Unmanned aerial vehicle fuselage structure

Abstract

The utility model discloses an unmanned aerial vehicle fuselage structure which comprises a framework, a skin assembly is installed on the outer side of the framework, the skin assembly comprises a skin body, a covering cap is installed on the skin body, a wire passing hole is formed in the top of the skin body, and an undercarriage groove is formed in the bottom of the skin body. The structure is high in safety, the two main frames are arranged near the undercarriage, the load of the undercarriage can be directly transmitted to the upper platform, the load of the undercarriage and the load of the central wing are balanced, force transmission is direct, and the safety is high.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles (UAVs), and in particular to a UAV fuselage structure. Background Art

[0002] The drone fuselage is not only the aircraft's skeleton and protective structure, but also involves aerodynamic design, support structures, wing attachment, and landing gear, ensuring stable flight and safe landing. The interior of the fuselage can serve as a cargo hold and also provides space for avionics equipment and power batteries. A drone fuselage consists of a skin and a frame, typically made of composite materials. The frame is composed of circumferential and longitudinal components, which are molded using a mold. The fuselage's interior is designed with appropriate installation spaces and provides force transmission between the landing gear and wings. Many existing fuselages, such as the Chinese utility model patent application number 202022320035.7, "A Co-cured Composite UAV Fuselage," integrate the skin, frame, and beams into a single, co-cured mold. This complex mold reduces assembly workload but increases the molding effort. This integrated structure is prone to manufacturing defects during molding, leading to component failure. Furthermore, damage during use makes component replacement and repair difficult. The fuselage also has limited upper covers, making it difficult to install internal equipment and cargo. Utility Model Content

[0003] The present invention aims to provide a drone fuselage structure to address the problems mentioned in the background art. To achieve this objective, the present invention provides the following technical solution: a drone fuselage structure comprising a skeleton, a skin assembly mounted on the outer side of the skeleton, the skin assembly comprising a skin body, a cover mounted on the skin body, a cable hole formed at the top of the skin body, and a landing gear slot at the bottom.

[0004] Preferably, the periphery of the wire hole is coated with a wear-resistant material.

[0005] Preferably, the skeleton includes a landing gear connecting block, the front and rear ends of the landing gear connecting block are connected to the front main frame and the rear main frame, an upper platform is installed on the top between the front main frame and the rear main frame, the front side of the front main frame is connected to the front equipment compartment, and the rear side of the rear main frame is connected to the rear equipment compartment, and the front equipment compartment and the rear equipment compartment are connected to the landing gear connecting block through longitudinal beams.

[0006] Preferably, the upper platform includes a support frame, and a wing-body connecting seat is installed on the support frame.

[0007] Preferably, a plurality of lightening holes are provided on the front main frame and the rear main frame, and connection grooves are provided at upper and lower ends of the front main frame and the rear main frame respectively.

[0008] Preferably, the wing-body connection seat is clamped inside the support frame through a flange.

[0009] The technical effects and advantages of the utility model are as follows: the structure is highly safe: the two main frames are arranged near the landing gear, which can directly transfer the landing gear load to the upper platform and balance it with the central wing load, with direct force transmission and high safety;

[0010] Easy connection: The fuselage and wings are connected through four wing-body connectors and four fasteners, which can achieve quick disassembly and assembly.

[0011] Good maintainability: The fuselage skin is designed with many access covers to facilitate the inspection of internal equipment and structures, as well as the loading and unloading of cargo;

[0012] Low cost: The frame is assembled with flat parts and can be manufactured without molds and special work, so the cost is low;

[0013] Low aerodynamic resistance: A groove is designed on the skin body at the connection position with the landing gear, so that after the landing gear is installed with the fuselage structure, the connection area does not protrude from the surface of the fuselage skin, thereby reducing aerodynamic resistance. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 This is an exploded view of the utility model;

[0015] Figure 2 This is an exploded view of the fuselage skin assembly of the utility model;

[0016] Figure 3 This is an axonometric view of the skin body of the utility model;

[0017] Figure 4 It is an axonometric drawing of the skeleton of the present invention from the top perspective;

[0018] Figure 5 This is an axonometric view of the skeleton of the present invention from a bottom perspective;

[0019] Figure 6 This is a partial view of the frame of the utility model at the wing-body connection seat;

[0020] Figure 7 This is an axonometric drawing of the front main frame of the present utility model;

[0021] Figure 8 This is a cross-sectional view of the wing-body connecting seat of the utility model;

[0022] Figure 9 This is an axonometric drawing of the utility model assembled with a drone.

[0023] In the figure, 1. Fuselage structure; 11. Skin assembly; 111. Skin body; 1111. Wire hole; 1112. Landing gear slot; 112. Cover; 12. Frame; 121. Front main frame; 1211. Lightening hole; 1212. Connection slot; 122. Rear main frame; 123. Upper platform; 1231. Wing-body connection seat; 1232. Support frame; 124. Front equipment compartment; 125. Rear equipment compartment; 126. Landing gear connection block; 127. Longitudinal beam; 2. UAV. DETAILED DESCRIPTION

[0024] In order to make the technical means for realizing the present invention, the creative features, the purpose and the effect easily understood, the present invention is further explained below in conjunction with specific diagrams. In the description of the present invention, it should be noted that, unless otherwise clearly stipulated and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, an integral connection or a mechanical connection, or an electrical connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be internal communication between two components.

[0025] Example

[0026] like Figure 9 As shown, the drone's fuselage structure 1 is connected to the landing gear at the bottom and the wings at the top. Cargo, equipment, and other items are housed within. Wiring harnesses connect to the fuselage and other components, extending throughout the drone 2. The fuselage structure 1 bears the landing gear load and transfers it to the wings, where it converges at the center of the wings above the fuselage to achieve force balance. The fuselage structure must meet aerodynamic requirements and minimize aerodynamic drag.

[0027] like Figure 1 As shown, the fuselage structure 1 includes a skeleton 12 and a skin assembly 11. The skin assembly 11 is installed on the outside of the skeleton 12. The skin assembly 11 maintains the aerodynamic shape, provides a passage in and out of the fuselage, and transfers the aerodynamic load to the skeleton 12. The skeleton 12 serves as the main load-bearing component and bears the main load of the fuselage structure. At the same time, the internal space serves as a fixed cargo, equipment, etc. The skin assembly 11 and the skeleton 12 are bonded together by structural adhesive to form a whole.

[0028] like Figure 2As shown, the skin assembly includes a skin body 111 and multiple flaps 112. The flaps 112 are designed in different sizes at the top, sides, bottom, and rear as needed. The flaps 112 are connected to the skin body 111 using removable single-sided fasteners, such as a support nut and bolt pair, a rivet nut and bolt pair, etc. The skin body 111 is a foam sandwich structure, which increases its rigidity and prevents buckling caused by aerodynamic forces during flight, which could affect aerodynamic performance. The skin body 111 can be a carbon fiber composite foam sandwich structure or a glass fiber composite foam sandwich structure. In this example, a glass fiber composite foam sandwich structure is used to reduce costs. The flaps 112 provide access to the interior of the fuselage structure 1, facilitating maintenance of equipment and loading and unloading of cargo. Larger flaps 112 are glass fiber composite foam sandwich structures, while smaller flaps 112 are glass fiber composite laminate structures.

[0029] like Figure 3 As shown, the skin body 111 is designed with a wire hole 1111 and a landing gear slot 1112. The wire hole 1111 is located at the top of the skin body 111 to facilitate the passage of avionics and power harnesses, connecting the harnesses inside the wing and fuselage together to form a complete pathway. To prevent the wire hole 1111 from abrading the harnesses, the periphery of the wire hole 1111 can be coated with a wear-resistant material such as foam or rubber to increase the life of the harnesses. The landing gear slot 1112 is opened at the bottom of the skin body 111 and is recessed to a certain depth at the location where the skin shape mates with the landing gear. This ensures that the lower surface of the landing gear is flush with the fuselage skin, reducing aerodynamic drag and improving the aircraft's aerodynamic performance.

[0030] like Figure 4 、 Figure 5 and Figure 6As shown, the skeleton 12 includes a front main frame 121, a rear main frame 122, an upper platform 123, a front equipment compartment 124, a rear equipment compartment 125, a landing gear connecting block 126, and a longitudinal beam 127. Except for the landing gear connecting block 126, other parts are all spliced together by carbon fiber composite flat plate structures. The landing gear connecting block 126 is a carbon fiber composite material structure with a foam core to improve the stiffness of the connection; the front main frame 121 and the rear main frame 122 are two annular parts, which are installed at the front and rear ends of the landing gear connecting block 126 and are supported on the skin body 111 on all sides. They can transfer the landing gear load directly to the upper platform 123 through the front and rear main frames. The upper platform 123 is installed at the top between the front main frame 121 and the rear main frame 122. The upper platform 123 is connected to the wing. The skeleton density in this area is relatively high, and the wing load is transferred to this area for balance. The upper platform 123 is connected to the wing-body connection seat 1231 by a support frame 1232 composed of flat plates. The wing-body connection seat 1231 is connected to the wing, and the entire fuselage is hung on the lower part of the wing through four wing-body connection seats 1231. The front equipment compartment 124 is connected to the front side of the front main frame 121, and the rear equipment compartment 125 is connected to the rear side of the rear main frame 122. The front equipment compartment 124 is connected to the battery and is heavy, which is conducive to adjusting the center of gravity of the entire drone. The rear equipment compartment 125 is connected to the avionics equipment and is light. It is close to the flight control computer inside the wing, saving the length and weight of the wiring harness. The front equipment compartment 124 and the rear equipment compartment 125 are connected to the landing gear connecting block 126 through the longitudinal beam 127. The longitudinal beam 127 transmits the longitudinal load in the front and rear directions, and at the same time supports the circumferential frame, thereby improving the ability of the entire skeleton to withstand longitudinal loads.

[0031] like Figure 7 As shown, the front main frame 121 is designed with lightening holes 1211 and connecting slots 1212. The connecting slots 1212 are located at the top and bottom ends of the front main frame 121. The width of the connecting slots 1212 matches the width of the connected parts. Other flat parts are inserted into the connecting slots 1212 to complete the skeleton assembly. Lightening holes 1211 reduce the weight of the structure and improve the performance of the drone. This figure only shows the front main frame 121; the rear main frame 122 has a similar structure.

[0032] like Figure 8 As shown, the wing-body connection seat 1231 is clamped inside the support frame 1232 through a flange to keep the wing-body connection seat fixed. When subjected to axial force, it will not fall out of the support frame 1232, thereby improving the reliability of the connection. The wing-body connection seat 1231 is made of aluminum alloy, which can improve the wear performance between the fasteners when disassembling the wings and fuselage.

[0033] Finally, it should be noted that the above is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or make equivalent replacements for some of the technical features therein. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A UAV fuselage structure, comprising a frame, characterized in that: A skin assembly is installed on the outer side of the skeleton. The skin assembly includes a skin body. A cover is installed on the skin body. A wire hole is opened on the top of the skin body and a landing gear slot is provided on the bottom.

2. The UAV fuselage structure according to claim 1, characterized in that: The periphery of the wire hole is covered with wear-resistant material.

3. The UAV fuselage structure according to claim 1, characterized in that: The skeleton includes a landing gear connecting block, the front and rear ends of the landing gear connecting block are connected to the front main frame and the rear main frame, an upper platform is installed on the top between the front main frame and the rear main frame, the front side of the front main frame is connected to the front equipment compartment, and the rear side of the rear main frame is connected to the rear equipment compartment, and the front equipment compartment and the rear equipment compartment are connected to the landing gear connecting block through longitudinal beams.

4. The UAV fuselage structure according to claim 3, characterized in that: The upper platform includes a support frame, and a wing-body connecting seat is installed on the support frame.

5. The UAV fuselage structure according to claim 3, characterized in that: A plurality of lightening holes are provided on the front main frame and the rear main frame, and connection grooves are provided on the upper and lower ends of the front main frame and the rear main frame respectively.

6. The UAV fuselage structure according to claim 4, characterized in that: The wing-body connecting seat is clamped inside the supporting frame through a flange.

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