An aircraft component maintenance and inspection device and its usage method

Abstract

An aircraft component maintenance and inspection device and its usage method belong to the technical field of component maintenance. The top plate of the housing is provided with a pushing mechanism, and a visual inspection camera is installed on the inner top surface of the housing. The interior of the housing is slidably connected to a horizontally arranged sliding plate through a transmission mechanism. A self-clamping mechanism is fixed on the sliding plate, and the sliding plate can slide out to the outside of the housing. The self-clamping mechanism is arranged in cooperation with the visual inspection camera and is connected to the pushing mechanism in cooperation. The present invention can sequentially move the two self-clamping mechanisms to the lower part of the visual inspection camera for maintenance, and at the same time allows the self-clamping mechanism on the other side to move out of the housing for the replacement of aircraft components, reducing the time required for material replacement. In addition, the functions of automatic clamping and release of the limit not only simplify the operation process but also improve the overall efficiency of aircraft component maintenance and inspection.

Description

Technical Field

[0001] The present invention relates to an aircraft component maintenance and inspection device and its usage method, belonging to the technical field of component maintenance. Background Art

[0002] To ensure that an aircraft continuously maintains a good flight state, its components must undergo strict maintenance and inspection after being used for a period of time. The aim 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 components usually relies on manual operation. Before the maintenance and inspection start, the staff needs to manually fix the components on the device to prevent them from moving or having an accident during the inspection. Similarly, after the maintenance and inspection are completed, the staff also needs to manually release the positioning measures to reinstall the components back onto the aircraft.

[0004] This way that relies on manual operation is not only cumbersome but also time-consuming and laborious, affecting the efficiency of aircraft component maintenance and repair work, increasing unnecessary time costs, and may cause delays in the timely maintenance and reuse of the aircraft. Summary of the Invention

[0005] To solve the problems in the background art, the present invention provides an aircraft component maintenance and inspection device and its usage method.

[0006] To achieve the above object, the present invention adopts the following technical solution: An aircraft component maintenance and inspection device includes a housing, a sliding plate, a visual inspection camera, a pushing mechanism, a transmission mechanism, and a self-clamping mechanism; the top plate of the housing is provided with a pushing mechanism, the inner top surface of the housing is installed with a visual inspection camera, the inside of the housing is slidably connected to the horizontally arranged sliding plate through a transmission mechanism, the sliding plate is fixed with a self-clamping mechanism and the sliding plate can slide out to the outside of the housing, the self-clamping mechanism is arranged in cooperation with the visual inspection camera, and the self-clamping mechanism is connected in cooperation with the pushing mechanism.

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

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

[0009] A spring is sleeved on the outside of the sliding rod, one end of the spring abuts against the slider, 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 housing 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 housing and the movable end of the automatic telescopic rod is fixedly connected to the baffle, and the baffle is cooperatively connected with the clamping plate.

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

[0012] Self-clamping mechanisms are fixedly connected to both ends of the upper surface of the sliding plate, and the two self-clamping mechanisms are symmetrically arranged. The top plate of the housing is provided with two pushing mechanisms, and the two pushing mechanisms are located on both sides of the visual inspection camera. Each pushing mechanism is respectively cooperatively connected with the corresponding self-clamping mechanism.

[0013] A method for using an aircraft component maintenance and inspection device according to the present invention, the method comprising the following steps:

[0014] S1: Place an aircraft component to be repaired on the bearing plate of one of the self-clamping mechanisms;

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

[0016] S3: Connect the power supply of the motor, the motor drives the gear to rotate, the gear drives the rack to move, the rack drives the sliding plate to slide, the sliding plate drives the aircraft component to be repaired in the self-clamping mechanism to move below the visual inspection camera, and after the baffle abuts against the clamping plate, the baffle pushes the clamping plate to automatically clamp the aircraft component to be repaired, and the motor stops working;

[0017] S4: Place another aircraft component to be repaired on the bearing plate of the other self-clamping mechanism;

[0018] S5: The visual inspection camera performs an appearance damage inspection on the aircraft component to be repaired described in S1;

[0019] S6: The staff holds a tool to repair the aircraft component to be repaired described in S1;

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

[0021] S8: The clamping plate loses its limit and resets under the elastic force of the spring, that is, the limit on the repaired aircraft component is automatically released;

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

[0023] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0024] Through the meshing transmission of the motor-driven gear and the rack, the present invention realizes the reciprocating movement of the slide plate, so that the two self-clamping mechanisms can be successively moved below the visual inspection camera for maintenance, and at the same time, the self-clamping mechanism on the other side is allowed to move out of the housing for the replacement of aircraft parts, effectively reducing the time required for material change. In addition, the cooperation of the baffle plate at the lower end of the automatic telescopic rod and the clamping plate can automatically clamp the aircraft parts during feeding to ensure the stability of the maintenance work; when discharging, the spring force pushes the slider to reset, driving the clamping plate to automatically release the limit on the aircraft parts, facilitating the quick replacement of the repaired parts. The functions of automatic clamping and release of the limit not only simplify the operation process but also improve the overall efficiency of aircraft parts maintenance and detection. Description of the Drawings

[0025] Figure 1 is the structural schematic diagram of the present invention;

[0026] Figure 2 is Figure 1 the bottom view of

[0027] Figure 3 is Figure 2 the enlarged view of part A of Detailed Embodiments

[0028] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0029] An aircraft component maintenance and inspection device includes a housing 1, a sliding plate 2, a visual inspection camera 11, a pushing mechanism, a transmission mechanism, and a self-clamping mechanism; a pushing mechanism is provided on the top plate of the housing 1, the inner top surface of the housing 1 is installed with a visual inspection camera 11, the inside of the housing 1 is slidably connected to the horizontally arranged sliding plate 2 through a transmission mechanism, and a self-clamping mechanism is fixed on the sliding plate 2 and the sliding plate 2 can slide out to the outside of the housing 1. Specifically: through grooves are opened on the side of the housing 1, limiting blocks 3 are fixed on the inner walls on both sides of the through groove, sliding grooves are opened on both side walls of the sliding plate 2, and the two limiting blocks 3 are respectively slidably connected to the corresponding sliding grooves, so that the sliding plate 2 can stably slide between the through grooves, that is, it can stably drive the aircraft component to enter and exit the housing 1; the self-clamping mechanism is arranged in cooperation with the visual inspection camera 11, and the self-clamping mechanism is connected in cooperation with the pushing mechanism.

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

[0031] The upper end of the slider 8 is detachably fixedly connected to the clamping plate 9 by bolt threading and locking, so that the clamping plate 9 can be easily detached from the slider 8. When limiting aircraft components of different sizes, clamping plates 9 of different thicknesses can be replaced.

[0032] A spring 7 is sleeved on the outside of the sliding 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 body 4. In the natural state, the elastic force of the spring 7 will push the slider 8 to the side away from the bearing plate 5, that is, it can automatically release the limit on the aircraft component.

[0033] The pushing mechanism includes an automatic telescopic rod 10 and a baffle 12; the top plate of the housing 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 inside of the housing 1 and the movable end of the automatic telescopic rod 10 is fixedly connected to the baffle 12, and the baffle 12 is connected in cooperation with the clamping plate 9.

[0034] The transmission mechanism includes 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 and fixedly connected to the horizontally arranged gear 15, the lower end of the sliding plate 2 is fixedly provided with a horizontally arranged rack 13, and the rack 13 is meshed with the gear 15.

[0035] To improve production efficiency, two sets of the pushing mechanism and the self-clamping mechanism are provided and used alternately, that is: self-clamping mechanisms are fixedly arranged at both ends of the upper surface of the sliding plate 2, and the two self-clamping mechanisms are symmetrically arranged; two pushing mechanisms are provided on the top plate of the housing 1, and the two pushing mechanisms are located on both sides of the vision detection camera 11, and each pushing mechanism is respectively connected and cooperated with the corresponding self-clamping mechanism.

[0036] A method for using an aircraft component maintenance and detection device according to the present invention, the method comprising the following steps:

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

[0038] S2: The movable end of the automatic telescopic rod 10 extends out, so that the baffle 12 moves downward;

[0039] S3: Connect the power supply 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 sliding plate 2 to slide, the sliding plate 2 drives the aircraft component to be repaired in the self-clamping mechanism to move below the vision detection camera 11, and after the baffle 12 abuts against the clamping plate 9, it pushes the clamping plate 9 to automatically clamp the aircraft component to be repaired, facilitating stable repair work, and the motor 14 stops working;

[0040] S4: Place another aircraft component to be repaired on the bearing plate 5 of the other self-clamping mechanism;

[0041] S5: The vision detection camera 11 performs appearance damage detection on the aircraft component to be repaired described in S1;

[0042] S6: The staff holds a tool to repair the aircraft component to be repaired described in S1;

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

[0044] S8: The clamping plate 9 loses its limit and resets under the elastic force of the spring 7, that is, the limit on the repaired aircraft component is automatically released;

[0045] Step S9: After taking out the repaired aircraft components, put in new aircraft components to be inspected, and repeat the above work process.

[0046] For those skilled in the art, it is obvious that the present invention is not limited to the details of the above exemplary embodiments, and the present invention can be implemented in other forms without departing from the spirit or basic characteristics of the present invention. Therefore, from any point of view, the embodiments should be regarded as exemplary and non-restrictive. The scope of the present invention is defined by the appended claims rather than the above description. Therefore, all changes falling within the meaning and scope of the equivalent conditions of the claims are intended to be embraced within the present invention. Any reference signs in the claims should not be construed as limiting the claims concerned.

[0047] In addition, it should be understood that although this specification is described according to embodiments, not every embodiment only contains an independent technical solution. This narrative way of the specification is only for clarity. Those skilled in the art should regard the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. An aircraft component maintenance and inspection device, characterized in that: It includes a housing (1), a sliding plate (2), a visual inspection camera (11), a pushing mechanism, a transmission mechanism, and a self-clamping mechanism; a pushing mechanism is provided on the top plate of the housing (1), a visual inspection camera (11) is installed on the inner top surface of the housing (1), the inside of the housing (1) is slidably connected to the horizontally arranged sliding plate (2) through the transmission mechanism, a self-clamping mechanism is fixed on the sliding plate (2) and the sliding plate (2) can slide out to the outside of the housing (1), the self-clamping mechanism is arranged in cooperation with the visual inspection camera (11), and the self-clamping mechanism is connected to the pushing mechanism in cooperation; the self-clamping mechanism includes a frame body (4), a bearing plate (5), a sliding rod (6), a slider (8), and a clamping plate (9); the frame body (4) is fixed to the upper end of the sliding plate (2), a horizontally arranged bearing plate (5) is fixed at one end inside the frame body (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 fixed to the frame body (4), a slider (8) is slidably sleeved on the outside of the sliding rod (6), and a clamping plate (9) is installed at the upper end of the slider (8); the pushing mechanism includes an automatic telescopic rod (10) and a baffle plate (12); the top plate of the housing (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 inside of the housing (1) and the movable end of the automatic telescopic rod (10) is fixedly connected to the baffle plate (12), and the baffle plate (12) is connected to the clamping plate (9) in cooperation.

2. The aircraft component maintenance and inspection device according to claim 1, characterized in that: The clamping plate (9) is detachably and fixedly connected to the upper end of the slider (8).

3. The aircraft component maintenance and inspection device according to claim 2, characterized in that: A spring (7) is sleeved on the outside of the sliding 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 body (4).

4. An aircraft component maintenance and inspection device according to claim 3, characterized in that: The transmission mechanism includes 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 and fixedly connected to the horizontally arranged gear (15), the lower end of the sliding plate (2) is fixedly connected to the horizontally arranged rack (13), and the rack (13) is meshed with the gear (15).

5. An aircraft component maintenance and inspection device according to claim 1, characterized in that: Self-clamping mechanisms are fixed at both ends of the upper surface of the sliding plate (2), the two self-clamping mechanisms are symmetrically arranged, two pushing mechanisms are provided on the top plate of the housing (1), the two pushing mechanisms are located on both sides of the visual inspection camera (11), and each pushing mechanism is respectively connected to the corresponding self-clamping mechanism in cooperation.

6. A method for using the aircraft component maintenance and inspection device according to claim 4, characterized in that: The method includes the following steps: S1: Place an aircraft component to be repaired on the bearing plate (5) of one of the self-clamping mechanisms; S2: The movable end of the automatic telescopic rod (10) extends out, causing the baffle plate (12) to move downward; S3: Connect the power supply 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 component to be repaired in the self-clamping mechanism to move below the visual inspection camera (11). After the baffle (12) abuts against the clamping plate (9), it pushes the clamping plate (9) to automatically clamp the aircraft component to be repaired, and the motor (14) stops working; S4: Place another aircraft component to be repaired on the bearing plate (5) of another self-clamping mechanism; S5: The visual inspection camera (11) performs an appearance damage inspection on the aircraft component to be repaired described in S1; S6: The staff holds a tool to repair the aircraft component to be repaired described in S1; S7: After the repair is completed, the motor (14) rotates in reverse to move the repaired aircraft component out of the housing (1), and at the same time move the other aircraft component to be repaired described in S4 into the housing (1). The working process of the other aircraft component to be repaired described in S4 is the same as that of the aircraft component to be repaired described in S1; S8: The clamping plate (9) loses its limit and resets under the elastic force of the spring (7), that is, the limit on the repaired aircraft component is automatically released; S9: After taking out the repaired aircraft component and putting in a new aircraft component to be repaired, repeat the above working process.

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