Composite material leading edge structure of unmanned aerial vehicle and manufacturing method of composite material leading edge structure

Abstract

The invention relates to the technical field of unmanned aerial vehicle structure design, and discloses an unmanned aerial vehicle composite material leading edge structure and a manufacturing method thereof, and the unmanned aerial vehicle composite material leading edge structure comprises a front beam, a partition plate, a core material and a leading edge skin. The partition plate, the core material, the front beam and the front edge skin are fixed together through secondary glue joint to form the composite airfoil front edge. All-composite material parts are adopted and formed through a composite material secondary cementing process, and the structure has the advantages of being excellent in bird impact resistance, simple in structure, light in weight, easy to assemble, short in manufacturing period, low in cost and the like.

Description

Technical Field

[0001] The present invention belongs to the technical field of unmanned aerial vehicle (UAV) structural design, and in particular relates to a composite leading edge structure of an unmanned aerial vehicle (UAV) and a manufacturing method thereof. Background Art

[0002] With the continuous progress of science and technology, UAVs have become an important technological innovation in modern design. The development of UAVs is not only widely used in the military field, but also shows great potential in the civilian field. At the same time, due to the characteristics of composite materials such as light weight, high specific strength, high specific modulus, and good designability, the body structure of UAVs now mostly adopts composite materials.

[0003] The leading edge of the drone wing is in the aerodynamic leading edge area, which requires not only good aerodynamic characteristics but also good bird strike resistance. The leading edge structure of civil aircraft wings mostly adopts the "composite honeycomb sandwich wall panel + dense partition" structure, which uses composite honeycomb sandwich wall panels to improve the strength and rigidity of the leading edge structure in order to meet the requirements of aerodynamic characteristics and bird strike resistance. Among them, small and medium-sized civil aircraft mostly use Figure 4 (a) Leading edge panel structure, mostly used in large and medium-sized civil aircraft Figure 4 (b) Leading edge panel structure: These two types of leading edge panel structures mainly have a higher leading edge cabin space height and a longer chord length. The leading edge panel can adopt a composite material honeycomb sandwich panel structure, which has the characteristics of light weight, simple structure, good processability and low cost.

[0004] However, due to the small size of the front edge section (height and chord length) of the UAV wing, the space inside the front edge cabin is small. If the front edge wall panel is made of composite honeycomb sandwich wall panel, the manufacturing process is poor, and the wall panel has internal quality problems such as delamination and gaps. Therefore, it is not suitable to use composite honeycomb sandwich wall panel structure for the front edge wall panel. In addition, the front edge cabin is limited by the small internal space, making it impossible to arrange reinforced longitudinal beams in the front edge cabin to meet the anti-bird strike design.

[0005] The technical problem that urgently needs to be solved now is to design a simple, reasonable, lightweight UAV composite leading edge structure and its manufacturing method, which can meet the aerodynamic characteristics of the leading edge area and the aerodynamic outer edge tolerance requirements; at the same time, it can meet the bird strike resistance design requirements. Summary of the invention

[0006] In view of the problems of the background technology, the present invention proposes a simple, reasonable, lightweight UAV composite leading edge structure and a manufacturing method thereof, which can meet the aerodynamic characteristics of the leading edge area and the aerodynamic outer edge tolerance requirements; at the same time, it can also meet the anti-bird strike design requirements.

[0007] The technical solution of the present invention is achieved in this way:

[0008] A composite leading edge structure of an unmanned aerial vehicle, comprising:

[0009] front beam;

[0010] Core material, designed according to aerodynamic shape;

[0011] A partition plate adapted to the end surface of the core material;

[0012] A leading edge skin adapted to the curved surface of the core material;

[0013] The core material is wrapped on the front beam through the leading edge skin, and the two ends are encapsulated by the partition. The leading edge skin and the core material, the partition and the core material, the front beam and the core material, and the front beam and the leading edge skin are all fixed by secondary bonding with adhesive film.

[0014] As a further solution of the present invention: the front beam is designed to be an I-shaped beam, which has a bottom plate and a baffle, and a recessed area adapted to the baffle is provided on the curved surface of the core material.

[0015] As a further solution of the present invention: the core material includes a curved surface, a bottom surface, two end surfaces and a recessed area, and the adhesive film can be a whole or can be arranged in blocks according to the surface shape of the core material.

[0016] As a further solution of the present invention: the core material can be any one of a honeycomb core and a foam core, and the core material is a full-height core material.

[0017] As a further solution of the present invention: the front beam, the partition and the leading edge skin are all made of composite material carbon fiber fabric or glass fiber fabric or a mixture of carbon fiber fabric and glass fiber fabric.

[0018] As a further solution of the present invention: after the secondary bonding of the leading edge skin, the front beam and the partition is completed, it is fixed to the enclosure of the front beam by rivets.

[0019] A method for manufacturing a composite leading edge structure of an unmanned aerial vehicle comprises the following steps:

[0020] Prepare core materials and prepregs, and use prepregs to prepare front beams, bulkheads and leading edge skins;

[0021] The partition, the core material, the front beam and the front edge skin are fixed together by secondary bonding with adhesive film to obtain the front edge blank;

[0022] The leading edge blank is profiled and fixed with rivets;

[0023] Nondestructive testing was performed to obtain the composite leading edge parts of the UAV.

[0024] A method for manufacturing a composite leading edge structure of an unmanned aerial vehicle comprises the following steps:

[0025] Prepare prepreg and lay it on the mold to form the bottom surface;

[0026] Apply glue on the bottom surface, place the core material, and then apply glue on the surface of the core material;

[0027] Use prepreg to lay the surface on the glue-coated core material. After the operation is completed, it is formed according to the composite material manufacturing process to obtain the leading edge part of the UAV composite material.

[0028] The beneficial effects of this application are:

[0029] 1. This application adopts all-composite parts formed by composite secondary bonding process. This structure not only has excellent bird strike resistance, but also has the characteristics of simple structure, light weight, simple assembly, short manufacturing cycle and low cost.

[0030] 2. This application can meet the aerodynamic characteristics of the leading edge area and the aerodynamic outer edge tolerance requirements.

[0031] The present application is further described in detail below in conjunction with the accompanying drawings of the embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 A schematic diagram of the composite leading edge structure of a UAV and a manufacturing method thereof according to the present invention;

[0033] Figure 2 It is a schematic diagram of the bonding relationship of the leading edge structure of the present invention;

[0034] Figure 3 It is a schematic diagram of riveting the end of the adhesively bonded rear beam edge strip of the present invention;

[0035] Figure 4 This is a schematic diagram of the composite wing leading edge panel structure of a civil aircraft;

[0036] Figure 5 The present invention is a schematic diagram of the process of manufacturing the leading edge structure of a composite material of an unmanned aerial vehicle.

[0037] The reference numerals in the drawings are: 1 front beam, 2 left end partition, 3 right end partition, 4 core material, 5 leading edge skin, 6 adhesive film, 7 rivet. DETAILED DESCRIPTION

[0038] The technical solution of the present application will be described clearly and completely below in conjunction with the accompanying drawings of the embodiments.

[0039] Figures 1 to 5 It is a schematic diagram for illustrating an embodiment of the composite leading edge structure of a UAV and a method for manufacturing the same according to the present invention.

[0040] First, see Figure 1-3The present invention provides a composite leading edge structure of a drone, which includes: a front beam 1, a left end baffle 2, a right end baffle 3, a core material 4 and a leading edge skin 5. The left end baffle 2, the right end baffle 3, the core material 4, the front beam 1 and the leading edge skin 5 are fixed together by secondary bonding to form a composite wing leading edge. The specific structure is as follows:

[0041] The front beam 1 is designed to be an I-shape, and has a bottom plate and a surround. The curved surface of the core material 4 is provided with a recessed area matched with the surround.

[0042] The core material 4 is designed according to the aerodynamic shape; the core material 4 includes a curved surface, a bottom surface, two end surfaces and a concave area, and the adhesive film 6 can be a whole or divided into blocks according to the surface shape of the core material 4. The core material 4 can be any one of a honeycomb core and a foam core, and the core material 4 is a full-height core material 4.

[0043] The partition is adapted to the end surface of the core material 4; it includes a left end partition 2 and a right end partition 3

[0044] The leading edge skin 5 is adapted to the curved surface of the core material 4; the front beam 1, the partition and the leading edge skin 5 are all made of composite material carbon fiber fabric or glass fiber fabric or a mixture of carbon fiber fabric and glass fiber fabric.

[0045] The core material 4 is wrapped on the front beam 1 through the leading edge skin 5, and the two ends are encapsulated by the partition. The leading edge skin 5 and the core material 4, the partition and the core material 4, the front beam 1 and the core material 4, and the front beam 1 and the leading edge skin 5 are all fixed by secondary bonding through the adhesive film 6.

[0046] Furthermore, after the secondary bonding of the leading edge skin 5 to the front beam 1 and the partition is completed, it is fixed to the enclosure of the front beam 1 by rivets 7.

[0047] The composite leading edge structure of the UAV is made of all-composite parts formed using a composite secondary bonding process. This structure not only has excellent bird strike resistance, but also has the characteristics of simple structure, light weight, simple assembly, short manufacturing cycle and low cost.

[0048] Second, see Figure 5 The present invention provides a method for manufacturing a composite leading edge structure of an unmanned aerial vehicle, which comprises the following steps:

[0049] Prepare core material 4 and prepreg, and use the prepreg to prepare front beam 1, partition and leading edge skin 5;

[0050] The partition, the core material 4, the front beam 1 and the leading edge skin 5 are fixed together by secondary bonding with the adhesive film 6 to obtain the leading edge blank;

[0051] The front edge blank is profiled and fixed with rivets 7;

[0052] Nondestructive testing was performed to obtain the composite leading edge parts of the UAV.

[0053] Specifically, first prepare composite parts such as the front beam 1, the left end partition 2, the right end partition 3, the core material 4, and the leading edge skin 5; then glue the above parts together for a second time through a film 6; then process the leading edge structure contour according to the contour size requirements of the leading edge structure drawing, and connect and fix the leading edge skin 5, the edge strip of the front beam 1, and the edge strips of the left and right end partitions 3 at the two ends of the front beam 1 through high-locking bolts or rivets 7; finally, perform non-destructive testing on the leading edge structure, and if the test is qualified, the manufacturing of a composite leading edge structure of an unmanned aerial vehicle is completed.

[0054] Thirdly, the following method can also be used to prepare the leading edge structure of the composite material of the UAV, and the specific steps are as follows:

[0055] Prepare prepreg and lay it on the mold to form the bottom surface (front beam 1);

[0056] Apply glue on the bottom surface, place the core material 4, and then apply glue on the surface of the core material 4;

[0057] Use prepreg to lay the surface (partition, leading edge skin 5) on the glue-coated core material 4, and after the operation is completed, form it according to the composite material manufacturing process to obtain the composite leading edge part of the drone.

[0058] So far, the purpose of the present invention has been achieved.

[0059] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A composite leading edge structure for an unmanned aerial vehicle, characterized in that: include: front beam; Core material, designed according to aerodynamic shape; A partition plate adapted to the end surface of the core material; A leading edge skin adapted to the curved surface of the core material; The core material is wrapped on the front beam through the leading edge skin, and the two ends are encapsulated by the partition. The leading edge skin and the core material, the partition and the core material, the front beam and the core material, and the front beam and the leading edge skin are all fixed by secondary bonding with adhesive film.

2. The composite leading edge structure of the unmanned aerial vehicle according to claim 1, characterized in that: The front beam is designed to be an I-shape, and has a bottom plate and a baffle. A recessed area matched with the baffle is provided on the curved surface of the core material.

3. The composite leading edge structure of a drone according to claim 2, characterized in that: The core material comprises a curved surface, a bottom surface, two end surfaces and a concave area, and the adhesive film can be a whole or can be arranged in blocks according to the surface shape of the core material.

4. The composite leading edge structure of a drone according to claim 3, characterized in that: The core material may be any one of a honeycomb core and a foam core, and the core material is a full-height core material.

5. The composite leading edge structure of a drone according to claim 4, characterized in that: The front beam, the partition and the leading edge skin are all made of composite material carbon fiber fabric or glass fiber fabric or a mixture of carbon fiber fabric and glass fiber fabric.

6. The composite leading edge structure of a drone according to any one of claims 2 to 5, characterized in that: After the secondary bonding of the leading edge skin, the front beam and the partition is completed, it is fixed on the enclosure of the front beam by rivets.

7. A method for manufacturing a composite leading edge structure of an unmanned aerial vehicle, characterized in that: The following steps are involved: Prepare core materials and prepregs, and use prepregs to prepare front beams, bulkheads and leading edge skins; The partition, the core material, the front beam and the front edge skin are fixed together by secondary bonding with adhesive film to obtain the front edge blank; The leading edge blank is profiled and fixed with rivets; Nondestructive testing was performed to obtain the composite leading edge parts of the UAV.

8. A method for manufacturing a composite leading edge structure of an unmanned aerial vehicle, characterized in that: The following steps are involved: Prepare prepreg and lay it on the mold to form the bottom surface; Apply glue on the bottom surface, place the core material, and then apply glue on the surface of the core material; Use prepreg to lay the surface on the glue-coated core material. After the operation is completed, it is formed according to the composite material manufacturing process to obtain the leading edge part of the UAV composite material.

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