing skin shell to the inner side, the first composite layer, the second composite layer, the third composite layer, the fourth composite layer, the fifth composite layer, the sixth composite layer, the seventh composite layer and the eighth composite layer, wherein the fiber directions of materials of the first composite layer and the eighth composite layer are the same, the fiber directions of materials of the second composite layer and the seventh composite layer are the same, the fiber directions of materials of the third composite layer and the sixth composite layer are the same, the fiber directions of materials of the fourth composite layer and the fifth composite layer are the same, and the fiber directions of materials of the first to fourth composite layers are all different.

[0028] When the fiber direction θ1 of the first and eighth composite material layers is 0°, the fiber direction θ2 of the second and seventh composite material layers is 45°, the fiber direction θ3 of the third and sixth composite material layers is 90°, and the fiber direction θ4 of the fourth and fifth composite material layers is -90°. In order to improve the vibration characteristics of the wing skin structure under gust flight conditions, the ply sequence of the wing skin is improved to obtain a larger frequency characteristic, and the fiber laying angles of the same layers in each area are the same in the design to further reduce the manufacturing difficulty.

[0029] The first skin layer 4 and the fifth skin layer 8 are both made of carbon fiber / cyanate resin HS300 / ET223; the second skin layer 5 and the sixth skin layer 9 are both made of carbon fiber composite material T800H / 924C; the third skin layer 6 is made of carbon fiber epoxy resin material HT7 / 5438; the fourth skin layer 7 is made of carbon / glass fiber material BT250E-6.

[0030] The invention of a laminated hybrid composite material wing structure of the present invention lies in the material layout and lamination stacking sequence of the wing structure. The material layout of the internal skeleton and external skin of the wing are designed based on the load conditions of the wing and comprehensively consider multiple factors such as weight and performance. Ultimately, the stiffness and strength characteristics of the wing structure can be improved, and the requirements for lightweight structure can be achieved, thereby improving the flight efficiency and mechanical properties of the aircraft.

Claims

1. A laminated hybrid composite wing structure, characterized in that: The invention comprises a plurality of wing ribs (1), trusses (2), wing spars (3) and a wing skin shell, wherein each wing rib (1), truss (2) and wing spars (3) are located inside the wing skin shell, each wing rib (1) is evenly spaced on the wing spars (3) along the length direction of the wing spars (3), each wing rib (1) is connected by a truss (2), and the outer periphery of each wing rib (1) is closely attached to the inner side surface of the wing skin shell; the wing structure is installed on the fuselage of the aircraft through one end of the wing spars (3) as the side wing of the aircraft; The wing skin shell is formed by connecting a first skin layer (4), a second skin layer (5), a third skin layer (6), a fourth skin layer (7), a fifth skin layer (8) and a sixth skin layer (9) in sequence; the first skin layer (4), the second skin layer (5), the third skin layer (6), the fourth skin layer (7), the fifth skin layer (8) and the sixth skin layer (9) are all long sheet structures; the length directions of the first skin layer (4), the second skin layer (5), the third skin layer (6), the fourth skin layer (7), the fifth skin layer (8) and the sixth skin layer (9) are all parallel to the length direction of the spar (3) and the lengths are all equal to the distance between the first rib (1) and the last rib (1); The first skin layer (4), the second skin layer (5) and the third skin layer (6) are located above each wing rib (1), and the fourth skin layer (7), the fifth skin layer (8) and the sixth skin layer (9) are located below each wing rib (1); the first skin layer (4) and the sixth skin layer (9) are close to the leading edge of the wing structure, and the third skin layer (6) and the fourth skin layer (7) are close to the trailing edge of the wing structure; The first skin layer (4), the second skin layer (5), the third skin layer (6), the fourth skin layer (7), the fifth skin layer (8) and the sixth skin layer (9) are all skin layers formed by stacking eight layers of composite materials, and the eight layers of composite materials are, from the outer side of the wing skin shell to the inner side, the first composite material layer, the second composite material layer, the third composite material layer, the fourth composite material layer, the fifth composite material layer, the sixth composite material layer, the seventh composite material layer and the eighth composite material layer in order, wherein the fiber directions of the materials of the first composite material layer and the eighth composite material layer are the same, the fiber directions of the materials of the second composite material layer and the seventh composite material layer are the same, the fiber directions of the materials of the third composite material layer and the sixth composite material layer are the same, the fiber directions of the materials of the fourth composite material layer and the fifth composite material layer are the same, and the fiber directions of the materials of the first to fourth composite material layers are all different; The first skin layer (4) and the fifth skin layer (8) are both made of carbon fiber / cyanate resin HS300 / ET223; the second skin layer (5) and the sixth skin layer (9) are both made of carbon fiber composite material T800H / 924C; the third skin layer (6) is made of carbon fiber epoxy resin material HT7 / 5438; the fourth skin layer (7) is made of carbon / glass fiber material BT250E-6; The wing rib (1) is made of high-strength carbon fiber material IM6 / 3501-6 or carbon fiber epoxy resin material HT3 / 5405; The wing beam (3) is made of carbon fiber pre-impregnated unidirectional tape material HTS134 / 977-2.

2. A laminated hybrid composite wing structure according to claim 1, characterized in that: The planes where the wing ribs (1) are located are parallel to each other, the wing beam (3) passes through the wing ribs (1) and is perpendicular to the plane where each wing rib (1) is located, and the wing beam (3) is close to the leading edge of the wing structure.

3. A laminated hybrid composite wing structure according to claim 1, characterized in that: The truss (2) comprises a plurality of trusses, each of which is arranged along the length direction of the wing beam (3) and sequentially connects each rib (1).

4. A laminated hybrid composite wing structure according to claim 1, characterized in that: When the fiber direction of the material of the first composite layer and the eighth composite layer is 0°, the fiber direction of the material of the second composite layer and the seventh composite layer is 45°, the fiber direction of the material of the third composite layer and the sixth composite layer is 90°, and the fiber direction of the material of the fourth composite layer and the fifth composite layer is -90°.

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