Manufacturing process of 3D additive matrix composite skin of unmanned aerial vehicle
A manufacturing process, UAV technology, applied in additive processing, fuselage, aircraft assembly, etc., can solve problems such as insufficient structural strength of parts, and achieve the effect of rapid design and rapid manufacturing
Pending Publication Date: 2021-01-05
XIAN AERONAUTICAL UNIV
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Problems solved by technology
[0005] In order to solve the above technical problems, the purpose of the present invention is to provide a 3D additive matrix composite skin manufacturing process for unmanned aerial vehicles. Its manufacture has the disadvantage of insufficient structural strength of parts
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[0040] The present invention will be described in further detail below in conjunction with the accompanying drawings.
[0041] Such as Figure 1-Figure 6 Shown: a UAV 3D additive matrix composite skin manufacturing process, including the following steps;
[0042] 1. Build the body frame (key points: the frame base 1 is flat, the frame slot 2 is tangent to the fuselage structure 3);
[0043] The UAV body frame includes a base support body 4 and a frame slot 2 fixed on the base 5 for positioning the UAV body structure 3 .
[0044] Wherein, the base support body 4 is used to ensure the accuracy of the horizontal direction during the fuselage manufacturing process. Therefore, the part is manufactured horizontally and cannot move during the manufacturing process.
[0045] The base support body 4 has a fixed groove 6 that conforms to the longitudinal manufacturing accuracy of the UAV fuselage structure, and the fixed groove 6 is fixed on the positioning frame slot 7 for the UAV f...
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The invention discloses a manufacturing process of a 3D additive matrix composite skin of an unmanned aerial vehicle. The manufacturing process comprises the following steps: step 1, a machine body fixture is built; and the machine body fixture comprises a fixture base, the fixture base is flatly arranged on the ground, a fixture clamping groove is formed in the upper surface of the fixture base,a machine body structure is arranged on the fixture clamping groove, the fixture clamping groove is tangent to the machine body structure, and the precision of the fixture clamping groove in the horizontal direction is controlled through a base supporting body arranged on the upper surface of the fixture base; step 2, the machine body fixture is assembled and fixed; unmanned aerial vehicle body bulkheads are mounted on the unmanned aerial vehicle body frame according to the corresponding sequence, vehicle body main beams are placed on the unmanned aerial vehicle body bulkhead components, and the unmanned aerial vehicle body bulkhead components and the vehicle body main beams are combined into a whole through the means of welding, riveting, gluing and the like; and step 3, a base body of the 3D additive skin is laid on the outer side of the whole obtained in the step 2, and a composite material is laid on the base body. Rapid design and rapid manufacturing of a large-curvature structural part are achieved.
Description
technical field [0001] The invention relates to the technical field of unmanned aerial vehicles, in particular to a 3D additive matrix composite skin manufacturing process for unmanned aerial vehicles. Background technique [0002] The existing UAV large-curvature structure manufacturing is mainly based on mold and sheet metal processing and manufacturing processes. These manufacturing technologies have the advantages of mature technology and strong applicability. However, for parts with large curvatures such as the fuselage and wings, mold and sheet metal processing and manufacturing technologies also have disadvantages such as high production costs and long manufacturing cycles. Moreover, the sheet metal manufacturing process has difficulties in ensuring manufacturing accuracy and structural strength for large curvature parts. [0003] In recent years, the development of 3D additive manufacturing technology has brought new ways to solve the manufacturing problems between...
Claims
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IPC IPC(8): B64F5/10B64C1/12B33Y80/00
CPCB64C1/12B64C2001/0072B33Y80/00B64F5/10
Inventor 李继广董彦非屈高敏李嘉兴严天健唐家坤闫朋张阿龙赵成功陆南李二博
Owner XIAN AERONAUTICAL UNIV