Complete machine test and maintenance platform for unmanned aerial vehicle

Abstract

The utility model discloses an unmanned aerial vehicle complete machine test and maintenance platform, and relates to the field of unmanned aerial vehicle maintenance. The platform comprises a platform body, a plurality of first universal flexible shafts and second universal flexible shafts are fixedly installed on the front side of an installation plate, wing clamps are arranged at one ends of the first universal flexible shafts, and fuselage clamps are arranged at one ends of the second universal flexible shafts. The positions of the fixed wings and the fuselage are flexibly adjusted through position movement of the first universal flexible shaft and the second universal flexible shaft, so that maintenance personnel can easily perform multi-directional butt joint on the broken wings and the fuselage, and do not need to manually adjust or splice parts with great effort, so that the maintenance convenience is greatly improved, and the maintenance efficiency is improved. Therefore, the stable posture can be kept in the butt joint process, the more accurate butt joint effect can be achieved, the maintenance quality and efficiency are improved, and great significance is achieved for rapid recovery and use of the unmanned aerial vehicle.

Description

Technical Field

[0001] The utility model relates to the field of unmanned aerial vehicle maintenance, in particular to a complete unmanned aerial vehicle testing and maintenance platform. Background Art

[0002] The drone maintenance tool table is an integrated workbench designed specifically for drone maintenance. It integrates multiple functions such as tool storage, parts storage, and a spacious work surface, making it convenient for maintenance personnel to quickly access tools and replace parts. Its stable and durable structure and easy-to-clean surface material ensure the smooth progress of maintenance work and a clean environment.

[0003] When the existing UAV whole machine testing and maintenance platform is repairing the UAV, the damage to the UAV is mostly "explosion" and the fuselage and wings are broken. During maintenance, maintenance personnel often need to piece together the broken parts of each part and then carry out maintenance. When there are many broken parts, it is difficult to piece them together, which undoubtedly reduces the convenience of UAV maintenance. Utility Model Content

[0004] Based on this, the purpose of the utility model is to provide a UAV whole machine testing and maintenance platform to solve the technical problem that the existing UAV maintenance platform is less convenient when piecing together multiple broken parts.

[0005] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a UAV whole machine testing and maintenance platform, including a platform body, a tool wall is installed on the top side of the platform body, a support assembly is installed on the front side of the tool wall, the support assembly includes a mounting plate, a plurality of first universal joint flexible shafts and second universal joint flexible shafts are fixedly installed on the front side of the mounting plate, a wing clamp is provided at one end of the first universal joint flexible shaft, and a body clamp is provided at one end of the second universal joint flexible shaft.

[0006] By adopting the above technical solution, the positions of the first universal joint flexible shaft and the second universal joint flexible shaft are moved, so that the fixed wing and fuselage can be flexibly adjusted, so that maintenance personnel can easily dock the broken wing and fuselage in all directions without the need for laborious manual adjustment or piecing together parts, thereby greatly improving the convenience of maintenance.

[0007] Furthermore, the wing clamp includes a first spring sheet and a second spring sheet, the first spring sheet is threadedly connected with a tightening hand wheel, and the tightening hand wheel passes through the second spring sheet through a through hole, so as to adjust the distance between the first spring sheet and the second spring sheet.

[0008] By adopting the above technical solution, the wing can be firmly clamped in the fixture, providing a stable operating basis for subsequent maintenance work. At the same time, the tightening handwheel threaded on the first spring sheet passes through the second spring sheet through the through hole. This structure allows maintenance personnel to easily adjust the distance between the first spring sheet and the second spring sheet by rotating the tightening handwheel.

[0009] Furthermore, guide grooves are formed on opposite sides of the ends of the first spring piece and the second spring piece, and clamping grooves are formed on opposite sides of the first spring piece and the second spring piece.

[0010] By adopting the above technical solution, the wing can enter the clamp more smoothly during the clamping process, reducing the clamping difficulty caused by position deviation or misalignment.

[0011] Furthermore, the fuselage clamp comprises a fixing plate, a sliding groove is formed in the middle of the fixing plate, and clamping plates are slidably connected at both ends of the fixing plate through the sliding groove.

[0012] By adopting the above technical solution, the fixed plate serves as the main part of the clamp, providing a stable supporting structure. At the same time, the sliding groove formed in the middle of the fixed plate allows the clamping plate to be slidably connected in the sliding groove. This sliding connection mechanism enables the clamping plate to be flexibly adjusted according to the shape and size of the fuselage, thereby achieving a more stable clamping.

[0013] Furthermore, two groups of tension springs are installed between a single clamping plate and the inner wall of the sliding groove, and a plurality of friction strips are arranged on the inner surface of the clamping plate in an equidistant linear arrangement.

[0014] By adopting the above technical solution, the clamping plate can maintain a firm clamp on the fuselage through the tension of the tension spring when there is no external force. When the fuselage needs to be placed or removed, the maintenance personnel can easily overcome the tension of the tension spring and move the clamping plate, thereby conveniently adjusting the clamp to adapt to fuselages of different sizes.

[0015] Furthermore, a plurality of parts boxes are installed above the front side of the tool wall, and a plurality of hangers are installed below the front side of the tool wall.

[0016] By adopting the above technical solution, maintenance personnel can conveniently classify and store commonly used parts and accessories for quick access. During the maintenance process, they can quickly find the required parts, which greatly improves maintenance efficiency.

[0017] Furthermore, a socket strip is installed on one side of the top of the platform body, and the socket strip is electrically connected to an external power source.

[0018] By adopting the above technical solution, maintenance personnel can easily connect various power tools or test equipment during work without having to look for additional power sockets, which greatly improves the convenience of work. The position of the socket strip is reasonably set, which will not interfere with maintenance operations and ensure that the power cord is long enough to meet the use requirements of various equipment.

[0019] In summary, the utility model mainly has the following beneficial effects:

[0020] 1. The utility model realizes flexible position adjustment of the fixed wing and fuselage by moving the positions of the support assembly, the first universal flexible shaft and the second universal flexible shaft, so that maintenance personnel can easily dock the broken wing with the fuselage in all directions without the need for laborious manual adjustment or piecing together of parts, thereby greatly improving the convenience of maintenance. At the same time, since the wing and the fuselage are firmly clamped in the corresponding fixture, they can maintain a stable posture during the docking process, which helps to achieve a more accurate docking effect. The setting of this maintenance platform not only simplifies the maintenance process, but also improves the maintenance quality and efficiency, which is of great significance for the rapid recovery and use of the UAV;

[0021] 2. The utility model provides a parts box, a hanger, and a socket strip. The parts box allows maintenance personnel to conveniently classify and store commonly used parts and accessories for quick access. During the maintenance process, they can quickly find the required parts, which greatly improves the maintenance efficiency. At the same time, the hanger provides a stable hanging and storage position for maintenance tools, allowing maintenance personnel to easily hang the tools neatly, which not only saves space, but also makes the work area more tidy and orderly, further improving the convenience of maintenance work. In addition, the socket strip allows maintenance personnel to easily access various power tools or test equipment without having to find an additional power socket, and its electrical connection with the external power supply ensures a stable supply of power during the maintenance process, ensuring the smooth progress of the maintenance work. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a three-dimensional structural schematic diagram of the utility model;

[0023] Figure 2 This is a schematic diagram of the main structure of the utility model;

[0024] Figure 3 This is a schematic diagram of the structure of the wing clamp of the utility model;

[0025] Figure 4 It is a structural schematic diagram of the fuselage clamp of the utility model;

[0026] Figure 5 It is a schematic diagram of the exploded structure of the fuselage clamp of the utility model.

[0027] In the figure: 1. Platform body; 2. Tool wall; 3. Parts box; 4. Hanger; 5. Socket strip; 6. Support assembly; 601. Mounting plate; 602. First universal flexible shaft; 603. Second universal flexible shaft; 7. Wing clamp; 701. First spring sheet; 702. Second spring sheet; 703. Guide groove; 704. Tightening hand wheel; 705. Clamping groove; 8. Fuselage clamp; 801. Fixed plate; 802. Sliding groove; 803. Clamping sheet; 804. Tension spring; 805. Friction strip. DETAILED DESCRIPTION

[0028] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. The embodiments described below with reference to the drawings are exemplary and are only used to explain the utility model, and cannot be understood as limiting the utility model.

[0029] In the description of the present invention, it should be noted that the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside", etc. indicate directions or positional relationships based on the directions or positional relationships shown in the accompanying drawings. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction. Therefore, they cannot be understood as limitations on the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance.

[0030] In the description of the present utility model, it should be noted that, unless otherwise clearly stipulated and limited, the terms "install", "connect", "connect", and "set" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral 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; it can be the internal connection of two components. For ordinary technicians in this field, the specific meanings of the above terms in the utility model can be understood according to specific circumstances.

[0031] The following describes an embodiment of the utility model based on its overall structure.

[0032] Embodiment 1:

[0033] A UAV whole machine testing and maintenance platform, such as Figure 1-Figure 5As shown, it includes a platform body 1, a tool wall 2 is installed on one side of the top of the platform body 1, a support assembly 6 is installed on the front side of the tool wall 2, and the support assembly 6 includes a mounting plate 601, and a plurality of first universal flexible shafts 602 and second universal flexible shafts 603 are fixedly installed on the front side of the mounting plate 601, a wing clamp 7 is arranged at one end of the first universal flexible shaft 602, and a fuselage clamp 8 is arranged at one end of the second universal flexible shaft 603. The position movement of the first universal flexible shaft 602 and the second universal flexible shaft 603 realizes flexible position adjustment of the fixed wing and fuselage, so that maintenance personnel can easily dock the broken wing with the fuselage in multiple directions without the need for laborious manual adjustment or piecing together parts, thereby greatly improving the convenience of maintenance. At the same time, since the wing and the fuselage are firmly clamped in the corresponding clamps, they can maintain a stable posture during the docking process, which is conducive to achieving a more accurate docking effect, which not only simplifies the maintenance process, but also improves the maintenance quality and efficiency, which is of great significance for the rapid recovery and use of the UAV.

[0034] See also Figure 1 , Figure 2 , Figure 3 The wing clamp 7 includes a first spring sheet 701 and a second spring sheet 702. A tightening hand wheel 704 is threadedly connected to the first spring sheet 701, and the tightening hand wheel 704 passes through the second spring sheet 702 through a through hole, so as to adjust the distance between the first spring sheet 701 and the second spring sheet 702. The wing can be firmly clamped in the clamp, providing a stable operating basis for subsequent maintenance work. At the same time, the tightening hand wheel 704 threadedly connected to the first spring sheet 701 passes through the second spring sheet 702 through a through hole. This structure enables maintenance personnel to easily adjust the distance between the first spring sheet 701 and the second spring sheet 702 by rotating the tightening hand wheel 704. This adjustment mechanism not only adapts to wings of different sizes, but also ensures that the wing will not be damaged by excessive pressure during the clamping process, thereby improving the flexibility and safety of maintenance.

[0035] See also Figure 1 , Figure 2 , Figure 3 Guide grooves 703 are formed on opposite sides of the ends of the first spring piece 701 and the second spring piece 702, and clamping grooves 705 are provided on opposite sides of the first spring piece 701 and the second spring piece 702, so that the wing can enter the clamp more smoothly during the clamping process, reducing the clamping difficulty caused by position deviation or misalignment. At the same time, the clamping grooves 705 provided on opposite sides of the first spring piece 701 and the second spring piece 702 provide stable clamping points for the wing. These clamping grooves 705 can effectively disperse the clamping force to prevent the wing from being damaged by excessive local pressure during maintenance.

[0036] Embodiment 2:

[0037] See also Figure 1 , Figure 2 , Figure 4 , Figure 5 The fuselage clamp 8 includes a fixing plate 801, a sliding groove 802 is formed in the middle of the fixing plate 801, and both ends of the fixing plate 801 are slidably connected with clamping pieces 803 through the sliding groove 802. The fixing plate 801, as the main part of the clamp, provides a stable supporting structure. At the same time, the sliding groove 802 formed in the middle of the fixing plate 801 allows the clamping piece 803 to be slidably connected in the sliding groove 802. This sliding connection mechanism enables the clamping piece 803 to be flexibly adjusted according to the shape and size of the fuselage, thereby achieving more stable clamping. When different models of drones need to be repaired, it can quickly adapt to changes in the fuselage, thereby improving the versatility and practicality of the clamp.

[0038] See also Figure 1 , Figure 2 , Figure 4 , Figure 5 Two groups of tension springs 804 are installed between a single clamping piece 803 and the inner wall of the sliding groove 802, and a plurality of friction strips 805 are arranged on the inner surface of the clamping piece 803 in an equidistant linear arrangement, so that the clamping piece 803 can maintain a firm clamp on the fuselage through the tension of the tension spring 804 when there is no external force. When the fuselage needs to be placed or removed, the maintenance personnel can easily overcome the tension of the tension spring 804 and move the clamping piece 803, so as to conveniently adjust the clamp to adapt to fuselages of different sizes. At the same time, a plurality of friction strips 805 are arranged on the inner surface of the clamping piece 803 in an equidistant linear arrangement, which increases the friction between the clamping piece 803 and the fuselage, making the clamping more stable and preventing the fuselage from accidentally sliding or shifting during the maintenance process, which not only improves the safety of maintenance, but also ensures the accuracy of maintenance, because the stable clamping of the fuselage is the basis for maintenance work.

[0039] See also Figure 1 , Figure 2 A plurality of parts boxes 3 are installed on the upper front side of the tool wall 2, and a plurality of hangers 4 are installed on the lower front side of the tool wall 2, so that maintenance personnel can conveniently classify and store commonly used parts and accessories for quick access. During the maintenance process, the required parts can be quickly found, which greatly improves the maintenance efficiency. At the same time, the plurality of hangers 4 installed on the lower front side of the tool wall 2 provide a stable hanging and storage position for maintenance tools, so that maintenance personnel can easily hang the tools neatly, which not only saves space, but also makes the working area more tidy and orderly. When needed, the tools are readily available, which further improves the convenience of maintenance work.

[0040] See also Figure 1 , Figure 2A socket strip 5 is installed on one side of the top of the platform body 1, and the socket strip 5 is electrically connected to an external power source, so that maintenance personnel can easily access various power tools or test equipment during work without having to find an additional power socket, which greatly improves the convenience of work. The position of the socket strip is reasonably set, which will not interfere with the maintenance operation, and can ensure that the length of the power cord is sufficient to meet the use requirements of various equipment. At the same time, the socket strip 5 is electrically connected to an external power source, ensuring a stable supply of power during the maintenance process, avoiding unstable power supply or power outages caused by too long a power cord or improper socket position, and ensuring the smooth progress of maintenance work.

[0041] The implementation principle of the utility model is as follows: in view of the "explosion" situation, a repair plan for the broken wings of the UAV is provided. First, the broken wing is placed inside the clamping groove 705 between the first spring sheet 701 and the second spring sheet 702, and then the tightening hand wheel 704 is turned. The threaded connection between the tightening hand wheel 704 and the first spring sheet 701 is used to adjust the distance between the first spring sheet 701 and the second spring sheet 702 to achieve the clamping and limiting operation of the wing. Then, the two sets of clamping sheets 803 on both sides of the fixing plate 801 are pulled, so that the clamping sheets 803 overcome the tension springs. The tension of the tension spring 804 is used to move the position, thereby increasing the distance between the two sets of clamping plates 803. Then, the UAV fuselage that needs to be repaired is placed between the two sets of clamping plates 803. Subsequently, the force applied to the clamping plates 803 is released, and the tension of the tension spring 804 on the clamping plates 803 is used to clamp the inner fuselage. After that, the position of the fixed wing and fuselage is moved by moving the first universal joint 602 and the second universal joint 603, so as to achieve multi-directional docking of the broken wing and fuselage, thereby improving the convenience of UAV maintenance.

[0042] Parts not involved in the present invention are the same as the prior art or can be implemented by using the prior art, and will not be described in detail here.

[0043] Although an embodiment of the utility model has been shown and described, this specific embodiment is only an explanation of the utility model and is not a limitation of the utility model. The specific features, structures, materials or characteristics described may be combined in a suitable manner in any one or more embodiments or examples. After reading this specification, those skilled in the art may make modifications, substitutions and variations to the embodiments without creative contribution as needed without departing from the principles and purpose of the utility model. However, as long as they are within the scope of the claims of the utility model, they are protected by patent law.

Claims

1. A UAV whole machine testing and maintenance platform, characterized by: The invention comprises a platform body (1), a tool wall (2) is installed on one side of the top of the platform body (1), a support assembly (6) is installed on the front side of the tool wall (2), and the support assembly (6) comprises a mounting plate (601), a plurality of first universal flexible shafts (602) and second universal flexible shafts (603) are fixedly installed on the front side of the mounting plate (601), a wing clamp (7) is arranged at one end of the first universal flexible shaft (602), and a body clamp (8) is arranged at one end of the second universal flexible shaft (603).

2. The UAV whole machine testing and maintenance platform according to claim 1 is characterized by: The wing clamp (7) comprises a first spring sheet (701) and a second spring sheet (702); a tightening hand wheel (704) is threadedly connected to the first spring sheet (701); and the tightening hand wheel (704) passes through the second spring sheet (702) through a through hole, so as to adjust the distance between the first spring sheet (701) and the second spring sheet (702).

3. The UAV whole machine testing and maintenance platform according to claim 2 is characterized by: The first spring piece (701) and the second spring piece (702) are provided with guide grooves (703) on opposite sides of their ends, and the first spring piece (701) and the second spring piece (702) are provided with clamping grooves (705) on opposite sides thereof.

4. The UAV whole machine testing and maintenance platform according to claim 1 is characterized by: The fuselage clamp (8) comprises a fixing plate (801), a sliding groove (802) is formed in the middle of the fixing plate (801), and clamping plates (803) are slidably connected at both ends of the fixing plate (801) through the sliding groove (802).

5. The UAV complete machine testing and maintenance platform according to claim 4 is characterized by: Two groups of tension springs (804) are installed between a single clamping piece (803) and the inner wall of the sliding groove (802), and a plurality of friction strips (805) are arranged on the inner surface of the clamping piece (803) in an equidistant linear arrangement.

6. The UAV complete machine testing and maintenance platform according to claim 1 is characterized by: A plurality of parts boxes (3) are installed above the front side of the tool wall (2), and a plurality of hangers (4) are installed below the front side of the tool wall (2).

7. The UAV whole machine testing and maintenance platform according to claim 1 is characterized by: A socket strip (5) is installed on one side of the top of the platform body (1), and the socket strip (5) is electrically connected to an external power source.

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