Light missile wing and preparation method thereof

Abstract

The invention discloses a light missile wing which comprises a metal wing handle, a main beam, an auxiliary beam, an end rib, a filling core material and a composite material skin wrapping the outer layer. The wing handles, the main beams, the auxiliary beams, the end ribs and the filling core materials are bonded through adhesive films to form a missile wing body. The composite material skin is laid on the surface of the missile wing body and then is subjected to mold pressing co-curing and integrated forming to form the clear-edge missile wing. According to the light missile wing, the composite material is mainly selected, the advantages of low density and high strength of the composite material are utilized, the structural strength and rigidity can be guaranteed, the overall structure is light, the structural efficiency is high, and the range and the effective load of a missile are increased; the structural design is simple, the working hours can be reduced, the production cost is reduced, the production efficiency is greatly improved, in addition, the high-strength barium phenolic glass fiber fabric prepreg is laid on the standard layer, and the thermal protection performance of the surface layer of the missile wing is greatly improved.

Description

Technical Field

[0001] The invention relates to the technical field of composite material production, and in particular to a light missile wing and a preparation method thereof. Background Art

[0002] The tactical idea of ​​long-range precision strike has formed a broad consensus around the world, and the wing is a very important part of the missile, which is related to the range, maximum altitude and maneuverability of the entire missile. The role of the wing is similar to that of the wing of an aircraft, and it can provide lift for the missile very well. For example, the wing design of a cruise missile can provide about 80% of the lift for the cruise missile, that is, in the ascent phase of the cruise missile, only 20% of the lift is provided by the engine. In the future, missiles will develop in the direction of long range, high speed, good maneuverability and other characteristics, which determines that missiles must take the path of lightweight. As a key component to ensure the key tactical indicators of missiles, the design of the wing is crucial.

[0003] Traditional missile wings are mostly made of metal structures. Although they are highly durable and can maintain structural integrity in harsh environments, they are heavy, which affects the flight performance and range of the missile. At the same time, their thermal protection capabilities are limited and they may be deformed or damaged by high temperatures, thus affecting the overall performance of the missile.

[0004] Therefore, it is necessary to design a lightweight wing and a preparation method thereof to solve the above problems. Summary of the invention

[0005] The purpose of the present invention is to address the deficiencies of the prior art and to provide a lightweight wing and a preparation method thereof.

[0006] The technical solution of the present invention is: a light missile wing, including a metal wing handle, a main beam, an auxiliary beam, an end rib, a filling core material and a composite material skin coated on the outer layer; the wing handle, the main beam, the auxiliary beam, the end rib and the filling core material are bonded by a film to form a missile wing body; the composite material skin is laminated on the surface of the missile wing body and then co-cured by molding to form an integrated unit to form a clean-edge missile wing.

[0007] A steel bushing for connecting is embedded on the wing handle.

[0008] The main beam and the auxiliary beam are arranged in parallel at one end of the wing handle, and the main beam is arranged at a position of 25%-35% chord length from the leading edge of the wing, and the auxiliary beam is arranged at a position of 60%-70% chord length from the leading edge.

[0009] The main beam, auxiliary beam and end ribs are plate structures and can be directly manufactured on a flat tooling and then machined to improve production efficiency.

[0010] The material of the filling core material is PMI.

[0011] The edge of the end rib has an extension section extending inward; the extension section is provided with a sealing strip that seals with the composite material skin, and the outermost layer of the end rib can be directly paved with waterproof material during molding to further improve the waterproof performance.

[0012] The outer layer of the composite material skin is laid with a layer of high-strength barium phenolic glass fiber fabric prepreg at a laying angle of 45°, which plays a role in thermal protection while ensuring the impact resistance of the wing.

[0013] A method for preparing the above-mentioned lightweight wing comprises the following steps:

[0014] S1: Assemble the wing handle, main beam, auxiliary beam, end rib and filling core material into the wing body by adhesive film bonding;

[0015] S2: Lay composite skin prepreg on the surface of the wing body, and lay the 1-10 layers in a variable thickness dropping method;

[0016] S3: Laying a layer of high-strength barium phenolic glass fiber fabric prepreg on the outermost surface of the skin;

[0017] S4: The wing body laid out in S3 is molded into a clean-edge integrated wing.

[0018] The thickness of the layers 1 to 10 in S2 is thicker near the wing handle and thinner away from the wing handle.

[0019] The layers 1 to 10 in S2 are symmetrical laminate structures.

[0020] By adopting the above technical scheme, the present invention has the following beneficial effects: the present invention provides a lightweight missile wing, which mainly uses composite materials, utilizes the advantages of low density and high strength of composite materials, can ensure structural strength and rigidity, and has a light overall structure and high structural efficiency, thereby increasing the range and effective load of the missile; and the structural design is simple, which can reduce working hours, reduce production costs, and greatly improve production efficiency. In addition, the standard layer is paved with high-strength barium phenolic glass fiber fabric prepreg, which greatly improves the thermal protection performance of the surface layer of the missile wing. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to make the contents of the present invention more clearly understood, the present invention is further described in detail below based on specific embodiments in conjunction with the accompanying drawings.

[0022] Figure 1 It is a structural schematic diagram of the present invention.

[0023] The reference numerals in the accompanying drawings are:

[0024] Wing handle 1, main beam 2, auxiliary beam 3, end rib 4, filling core material 5, composite material skin 6, steel bushing 7. DETAILED DESCRIPTION

[0025] (Example 1)

[0026] See Figure 1 A light missile wing of this embodiment includes a metal wing handle 1, a main beam 2, an auxiliary beam 3, an end rib 4, a filling core material 5 and a composite material skin 6 coated on the outer layer; the wing handle 1, the main beam 2, the auxiliary beam 3, the end rib 4 and the filling core material 5 are bonded by a film to form a missile wing body; the composite material skin 6 is laminated on the surface of the missile wing body and is molded and co-cured to form an integrated unit to form a clean-edge missile wing.

[0027] Furthermore, a steel bushing 7 for connecting is embedded on the wing handle 1 to facilitate the installation of the missile wing. The metal wing handle 1 mainly serves as a connection for connecting the missile wing and the missile, and is also used to ensure the overall rigidity of the missile wing and the deflection of the end of the missile wing to meet the required value, thereby ensuring the flight performance of the missile. The steel bushing 7 improves the anti-wear protection function of the connection between the missile wing and the missile on the one hand, and on the other hand, the connection position is subjected to greater force, and the steel bushing 7 has a higher strength, which can ensure its strength index, and is easy to replace after subsequent damage, and has a lower cost.

[0028] Furthermore, the main beam 2 and the auxiliary beam 3 are arranged in parallel at one end of the wing handle 1, and the main beam 2 is arranged at a position of 25%-35% of the chord length from the leading edge of the wing, preferably 30%, and the auxiliary beam 3 is arranged at a position of 60%-70% of the chord length from the leading edge, preferably 65%; this design can effectively ensure the overall structural strength of the wing.

[0029] Furthermore, the main beam 2, auxiliary beam 3 and end rib 4 may adopt a plate structure, which can be directly manufactured on a flat tooling and then machined into a designed structure, which can greatly improve production efficiency.

[0030] Furthermore, the filling core material 5 is made of PMI, which has a large compression strength and can meet the process requirements of the molding pressure.

[0031] Furthermore, in order to ensure the sealing between the skin and the end rib 4, the edge of the end rib 4 has an extension section extending inward; the extension section is provided with a sealing strip sealed with the composite skin 6, and the outermost layer of the end rib 4 can be directly laid with waterproof material during molding to further improve the waterproof performance.

[0032] Furthermore, a layer of high-strength barium phenolic glass fiber fabric prepreg is laid on the outer layer of the composite material skin at a laying angle of 45°, which plays a role in thermal protection while ensuring the impact resistance of the wing.

[0033] A method for preparing the above-mentioned lightweight wing comprises the following steps:

[0034] S1: The wing handle 1, the main beam 2, the auxiliary beam 3, the end rib 4 and the filling core material 5 are assembled into a wing body by bonding with adhesive film;

[0035] S2: laying a carbon fiber prepreg composite material skin 6 on the surface of the wing body, and laying the 1-10 layers by a variable thickness dropping layer method;

[0036] S3: Lay a layer of high-strength barium phenolic glass fiber fabric prepreg on the outermost surface of the skin at a laying angle of 45°;

[0037] S4: The wing body laid out in S3 is molded into a clean-edge integrated wing.

[0038] Furthermore, the thickness of the layers 1 to 10 in S2 is thicker near the wing handle 1 and thinner away from the wing handle 1, thereby reducing the structural mass while ensuring the rigidity.

[0039] Furthermore, the layers 1 to 10 in S2 are symmetrical laminate structures, which can effectively reduce the deformation caused by coupling and ensure the structural stability of the wing. The specific laying method is:

[0040] Layer 1, layer angle: ±45°, layer material: T700 carbon fiber fabric prepreg, layer position: whole layer;

[0041] Layer 2, layer angle: 0 / 90°, layer material: T700 carbon fiber fabric prepreg, layer position: drop layer;

[0042] Layer 3, layer angle: 0 / 90°, layer material: T700 carbon fiber fabric prepreg, layer position: drop layer;

[0043] Layer 4, layer angle: ±45°, layer material: T700 carbon fiber fabric prepreg, layer position: drop layer;

[0044] Layer 5, layer angle: 0 / 90°, layer material: T700 carbon fiber fabric prepreg, layer position: whole layer;

[0045] Layer 6, layer angle: 0 / 90°, layer material: T700 carbon fiber fabric prepreg, layer position: whole layer;

[0046] Layer 7, layer angle: ±45°, layer material: T700 carbon fiber fabric prepreg, layer position: missing layer;

[0047] Layer 8, layer angle: 0 / 90°, layer material: T700 carbon fiber fabric prepreg, layer position: missing layer;

[0048] Laying layer 9, laying angle: 0 / 90°, laying material: T700 carbon fiber fabric prepreg, laying position: missing layer.

[0049] Lamination 10, lamination angle: ±45°, lamination material: T700 carbon fiber fabric prepreg, lamination position: whole layer.

[0050] The missile wing prepared by the lightweight missile wing and the preparation method thereof of this embodiment has the advantages of high strength, can ensure structural strength and rigidity, the overall structure is light, the structural efficiency is high, and the range and effective load of the missile are increased; and the structural design is simple, which can reduce working hours, reduce production costs, and greatly improve production efficiency. In addition, the surface is paved with high-strength barium phenolic glass fiber fabric prepreg, which greatly improves the thermal protection and impact resistance of the surface of the missile wing.

[0051] The specific embodiments described above further illustrate the objectives, technical solutions and beneficial effects of the present invention in detail. It should be understood that the above description is only a specific embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A lightweight bomb wing, characterized in that: The invention comprises a metal wing handle (1), a main beam (2), an auxiliary beam (3), an end rib (4), a filling core material (5) and a composite material skin (6) coated on an outer layer; the wing handle (1), the main beam (2), the auxiliary beam (3), the end rib (4) and the filling core material (5) are bonded by adhesive film to form a wing body; the composite material skin (6) is laminated on the surface of the wing body and then co-cured by molding to form an integrated body to form a clean-edge wing.

2. A lightweight bomb wing according to claim 1, characterized in that: The wing handle (1) is embedded with a steel bushing (7) for connecting.

3. A lightweight wing according to claim 1, characterized in that: The main beam (2) and the auxiliary beam (3) are arranged in parallel at one end of the wing handle (1), and the main beam (2) is arranged at a position of 25%-35% of the chord length from the leading edge of the wing, and the auxiliary beam (3) is arranged at a position of 60%-70% of the chord length from the leading edge.

4. A lightweight bomb wing according to claim 1, characterized in that: The main beam (2), the auxiliary beam (3) and the end rib (4) are plate-type structures, and the main beam (2), the auxiliary beam (3) and the end rib (4) can be directly manufactured on a flat tooling and then machined into shape.

5. A lightweight bomb wing according to claim 1, characterized in that: The material of the filling core material (5) is PMI.

6. A lightweight bomb wing according to claim 1, characterized in that: The edge of the end rib (4) has an extension section extending inward; the extension section is provided with a sealing strip for sealing with the composite material skin (6), and the outermost layer of the end rib (4) is paved with a waterproof material.

7. A lightweight bomb wing according to claim 1, characterized in that: The outer layer of the composite material skin (6) is laid with a layer of high-strength barium phenolic glass fiber fabric prepreg at a laying angle of 45°.

8. A method for preparing the lightweight wing according to any one of claims 1 to 6, characterized in that: The following steps are involved: S1: The wing handle (1), the main beam (2), the auxiliary beam (3), the end rib (4) and the filling core material (5) are assembled into a wing body by bonding with adhesive film; S2: laying composite material skin (6) prepreg on the surface of the wing body, and laying 1-10 layers by variable thickness dropping method; S3: Laying a layer of high-strength barium phenolic glass fiber fabric prepreg on the outermost surface of the skin; S4: The wing body laid out in S3 is molded into a clean-edge integrated wing.

9. The method for preparing a lightweight wing according to claim 8, characterized in that: The thickness of the layers 1 to 10 in S2 is greater near the wing handle (1) and less far from the wing handle (1).

10. The method for preparing a lightweight wing according to claim 8, characterized in that: The layers 1 to 10 in S2 are a symmetrical laminate structure.

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