Simulated nose landing gear centering device

Abstract

According to the simulation nose landing gear centering device provided by the utility model, a cylinder actuation mode is adopted to replace a traditional hydraulic system, and a joint bearing and a connecting lug seat of a connecting assembly are matched, so that the coaxiality requirement is reduced, the machining precision requirement is reduced, the overall structure of the device is simplified, and the manufacturing and maintenance cost is remarkably reduced; meanwhile, the risk of hydraulic oil leakage is avoided. Due to the introduction of the thrust ball bearing and the sliding bearing, the smoothness of rotation and axial movement of the inner cylinder is remarkably improved, the problem of centering clamping caused by insufficient machining precision in the prior art is solved, and efficient and accurate centering of the inner cylinder is achieved. The centering structures symmetrically arranged on the two sides further enhance the centering stability and reliability, so that the device is suitable for a simulation experiment environment and has a wide application prospect.

Description

Technical Field

[0001] This utility model relates to the field of aircraft structure simulation technology, and more specifically, to a simulation nose landing gear centering device. Background Technology

[0002] The front landing gear centering mechanism is used to keep the front wheels in a centered position. Simulation can be used to verify its reliability and teach its principles. Existing simulated lifting and centering mechanisms typically use hydraulic actuation, consisting of a cylinder and piston rod, and require auxiliary equipment such as a hydraulic pump, hydraulic lines, and hydraulic valves. This hydraulic drive method requires high machining precision for the cylinder and piston rod, and the complexity of the system significantly increases manufacturing and maintenance costs. Furthermore, insufficient machining precision or inadequate filtration of the hydraulic oil can easily lead to cylinder actuation jamming and hydraulic oil leakage, which not only affects the stability and reliability of the system but also increases maintenance difficulty and usage risks.

[0003] In view of this, the applicant hereby submits this application after studying the existing technology. Utility Model Content

[0004] This invention provides a simulated nose landing gear centering device, which aims to improve at least one of the above-mentioned technical problems.

[0005] To solve the above-mentioned technical problems, this utility model provides a simulated nose landing gear centering device. The simulated nose landing gear includes an inner cylinder and an outer cylinder. The upper part of the inner cylinder is housed within the inner cavity of the outer cylinder. A centering device is connected between the inner cylinder and the outer cylinder. The centering device includes a cylinder, a centering ring, a centering component, and a connecting assembly. The cylinder is coaxially disposed at the top of the inner cavity, and the piston rod is vertically downward. The centering ring is coaxially mounted and fixed at the top of the inner cylinder. The inner cylinder is rotatably connected to the piston rod via the connecting assembly. The centering component is mounted and connected to the outer cylinder for centering in conjunction with the centering ring.

[0006] As a further optimization, the centering ring is provided with a downward-facing positioning port, and the distance between the two inner sides of the positioning port gradually decreases from bottom to top; the centering component is provided with a positioning part, which extends to the bottom of the positioning port.

[0007] As a further optimization, a centering groove is provided at the top of the positioning port; the top end of the positioning part is arc-shaped and adapted to the centering groove.

[0008] As a further optimization, two positioning ports are symmetrically arranged on both sides of the centering ring; two centering components are symmetrically arranged on the outer cylinder.

[0009] As a further optimization, the connecting assembly includes a spherical bearing, a connecting lug, a first bearing, a bolt with holes, and a connector; the spherical bearing is mounted on the bottom end of the piston rod and hinged to the connecting lug; the first bearing is connected between the bolt with holes and the connecting lug; the end of the bolt with holes passes through the top end of the inner cylinder and is coaxially connected to the inner cylinder via the connector.

[0010] As a further optimization, the first bearing is a thrust ball bearing.

[0011] As a further optimization, a second bearing, which is a sliding bearing, is also provided between the inner side of the outer cylinder and the outer side of the inner cylinder.

[0012] By adopting the above technical solution, the present invention can achieve the following technical effects:

[0013] This application provides a simulated nose landing gear centering device that replaces the traditional hydraulic system with a cylinder actuation method. Combined with the spherical bearings and connecting lugs of the connecting components, this reduces coaxiality requirements, decreases machining accuracy requirements, simplifies the overall structure of the device, significantly reduces manufacturing and maintenance costs, and avoids the risk of hydraulic oil leakage. The introduction of thrust ball bearings and sliding bearings significantly improves the smoothness of the inner cylinder's rotation and axial movement, solving the centering jamming problem caused by insufficient machining accuracy in existing technologies, and achieving efficient and precise centering of the inner cylinder. The symmetrically arranged centering structure further enhances the stability and reliability of centering, making the device suitable for simulation experimental environments and possessing broad application prospects. Attached Figure Description

[0014] To more clearly illustrate the technical solutions of the embodiments of this utility model, the drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this utility model and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained from these drawings without creative effort.

[0015] Figure 1 This is a cross-sectional structural schematic diagram of a simulated nose landing gear centering device according to the present invention;

[0016] Figure 2 This is a utility model Figure 1 Schematic diagram of the structure at point A in the middle;

[0017] Figure 3 This is a schematic diagram of the structure of a simulated nose landing gear centering device according to this utility model;

[0018] Figure 4This is a partial structural diagram of the connecting component of this utility model;

[0019] The markings in the diagram are: 1. Inner cylinder; 2. Outer cylinder; 3. Inner cavity; 4. Cylinder; 5. Centering ring; 6. Centering component; 7. Connecting assembly; 8. Positioning port; 9. Positioning part; 10. Centering groove; 11. Spherical bearing; 12. Connecting lug; 13. First bearing; 14. Bolt with hole; 15. Connector; 16. Second bearing. Detailed Implementation

[0020] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this utility model, not all of them. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model. Therefore, the following detailed description of the embodiments of this utility model provided in the accompanying drawings is not intended to limit the scope of the claimed utility model, but merely represents selected embodiments of this utility model. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.

[0021] Depend on Figures 1 to 4 As shown, this utility model provides a simulated nose landing gear centering device, wherein the simulated nose landing gear includes an inner cylinder 1 and an outer cylinder 2. The upper part of the inner cylinder 1 is housed within the inner cavity 3 of the outer cylinder 2, and a centering device is connected between the inner cylinder 1 and the outer cylinder 2. The upper part of the inner cylinder 1 is housed within the inner cavity 3 of the outer cylinder 2, and the centering device enables lifting and centering functions. The centering device consists of a cylinder 4, a centering ring 5, a centering component 6, and a connecting assembly 7. The cylinder 4 is coaxially mounted on the top of the inner cavity 3 of the outer cylinder 2, with its piston rod vertically downward, and is rotatably connected to the inner cylinder 1 through the connecting assembly 7. The centering ring 5 is fixedly mounted on the top of the inner cylinder 1 and is used to cooperate with the centering component 6 provided on the outer cylinder 2 to complete the centering action of the inner cylinder 1.

[0022] Preferably, the centering ring 5 has a downward-opening positioning port 8, and the distance between the two inner sides of the positioning port 8 gradually decreases from bottom to top, forming a guide slope. The centering component 6 has a positioning part 9, which extends below the positioning port 8 and can contact the slope of the positioning port 8. When the cylinder 4 drives the inner cylinder 1 to move downward, the positioning part 9 contacts the slope of the positioning port 8 and is guided, so that the middle part of the positioning part 9 gradually approaches the middle part of the positioning port 8, thereby driving the inner cylinder 1 to complete the centering action by means of the rotation of the centering ring 5.

[0023] Furthermore, the top of the positioning port 8 is also provided with a centering groove 10, and the top end of the positioning part 9 is designed in an arc shape to fit the centering groove 10. The centering groove 10 and the positioning part 9 are connected by insertion to further enhance the centering effect and stability. In addition, two positioning ports 8 are symmetrically arranged on both sides of the centering ring 5, and two centering parts 6 are correspondingly arranged on the outer cylinder 2, which cooperate with the two positioning ports 8 respectively. The symmetrical double-sided centering structure ensures that the inner cylinder 1 is subjected to uniform force during the centering process, avoiding the displacement or jamming caused by unilateral force.

[0024] Preferably, the connecting assembly 7 includes a spherical plain bearing 11, a connecting lug 12, a first bearing 13, a bolt with holes 14, and a connector 15. The spherical plain bearing 11 is mounted on the bottom end of the piston rod of the cylinder 4 and hinged to the connecting lug 12. The first bearing 13 is provided between the bolt with holes 14 and the connecting lug 12. In this embodiment, the first bearing 13 is a thrust ball bearing. The end of the bolt with holes 14 passes through the top end of the inner cylinder 1 and is coaxially connected to the inner cylinder 1 through the connector 15. The above connection method realizes the rotatable connection between the inner cylinder 1 and the piston rod of the cylinder 4, while ensuring the flexibility of the inner cylinder 1 during axial movement, reducing the coaxiality requirement, and reducing the processing difficulty. The application of the thrust ball bearing significantly reduces the friction of the inner cylinder 1 during rotation, ensuring that the inner cylinder 1 rotates smoothly under the action of the centering ring 5 and the centering member 6, and finally accurately enters the centering position. Compared to the traditional design of bolts and pads as rotating pairs, thrust ball bearings effectively reduce jamming caused by uneven force, and improve the stability and reliability of the centering process.

[0025] Preferably, a second bearing 16 is further provided between the inner side of the outer cylinder 2 and the outer side of the inner cylinder 1. In this embodiment, the second bearing 16 is a sliding bearing. The sliding bearing enhances the stability of the axial movement of the inner cylinder 1 and reduces frictional resistance. With the assistance of the sliding bearing, the inner cylinder 1 can maintain high stability during axial movement, avoiding poor movement or positional deviation caused by excessive friction.

[0026] The working process of this device is as follows: The cylinder 4 is activated, causing its piston rod to extend downwards, driving the inner cylinder 1 to descend axially within the inner cavity 3 of the outer cylinder 2. During the descent, the positioning part 9 of the centering component 6 contacts the inclined surface of the positioning port 8 of the centering ring 5, receiving a guiding effect. This causes the center of the positioning part 9 to gradually approach the center of the positioning port 8, thereby driving the inner cylinder 1 to complete initial centering through the rotation of the centering ring 5. When the inner cylinder 1 continues to descend to a certain position, the arc-shaped end of the positioning part 9 inserts into the centering groove 10. The insertion and engagement between the centering groove 10 and the positioning part 9 further enhances the centering effect and improves stability. Throughout the descent process, the thrust ball bearing ensures low frictional resistance during rotation of the inner cylinder 1, preventing jamming caused by uneven force. The sliding bearing provides additional support and friction reduction between the outer cylinder 2 and the inner cylinder 1, ensuring the smoothness of the inner cylinder 1 during axial movement. Once the inner cylinder 1 is fully in the neutral position, the cylinder 4 stops operating. At this point, the aircraft's front wheel connected to the bottom of the inner cylinder 1 is in a neutral position, which meets the requirements of the simulation experiment.

[0027] This invention simplifies the overall structure of the device by using a cylinder 4 for actuation instead of a hydraulic system, significantly reducing manufacturing and maintenance costs while avoiding the risk of hydraulic oil leakage. The spherical plain bearing 11 and connecting lug 12 reduce the precision requirements of machining. The introduction of thrust ball bearings and sliding bearings significantly improves the smoothness of rotation and axial movement of the inner cylinder 1, solving the centering jamming problem caused by insufficient machining precision in existing technologies, and achieving efficient and precise centering of the inner cylinder 1. The symmetrical centering structure on both sides further enhances the stability and reliability of centering, making the device suitable for simulation experimental environments and possessing broad application prospects.

[0028] In practical applications, this device can be used for simulation experiments of aircraft nose landing gear. For example, during simulated aircraft landing or taxiing, the nose landing gear needs to frequently perform raising, lowering, and centering operations. This device, through optimized structural design and the introduction of key components, can meet the high requirements for centering accuracy and stability in simulation experiments. Furthermore, due to its compact structure and low manufacturing difficulty, it can significantly reduce the manufacturing cost of experimental equipment and improve experimental efficiency.

[0029] In summary, this utility model provides a compact, easy-to-process, low-cost, and stable simulation nose landing gear centering device through structural optimization and the introduction of key components. It effectively solves the problems of high complexity, easy leakage, and high processing accuracy requirements in the prior art, and provides important technical support for the development of aircraft structure simulation technology.

[0030] The above description is merely a preferred embodiment of this utility model and is not intended to limit the utility model. Various modifications and variations can be made to this utility model by those skilled in the art. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of this utility model should be included within the protection scope of this utility model.

Claims

1. A simulation nose landing gear centering device, the simulation nose landing gear comprising an inner cylinder and an outer cylinder, an upper portion of the inner cylinder being accommodated in an inner cavity of the outer cylinder, a centering device being arranged between the inner cylinder and the outer cylinder, characterized in that, The centering device comprises a cylinder, a centering ring, a centering piece and a connecting assembly, the cylinder is coaxially arranged at the top of the inner cavity, and a piston rod is vertically arranged downward; the centering ring is coaxially fixed at the top of the inner cylinder, and the inner cylinder is rotatably connected to the lower part of the piston rod through the connecting assembly; the centering piece is connected to the outer cylinder and is used for cooperating with the centering ring.

2. A simulated nose landing gear centering device as in claim 1, wherein The centering ring is provided with a positioning opening downward, and the distance between the two inner sides of the positioning opening gradually decreases from bottom to top; the centering piece is provided with a positioning part, and the positioning part extends below the positioning opening.

3. An aircraft landing gear centering device according to claim 2, wherein The top end of the positioning opening is provided with a centering groove; the top end of the positioning part is arc-shaped and is matched with the centering groove.

4. An aircraft landing gear centering device according to claim 3, wherein Two positioning openings are symmetrically arranged on the two sides of the centering ring; two centering pieces are symmetrically arranged on the outer cylinder.

5. An aircraft landing gear centering device according to claim 1, wherein The connecting assembly comprises a joint bearing, a connecting lug, a first bearing, a bolt with holes and a connecting head; the joint bearing is arranged at the bottom end of the piston rod and is hingedly connected to the connecting lug; the first bearing is arranged between the bolt with holes and the connecting lug; the end of the bolt with holes penetrates through the top end of the inner cylinder and is coaxially connected to the inner cylinder through the connecting head.

6. An aircraft landing gear centering device according to claim 5, wherein The first bearing is a thrust ball bearing.

7. An aircraft landing gear centering device according to claim 1, wherein A second bearing is further arranged between the inner side of the outer cylinder and the outer side of the inner cylinder, and the second bearing is a sliding bearing.

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