Truss structure joint of unmanned aerial vehicle and manufacturing method of truss structure joint

Abstract

The invention belongs to the technical field of unmanned aerial vehicle structures, and particularly relates to an unmanned aerial vehicle truss structure connector which comprises a node position, a transition section, a connecting position and an external connecting piece. The surface of the node is connected with a plurality of transition sections; one end, far away from the node, of each transition section is connected with the joint; each connecting position is connected with the corresponding external connecting piece, and the joints are the positions of the gathering intersection points of the external connecting pieces. According to the unmanned aerial vehicle truss structure, by arranging the node, the transition section and the connecting position, externally-connected tubular beams can be conveniently gathered at the same node, concentrated and efficient transmission of force flow is achieved, additional bending moment caused by node eccentricity or centering deviation is avoided, and the technical problem that an existing unmanned aerial vehicle truss structure node is prone to deformation is solved.

Description

Technical Field

[0001] This invention belongs to the field of unmanned aerial vehicle (UAV) structural technology, and more specifically, relates to a UAV truss structure joint and its manufacturing method. Background Technology

[0002] In the field of UAV structural design, truss structures possess significant advantages such as lightweight yet high strength, rational stress distribution, and ease of integration. Through a rational member layout and the selection of lightweight materials, truss structures can achieve high specific strength while effectively reducing weight. The stable configuration based on triangular units creates an efficient load transfer path, resulting in a more rational stress distribution. Its open spatial layout facilitates the installation of batteries, sensors, flight control systems, and other equipment, and is beneficial for wiring, heat dissipation, and subsequent maintenance. Furthermore, truss structures have excellent bending and torsional stiffness, effectively reducing vibration and deformation during flight, improving flight stability and control accuracy. They are particularly suitable for the design of small and medium-sized UAVs and represent an important technological path to achieving high-performance, modular, and scalable structures.

[0003] Traditional truss structure nodes typically connect several tube beams using welding. However, when irregular nodes of multi-directional, variable cross-section tube beams are welded together, it is difficult to achieve precise alignment at the nodes. Furthermore, insufficient welding (such as incomplete welds or lack of fusion) is prone to occur at the nodes. In addition, the welding process is carried out in a high-temperature environment, and thermal deformation is likely to occur in the weld area after cooling. Due to the use of thin-walled tube beam materials, some of the manufactured components can have angular deformation of 1° to 5°. Even with the assistance of tooling fixtures for positioning, residual stress that cannot be ignored will still form inside the tube beam, affecting the accuracy and mechanical properties of the structure. Summary of the Invention

[0004] In view of the above-mentioned defects or improvement needs of the existing technology, the present invention provides a joint for a UAV truss structure and a method for manufacturing the same, thereby solving the technical problem of easy deformation of nodes in existing UAV truss structures.

[0005] To achieve the above objectives, according to one aspect of the present invention, a UAV truss structure joint is provided, including a node, transition sections, connections, and external connectors; the surface of the node is connected to a plurality of transition sections; one end of each transition section away from the node is connected to the connection; each connection is connected to the external connectors, and the node is the location where the external connectors converge.

[0006] Preferably, the length of the transition section is 30-50 mm, and the length of the connection is 20-30 mm.

[0007] Preferably, the connection is a bushing structure or a threaded structure; the bushing structure specifically includes a bushing hollow tube and a protrusion structure disposed on the outer wall of the bushing hollow tube; the transition section and the external connector are respectively snapped into the two ends of the bushing hollow tube and are separated from each other by the protrusion structure.

[0008] Preferably, the thickness of the protruding structure along the line connecting the transition section and the external connector is 0.2 to 0.3 mm; the wall thickness of the bushing hollow tube is 0.8 to 3 mm, preferably 1.0 to 1.5 mm; and the wall thickness of the bushing hollow tube is 0.8 to 1.0 times the wall thickness of the external connector.

[0009] Preferably, the envelope diameter at the node ranges from 10 mm to 60 mm, and more preferably from 20 mm to 30 mm.

[0010] Preferably, the envelope diameter at the node is 1.5 to 5 times the cross-sectional diameter of the external connector.

[0011] Preferably, the material of the connection is selected from stainless steel, aluminum alloy or titanium alloy, with titanium alloy being the most preferred.

[0012] Preferably, the transition section has the same shape as the cross-section of the external connector; the area of ​​the transition section is the same as that of the cross-section of the external connector.

[0013] According to another aspect of the present invention, a method for manufacturing a joint for a UAV truss structure is provided, comprising the following steps: (1) Based on the whole machine finite element analysis, the dimensions of the nodes and transition sections were defined, and the three-dimensional modeling of the nodes and transition sections was completed using three-dimensional modeling software; (2) The blank material is machined according to the three-dimensional model to connect several transition segments on the surface at the node; (3) Using welding or bolting, connect the end of each transition section away from the node to an external connector.

[0014] In summary, compared with the prior art, the above-described technical solutions conceived by this invention can achieve the following beneficial effects: (1) The present invention sets up nodes, transition sections and connections; the surface of the node is connected to several transition sections; the end of each transition section away from the node is connected to the connection; the node is the location of the convergence point of the connection, the connection is used to connect with the external tube beam of the UAV, each connection is connected with the external connector, the node is the location of the convergence point of the external connector, which facilitates the convergence of the external tube beams at the same node, realizes the concentrated and efficient transmission of force flow, avoids additional bending moment due to node eccentricity or centering deviation, thereby improving the efficiency and reliability of the force transmission path, and provides effective support for lightweight structural design.

[0015] (2) The present invention limits the diameter range of the node to 10mm ~ 60mm and the length of the transition section to 30~50mm, which not only realizes the concentrated force transmission and lightweight design of the joint, but also ensures that the overall size is compact enough, thereby reducing cutting waste and shortening the working time during machining, and effectively reducing the overall processing cost of the parts.

[0016] (3) The present invention defines the specific structure of the bushing, which on the one hand can avoid the structural strength reduction due to insufficient welding inside the tube beam, and on the other hand can effectively prevent the deterioration of the inner surface performance during the welding process through interference fit, thereby reducing the risk of subsequent corrosion.

[0017] (4) The nodes and transition sections of this invention are made by machining, which can effectively avoid process defects such as false welding and lack of fusion at the nodes, improve the processing yield of the truss structure joints, and can be basically controlled at more than 98%. At the same time, the nodes and transition sections are made by machining so that the two form an integral structure, which can effectively reduce the deformation problem caused by the welding process and improve the processing accuracy of the truss structure. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the welded truss structure joint and external connecting parts in Example 1.

[0019] Figure 2 This is a partially enlarged schematic diagram of the joint connection of the truss structure of the present invention.

[0020] Figure 3 This is a schematic diagram of the joint and external connecting parts of the bolted truss structure in Example 2.

[0021] Figure 4 This is a flowchart of the fabrication process for the joints of a drone truss structure.

[0022] In all the accompanying drawings, the same reference numerals are used to denote the same elements or structures, wherein: 1. Node; 2. Transition section; 3. Connection; 4. External connector. Detailed Implementation

[0023] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention. Furthermore, the technical features involved in the various embodiments of this invention described below can be combined with each other as long as they do not conflict with each other.

[0024] Example 1 This invention provides a truss structure joint for unmanned aerial vehicles, such as... Figure 1 As shown, it includes node 1, transition section 2, connection 3, and external connector 4.

[0025] The node 1 of the truss structure joint is located on the inner side of the joint. It is the intersection point where the transition sections 2 of multiple directions and different cross-sectional areas converge. It is mainly used for load accumulation and diffusion in different directions. The outer side is distributed according to the direction of the tube beam arrangement of the transition section 2. The transition section 2 of the truss structure joint is located in the middle of the joint, with node 1 on the inner side and connection 3 on the outer side. It is mainly used to transmit and diffuse the load of the external connector 4 at different connection points. The cross-sectional shape and size of the transition section 2 are consistent with the external connector 4 at the corresponding connection point, and its cross-sectional shape is a circular tube beam. The transition section 2 and the external connector 4 are welded together.

[0026] The connection 3 of the truss structure joint is located on the outside of the joint and is mainly used to connect with the external connector 4 of the UAV. The inner cavity cross section of the connection 3 can enclose the surface of the external connector 4.

[0027] The material of the truss structure connection 3 is stainless steel, the envelope diameter of the node 1 is 20 mm, the length of the transition section 2 is 30 mm, and the length of the connection 3 is 20 mm.

[0028] The connection 3 is a bushing structure; specifically, the bushing structure includes a hollow bushing tube and a protrusion structure disposed on the outer wall of the hollow bushing tube; the transition section 2 and the external connector 4 are respectively snapped onto both ends of the hollow bushing tube and are separated from each other by the protrusion structure. The thickness of the protrusion structure along the line connecting the transition section 2 and the external connector 4 is 0.2 mm; the wall thickness of the hollow bushing tube is 1 mm.

[0029] The method for manufacturing the joint of the UAV truss structure, such as Figure 4 As shown, it includes the following steps: (1) Based on the whole machine finite element analysis, complete the material selection and cross-sectional dimension definition at the nodes and transition sections; (2) Using Catia 3D modeling software, first create a sphere with the node as the origin, where the diameter of the sphere is 1.5 times the cross-sectional size of each external connector. Extend the cross-sections of the external connectors to intersect the sphere. Then, perform rounding / faceting smooth transition processing on the intersection curves to avoid stress concentration caused by direct connection. Finally, complete the modeling of the node and transition section. The joint node 1 should be able to enclose the cross-sections of all external connectors 4 and be a solid. (3) The blank material is machined according to the truss structure joint model so that the surface at the node is connected by several transition sections 2; (4) Using welding, the end of each transition section 2 furthest from the node is connected to the external connector 4.

[0030] When using welding to connect, a bushing structure should be pre-assembled at the connection point. The transition section 2 and the external connector 4 are respectively snapped onto both ends of the bushing hollow tube and are separated from each other by the protruding structure. For details of the specific construction, please refer to [link to details]. Figure 2 and Figure 3 The different connection points 3 and transition section 2 are welded together using auxiliary tooling fixtures, and then ground and polished to ensure that the surface is free of obvious defects. Using this type of bushing can, on the one hand, prevent a decrease in structural strength due to insufficient welding inside the pipe beam, and on the other hand, effectively prevent the deterioration of the inner surface properties during welding through interference fit, thereby reducing the risk of subsequent corrosion.

[0031] Example 2 This invention provides a truss structure joint for unmanned aerial vehicles, such as... Figure 3 As shown, it includes node 1, transition section 2, connection 3, and external connector 4.

[0032] The node 1 of the truss structure joint is located on the inner side of the joint. It is the intersection point where the transition sections 2 of multiple directions and different cross-sectional areas converge. It is mainly used for load accumulation and diffusion in different directions. The outer side is distributed according to the direction of the tube beam arrangement of the transition section 2. The transition section 2 of the truss structure joint is located in the middle of the joint, with node 1 on the inner side and connection 3 on the outer side. It is mainly used to transmit and diffuse the load of the external connector 4 at different connection points. Its cross-sectional shape and size are consistent with the external connector 4 at the corresponding connection point. Its cross-sectional shape adopts a circular tube beam. The transition section 2 and the external connector 4 are connected by threads.

[0033] The connection point 3 of the truss structure joint is located on the outside of the joint and is mainly used for threaded connection with the external connector 4 of the UAV. Its outer surface is flat to facilitate bolt connection and force transmission. The material of the truss structure connection 3 is stainless steel, the envelope diameter of the node 1 is 30 mm, the length of the transition section 2 is 40 mm, and the length of the connection 3 is 30 mm.

[0034] The method for manufacturing the joint of the UAV truss structure, such as Figure 4 As shown, it includes the following steps: (1) Based on the whole machine finite element analysis, complete the material selection and cross-sectional dimension definition at the nodes and transition sections; (2) SolidWorks 3D modeling software was used to complete the modeling of the nodes and transition sections. The joint nodes should be able to encompass all pipe beam sections and be solids. (3) Machining the blank material according to the truss structure joint model so that the surface at the node is connected by several transition sections; (4) Using a bolted connection method, the end of each transition section furthest from the node is connected to the joint. When using a bolted connection method, the through holes and inner holes of the truss structure joint are manually precision reamed to control the hole position accuracy within 0.01mm.

[0035] Example 3 This invention provides a truss structure joint for unmanned aerial vehicles, such as... Figure 1 As shown, it includes node 1, transition section 2, connection 3, and external connector 4.

[0036] The node 1 of the truss structure joint is located on the inner side of the joint. It is the intersection point where the transition sections 2 of multiple directions and different cross-sectional areas converge. It is mainly used for load accumulation and diffusion in different directions. The outer side is distributed according to the direction of the tube beam arrangement of the transition section 2. The transition section 2 of the truss structure joint is located in the middle of the joint, with node 1 on the inner side and connection 3 on the outer side. It is mainly used to transmit and diffuse the load of the external connector 4 at different connection points. The cross-sectional shape and size of the transition section 2 are consistent with the external connector 4 at the corresponding connection point, and its cross-sectional shape is a circular tube beam. The transition section 2 and the external connector 4 are welded together.

[0037] The connection 3 of the truss structure joint is located on the outside of the joint and is mainly used to connect with the external connector 4 of the UAV. The inner cavity cross section of the connection 3 can enclose the surface of the external connector 4.

[0038] The material of the truss structure connection 3 is stainless steel, the envelope diameter of the node 1 is 50 mm, the length of the transition section 2 is 50 mm, and the length of the connection 3 is 30 mm.

[0039] The connection 3 is a bushing structure; specifically, the bushing structure includes a hollow bushing tube and a protrusion structure disposed on the outer wall of the hollow bushing tube; the transition section 2 and the external connector 4 are respectively snapped onto both ends of the hollow bushing tube and are separated from each other by the protrusion structure. The thickness of the protrusion structure along the line connecting the transition section 2 and the external connector 4 is 0.3 mm; the wall thickness of the hollow bushing tube is 2 mm.

[0040] The method for manufacturing the joint of the UAV truss structure, such as Figure 4 As shown, it includes the following steps: (1) Based on the whole machine finite element analysis, complete the material selection and cross-sectional dimension definition at the nodes and transition sections; (2) Using UG 3D modeling software, first create a sphere with the node as the origin, where the diameter of the sphere is twice the cross-sectional size of each external connector. Extend the cross-sections of the external connectors to intersect the sphere. Then, perform rounding / faceting smooth transition processing on the intersection curves to avoid stress concentration caused by direct connection. Finally, complete the modeling of the node and transition section. The joint node 1 should be able to enclose the cross-sections of all external connectors 4 and be a solid. (3) The blank material is machined according to the truss structure joint model so that the surface at the node is connected by several transition sections 2; (4) Using welding, the end of each transition section 2 furthest from the node is connected to the external connector 4.

[0041] When using welding to connect, a bushing structure should be pre-assembled at the connection point. The transition section 2 and the external connector 4 are respectively snapped onto both ends of the bushing hollow tube and are separated from each other by the protruding structure. For details of the specific construction, please refer to [link to details]. Figure 2 and Figure 3 The different connection points 3 and transition section 2 are welded together using auxiliary tooling fixtures, and then ground and polished to ensure that the surface is free of obvious defects. Using this type of bushing can, on the one hand, prevent a decrease in structural strength due to insufficient welding inside the pipe beam, and on the other hand, effectively prevent the deterioration of the inner surface properties during welding through interference fit, thereby reducing the risk of subsequent corrosion.

[0042] Those skilled in the art will readily understand that the above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A truss structure joint for unmanned aerial vehicles (UAVs), characterized in that, It includes a node (1), a transition section (2), a connection (3), and an external connector (4); the surface of the node (1) is connected to several transition sections (2); the end of each transition section (2) away from the node (1) is connected to the connection (3); each connection (3) is connected to the external connector (4), and the node (1) is the location where the external connectors (4) converge.

2. The UAV truss structure joint as described in claim 1, characterized in that, The length of the transition section (2) is 30~50mm, and the length of the connection (3) is 20~30mm.

3. The UAV truss structure joint as described in claim 1, characterized in that, The connection (3) is a bushing structure or a threaded structure; the bushing structure specifically includes a bushing hollow tube and a protrusion structure provided on the outer wall of the bushing hollow tube; the transition section (2) and the external connector (4) are respectively snapped into the two ends of the bushing hollow tube and are separated from each other by the protrusion structure.

4. The UAV truss structure joint as described in claim 3, characterized in that, The thickness of the protruding structure along the line connecting the transition section (2) and the external connector (4) is 0.2 to 0.3 mm; the wall thickness of the bushing hollow tube is 0.8 to 3 mm, preferably 1.0 to 1.5 mm; the wall thickness of the bushing hollow tube is 0.8 to 1.0 times the wall thickness of the external connector (4).

5. A UAV truss structure joint as described in claim 1, characterized in that, The envelope diameter at the node (1) ranges from 10 mm to 60 mm, preferably from 20 mm to 30 mm.

6. A UAV truss structure joint as described in claim 5, characterized in that, The envelope diameter at the node (1) is 1.5 to 5 times the cross-sectional diameter of the external connector (4).

7. The UAV truss structure joint as described in claim 1, characterized in that, The material of the connection (3) is selected from stainless steel, aluminum alloy or titanium alloy, preferably titanium alloy.

8. A UAV truss structure joint as described in claim 1, characterized in that, The transition section (2) has the same shape as the cross-section of the external connector (4); the area of ​​the transition section (2) is the same as that of the cross-section of the external connector (4).

9. A method for manufacturing a UAV truss structure joint as described in any one of claims 1 to 8, characterized in that, Includes the following steps: (1) Based on the whole machine finite element analysis, the dimensions of the nodes and transition sections were defined, and the three-dimensional modeling of the nodes and transition sections was completed using three-dimensional modeling software; (2) The blank material is machined according to the three-dimensional model to connect several transition segments on the surface at the node; (3) Using welding or bolting, connect the end of each transition section away from the node to an external connector.

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