Composite truss of unmanned aerial vehicle

Abstract

The utility model belongs to the technical field of unmanned aerial vehicle design, and particularly relates to an unmanned aerial vehicle composite material truss which comprises keel beams, a fuselage frame, inclined rods and node connectors. The keel beam is tubular and is made of a composite material; the four keel beams are arranged in a rectangular shape; the fuselage frame is rectangular, has a tubular edge and is made of a composite material; the fuselage frames are distributed in the four keel beams in the axial direction, and the four vertex angles are connected to the four keel beams; the inclined rods are of tubular structures and are made of composite materials, and the adjacent fuselage frames are connected through one inclined rod between a pair of inclined vertex angles on the same side of the four keel beams; each group comprises four node joints, the node joints are arranged at the joints where the vertex angles of the fuselage frames are connected with the four keel beams, the node joints are connected to the corresponding keel beams in a sleeving mode through the through holes and connected with the edges of the corresponding fuselage frames and the ends of the inclined rods through the insertion holes, and the node joints are bonded through the gluing technology.

Description

Technical Field

[0001] The present application belongs to the technical field of unmanned aerial vehicle design, and specifically relates to a composite material truss for an unmanned aerial vehicle. Background Art

[0002] UAVs, especially solar-powered UAVs, have a very low fuselage weight coefficient and strict weight control. Therefore, composite materials are currently used to manufacture fuselage trusses.

[0003] Existing UAV composite trusses are mostly suitable for small fuselages. They lack the necessary strength design for the connection of large wings, horizontal tails, vertical tails, and landing gears. They are not easy to disassemble and assemble, and cannot meet the installation requirements of devices such as solar cells and electronic equipment. In addition, the node connection parts are mostly wrapped with artificial carbon cloth, which is extremely dependent on manual operation and experience, time-consuming and labor-intensive, and the connection reliability is difficult to be effectively guaranteed.

[0004] This application is proposed in view of the above-mentioned technical defects. Summary of the invention

[0005] The purpose of the present application is to provide a composite truss for an unmanned aerial vehicle to overcome or alleviate at least one of the known technical deficiencies.

[0006] The technical solution of this application is:

[0007] A composite truss for an unmanned aerial vehicle, comprising a keel beam, a fuselage frame, a diagonal rod, and a node joint;

[0008] The keel beam is tubular and made of composite materials; there are four keel beams arranged in a rectangular shape;

[0009] The fuselage frame is rectangular, with a tubular structure at the edge, and is made of composite materials; there are multiple fuselage frames, which are distributed axially within the four keel beams, and the four vertex corners are connected to the four keel beams;

[0010] The diagonal rod is a tubular structure made of composite materials. Adjacent fuselage frames are connected by a diagonal rod between a pair of diagonal top corners on the same side of the four keel beams;

[0011] There are multiple groups of node joints, each group has four, which are arranged at the nodes where each fuselage frame top corner is connected to the four keel beams. Each node joint is sleeved on the corresponding keel beam with a through hole, and is connected to the corresponding fuselage frame edge and the end of the oblique rod with a socket, and is bonded by a gluing process.

[0012] According to at least one embodiment of the present application, in the above-mentioned UAV composite truss, the fuselage frame is divided into an ordinary frame and a reinforced frame, and the tubular structure at the edge of the reinforced frame has a larger tube diameter and thickness than the ordinary frame, wherein the reinforced frame is arranged at the position where the wing, horizontal tail, landing gear need to be connected, and where solar cells and electronic equipment devices need to be installed, and ordinary frames are arranged at the remaining positions.

[0013] According to at least one embodiment of the present application, in the above-mentioned UAV composite material truss, the diagonal rods are divided into ordinary rods and reinforcement rods. The reinforcement rods have a larger tube diameter and thickness than the ordinary rods, wherein the reinforcement rods are arranged at the positions where the wings and landing gear need to be connected, and solar cells and electronic equipment devices need to be installed, and ordinary rods are arranged at the remaining positions.

[0014] According to at least one embodiment of the present application, in the above-mentioned UAV composite truss, the node joints are divided into composite joints and metal joints, wherein the metal joints are arranged at the positions where the wings, horizontal tail, vertical tail, and landing gear need to be connected, and composite joints are arranged at the remaining positions. The metal joints have double-ear joints, which are connected to the corresponding single-ear joints on the wings, horizontal tail, vertical tail, and landing gear through pins.

[0015] According to at least one embodiment of the present application, in the above-mentioned UAV composite material truss, the four keel beams are located behind the horizontal tail, and the cross-sectional dimensions enclosed by them are shrunk and tapered.

[0016] This application has at least the following beneficial technical effects:

[0017] Provided is a composite material truss for an unmanned aerial vehicle, in which a keel beam, a fuselage frame and an oblique rod constituting the truss are designed to be made of composite materials and have a light weight. The node positions at which the trusses are connected are plugged in with node joints and bonded with an adhesive bonding process, which is convenient, fast and reliable in connection. Four keel beams can be used to maintain the heading stiffness and strength, a plurality of fuselage frames can be used to provide circumferential stiffness and strength support, and the oblique rods can be used to enhance the in-plane stiffness and strength, so that the truss can meet the requirements for the connection of large wings, horizontal tails, vertical tails and landing gears, as well as the installation requirements of solar cells, electronic equipment and other devices to a certain extent. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 is a schematic diagram of a composite material truss of a UAV provided in an embodiment of the present application;

[0019] Figure 2 is a schematic diagram of a composite material joint provided in an embodiment of the present application;

[0020] Figure 3 is a schematic diagram of a metal joint provided in an embodiment of the present application;

[0021] Figure 4 This is a schematic diagram of the design of the composite truss for connecting the wings and taking off and landing of the drone provided in the embodiment of the present application;

[0022] Figure 5 This is a schematic diagram of the design of a composite truss for connecting the horizontal tail and the vertical tail of a UAV provided in an embodiment of the present application;

[0023] in:

[0024] 1-keel beam; 2-fuselage frame; 3-diagonal rod; 4-node joint; 5-landing gear.

[0025] In order to better illustrate this embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and cannot be understood as limitations on this patent. DETAILED DESCRIPTION

[0026] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design.

[0027] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the usual meanings understood by those of ordinary skill in the art to which this application belongs. The words used in the description of this application to indicate orientation are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application indicates that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0028] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installation", "connection" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0029] A composite truss for an unmanned aerial vehicle comprises a keel beam 1, a fuselage frame 2, a diagonal rod 3, and a node joint 4. Figure 1 shown.

[0030] The keel beam 1 is tubular and made of composite material. There are four keel beams 1 arranged in a rectangular shape.

[0031] The fuselage frame 2 is rectangular, has a tubular structure at the edge, and is made of composite material. There are multiple fuselage frames 2, which are distributed axially within the four keel beams 1, and four vertex angles are connected to the four keel beams 1.

[0032] The oblique rod 3 is a tubular structure made of composite materials. Adjacent fuselage frames 2 are connected by an oblique rod 3 between a pair of oblique top corners on the same side of the four keel beams 1 .

[0033] There are multiple groups of node joints 4, each group has four, which are arranged at the nodes where the top corners of each fuselage frame 2 are connected to the four keel beams 1. Each node joint 4 is sleeved on the corresponding keel beam 1 with a through hole, and is connected to the edge of the corresponding fuselage frame 2 and the end of the oblique rod 3 with a socket, and is bonded by a gluing process.

[0034] The composite truss of the unmanned aerial vehicle disclosed in the above embodiment may be provided with a fairing at the front end and a skin on the periphery to form a fuselage, wherein the fairing may be a two-layer carbon fiber fabric laminate structure and the skin may be a fiber-reinforced film structure.

[0035] In the composite material truss of the unmanned aerial vehicle disclosed in the above-mentioned embodiment, the keel beam 1, the fuselage frame 2, and the diagonal rod 3 constituting the truss are designed to be made of composite materials and have a light weight. The node parts designed to be connected are plugged in with node joints 4 and bonded with a gluing process, which is convenient, fast, and reliable in connection. The four keel beams 1 can be used to maintain the directional stiffness and strength, and the multiple fuselage frames 2 can be used to provide circumferential stiffness and strength support, and the diagonal rods 3 can be used to enhance the in-plane stiffness and strength. It can meet the installation requirements of large wings, horizontal tails, vertical tails, landing gear connections, and solar cells, electronic equipment and other devices to a certain extent.

[0036] The fuselage frame 2 is divided into a common frame and a reinforced frame. The tubular structure at the edge of the reinforced frame has a larger diameter and thickness than the common frame. Specifically, the outer diameter of the tubular structure at the edge of the common frame can be designed to be 19 mm and the thickness can be 0.48 mm, and the outer diameter of the tubular structure at the edge of the reinforced frame can be 29 mm and the thickness can be 1.2 mm. Among them, the reinforced frame is set at and near the position where the wing, horizontal tail, landing gear need to be connected, and the solar cell, electronic equipment and other devices need to be installed. The common frame is set at the other positions to meet the strength requirements of the connection of the wing, horizontal tail, landing gear and the installation of solar cells, electronic equipment and other devices, and the fuselage frame 2 at the wing connection position can be designed to be encrypted. In the case where the strength and rigidity of the composite truss of the unmanned aerial vehicle are sufficient, in order to reduce the weight of the fuselage or avoid interference, part of the edge of the fuselage frame 2 can be omitted, and the specific distribution positions of the common frame and the reinforced frame can also be appropriately adjusted according to the actual situation.

[0037] The oblique rods 3 are divided into ordinary rods and reinforcing rods. The reinforcing rods have a larger diameter and thickness than the ordinary rods. Specifically, the ordinary rods can be designed to have an outer diameter of 19 mm and a thickness of 0.36 mm, and the reinforcing rods can be designed to have an outer diameter of 29 mm and a thickness of 1.2 mm. Among them, the reinforcing rods are arranged at and near the positions where the wings and landing gears need to be connected, and the solar cells, electronic equipment and other devices need to be installed. Ordinary rods are arranged at other positions to meet the strength requirements of the wings, landing gear connections, and the installation of solar cells, electronic equipment and other devices. When the strength and rigidity of the UAV composite material truss are sufficient, in order to reduce the weight of the fuselage or avoid interference, some oblique rods 3 can be omitted between some fuselage frames 2. The specific distribution positions of the ordinary rods and reinforcing rods can also be appropriately adjusted according to actual conditions.

[0038] The node joint 4 is divided into a composite material joint and a metal joint. The composite material joint can adopt a carbon fiber laminate structure with a wall thickness of 0.84 mm. Figure 2 As shown; the metal joint can be made of aluminum alloy material, such as Figure 3 As shown. Metal joints are set at the positions where the wings, horizontal tail, vertical tail and landing gear need to be connected, and composite material joints are set at other positions. The metal joints have double-ear joints, which are connected to the corresponding single-ear joints on the wings, horizontal tail, vertical tail and landing gear through pins, so as to ensure the strength requirements of the connection between the wings, horizontal tail, vertical tail and landing gear, and facilitate the rapid disassembly and assembly of the wings, horizontal tail, vertical tail and landing gear.

[0039] The four keel beams 1 are located behind the horizontal tail, and the cross-section enclosed by them is shrunk and tapered to improve the rigidity of the tail.

[0040] In a specific embodiment, the outer diameter of the four keel beams 1 is 29 mm, the thickness is 1.2 mm, the length is 14.224 meters, and the enclosed cross-section is 395 mm×395 mm. The number of fuselage frames 2 is 23, which are numbered 1#, 2#, 3#...23# from front to back, among which 1#, 2#, 3#, 7#, 9#, 20#, use reinforced frames, the diagonal rods 3 between the 1#, 2#, 3#, and 4# fuselage frames 2 use reinforced rods, and the diagonal rods 3 between the left and right sides of the 7#, 8#, 9# fuselage frames 2 use reinforced rods.

[0041] 1# fuselage frame 2 is the connection frame of the fairing.

[0042] The 2# and 3# fuselage frames 2 are installation frames for solar cells, electronic devices and other devices. The carbon fiber composite material board is installed on the lower plane through buckles, the electronic equipment is installed on the composite material board, and the solar cell is mounted on the top edge of the frame.

[0043] The 7# and 9# fuselage frames 2 are wing connection frames. Metal joints are set at the top corners of the upper sides of the 7# and 9# fuselage frames 2, and the double ears are connected to the single ears on the wing. The 7# and 8# fuselage frames 2 are landing gear connection frames. Metal joints are set at the top corners of the lower sides of the 7# and 8# fuselage frames 2, and the double ears are connected to the single ears on the landing gear 5. Figure 4 shown.

[0044] The 20# fuselage frame 2 is a horizontal tail connection frame. A metal joint is set at the top corner of the lower side of the 20# fuselage frame 2, and the double ears are connected to the single ear on the horizontal tail, such as Figure 5 As shown, the cross-sectional dimensions of the four keel beams 1 at the position behind the 20# fuselage frame 2 are shrunk and tapered.

[0045] The 22# and 23# fuselage frames 2 are the vertical tail connection frames. Metal joints are set at the top corners of the 22# and 23# fuselage frames 2, and the double ears are connected to the single ear on the vertical tail, such as Figure 5 shown.

[0046] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.

Claims

1. A composite truss for an unmanned aerial vehicle, characterized in that: It comprises a keel beam (1), a fuselage frame (2), an oblique rod (3), and a node joint (4); The keel beam (1) is tubular and made of composite material; there are four keel beams (1) arranged in a rectangular shape; The fuselage frame (2) is rectangular, has a tubular structure at the edge, and is made of composite materials; there are multiple fuselage frames (2), which are distributed along the axial direction inside the four keel beams (1), and the four vertex angles are connected to the four keel beams (1); The oblique rod (3) is a tubular structure made of composite materials. Adjacent fuselage frames (2) are connected by an oblique rod (3) between a pair of oblique top corners on the same side of the four keel beams (1). There are multiple groups of node joints (4), each group having four nodes, which are arranged at the nodes where the top corners of each fuselage frame (2) are connected to the four keel beams (1). Each node joint (4) is sleeved on the corresponding keel beam (1) through a through hole, and is connected to the edge of the corresponding fuselage frame (2) and the end of the oblique rod (3) through a socket, and is bonded by a gluing process.

2. The composite truss of the unmanned aerial vehicle according to claim 1, characterized in that: The fuselage frame (2) is divided into a common frame and a reinforced frame. The tubular structure at the edge of the reinforced frame has a larger diameter and thickness than that of the common frame. The reinforced frame is arranged at positions where the wing, horizontal tail, landing gear need to be connected, and where solar cells and electronic equipment components need to be installed, and the common frames are arranged at other positions.

3. The composite truss of the unmanned aerial vehicle according to claim 1, characterized in that: The oblique rods (3) are divided into ordinary rods and reinforcing rods. The reinforcing rods have a larger diameter and thickness than the ordinary rods. The reinforcing rods are arranged at positions where wings and landing gears need to be connected, and where solar cells and electronic equipment components need to be installed, while ordinary rods are arranged at other positions.

4. The composite truss of the unmanned aerial vehicle according to claim 1, characterized in that: The node joint (4) is divided into a composite material joint and a metal joint, wherein the metal joint is arranged at the position where the wing, horizontal tail, vertical tail and landing gear need to be connected, and the composite material joint is arranged at the other positions, and the metal joint has a double-ear joint, which is connected to the corresponding single-ear joint on the wing, horizontal tail, vertical tail and landing gear through a pin shaft.

5. The composite truss of the unmanned aerial vehicle according to claim 1, characterized in that: The four keel beams (1) are located behind the horizontal tail, and the cross-section enclosed by them is shrunk in size and presents a cone shape.

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