An aircraft landing gear strut lock

Abstract

The application provides an aircraft landing gear support rod lock, belonging to the technical field of aircraft landing gears, and comprising a front lock support rod, a rear lock support rod, an unlocking rocker arm, an unlocking actuating cylinder, an upper lock damping actuating cylinder and an upper lock spring, wherein one end of the front lock support rod is connected with the landing gear support rod, the other end of the front lock support rod is hingedly connected with the rear lock support rod, the other end of the rear lock support rod is hingedly connected on the landing gear strut and is hingedly connected with the upper lock damping actuating cylinder, the unlocking rocker arm is arranged at the hinge connection between the front lock support rod and the rear lock support rod, one end of the unlocking actuating cylinder is connected with the front lock support rod and the other end is connected on the unlocking rocker arm, one end of the upper lock damping actuating cylinder is hingedly connected with the rear lock support rod and the other end is connected with the upper lock spring, the other end of the upper lock spring is connected with the front lock support rod, and the connection end of the upper lock spring and the upper lock damping actuating cylinder is arranged on the landing gear strut.

Description

Technical Field

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

[0002] Aircraft landing gear struts support the landing gear struts. When the landing gear is extended, a strut lock mechanism is required to lock the struts in a position supporting the landing gear struts. Simultaneously, when the landing gear is retracted, the struts are locked to the landing gear struts. Furthermore, the angle between the struts and the landing gear struts is large between the retracted and extended positions. Due to the limited space available for retracting the landing gear, existing landing gear strut locks cannot meet this wide-angle locking requirement. Summary of the Invention

[0003] The purpose 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, and the other end of the front locking strut is hinged to the rear locking strut, and the other end of the rear locking strut is hinged on 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, and 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, and a first rotating shaft is provided inside the left mounting interface for connecting to the front locking strut; a right mounting interface is provided on the other side of the rear locking strut, and a second rotating shaft is provided inside the right mounting interface for connecting to the landing gear strut, and a third rotating shaft is provided outside the right mounting interface for connecting to 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 lock support rod, the left joint is connected to the outer tube, and 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, 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.

[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 achieve locking and stopping, has firm locking, reliable unlocking, occupies little space, and can be folded at a large angle. BRIEF DESCRIPTION OF THE DRAWINGS

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

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

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

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

[0019] Figure 4 Schematic diagram of the locking damping actuator in this application.

[0020] Figure 5 This is an enlarged 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 this application.

[0024] Figure 9 This is a schematic diagram of the landing gear strut lock folding at a large angle according to 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 retraction space is extremely narrow, the strut lock needs to fold to a larger angle, which often leads to an imbalance between its locking ability and unlocking ability. Therefore, in order to improve the locking ability while ensuring it has 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 lock support rod 1 and the rear lock support rod 2. One end of the unlocking actuator 4 is connected to the front lock support rod 1, and the other end is connected to the unlocking rocker arm 3.

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

[0031] like Figure 2 As shown, spring shafts 11 are provided on both sides of the middle portion 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 a double-ear structure at both ends.

[0033] like Figure 3As shown, the left side of the rear lock strut 2 is provided with a left mounting interface 21, within which is housed a first rotating shaft 23 for articulating with the front lock strut 1. A protrusion 26 is provided on the side of the rear lock strut 2 near the first rotating shaft 23. This protrusion 26 is designed to engage with the unlock rocker arm 3. Driven by the unlock actuator 4, the unlock rocker arm 3 can be rotated to the protrusion 26, applying torque to the protrusion 26, thereby rotating the rear lock strut 2. A right mounting interface 22 is provided on the right side of the rear lock strut 2. A second rotating shaft 24 is located inside the right mounting interface 22 for articulating with the landing gear strut 30. Furthermore, third rotating shafts 25 are located on both sides of the outside of the right mounting interface 22 for articulating 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 meet the needs of large folding space and have a simple strut structure.

[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 connected to the locking spring 6, and the right joint 52 is connected to the rear lock strut 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 disposed within the outer tube 53, forming a high-pressure air chamber A on the left side between the two. A gap is defined between the floating piston 55 and the right side of the outer tube 53. The piston 54 is disposed outside the floating piston 55 and located within the gap between the floating piston 55 and the outer tube 53, thereby forming a high-pressure oil chamber B between the piston 54 and the outer tube 53. The locking damping actuator 5 provides locking damping through the high-pressure air chamber A, and provides locking assistance through the high-pressure oil chamber B.

[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, in the landing gear strut lock 10 of the present application, the front lock strut 1 is hinged to the landing gear frame 20, the rear lock strut 2 is hinged to the landing gear strut 30 via a second rotating shaft 24, and the hinge point between 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 frame 20 and the landing gear strut 30, and the locking damping actuator 5 can realize the folding of the landing gear frame 20 and the landing gear strut 30 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 arranged in parallel. The lateral arrangement of the double locking springs 6 and the double locking damping actuators 5 realizes the large folding angle retraction and locking requirements, 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 unlocking purpose 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 achieve locking and stopping, has firm locking, reliable unlocking, occupies little space, and can be folded at a large angle.

[0041] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in this application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection 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 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 locking The connecting end of the spring and the locking damping actuator is set on the landing gear strut, wherein 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 lock support rod, the left joint is connected to the outer tube, and the piston is connected to the right joint. The floating piston is set 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 set on the outside of the floating piston and is located in the gap between the floating piston and the outer tube, so that a high-pressure oil chamber is formed between the piston and the outer tube.

2. The aircraft landing gear strut lock according to claim 1, wherein: 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, wherein: Spring shafts are provided 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, wherein: 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, wherein: Both ends of the unlocking rocker arm are double-ear structures.

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

7. The aircraft landing gear strut lock according to claim 6, wherein: The rear locking strut 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 unlocking actuator driving force to the rear locking strut.

8. The aircraft landing gear strut lock according to claim 1, wherein: 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.

9. The aircraft landing gear strut lock according to claim 1, wherein: 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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