Assembling fixture for fuselage of large freight unmanned aerial vehicle and assembling method of assembling fixture

Abstract

The invention discloses an assembly fixture for a fuselage of a large freight unmanned aerial vehicle and an assembly method of the assembly fixture. The assembly fixture comprises a base, a fuselage positioning frame and a skin gluing frame, the fuselage positioning frame is installed in the middle of the base, sliding rails are arranged on the two sides of the base, and the skin gluing frame is divided into a left skin gluing frame and a right skin gluing frame which are arranged on the sliding rails on the two sides of the base respectively and are in sliding fit with the sliding rails; the base is provided with a servo motor for driving the left skin gluing frame and the right skin gluing frame to horizontally move along the sliding rails, and the skin gluing frames are provided with a PLC control module used for controlling the servo motor to work. The fuselage positioning frame and the skin gluing frame are integrated on the same base, and the left skin and the right skin of the whole fuselage are integrally glued through the sliding rail and the appearance clamping plate device; and the positions of the left skin and the right skin are accurately controlled by utilizing the PLC control module, so that the appearance and the position degree of the fuselage skin are ensured.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicle assembly, and in particular to an assembly jig for a large-scale cargo unmanned aerial vehicle fuselage and an assembly method thereof. Background Art

[0002] With the development of UAV technology, more and more large UAVs have emerged, especially large cargo UAVs, which are very large in size and have very high assembly requirements. UAVs include a skeleton structure and a skin structure. When assembling, it is necessary to first install beams and ribs separately, rivet the ribs on the beams through tooling positioning to form a skeleton, and finally glue the skin to the skeleton composed of beams and ribs. The skin structure surrounds the outside of the skeleton structure to form the UAV fuselage.

[0003] At present, the skeleton structure and skin structure of the UAV are assembled on their respective matching assembly tools, and then put on the shelf for the second time to realize the overall assembly. However, after the second time, coordination errors may occur between the outer skin and the skeleton, the assembly accuracy deteriorates, and the overall assembly efficiency is low, and the assembly cost is high. Summary of the invention

[0004] In order to solve the above problems, the present invention provides an assembly jig for a large cargo UAV fuselage and an assembly method thereof, which can improve the assembly efficiency and assembly quality of the UAV.

[0005] To this end, the technical solution of the present invention is: a method for assembling a large cargo drone fuselage, comprising the following steps:

[0006] S1. Use the middle column, fuselage cross beam positioner, and fuselage long beam positioner to overlap the frame structure and perform gluing and curing;

[0007] S2. After the skeleton structure is solidified, the right column and the right positioning piece of the skeleton structure are removed to make room for gluing the right skin;

[0008] S3, positioning the right skin on the right skin bonding frame, using the vacuum suction cup and the skin shape clamping plate to absorb the skin, so that the skin is closely attached to the shape clamping plate;

[0009] S4, controlling the right skin bonding frame to move toward one side of the skeleton structure through the PLC control module, and measuring the bonding gap after reaching the theoretical position;

[0010] S5. Adjust the gap according to the situation and record the bonding position of the right skin bonding frame when the bonding gap meets the requirements;

[0011] S6, controlling the right skin glued frame to move away from the skeleton structure through the PLC control module;

[0012] S7. Apply structural adhesive to the joint between the skin and the fuselage frame;

[0013] S8, controlling the right skin bonding frame to move toward the frame structure to a bonding position through the PLC control module, fixing the position of the right skin bonding frame on the slide rail using the positioning pins, and bonding and curing the right skin and the fuselage frame;

[0014] S9, referring to steps S2 to S8, completing the bonding and curing of the left side skin and the fuselage frame;

[0015] S10. After the bonding is complete, use the joint locators on the right skin bonding frame and the left skin bonding frame to respectively locate the wing-to-fuselage joint, the fuselage-to-vertical tail joint, and the fuselage-to-horizontal tail joint, and connect the fasteners.

[0016] On the basis of the above scheme and as a preferred scheme of the above scheme: in the step S9, a skin support assembly is added when gluing the left skin to ensure that the skin shape is not concave when gluing the skin and the gluing quality of the middle seam of the skin is ensured.

[0017] The second technical solution of the present invention is: an assembly jig for the fuselage of a large cargo UAV, comprising a base, a fuselage positioning frame and a skin bonding frame; the fuselage positioning frame is installed in the middle of the base, and slide rails are provided on both sides of the base, and the skin bonding frame is divided into a left skin bonding frame and a right skin bonding frame, which are respectively arranged on the slide rails on both sides of the base and slide with the slide rails; a servo motor is provided on the base to drive the left skin bonding frame and the right skin bonding frame to translate along the slide rail, and a PLC control module is provided on the skin bonding frame for controlling the operation of the servo motor.

[0018] On the basis of the above scheme and as a preferred scheme of the above scheme: a plurality of skin shape clamps and skin ear locators are provided on the opposite sides of the left skin bonding frame and the right skin bonding frame; a plurality of vacuum suction cups with different directions are provided on the left skin bonding frame and the right skin bonding frame.

[0019] On the basis of the above scheme and as a preferred scheme of the above scheme: the fuselage positioning frame includes a fuselage cross beam positioner, a fuselage long beam positioner and a column, and a fuselage frame positioning piece is provided on the column.

[0020] On the basis of the above scheme and as a preferred scheme of the above scheme: the left skin glued frame and the right skin glued frame are provided with joint locators for locating the wing-fuselage joint, the fuselage-vertical tail joint, and the fuselage-horizontal tail intersection.

[0021] On the basis of the above scheme and as a preferred scheme of the above scheme: the skin glued frame also includes a skin support assembly, which is located between the left skin glued frame and the right skin glued frame.

[0022] Compared with the prior art, the present invention has the following beneficial effects:

[0023] 1. Integrate the fuselage positioning frame and the skin bonding frame on the same base. The skin bonding frame and the base are connected by sliding rails. The left and right skins of the entire fuselage are bonded as a whole using the sliding rails and the shape clamping device. The positions of the left and right skins are precisely controlled using the PLC control module to ensure the shape and position of the fuselage skin.

[0024] 2. Suction cups and shape clamps are set on the skin bonding frame, and the skin is adsorbed by the suction cups and shape clamps. The skin is tightly attached to the shape clamps to ensure the aerodynamic shape of the body; and a skin support component is added when the left skin and the right skin are spliced ​​together to ensure that the skin shape is not concave when bonding the skin and the bonding quality of the middle seam of the skin.

[0025] 3. The use of slide rail assembly jigs can effectively improve the assembly efficiency and quality of large UAVs, reduce assembly costs, and provide new ideas for the assembly and bonding of large unmanned transport aircraft skins. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 It is a structural schematic diagram of the present invention;

[0027] Figure 2 It is a top view of the structure of the present invention;

[0028] Figure 3 It is a structural front view of the present invention;

[0029] Figure 4 It is a schematic diagram of the structure of the present invention when it is in use;

[0030] Figure 5 for Figure 4 A partial enlarged view of

[0031] Figure 6 A top view of the structure of the present invention in use;

[0032] Figure 7 It is a front view of the structure of the present invention in use.

[0033] Marked in the figure are: base 1, slide rail 11, fuselage positioning frame 2, left skin glued frame 31, right skin glued frame 32, skin shape clamping plate 33, vacuum suction cup 34, servo motor 4, PLC control module 5, and skeleton structure 6. DETAILED DESCRIPTION

[0034] In the description of the present invention, it should be noted that directional words, such as the terms "center", "lateral (X)", "longitudinal (Y)", "vertical (Z)", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", etc., indicating directions and positional relationships are based on the directions or positional relationships shown in the accompanying drawings, which are only for the convenience of narrating the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and cannot be understood as limiting the specific scope of protection of the present invention.

[0035] In addition, the terms "first" and "second" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features. Therefore, the definition of "first" and "second" features can explicitly or implicitly include one or more of the features. In the description of the present invention, "several" and "a number" mean two or more, unless otherwise clearly and specifically defined.

[0036] See the attached drawings. The assembly jig of the large cargo UAV fuselage described in this embodiment includes a base 1, a fuselage positioning frame 2 and a skin gluing frame; the fuselage positioning frame 2 is derived from the base 1, and the fuselage positioning frame 2 includes a fuselage cross beam positioner, a fuselage long beam positioner and a column, and the column is provided with a fuselage frame positioning piece. When the skeleton structure is built, the bottom is positioned by the fuselage cross beam positioner and the fuselage long beam positioner; the two sides of the skeleton are positioned by the columns and the fuselage frame positioning pieces, and after the fuselage skeleton structure is built, the columns and the fuselage frame positioning pieces on both sides are removed to facilitate the skinning operation. The fuselage cross beam positioner, the fuselage long beam positioner, the column and the fuselage frame positioning piece can be matched according to the actual structure of the UAV. This is an existing mature technology and will not be repeated here.

[0037] A plurality of parallel slide rails 11 are provided on both sides of the base 1, and the skin glued frame is divided into a left skin glued frame 31 and a right skin glued frame 32, which are respectively arranged on the slide rails 11 on both sides of the base 1 and slideably cooperate with the slide rails 11. At the same time, a servo motor 4 is provided on the base 1 to drive the left skin glued frame 31 and the right skin glued frame 32 to translate along the slide rails 11, and a PLC control module 5 is provided on the skin glued frame for controlling the operation of the servo motor 4 and accurately controlling the moving positions of the left skin glued frame 31 and the right skin glued frame 32.

[0038] A plurality of skin shape clamps 33 and skin ear piece positioners are provided on the opposite sides of the left skin glued frame 31 and the right skin glued frame 32; a plurality of vacuum suction cups 34 with different orientations are provided on the left skin glued frame 31 and the right skin glued frame 32. The skin glued frame uses suction cups and shape clamps to absorb the skin, and the skin is closely attached to the shape clamps to ensure the aerodynamic shape of the body.

[0039] The left skin bonding frame 31 and the right skin bonding frame 32 are provided with joint locators for locating the joint between the wing and the fuselage, the joint between the fuselage and the vertical tail, and the intersection between the fuselage and the horizontal tail. The skin bonding frame also includes a skin support assembly, which is located between the left skin bonding frame and the right skin bonding frame, and is used to ensure that the skin shape does not sag when bonding the skin and the bonding quality of the middle seam of the skin.

[0040] The assembly steps are as follows:

[0041] S1. Build a skeleton structure 6 on the base 1, use the middle column, fuselage cross beam positioner, and fuselage long beam positioner to position the skeleton structure, and perform gluing and curing after positioning is complete.

[0042] S2. After the skeleton structure 6 is solidified, the right column and the right positioning piece of the skeleton structure 6 are removed to make room for gluing the right skin.

[0043] S3, positioning the right skin on the right skin bonding frame 32, using the vacuum suction cup 34 and the skin shape clamping plate 33 to absorb the skin, so that the skin is closely attached to the shape clamping plate.

[0044] S4. Control the right skin bonding frame 32 to move toward the skeleton structure 6 through the PLC control module 5. After reaching the theoretical position, measure the bonding gap.

[0045] S5. If the measured value of the bonding gap does not meet the set adjustment, the gap is adjusted according to the situation, and the PLC control module 5 controls the movement and adjustment of the right skin bonding frame 32 until the right skin bonding frame 32 reaches a position that meets the bonding gap requirements. This position can be recorded as the bonding position of the right skin bonding frame 32.

[0046] S6. Control the right skin adhesive frame 32 to move away from the skeleton structure 6 through the PLC control module 5.

[0047] S7. Apply structural adhesive to the joints between the skin and the fuselage frame.

[0048] S8. Control the right skin gluing frame 32 to move toward the side of the skeleton structure 6 through the PLC control module 5, and move to the gluing position recorded in step S5. After reaching the position, use the positioning pins to fix the position of the right skin gluing frame on the slide rail, use mechanical fixation to prevent the right skin gluing frame from moving, and then glue and cure the right skin and the fuselage skeleton.

[0049] S9, referring to steps S2 to S8, completing the bonding and curing of the left side skin and the fuselage frame;

[0050] S9.1. Remove the left column and left positioning piece of the skeleton structure 6 to make room for gluing the left skin;

[0051] S9.2, positioning the left skin on the left skin bonding frame 31, using the vacuum suction cup and the skin shape clamping plate to absorb the skin, so that the skin is closely attached to the shape clamping plate;

[0052] S9.3, controlling the left skin bonding frame 31 to move toward the side of the skeleton structure 6 through the PLC control module 5, and measuring the bonding gap after reaching the theoretical position;

[0053] S9.4, if the measured value of the bonding gap does not meet the set adjustment, the gap is adjusted according to the situation, and the PLC control module 5 controls the movement and adjustment of the left skin bonding frame 31 until the left skin bonding frame 31 reaches a position that meets the bonding gap requirement, and this position can be recorded as the bonding position of the left skin bonding frame 31;

[0054] S9.5, controlling the left skin glued frame 31 to move away from the skeleton structure through the PLC control module 5;

[0055] S9.6. Apply structural adhesive to the skin and fuselage frame where they are to be glued together; add a skin support assembly when gluing the left skin to ensure that the skin shape does not sag when gluing the skin and the gluing quality of the middle seam of the skin;

[0056] S9.7. Control the left skin gluing frame 31 to move toward the side of the skeleton structure 6 through the PLC control module 5, and move to the gluing position recorded in step S9.4. After reaching the position, use the positioning pin to fix the position of the left skin gluing frame on the slide rail, use mechanical fixation to prevent the left skin gluing frame from moving, and then glue and cure the left skin and the fuselage skeleton.

[0057] S10, after the gluing is complete, the joint positioners on the right skin gluing frame 32 and the left skin gluing frame 31 are used to position the joint between the wing and the fuselage, the joint between the fuselage and the vertical tail, and the joint between the fuselage and the horizontal tail, respectively, and fasteners are connected.

[0058] S11. After the overall assembly is complete, the aerodynamic shape detection device is used to detect whether the shape of the machine body meets the technical requirements.

[0059] The assembly jig needs to be debugged before use. The large datum A is established with the base as the reference, and the TB point is set on the base datum A; the left skin glued frame is used as the reference B, and the right skin glued frame is used as the reference C. B and C are restored with the base datum A as the reference. The outside of the frame is provided with ERS points during the manufacturing process to meet the debugging requirements; ERS points are provided at the intersection to meet the joint debugging requirements; the overall accuracy of the tooling meets ±0.1mm, and the accuracy at the intersection joint can meet ±0.05mm.

[0060] The above is only a preferred embodiment of the present invention, and the protection scope of the present invention is not limited to the above embodiments. All technical solutions under the concept of the present invention belong to the protection scope of the present invention. It should be pointed out that for ordinary technicians in this technical field, some improvements and modifications without departing from the principle of the present invention should also be regarded as the protection scope of the present invention.

Claims

1. A method for assembling a large cargo drone fuselage, characterized in that: The following steps are involved: S1. Use the middle column, fuselage cross beam positioner, and fuselage long beam positioner to overlap the frame structure and perform gluing and curing; S2. After the skeleton structure is solidified, the right column and the right positioning piece of the skeleton structure are removed to make room for gluing the right skin; S3, positioning the right skin on the right skin bonding frame, using the vacuum suction cup and the skin shape clamping plate to absorb the skin, so that the skin is closely attached to the shape clamping plate; S4, controlling the right skin bonding frame to move toward one side of the skeleton structure through the PLC control module, and measuring the bonding gap after reaching the theoretical position; S5. Adjust the gap according to the situation and record the bonding position of the right skin bonding frame when the bonding gap meets the requirements; S6, controlling the right skin glued frame to move away from the skeleton structure through the PLC control module; S7. Apply structural adhesive to the joint between the skin and the fuselage frame; S8, controlling the right skin bonding frame to move toward the frame structure to a bonding position through the PLC control module, fixing the position of the right skin bonding frame on the slide rail using the positioning pins, and bonding and curing the right skin and the fuselage frame; S9, referring to steps S2 to S8, completing the bonding and curing of the left side skin and the fuselage frame; S10. After the bonding is complete, use the joint locators on the right skin bonding frame and the left skin bonding frame to respectively locate the wing-to-fuselage joint, the fuselage-to-vertical tail joint, and the fuselage-to-horizontal tail joint, and connect the fasteners.

2. The method for assembling a large cargo drone fuselage according to claim 1, characterized in that: In step S9, a skin support assembly is added when gluing the left skin, so as to ensure that the skin shape is not concave when gluing the skin and the gluing quality of the middle seam of the skin is ensured.

3. An assembly jig for a large cargo drone fuselage, characterized in that: It includes a base, a fuselage positioning frame and a skin glued frame; the fuselage positioning frame is installed in the middle of the base, and slide rails are provided on both sides of the base; the skin glued frame is divided into a left skin glued frame and a right skin glued frame, which are respectively arranged on the slide rails on both sides of the base and slide with the slide rails; a servo motor is provided on the base to drive the left skin glued frame and the right skin glued frame to translate along the slide rail, and a PLC control module is provided on the skin glued frame to control the operation of the servo motor.

4. The assembly jig for the fuselage of a large cargo drone as claimed in claim 3, characterized in that: A plurality of skin shape clamps and skin ear piece positioners are arranged on the facing sides of the left skin adhesive bonding frame and the right skin adhesive bonding frame; a plurality of vacuum suction cups with different directions are arranged on the left skin adhesive bonding frame and the right skin adhesive bonding frame.

5. The assembly jig for the fuselage of a large cargo drone as claimed in claim 3, characterized in that: The fuselage positioning frame comprises a fuselage cross beam positioner, a fuselage long beam positioner and a column, and a fuselage frame positioning piece is arranged on the column.

6. The assembly jig for the fuselage of a large cargo drone as claimed in claim 3, characterized in that: The left skin glued frame and the right skin glued frame are provided with joint locators for locating the joint between the wing and the fuselage, the joint between the fuselage and the vertical tail, and the intersection between the fuselage and the horizontal tail.

7. The assembly jig for the fuselage of a large cargo drone as claimed in claim 3, characterized in that: The skin bonding frame also includes a skin supporting assembly, which is located between the left skin bonding frame and the right skin bonding frame.

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