Undercarriage folding and unfolding actuator cylinder with buffer devices at two ends
By designing the outer cylinder of the actuator cylinder and the guide sleeve as one, and a buffer device is arranged on the circumference of the outer cylinder, the problem of inconvenient arrangement of the buffer device is solved, and the effects of weight reduction and mechanical impact reduction are achieved.
Patent Information
- Application Number
- CN202422444845.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-10-10
- Publication Date
- 2025-07-04
- Estimated Expiration
- 2034-10-10
AI Technical Summary
In the prior art, the integrated design of the operating barrel guide sleeve and the outer barrel leads to inconvenient arrangement of the buffer device and affects product performance.
The outer cylinder of the actuator cylinder is designed as one and the guide sleeve, and an end buffer device is arranged on the circumference of the outer cylinder. The structure with buffering devices at both ends is adopted, and the buffering effect is achieved through the design of the oil hole on the piston rod motion path.
A buffer structure is arranged at the end of the actuator cylinder, which reduces weight and reduces mechanical impact, and improves the performance of the actuator cylinder.
Smart Images
Figure CN223059246U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to a landing gear retraction actuator, in particular to a landing gear retraction actuator with buffer devices at both ends. Background Art
[0002] The landing gear retraction actuator belongs to the landing gear retraction subsystem of the flight control system - hydraulic subsystem. The landing gear retraction actuator of an aircraft adopts a hydraulic actuation method, generally pressurized by the on-board hydraulic system. When the aircraft takes off and lands, it overcomes the retraction and extension loads, causing the piston rod of the retraction actuator to retract / extend, so as to realize the lowering / retracting of the landing gear strut to the locked position. To reduce the impact caused by retracting / extending the landing gear, buffer devices are arranged at the end of the actuator stroke. The general practice is to arrange the buffer device at one end inside the actuator and at the other end inside the actuator guide sleeve (the traditional actuator includes an outer cylinder and a guide sleeve, and the guide sleeve is arranged inside the outer cylinder for guiding the piston during movement). With the technical development of the landing gear retraction actuator, currently when designing the actuator, it is usually considered to design the actuator guide sleeve and the outer cylinder as one part to achieve the purpose of weight reduction. However, such a design will affect the arrangement of the buffer structure at the end of the actuator and has a certain impact on the product performance. Summary of the Utility Model
[0003] The technical problem to be solved by the utility model is that, aiming at the inconvenience of arranging the buffer device caused by the integrated design of the actuator guide sleeve and the outer cylinder, the utility model provides a landing gear retraction actuator with buffer devices at both ends.
[0004] To solve the above technical problem, the utility model adopts the following technical scheme:
[0005] A landing gear retraction actuator with buffer devices at both ends includes a cylinder body and a piston. The piston is slidably installed in the cylinder body, and the piston is sealingly connected to the cylinder body. The cylinder body is divided into a rodless chamber and a rod chamber by the piston. A first oil port is arranged on the rodless chamber, and a second oil port and a third oil port are sequentially arranged at the end of the rod chamber. A buffer device installation position is arranged on the cylinder body between the second oil port and the third oil port. A second buffer device is installed at the buffer device installation position. A second nozzle is installed in the second oil port. The second nozzle is connected to the oil outlet of the second buffer device, and the oil inlet of the second buffer device is connected to the third oil port.
[0006] Preferably, a first oil passage hole is arranged at the upper part of the second nozzle, a second oil passage hole is arranged in the middle part, and a plurality of third oil passage holes communicating with the rod chamber are arranged at the lower part. The first oil passage hole, the second oil passage hole, and the third oil passage holes are sequentially communicated, and the second oil passage hole is communicated with the oil outlet of the second buffer device.
[0007] Preferably, a plurality of the second oil passing holes are arranged in sequence along the movement path of the piston rod.
[0008] Preferably, the aperture of the second oil passing hole is larger than that of the third oil passing hole.
[0009] Preferably, the piston and the cylinder body are hermetically connected through a sealing ring and an expansion ring.
[0010] Preferably, a first buffer device is installed at the end of the rodless cavity.
[0011] Preferably, a first nozzle is installed on the first oil port.
[0012] Preferably, weight-reducing grooves are respectively arranged on the cylinder body and the piston.
[0013] Preferably, the installation position of the buffer device is integrally formed with the outer cylinder of the cylinder body.
[0014] In the present utility model, the outer cylinder of the actuating cylinder and the guide sleeve are designed as a whole, and a terminal buffer device (second buffer device) is arranged on the circumference of the outer cylinder, which solves the problem that when the outer cylinder of the actuating cylinder and the guide sleeve are designed as a whole, the terminal buffer device of the actuating cylinder cannot be arranged, or solves the problem that after the buffer device is arranged at the end of the actuating cylinder, the outer cylinder and the guide sleeve cannot be designed as a whole.
[0015] Compared with the traditional structure in which the buffer device is arranged in the guide sleeve of the actuating cylinder, the present utility model can reduce the weight of the actuating cylinder; compared with the structure in which the guide sleeve and the outer cylinder of the actuating cylinder are designed as one part, a buffer structure can be arranged at the end of the actuating cylinder to achieve the effect of terminal buffering. BRIEF DESCRIPTION OF THE DRAWINGS
[0016] In order to more clearly illustrate the technical solutions in the embodiments of the present utility model or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present utility model. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.
[0017] Figure 1 It is a cross-sectional view of the landing gear retraction and extension actuating cylinder with buffer devices at both ends of the present utility model.
[0018] Figure 2 It is a schematic diagram of the state at the start of buffering of the present utility model.
[0019] Figure 3 It is a schematic diagram of the state during buffering of the present utility model.
[0020] Figure 4 It is a schematic diagram of the state at the end of buffering of the present utility model.
[0021] In the figure: 1 end cap, 2 first nozzle, 3 outer cylinder, 4 sealing ring, 5 expansion ring, 6 piston rod, 7 second nozzle, 8 second buffer device, 9 piston, 10 first oil port, 11 first buffer device, 12 second oil port, 13 third oil port, 14 first oil passage hole, 15 second oil passage hole, 16 third oil passage hole. Specific embodiments
[0022] The present invention will be further described below in conjunction with specific preferred embodiments, but the protection scope of the present invention is not limited thereby.
[0023] In the description of the present invention, it should be noted that the orientation or positional relationship indicated by the terms "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present invention. In addition, the terms "first", "second", and "third" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance.
[0024] In the description of the present invention, it should be noted that unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection; it can be directly connected, or indirectly connected through an intermediate medium, and it can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.
[0025] Please refer to Figure 1 , an embodiment of the landing gear retraction and extension actuator with buffer devices at both ends of the present invention includes an end cap 1, a first nozzle 2, an outer cylinder 3, a sealing ring 4, an expansion ring 5, a piston rod 6, a second nozzle 7, a buffer device assembly 8, and a piston 9. The end cap 1 closes one end of the outer cylinder 3, and the other end of the outer cylinder 3 is used for sliding and sealing connection with the piston rod 6. The piston 9 is slidably installed in the outer cylinder 3, and the piston 9 is hermetically connected to the outer cylinder 3 through the sealing ring 4 and the expansion ring 5. The inside of the outer cylinder 3 is divided into a rodless cavity and a rod cavity by the piston 9.
[0026] A first oil port 10 and a first buffer device 11 are provided at the end of the rodless cavity, and the first nozzle 2 is installed on the first oil port 10.
[0027] The piston rod 6 is installed in the rod cavity, and one end of the piston rod 6 is fixedly connected to the piston 9, and the other end extends out of the outer cylinder 3.
[0028] A second oil port 12 and a third oil port 13 are sequentially arranged at the end of the rodless cavity. A buffer device mounting position 12 is integrally formed on the outer cylinder 3 between the second oil port 12 and the third oil port 13, and a second buffer device 8 is mounted on the buffer device mounting position 12. A second nozzle 7 is installed in the second oil port 12. A first oil passing hole 14 is arranged at the upper part of the second nozzle 7, a second oil passing hole 15 is arranged in the middle, and a plurality of third oil passing holes 16 communicating with the rodless cavity are arranged at the lower part. The first oil passing hole 14, the second oil passing hole 15, and the third oil passing holes 16 are sequentially communicated, and the second oil passing hole 15 is communicated with the oil outlet of the second buffer device 8. The aperture of the second oil passing hole 15 is larger than the aperture of the third oil passing hole 16 to ensure that the hydraulic oil flowing out from the oil outlet of the second buffer device 8 directly flows out through the second oil passing hole 15 and the first oil passing hole 14 in sequence. The third oil port 13 is communicated with the oil inlet of the second buffer device 8.
[0029] It should be noted that the first buffer device 11 and the second buffer device 8 mentioned in this article are both prior arts, so no more description will be given here.
[0030] A guiding structure (not shown in the figure) is arranged on the inner wall of the outer cylinder 3. The piston rod 6 or the piston 9 is connected with the guiding structure, and during the movement of the piston 9, the inner wall of the outer cylinder 3 is directly used as a guiding sleeve.
[0031] When the present utility model is in use, when the piston rod 6 is in the fully compressed position, oil enters through the first nozzle 2. Under the action of the oil pressure, the piston 9 is pushed to gradually extend the piston rod 6. When the piston rod 6 does not enter the buffer stroke, since the piston 9 and the outer cylinder 3 are hermetically connected through the sealing ring 4 and the expansion ring 5, the rodless cavity forms a damping cavity. The oil in the rodless cavity is decelerated by directly returning oil through a plurality of third oil passing holes 16 with smaller apertures (in this embodiment, the aperture of the third oil passing hole 16 is Φ3) centrally arranged below the second nozzle 7, the second oil passing hole 15, and the first oil passing hole 14, as shown in Figure 2 ; when the piston rod 6 extends to enter the buffer stroke, the oil in the rodless cavity can only return oil through the third oil port 13, the second buffer device 8, the second oil passing hole 15, and the third oil passing holes 16 of the second nozzle 7 in sequence, as shown in Figure 3 . The oil flows through the second buffer device 8 to generate a damping force, thereby further slowing down the movement speed of the piston rod 6 and greatly reducing the mechanical impact at the end of the actuator.
[0032] As described above, it is only the specific implementation of the present utility model, but the protection scope of the present utility model is not limited thereto. Any person skilled in the art can make many possible changes and modifications to the technical solution of the present utility model by using the technical content disclosed above, or modify it into an equivalent embodiment with equivalent changes. Therefore, all content that does not depart from the technical solution of the present utility model, any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present utility model shall fall within the protection scope of the technical solution of the present utility model.
Claims
1. A landing gear retraction actuator with buffer devices at both ends, comprising a cylinder body and a piston. The piston is slidably installed in the cylinder body, and the piston is sealingly connected to the cylinder body. The cylinder body is divided into a rodless chamber and a rod chamber by the piston. A first oil port is provided on the rodless chamber, and it is characterized in that: A second oil port and a third oil port are sequentially arranged at the end of the rod chamber. A buffer device installation position is arranged on the cylinder body between the second oil port and the third oil port. A second buffer device is installed at the buffer device installation position. A second nozzle is installed in the second oil port. The second nozzle is connected to the oil outlet of the second buffer device. The oil inlet of the second buffer device is connected to the third oil port.
2. The landing gear retraction actuator with buffer devices at both ends according to claim 1, wherein A first oil passing hole is arranged at the upper part of the second nozzle, a second oil passing hole is arranged in the middle part, and a plurality of third oil passing holes communicating with the rod chamber are arranged at the lower part. The first oil passing hole, the second oil passing hole, and the third oil passing holes are sequentially communicated, and the second oil passing hole is communicated with the oil outlet of the second buffer device.
3. The landing gear retraction actuator with buffer devices at both ends according to claim 2, characterized in that, A plurality of the second oil passing holes are sequentially arranged along the movement path of the piston rod.
4. The landing gear retraction and extension actuator with buffer devices at both ends according to claim 2, characterized in that, The aperture of the second oil passing hole is larger than the aperture of the third oil passing hole.
5. The landing gear retraction actuator with buffer devices at both ends according to any one of claims 1-4, characterized in that, The piston and the cylinder body are hermetically connected through a sealing ring and an expansion ring.
6. The landing gear retraction actuator with buffer devices at both ends according to any one of claims 1-4, characterized in that, A first buffer device is installed at the end of the rodless chamber.
7. The landing gear retraction and extension actuator with buffer devices at both ends according to any one of claims 1-4, characterized in that A first nozzle is installed on the first oil port.
8. The landing gear retraction actuator with buffer devices at both ends according to any one of claims 1-4, characterized in that, Weight-reducing grooves are respectively arranged on the cylinder body and the piston.
9. The landing gear retraction actuator with buffer devices at both ends according to any one of claims 1-4, characterized in that, The buffer device installation position is integrally formed with the outer cylinder of the cylinder body.