A composite honeycomb sandwich panel longitudinal wall unit

Abstract

The application belongs to the field of wallboard design, and particularly relates to a composite honeycomb sandwich wallboard longitudinal wall integral forming piece, which comprises an outer skin, a wallboard core material, an inner skin, a web core material, a rim strip and a film. The outer skin and the inner skin are correspondingly arranged, the inner skin and the outer skin are provided with the rim strip which is perpendicular to the outer skin, the web core material is arranged in the rim strip, the wallboard core material has two groups and is arranged in the outer skin and the inner skin respectively, and the film has multiple groups and is arranged in the outer skin, the inner skin and the web respectively. The rim strip and the web core material form the longitudinal wall. The outer skin, the inner skin and the rim strip are all composite materials. The film can be used for bonding between the outer skin and the wallboard core material, the inner skin and the wallboard core material, and the rim strip and the web core material. The stiffness, strength and stability are optimized, the thickness and layering sequence of the inner and outer skins and the rim strip are determined according to the designability of the composite material, and the appropriate aramid paper honeycomb specifications and thickness are selected according to the process conditions.

Description

Technical Field

[0001] This application belongs to the field of wall panel design, and specifically relates to an integrally molded longitudinal wall component of a composite honeycomb sandwich wall panel. Background Technology

[0002] Composite honeycomb sandwich panels possess lightweight and high rigidity characteristics, and are frequently used in aircraft control surfaces. A full-height honeycomb sandwich structure is employed to achieve ideal control surface stiffness, representing a lightweight and high-rigidity structural configuration. High-altitude long-endurance unmanned aerial vehicles (UAVs) require further lightweight design to achieve long-endurance technical specifications, demanding a low structural weight coefficient. The innovative application of composite honeycomb sandwich panel configurations is one of the effective ways to achieve lightweight wing panels and longitudinal walls. Utility Model Content

[0003] The purpose of this application is to provide an integrally molded composite honeycomb sandwich panel longitudinal wall to solve the problem of excessive weight in existing body structures.

[0004] The technical solution of this application is: a composite material honeycomb sandwich wall panel longitudinal wall integral molding part, including an outer skin, wall panel core material, inner skin, web core material, edge strip and adhesive film;

[0005] A longitudinal wall is set perpendicular to the outer skin and the inner skin. The web core material and the flange strip are both located on the longitudinal wall. The web core material is located inside the flange strip. There are two sets of wall panel core materials, which are respectively located inside the outer skin and the inner skin. There are multiple sets of adhesive film, which are respectively located inside the outer skin, the inner skin and the web. The flange strip and the web core material form the longitudinal wall.

[0006] The outer skin, inner skin, and flange are all composite materials; the adhesive film can bond the outer skin to the core material of the wall panel, the inner skin to the core material of the wall panel, and the flange to the core material of the web.

[0007] Preferably, the materials of the wall panel core material and the web chip are both paper honeycomb.

[0008] Preferably, the cross-section of the flange is T-shaped, and no wall panel core material is provided at the positions of the inner and outer skins corresponding to the flange.

[0009] The composite honeycomb sandwich panel longitudinal wall integral molding component of this application realizes multi-constraint optimization design of stiffness, strength and stability, makes full use of the designability of composite materials to determine the thickness and layup sequence of the inner and outer skins and edge strips of composite materials, and selects appropriate aramid paper honeycomb specifications and thickness in combination with process conditions. Attached Figure Description

[0010] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0011] Figure 1 This is a schematic diagram of the overall structure of this application.

[0012] 1. Outer skin; 2. Wall panel core material; 3. Inner skin; 4. Web core material; 5. Flanging strip; 6. Adhesive film. Detailed Implementation

[0013] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0014] A composite material honeycomb sandwich panel longitudinal wall integral molding component, such as Figure 1 As shown, it includes an outer skin 1, a wall panel core material 2, an inner skin 3, a web core material 4, a flange strip 5, and a film 6.

[0015] A longitudinal wall is set perpendicular to the outer skin 1 and the inner skin 3. The web core material 4 and the flange strip 5 are both located on the longitudinal wall. The web core material 4 is located inside the flange strip 5. There are two sets of wall panel core materials 2, which are respectively located inside the outer skin 1 and the inner skin 3. There are multiple sets of adhesive film 6, which are respectively located inside the outer skin 1, the inner skin 3 and the web. The flange strip 5 and the web core material 4 form the longitudinal wall.

[0016] The outer skin 1, inner skin 3, and flange 5 are all composite materials. The adhesive film 6 can bond the outer skin 1 to the wall panel core material 2, the inner skin 3 to the wall panel core material 2, and the flange 5 to the web core material 4.

[0017] Through the above design, the stiffness, strength and stability multi-constraint optimization design is realized. The designability of composite materials is fully utilized to determine the thickness and layup sequence of the inner and outer skins 1 and the edge strips 5 of the composite materials, and the appropriate aramid paper honeycomb specifications and thickness are selected in combination with the process conditions.

[0018] Preferably, the materials of the wall panel core material 2 and the web chip are both paper honeycomb.

[0019] Preferably, the cross-section of the flange 5 is T-shaped, and the inner skin 3 and the outer skin 1 are not provided with wall panel core material 2 at the positions corresponding to the flange 5, so as to ensure the connection stability of the flange 5.

[0020] During the manufacturing process, the outer skin 1 and longitudinal wall of the composite material are pre-fixed and bonded together to achieve the overall bonding and molding of the outer skin 1, paper honeycomb core material, inner skin 3, and longitudinal wall. The composite honeycomb sandwich structure improves the bending stiffness of the wall panel / longitudinal wall cross section. The overall bonded structure replaces the connecting fasteners of the previous combined structure, effectively improving the overall structural integrity.

[0021] The manufacturing process is as follows:

[0022] The outer skin 1 of the composite material is pre-formed in a mold using a co-curing process with unidirectional tape prepreg. The longitudinal walls of the composite honeycomb sandwich core are pre-formed in a mold using a co-curing process with unidirectional tape prepreg, honeycomb core material, and adhesive film 6. After the outer skin 1, wall panel core material 2, and longitudinal walls are bonded and pre-assembled with the inner skin 3, the integrated wall panel / longitudinal wall assembly is formed in a mold using a co-bonding process. Under the same design parameters such as stiffness and strength, the weight is reduced by more than 30% compared to the metal wall panel / longitudinal wall assembly, achieving significant weight reduction benefits.

[0023] In the manufacturing process, compared with traditional wall panel (composite material, metal) and longitudinal wall (composite material, metal) assemblies, the new composite honeycomb sandwich wall panel longitudinal wall integral molding component, due to the use of composite materials with high specific stiffness and specific strength and aramid paper honeycomb, and high cross-sectional stiffness configuration, makes the wall panel / longitudinal wall lighter. At the same time, through co-bonding integral molding, the fasteners used for connecting traditional wall panel and longitudinal wall assemblies are eliminated, improving the overall structural integrity and stiffness characteristics, and effectively reducing the structural weight.

[0024] This application adopts advanced composite materials, honeycomb core materials and their integrated technology, with a simple, novel and efficient structure. It fully utilizes the excellent performance of composite honeycomb sandwich panels and can achieve the requirements of lightweight, high rigidity and long service life of integrated wall panel longitudinal wall assemblies.

[0025] Finally, it should be noted that the accompanying drawings of the embodiments disclosed in this utility model only involve the structures involved in the embodiments disclosed in this utility model. Other structures can refer to the general design. In the absence of conflict, the same embodiment and different embodiments of this utility model can be combined with each other.

[0026] Finally: The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A composite material honeycomb sandwich panel longitudinal wall integrally molded component, characterized in that: It includes outer skin (1), wall panel core material (2), inner skin (3), web core material (4), flange strip (5), and adhesive film (6); A longitudinal wall is set perpendicular to the outer skin (1) and the inner skin (3). The web core material (4) and the flange strip (5) are both located on the longitudinal wall. The web core material (4) is located inside the flange strip (5). There are two sets of wall panel core materials (2) and they are respectively located inside the outer skin (1) and the inner skin (3). There are multiple sets of adhesive film (6) and they are respectively located inside the outer skin (1), the inner skin (3) and the web. The flange strip (5) and the web core material (4) form the longitudinal wall. The outer skin (1), inner skin (3) and flange strip (5) are all composite materials; the adhesive film (6) can bond the outer skin (1) to the wall core material (2), the inner skin (3) to the wall core material (2), and the flange strip (5) to the web core material (4).

2. The integrally molded longitudinal wall component of the composite honeycomb sandwich panel as described in claim 1, characterized in that: The materials of the wall panel core material (2) and the web chip are both paper honeycomb.

3. The integrally molded longitudinal wall component of the composite honeycomb sandwich panel as described in claim 1, characterized in that: The cross-section of the flange (5) is T-shaped, and the inner skin (3) and outer skin (1) are not provided with wall panel core material (2) at the positions corresponding to the flange (5).

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