An arm assembly jig for a multi-copter manned aerial vehicle

Abstract

This invention discloses a jig for assembling the arms of a multi-rotor manned aircraft. The jig uses a locking mechanism to fix the arm components, further completing the assembly of the arm components. This invention utilizes a small number of parts to assemble the arms of a multi-rotor manned aircraft with high quality, reducing assembly errors. Improved assembly precision of individual arms reduces the cumulative assembly error of all arms in the multi-rotor manned aircraft, thereby reducing the difficulty of parameter control. This results in a significant reduction in yaw control throttle, improved yaw angle tracking accuracy, extended flight time, and further enhanced safety of the manned aircraft. The invention is simple to implement, easy to operate, and highly effective.

Description

Technical Field

[0001] This invention belongs to the field of assembly fixture technology, and particularly relates to an assembly fixture for the arm of a multi-rotor manned aircraft. Background Technology

[0002] In recent years, with the continuous launch of various aircraft products into the market, the corresponding production equipment has also been developing. However, there is still a lack of mature assembly fixtures in the current assembly process of multi-rotor manned aircraft arms, and the precision of manual assembly cannot be guaranteed. The arm assembly precision of existing small and medium-sized multi-rotor aircraft on the market is also not high, and manual adjustment of the arm's level with the overall aircraft is usually required after assembly, resulting in low efficiency. To address the current problems in arm assembly, it is necessary to design a structural assembly fixture for large, multi-rotor arms that meets the requirements of high-efficiency and high-quality assembly. Summary of the Invention

[0003] To address the shortcomings of existing technologies, this invention provides a jig for assembling the arm of a multirotor manned aircraft. This invention is achieved through the following technical solution: a jig for assembling the arm of a multirotor manned aircraft, applied to the arm assembly of a multirotor manned aircraft, the jig body comprising:

[0004] First swing locking mechanism, second swing locking mechanism, third swing locking mechanism, three swing locking mechanism fixing seats, motor base positioning component, clamp base, push-pull locking mechanism fixing seat, push-pull locking mechanism, locking mechanism push head and arm folding seat positioning component;

[0005] The first, second, and third swing locking mechanisms are respectively fixedly mounted on three swing locking mechanism mounting bases; the third swing locking mechanism corresponds to a swing locking mechanism mounting base; the three swing locking mechanism mounting bases are respectively fixedly mounted on a clamp base; the motor base positioning component is fixedly mounted on the clamp base; the push-pull locking mechanism is fixedly mounted on a push-pull locking mechanism mounting base, the push-pull locking mechanism mounting base is fixedly mounted on the clamp base, and the arm folding seat positioning component is fixedly mounted on the clamp base; a locking mechanism push head is fixedly mounted at the front end of the swing locking mechanism and the push-pull locking mechanism.

[0006] The arm assembly includes an arm folding base, an arm carbon tube, two pairs of locking bolts, two pairs of locking nuts, a motor base, and two pairs of rivets.

[0007] After the multi-rotor manned aircraft arm is assembled, one end of the arm carbon tube is fastened and fixed in the arm folding seat by rivets, locking bolts and locking nuts; the other end of the arm carbon tube is also fastened and fixed in the motor seat by rivets, locking bolts and locking nuts.

[0008] Furthermore, the locking mechanism push head can rotate with the swing locking mechanism, which has two states: open and locked.

[0009] Furthermore, the locking mechanism push head can move in translational motion with the push-pull locking mechanism, which has two states: open and locked.

[0010] Furthermore, the arm assembly is placed inside the fixture body for assembly during the assembly process.

[0011] Furthermore, the motor base positioning component and the arm folding base positioning component are made of No. 45 steel, and the fixture base is made of aluminum profile.

[0012] The beneficial effects of this invention are as follows:

[0013] This invention secures the arm assembly by opening and closing the locking mechanism in the fixture, further completing the assembly of the arm assembly. Since the planes of the motor mount positioning component and the arm folding seat positioning component in the arm assembly fixture are parallel, the assembly fixture can achieve high-quality assembly of the multi-rotor manned aircraft arm, ensuring that the motor mount and the upper plane of the arm folding component are as parallel as possible, thereby reducing the angular error between the arm assembly and the aircraft itself. Improved assembly precision of individual arms reduces the cumulative assembly error of all arms in the multi-rotor manned aircraft, thus reducing the difficulty of parameter control for the manned aircraft. This results in a significant reduction in yaw control throttle, improved yaw angle tracking accuracy, and extended flight time. This invention is simple to implement, easy to operate, and highly effective. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of the structure of the arm assembly fixture for a multi-rotor manned aircraft according to the present invention;

[0015] Figure 2 This is a schematic diagram of the arm assembly of the present invention after being placed into the assembly fixture;

[0016] Figure 3 This is a schematic diagram of the assembled state of the robotic arm of the present invention.

[0017] The labels in the attached diagram are as follows: 1-arm assembly, 2-clamp body, 3-first swing locking mechanism, 4-swing locking mechanism fixing seat, 5-motor seat positioning component, 6-clamp base, 7-push-pull locking mechanism fixing seat, 8-push-pull locking mechanism, 9-locking mechanism push head, 10-arm folding seat positioning component, 11-arm folding seat, 12-arm carbon tube, 13-locking bolt, 14-locking nut, 15-motor seat, 16-rivet, 17-second swing locking mechanism, 18-third swing locking mechanism. Detailed Implementation

[0018] The present invention will become clearer from the following detailed description with reference to the accompanying drawings and preferred embodiments.

[0019] The present 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 of the invention and are not intended to limit the invention.

[0020] In this invention, the material requirements are as follows: the motor base positioning component 5 and the arm folding base positioning component 10 are made of 45 steel, and the clamp base 6 is made of metal aluminum profile with high flatness.

[0021] Processing requirements: The surface roughness Ra of the contact surfaces between the motor base positioning component 5, the arm folding base positioning component 10 and the arm assembly 1 should be approximately 1.6 micrometers.

[0022] Installation requirements: The contact surfaces between the motor base positioning component 5 and the arm assembly 1 and the arm folding seat positioning component 10 and the arm assembly 1 should be as parallel as possible. If they are not parallel, leveling treatment is required.

[0023] like Figure 1 This is a schematic diagram of the arm assembly fixture structure for a multi-rotor manned aircraft according to the present invention, including an arm assembly 1 and a fixture body 2.

[0024] The fixture body 2 includes a first swing locking mechanism 3, a second swing locking mechanism 17, a third swing locking mechanism 18, three swing locking mechanism fixing seats, a motor base positioning component 5, a fixture base 6, a push-pull locking mechanism fixing seat 7, a push-pull locking mechanism 8, a locking mechanism push head 9, and a machine arm folding seat positioning component 10.

[0025] The first swing locking mechanism 3, the second swing locking mechanism 17, and the third swing locking mechanism 18 are respectively fixed to the three swing locking mechanism mounting bases by bolt fastening; the third swing locking mechanism 18 corresponds to the swing locking mechanism mounting base 4; and all three swing locking mechanism mounting bases are fixed to the clamp base 6 by bolt and nut locking; the motor base positioning component 5 is fixed to the clamp base 6 by bolt and nut locking; the push-pull locking mechanism 8 is fixed to the push-pull locking mechanism mounting base 7 by nut locking, the push-pull locking mechanism mounting base 7 is fixed to the clamp base 6 by bolt and nut locking, and the arm folding seat positioning component 10 is fixed to the clamp base 6 by bolt and nut locking; the front end of the first swing locking mechanism 3 and the push-pull locking mechanism 8 is fixed with a locking mechanism push head 9.

[0026] The front locking mechanism push head 9 can rotate with the first swing locking mechanism 3, which has two states: open and locked.

[0027] The front locking mechanism push head 9 can move in translation with the push-pull locking mechanism 8, which has two states: open and locked.

[0028] The arm assembly 1 includes an arm folding seat 11, an arm carbon tube 12, four locking bolts 13, four locking nuts 14, a motor base 15, and four rivets 16;

[0029] After the multi-rotor manned aircraft arm is assembled, one end of the arm carbon tube 12 is fixed in the arm folding seat 11 by riveting with rivets 16 and fastening with locking bolts 13 and locking nuts 14; the other end of the arm carbon tube 12 is also fixed in the motor seat 15 by riveting with rivets 16 and fastening with locking bolts 13 and locking nuts 14.

[0030] like Figure 2 This is a schematic diagram of the robotic arm assembly of the present invention after being placed in the assembly fixture. The robotic arm assembly 2 is placed in the fixture body 1 for assembly during the assembly process. In the figure, the first swing locking mechanism 3, the second swing locking mechanism 17, the third swing locking mechanism 18 and the push-pull locking mechanism 8 are in the open state.

[0031] like Figure 3 This is a schematic diagram of the assembly state of the arm of the present invention. In the figure, the first swing locking mechanism 3, the second swing locking mechanism 17, the third swing locking mechanism 18 and the push-pull locking mechanism 8 are in the locked state.

[0032] The working process of this invention is as follows: The two ends of the arm carbon tube 12 are respectively placed into the arm folding seat 11 and the motor seat 15, and then the entire arm assembly 2 is placed into the fixture body 1. The motor seat 15 is placed into the motor seat positioning member 5, and the arm folding seat 11 is placed into the arm folding seat positioning member 10. Next, the arm carbon tube 12 is rotated and positioned so that its holes align with the holes on the arm folding seat 11 and the motor seat 15. Next, the push-pull locking mechanism 8 is switched from the open state to the locked state. At this time, the arm folding seat 11, arm carbon tube 12, motor seat 15, and motor seat positioning member 5 are under continuous force clamping and are fixed horizontally. Then, the first swing locking mechanism 3, the second swing locking mechanism 17, and the third swing locking mechanism 18 are switched from the open state to the locked state. At this time, the motor seat 15 and the arm folding seat 11 are under force clamping and are fixed vertically. Next, insert the two pairs of rivets 16 at both ends into the holes of the motor base 15 and the carbon tube 12 of the arm, and then insert the rivets 16 into the holes of the arm folding seat 11 and the carbon tube 12 of the arm, completing the riveting work with a tool. Then, pass the two pairs of bolts 13 and locking nuts 14 through the holes at the lower end of the motor base 15 to secure them, thus tightening the motor base 15 and the carbon tube 12 of the arm. Similarly, pass the two pairs of locking bolts 13 and locking nuts 14 through the holes at the lower end of the arm folding seat 11 to secure it, thus tightening the arm folding seat 11 and the carbon tube 12 of the arm. This completes the assembly of the arm. To remove the assembled arm, open the first swing locking mechanism 3, the second swing locking mechanism 17, and the third swing locking mechanism 18, along with the push-pull locking mechanism 8, and then remove it.

[0033] The above description is merely a preferred embodiment of the present invention and does not constitute any limitation on the structure of the present invention. Any simple modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of the present invention shall fall within the protection scope of the present invention.

Claims

1. A jig for assembling the arm of a multi-rotor manned aircraft, characterized in that, Its arm assembly (1) used in multi-rotor manned aircraft, the clamp body (2) includes: First swing locking mechanism (3), second swing locking mechanism (17), third swing locking mechanism (18), three swing locking mechanism fixing seats, motor seat positioning component (5), clamp base (6), push-pull locking mechanism fixing seat (7), push-pull locking mechanism (8), locking mechanism push head (9) and arm folding seat positioning component (10). The first swing locking mechanism (3), the second swing locking mechanism (17), and the third swing locking mechanism (18) are respectively fixedly mounted on three swing locking mechanism mounting seats; the third swing locking mechanism (18) corresponds to the swing locking mechanism mounting seat (4); the three swing locking mechanism mounting seats are respectively fixedly mounted on the clamp base (6); the motor base positioning component (5) is fixedly mounted on the clamp base (6); the push-pull locking mechanism (8) is fixedly mounted on the push-pull locking mechanism mounting seat (7), and the push-pull locking mechanism... The fixed seat (7) is fixedly set on the clamp base (6), and the arm folding seat positioning component (10) is fixedly set on the clamp base (6); a locking mechanism push head (9) is fixedly set at the front end of the swing locking mechanism (3) and the push-pull locking mechanism (8); the locking mechanism push head (9) can rotate with the swing locking mechanism, and the swing locking mechanism has two states: open and locked; the locking mechanism push head (9) can translate with the push-pull locking mechanism (8), and the push-pull locking mechanism (8) has two states: open and locked.

2. The arm assembly fixture for a multi-rotor manned aircraft according to claim 1, characterized in that, The arm assembly (1) includes an arm folding seat (11), an arm carbon tube (12), two pairs of locking bolts (13), two pairs of locking nuts (14), a motor seat (15), and two pairs of rivets (16). After the multi-rotor manned aircraft arm is assembled, one end of the arm carbon tube (12) is riveted with rivets (16) and fastened and fixed in the arm folding seat (11) by locking bolts (13) and locking nuts (14); the other end of the arm carbon tube (12) is also riveted with rivets (16) and fastened and fixed in the motor seat (15) by locking bolts (13) and locking nuts (14).

3. The arm assembly fixture for a multi-rotor manned aircraft according to claim 1, characterized in that, The arm assembly (1) is placed inside the fixture body (2) during the assembly process for assembly.

4. The arm assembly fixture for a multi-rotor manned aircraft according to claim 1, characterized in that, The motor base positioning component (5) and the arm folding base positioning component (10) are made of No. 45 steel, and the clamp base (6) is made of aluminum profile.

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