Aircraft landing gear brace rod lock

Abstract

The invention provides an aircraft landing gear supporting rod lock and belongs to the technical field of aircraft landing gear, the aircraft landing gear supporting rod lock comprises a front lock supporting rod, a rear lock supporting rod, an unlocking rocker arm, an unlocking actuating cylinder, a locking damping actuating cylinder and a locking spring, one end of the front lock supporting rod is connected with the landing gear supporting rod, the other end of the front lock supporting rod is hinged to the rear lock supporting rod, and the rear lock supporting rod is hinged to the rear lock supporting rod. The other end of the rear lock supporting rod is hinged to an undercarriage supporting column and hinged to the locking damping actuating cylinder, the unlocking rocker arm is arranged at the hinged position of the front lock supporting rod and the rear lock supporting rod, one end of the unlocking actuating cylinder is connected with the front lock supporting rod, and the other end of the unlocking actuating cylinder is connected to the unlocking rocker arm. One end of the locking damping actuating cylinder is hinged to the rear lock supporting rod, the other end of the locking damping actuating cylinder is connected with the locking spring, the other end of the locking spring is connected with the front lock supporting rod, and the connecting end of the locking spring and the locking damping actuating cylinder is arranged on the landing gear supporting column.

Description

Technical Field

[0001] The present application belongs to the field of aircraft landing gear design, and in particular relates to an aircraft landing gear strut lock. Background Art

[0002] The aircraft landing gear strut is used to support the landing gear strut. When the landing gear is opened, the strut needs to be locked in the state of supporting the landing gear strut through the strut lock mechanism. At the same time, when the landing gear is retracted, the strut and the landing gear strut are locked. In addition, the retraction angle between the strut and the landing gear strut is large between the retracted and lowered states. Due to the narrow retraction space of the landing gear, the existing landing gear strut lock cannot meet the large angle locking requirement of the strut and the landing gear strut. Summary of the invention

[0003] The object of the present application is to provide an aircraft landing gear strut lock to solve or alleviate at least one problem in the background technology.

[0004] The technical solution of the present application is: an aircraft landing gear strut lock, comprising: a front locking strut, a rear locking strut, an unlocking rocker arm, an unlocking actuator cylinder, a locking damping actuator cylinder and a locking spring, wherein one end of the front locking strut is connected to the landing gear strut, the other end of the front locking strut is hinged to the rear locking strut, the other end of the rear locking strut is hinged to the landing gear strut and hinged to the locking damping actuator cylinder, the unlocking rocker arm is arranged at the hinge of the front locking strut and the rear locking strut, one end of the unlocking actuator cylinder is connected to the front locking strut, and the other end is connected to the unlocking rocker arm, one end of the locking damping actuator cylinder is hinged to the rear locking strut, and the other end is connected to the locking spring, the other end of the locking spring is connected to the front locking strut, and the connecting end of the locking spring and the locking damping actuator cylinder is arranged on the landing gear strut.

[0005] Preferably, there are two locking damping actuators and two locking springs, the two locking damping actuators are arranged in parallel, and the two locking springs are arranged in parallel.

[0006] Preferably, spring shafts are provided on both sides of the front locking support rod, and the spring shafts are used to connect the locking springs.

[0007] Preferably, the unlocking actuator and the locking spring are located on both sides of the front locking support rod.

[0008] Preferably, both ends of the unlocking rocker arm are double-ear structures.

[0009] Preferably, a left mounting interface is provided on one side of the rear locking strut rod, and a first rotating shaft is provided inside the left mounting interface for connecting with the front locking strut rod; a right mounting interface is provided on the other side of the rear locking strut rod, and a second rotating shaft is provided inside the right mounting interface for connecting with the landing gear strut, and a third rotating shaft is provided outside the right mounting interface for connecting with the locking damping actuator cylinder.

[0010] Preferably, protrusions are provided on both sides of the rear locking strut near the left mounting interface, and the protrusions are used to cooperate with the unlocking rocker arm to transmit the driving force of the unlocking actuator to the rear locking strut.

[0011] Preferably, the locking damping actuator includes a left joint, a right joint, an outer tube, a piston and a floating piston, the left joint is used to connect to the locking spring, the right joint is used to connect to the rear locking support rod, the left joint is connected to the outer tube, the piston is connected to the right joint, the floating piston is arranged in the outer tube and a high-pressure air chamber is formed on one side between the floating piston and the outer tube, the floating piston and the other side of the outer tube have a gap, the piston is arranged on the outside of the floating piston and is located in the gap between the floating piston and the outer tube, thereby forming a high-pressure oil chamber between the piston and the outer tube.

[0012] Preferably, sealing rings are provided between the floating piston and the outer cylinder, between the floating piston and the piston, and between the piston and the outer cylinder.

[0013] Preferably, the locking damping actuator realizes damping and shock absorption through the high-pressure air chamber, and realizes angle folding drive through the high-pressure oil chamber.

[0014] The aircraft landing gear strut lock of the present application can realize locking and stopping, has firm locking, reliable unlocking, occupies little space, and can realize large-angle folding. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.

[0016] Figure 1 This is a schematic diagram of the landing gear strut lock structure of the present application.

[0017] Figure 2 This is a schematic diagram of the positions of the front locking support rod and the unlocking rocker arm in this application.

[0018] Figure 3 Schematic diagram of the rear locking support rod in this application.

[0019] Figure 4 It is a schematic diagram of the locking damping actuator in this application.

[0020] Figure 5 This is a schematic diagram of the uniform distribution of the locking damping actuator in this application.

[0021] Figure 6 Schematic diagram of the piston assembly in this application.

[0022] Figure 7 This is a schematic diagram of the landing gear strut lock in the lowered position of the present application.

[0023] Figure 8 This is a schematic diagram of the unlocked position of the landing gear strut lock of the present application.

[0024] Fig. 9 This is a schematic diagram of the large-angle folding of the landing gear strut lock of the present application. DETAILED DESCRIPTION

[0025] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application.

[0026] When the retractable space is extremely narrow, the strut lock needs to be folded to a larger angle, which often leads to an unbalanced locking and unlocking ability. Therefore, in order to improve the locking ability while ensuring good unlocking ability, the present application provides a landing gear strut lock.

[0027] like Figures 1 to 6 As shown, the landing gear strut lock 10 provided in the present application includes a front locking strut 1, a rear locking strut 2, an unlocking rocker arm 3, an unlocking actuator 4, a locking damping actuator 5 and a locking spring 6.

[0028] Among them, one end of the front lock strut 1 is connected to the landing gear strut 20, and the other end of the front lock strut 1 is hinged to the rear lock strut 2. The other end of the rear lock strut 2 is installed on the landing gear strut 30 and is hinged to the locking damping actuator 5.

[0029] The unlocking rocker arm 3 is arranged at the hinge of the front locking support rod 1 and the rear locking support rod 2. One end of the unlocking actuator 4 is connected to the front locking support rod 1, and the other end is connected to the unlocking rocker arm 3.

[0030] The two ends of the locking damping actuator cylinder 5 are respectively connected to the rear locking support rod 2 and the locking spring 6. The two ends of the locking spring 6 are respectively connected to the front locking support rod 1 and the locking damping actuator cylinder 5.

[0031] like Figure 2 As shown, spring shafts 11 are provided on both sides of the middle of the front lock support rod 1 , and the spring shafts 11 are used for installing the locking spring 6 .

[0032] In some embodiments of the present application, the unlocking rocker arm 3 has double-ear structures at both ends.

[0033] like Figure 3As shown, a left mounting interface 21 is provided on the left side of the rear lock support rod 2, and a first rotating shaft 23 is provided therein for articulation with the front lock support rod 1. A protrusion 26 is provided on the side of the rear lock support rod 2 close to the first rotating shaft 23, and the protrusion 26 is used to cooperate with the unlocking rocker arm 3. Under the drive of the unlocking actuator 4, the unlocking rocker arm 3 can be rotated to the protrusion 26, and a torque is applied to the protrusion 26, so that the rear lock support rod 2 rotates. A right mounting interface 22 is provided on the right side of the rear lock support rod 2, and a second rotating shaft 24 is provided inside the right mounting interface 22 for articulation with the landing gear strut 30. At the same time, third rotating shafts 25 are provided on both sides of the outer side of the right mounting interface 22 for articulation with the locking damping actuator 5.

[0034] In the present application, the locking spring 6 and the unlocking actuator 4 are both arranged on both sides of the front locking strut 1 or the rear strut 2, which can adapt to the space for large folding and the strut structure is simple.

[0035] like Figures 4 to 6 As shown, the locking damping actuator 5 includes a left joint 51, a right joint 52, an outer tube 53, a piston 54 and a floating piston 55. The left joint 51 is used to connect with the locking spring 6, and the right joint 52 is used to connect with the rear lock support rod 2. The left joint 51 and the outer tube 53 can be connected by a threaded structure, and the piston 54 and the right joint 52 can be connected by threads or welding to form a piston assembly. The floating piston 55 is arranged in the outer tube 53, and a high-pressure air chamber A is formed on the left side between the two. There is a gap between the floating piston 55 and the right side of the outer tube 53. The piston 54 is arranged outside the floating piston 55 and is located in the gap between the floating piston 55 and the outer tube 53, so that a high-pressure oil chamber B is formed between the piston 54 and the outer tube 53. Through the high-pressure air chamber A, the locking damping actuator 5 provides locking damping, and through the high-pressure oil chamber B, the locking damping actuator 5 also provides locking assistance.

[0036] In some embodiments of the present application, sealing rings 56 may be provided between the floating piston 55 and the outer cylinder 53 , between the floating piston 55 and the piston 54 , and between the piston 54 and the outer cylinder 53 .

[0037] like Figures 7 to 9 As shown, the front lock strut 1 in the landing gear strut lock 10 of the present application is hinged to the landing gear support 20, the rear lock strut 2 is hinged to the landing gear strut 30 through the second rotating shaft 24, and the hinge point of the locking damping actuator 5 and the locking spring 6 is connected to the landing gear strut 30. The unlocking actuator 4 can realize the unlocking and lowering of the landing gear support 20 and the landing gear strut 30, and the locking damping actuator 5 can make the landing gear support 20 and the landing gear strut 30 folded at a large angle.

[0038] In the present application, there are two locking springs 6 and two locking damping actuators 5, and the locking springs 6 and the locking damping actuators 5 are respectively arranged in parallel. The lateral arrangement of the double locking springs 6 and the double locking damping actuators 5 realizes the requirements of large folding angle retraction and locking, reduces the locking impact load and enhances the locking ability.

[0039] In the present application, an independent external unlocking rocker arm 3 is provided to achieve the purpose of unlocking and adapt to large-angle folding. The unlocking mechanism is simple and reliable, and both locking performance and unlocking performance are given equal importance.

[0040] The aircraft landing gear strut lock of the present application can realize locking and stopping, has firm locking, reliable unlocking, occupies little space, and can realize large-angle folding.

[0041] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. An aircraft landing gear strut lock, characterized in that: include: A front locking strut, a rear locking strut, an unlocking rocker arm, an unlocking actuator, a locking damping actuator and a locking spring, wherein one end of the front locking strut is connected to the landing gear strut, the other end of the front locking strut is hinged to the rear locking strut, the other end of the rear locking strut is hinged to the landing gear strut and hinged to the locking damping actuator, the unlocking rocker arm is arranged at the hinge of the front locking strut and the rear locking strut, one end of the unlocking actuator is connected to the front locking strut, and the other end is connected to the unlocking rocker arm, one end of the locking damping actuator is hinged to the rear locking strut, and the other end is connected to the locking spring, the other end of the locking spring is connected to the front locking strut, and the connecting end of the locking spring and the locking damping actuator is arranged on the landing gear strut.

2. The aircraft landing gear strut lock according to claim 1, characterized in that: There are two locking damping actuators and two locking springs, and the two locking damping actuators are arranged in parallel, and the two locking springs are arranged in parallel.

3. The aircraft landing gear strut lock according to claim 2, characterized in that: Spring shafts are arranged on both sides of the front locking support rod, and the spring shafts are used to connect the locking springs.

4. The aircraft landing gear strut lock according to claim 1, characterized in that: The unlocking actuator and the locking spring are located on both sides of the front locking support rod.

5. The aircraft landing gear strut lock according to claim 1, characterized in that: Both ends of the unlocking rocker arm are double-ear structures.

6. The aircraft landing gear strut lock according to claim 5, characterized in that: A left mounting interface is provided on one side of the rear locking strut rod, and a first rotating shaft is provided inside the left mounting interface for connecting with the front locking strut rod; a right mounting interface is provided on the other side of the rear locking strut rod, and a second rotating shaft is provided inside the right mounting interface for connecting with the landing gear strut, and a third rotating shaft is provided outside the right mounting interface for connecting with the locking damping actuator cylinder.

7. The aircraft landing gear strut lock according to claim 6, characterized in that: The rear locking support rod is provided with protrusions on both sides close to the left mounting interface, and the protrusions are used to cooperate with the unlocking rocker arm to transmit the driving force of the unlocking actuator to the rear locking support rod.

8. The aircraft landing gear strut lock according to claim 1, characterized in that: The locking damping actuator includes a left joint, a right joint, an outer tube, a piston and a floating piston. The left joint is used to connect with the locking spring, the right joint is used to connect with the rear locking support rod, the left joint is connected with the outer tube, and the piston is connected with the right joint. The floating piston is arranged in the outer tube and a high-pressure air chamber is formed on one side between the floating piston and the outer tube, and a gap is provided between the floating piston and the other side of the outer tube. The piston is arranged on the outside of the floating piston and is located in the gap between the floating piston and the outer tube, thereby forming a high-pressure oil chamber between the piston and the outer tube.

9. The aircraft landing gear strut lock according to claim 8, characterized in that: Sealing rings are arranged between the floating piston and the outer cylinder, between the floating piston and the piston, and between the piston and the outer cylinder.

10. The aircraft landing gear strut lock according to claim 8, characterized in that: The locking damping actuator realizes damping and shock absorption through the high-pressure air chamber, and realizes angle folding drive through the high-pressure oil chamber.

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