Aircraft undercarriage locking assembly spring inspection device

Abstract

The utility model discloses an aircraft undercarriage locking assembly spring inspection device which comprises a limiting device and an operating rod piece. The limiting device comprises a body, a handle and a combination part which are connected into a whole, the combination part is located at the front end of the body and matched with a lock hook of a locking assembly on an aircraft undercarriage, the handle is located at the end, away from the combination part, of the body, and at least one stop part is arranged on the body; and the operating rod piece is used for contacting the spring to confirm the fracture state of the spring. By using the spring inspection device for the locking assembly of the aircraft undercarriage, the spring in the locking assembly can be directly and visually inspected and touched, whether the spring is broken or not can be visually and accurately inspected, the situation that failure of double springs causes faults of the locking assembly and influences flight safety and flight normality is avoided, the aircraft attendance failure rate is reduced, and the service life of the aircraft is prolonged. And the airplane release reliability is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft maintenance and detection, in particular to a spring inspection device for a locking assembly of an aircraft landing gear. Background Art

[0002] In current aviation maintenance practices, inspections of main landing gear lock assemblies rely primarily on regular visual inspections. For example, the A330 requires detailed inspections every 3000 FC or 24 MO. This inspection method has limitations, particularly in assessing the condition of internal springs, often failing to accurately detect internal spring fractures.

[0003] Because existing visual inspections cannot accurately detect broken internal springs, numerous incidents have occurred where this has caused main landing gear locking assembly failures. This has particularly impacted the critical approach phase after the aircraft lowers the landing gear, triggering the ECAM warning "L / G GEAR UPLOCK FAULT." This has led to flight irregularities such as missed approaches and low-altitude passes, impacting flight safety and the passenger experience. A landing gear locking failure requires additional manual resetting of the landing gear. Utility Model Content

[0004] In response to these shortcomings of the prior art, the present application proposes an aircraft landing gear locking assembly spring inspection device, which aims to address the limitations of existing inspection methods, avoid the locking of the landing gear locking assembly during inspection, and avoid additional manual resetting of the landing gear. By providing a professional and efficient detection device, it is hoped that the accuracy, safety and efficiency of inspection will be improved.

[0005] The technical solutions provided by this utility model are as follows:

[0006] An aircraft landing gear locking assembly spring inspection device includes a limit device and an operating rod;

[0007] The limiting device includes a body, a handle, and a coupling portion connected as one body. The coupling portion is located at the front end of the body and is adapted to be matched with a lock hook of a locking assembly on an aircraft landing gear. The handle is located on the body at an end away from the coupling portion. The body is provided with at least one stop portion.

[0008] The operating rod is used to contact the spring to confirm its broken state.

[0009] Furthermore, the stopper comprises a first stopper and a second stopper, wherein the first stopper is provided on both sides of the middle portion of the body, and the first stopper acts on the inner side of the blocking block of the aircraft landing gear locking assembly;

[0010] The second stopping portions are located at both sides of the bottom of the main body, and the second stopping portions act on the inclined surface of the blocking block.

[0011] Furthermore, the first stopper is a columnar protrusion structure;

[0012] The second stopping portion is a block-shaped structure with an inclined surface.

[0013] Furthermore, a socket is provided at one end of the body away from the coupling portion, and the socket is adapted to fit the operating rod.

[0014] Furthermore, it also includes a connecting ring and / or a connecting rope;

[0015] The limiting device and the operating rod are connected together through the connecting ring and / or the connecting rope.

[0016] Furthermore, it also includes a warning belt, which is arranged on the connecting ring and / or connecting rope together with the limiting device and the operating rod.

[0017] Furthermore, the limiting device and the operating lever are suitable for the A330 aircraft.

[0018] Furthermore, the operating rod is a rod-shaped structure with a length of 150 mm and a diameter of 10 mm.

[0019] Furthermore, the first stopper has a height of 10-15 mm and a diameter of 8-12 mm; the second stopper has a height of 15-20 mm;

[0020] The joint is a semicircular structure with a diameter of 45-55 mm and a thickness of 30-50 mm;

[0021] The handle forms an obtuse angle with the body, has a length of 100-150 mm, and a thickness of 30-50 mm;

[0022] The total length of the main body and the connecting portion is 150-200 mm.

[0023] Furthermore, the first stopper has a diameter of 10 mm and a height of 15 mm; the second stopper has a height of 15 mm;

[0024] The joint is a semicircular structure with a diameter of 50 mm and a thickness of 40 mm;

[0025] The handle is 100 mm long and 40 mm thick;

[0026] The total length of the main body and the connecting portion is 150 mm.

[0027] Compared with the prior art, the beneficial effects of the present invention are:

[0028] 1. The aircraft landing gear locking assembly spring inspection device provided in this application allows direct visual inspection and actuation of the spring inside the locking assembly, intuitively and accurately checking for spring breakage. This prevents double spring failure from causing locking assembly failure, which could affect flight safety and flight regularity, thereby reducing aircraft dispatch failure rates and improving aircraft dispatch reliability.

[0029] 2. This aircraft landing gear locking assembly spring inspection device features a simple structure and is easy to operate. The ergonomically designed handle reduces the risk of maintenance personnel directly touching the locking assembly during operation. It also prevents the locking hook from accidentally being actuated into the locked position, reducing unnecessary unlocking and resetting work.

[0030] 3. The shape and size of the operating rod, which is approximately 10mm in diameter, is designed to gently touch the spring and confirm whether there is a break, ensuring the accuracy and safety of the inspection process. It has a moderate thickness and length.

[0031] 4. The aircraft landing gear locking assembly spring inspection device provided in this application has all mechanical components made of high-performance materials and subjected to special surface treatment to improve durability and corrosion resistance, ensuring that the tool can be used reliably in various environments;

[0032] 5. The aircraft landing gear locking assembly spring inspection device provided in this application is suitable for inspecting the internal springs of the main landing gear locking assembly of the A330 aircraft. It can also be used to inspect the springs of other aircraft models or landing gear assemblies according to actual conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 This is a structural diagram of the A330 model locking assembly in the locked position in the embodiment of the present utility model;

[0034] Figure 2 This is a structural diagram of the A330 model locking assembly in the unlocked position in an embodiment of the present utility model;

[0035] Figure 3 This is a schematic diagram of the position of the blocking block of the locking assembly of the A330 aircraft in the embodiment of the present utility model;

[0036] Figure 4 This is a schematic structural diagram of a blocking block of an A330 aircraft locking assembly in an embodiment of the present invention;

[0037] Figure 5 This is a schematic structural diagram of a spring inspection device for an aircraft landing gear locking assembly according to an embodiment of the present invention;

[0038] Figure 6 Schematic diagram of the structure of the second stopper in the embodiment of the present utility model.

[0039] The reference numerals are as follows:

[0040] 1-lock hook, 2-lock assembly, 3-piston, 4-target, 5-main landing gear locking roller, 6-spring, 7-lock hook upper lip, 8-stop block, 801-inclined surface, 802-inner surface, 10-limiting device, 101-body, 102-handle, 103-joining part, 104-first stop part, 105-second stop part, 106-socket, 20-operating lever, 30-warning tape, 40-connecting ring, 50-connecting rope. DETAILED DESCRIPTION

[0041] To make the objectives, technical solutions, and advantages of the embodiments of the present application more clear, the technical solutions in the embodiments of the present application will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present application. Obviously, the embodiments described below are part of the embodiments of the present application, not all of the embodiments. Generally, the components of the embodiments of the present application described and shown in the drawings herein can be arranged and designed in various different configurations.

[0042] Therefore, the detailed description of the embodiments of the present application provided below in conjunction with the accompanying drawings is intended to represent only selected embodiments of the present application and is not intended to limit the scope of protection claimed in the present application. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present application without making any creative efforts shall fall within the scope of protection claimed in the present application.

[0043] It should be understood that in the description of the embodiments of the present invention, the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like to indicate the orientation or position relationship based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing the embodiments of 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 operate in a specific orientation, and therefore cannot be understood as limiting the embodiments of the present invention. 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 the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the said features. In the description of the embodiments of the present invention, the meaning of "multiple" is two or more, unless otherwise clearly and specifically defined.

[0044] In the description of the embodiments of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "disposed," "installed," "connected," and "connected" should be understood in a broad sense. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections, electrical connections, or mutual communication; they can refer to direct connections or indirect connections through an intermediate medium; they can refer to internal communication between two elements or an interaction between two elements. For those skilled in the art, the specific meanings of the above terms in the embodiments of the present invention can be understood according to specific circumstances.

[0045] The A330's locking assembly primarily consists of a mechanical subassembly, a hydraulic subassembly, and an electrical indicator subassembly. The spring, which is prone to breakage, is part of the mechanical subassembly. A spring 6 connects the locking assembly 2 and the hook 1, which is fitted with a target 4. The hook 1 has a concave, rounded interior that mates with the main landing gear locking roller. The hook also includes an upper lip 7.

[0046] like Figure 1 As shown in the upper locked position, when the landing gear is retracted, the hook 1 rotates to the upper locked position under the action of the main landing gear locking roller 5 and locks. The hook 1 drives the lock assembly 2 through the spring 6, bringing the target 4 close to the proximity sensor, which reports that the landing gear is in the upper locked position. At this time, the spring 6 is under a large tension state.

[0047] like Figure 2 As shown in the unlocked position, when the landing gear is commanded to lower, piston 3 extends under the action of hydraulic pressure, pushing lock assembly 2, unlocking hook 1 and moving target 4 away from the proximity sensor, indicating that the landing gear is in the unlocked position. At the same time, spring 6 drives hook 1 to rotate. At this point, lock assembly 2 and hook 1 are in a relatively stable state due to the spring force.

[0048] The locking assembly provided by the utility model further comprises a blocking block 8, the position of the blocking block 8 is as follows Figure 3 As shown. The structure of the blocking block 8 is as shown Figure 4 As shown, the end has a bevel 801 and an inner side 802. Figures 1-4 The structures shown are all existing devices, and their working principles and connection relationships are not explained here.

[0049] See Figure 5 The utility model provides a spring inspection device for the locking assembly of an aircraft landing gear, which is suitable for Figure 1 、 Figure 2 The locking assembly for the A330 aircraft shown is also applicable to other aircraft models that adopt the above-mentioned locking assembly. The device includes a limiting device 10 and an operating rod 20.

[0050] The limiting device 10 is a special-shaped structure, including a main body 101, a handle 102, and a connecting portion 103. The main body 101, the handle 102, and the connecting portion 103 are of an integral design. The connecting portion 103 is located at the front end of the main body 101. The connecting portion 103 is adapted to the lock hook 1 of the locking assembly of the aircraft landing gear. The handle 102 is located on the main body 101 at one end away from the connecting portion 103. At least one stop portion is provided on the main body 101.

[0051] The operating lever 20 is used to contact the spring 6 to confirm its broken state.

[0052] By using the aircraft landing gear locking assembly spring inspection device provided in the present application, the spring 6 inside the locking assembly can be directly visually inspected and touched, and the spring 6 can be intuitively and accurately checked for breakage, thereby avoiding failure of the locking assembly caused by failure of the double spring 6, affecting flight safety and flight normality, reducing the aircraft attendance failure rate, and improving the reliability of aircraft release.

[0053] Optionally, the stopper includes a first stopper 104 and a second stopper 105 , the first stopper 104 is disposed on both sides of the middle portion of the body 101 , and the second stopper 105 is located on both sides of the bottom portion of the body 101 .

[0054] It should be noted that when the coupling portion 103 of the device is placed into the locking hook 1, the blocking block 8 is blocked by the first stop portion 104 and the second stop portion 105. Specifically, the first stop portion 104 contacts the inner side surface 802 of the blocking block 8, and the second stop portion 105 contacts the inclined surface 801 of the blocking block 8. In order to ensure that the second stop portion 105 better contacts the inclined surface 801 of the blocking block 8 with the maximum area, the second stop portion 105 is also designed to be an inclined surface that adapts to the shape of the inclined surface 801.

[0055] The aircraft landing gear locking assembly spring inspection device provided in this application is specially designed based on the internal structure of the main landing gear locking assembly of models such as the A330. The function (shape, size, material and structure) of the device is designed to include a main body 101, a coupling 103, a handle 102 and two stops. The coupling 103 is used to accurately wedge into the lock hook 1 of the locking assembly, overcome the spring force and rotate the lock hook 1, while effectively preventing the lock hook 1 from rotating to the locked position or disengaging from the lock hook 1 without causing damage to the lock hook 1.

[0056] Optionally, the first stopping portion 104 is a columnar protrusion structure, acting on the inner side surface 802 of the blocking block 8 .

[0057] The second stopping portion 105 is a block-shaped structure with an inclined surface, and its inclined surface is adapted to the inclined surface 801 of the blocking block 8 .

[0058] The first stop portion 104 is used to limit the locking hook 1 , and the second stop portion 105 is used to limit the inclined surface 801 of the blocking block 8 .

[0059] Optionally, a socket 106 is provided at one end of the body 101 away from the coupling portion 103 , and the socket 106 is adapted to fit the operating rod 20 .

[0060] Optionally, the aircraft landing gear locking assembly spring inspection device further includes a connecting ring 40 or a connecting rope 50, which connects the stopper 10 and the operating rod 20 together to prevent loss during use or storage. Alternatively, the aircraft landing gear locking assembly spring inspection device can be connected together via the connecting ring 40 and the connecting rope 50.

[0061] Optionally, a warning tape 30 is further included, which is provided together with the limit device 10 and the operating rod 20 on the connecting ring 40 and / or the connecting rope 50. The function of the warning tape 30 is to remind all components to be stored together after use to prevent them from being lost, or to warn people to pay attention to safety during use.

[0062] Optionally, the operating rod 20 is a rod-shaped structure with a length of 80-200 mm and a diameter of 5-15 mm. In this embodiment, the operating rod 20 has a length of 150 mm and a diameter of 10 mm.

[0063] Optionally, the first stopper 104 has a height of 10-15 mm and a diameter of 8-12 mm, and the second stopper 105 has a height of 15-20 mm.

[0064] The connecting portion 103 is a semicircular structure with a diameter of 45-55 mm and a thickness of 30-50 mm.

[0065] The handle 102 extends obliquely rearward of the body 101 , that is, an obtuse angle is formed between the handle 102 and the body 101 . The angle can be set according to the maximum comfort level during use, generally 135°-150°.

[0066] The handle 102 has a length of 100-150 mm and a thickness of 30-50 mm.

[0067] The total length of the main body 101 and the connecting portion 103 is 150-200 mm.

[0068] like Figure 5 As shown, the aircraft landing gear locking assembly spring inspection device provided in this embodiment is an integral component with overall dimensions of about 210 mm in length, about 150 mm in height, and about 70 mm in width.

[0069] The front end of the body 101 is a solid body with a semicircular diameter of about 50 mm and a thickness of about 40 mm, which is used to wedge into the lock hook 1 of the locking assembly and rotate the lock hook 1 to overcome the spring force.

[0070] The handle 102 is about 40 mm thick and about 100 mm long, which conforms to ergonomic considerations and facilitates application of the spring force to overcome the lock hook.

[0071] The first stopper 104 is located on both sides of the middle of the body 101 and is a cylindrical protruding structure with a diameter of about 10 mm and two sections protruding about 15 mm each. Figure 6 As shown, the second stopper 105 is located on both sides of the bottom of the body 101. It is 70mm long and 35mm high, with one side being configured as a sloped surface with a top width of 12.3mm and a bottom width of 13.7mm. These two protruding stops serve as position limits when rotating the lock hook 1, preventing the lock hook 1 of the locking assembly from rotating to the upper locking position and also preventing it from dislodging from the lock hook 1. Specifically, when limiting the position, the first stopper 104 contacts the inner side surface 802 of the blocking block 8, and the second stopper 105 contacts the sloped surface 801 of the blocking block 8.

[0072] The operating rod 20 has an overall size of about 150 mm in length and a diameter of about 10 mm and is used to lightly touch the springs 6 to confirm whether there is a break when the two springs 6 are exposed. The operating rod 20 ensures the accuracy and safety of the inspection process and has a moderate thickness and length.

[0073] The aircraft landing gear locking assembly spring inspection device provided in this application has a simple design and is easy to operate. The handle design takes ergonomics into consideration, which reduces the risk of maintenance personnel directly contacting the locking assembly during operation, while avoiding the possibility of the locking hook being accidentally actuated to the locked position, thereby reducing unnecessary unlocking and resetting workload.

[0074] The aircraft landing gear locking assembly spring inspection device provided in this application has all mechanical components made of high-performance materials and subjected to special surface treatment to improve durability and corrosion resistance, ensuring that the tool can be used reliably in various environments.

[0075] The above is only a specific embodiment of the present application, but the scope of protection of this application is not limited to this. Any changes or substitutions within the technical scope disclosed in this application should be included in the scope of protection of this application. Therefore, the scope of protection of this application should be based on the scope of protection of the claims.

Claims

1. An aircraft landing gear locking assembly spring inspection device, characterized by: Including limit devices and operating rods; The limiting device includes a body, a handle, and a coupling portion connected as one body. The coupling portion is located at the front end of the body and is adapted to be matched with a lock hook of a locking assembly on an aircraft landing gear. The handle is located on the body at an end away from the coupling portion. The body is provided with at least one stop portion. The operating rod is used to contact the spring to confirm its broken state.

2. The aircraft landing gear locking assembly spring inspection device according to claim 1, characterized in that: The stopper comprises a first stopper and a second stopper, wherein the first stopper is provided on both sides of the middle portion of the body, and the first stopper acts on the inner side of the blocking block of the aircraft landing gear locking assembly; The second stopping portions are located at both sides of the bottom of the main body, and the second stopping portions act on the inclined surface of the blocking block.

3. The aircraft landing gear locking assembly spring inspection device according to claim 2, characterized in that: The first stopper is a columnar protrusion structure; The second stopping portion is a block-shaped structure with an inclined surface.

4. The aircraft landing gear locking assembly spring inspection device according to claim 2 or 3, characterized in that: The main body is provided with a socket at one end away from the coupling portion, and the socket is adapted to the operating rod.

5. The aircraft landing gear locking assembly spring inspection device according to claim 4, characterized in that: Also includes a connecting ring and / or a connecting rope; The limiting device and the operating rod are connected together through the connecting ring and / or the connecting rope.

6. The aircraft landing gear locking assembly spring inspection device according to claim 5, characterized in that: It also includes a warning belt, which is arranged on the connecting ring and / or the connecting rope together with the limiting device and the operating rod.

7. The aircraft landing gear locking assembly spring inspection device according to claim 5 or 6, characterized in that: The limiting device and the operating lever are suitable for the A330 aircraft.

8. The aircraft landing gear locking assembly spring inspection device according to claim 7, characterized in that: The operating rod is a rod-shaped structure with a length of 150 mm and a diameter of 10 mm.

9. The aircraft landing gear locking assembly spring inspection device according to claim 7, characterized in that: The first stopper has a diameter of 8-12 mm and a height of 15-20 mm, and the second stopper has a height of 15-20 mm; The joint is a semicircular structure with a diameter of 45-55 mm and a thickness of 30-50 mm; The handle forms an obtuse angle with the body, has a length of 100-150 mm, and a thickness of 30-50 mm; The total length of the main body and the connecting portion is 150-200 mm.

10. The aircraft landing gear locking assembly spring inspection device according to claim 9, characterized in that: The first stopper has a diameter of 10 mm and a height of 15 mm, and the second stopper has a height of 15 mm; The joint is a semicircular structure with a diameter of 50 mm and a thickness of 40 mm; The handle is 100 mm long and 40 mm thick; The total length of the main body and the connecting portion is 150 mm.

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