Joint and beam wall integrated rudder structure and forming method

Abstract

The application relates to a joint and beam wall integrated rudder surface structure which is composed of a main joint, an integral skin, a sandwich and a cushion block; one end of the main joint is a connecting joint, and the other end is a C-shaped structure with a Z-shaped section; the skin is designed as an integral skin which wraps the main joint, and the skin length is greater than the main joint length; the sandwich completely fills the cavity area between the skin and the main joint, and a composite material cushion block is used to fill the rear edge part of the rudder surface. The rudder surface structure integrates the main joint and the beam wall into a machining form, and the upper and lower skins and the front edge are designed as an integral skin, so that a plurality of parts are cancelled. The purpose is to reduce the part quantity, simplify the manufacturing process, shorten the manufacturing period and further reduce the rudder surface manufacturing cost.

Description

Technical Field

[0001] This invention belongs to the field of aircraft structural design technology, and specifically relates to an integrated control surface structure of joint and beam wall and its forming method. Background Technology

[0002] Control surfaces are crucial components on aircraft, ensuring good maneuverability and stability. With the increasing demand for lightweight aircraft structures, more and more control surfaces are adopting composite sandwich structures. Traditional composite sandwich structures generally include metal joints, reinforcing beams and walls, a core, upper and lower skins, leading edges, and other parts. These parts need to be assembled through adhesive bonding, mechanical connections, and other methods, resulting in a complex structure, high manufacturing costs, and long manufacturing cycles. Summary of the Invention

[0003] Purpose of the invention: To provide an integrated rudder surface structure with a joint and beam wall, wherein the main joint and beam wall are integrally machined, and the upper and lower skins and the leading edge are designed as a single integral skin, eliminating multiple parts. The aim is to reduce the number of parts, simplify the manufacturing process, shorten the manufacturing cycle, and further reduce the manufacturing cost of the rudder surface.

[0004] Technical solution: An integrated rudder surface structure with joint and beam wall, consisting of a main joint, an integral skin, a core, and pads; one end of the main joint is a connecting joint, and the other end is a C-shaped structure with a "Z" cross section; the skin is designed as an integral skin that wraps around the main joint, and the length of the skin is greater than the length of the main joint; the core completely fills the cavity area between the skin and the main joint, and the trailing edge of the rudder surface is filled with composite material pads.

[0005] Furthermore, both the upper and lower ends of the Z-shaped cross-section are designed with arcs to completely fit the inner surface of the skin; this structure increases the bonding area with the skin and improves the connection strength between the skin and the main joint.

[0006] Furthermore, the leading edge of the rudder surface adopts a circular arc transition, and the core is fully filled in the transition area.

[0007] Furthermore, the sandwich core is machined from lightweight PMI foam board.

[0008] Furthermore, the connecting end of the main connector has a connecting groove and a lightening hole.

[0009] Furthermore, a skin thickness difference is formed between the outer surface of the main connector's connecting joint and the outer surface of the C-shaped structure; the outer surface of the main connector's mounting joint is flush with the outer surface of the skin to ensure aerodynamic shape.

[0010] In this design, the control surface consists of a main joint, an integral skin, a core, and pads. One end of the main joint has a connecting groove and a lightening hole, while the other end has a C-shaped structure with a Z-shaped cross-section. The Z-shaped cross-section increases the bonding area with the skin, improving the connection strength between the skin and the main joint, and eliminating the need for a mechanical connection. The C-shaped structure increases the rigidity of the control surface. The skin, providing shape support, is designed as an integral skin, simplifying the manufacturing process. The core completely fills the cavity between the skin and the main joint, and is machined using lightweight PMI foam board. The trailing edge of the control surface is filled with composite material pads.

[0011] Beneficial technical effects: The present invention has the following main advantages:

[0012] 1) The main joint of the rudder surface is designed as an integral part of the beam wall, which reduces the number of parts, improves the rigidity of the rudder surface, simplifies the manufacturing process, and reduces production costs.

[0013] 2) The main joint is designed with a "Z" shaped cross section, which increases the bonding area with the skin and improves the connection strength;

[0014] 3) The skin is designed as a single piece, which simplifies the manufacturing process. Attached Figure Description

[0015] Figure 1 This is a general diagram of the rudder surface structure of the present invention;

[0016] Figure 2 for Figure 1 Sectional view of section AA;

[0017] Figure 3 Schematic diagram of the main connector structure;

[0018] Among them, 1-main connector, 2-integral skin, 3-core sandwich, 4-pad block, 1-1-lightening hole, 1-2-connecting groove, 1-3-front beam, 1-4-rear beam, 1-5-reinforcing rib. Detailed Implementation

[0019] 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.

[0020] See Figures 1-3The control surface consists of a main connector 1, an integral skin 2, a core 3, and pads 4. One end of the main connector 1 has a connecting groove and a lightening hole, while the other end is a C-shaped structure composed of a front beam, a rear beam, and reinforcing ribs. The positions of the beams and ribs can be adaptively adjusted according to aerodynamic loads. The C-shaped structure has a Z-shaped cross-section, and the width of the upper and lower Z-shaped flanges can also be adjusted according to strength requirements, thus eliminating the mechanical connection between the skin and the main connector. The integral skin 2 integrates the upper and lower skins and the leading-edge fairing, allowing for a thinner design and reduced manufacturing costs. The core 3 is directly machined from lightweight, low-density materials, eliminating the need for molding molds compared to traditional foamed aluminum or foamed rubber, further shortening the manufacturing cycle. The pads 4 can be filled with composite material monofilaments.

[0021] In the specific implementation process, the outer surface of the main connector 1 is flush with the outer surface of the skin to ensure the aerodynamic shape.

[0022] The integrated rudder surface structure of the joint and beam wall designed in this invention has the following molding process: during molding, the main joint 1 and the core 3 are machined and then combined with the pad block 4 to form an integral core mold. Then, the integral skin 2 is laid on this integral core mold. After the laying is completed, it is cured and formed into an integral rudder surface.

[0023] During the molding process, when the core is assembled into an integral core mold, the core, main connector, and pad are all fixed with adhesive film; adhesive film is also provided between the skin and the core mold.

[0024] This invention presents an integrated rudder surface structure with a joint and beam-wall. This structure utilizes the integrated nature of the rudder surface joint and beam-wall, eliminating components such as the beam-wall and leading edge. The rudder surface structure is simplified to four parts: the main joint, the integral skin, the lightweight PMI foam core, and the padding blocks. This reduces the number of parts while maintaining rudder surface rigidity, simplifying the manufacturing process and reducing production costs.

[0025] The above specific embodiments or examples are only used to explain the technical solutions of the present invention and are not intended to limit the present application. Parts not described in detail are considered to be conventional technical means or common knowledge in the field. Those skilled in the art should understand that, based on the design concept of the present application, it is possible to make adaptive modifications to the technical solutions described in the foregoing embodiments or to make equivalent substitutions for some or all of the technical features. These modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the various embodiments of the present invention.

Claims

1. A rudder surface structure integrating the joint and beam / wall, characterized in that, It consists of a main connector, skin, core, and pads. One end of the main connector is a connecting joint, and the other end is a C-shaped structure composed of a front beam, a rear beam, and reinforcing ribs. The cross-sectional shape of the C-shaped structure is Z-shaped. The skin is designed as an integral skin that wraps around the main connector, and the length of the skin is greater than the length of the main connector. The core completely fills the cavity area between the skin and the main connector, while the trailing edge of the control surface is filled with composite material pads. The upper and lower ends of the Z-shaped cross-section are both arc-shaped, completely fitting the inner surface of the skin. The leading edge of the control surface has a rounded transition, and the core fully fills the transition area. A skin thickness difference is formed between the outer surface of the connecting joint of the main connector and the outer surface of the C-shaped structure. The outer surface of the connecting joint of the main connector is flush with the outer surface of the skin to ensure aerodynamic shape.

2. The integrated joint and beam-wall rudder surface structure as described in claim 1, characterized in that, The sandwich core is machined from lightweight PMI foam board.

3. The integrated joint and beam-wall rudder surface structure as described in claim 1, characterized in that, The main connector has a connecting groove and a lightening hole at the end of the connecting joint.

4. A method for forming an integrated rudder surface structure of joint and beam wall as described in any one of claims 1 to 3, characterized in that, After the main connector and core are formed by the core-clamping machine, they are combined with the pad block to form an integral core mold. Then, the integral skin is laid on this integral core mold. After the skin is laid, it is cured and formed into an integral rudder surface.

5. The forming method of the integrated joint and beam-wall rudder surface structure as described in claim 4, characterized in that, When assembled into a single core mold, the core is bonded and fixed to the main connector and the pad block with adhesive film; adhesive film is also provided between the skin and the core mold.

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