Locking ring of aircraft landing gear

Abstract

The utility model provides an aircraft landing gear locking ring, and belongs to the technical field of aircraft landing gears, the aircraft landing gear locking ring comprises a left support arm, a right support arm, a first rotating shaft, a second rotating shaft, a reinforcing rotating shaft, a drum-shaped roller and a reset torsion spring, the left support arm and the right support arm are arranged in parallel, and the first rotating shaft and the second rotating shaft are respectively arranged at the upper end and the lower end of the left support arm and the upper end and the lower end of the right support arm; the reinforcing rotating shaft is arranged in the middle of the left supporting arm and the right supporting arm, the drum-shaped rolling wheel is installed on the first rotating shaft and located between the left supporting arm and the right supporting arm, and the drum-shaped rolling wheel can rotate relative to the first rotating shaft; a drum-shaped roller on the first rotating shaft is connected with the lock hook, and a second rotating shaft is connected with the undercarriage single-lug support; the reset torsional spring is installed on the second rotating shaft, abuts against the left supporting arm and the right supporting arm and is used for providing swing reset elastic force for the left supporting arm and the right supporting arm. The locking ring can independently keep lubrication in all rotating areas under the large-load and large-deformation environment, so that the self-adaptive locking function is achieved.

Description

An aircraft landing gear locking ring Technical Field

[0001] This application belongs to the field of aircraft landing gear, and specifically relates to an aircraft landing gear locking ring. Background Technology

[0002] The landing gear locking ring is a key mechanical component in the aircraft landing gear retraction and extension system. Its main function is to ensure reliable locking of the landing gear when it is in the retracted or extended position, preventing accidental movement during flight or failure during ground operation. Figure 1 shows a typical landing gear locking ring structure in the prior art. Existing landing gear locking rings may experience abnormal wear during locking and unlocking under heavy loads and large deformations, potentially affecting their locking function. Summary of the Invention

[0003] The purpose of this application is to provide an aircraft landing gear locking ring to solve or mitigate at least one of the problems in the prior art.

[0004] The technical solution of this application is: an aircraft landing gear locking ring, comprising: a left support arm, a right support arm, a first rotating shaft, a second rotating shaft, a reinforcing rotating shaft, a drum-shaped roller, and a return torsion spring. The left support arm and the right support arm are arranged in parallel. The first rotating shaft and the second rotating shaft are respectively arranged at the upper and lower ends of the left support arm and the right support arm. The reinforcing rotating shaft is arranged in the middle of the left support arm and the right support arm. The drum-shaped roller is mounted on the first rotating shaft and located between the left support arm and the right support arm. The drum-shaped roller can rotate relative to the first rotating shaft.

[0005] The first rotating shaft is connected to the locking hook via a drum-shaped roller, and to the landing gear single-ear support via the second rotating shaft; the return torsion spring is mounted on the second rotating shaft and abuts against the left and right support arms, and is used to provide the swinging return spring force for the left and right support arms.

[0006] Preferably, the drum-shaped roller is a cylindrical structure with a large diameter in the middle and small diameters at both ends.

[0007] Preferably, the left support arm has a first oil injection hole connected to the first rotating shaft, and the inlet of the first oil injection hole has a first oil injection nozzle.

[0008] Preferably, the right support arm has a second oil injection hole connected to the first rotating shaft, and the inlet of the second oil injection hole has a second oil injection nozzle.

[0009] Preferably, the first rotating shaft has a third oil injection hole that connects to the drum-shaped roller, and the inlet of the third oil injection hole has a third oil injection nozzle.

[0010] Preferably, the second rotating shaft has a fourth oil injection hole that connects to the left support arm and / or the right support arm, and the inlet of the fourth oil injection hole has a fourth oil injection nozzle.

[0011] Preferably, the aircraft landing gear locking ring further includes an adjusting shim, which is disposed on the first rotating shaft, the second rotating shaft and / or the reinforcing rotating shaft, for adjusting the clearance of the first rotating shaft, the second rotating shaft and the reinforcing rotating shaft relative to the left support arm and the right support arm.

[0012] The aircraft landing gear locking ring provided in this application can independently maintain lubrication in each rotating area under high load and large deformation conditions, thereby achieving an adaptive locking function. It can also ensure the rigidity of the landing gear locking ring under high load and has a certain degree of free swing and reset capability, which can compensate for its locking capability under high load and large deformation conditions. Attached Figure Description

[0013] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0014] Figure 1 is a schematic diagram of the landing gear locking ring structure in the prior art.

[0015] Figure 2 is a schematic diagram of the landing gear locking ring structure of this application.

[0016] Figure 3 is a perspective view of the landing gear locking ring of this application. Detailed Implementation

[0017] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings.

[0018] To address the issues of abnormal wear and impaired locking that may occur in existing landing gear locking rings under heavy loads and deformations, this application provides an adaptively adjustable aircraft landing gear locking ring structure with higher reliability.

[0019] As shown in Figures 2 and 3, the aircraft landing gear locking ring provided in this application includes: a left support arm 1, a right support arm 2, a first rotating shaft 3, a second rotating shaft 4, a reinforcing rotating shaft 5, a drum-shaped roller 6, and a return torsion spring 7. The left support arm 1 and the right support arm 2 are arranged approximately parallel to each other. The first rotating shaft 3, the second rotating shaft 4, and the reinforcing rotating shaft 5 are respectively located at the upper end, lower end, and approximately middle position of the left support arm 1 and the right support arm 2. The drum-shaped roller 6 is mounted on the first rotating shaft 3 and located between the left support arm 1 and the right support arm 2, and can rotate relative to the first rotating shaft 3. The drum-shaped roller 6 on the first rotating shaft 3 is connected to a locking hook (not shown), and the second rotating shaft 4 is connected to a single-ear support of the landing gear (not shown). The return torsion spring 7 is mounted on the second rotating shaft 4 and abuts against the left support arm 1 and the right support arm 2, providing a swing-like return force for the left support arm 1 and the right support arm 2, thereby compensating for locking capability under large loads and large deformations.

[0020] In a preferred embodiment of this application, the drum-shaped roller 6 is a cylindrical structure with a relatively large diameter in the middle and relatively small diameters at both ends.

[0021] The aircraft landing gear locking ring provided in this application adopts a split left and right support arm and a drum-shaped roller 6, which enables the landing gear locking ring to achieve an adaptive locking function. By setting a reinforcing pivot 5 in the middle of the left and right support arms, the rigidity of the landing gear locking ring under heavy loads can be guaranteed. By setting a return torsion spring between the second pivot 4 and the left and right support arms, the landing gear locking ring can have a certain angle of free swing and return function, thereby compensating for its locking ability under heavy loads and large deformations.

[0022] In the preferred embodiment of the aircraft landing gear locking ring of this application, the left support arm 1 has a first oil injection hole connected to the first rotating shaft 3, and a first oil injection nozzle 71 is provided at the entrance of the first oil injection hole. Simultaneously, the right support arm 2 has a second oil injection hole connected to the first rotating shaft 3, and a second oil injection nozzle 71 is provided at the entrance of the second oil injection hole. The first oil injection nozzle 71 and the second oil injection nozzle 71 respectively inject lubricating oil into the first oil injection hole and the second oil injection hole, enabling the first rotating shaft 3 to achieve better relative rotation with the left and right support arms.

[0023] Furthermore, the first rotating shaft 3 is provided with a third oil injection hole that connects to the drum-shaped roller 6, and a third oil injection nozzle 73 is provided at the entrance of the third oil injection hole. By injecting lubricating oil into the third oil injection hole through the third oil injection nozzle 73, the first rotating shaft 3 and the drum-shaped roller 6 can achieve better relative rotation.

[0024] Furthermore, the second rotating shaft 4 is provided with a fourth oil injection hole that connects to the left and right support arms, and a fourth oil injection nozzle 74 is provided at the entrance of the fourth oil injection hole. By injecting lubricating oil into the fourth oil injection hole through the fourth oil injection nozzle 74, the second rotating shaft 4 and the left and right support arms can achieve better relative rotation.

[0025] In a preferred embodiment of this application, the aircraft landing gear locking ring further includes an adjusting shim 8, which is disposed on the first rotating shaft 3, the second rotating shaft 4 and / or the reinforcing rotating shaft 5, and is used to adjust the clearance between each rotating shaft and the left and right support arms.

[0026] The aircraft landing gear locking ring provided in this application can independently maintain lubrication in each rotating area under high load and large deformation conditions, thereby achieving an adaptive locking function. It can also ensure the rigidity of the landing gear locking ring under high load and has a certain degree of free swing and reset capability, which can compensate for its locking capability under high load and large deformation conditions.

[0027] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. An aircraft landing gear locking ring, characterized in that, include: The structure comprises a left support arm (1), a right support arm (2), a first rotating shaft (3), a second rotating shaft (4), a reinforcing rotating shaft (5), a drum-shaped roller (6), and a return torsion spring (7). The left support arm (1) and the right support arm (2) are arranged parallel to each other. The first rotating shaft (3) and the second rotating shaft (4) are respectively located at the upper and lower ends of the left support arm (1) and the right support arm (2). The reinforcing rotating shaft (5) is located in the middle of the left support arm (1) and the right support arm (2). The drum-shaped roller (6) is mounted on the first rotating shaft (1). 3) Located between the left support arm (1) and the right support arm (2), the drum roller (6) is able to rotate relative to the first rotating shaft (3); the drum roller (6) on the first rotating shaft (3) is connected to the locking hook, and the second rotating shaft (4) is connected to the landing gear single-ear support; the return torsion spring (7) is installed on the second rotating shaft (4) and abuts against the left support arm (1) and the right support arm (2), and is used to provide the swing return spring force for the left support arm (1) and the right support arm (2).

2. The aircraft landing gear locking ring as described in claim 1, characterized in that, The drum-shaped roller (6) is a cylindrical structure with a large diameter in the middle and small diameters at both ends.

3. The aircraft landing gear locking ring as described in claim 1, characterized in that, The left support arm (1) is provided with a first oil injection hole that connects to the first rotating shaft (3), and the inlet of the first oil injection hole is provided with a first oil injection nozzle (71).

4. The aircraft landing gear locking ring as described in claim 3, characterized in that, The right support arm (2) is provided with a second oil injection hole that connects to the first rotating shaft (3), and the inlet of the second oil injection hole is provided with a second oil injection nozzle (72).

5. The aircraft landing gear locking ring as described in claim 3 or 4, characterized in that, The first rotating shaft (3) has a third oil injection hole that connects to the drum-shaped roller (6), and a third oil injection nozzle (73) is provided at the entrance of the third oil injection hole.

6. The aircraft landing gear locking ring as described in claim 5, characterized in that, The second rotating shaft (4) is provided with a fourth oil injection hole that connects to the left support arm (1) and / or the right support arm (2), and a fourth oil injection nozzle (74) is provided at the entrance of the fourth oil injection hole.

7. The aircraft landing gear locking ring as described in claim 1, characterized in that, The aircraft landing gear locking ring also includes an adjusting shim (8), which is disposed on the first rotating shaft (3), the second rotating shaft (4) and / or the reinforcing rotating shaft (5) for adjusting the clearance of the first rotating shaft (3), the second rotating shaft (4) and the reinforcing rotating shaft (5) relative to the left support arm (1) and the right support arm (2).

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