Composite cap-shaped stringer integral wall plate for nacelle of unmanned aerial vehicle and preparation method thereof

Abstract

The invention relates to the technical field of aircraft design, and discloses an unmanned aerial vehicle nacelle composite cap-shaped stringer integral panel and a preparation method thereof, and the unmanned aerial vehicle nacelle composite cap-shaped stringer integral panel is located at the rear section of an unmanned aerial vehicle nacelle and is of an integral panel structure form. The wallboards are made of carbon fiber fabrics, the stringers are made of rigid foam cores, and the wallboards are divided into inner skins and outer skins at the stringers; the method comprises the following steps: paving an outer skin on a mold, and paving an inner skin by taking a stringer as a mold tire after the stringer is fixed on the outer skin; after the inner skin is paved, the periphery of the stringer is connected with the skin to form a closed section; and crack stopping nails are mounted near the ends of the stringers for structural reinforcement. The integral composite wallboard is continuous in structure, free of connection hard points and excellent in load transfer performance and fatigue resistance.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft design, and specifically relates to a composite hat-shaped long-string integral wall panel of an unmanned aerial vehicle nacelle and a preparation method thereof. Background Art

[0002] At present, the use of drones for cargo transportation is a new logistics model. Compared with traditional logistics transportation methods such as vehicles, drone transportation can quickly and accurately transport goods to the destination without human intervention, saving costs and time, especially in areas with poor road traffic. Most drones on the market now have a small load capacity, and the number of goods delivered each time is limited. Multiple round trips are required to pick up the goods, which greatly increases the delivery cost. When performing heavy-load, medium- and long-distance feeder transportation, light weight, large capacity, and low cost are the key design factors that need to be considered in the design of cargo drones.

[0003] The structural weight of drones directly affects the economic benefits of freight transportation. In order to reduce weight and reduce costs, large-tonnage cargo drones must consider the weight of the body structure, which accounts for a relatively large proportion of the empty aircraft. Currently, large-tonnage cargo drones are mostly manned aircraft, with the "three more" characteristics of a large number of parts, many connectors, and many standard parts, which greatly affects the application prospects of cargo drones. The nacelle structure used to install important power equipment such as engines has the characteristics of small size, complex appearance, and large load-bearing capacity. Therefore, it is hoped to design a nacelle structure that is light in weight, simple in structure, and meets both low-cost requirements and maximum structural efficiency. Summary of the invention

[0004] In view of the problems of the background technology, the present invention proposes a UAV nacelle wall panel structure which is light in weight, simple in structure, excellent in performance and can meet the low cost requirement.

[0005] The technical solution of the present invention is achieved in this way:

[0006] A composite hat-shaped long-string integral wall panel of a drone nacelle adopts a U-shaped structure design, which includes:

[0007] Laminated structural skin, made of multiple layers of carbon fiber fabric stacked and bent into a U shape;

[0008] Hat-shaped long spars are evenly arranged on the concave surface of the laminated structure skin and fixed with crack-stop nails.

[0009] As a further solution of the present invention: the hat-shaped long stringer is arranged on the laminated structure skin along the heading direction.

[0010] As a further solution of the present invention: the hat-shaped long girder adopts a rigid foam core, and the wall panel is divided into an outer skin and an inner skin with the rigid foam core as the boundary. The inner skin is first laid on the mold, and after the inner skin is fixed, the outer skin is laid with the rigid foam core as the mold shape; after the outer skin is laid, it is connected to the skin around the rigid foam core to form a closed section.

[0011] As a further solution of the present invention: the rigid foam core is wrapped by an adhesive.

[0012] As a further solution of the present invention: composite material twists are placed in the fillet area of ​​the rigid foam core wrapped by the adhesive to fill and compact it.

[0013] As a further solution of the present invention: the composite material twist is formed by manually rolling or machine rolling the composite material prepreg.

[0014] As a further solution of the present invention: the rigid foam core is designed as a trapezoidal structure.

[0015] A method for preparing a composite hat-shaped long-string integral wall panel of an unmanned aerial vehicle nacelle, comprising the following steps:

[0016] Prepare prepreg and lay the bottom surface on the mold;

[0017] Apply glue on the bottom surface, place a rigid foam core at intervals, and then apply glue on the surface of the rigid foam core;

[0018] Prepreg is used to lay the surface on the rigid foam core after glue coating. After the operation is completed, it is formed according to the composite material manufacturing process to obtain the integral wall panel of the UAV cap-shaped long truss.

[0019] The beneficial effects of this application are:

[0020] 1. The overall wall panel structure of the composite material is continuous, without any connection hard points, and has excellent load-transmitting performance and fatigue resistance.

[0021] 2. The hat-shaped long girder has good designability and can realize wall panel mechanisms with different curved surfaces.

[0022] 3. The wall panel adopts a hat-shaped long-string integral wall panel design. The smooth curved surface reduces the sharp structure of the internal space, which is beneficial to the passage of equipment such as cables and pipelines, and does not affect the aerodynamic performance of the aircraft.

[0023] 4. The periphery of the long stringer is connected with the skin to form a closed section, forming an overall axial compression closed structure with high compressive stability.

[0024] 5. The hat-shaped long stringer and the skin are integrally formed with the reinforced wall panels, which reduces the number of parts, connectors, and standard parts, and reduces the structural weight.

[0025] The present application is further described in detail below in conjunction with the accompanying drawings of the embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 This is a schematic diagram of the structural position of the nacelle of the UAV of the present invention;

[0027] Figure 2 It is a schematic diagram of the structure of the composite material hat-shaped long girder integral wall panel of the present invention;

[0028] Figure 3 It is a schematic diagram of the cross-sectional structure of the composite material hat-shaped long girder integral wall panel structure of the present invention.

[0029] The accompanying drawings are marked as: 1 nacelle front section, 2 nacelle middle section, 3 nacelle rear section, 4 tail support, 5 laminated structural skin, 6 hat-type long spars, 7 crack arrest nails, 8 rigid foam core, 9 adhesive, 10 composite material twister, 11 outer skin composite material prepreg, 12 inner skin composite material prepreg. DETAILED DESCRIPTION

[0030] The technical solution of the present application will be described clearly and completely below in conjunction with the accompanying drawings of the embodiments.

[0031] In a first aspect, the present invention provides a composite hat-shaped long-string integral wall panel of an unmanned aerial vehicle nacelle, which adopts a U-shaped structural design.

[0032] Figures 1 to 3 It is a schematic diagram for illustrating an embodiment of the composite hat-shaped long-string integral wall panel of the UAV nacelle of the present invention.

[0033] Referring to the attached drawings, the composite hat-shaped long-string integral wall panel structure 3 of the drone of the present application is located behind the middle section 2 of the drone nacelle and in front of the tail support 4, as shown in FIG. Figure 1 The composite hat-shaped long stringer integral wall plate structure of the unmanned aerial vehicle of the present application comprises a laminated structure skin 5, a hat-shaped long stringer 6 and a crack stop nail 7, as shown in FIG. Figure 2 shown.

[0034] The composite hat-shaped long stringer integral wall panel structure is divided into an outer skin and an inner skin by a rigid foam core long stringer 8; after laying the inner skin composite material prepreg 12 on the mold, the rigid foam core 8 wrapped by the adhesive 9 is placed on the inner skin composite material prepreg 12 and positioned, and the composite material twister 10 is placed in the fillet area of ​​the rigid foam core 8 wrapped by the adhesive 9 to fill and compact it, and then the outer skin composite material prepreg 11 is laid, such as Figure 3 shown.

[0035] The rigid foam core 8 is formed by machining and is wrapped with an adhesive 9; the composite material twister 10 is manually rolled or machine rolled with composite material prepreg.

[0036] After the operation is completed, the composite material is molded according to the manufacturing process, and after molding, the crack stop nails 7 are installed near the end of the long stringer to strengthen the structure.

[0037] In a second aspect, the present invention provides a method for preparing a composite hat-shaped long-string integral wall panel of a nacelle of an unmanned aerial vehicle, which comprises the following steps:

[0038] Prepare prepreg and lay the bottom surface on the mold;

[0039] Apply glue on the bottom surface, place a rigid foam core at intervals, and then apply glue on the surface of the rigid foam core;

[0040] Prepreg is used to lay the surface on the rigid foam core after glue coating. After the operation is completed, it is formed according to the composite material manufacturing process to obtain the integral wall panel of the UAV cap-shaped long truss.

[0041] So far, the purpose of the present invention has been achieved.

[0042] 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 hat-shaped long-string integral wall panel for a drone nacelle, characterized in that: Adopt U-shaped structure design, including: Laminated structural skin, made of multiple layers of carbon fiber fabric stacked and bent into a U shape; Hat-shaped long spars are evenly arranged on the concave surface of the laminated structure skin and fixed with crack-stop nails.

2. The composite hat-shaped long-string integral wall panel of the UAV nacelle according to claim 1 is characterized in that: The hat-shaped long stringer is arranged on the laminated structural skin along the heading direction.

3. The composite hat-shaped long-string integral wall panel of the UAV nacelle according to claim 1 or 2, characterized in that: The hat-shaped long girder uses a rigid foam core, and the wall panel is divided into an outer skin and an inner skin with the rigid foam core as the boundary. The inner skin is first laid on the mold, and after the inner skin is fixed, the outer skin is laid with the rigid foam core as the mold shape; after the outer skin is laid, it is connected to the skin around the rigid foam core to form a closed section.

4. The composite hat-shaped long stringer integral wall panel of the UAV nacelle according to claim 3 is characterized in that: The rigid foam core is wrapped with an adhesive.

5. The composite hat-shaped long stringer integral wall panel of the UAV nacelle according to claim 4 is characterized in that: Composite twists are placed in the fillet area of ​​the rigid foam core wrapped by the adhesive and compacted.

6. The composite hat-shaped long stringer integral wall panel of the UAV nacelle according to claim 5 is characterized in that: The composite material twist is formed by manually rolling or machine rolling the composite material prepreg.

7. The composite hat-shaped long stringer integral wall panel of the UAV nacelle according to any one of claims 1 to 6, characterized in that: The rigid foam core is designed as a trapezoidal structure.

8. A method for preparing a composite hat-shaped long-string integral wall panel for a drone nacelle, characterized in that: The steps include: Prepare prepreg and lay the bottom surface on the mold; Apply glue on the bottom surface, place a rigid foam core at intervals, and then apply glue on the surface of the rigid foam core; Prepreg is used to lay the surface on the rigid foam core after glue coating. After the operation is completed, it is formed according to the composite material manufacturing process to obtain the integral wall panel of the UAV cap-shaped long truss.

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