A large-load-bearing high-rigidity lightweight composite wing and a preparation method thereof

Abstract

The present application relates to a kind of big load high rigidity light composite material wing and its preparation method;Steps: preparation weight-reducing foam, trailing edge weight-reducing foam and composite connecting plate;According to the length direction of the corresponding length of each unit section of weight-reducing foam in lower mold, multiple laying areas are divided, carbon fiber prepreg is laid in each laying area, lower prepreg layer is formed, and the thickness of lower prepreg layer in each laying area is ladder type decreasing;The insertion section of metal wing handle is placed on lower mold, one end of composite connecting plate is inserted with insertion section and is fixed, multiple weight-reducing foams are placed at intervals, and trailing edge weight-reducing foam is placed at wing trailing edge;Carbon fiber prepreg is laid according to the laying mode of lower prepreg layer, and upper prepreg layer is formed;Upper mold and lower mold are closed, cured, demoulded, and the preparation method of big load high rigidity light composite material wing is obtained, and the technical problem of existing wing weight is solved by big load high rigidity light composite material wing and its preparation method.

Description

Technical Field

[0001] This invention relates to the field of projectile technology, and in particular to a high-load-bearing, high-rigidity, lightweight composite material projectile wing and its preparation method. Background Technology

[0002] Traditional missile wings utilize a large amount of metal to ensure sufficient strength and rigidity, but this results in significant weight and increased energy consumption. Compared to traditional metal materials, composite materials offer numerous advantages, including higher specific strength and stiffness, corrosion resistance, and design flexibility, leading to their widespread application in aircraft structures.

[0003] CN202311149197.0 discloses a high-load-bearing lightweight composite material flight wing and its preparation method. The composite wing surface is prepared using composite materials, comprising a main wing surface and a trailing edge wing surface connected to one side of the main wing surface. Connecting cavities and reinforcing cavities are sequentially arranged along the length of the main wing surface. Multiple closely arranged reinforcing foam boards are placed within the reinforcing cavities, with one end of each reinforcing foam board extending into the connecting cavity and gradually decreasing in volume. Compared to an all-metal wing, this significantly reduces weight. However, with the above structural design, the composite material layup maintains a consistent thickness along the wingspan, resulting in a single wing weighing approximately 15-25 kg, which still cannot meet the requirements for high load-bearing capacity and low energy consumption (single wing weight less than 15 kg).

[0004] Therefore, in order to address the above problems, the present invention urgently needs a high load-bearing, high-rigidity, lightweight composite material wing and its preparation method. Summary of the Invention

[0005] The purpose of this invention is to provide a high-load-bearing, high-stiffness, lightweight composite material projectile wing and its preparation method, thereby solving the technical problem of heavy projectile wings in existing systems.

[0006] This invention provides a method for preparing a high-load-bearing, high-stiffness, lightweight composite material projectile wing, comprising the following preparation steps: Multiple wing-surface weight-reducing foams are prepared. Each wing-surface weight-reducing foam is divided into multiple unit segments along its length. The number of unit segments is set according to the number of wing-surface loading points of the composite material wing. The thickness of each unit segment of the wing-surface weight-reducing foam increases in a stepwise manner along the length of the wing-surface weight-reducing foam. Preparation of trailing edge weight-reducing foam; Prepare a composite connecting plate for connecting a metal wing rotor and multiple wing surface weight-reducing foams; A mold for wing surface forming is made. The mold includes a lower half mold and an upper half mold that fits together. One end of the lower half mold is the projectile connection end. According to the placement position of each unit segment of the wing surface weight reduction foam, multiple laying areas are sequentially divided along the length of the lower half mold. The placement position of each unit segment corresponds one-to-one with each laying area. Fiber prepreg for forming the skin is laid in each laying area to obtain a lower prepreg layer. The thickness of the lower prepreg layer in each laying area decreases in a stepwise manner from the projectile connection end to the other end. Place one end of the metal wing handle on the lower half mold, and insert and fix one end of the composite connecting plate to the metal wing handle. Place multiple wing surface weight-reducing foams at intervals along the width direction of the lower prepreg layer. The placement method of each wing surface weight-reducing foam is that the thickness of each unit segment increases in a step manner from the end closest to the projectile connecting end to the other end. Place the trailing edge weight-reducing foam on one side of the wing surface weight-reducing foam, and extend one end of each wing surface weight-reducing foam into the interior of the composite connecting plate. According to the laying method of the lower prepreg layer, lay fiber prepreg to form the skin on the metal wing handle, wing surface weight-reducing foam, composite connecting plate and trailing edge weight-reducing foam to obtain the upper prepreg layer. The upper and lower mold halves are joined together, heated and cured, and then demolded to obtain a high-load-bearing, high-rigidity, lightweight composite material wing.

[0007] Preferably, the metal wing stick includes a connecting section for connection with the wing and an insert section for insertion into the wing surface.

[0008] Preferably, the insertion section includes an upper insertion plate and a lower insertion plate, and an insertion gap is provided between the upper insertion plate and the lower insertion plate.

[0009] Preferably, each wing surface has five unit segments arranged sequentially along the extension direction of the weight-reducing foam.

[0010] Preferably, the four wing-shaped weight-reducing foams are placed at equal intervals along the width direction of the lower prepreg layer.

[0011] Preferably, the fiber is carbon fiber or glass fiber.

[0012] Preferably, the weight-reducing foam on each wing surface and the weight-reducing foam on the trailing edge are both high-strength rigid foams; the metal wing rotor is made of alloy.

[0013] Preferably, the length of the wing surface is 1.2 to 2.0 m, and the aspect ratio of the wing surface is (4 to 9):1.

[0014] The present invention also provides a high load-bearing, high stiffness, lightweight composite material projectile wing obtained by the preparation method of the high load-bearing, high stiffness, lightweight composite material projectile wing as described in any one of the above-mentioned methods, comprising a metal wing rotor and a wing surface, one end of the metal wing rotor being inserted into the wing surface and fixedly connected to the wing surface as a whole; one side of the wing surface is the wing root, and the other side is the wing tail, with the metal wing rotor located on the wing root side; The wing surface includes a skin formed of fiber prepreg and a composite connecting plate. The skin has multiple wing surface weight-reducing foams spaced apart along its width and a trailing edge weight-reducing foam inside. Each wing surface weight-reducing foam is divided into multiple unit segments along its length. The average thickness of each unit segment increases in a stepwise manner from the end closest to the metal wing handle to the outside. The thickness of the fiber prepreg skin decreases in a stepwise manner from the end closest to the metal wing handle to the outside.

[0015] The metal wing handle (1), composite connecting plate (5), and skin are connected as one unit by screws. The projectile wing provided by this invention has the following advantages compared with the prior art: The present invention provides a method for manufacturing high-load-bearing, high-stiffness, lightweight composite material projectile wings. The thickness of the weight-reducing foam on each wing surface increases in a gradient manner. The overall thickness of the skin formed by the lower and upper prepreg layers complements the thickness of the weight-reducing foam on the wing surfaces. The skin formed by the lower and upper prepreg layers gradually thins from the side closest to the projectile body towards the wing span, while the thickness of the weight-reducing foam on each wing surface gradually increases from the side closest to the projectile body towards the wing span. The skin formed by the lower and upper prepreg layers can be designed with equal strength according to the projectile wing load requirements. The design achieves adaptive load-bearing capacity, meeting load requirements. At the same time, by reducing the carbon fiber prepreg layer design on the wing surface away from the projectile body, the overall weight of the wing can be reduced, reducing energy consumption. The weight of the composite material wing can be reduced to as low as 13 kg, with a load-bearing capacity greater than 15 kN. When a 16.5 kN load is applied to the obtained composite material wing, the wingtip deformation is ≤145 mm. Compared with existing metal winglets, the overall weight is reduced by 20-25 kg, and compared with existing composite winglets of the same size, the weight is reduced by 5-10 kg. Attached Figure Description

[0016] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0017] Figure 1 This is a schematic diagram (three-dimensional view) of the high load-bearing, high stiffness, lightweight composite material projectile wing described in this invention. Figure 2 This is a schematic diagram (three-dimensional view, excluding the skin formed by carbon fiber prepreg and the composite connecting plate) of the high load-bearing, high stiffness, and lightweight composite material projectile wing described in this invention. Figure 3 This is a schematic diagram (perspective view) of the structure of the metal wing rotor described in this invention. Figure 4This is a schematic diagram (three-dimensional view, with the skin formed by carbon fiber prepreg removed) of the high load-bearing, high stiffness, lightweight composite material projectile wing described in this invention. Figure 5 This is a schematic diagram (three-dimensional view) of the composite connecting plate described in this invention. Explanation of reference numerals in the attached figures: 1. Metal wing rotor; 101. Connecting section; 102. Insertion section; 2. Wing surface weight-reducing foam; 3. Skin; 4. Trailing edge weight-reducing foam; 5. Composite connecting plate. Detailed Implementation

[0018] The technical solution of the present invention will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0019] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0020] Those skilled in the art should understand that the following specific embodiments or implementation methods are a series of optimized configurations listed to further explain the specific content of the invention. These configuration methods can be combined or used in conjunction with each other, unless the invention explicitly states that some or a specific embodiment or implementation method cannot be associated with or used in conjunction with other embodiments or implementation methods. Furthermore, the following specific embodiments or implementation methods are merely optimized configurations and are not intended to limit the scope of protection of the invention.

[0021] The present invention will be further explained below with reference to specific embodiments.

[0022] like Figure 1 , Figure 2 , Figure 3 Figure 4 As shown in the figure, this embodiment provides a method for preparing a high-load-bearing, high-stiffness, lightweight composite material projectile wing, which includes the following preparation steps: 1) Prepare multiple wing surface weight reduction foams 2. Each wing surface weight reduction foam 2 is divided into multiple unit segments along its length. The number of unit segments is set according to the number of wing surface loading points of the composite material wing. The thickness of each unit segment of the wing surface weight reduction foam 2 increases in a stepwise manner along the length direction of the wing surface weight reduction foam 2. 2) Prepare trailing edge weight-reducing foam 4; 3) Prepare a composite connecting plate 5 for connecting the metal wing rotor 1 and multiple wing surface weight-reducing foams 2; 4) Make a mold for wing surface forming. The mold includes a lower half mold and an upper half mold that fits together. One end of the lower half mold is the projectile connection end. According to the placement position of each unit segment of the wing surface weight reduction foam 2, the lower half mold is divided into multiple laying areas in sequence along its length. The placement position of each unit segment corresponds to each laying area. Fiber prepreg for forming the skin is laid in each laying area to obtain a lower prepreg layer. The thickness of the lower prepreg layer in each laying area decreases in a stepwise manner from the projectile connection end to the other end. 5) Place one end of the metal wing stick 1 on the lower half mold, located at the projectile connection end of the lower half mold. Insert and fix one end of the composite connecting plate 5 to the metal wing stick 1. Place multiple wing surface weight-reducing foams 2 at intervals along the width direction of the lower prepreg layer. The placement method of each wing surface weight-reducing foam 2 is that the thickness of each unit segment increases in a stepwise manner from the projectile connection end to the other end. Place the trailing edge weight-reducing foam 4 on one side of the outer wing surface weight-reducing foam 2. One end of each wing surface weight-reducing foam 2 extends into the interior of the composite connecting plate 5. According to the laying method of the lower prepreg layer, lay fiber prepreg for forming the skin on the metal wing stick 1, wing surface weight-reducing foam 2, composite connecting plate 5 and trailing edge weight-reducing foam 4 to obtain the upper prepreg layer. The upper and lower mold halves are joined together, heated and cured, and then demolded to obtain a high-load-bearing, high-rigidity, lightweight composite material wing.

[0023] By using the above settings, a lightweight composite material wing can be obtained while still meeting the load-bearing requirements and exhibiting good rigidity. The weight of the obtained high-load-bearing, high-rigidity, lightweight composite material wing can be reduced to as low as 13 kg, with a load-bearing capacity greater than 15 kN. When a 16.5 kN load is applied to the obtained composite material wing, the wingtip deformation is ≤145 mm.

[0024] In some embodiments, before fabrication, engineering algorithms can be used to theoretically calculate the maximum thickness of the skin in the region corresponding to each loading point based on the size of the loading point, and then adjustments can be made based on the simulation calculation results.

[0025] The wing surface includes the wing root (near the metal wing rod) and the wing tail (away from the metal wing rod).

[0026] Specifically, the engineering algorithm formula is as follows:

[0027] Where d(x) is the skin thickness formed by the upper and lower prepreg layers in the loading area at a distance x from the wing root; L is the wing length; P is the pressure (total loading force of the wing / wing surface bearing area, i.e., the average pressure on the wing); E is the elastic modulus of the material used in the product after ply calculation; δ0 is the required value of wingtip deformation; D is the required total thickness of the product; and x is the distance from the wing section to the wing root at each loading point.

[0028] Specifically, the airfoil is divided into five loading zones along its length. When the design requirements are L = 1600mm, E = 120000MPa, δ0 = 145mm, and D = 40mm, the distances x from the airfoil root are 200mm, 500mm, 800mm, 1100mm, and 1400mm, respectively. Through engineering algorithm formulas, d(x) are 23mm, 16mm, 10mm, 4.9mm, and 1.2mm, respectively. The upper prepreg layer is half the thickness of d(x).

[0029] The second stage involves adjustments based on the simulation results.

[0030] Preferably, the skin thickness difference between adjacent loading points at the wing root is 6-8 mm, the skin thickness difference between adjacent loading points at the wing tail is 1-4 mm, and the decreasing skin thickness difference between intermediate adjacent loading points is 4-6 mm. This achieves lightweight design while ensuring sufficient load-bearing capacity and stiffness.

[0031] The present invention provides a method for manufacturing high-load-bearing, high-stiffness, lightweight composite material projectile wings. The thickness of the weight-reducing foam 2 on each wing surface increases in a gradient along its length. The overall thickness of the skin formed by the lower and upper prepreg layers complements the thickness of the weight-reducing foam 2 on the wing surfaces. The skin formed by the lower and upper prepreg layers gradually thins from the side closest to the projectile body towards the wingspan direction, while the thickness of the weight-reducing foam 2 on each wing surface gradually increases from the side closest to the projectile body towards the wingspan direction. The skin formed by the lower and upper prepreg layers can be made with equal strength according to the projectile wing load requirements. The design achieves adaptive load-bearing capacity, meeting load requirements. At the same time, reducing the carbon fiber prepreg layer design on the wing surface away from the projectile body can reduce the overall weight of the wing and reduce energy consumption. The resulting single wing weighs less than 13 kg, which is 20-25 kg lighter than existing metal wings of the same size. Compared with existing composite winglets of the same size (with uniform skin thickness), it can reduce weight by 5-10 kg, while still maintaining a load-bearing capacity greater than 15 kN. The wingtip deformation of the high-load, high-rigidity, lightweight composite material wing is ≤145 mm, exhibiting good rigidity.

[0032] like Figure 3As shown, the metal wing handle 1 in this embodiment includes a connecting section 101 for connecting with the missile wing and an insertion section 102 for inserting into the wing surface. The insertion section 102 is located between the lower prepreg layer and the upper prepreg layer. The insertion section 102 includes an upper insert plate and a lower insert plate, and an insertion gap 103 is provided between the upper insert plate and the lower insert plate. One end of the composite connecting plate 5 can extend into the insertion gap 103, thereby realizing the connection between the composite connecting plate 5 and the metal wing handle 1. It can be tightened by bolts. The connection structure between the composite connecting plate 5 and the metal wing handle 1 can reduce the weight of the original metal wing handle 1 while ensuring the connection strength, thereby reducing the overall weight of the missile wing.

[0033] The wing-surface weight-reducing foam 2 of the present invention has five unit segments arranged sequentially in the extension direction; ensuring overall rigidity and load-bearing capacity.

[0034] The present invention includes four wing-shaped weight-reducing foams, which are placed at equal intervals along the width direction of the lower prepreg layer.

[0035] The fiber of this invention is carbon fiber or glass fiber, which can be selected as needed. It can also be prepared using glass fiber composite materials and has wave-transmitting function.

[0036] The wing surface weight-reducing foam and trailing edge weight-reducing foam 4 of this invention are both high-strength rigid foams; the metal wing rotor 1 is made of alloy to ensure sufficient mechanical strength.

[0037] The length of the wing surface of the present invention is 1.2 to 2.0 m, and the aspect ratio of the wing surface 1 is (4 to 9):1.

[0038] The present invention also provides a high load-bearing, high stiffness, lightweight composite material projectile wing obtained by the preparation method of the high load-bearing, high stiffness, lightweight composite material projectile wing as described in any one of the above-mentioned methods, comprising a metal wing rotor 1 and a wing surface, one end of the metal wing rotor 1 being inserted into the wing surface 3 and fixedly connected to the wing surface as a whole; one side of the wing surface is the wing root, and the other side is the wing tail, with the metal wing rotor located on the wing root side; the wing surface comprises a skin 3 formed of fiber prepreg and a composite connecting plate 5, the skin having multiple wing surface weight-reducing foams 2 spaced apart along its width and a trailing edge weight-reducing foam 4, each wing surface weight-reducing foam 2 being divided into multiple unit segments along its length, the average thickness of each unit segment increasing stepwise from the end close to the metal wing rotor 1 outwards, and the thickness of the fiber prepreg skin decreasing stepwise from the end close to the metal wing rotor 1 outwards.

[0039] like Figure 5 As shown, the composite connecting plate 5 in this embodiment includes a body 501. The upper and lower end faces of the body 501 are respectively provided with upper and lower embedding grooves for the upper and lower insert plates, respectively. One end of the upper and lower embedding grooves is connected to the side end of the body 501. The metal wing handle 1, the composite connecting plate 5, and the skin of this invention are connected together by screws to ensure the tightness of the connection.

[0040] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A method for manufacturing a high-load-bearing, high-stiffness, lightweight composite material projectile wing, characterized in that: The preparation steps include the following: Prepare multiple wing surface weight reduction foams (2), each wing surface weight reduction foam (2) is divided into multiple unit segments along its length, the number of unit segments is set according to the number of wing surface loading points of the composite material wing, and the thickness of each unit segment of the wing surface weight reduction foam (2) increases in a stepwise manner along its length. Preparation of trailing edge weight-reducing foam (4); Prepare a composite connecting plate (5) for connecting the metal wing shank (1) and multiple wing surface weight reduction foams (2); A mold for wing surface forming is made. The mold includes a lower half mold and an upper half mold that fits together. One end of the lower half mold is the projectile connection end. According to the placement position of each unit segment of the wing surface weight reduction foam (2), multiple laying areas are sequentially divided in the length direction of the lower half mold. The placement position of each unit segment corresponds to each laying area. Fiber prepreg for forming the skin is laid in each laying area to obtain the lower prepreg layer. The thickness of the lower prepreg layer in each laying area decreases in a stepwise manner from the projectile connection end to the other end. Place one end of the metal wing handle (1) on the lower half mold, and insert and fix one end of the composite connecting plate (5) to the metal wing handle (1). Place multiple wing surface weight-reducing foams (2) at intervals along the width direction of the lower prepreg layer. The placement method of each wing surface weight-reducing foam (2) is that the thickness of each unit segment increases stepwise from the end close to the projectile connection end to the other end. Place the trailing edge weight-reducing foam (4) on one side of the wing surface weight-reducing foam (2), and extend one end of each wing surface weight-reducing foam (2) into the interior of the composite connecting plate (5). According to the laying method of the lower prepreg layer, lay fiber prepreg for forming the skin on the metal wing handle (1), wing surface weight-reducing foam (2), composite connecting plate (5) and trailing edge weight-reducing foam (4) to obtain the upper prepreg layer. The upper and lower mold halves are joined together, heated and cured, and then demolded to obtain a high-load-bearing, high-rigidity, lightweight composite material wing.

2. The method for preparing a high-load-bearing, high-stiffness, lightweight composite material projectile wing according to claim 1, characterized in that: Before fabrication, engineering algorithms can be used to theoretically calculate the maximum thickness of the skin in the corresponding area of ​​each loading point based on the size of the loading point, and then adjust it according to the simulation calculation results; the wing surface includes the wing root (the end near the metal wing shank) and the wing tail (the end away from the metal wing shank). The engineering algorithm formula is: Where d(x) is the skin thickness formed by the upper and lower prepreg layers in the loading area at a distance x from the wing root; L is the wing length; P is the pressure (total loading force of the wing / wing surface bearing area, i.e., the average pressure on the wing); E is the elastic modulus of the material used in the product after ply calculation; δ0 is the required value of wingtip deformation; D is the required total thickness of the product; and x is the distance from the wing section to the wing root at each loading point.

3. The method for preparing a high-load-bearing, high-stiffness, lightweight composite material projectile wing according to claim 1, characterized in that: The metal wing stick (1) includes a connecting section (101) for connecting with the wing and an insert section (102) for inserting into the wing surface. The insertion section (102) includes an upper insertion plate and a lower insertion plate, and an insertion gap (103) is provided between the upper insertion plate and the lower insertion plate.

4. The method for preparing a high-load-bearing, high-stiffness, lightweight composite material projectile wing according to claim 1, characterized in that: Each wing surface weight reduction foam (2) has five unit segments arranged sequentially in the extension direction.

5. The method for preparing a high-load-bearing, high-stiffness, lightweight composite material projectile wing according to claim 1, characterized in that: It includes four wing-shaped weight-reducing foams, and the four wing-shaped weight-reducing foams (2) are placed at equal intervals along the width direction of the lower prepreg layer.

6. The method for preparing a high-load-bearing, high-stiffness, lightweight composite material projectile wing according to claim 1, characterized in that: The fiber is carbon fiber or glass fiber.

7. The method for preparing a high-load-bearing, high-stiffness, lightweight composite material projectile wing according to claim 1, characterized in that: The wing surface weight reduction foam and the trailing edge weight reduction foam (4) are both high-strength rigid foams; the metal wing shank (1) is made of alloy.

8. The method for preparing a high-load-bearing, high-stiffness, lightweight composite material projectile wing according to claim 1, characterized in that: The length of the wing surface is 1.2 to 2.0 m, and the aspect ratio of the wing surface is (4 to 9):

1.

9. A high-load-bearing, high-stiffness, lightweight composite material projectile wing obtained by the preparation method of the high-load-bearing, high-stiffness, lightweight composite material projectile wing according to any one of claims 1-8, characterized in that: It includes a metal wing rotor (1) and a wing surface. One end of the metal wing rotor (1) is inserted into the wing surface (3) and fixed to the wing surface as a whole. One side of the wing surface is the wing root and the other side is the wing tail. The metal wing rotor is located on one side of the wing root. The wing surface includes a skin (3) formed by fiber prepreg and a composite connecting plate (5). The skin has multiple wing surface weight-reducing foams (2) arranged at intervals along its width and a trailing edge weight-reducing foam (4). Each wing surface weight-reducing foam (2) is divided into multiple unit segments along its length. The average thickness of each unit segment increases stepwise from the end close to the metal wing handle (1) to the outside. The thickness of the skin formed by fiber prepreg decreases stepwise from the end close to the metal wing handle (1) to the outside.

10. The high load-bearing, high-stiffness, lightweight composite material projectile wing according to claim 9, characterized in that: The metal wing handle (1), the composite connecting plate (5), and the skin are connected together by screws.

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