Aircraft part maintenance and detection device and use method thereof

Abstract

The invention discloses an aircraft part maintenance and detection device and a use method thereof, and belongs to the technical field of part maintenance. A pushing mechanism is arranged on a top plate of the shell, a visual detection camera is installed on the inner top face of the shell, the interior of the shell is slidably connected with a horizontally-arranged sliding plate through a transmission mechanism, a self-clamping mechanism is fixed to the sliding plate, the sliding plate can slidably stretch out of the outer side of the shell, and the self-clamping mechanism and the visual detection camera are arranged in a matched mode. The self-clamping mechanism is connected with the pushing mechanism in a matched mode. The two self-clamping mechanisms can be moved to the position below a visual inspection camera in sequence to be overhauled, meanwhile, the self-clamping mechanism on the other side is allowed to be moved out of a shell to replace aircraft parts, and the time needed for material replacement is shortened. In addition, due to the automatic clamping and limiting releasing functions, the operation process is simplified, and the overall efficiency of aircraft part maintenance and detection is improved.

Description

Technical Field

[0001] The invention relates to an aircraft component maintenance and detection device and a use method thereof, belonging to the technical field of component maintenance. Background Art

[0002] To ensure that the aircraft continues to maintain good flight condition, its parts must undergo rigorous maintenance and inspection after a period of use. This is to identify and repair any potential defects or wear that may affect the overall safety and reliability of the aircraft.

[0003] In traditional maintenance and inspection devices, the positioning of aircraft parts usually relies on manual operation. Before the maintenance and inspection begins, the staff needs to manually fix the parts on the device to prevent them from moving or causing accidents during the inspection. Similarly, after the maintenance and inspection is completed, the staff also needs to manually release the positioning measures so that the parts can be reinstalled on the aircraft.

[0004] This method that relies on manual operation is not only cumbersome, but also time-consuming and labor-intensive, affecting the efficiency of aircraft component maintenance and overhaul, adding unnecessary time costs, and may cause delays in the timely repair and return to service of the aircraft. Summary of the invention

[0005] In order to solve the problems existing in the background technology, the present invention provides an aircraft parts maintenance and detection device and a use method thereof.

[0006] To achieve the above-mentioned purpose, the present invention adopts the following technical scheme: an aircraft parts maintenance and inspection device, including a shell, a slide plate, a visual inspection camera, a pushing mechanism, a transmission mechanism and a self-clamping mechanism; the top plate of the shell is provided with a pushing mechanism, the inner top surface of the shell is installed with a visual inspection camera, the interior of the shell is slidably connected to the horizontally arranged slide plate through a transmission mechanism, the slide plate is fixed with a self-clamping mechanism and the slide plate can be slidably extended to the outside of the shell, the self-clamping mechanism is arranged in conjunction with the visual inspection camera, and the self-clamping mechanism is connected in conjunction with the pushing mechanism.

[0007] The self-clamping mechanism includes a frame, a load-bearing plate, a sliding rod, a slider and a clamping plate; the frame is fixed to the upper end of the slide plate, a horizontally arranged load-bearing plate is fixed to one end inside the frame, a horizontally arranged sliding rod is fixed to the lower end of the load-bearing plate, both ends of the sliding rod are fixedly connected to the frame, a sliding rod is slidably sleeved on the outer side of the sliding rod, and a clamping plate is installed on the upper end of the slider.

[0008] The upper end of the sliding block is detachably and fixedly connected with a clamping plate.

[0009] A spring is sleeved on the outer side of the slide bar, one end of the spring abuts against the slide block, and the other end of the spring abuts against the frame.

[0010] The pushing mechanism includes an automatic telescopic rod and a baffle; the top plate of the shell is fixedly connected to the fixed end of the vertically arranged automatic telescopic rod, the movable end of the automatic telescopic rod extends into the interior of the shell and the movable end of the automatic telescopic rod is fixedly connected to the baffle, and the baffle is cooperatively connected to the splint.

[0011] The transmission mechanism includes a rack, a motor and a gear; the inner bottom surface of the shell is fixedly connected to the vertically arranged motor, the output shaft of the motor is coaxially fixedly connected to the horizontally arranged gear, and the lower end of the skateboard is fixed with a horizontally arranged rack, and the rack is meshingly connected to the gear.

[0012] Self-clamping mechanisms are fixed at both ends of the upper surface of the slide, and the two self-clamping mechanisms are symmetrically arranged. The top plate of the shell is provided with two pushing mechanisms, and the two pushing mechanisms are located on both sides of the visual detection camera. Each pushing mechanism is respectively connected with the corresponding self-clamping mechanism.

[0013] A method for using an aircraft parts maintenance and detection device of the present invention comprises the following steps:

[0014] S1: placing an aircraft component to be inspected on a carrying plate of one of the self-clamping mechanisms;

[0015] S2: The movable end of the automatic telescopic rod extends, causing the baffle to move downward;

[0016] S3: Turn on the power of the motor, the motor drives the gear to rotate, the gear drives the rack to move, the rack drives the slide to slide, the slide drives the aircraft parts to be inspected in the clamping mechanism to move to the bottom of the visual inspection camera, the baffle plate and the clamping plate are pushed to automatically clamp the aircraft parts to be inspected, and the motor stops working;

[0017] S4: placing another aircraft component to be inspected on a carrying plate of another self-clamping mechanism;

[0018] S5: A visual inspection camera performs appearance damage inspection on the aircraft parts to be inspected in S1;

[0019] S6: The staff uses hand-held tools to repair the aircraft parts to be repaired as described in S1;

[0020] S7: After the maintenance is completed, the motor is reversed to move the repaired aircraft component out of the housing, and at the same time, another aircraft component to be repaired in S4 is moved into the housing. The working process of the other aircraft component to be repaired in S4 is the same as that of the aircraft component to be repaired in S1;

[0021] S8: The clamp loses its limit and resets under the elastic force of the spring, which automatically releases the limit of the aircraft parts that have been repaired;

[0022] S9: After taking out the repaired aircraft parts, put in new aircraft parts to be repaired, and repeat the above working process.

[0023] Compared with the prior art, the present invention has the following beneficial effects:

[0024] The present invention realizes the reciprocating movement of the slide plate by meshing the gear and the rack driven by the motor, so that the two self-clamping mechanisms can be moved to the bottom of the visual inspection camera for inspection in turn, while allowing the self-clamping mechanism on the other side to be moved out of the shell for replacement of aircraft parts, effectively reducing the time required for material replacement. In addition, the baffle at the lower end of the automatic telescopic rod cooperates with the clamping plate to automatically clamp the aircraft parts during feeding, ensuring the stability of the inspection work; and when discharging, the spring elastic force pushes the slider to reset, driving the clamping plate to automatically release the limit on the aircraft parts, facilitating the rapid replacement of the inspected parts. The function of automatic clamping and limit release not only simplifies the operation process, but also improves the overall efficiency of aircraft parts maintenance and inspection. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 It is a schematic diagram of the structure of the present invention;

[0026] Figure 2 yes Figure 1 Bottom view of

[0027] Figure 3 yes Figure 2 Enlarged view of point A. DETAILED DESCRIPTION

[0028] The technical solution of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0029] A device for aircraft component maintenance and inspection comprises a shell 1, a slide plate 2, a visual inspection camera 11, a pushing mechanism, a transmission mechanism and a self-clamping mechanism; the top plate of the shell 1 is provided with a pushing mechanism, the inner top surface of the shell 1 is installed with a visual inspection camera 11, the interior of the shell 1 is slidably connected with the horizontally arranged slide plate 2 through a transmission mechanism, the slide plate 2 is fixed with a self-clamping mechanism and the slide plate 2 can be slidably extended to the outside of the shell 1, specifically: a through groove is provided on the side of the shell 1, and limiting blocks 3 are fixed on the inner walls on both sides of the through groove, and sliding grooves are provided on both side walls of the slide plate 2, and two limiting blocks 3 are respectively slidably connected with corresponding sliding grooves, so that the slide plate 2 can stably slide between the through grooves, that is, it can stably drive the aircraft components to enter and exit the shell 1; the self-clamping mechanism is arranged in coordination with the visual inspection camera 11, and the self-clamping mechanism is connected in coordination with the pushing mechanism.

[0030] The self-clamping mechanism includes a frame 4, a supporting plate 5, a sliding rod 6, a slider 8 and a clamping plate 9; the frame 4 is fixed to the upper end of the slide plate 2, a horizontally arranged supporting plate 5 is fixed to one end inside the frame 4, the outer wall of the supporting plate 5 is fixedly connected to the inner wall of the frame 4, a horizontally arranged sliding rod 6 is fixed to the lower end of the supporting plate 5, the sliding rod 6 is arranged along the moving direction of the slide plate 2 and both ends of the sliding rod 6 are fixedly connected to the frame 4, a slider 8 is slidably sleeved on the outer side of the sliding rod 6, both side walls of the slider 8 are slidably fitted with the corresponding inner side walls of the frame 4 or the lower end of the slider 8 is slidably connected to the upper surface of the slide plate 2 through a slide groove slider, so that the slider 8 can slide stably, and a clamping plate 9 is installed on the upper end of the slider 8.

[0031] The upper end of the slider 8 is detachably fixedly connected with a clamping plate 9 by bolt thread locking, so that the clamping plate 9 can be easily removed from the slider 8. When limiting aircraft parts of different sizes, clamping plates 9 of different thicknesses can be replaced.

[0032] A spring 7 is sleeved on the outer side of the slide rod 6, one end of the spring 7 abuts against the slider 8, and the other end of the spring 7 abuts against the frame 4. In a natural state, the elastic force of the spring 7 will push the slider 8 to the side away from the supporting plate 5, that is, it can automatically release the limit on the aircraft parts.

[0033] The pushing mechanism includes an automatic telescopic rod 10 and a baffle 12; the top plate of the shell 1 is fixedly connected to the fixed end of the vertically arranged automatic telescopic rod 10 (such as an electric push rod, a cylinder, a hydraulic cylinder, etc.), the movable end of the automatic telescopic rod 10 extends into the interior of the shell 1 and the movable end of the automatic telescopic rod 10 is fixedly connected to the baffle 12, and the baffle 12 is cooperatively connected to the splint 9.

[0034] The transmission mechanism includes a rack 13, a motor 14 and a gear 15; the inner bottom surface of the shell 1 is fixedly connected to the vertically arranged motor 14, the output shaft of the motor 14 is coaxially fixedly connected to the horizontally arranged gear 15, and the lower end of the skateboard 2 is fixed with a horizontally arranged rack 13, and the rack 13 is meshingly connected with the gear 15.

[0035] In order to improve production efficiency, the pushing mechanism and the self-clamping mechanism are provided in two sets for alternating use, namely: self-clamping mechanisms are fixed at both ends of the upper surface of the skateboard 2, and the two self-clamping mechanisms are symmetrically arranged. The top plate of the shell 1 is provided with two pushing mechanisms, and the two pushing mechanisms are located on both sides of the visual detection camera 11, and each pushing mechanism is respectively connected with the corresponding self-clamping mechanism.

[0036] A method for using an aircraft parts maintenance and detection device of the present invention comprises the following steps:

[0037] S1: placing an aircraft component to be repaired on a carrying plate 5 of one of the self-clamping mechanisms;

[0038] S2: The movable end of the automatic telescopic rod 10 extends, causing the baffle 12 to move downward;

[0039] S3: Turn on the power of the motor 14, the motor 14 drives the gear 15 to rotate, the gear 15 drives the rack 13 to move, the rack 13 drives the slide plate 2 to slide, the slide plate 2 drives the aircraft parts to be repaired in the clamping mechanism to move to the bottom of the visual inspection camera 11, the baffle 12 abuts against the clamping plate 9 and pushes the clamping plate 9 to automatically clamp the aircraft parts to be repaired, so as to facilitate stable maintenance work, and the motor 14 stops working;

[0040] S4: placing another aircraft component to be inspected on the carrying plate 5 of another self-clamping mechanism;

[0041] S5: The visual inspection camera 11 performs appearance damage inspection on the aircraft parts to be inspected in S1;

[0042] S6: The staff uses hand-held tools to repair the aircraft parts to be repaired as described in S1;

[0043] S7: After the maintenance is completed, the motor 14 is reversed to move the repaired aircraft component out of the housing 1, and at the same time, another aircraft component to be repaired in S4 is moved into the housing 1. The working process of the other aircraft component to be repaired in S4 is the same as that of the aircraft component to be repaired in S1;

[0044] S8: the clamping plate 9 loses its limit and is reset under the elastic force of the spring 7, which automatically releases the limit of the aircraft parts that have been repaired;

[0045] S9: After taking out the repaired aircraft parts, put in new aircraft parts to be repaired, and repeat the above working process.

[0046] It will be apparent to those skilled in the art that the invention is not limited to the details of the exemplary embodiments described above and that the invention can be implemented in other forms without departing from the spirit or essential features of the invention. Therefore, the embodiments should be considered in all respects as exemplary and non-limiting, and the scope of the invention is defined by the appended claims rather than the foregoing description, and it is intended that all variations within the meaning and range of equivalents of the claims be included in the invention. Any reference numeral in a claim should not be considered as limiting the claim to which it relates.

[0047] In addition, it should be understood that although the present specification is described according to implementation modes, not every implementation mode contains only one independent technical solution. This description of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment may also be appropriately combined to form other implementation modes that can be understood by those skilled in the art.

Claims

1. An aircraft parts maintenance and detection device, characterized in that: The invention comprises a shell (1), a slide plate (2), a visual detection camera (11), a pushing mechanism, a transmission mechanism and a self-clamping mechanism; the top plate of the shell (1) is provided with a pushing mechanism, the inner top surface of the shell (1) is installed with a visual detection camera (11), the interior of the shell (1) is slidably connected with a horizontally arranged slide plate (2) through a transmission mechanism, the slide plate (2) is fixed with a self-clamping mechanism and the slide plate (2) can be slidably extended to the outside of the shell (1), the self-clamping mechanism is arranged in coordination with the visual detection camera (11), and the self-clamping mechanism is connected in coordination with the pushing mechanism.

2. The aircraft parts maintenance and detection device according to claim 1, characterized in that: The self-clamping mechanism comprises a frame (4), a bearing plate (5), a sliding rod (6), a slider (8) and a clamping plate (9); the frame (4) is fixed to the upper end of the slide plate (2); a horizontally arranged bearing plate (5) is fixed to one end inside the frame (4); a horizontally arranged sliding rod (6) is fixed to the lower end of the bearing plate (5); both ends of the sliding rod (6) are fixedly connected to the frame (4); a sliding rod (8) is slidably sleeved on the outer side of the sliding rod (6); and a clamping plate (9) is installed on the upper end of the sliding rod (8).

3. The aircraft parts maintenance and detection device according to claim 2, characterized in that: The upper end of the sliding block (8) is detachably and fixedly connected with a clamping plate (9).

4. The aircraft parts maintenance and detection device according to claim 3, characterized in that: A spring (7) is sleeved on the outer side of the slide rod (6), one end of the spring (7) abuts against the slide block (8), and the other end of the spring (7) abuts against the frame (4).

5. An aircraft parts maintenance and detection device according to claim 2 or 4, characterized in that: The pushing mechanism comprises an automatic telescopic rod (10) and a baffle (12); the top plate of the shell (1) is fixedly connected to the fixed end of the vertically arranged automatic telescopic rod (10); the movable end of the automatic telescopic rod (10) extends into the interior of the shell (1) and the movable end of the automatic telescopic rod (10) is fixedly connected to the baffle (12); and the baffle (12) is cooperatively connected to the clamping plate (9).

6. The aircraft parts maintenance and detection device according to claim 1, characterized in that: The transmission mechanism comprises a rack (13), a motor (14) and a gear (15); the inner bottom surface of the housing (1) is fixedly connected to the vertically arranged motor (14); the output shaft of the motor (14) is coaxially fixedly connected to the horizontally arranged gear (15); the lower end of the slide plate (2) is fixedly provided with a horizontally arranged rack (13); the rack (13) is meshingly connected to the gear (15).

7. The aircraft parts maintenance and detection device according to claim 1, characterized in that: Self-clamping mechanisms are fixed at both ends of the upper surface of the slide plate (2), and the two self-clamping mechanisms are symmetrically arranged. The top plate of the shell (1) is provided with two pushing mechanisms, and the two pushing mechanisms are located on both sides of the visual detection camera (11). Each pushing mechanism is respectively connected to the corresponding self-clamping mechanism.

8. A method for using the aircraft parts maintenance and detection device according to any one of claims 1 to 7, characterized in that: The method comprises the following steps: S1: placing an aircraft component to be repaired on a carrying plate (5) of one of the self-clamping mechanisms; S2: The movable end of the automatic telescopic rod (10) extends, causing the baffle (12) to move downward; S3: The power supply of the motor (14) is turned on, the motor (14) drives the gear (15) to rotate, the gear (15) drives the rack (13) to move, the rack (13) drives the slide plate (2) to slide, the slide plate (2) drives the aircraft component to be inspected in the clamping mechanism to move to the bottom of the visual inspection camera (11), the baffle plate (12) and the clamping plate (9) are abutted against each other, and the clamping plate (9) is pushed to automatically clamp the aircraft component to be inspected, and the motor (14) stops working; S4: placing another aircraft component to be inspected on the carrier plate (5) of another self-clamping mechanism; S5: a visual inspection camera (11) performs appearance damage inspection on the aircraft parts to be inspected in S1; S6: The staff uses hand-held tools to repair the aircraft parts to be repaired as described in S1; S7: After the maintenance is completed, the motor (14) is reversed to move the repaired aircraft component out of the housing (1), and at the same time, another aircraft component to be repaired in S4 is moved into the housing (1). The working process of the other aircraft component to be repaired in S4 is the same as that of the aircraft component to be repaired in S1; S8: the clamping plate (9) loses its limit and is reset under the elastic force of the spring (7), i.e., the limit of the aircraft parts that have been repaired is automatically released; S9: After taking out the repaired aircraft parts, put in new aircraft parts to be repaired, and repeat the above working process.

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