Lengthened guide rail assembly for aviation aircraft wheel

Abstract

The utility model discloses a lengthened guide rail assembly for an aviation airplane wheel, and belongs to the technical field of aviation airplane wheel braking. Comprising a lengthened guide rail connected with an inner cavity of an external aviation aircraft wheel hub, a connecting module connected with the lengthened guide rail and a fastening gear connected with the connecting module, and the fastening gear is connected with an external electric driving device. The lengthened guide rail is composed of a plurality of sub guide rails, the first inclined face protruding blocks and the second inclined face protruding blocks are connected through first screws and second screws which are perpendicular to each other in the inclination direction, and every two adjacent second inclined face protruding blocks are connected through second screws which are perpendicular to each other in the inclination direction. According to the multi-directional screw connecting mode, fixing force is applied to the connecting part from different angles, the connecting stability of the whole lengthened guide rail is greatly enhanced, and the possibility of relative displacement between the sub guide rails in the using process of the aviation aircraft wheel is effectively reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft wheel brakes, in particular to an extended guide rail assembly for aircraft wheels. Background Art

[0002] In the field of aircraft wheel braking technology, the proper operation and safety of aircraft wheels are of paramount importance. With the continuous advancement of aviation technology, the performance requirements for aircraft wheels are also increasing. Traditional aircraft wheel guide rail assemblies are gradually revealing some limitations in their structure and function.

[0003] On the one hand, traditional guide rail assemblies lack connection stability. During aircraft wheel operation, especially under complex operating conditions such as vibration during high-speed flight and impact during takeoff and landing, the internal connection structure of the guide rail assembly is prone to loosening or relative displacement. This not only affects the normal rotation of the aircraft wheel, but may also cause failures in related components such as the brake system, thereby endangering flight safety.

[0004] On the other hand, traditional connection methods cannot effectively meet the requirements for efficient and stable torque transmission when connecting to external electric drive devices. Since aircraft wheels require precise control of rotation speed and direction, if the connection between the guide rail assembly and the electric drive device is not stable or cannot accurately transmit torque, precise control of the aircraft wheel will be difficult, and it will not meet the strict requirements of modern aviation for flight accuracy and safety.

[0005] In addition, traditional guide rail assemblies lack an effective buffering mechanism when dealing with possible minor deformations of the aircraft wheel hub or additional stresses generated under complex working conditions. This makes the entire aircraft wheel system more susceptible to fatigue damage during long-term operation, reducing the service life and reliability of the aircraft wheel.

[0006] Therefore, it is necessary to develop a novel lengthened guide rail assembly for aircraft wheels. Utility Model Content

[0007] In view of the above problems, the utility model discloses an extended guide rail assembly for aircraft wheels.

[0008] The technical solution of the utility model is: an extended guide rail assembly for an aircraft wheel, comprising an extended guide rail connected to an inner cavity of an external aircraft wheel hub, a connecting module connected to the extended guide rail, and a fastening gear connected to the connecting module, wherein the fastening gear is connected to an external electric drive device;

[0009] The extended guide rail is composed of multiple sub-guide rails connected end to end, and the sub-guide rails include two first sub-guide rails located at the end positions and a second sub-guide rail located between the two first sub-guide rails. A first inclined surface protrusion is provided on one side of the first sub-guide rail, and two second inclined surface protrusions are provided on the left and right sides of the second sub-guide rail, one above and one below, and the first inclined surface protrusion is movably connected to the adjacent second inclined surface protrusion.

[0010] Furthermore, the first inclined surface protrusion is provided with a plurality of first screws for connecting the second inclined surface protrusion, and the second inclined surface protrusion is provided with a plurality of second screws for connecting the first inclined surface protrusion, and the inclination direction of the first screws is perpendicular to the inclination direction of the second screws, and two adjacent second inclined surface protrusions are connected by the second screws whose inclination directions are perpendicular to each other.

[0011] Description: The first bevel protrusion and the second bevel protrusion are connected at the joint by the first screw and the second screw in an inclined direction perpendicular to each other. At the same time, the two adjacent second bevel protrusions are connected by the second screw in an inclined direction perpendicular to each other. The fixing force is applied to the connection part from different angles, thereby enhancing the stability of the entire extended guide rail connection and reducing the possibility of relative displacement between the sub-guide rails during use.

[0012] Furthermore, the side wall of the connecting module is connected to one of the first sub-guide rails through mortise and tenon joints, and the connecting module is provided with a snap-in recess for snapping into the fastening gear. The outer wall of the connecting module on the side opposite to the first sub-guide rail is threadedly connected with a T-shaped linkage frame placed at 90°, and the T-shaped linkage frame is connected to the side wall of the fastening gear through a self-locking nut.

[0013] Description: The mortise and tenon connection can ensure the precise fit between the connecting module and the first sub-guide rail, ensuring the structural stability of the entire extended guide rail assembly for the aircraft wheel. The snap-in recess on the connecting module is snapped into the fastening gear to provide a relatively stable connection. During the operation of the aircraft wheel, especially when facing complex working conditions such as vibration and impact, it can effectively prevent the fastening gear from displacing relative to the connecting module. The T-type linkage frame is placed at 90° and is threadedly connected to the connecting module. It is connected to the side wall of the fastening gear through a self-locking nut to effectively transmit force, and due to the presence of the threaded connection and the self-locking nut, the connection tightness between the T-type linkage frame and the fastening gear can be easily adjusted. During the operation of the aircraft wheel, if it is necessary to fine-tune the position of the fastening gear or the tightness of the transmission, it can be achieved by adjusting the self-locking nut, thereby ensuring the accuracy of the entire transmission system.

[0014] Furthermore, elastic buffer pads are respectively provided on both sides of the side walls of the engaging recess and the connection with the fastening gear, and the elastic buffer pads are made of an elastic buffer alloy.

[0015] Description: When the snap-in notch is connected to the fastening gear, an elastic buffer pad made of an elastic buffer alloy is used to ensure effective power transmission and to act as a buffer when there is slight deformation or vibration of the aircraft wheel hub, thereby reducing the impact on the external electric drive device.

[0016] Furthermore, the first sub-guide rail, the second sub-guide rail and the aircraft wheel hub are connected via self-locking nuts.

[0017] Description: It can ensure that the connection between the extended guide rail and the aircraft wheel hub remains stable during the entire operation of the aircraft wheel, avoiding separation or relative displacement of the extended guide rail and the aircraft wheel hub due to loosening of the nut, thereby ensuring the normal operation of the aircraft wheel.

[0018] Beneficial effects of the utility model:

[0019] When the extended guide rail assembly for an aircraft wheel of the present invention is in use, the extended guide rail is composed of a plurality of sub-guide rails. The first inclined surface protrusion and the second inclined surface protrusion are connected by a first screw and a second screw whose inclined directions are perpendicular to each other. Two adjacent second inclined surface protrusions are also connected by a second screw whose inclined directions are perpendicular to each other. This multi-directional screw connection method applies fixing force to the connection parts from different angles, greatly enhancing the stability of the entire extended guide rail connection and effectively reducing the possibility of relative displacement between the sub-guide rails during use of the aircraft wheel. At the same time, compared with existing guide rails, the extended guide rail assembly of the present invention individually adjusts the flatness and straightness of the guide rails, thereby improving installation accuracy, reducing vibration, and improving the stability of linear motion. This is very beneficial for the dynamic response of the aircraft wheel under high-speed flight and complex working conditions.

[0020] The extended guide rail is connected to the fastening gear of the external electric drive device through the connecting module, so that the torque of the electric drive device can be transmitted to the aircraft wheel hub, causing the aircraft wheel to rotate actively; the connecting module is provided with a snap-in recess for snapping with the fastening gear. This snap-in method can provide a relatively stable connection. During the operation of the aircraft wheel, especially when facing complex working conditions such as vibration and impact, it can effectively prevent the fastening gear from being displaced relative to the connecting module. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 This is a schematic diagram of the overall structure of the extended guide rail of the utility model when it is connected to the aircraft wheel hub;

[0022] Figure 2 This is a schematic diagram of the overall structure of the extended guide rail of the present invention when it is not connected to the aircraft wheel hub;

[0023] Figure 3 This utility model Figure 2 A in the enlarged view.

[0024] Among them, 1-extended guide rail, 10-aircraft wheel hub, 12-first sub-guide rail, 120-first inclined surface protrusion, 121-first screw, 13-second sub-guide rail, 130-second inclined surface protrusion, 131-second screw, 2-connecting module, 20-clamping recess, 21-T-type linkage frame, 22-self-locking nut, 23-elastic buffer pad, 3-fastening gear. DETAILED DESCRIPTION

[0025] Example 1: Figure 1 、 2 As shown, an extended guide rail assembly for an aircraft wheel includes an extended guide rail 1 connected to the inner cavity of an external aircraft wheel hub 10, a connecting module 2 connected to the extended guide rail 1, and a fastening gear 3 connected to the connecting module 2. The fastening gear 3 is connected to an external electric drive device;

[0026] The extended guide rail 1 is composed of four sub-guide rails connected end to end. The sub-guide rails include two first sub-guide rails 12 located at the end positions and a second sub-guide rail 13 located between the two first sub-guide rails 12. A first inclined surface protrusion 120 is provided on one side of the first sub-guide rail 12, and two second inclined surface protrusions 130 are provided on the left and right sides of the second sub-guide rail 13, one above and one below. The first inclined surface protrusion 120 is movably connected to the adjacent second inclined surface protrusion 130.

[0027] like Figure 3 As shown, the first bevel protrusion 120 is provided with 5 first screws 121 for connecting the second bevel protrusion 130, and the second bevel protrusion 130 is provided with 5 second screws 131 for connecting the first bevel protrusion 120, and the inclination direction of the first screw 121 and the inclination direction of the second screw 131 are perpendicular to each other, and the two adjacent second bevel protrusions 130 are connected by the second screws 131 with inclination directions perpendicular to each other, and the first bevel protrusion 120 and the second bevel protrusion 130 are connected at the joint by the first screws 121 and the second screws 131 with inclination directions perpendicular to each other. At the same time, the two adjacent second bevel protrusions 130 are connected by the second screws 131 with inclination directions perpendicular to each other, and the fixing force is applied to the connection part from different angles, thereby enhancing the stability of the connection of the entire extended guide rail 1 and reducing the possibility of relative displacement between the sub-guide rails during use. The first screws 121 and the second screws 131 both adopt existing technology.

[0028] The side wall of the connecting module 2 is connected to one of the first sub-guide rails 12 with mortise and tenon joints. The connecting module 2 is provided with a snap-in recess 20 that is snap-in to the fastening gear 3. The outer wall of the connecting module 2 on the side opposite to the first sub-guide rail 12 is threadedly connected with a T-shaped linkage frame 21 placed at 90 degrees. The T-shaped linkage frame 21 is connected to the side wall of the fastening gear 3 by a self-locking nut 22. The mortise and tenon connection can ensure the precise fit between the connecting module 2 and the first sub-guide rail 12, thereby ensuring the structural stability of the entire aircraft wheel extended guide rail assembly. The snap-in recess 20 on the connecting module 2 is snap-in to the fastening gear 3, which can provide a relatively stable connection during the operation of the aircraft wheel. In particular, when facing complex working conditions such as vibration and impact, the fastening gear 3 can be effectively prevented from being displaced relative to the connecting module 2. The T-shaped linkage frame 21 is placed at 90 degrees and is threadedly connected to the connecting module 2. It is connected to the side wall of the fastening gear 3 through the self-locking nut 22, which can effectively transmit force. In addition, due to the presence of the threaded connection and the self-locking nut 22, the connection tightness between the T-shaped linkage frame 21 and the fastening gear 3 can be easily adjusted. During the operation of the aircraft wheel, if it is necessary to fine-tune the position of the fastening gear 3 or the tightness of the transmission, it can be achieved by adjusting the self-locking nut 22, thereby ensuring the accuracy of the entire transmission system.

[0029] Elastic buffer pads 23 are provided on both sides of the side walls of the engaging recess 20 and the connection with the fastening gear 3. The elastic buffer pads 23 are made of an elastic buffer alloy. The elastic buffer alloy material adopts existing technology, for example, nickel-titanium alloy. When the engaging recess 20 is connected to the fastening gear 3, the elastic buffer pads 23 made of the elastic buffer alloy can not only ensure effective power transmission, but also play a buffering role when there is slight deformation or vibration of the aircraft wheel hub 10, thereby reducing the impact on the external electric drive device.

[0030] The first sub-guide rail 12 and the second sub-guide rail 13 are connected to the aircraft wheel hub 10 via self-locking nuts 22, which can ensure that the connection between the extended guide rail 1 and the aircraft wheel hub 10 remains stable during the entire operation of the aircraft wheel, avoiding separation or relative displacement of the extended guide rail 1 and the aircraft wheel hub 10 due to loosening of the nuts, thereby ensuring the normal operation of the aircraft wheel.

[0031] The installation method of the extended guide rail assembly for an aircraft wheel of this embodiment specifically includes the following steps:

[0032] S1. Take one first sub-guide rail 12 and one second sub-guide rail 13 respectively, align the first inclined surface protrusion 120 of the first sub-guide rail 12 with the second inclined surface protrusion 130 of the second sub-guide rail 13, screw the first screw 121 into the connecting portion of the first inclined surface protrusion 120 and the second inclined surface protrusion 130, and then screw the second screw 131 into the corresponding connecting portion to complete the connection between the first sub-guide rail 12 and the second sub-guide rail 13. Next, take another second sub-guide rail 13, align the second inclined surface protrusions 130 of two adjacent second sub-guide rails 13, screw the second screw 131 into the connecting portion of the two second sub-guide rails 13, and repeat this step to complete the connection between each second sub-guide rail 13 and the second sub-guide rail 13 and the first sub-guide rail 12, thereby obtaining the extended guide rail 1;

[0033] S2. Connect the assembled extended guide rail 1 to the aircraft wheel hub 10 through the self-locking nut 22;

[0034] S3. Engage the fastening gear 3 with the engaging notch 20 of the connecting module 2, so that the fastening gear 3 fits tightly against the elastic buffer pad 23 to ensure a secure engagement. Install the T-shaped linkage bracket 21 to the threaded portion of the outer wall of the connecting module 2 opposite the first sub-guide rail 12. Use a tool to tighten the T-shaped linkage bracket 21 to an appropriate degree so that it is positioned at a 90-degree angle. Use the self-locking nut 22 to connect the T-shaped linkage bracket 21 to the side wall of the fastening gear 3.

[0035] S4. Connect the connection module 2 to a first sub-guide rail 12 in the assembled extended guide rail 1 through mortise and tenon joints.

Claims

1. An extended guide rail assembly for an aircraft wheel, characterized in that: It comprises an extended guide rail (1) connected to the inner cavity of an external aircraft wheel hub (10), a connection module (2) connected to the extended guide rail (1), and a fastening gear (3) connected to the connection module (2), wherein the fastening gear (3) is connected to an external electric drive device; The extended guide rail (1) is composed of a plurality of sub-guide rails connected end to end in sequence, wherein the sub-guide rails include two first sub-guide rails (12) located at end positions and a second sub-guide rail (13) located between the two first sub-guide rails (12); a first inclined surface protrusion (120) is provided on one side of the first sub-guide rail (12); two second inclined surface protrusions (130) are provided on the left and right sides of the second sub-guide rail (13), one above the other. The first inclined surface protrusion (120) is movably connected to the adjacent second inclined surface protrusion (130).

2. The extended guide rail assembly for an aircraft wheel according to claim 1, characterized in that: The first inclined surface protrusion (120) is provided with a plurality of first screws (121) for connecting to the second inclined surface protrusion (130), and the second inclined surface protrusion (130) is provided with a plurality of second screws (131) for connecting to the first inclined surface protrusion (120), and the inclination direction of the first screws (121) and the inclination direction of the second screws (131) are perpendicular to each other, and two adjacent second inclined surface protrusions (130) are connected by the second screws (131) whose inclination directions are perpendicular to each other.

3. The extended guide rail assembly for an aircraft wheel according to claim 1, characterized in that: The side wall of the connection module (2) is connected to one of the first sub-guide rails (12) by mortise and tenon joints. The connection module (2) is provided with a clamping notch (20) for clamping with the fastening gear (3). The outer wall of the connection module (2) on the side opposite to the first sub-guide rail (12) is threadedly connected to a T-shaped linkage frame (21) placed at 90 degrees. The T-shaped linkage frame (21) is connected to the side wall of the fastening gear (3) by a self-locking nut (22).

4. The extended guide rail assembly for an aircraft wheel according to claim 3, characterized in that: Elastic buffer pads (23) are respectively provided on the side walls of the clamping recess (20) and on both sides of the connection with the fastening gear (3), and the elastic buffer pads (23) are made of elastic buffer alloy material.

5. The extended guide rail assembly for aircraft wheels according to claim 1, characterized in that: The first sub-guide rail (12) and the second sub-guide rail (13) are connected to the aircraft wheel hub (10) via self-locking nuts (22).

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