Integrated composite unmanned aerial vehicle engine mounting structure

Abstract

The utility model discloses an integrated composite unmanned aerial vehicle engine mounting structure, including integrated composite fuselage, the end surface of composite fuselage is as the mounting surface of engine, be equipped with L type corner piece and composite material corner box on the mounting surface, L type corner piece is used for the installation of tail cover, and composite material corner box is used for the installation of engine, and composite material corner box is connected with engine through connecting component. The utility model discloses integrated composite fuselage, has omitted the assembly process of skin and frame and skin, has improved production efficiency, has reduced the amount of fastener and structural glue simultaneously, can reduce weight properly, the design of composite material corner box not only has reduced structural weight, but also can solve the assembly problem, and the corner box bearing capacity is better, and the installation place can be locally thickened, and the design is better, and the cost is not high, and the design of L type corner piece is easier to manufacture, and the cost is lower than the machining piece, and the production cost is reduced.

Description

Technical Field

[0001] This utility model relates to the structural design of unmanned aerial vehicles (UAVs), and in particular to an integrated composite material UAV engine mounting structure. Background Technology

[0002] The key to drone production is low cost and rapid assembly, and how to reduce the amount of assembly is a problem. By using composite material fuselage for integrated molding, drones can reduce the need for skin molding and the connection assembly between the frame and skin, which can reduce assembly time, improve production efficiency, reduce the amount of structural adhesive and fasteners used, and thus achieve appropriate weight reduction.

[0003] Most drone engines are mounted on the rear fuselage, which happens to be the section where the fuselage cross-section tapers. When the engine mounting structure is located in this taper section, it becomes difficult to install using a unibody fuselage and a single-piece machined engine frame. Forcing the frame into the fuselage will scrape off the structural adhesive, resulting in insufficient adhesive and compromised bonding quality. Modifying the frame's shape to fit the fuselage segments requires applying structural adhesive of varying thicknesses, which also makes it difficult to guarantee bonding quality.

[0004] Therefore, it is necessary to design an integrated composite material UAV engine mounting structure to solve the above problems. Utility Model Content

[0005] The purpose of this invention is to address the shortcomings of existing technologies by proposing an integrated composite material unmanned aerial vehicle (UAV) engine mounting structure.

[0006] The technical solution of this utility model is: an integrated composite material unmanned aerial vehicle (UAV) engine mounting structure, comprising an integrally molded composite material fuselage; the end face of the composite material fuselage serves as the engine mounting surface; the mounting surface is provided with an L-shaped corner piece and a composite material corner box; the L-shaped corner piece is used for mounting the tail cover; the composite material corner box is used for mounting the engine; the composite material corner box and the engine are connected by a connecting component.

[0007] The composite material body is integrally formed by a combination of a heat-shrinkable core mold and a metal outer mold.

[0008] The composite material corner boxes are four in number, and are distributed at the four corners of the mounting surface.

[0009] The connecting assembly includes a bolt, a nut, a custom bushing, and a bushing nut; the custom bushing is installed in the bolt hole connecting the composite corner box and the engine; the bushing nut is threaded to the end of the custom bushing; the bolt extends from inside the tail cover through the engine mounting component and through the custom bushing into the composite corner box, and the nut is threaded to the end of the bolt extending into the composite corner box and abuts against the bushing nut.

[0010] The bushing nut has a hexagonal shoulder.

[0011] The composite material corner box has a thickened area at the connection with the engine.

[0012] The above-mentioned technical solution has the following beneficial effects: (1) The present invention adopts an integrated molded composite material body, which eliminates the skin mold closing and frame and skin assembly process, improves production efficiency, and at the same time reduces the amount of fasteners and structural adhesive, which can appropriately reduce weight; the design of composite material corner box not only reduces structural weight, but also solves assembly problems. At the same time, the corner box has good load-bearing capacity, the installation point can be locally thickened, the design is good, and the cost is not high. The design of L-shaped corner piece is easier to manufacture, and the cost is much lower than that of machined parts, thus reducing production costs.

[0013] (2) The connection component of this utility model adopts the combination of bolts, custom bushings and nuts, which is friendly to composite material structure and can solve the problem of difficult bolt disassembly. Attached Figure Description

[0014] To make the contents of this utility model easier to understand, the present utility model will be further described in detail below with reference to specific embodiments and accompanying drawings.

[0015] Figure 1 This is a schematic diagram of the structure of this utility model.

[0016] Figure 2 This is a schematic diagram of the installation of the composite material corner box of this utility model.

[0017] Figure 3 This is a schematic diagram of the bushing nut of this utility model.

[0018] The labels in the attached diagram are:

[0019] Composite material body 1, L-shaped corner piece 2, composite material corner box 3, connecting assembly 4, bolt 4-1, nut 4-2, custom bushing 4-3, bushing nut 4-4, hexagonal shoulder 4-5, thickened area 5. Detailed Implementation

[0020] (Example 1)

[0021] See Figures 1 to 3This embodiment discloses an integrated composite material UAV engine mounting structure, comprising an integrally molded composite material fuselage 1; the end face of the composite material fuselage 1 serves as the engine mounting surface; the mounting surface is provided with an L-shaped corner piece 2 and a composite material corner box 3; the L-shaped corner piece 2 is used for mounting the tail cover; the composite material corner box 3 is used for mounting the engine; the composite material corner box 3 is connected to the engine via a connecting component 4. The mold for manufacturing the fuselage has zero rounded corners because if the mold has large rounded corners, there will be a large gap between the fuselage and the tail cover. If the zero-rounded corner of the mold is further thickened, it will not be able to be compacted, easily leading to defects, and it will also not be able to withstand bending moments well. Therefore, a composite material corner box 3 is added at this location.

[0022] Furthermore, the composite material body 1 is integrally formed by a combination mold of a heat-shrinkable core mold and a metal outer mold.

[0023] Furthermore, the composite material corner boxes 3 are four in number, distributed at the four corners of the mounting surface, thereby improving the stability of the engine installation. The composite material corner boxes 3 have a C-shaped cross-section, which is relatively easy to manufacture, has low mold costs, and can be molded along with the can, resulting in low production costs.

[0024] Furthermore, to address the issue of difficult bolt disassembly, the connecting assembly 4 includes a bolt 4-1, a nut 4-2, a custom bushing 4-3, and a bushing nut 4-4. The custom bushing 4-3 is installed in the bolt 4-1 hole connecting the composite material corner box 3 to the engine. The bushing nut 4-4 is threadedly connected to the end of the custom bushing 4-3. The bolt 4-1 extends from inside the tail cover through the engine mounting component and the custom bushing 4-3 into the composite material corner box 3. The nut 4-2 is threadedly connected to the end of the bolt 4-1 that extends into the composite material corner box 3 and abuts against the bushing nut 4-4.

[0025] Furthermore, the bushing nut 4-4 has a hexagonal shoulder 4-5.

[0026] Furthermore, the composite material corner box 3 has a thickened area 5 at the connection with the engine.

[0027] The integrated composite material UAV engine mounting structure of this embodiment adopts an integrated molded composite material fuselage 1, which eliminates the skin molding and frame-skin assembly process, improves production efficiency, and reduces the amount of fasteners and structural adhesive used, thus appropriately reducing weight. The design of the composite material corner box 3 not only reduces structural weight but also solves assembly problems. At the same time, the corner box has good load-bearing capacity, and the installation area can be locally thickened, which has good design flexibility and low cost. The design of the L-shaped corner piece 2 is easier to manufacture, and the cost is significantly lower than that of machined parts, thus reducing production costs.

[0028] The specific embodiments described above further illustrate the purpose, technical solution, and beneficial effects of this utility model. It should be understood that the above descriptions are merely specific embodiments of this utility model and are not intended to limit this utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this utility model should be included within the protection scope of this utility model.

Claims

1. An integrated composite material unmanned aerial vehicle (UAV) engine mounting structure, characterized in that: It includes an integrally molded composite material fuselage (1); the end face of the composite material fuselage (1) serves as the mounting surface for the engine; the mounting surface is provided with an L-shaped corner piece (2) and a composite material corner box (3); the L-shaped corner piece (2) is used for the installation of the tail cover; the composite material corner box (3) is used for the installation of the engine; the composite material corner box (3) is connected to the engine through a connecting component (4).

2. The integrated composite material UAV engine mounting structure according to claim 1, characterized in that: The composite material body (1) is integrally formed by a combination of heat shrink core mold and metal outer mold.

3. The integrated composite material UAV engine mounting structure according to claim 1, characterized in that: The number of composite material corner boxes (3) is four, which are distributed at the four corners of the mounting surface.

4. The integrated composite material UAV engine mounting structure according to claim 1, characterized in that: The connecting assembly (4) includes a bolt (4-1), a nut (4-2), a custom bushing (4-3), and a bushing nut (4-4); the custom bushing (4-3) is installed in the bolt (4-1) hole connecting the composite material corner box (3) to the engine; the bushing nut (4-4) is threaded to the end of the custom bushing (4-3); the bolt (4-1) extends from inside the tail cover through the engine mounting component and through the custom bushing (4-3) into the composite material corner box (3); the nut (4-2) is threaded to the end of the bolt (4-1) that extends into the composite material corner box (3) and abuts against the bushing nut (4-4).

5. The integrated composite material UAV engine mounting structure according to claim 4, characterized in that: The bushing nut (4-4) has a hexagonal shoulder (4-5).

6. The integrated composite material UAV engine mounting structure according to claim 1, characterized in that: The composite material corner box (3) has a thickened area (5) at the connection with the engine.

Images