Aircraft fuselage skin detection element implantation structure

Abstract

The utility model belongs to the technical field of fuselage products for hovercars, and provides an aircraft skin detection element implantation structure, which comprises a fuselage skin and a plurality of detection elements, a skeleton layer is integrally formed on the fuselage skin, a plurality of mounting grooves corresponding to the detection elements are arranged on the skeleton layer, and the detection elements are arranged in the mounting grooves. The detection element is installed in the installation groove and attached to the skin surface of the fuselage or the framework. The utility model has the advantages of low cost, high efficiency, mass production, technical accumulation, high position precision of detection elements, high positioning efficiency, better product fusion degree and better detection effect, the framework layer is formed through the mould, the installation grooves are used for positioning, and the number of the detection elements is determined by the number of the installation grooves.

Description

Technical Field

[0001] The utility model belongs to the technical field of fuselage products for flying cars, and particularly relates to an aircraft fuselage skin detection element implantation structure. Background Art

[0002] The skin is the main structure of the aircraft fuselage, and composite materials are widely used. Composite materials have many superior properties, including high specific strength, high specific modulus, good fatigue resistance, excellent high-temperature performance, good shock absorption and good fracture safety. The skin mainly transmits tensile, compressive and shear loads. To ensure flight safety, detection elements are generally installed in the fuselage skin to check the strain generated during the stress process of the fuselage skin, so as to evaluate the health of the entire aircraft structure, predict possible fatigue damage and cracks, and take maintenance and repair measures in time. The existing method is to install the entire detection element by gluing it on the surface of the fuselage skin. The main disadvantages of this method are manual positioning and bonding, which is relatively time-consuming. The positioning accuracy is greatly affected by human operation and installation method. The thickness of the glue layer is uneven, which affects the data transmission results. In addition, the product and the detection element are independent and the integration is not good enough. Utility Model Content

[0003] The technical problem to be solved by the utility model is to provide an aircraft fuselage skin detection element implantation structure with precise installation position, good product integration and accurate detection in response to the current status of the existing technology.

[0004] The technical solution adopted by the present invention to solve the above technical problems is: an aircraft fuselage skin detection element implantation structure, including a fuselage skin and a plurality of detection elements, characterized in that a skeleton layer is integrally formed on the fuselage skin, and a plurality of mounting grooves corresponding to the detection elements are arranged on the skeleton layer, and the detection elements are installed in the mounting grooves and fit with the fuselage skin surface or the skeleton.

[0005] In the above-mentioned aircraft fuselage skin detection element implantation structure, there is also a structural adhesive layer between the detection element and the fuselage skin surface. After the detection element is placed in the installation groove, its inner surface is bonded to the fuselage skin surface through the structural adhesive layer.

[0006] In the above-mentioned aircraft fuselage skin detection element implantation structure, there is also a structural adhesive layer between the detection element and the bottom surface of the installation groove. After the detection element is placed in the installation groove, its inner surface is bonded to the bottom surface of the installation groove through the structural adhesive layer.

[0007] In the above-mentioned aircraft fuselage skin detection element implantation structure, the outer surface of the detection element is flush with the notch of the installation groove.

[0008] In the above-mentioned aircraft fuselage skin detection element implantation structure, the skeleton layer is made of plastic material and is integrally injection-molded on the surface of the fuselage skin.

[0009] In the above-mentioned aircraft fuselage skin detection element implantation structure, the thickness of the skeleton layer is 1.5 mm to 3 mm.

[0010] In the above-mentioned aircraft fuselage skin detection element implantation structure, the thickness of the structural adhesive layer is 0.1 mm-0.5 mm.

[0011] In the above-mentioned aircraft fuselage skin detection element implantation structure, the thickness of the fuselage skin is ≥0.4 mm.

[0012] In the above-mentioned aircraft fuselage skin detection element implantation structure, the fuselage skin is a composite material skin and is formed by molding.

[0013] Compared with the existing technology, the advantages of the present invention are low cost, high efficiency, mass production, and technical accumulation. The skeleton layer is formed by the mold and the mounting groove is used for positioning. The position accuracy of the detection element is high, the number of mounting grooves determines the number of detection elements, the positioning efficiency is high, the integration with the product is better, and the detection effect is better. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 This is a schematic diagram of the overall structure of the aircraft fuselage skin detection element implantation;

[0015] Figure 2 yes Figure 1 AA structural diagram;

[0016] Figure 3 yes Figure 1 Schematic diagram of the AA structure in another direction. DETAILED DESCRIPTION

[0017] The following are specific embodiments of the present invention and the accompanying drawings to further describe the technical solution of the present invention, but the present invention is not limited to these embodiments.

[0018] In the figure, there are fuselage skin 100; detection element 200; skeleton layer 300; mounting groove 400; notch 401; and structural adhesive layer 500.

[0019] Example 1

[0020] like Figure 1As shown, the aircraft skin detection element 200 implantation structure includes a fuselage skin 100 and a plurality of detection elements 200. In order to ensure strength and weight, the fuselage skin 100 can be a composite material. In this embodiment, the fuselage skin 100 is optimized to be a carbon fiber skin of a composite material. The carbon fiber skin is formed by composite molding. The thickness of the fuselage skin 100 is ≥ 0.4 mm. The detection elements 200 are arranged on the surface of the fuselage skin 100 and are mainly used to detect the entire strain and stress changes. Here, the most important feature of this patent is the detection element 200. The biggest innovation is that a skeleton layer 300 is integrally formed on the fuselage skin 100. The skeleton layer 300 is made of plastic material and is integrally injection-molded on the surface of the fuselage skin 100. The thickness of the skeleton layer 300 is 1.5mm-3mm, and is optimized to 2mm in this embodiment. In order to facilitate the installation of the entire detection element 200, a plurality of mounting grooves 400 corresponding to the detection elements 200 are arranged on the skeleton layer 300. The detection element 200 is installed in the mounting groove 400 and fits with the surface of the fuselage skin 100. Figure 3 As shown, there is a structural adhesive layer 500 between the detection element 200 and the bottom surface of the installation groove 400. After the detection element 200 is placed in the installation groove 400, its inner surface is bonded to the bottom surface of the installation groove 400 through the structural adhesive layer 500, that is, it fits with the bottom surface of the installation groove 400. Here, during installation, it is necessary to ensure that the outer surface of the detection element 200 is flush with the notch 401 of the installation groove 400. The main function of the installation groove 400 is to accommodate the entire detection element 200. Since the position of the installation groove 400 is fixed, the position of the detection element 200 after being installed in the installation groove 400 is also fixed. In this way, positioning by using the installation groove 400 can ensure that the detection The element 200 has high positioning accuracy and high positioning efficiency. In order to ensure the reliability of the positioning of the detection element 200, a structural adhesive layer 500 is provided between the detection element 200 and the surface of the fuselage skin 100. After the detection element 200 is placed in the installation groove 400, its inner surface is bonded to the surface of the fuselage skin 100 through the structural adhesive layer 500, or is adhered to the bottom surface of the installation groove 400. The thickness of the structural adhesive layer 500 is 0.1mm-0.5mm, which is specifically optimized to 0.3mm in this embodiment. The structural adhesive layer 500 mainly plays the role of bonding and positioning, and also facilitates the subsequent installation and connection of electronic components such as conductive silver paste with the detection element 200.

[0021] During the overall production, the composite material is first molded to form the fuselage skin 100, and then the skeleton layer 300 is injection-molded on the fuselage skin 100, and then glue is dispensed in the installation groove 400 to form a structural adhesive layer 500, and then the detection element 200 is bonded in the installation groove 400 through the structural adhesive layer 500.

[0022] Example 2

[0023] like Figure 1As shown, the aircraft skin detection element 200 implantation structure includes a fuselage skin 100 and a plurality of detection elements 200. In order to ensure strength and weight, the fuselage skin 100 can be a composite material. In this embodiment, the fuselage skin 100 is optimized to be a carbon fiber skin of a composite material. The carbon fiber skin is formed as a whole by composite molding. The thickness of the fuselage skin 100 can be ≥0.4mm. A skeleton layer 300 is integrally formed on the fuselage skin 100. The skeleton layer 300 is made of plastic material and is integrally injection molded on the surface of the fuselage skin 100. The thickness of the skeleton layer 300 is 1.5mm-3mm, which is optimized to 1.5mm in this embodiment. A plurality of mounting grooves 400 corresponding to the detection elements 200 are arranged on the skeleton layer 300. The detection elements 200 are installed in the mounting grooves 400 and fit with the surface of the fuselage skin 100. Figure 3 As shown, there is a structural adhesive layer 500 between the detection element 200 and the bottom surface of the installation groove 400. After the detection element 200 is placed in the installation groove 400, its inner surface is bonded to the bottom surface of the installation groove 400 through the structural adhesive layer 500, that is, it is in contact with the bottom surface of the installation groove 400, or it can be in contact with the bottom surface of the installation groove 400. There is also a structural adhesive layer 500 between the detection element 200 and the surface of the fuselage skin 100. After the detection element 200 is placed in the installation groove 400, its inner surface is bonded to the surface of the fuselage skin 100 through the structural adhesive layer 500, or it is in contact with the bottom surface of the installation groove 400. Here, the thickness of the structural adhesive layer 500 is 0.1mm-0.5mm, and is specifically optimized to 0.1mm in this embodiment.

[0024] Example 3

[0025] like Figure 1As shown, the aircraft skin detection element 200 implantation structure includes a fuselage skin 100 and a plurality of detection elements 200. In order to ensure strength and weight, the fuselage skin 100 can be a composite material. In this embodiment, the fuselage skin 100 is optimized to be a composite material skin. The carbon fiber skin is integrally formed by composite molding. The thickness of the fuselage skin 100 is ≥ 0.4 mm. A skeleton layer 300 is integrally formed on the fuselage skin 100. The skeleton layer 300 is made of plastic material and is integrally injection molded on the surface of the fuselage skin 100. The thickness of the skeleton layer 300 is optimized to 3 mm. A plurality of mounting grooves 400 corresponding to the detection elements 200 are arranged on 300. The detection element 200 is installed in the mounting groove 400 and is bonded to the surface of the fuselage skin 100, or it can be bonded to the bottom of the mounting groove 400. There is also a structural adhesive layer 500 between the detection element 200 and the surface of the fuselage skin 100. After the detection element 200 is placed in the mounting groove 400, its inner surface is bonded to the surface of the fuselage skin 100 through the structural adhesive layer 500, or it is bonded to the bottom of the mounting groove 400. Here, the thickness of the structural adhesive layer 500 is 0.1mm-0.5mm, and is specifically optimized to 0.5mm in this embodiment.

[0026] The detection element 200 formed by the fuselage skin 100 of the above embodiment has low structural cost, high efficiency, mass production capability, and technical accumulation. The skeleton layer 300 is formed by a mold and positioned by the mounting groove 400. The positioning accuracy of the detection element 200 is high, and the number of the mounting grooves 400 determines the number of the detection elements 200. The positioning efficiency is high, the integration with the product is better, and the detection effect is better.

[0027] The specific embodiments described in this article are merely examples of the spirit of the present invention. Technicians in the technical field to which the present invention belongs can make various modifications to the described specific embodiments or replace them with similar methods, but they will not deviate from the scope defined by the spirit of the present invention.

Claims

1. An aircraft fuselage skin detection element implantation structure, comprising a fuselage skin and a plurality of detection elements, characterized in that: A skeleton layer is integrally formed on the fuselage skin, and a plurality of mounting grooves corresponding to the detection elements are arranged on the skeleton layer. The detection elements are installed in the mounting grooves and fit with the fuselage skin surface or the skeleton.

2. The aircraft fuselage skin detection element implantation structure according to claim 1, characterized in that: There is also a structural adhesive layer between the detection element and the fuselage skin surface. After the detection element is placed in the installation groove, its inner surface is bonded to the fuselage skin surface through the structural adhesive layer.

3. The aircraft fuselage skin detection element implantation structure according to claim 1, characterized in that: There is also a structural adhesive layer between the detection element and the bottom surface of the installation groove. After the detection element is placed in the installation groove, its inner surface is bonded to the bottom surface of the installation groove through the structural adhesive layer.

4. The aircraft fuselage skin detection element implantation structure according to claim 1, characterized in that: The outer surface of the detection element is flush with the notch of the installation slot.

5. The aircraft fuselage skin detection element implantation structure according to claim 1, characterized in that: The skeleton layer is made of plastic material and is integrally injection-molded on the surface of the fuselage skin.

6. The aircraft fuselage skin detection element implantation structure according to claim 1, characterized in that: The thickness of the skeleton layer is 1.5mm-3mm.

7. The aircraft fuselage skin detection element implantation structure according to claim 2 or 3, characterized in that: The thickness of the structural adhesive layer is 0.1mm-0.5mm.

8. The aircraft fuselage skin detection element implantation structure according to claim 1, characterized in that: The thickness of the fuselage skin is ≥0.4 mm.

9. The aircraft fuselage skin detection element implantation structure according to claim 3, characterized in that: The fuselage skin is a composite material skin and is formed by molding.

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