Aircraft fuselage containing detection element

Abstract

The utility model belongs to the technical field of fuselage products for hovercars, and provides an aircraft fuselage containing a detection element, which comprises a fuselage skin, the detection element is used for detecting the strain condition generated in the stress process; the plug-in assembly is arranged on the fuselage skin and used for being connected with the plug-in control unit; and the connecting piece is arranged on the fuselage skin and is used for electrically connecting the detection element and the plugging assembly. The utility model has the advantages that the connector can be connected with a plurality of detection elements, the number of control units is reduced, analysis is facilitated, a dismounting scheme is convenient, dismounting can be carried out at any time according to needs, the position precision is higher, the cost is low, the efficiency is high, mass production is realized, technical accumulation exists, a framework layer is formed through a mold, positioning is carried out through a mounting groove, and the position precision of the detection elements is high; the number of the installation grooves determines the number of the detection elements, the positioning efficiency is high, the product fusion degree is better, and the detection effect is better.

Description

Technical Field

[0001] The utility model belongs to the technical field of fuselage products for flying cars, and in particular relates to an aircraft fuselage containing a detection element. 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 breaking safety. The skin mainly transmits tensile, compressive and shear loads. In order 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 on the surface of the fuselage skin by gluing, and then directly connect the wires to the strain sensor. After installation, this method is troublesome to disassemble and the wiring harness is complicated. Another disadvantage is manual positioning and bonding, which is 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 present invention is to provide an aircraft fuselage containing detection elements with convenient connection control, precise installation position and good product integration in view of 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 containing a detection element, characterized in that it includes:

[0005] fuselage skin;

[0006] Detection element, used to detect the strain generated during the force application process;

[0007] A connector assembly is arranged on the fuselage skin and is used to connect the connector control unit;

[0008] Connectors are arranged on the fuselage skin and are used to electrically connect detection elements and connector components.

[0009] In the above-mentioned aircraft fuselage containing a detection element, the connector assembly includes a connector and a connector positioning piece, the connector positioning piece is installed on the fuselage skin, the connector is installed on the connector positioning piece, and the connector is electrically connected to the detection element through a connecting piece.

[0010] As one of the methods, in the above-mentioned aircraft fuselage containing a detection element, the connecting piece is a conductive silver paste, which is coated on the surface of the fuselage skin and electrically connects the detection element and the connector.

[0011] In the above-mentioned aircraft fuselage containing the detection element, the detection element is arranged on the surface of the fuselage skin and is electrically connected to the connector through conductive silver paste.

[0012] In the above-mentioned aircraft fuselage containing a detection element, a structural adhesive layer is provided between the detection element and the fuselage skin surface, and the detection element is bonded to the fuselage skin surface via the structural adhesive layer.

[0013] As another embodiment, in the above-mentioned aircraft fuselage containing the detection element, a skeleton layer is integrally formed on the fuselage skin, and mounting grooves corresponding to the detection elements are arranged on the skeleton layer, and the detection elements are installed in the mounting grooves.

[0014] In the above-mentioned aircraft fuselage containing detection elements, the connecting parts are conductive silver paste and metal guide wire, the metal guide wire is embedded in the fuselage skin, and the conductive silver paste is coated on the surface of the skeleton layer. The detection element is electrically connected to the conductive silver paste, the conductive silver paste is electrically connected to one end of the metal guide wire, and the other end of the metal guide wire is electrically connected to the connector.

[0015] In the above-mentioned aircraft fuselage containing the detection element, the hole of the installation slot is a through hole, and the detection element is installed in the installation slot and fits with the surface of the fuselage skin.

[0016] In the above-mentioned aircraft fuselage containing a detection element, 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.

[0017] In the above-mentioned aircraft fuselage containing a detection element, a structural adhesive layer is provided 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.

[0018] Compared with the existing technology, the advantages of the present invention are that the connector can connect multiple detection elements, the control unit is reduced, the analysis is convenient, the disassembly and assembly plan can be disassembled and assembled at any time according to needs, the positioning accuracy is higher, the cost is low, the efficiency is high, it has mass production, and there is technical accumulation. The skeleton layer is formed by the mold and the mounting groove is used for positioning. The detection element position accuracy 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

[0019] Figure 1 This is a schematic diagram of one of the structural methods of an aircraft fuselage containing a detection element;

[0020] Figure 2 This is another structural diagram of an aircraft fuselage containing detection components.

[0021] Figure 3 This is a schematic diagram of the overall structure of the aircraft skin detection element implantation;

[0022] Figure 4 yes Figure 3 AA structural diagram;

[0023] Figure 5 yes Figure 3 Schematic diagram of another structural approach of AA. DETAILED DESCRIPTION

[0024] 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.

[0025] In the figure, the fuselage skin 100; the detection element 200; the skeleton layer 300; the mounting groove 400; the notch 401; the structural adhesive layer 500; the connector 600; the connector positioning member 700; the conductive silver paste 800; and the metal guide wire 900.

[0026] Example 1

[0027] like Figure 1 、 Figure 3 、 Figure 4 As shown, the aircraft fuselage containing the detection element mainly includes a fuselage skin 100, a detection element 200, a connector assembly and a connector. 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 is ≥0.4mm. The detection element 200 is used to detect the strain generated during the force application process. The biggest innovation of this patent 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, which is optimized to 2mm in this embodiment.

[0028] In order to facilitate the installation of the entire detection element 200, a plurality of installation grooves 400 corresponding to the detection element 200 are arranged on the skeleton layer 300. The holes of the installation grooves 400 are through holes. The detection element 200 is installed in the installation grooves 400 and fits with the surface of the fuselage skin 100. Here, 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 during installation. The main function of the installation groove 400 here 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 using the installation groove 400 can ensure the position accuracy of the detection element 200 and the positioning efficiency is high, in order to ensure the reliability of the positioning of the detection element 200.

[0029] 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. The thickness of the structural adhesive layer 500 here is 0.1mm-0.5mm, and is specifically optimized to 0.3mm in this embodiment. The structural adhesive layer 500 here mainly plays a role in bonding and positioning, and also facilitates the subsequent installation and connection of electronic components such as the conductive silver paste 800 and the detection element 200.

[0030] The plug-in assembly is arranged on the fuselage skin 100 for connecting the plug-in control unit; the plug-in assembly includes a connector 600 and a plug-in positioning member 700, wherein the plug-in positioning member 700 is mainly used to ensure the insertion position of the connector 600, the connector 600 is used to transmit strain information, the plug-in positioning member 700 is installed on the fuselage skin 100, the connector 600 is installed on the plug-in positioning member 700, the connector 600 is electrically connected to the detection element 200 through the connector, the connector is arranged on the fuselage skin 100 and is used to electrically connect the detection element 200 and the plug-in assembly, specifically, here in this embodiment the connector is a guide Conductive silver paste 800 and metal guide wire 900, the metal guide wire 900 is embedded in the fuselage skin 100, the conductive silver paste 800 is coated on the surface of the skeleton layer 300, the detection element 200 is electrically connected to the conductive silver paste 800, the conductive silver paste 800 is electrically connected to one end of the metal guide wire 900, and the other end of the metal guide wire 900 is electrically connected to the connector 600, so that the entire detection element 200 can be electrically connected to the connector 600, and the connector 600 can connect multiple detection elements 200, reducing the number of control units and facilitating analysis, and because of the connector positioning piece 700, it is easy to disassemble and assemble, and can be disassembled and assembled at any time according to needs.

[0031] Example 2

[0032] like Figure 5As shown, most of the structures of this embodiment are the same as those of embodiment 1, except that the installation method of the detection element 200 is different. Here, a skeleton layer 300 is integrally formed on the fuselage skin 100, and a mounting groove 400 corresponding to the detection element 200 is arranged on the skeleton layer 300. The detection element 200 is installed in the mounting groove 400, wherein a structural adhesive layer 500 is provided between the detection element 200 and the bottom surface of the mounting groove 400. After the detection element 200 is placed in the mounting groove 400, its inner surface is bonded to the bottom surface of the mounting groove 400 through the structural adhesive layer 500. That is to say, the detection element 200 is not directly attached to the surface of the fuselage skin 100, but is attached to the mounting groove 400, and the stress is transferred to the mounting groove 400 through the fuselage skin 100 for detection.

[0033] When the above-mentioned Examples 1 and 2 are manufactured as a whole, the composite carbon fiber 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 the metal guide wire 900 is embedded therein. Then, glue is dispensed in the installation groove 400 to form a structural adhesive layer 500, and then the detection element 200 is bonded to the installation groove 400 through the structural adhesive layer 500 (one is bonded to the surface of the fuselage skin 100, and the other is bonded to the bottom surface of the installation groove 400), and then the conductive silver paste 800 is applied to electrically connect the metal guide wire 900, and then the connector positioning member 700 and the connector 600 are installed to electrically connect the metal guide wire 900 and the connector 600.

[0034] Example 3

[0035] like Figure 2As shown, the aircraft fuselage containing the detection element 200 mainly includes a fuselage skin 100, a detection element 200, a connector assembly and a connector. 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 as a whole. The thickness of the fuselage skin 100 can be 1mm-2mm, which is optimized to 1.5mm in this embodiment. The detection element 200 is used to detect the strain generated during the force application process. Here, the connector assembly includes a connector 600 and a connector positioning member 700. The connector positioning member 700 is installed on the fuselage skin 100, and the connector 600 is installed on the connector positioning member 700. The connector 600 is electrically connected to the detection element 200 through a connector. The connector is a conductive silver paste 800. The conductive silver paste 800 is coated Distributed on the surface of the fuselage skin 100, the conductive silver paste 800 electrically connects the detection element 200 and the connector 600. The detection element 200 is arranged on the surface of the fuselage skin 100 and is electrically connected to the connector 600 through the conductive silver paste 800. There is also a structural adhesive layer 500 between the detection element 200 and the surface of the fuselage skin 100. The detection element 200 is bonded to the surface of the fuselage skin 100 through the structural adhesive layer 500. The thickness of the structural adhesive layer 500 here is 0.1mm-0.5mm, which is specifically optimized to 0.3mm in this embodiment. The scheme of this embodiment is a skeleton-free scheme. The detection element 200, the connector assembly and the connector are directly installed on the fuselage skin 100, so that the connector 600 can connect multiple detection elements 200, the control unit is reduced, and analysis is facilitated. The disassembly and assembly scheme can be disassembled and assembled at any time as needed, and the positioning accuracy is higher.

[0036] 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 containing a detection element, characterized in that: include: fuselage skin; Detection element, used to detect the strain generated during the force application process; A connector assembly is arranged on the fuselage skin and is used to connect the connector control unit; Connectors are arranged on the fuselage skin and are used to electrically connect detection elements and connector components.

2. The aircraft fuselage containing a detection element according to claim 1, characterized in that: The connector assembly includes a connector and a connector positioning piece. The connector positioning piece is installed on the fuselage skin, the connector is installed on the connector positioning piece, and the connector is electrically connected to the detection element through a connecting piece.

3. The aircraft fuselage containing a detection element according to claim 1, characterized in that: The connecting piece is conductive silver paste, which is coated on the surface of the fuselage skin and electrically connects the detection element and the connector.

4. The aircraft fuselage containing a detection element according to claim 3, characterized in that: The detection element is arranged on the surface of the fuselage skin and is electrically connected to the connector through conductive silver paste.

5. The aircraft fuselage containing a detection element according to claim 4, characterized in that: There is also a structural adhesive layer between the detection element and the fuselage skin surface, and the detection element is bonded to the fuselage skin surface through the structural adhesive layer.

6. The aircraft fuselage containing a detection element according to claim 2, characterized in that: A skeleton layer is integrally formed on the fuselage skin, and mounting grooves corresponding to the detection elements are arranged on the skeleton layer, and the detection elements are installed in the mounting grooves.

7. The aircraft fuselage containing a detection element according to claim 6, characterized in that: The connecting parts are conductive silver paste and metal guide wire. The metal guide wire is embedded in the fuselage skin, and the conductive silver paste is coated on the surface of the skeleton layer. The detection element is electrically connected to the conductive silver paste, and the conductive silver paste is electrically connected to one end of the metal guide wire. The other end of the metal guide wire is electrically connected to the connector.

8. The aircraft fuselage containing a detection element according to claim 6, characterized in that: The hole of the installation slot is a through hole, and the detection element is installed in the installation slot and fits with the surface of the fuselage skin.

9. The aircraft fuselage containing a detection element according to claim 6, 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.

10. The aircraft fuselage containing a detection element according to claim 6, 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.

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