Aircraft landing gear pull rod fixing device

Abstract

The utility model discloses an aircraft landing gear pull rod fixing device which is applied to the technical field of aircraft landing gears and comprises a fixed sliding rail, a motor is connected to one side of the outer portion of the fixed sliding rail in a bolting mode, the output end of the motor is fixedly connected with a threaded rod rotationally connected with the fixed sliding rail, and the surface of the threaded rod is sleeved with a threaded sleeve in a threaded mode. A rotating rod is welded to the side, close to the motor, of the bottom of the fixed sliding rail. When the motor drives the hydraulic cylinder to rotate by an angle to open, the hydraulic cylinder is started to drive the aircraft wheels to move up and down. Therefore, the aircraft landing gear can be quickly opened or closed, and the opening and retracting efficiency of the aircraft landing gear is improved. By means of the telescopic arc plates and the buffer springs, one end of the aircraft wheel can rotate between the two telescopic arc plates, and meanwhile impact force making contact with the ground is buffered. And the undercarriage can be buffered and protected, and damage is reduced. And the vibration sense is reduced, and the practicability is improved.

Description

Technical Field

[0001] The utility model belongs to the technical field of aircraft landing gears, and particularly relates to a tie rod fixing device for an aircraft landing gear. Background Art

[0002] The aircraft landing gear is an accessory device at the bottom of the aircraft used to support the aircraft during takeoff, landing or ground taxiing and to move on the ground. The aircraft landing gear generally requires the use of tie rods to install and fix the aircraft wheels.

[0003] At present, a Chinese utility model with the announcement number of CN219029758U discloses a helicopter landing gear fixing device, which relates to the technical field of support machine fixing. The device includes at least one locking device, which is used to lock the support tube of the landing gear. The locking device includes: a clamp base, which is used to be fixed on the helicopter transport carrier; a holding piece, one end of the holding piece is rotatably connected to an edge wall of the clamp base, and the holding surface of the holding piece and the top surface of the clamp base are both provided with clamping grooves. When the two clamping grooves are combined, a clamping cavity for clamping the support tube can be formed, and the other end of the holding piece can be clamped on the other edge wall of the clamp base. The utility model has a simple structure, and the landing gear can be clamped and fixed without tools. The operation is simple and quick, and the reliability and safety are ensured by using a purely mechanical structure.

[0004] After the existing aircraft landing gear is installed and fixed inside the aircraft wheel compartment, it is generally necessary to rotate the aircraft landing gear from the inside of the compartment to open it, and then the height of the aircraft wheel can be raised and lowered to make the aircraft wheel contact the ground. In this way, the aircraft landing gear is relatively slow whether it is opened or closed. In addition, when the aircraft landing gear is opened and the aircraft wheel contacts the ground, a large impact force will be generated, which will cause certain damage to the aircraft landing gear. For a long time, it is easy to cause the aircraft landing gear tie rod to bend and deform or the various components to be loosely connected, resulting in unstable aircraft taxiing and reducing the service life of the aircraft landing gear. Utility Model Content

[0005] The utility model aims to provide an aircraft landing gear tie rod fixing device, which has the advantages of improving the efficiency of opening and retracting the aircraft landing gear and buffering the impact force generated when the aircraft landing gear descends to the ground, thereby improving the sliding stability.

[0006] The above technical purpose of the utility model is achieved through the following technical scheme: a device for fixing an aircraft landing gear tie rod, comprising a fixed slide rail, a motor is bolted to one side of the outside of the fixed slide rail, a threaded rod rotatably connected to the fixed slide rail is fixedly connected to the output end of the motor, a threaded sleeve is threadedly sleeved on the surface of the threaded rod, a rotating rod is welded on the side of the bottom of the fixed slide rail close to the motor, a hydraulic cylinder is rotatably connected to the bottom of the rotating rod, a rotating joint is bolted to the surface of the hydraulic cylinder and the bottom of the threaded sleeve, and a support rod is rotatably connected between the hydraulic cylinder and the threaded sleeve via a rotating joint.

[0007] By adopting the above technical solution, when the motor drives the hydraulic cylinder to rotate and open, the hydraulic cylinder is turned on at the same time to drive the aircraft wheel to move up and down. Therefore, the aircraft landing gear can be quickly opened or closed, and the efficiency of opening and retracting the aircraft landing gear is improved. By using the telescopic arc plate and the buffer spring, one end of the aircraft wheel can rotate between the two telescopic arc plates, and at the same time, the impact force of contacting the ground is buffered. Not only can the aircraft landing gear be buffered and protected to reduce damage, but also the vibration is reduced, improving practicality.

[0008] The utility model is further configured as follows: a fixed block is bolted to the output end of the hydraulic cylinder, connecting plates are welded on both sides of the fixed block, a fixed seat is installed on the side of the connecting plate away from the fixed block, telescopic arc plates are slidably connected to both sides of the top and bottom of the inner cavity of the fixed seat, a rotating joint is slidably sleeved between the two telescopic arc plates, and a buffer spring fixedly connected to the fixed seat is fixedly connected to one end of the telescopic arc plate away from the rotating joint.

[0009] The above technical solution can not only provide buffer protection for the aircraft landing gear and reduce damage, but also reduce vibration and improve practicality.

[0010] The utility model is further configured as follows: bolting pieces are welded on the four corners of the top of the fixed slide rail.

[0011] The adoption of the technical solution makes it easy to install the aircraft landing gear inside the aircraft wheel well.

[0012] The utility model is further configured as follows: the fixed block and the hydraulic cylinder surface are rotatably connected to the first reinforcement rod and the second reinforcement rod at one side away from the support rod, and the first reinforcement rod and the second reinforcement rod are rotatably connected at one end close to each other.

[0013] By adopting the above technical solution, the fixed block is supported and reinforced when sliding up and down, thereby improving the sliding stability.

[0014] The utility model is further configured as follows: a rotating shaft is welded to one end of the rotating joint away from the interior of the fixing seat, a mounting plate is bolted to one side of the rotating shaft away from the fixing seat, aircraft wheels are arranged on both sides of the fixing block, and the rotating shaft is bolted to the aircraft wheels through the mounting plate.

[0015] By adopting the above technical solution, the aircraft wheel can be installed and disassembled from both sides of the fixing block, thereby facilitating the inspection and maintenance of the parts.

[0016] The utility model is further configured as follows: the surfaces of the rotating joints are all rotatably connected with balls that are slidably connected to the telescopic arc plates.

[0017] By adopting the above technical solution, the friction force of the rotating joint when rotating between the two telescopic arc plates is reduced, thereby improving the rotation stability.

[0018] The utility model is further configured as follows: a bolt threadedly penetrates the interior of the connecting plate and is connected to the fixing seat.

[0019] By adopting the above technical solution, the connecting plate and the fixing seat can be disassembled, thereby facilitating the replacement of internal parts.

[0020] In summary, the utility model has the following beneficial effects:

[0021] 1. When the motor drives the hydraulic cylinder to rotate and open, the hydraulic cylinder is turned on at the same time to drive the aircraft wheels to move up and down. This allows the aircraft landing gear to be opened or closed quickly, improving the efficiency of opening and retracting the aircraft landing gear;

[0022] 2. By using the telescopic arc plate and buffer spring, one end of the aircraft wheel can rotate between the two telescopic arc plates, and at the same time, the impact force of contacting the ground can be buffered. It can not only buffer and protect the aircraft landing gear and reduce damage, but also reduce the vibration and improve practicality. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 It is a schematic diagram of the structure of the utility model;

[0024] Figure 2 It is a cross-sectional view of the structure of the utility model;

[0025] Figure 3 It is a side sectional view of the local structure of the utility model;

[0026] Figure 4 It is a cross-sectional view of another side of the local structure of the utility model;

[0027] Figure 5 This utility model Figure 2 Enlarged view of point A in .

[0028] Figure numerals: 1. fixed slide rail; 2. motor; 3. hydraulic cylinder; 4. rotating rod; 5. threaded rod; 6. threaded sleeve; 7. rotating joint; 8. support rod; 9. fixed block; 10. connecting plate; 11. fixed seat; 12. rotating shaft; 13. rotating joint; 14. telescopic arc plate; 15. buffer spring; 16. mounting plate; 17. aircraft wheel; 18. bolt plate; 19. first reinforcement rod; 20. second reinforcement rod; 21. ball bearing; 22. bolt. DETAILED DESCRIPTION

[0029] The utility model is further described in detail below in conjunction with the accompanying drawings.

[0030] Embodiment 1:

[0031] refer to Figure 1 , Figure 2 , Figure 5 A device for fixing the tie rod of an aircraft landing gear comprises a fixed rail 1, a motor 2 is bolted to one side of the outside of the fixed rail 1, a threaded rod 5 rotatably connected to the fixed rail 1 is fixedly connected to the output end of the motor 2, a threaded sleeve 6 is threadedly sleeved on the surface of the threaded rod 5, a rotating rod 4 is welded to the side of the bottom of the fixed rail 1 close to the motor 2, a hydraulic cylinder 3 is rotatably connected to the bottom of the rotating rod 4, a rotating joint 7 is bolted to the surface of the hydraulic cylinder 3 and the bottom of the threaded sleeve 6, and a support rod 8 is rotatably connected between the hydraulic cylinder 3 and the threaded sleeve 6 through the rotating joint 7. When the hydraulic cylinder 3 is driven by the motor 2 to rotate and open, the hydraulic cylinder 3 is turned on at the same time to drive the aircraft wheels to move up and down. Thereby, the aircraft landing gear can be quickly opened or closed, and the efficiency of opening and retracting the aircraft landing gear is improved.

[0032] refer to Figure 1 , Figure 2 The four corners at the top of the fixed slide rail 1 are all welded with bolting pieces 18. It is convenient to install the aircraft landing gear inside the aircraft wheel compartment.

[0033] Brief description of the use process: by turning on the motor 2, the threaded rod 5 is driven to rotate inside the fixed rail 1, so that the threaded rod 5 and the threaded sleeve 6 can be threadedly engaged to drive the threaded sleeve 6 to slide back and forth left and right inside the fixed rail 1. Then, the support rod 8 is rotated on one side of the hydraulic cylinder 3 and the bottom of the threaded sleeve 6 by using the rotating joint 7, so that when the threaded sleeve 6 slides to one side, it drives the support rod 8 to support the hydraulic cylinder 3, so that the hydraulic cylinder 3 is vertically downward from the bottom of the fixed rail 1 through the rotating rod 4, so that the aircraft landing gear can be quickly opened. At the same time, when the threaded sleeve 6 slides to the other side, the support rod 8 can pull the hydraulic cylinder 3 to rotate and fold at the bottom of the fixed rail 1, so that the aircraft landing gear can be quickly retracted.

[0034] Embodiment 2:

[0035] refer to Figure 1 , Figure 2 , Figure 3 , Figure 4 A device for fixing the tie rod of an aircraft landing gear, wherein the output end of a hydraulic cylinder 3 is bolted with a fixing block 9, and connecting plates 10 are welded on both sides of the fixing block 9, and a fixing seat 11 is installed on the side of the connecting plate 10 away from the fixing block 9, and both sides of the top and bottom of the inner cavity of the fixing seat 11 are slidably connected with telescopic arc plates 14, and a rotating joint 13 is slidably sleeved between the two telescopic arc plates 14, and a buffer spring 15 fixedly connected to the fixing seat 11 is fixed at one end of the telescopic arc plate 14 away from the rotating joint 13. By using the telescopic arc plate 14 and the buffer spring 15, one end of the aircraft wheel 17 can rotate between the two telescopic arc plates 14, and at the same time, the impact force of contacting the ground is buffered. Not only can the aircraft landing gear be buffered and protected to reduce damage. It also reduces the sense of vibration and improves practicality.

[0036] refer to Figure 1 , Figure 2 The fixed block 9 and the hydraulic cylinder 3 are respectively connected to the first reinforcement rod 19 and the second reinforcement rod 20 on the side away from the support rod 8, and the first reinforcement rod 19 and the second reinforcement rod 20 are connected to each other on the ends close to each other. The fixed block 9 is supported and reinforced for sliding up and down to improve the sliding stability.

[0037] refer to Figure 1 , Figure 2 , Figure 3 The rotating shaft 12 is welded to one end of the rotating joint 13 away from the inside of the fixing seat 11, and the side of the rotating shaft 12 away from the fixing seat 11 is bolted with a mounting plate 16. Aircraft wheels 17 are arranged on both sides of the fixing block 9, and the rotating shaft 12 is bolted to the aircraft wheels 17 through the mounting plate 16. The aircraft wheels 17 can be installed and removed from both sides of the fixing block 9, so that the parts can be easily inspected and repaired.

[0038] refer to Figure 3 , Figure 4 The surface of the rotating joint 13 is rotatably connected with a ball 21 that is slidably connected to the telescopic arc plate 14. The friction force when the rotating joint 13 rotates between the two telescopic arc plates 14 is reduced, and the rotation stability is improved.

[0039] refer to Figure 1 , Figure 2 , Figure 3 The inside of the connecting plate 10 is threadedly connected with a bolt 22 that is bolted to the fixing seat 11. The connecting plate 10 and the fixing seat 11 can be disassembled, thereby facilitating the replacement of internal parts.

[0040] Brief description of the use process: The aircraft wheel 17 rotates between the two telescopic arc plates 14 using the rotating shaft 12 and the rotating joint 13, so that the elastic force of the buffer spring 15 can push the telescopic arc plate 14 to support the rotating joint 13, so that the aircraft wheel 17 can roll on the ground. At the same time, when the aircraft wheel 17 collides with the ground to generate impact force, the rotating joint 13 is driven to swing up and down between the two telescopic arc plates 14. The reciprocating rebound force of the buffer spring 15 buffers the aircraft wheel 17, thereby reducing the impact force of the collision with the aircraft landing gear.

[0041] This specific embodiment is merely an explanation of the present invention and is not a limitation of the present invention. After reading this specification, those skilled in the art may make non-creative modifications to the present embodiment as needed, but such modifications are protected by patent law as long as they are within the scope of the claims of the present invention.

Claims

1. An aircraft landing gear tie rod fixing device, comprising a fixing slide rail (1), characterized in that: A motor (2) is bolted to one side of the outside of the fixed slide rail (1); a threaded rod (5) rotatably connected to the fixed slide rail (1) is fixedly connected to the output end of the motor (2); a threaded sleeve (6) is threadedly sleeved on the surface of the threaded rod (5); a rotating rod (4) is welded to the side of the bottom of the fixed slide rail (1) close to the motor (2); a hydraulic cylinder (3) is rotatably connected to the bottom of the rotating rod (4); a rotating joint (7) is bolted to the surface of the hydraulic cylinder (3) and the bottom of the threaded sleeve (6); a support rod (8) is rotatably connected between the hydraulic cylinder (3) and the threaded sleeve (6) via the rotating joint (7).

2. The aircraft landing gear tie rod fixing device according to claim 1, characterized in that: The output end of the hydraulic cylinder (3) is bolted to a fixed block (9), and connecting plates (10) are welded on both sides of the fixed block (9). A fixed seat (11) is installed on the side of the connecting plate (10) away from the fixed block (9), and both sides of the top and bottom of the inner cavity of the fixed seat (11) are slidably connected with telescopic arc plates (14), and a rotating joint (13) is slidably sleeved between the two telescopic arc plates (14), and a buffer spring (15) fixedly connected to the fixed seat (11) is fixedly connected to one end of the telescopic arc plate (14) away from the rotating joint (13).

3. The aircraft landing gear tie rod fixing device according to claim 1, characterized in that: Bolt plates (18) are welded to the four corners of the top of the fixed slide rail (1).

4. The aircraft landing gear tie rod fixing device according to claim 2, characterized in that: The fixed block (9) and the hydraulic cylinder (3) are rotatably connected to the first reinforcing rod (19) and the second reinforcing rod (20) at the side away from the support rod (8) respectively, and the ends of the first reinforcing rod (19) and the second reinforcing rod (20) that are close to each other are rotatably connected.

5. The aircraft landing gear tie rod fixing device according to claim 2, characterized in that: A rotating shaft (12) is welded to one end of the rotating joint (13) away from the interior of the fixing seat (11); a mounting plate (16) is bolted to the side of the rotating shaft (12) away from the fixing seat (11); aircraft wheels (17) are provided on both sides of the fixing block (9); and the rotating shaft (12) is bolted to the aircraft wheels (17) via the mounting plate (16).

6. The aircraft landing gear tie rod fixing device according to claim 2, characterized in that: The surface of the rotating joint (13) is rotatably connected with a ball (21) which is slidably connected to the telescopic arc plate (14).

7. The aircraft landing gear tie rod fixing device according to claim 2, characterized in that: The interior of the connection plate (10) is threadedly connected with a bolt (22) that is bolted to the fixing seat (11).

Images