CN214986020U

CN214986020U - Composite sandwich wall plate and unmanned aerial vehicle airfoil structure

Info

Publication number: CN214986020U
Application number: CN202022892859.1U
Authority: CN
Inventors: 李德勇; 梁兵; 陈建农; 张庆茂; 彭涛; 胡利
Original assignee: AVIC Chengdu Aircraft Design and Research Institute
Current assignee: AVIC Chengdu Aircraft Design and Research Institute
Priority date: 2020-12-04
Filing date: 2020-12-04
Publication date: 2021-12-03
Anticipated expiration: 2030-12-04

Abstract

The utility model discloses a combined material presss from both sides core wallboard and unmanned aerial vehicle airfoil structure. The composite material sandwich wall panel is characterized by comprising one or a plurality of continuous composite material sandwich wall panel units, wherein the composite material sandwich wall panel units comprise bonded outer skins (1), core materials (2) and inner skins (3), and transition areas among the plurality of continuous composite material sandwich wall panel units are formed by the bonded outer skins (1) and the bonded inner skins (3). The utility model discloses a combined material presss from both sides core wallboard light high-efficient can improve airfoil structure bulk strength and rigidity, satisfies flight load requirement, is applicable to the high altitude long-term unmanned aerial vehicle that navigates to part shaping and assembly problem have effectively been solved.

Description

Composite sandwich wall plate and unmanned aerial vehicle airfoil structure

Technical Field

The utility model belongs to the technical field of aircraft structural design, concretely relates to combined material presss from both sides core wallboard and unmanned aerial vehicle airfoil structure.

Background

With the development of high-altitude long-endurance unmanned aerial vehicle technology, conventional airfoil wall panels include conventional skin (composite laminate skin, metal skin), stiffened wall panels, and the like. Conventional skins cannot meet structural design requirements at light weight due to stability and damage tolerance limitations. The reinforced wall plate has obvious weight increment on the structure. In the wing structure formed by the wing panels, in order to improve stability, a core material can be filled between the upper and lower panels of the wing, namely, the full-height core material structure type, in this case, a system and a cable cannot be arranged in the wing structure, and the weight of the structure is increased. At present, a light and efficient wing surface wall plate meeting the requirement of long-endurance flight is urgently needed.

SUMMERY OF THE UTILITY MODEL

In view of prior art's above-mentioned problem, the utility model aims at coping with high altitude long time unmanned aerial vehicle's development trend when navigating, provide a combined material presss from both sides core wallboard and unmanned aerial vehicle airfoil structure to improve airfoil structure bulk strength and rigidity, satisfy the flight load requirement.

According to the utility model discloses an aspect provides a combined material presss from both sides core wallboard, its characterized in that includes one or continuous a plurality of combined material and presss from both sides core wallboard unit, combined material presss from both sides core wallboard unit and includes bonded outer covering, core and interior covering, and wherein the transition region between continuous a plurality of combined material presss from both sides core wallboard unit comprises bonded outer covering and interior covering.

Further, in the composite material sandwich wall panel unit, a triangular closed area formed by the outer skin, the core material and the inner skin is filled with filler. Because the triangular closed area is low in height, the core material is difficult to mold, and the filler can effectively improve the bonding quality, so that the problem of wall plate unit molding is solved. The filler is formed by compression molding of prepreg and resin. The included angle between the outer skin and the inner skin of the triangular closed area is not more than 20 degrees, the minimum height of the core material is 2mm +/-1 mm, namely the length of the side, opposite to the included angle, of the triangular closed area is 2mm +/-1 mm.

The core material may be a honeycomb core or a foam core, preferably a lightweight paper honeycomb.

In order to avoid the internal framework and maintain the channel, the core material is preferably in a blocking form, so that the forming quality is improved, the manufacturing defects of parts are reduced, and the working efficiency is improved.

According to an aspect of the utility model provides an unmanned aerial vehicle airfoil structure, including last wallboard and lower wallboard, wherein go up wallboard and lower wallboard and press from both sides core wallboard by the combined material as above and press from both sides the wing and constitute.

The utility model discloses a combined material presss from both sides core wallboard light high-efficient can improve airfoil structure bulk strength and rigidity, satisfies flight load requirement, is applicable to the high altitude long-term unmanned aerial vehicle that navigates to part shaping and assembly problem have effectively been solved.

Drawings

Fig. 1 is a structural layout diagram of the composite sandwich wall panel of the present invention.

Fig. 2 is a partial detail view of the composite sandwich panel of the present invention, wherein the upper part is an enlarged view of a triangular closed region and the lower part is an enlarged view of a transition region between the composite sandwich panel units.

Fig. 3 is a schematic view of the composite sandwich panel of the present invention in use on the airfoil structure.

Detailed Description

The present invention will be described in further detail with reference to the accompanying drawings in conjunction with specific embodiments.

Referring to fig. 1, the composite sandwich panel of the present invention includes one or more continuous composite sandwich panel units, which include bonded outer skin 1, core 2 and inner skin 3.

As shown in fig. 2, the transition area between the continuous multiple composite sandwich wall panel units is formed by the bonded outer skin 1 and inner skin 3 (see the lower part of fig. 2), and the composite sandwich wall panel is formed by gluing the outer skin 1, the core material 2 and the inner skin 3, so that the composite sandwich wall panel is easy to form, and the overall rigidity and strength of the composite sandwich wall panel assembly are effectively improved. In the composite sandwich panel unit, a triangular closed area formed by the outer skin 1, the core 2 and the inner skin 3 is filled with a filler 6 (see the upper part of fig. 2). Because the triangular closed area is low in height, the core material 2 is difficult to form, and the filler 6 can effectively improve the bonding quality, so that the problem of forming the wall plate unit is solved. The filler 6 is formed by compression molding of carbon fiber prepreg and resin. The included angle between the outer skin 1 and the inner skin 3 of the triangular closed area is not more than 20 degrees, the minimum height of the core material 2 is 2mm +/-1 mm, namely, the length of the side of the triangular closed area opposite to the included angle is 2mm +/-1 mm. The outer skin 1 and the inner skin 3 may be made of a high load-bearing carbon fiber composite material, preferably an epoxy carbon fiber composite material. The core material 2 may be a honeycomb core or a foam core, preferably a lightweight paper honeycomb.

The outer skin 1 and the core material 2, and the inner skin 3 and the core material 2 are bonded by a high-strength slab core glue 4 (i.e., a bonding glue between the skin and the core material, specifically, the slab core glue 4 may be an LWF-2A glue film), and the outer skin 1 and the inner skin 3 are bonded by a high-strength slab glue 5 (i.e., a bonding glue between the skin, specifically, the slab glue 5 may be an LWF-2B glue film).

In addition, as shown in fig. 1, in order to avoid the internal skeleton and maintain the channel, the core material 2 is preferably in a block form, which is beneficial to improving the forming quality, reducing the manufacturing defects of parts and improving the working efficiency.

Fig. 3 is a schematic view of the composite sandwich panel of the present invention in use on the airfoil structure. As shown in fig. 3, the drone airfoil structure includes an upper panel and a lower panel, wherein the upper and lower panels are formed in wing shape from composite sandwich panels as described above. In this example, the airfoil structure has an airfoil height of about 400mm and the height of the upper and lower panels is 40-50 mm. Although the composite sandwich panel shown in FIG. 3 includes only one composite sandwich panel unit, it is clearly not limited thereto, and the composite sandwich panel may include a plurality of composite sandwich panel units in series, as desired. In addition, as shown in the figure, the upper wall plate and the lower wall plate are provided with core materials, so that the overall stability of the wall plate can be improved. No core material needs to be filled in the space between the upper and lower wall plates, and the space between the upper and lower wall plates can be used for arranging systems, cables and the like. And a reinforcing framework can be arranged between the upper wall plate and the lower wall plate for further improving the strength.

Claims

1. The composite material sandwich wall panel is characterized by comprising one or a plurality of continuous composite material sandwich wall panel units, wherein each composite material sandwich wall panel unit comprises an outer skin (1), a core material (2) and an inner skin (3) which are bonded, transition regions among the plurality of continuous composite material sandwich wall panel units are formed by the outer skin (1) and the inner skin (3) which are bonded, in the composite material sandwich wall panel units, a triangular closed region formed by the outer skin (1), the core material (2) and the inner skin (3) is filled with a filler (6), and the filler (6) is formed by compression molding of prepreg and resin.

2. The composite sandwich panel according to claim 1, characterised in that the angle between the outer skin (1) and the inner skin (3) of the triangular closed area is less than or equal to 20 °, and the minimum height of the core material (2) is 2mm ± 1 mm.

3. The composite sandwich panel according to claim 1, characterized in that the core material (2) is a honeycomb core or a foam core.

4. The composite sandwich panel according to claim 1, characterized in that the core material (2) is a lightweight paper honeycomb.

5. The composite sandwich panel according to claim 1, characterized in that the core material (2) is in the form of segments.

6. An unmanned aerial vehicle airfoil structure comprising an upper panel and a lower panel, wherein the upper panel and the lower panel are formed in a wing shape from a composite sandwich panel according to any one of claims 1 to 5.