Aircraft ground handling connection device

Abstract

An aircraft ground operation connection device, removably mounted to the landing gear of an aircraft, includes: a support shaft inserted into the landing gear; a pair of multi-functional connectors respectively fixed to both ends of the support shaft, wherein each of the pair of multi-functional connectors includes: a base including double lugs facing away from an opening on the support shaft; and a short post inserted through the double lugs; and a load-bearing frame removably mounted to the multi-functional connector on both sides. This aircraft ground operation connection device allows for various ground operations and can be easily installed onto or removed from the landing gear.

Description

Technical Field

[0001] This invention relates to the field of aircraft connection methods, and more specifically, to an aircraft ground operation connection device. Background Technology

[0002] Connection devices used for ground operations such as towing, mooring, and lifting of aircraft are usually located on or near the landing gear axles. For example, the towing connection assembly is usually located near the nose landing gear axle and is designed as a cylindrical joint with a fixed joint at one end of the towing rod; the nose mooring connection assembly is usually located on the nose landing gear axle and is designed as a fixed lug joint; the landing gear lifting joint is located at the bottom of the landing gear axle.

[0003] While existing connection devices can perform towing, mooring, and lifting operations, these devices are fixed to the aircraft, particularly to the landing gear, resulting in an additionally complex landing gear structure. Furthermore, their fixed location prevents them from meeting the demands for flexible towing, mooring, and lifting operations. Specifically, the towing, mooring, or lifting connections are fixed joints that are not used during flight, thus adding extra weight to the aircraft for most of its operational time. Additionally, some joints are located close to the ground and cannot be adjusted, causing inconvenience for ground operations. Moreover, existing mooring connections are limited by space constraints, requiring them to be positioned in a specific direction (e.g., forward mooring joints often have to be positioned forward). Otherwise, the mooring rope may interfere with the aircraft's doors or other structural elements, preventing the use of ground anchors on either side of the airport parking lines or in the rear area for mooring, significantly limiting the flexibility of ground mooring and airport docking adaptability. Furthermore, the connecting device used for lifting the landing gear axle is usually located at the bottom of the landing gear axle, with a very low ground clearance, and is typically situated in the gap between two or more tires. This limits the flexibility in selecting the lifting device and the convenience of actual operation. In some cases, special lifting devices must be used, resulting in limited operating space and poor flexibility. In emergency situations such as a tire blowout and runway derailment, if the tire is on uneven ground such as mud, the lifting point may be too close to the ground to be used for rescue lifting operations.

[0004] Therefore, there is a need to propose an improved aircraft ground operation connection device that can solve the problems and defects existing in the prior art. Summary of the Invention

[0005] The purpose of this invention is to provide a ground operation connection device for an aircraft that integrates functions such as towing, mooring, and lifting, and can be easily installed on or removed from an aircraft.

[0006] According to the present invention, a ground operation connection device for an aircraft is provided, wherein the ground operation connection device is removably mounted to the landing gear of an aircraft, comprising: a support shaft inserted into the landing gear; a pair of multi-functional connectors respectively fixed to both ends of the support shaft, wherein each of the pair of multi-functional connectors comprises: a base including double lugs facing away from the opening of the support shaft; and a short post inserted through the double lugs; and a load-bearing frame removably mounted to the multi-functional connector on both sides thereof.

[0007] The multi-functional connector allows for lateral mooring or lifting, while the load-bearing frame allows for forward or rearward mooring. Therefore, this aircraft ground operation connection allows for a variety of flexible ground connection operations. Furthermore, the support shaft can be inserted into the landing gear to install the aircraft ground operation connection, and can also be removed from the landing gear to remove the aircraft ground operation connection, thus providing convenience in installation and removal.

[0008] According to another aspect of the invention, the support shaft can switch between a contracted state and an expanded state, wherein the diameter of the support shaft in the expanded state is larger than the diameter of the support shaft in the contracted state.

[0009] According to another aspect of the invention, the aircraft ground operation connection device further includes a pair of rotary locking members, each of which is fixed to one end of a support shaft, wherein the rotary locking members lock the support shaft in an extended state.

[0010] According to another aspect of the invention, the support shaft further includes an obstacle avoidance portion, the diameter of which is smaller than the diameter of the rest of the support shaft, and the diameter of the obstacle avoidance portion is fixed.

[0011] According to another aspect of the invention, the rotary locking member has: a body fixed to a support shaft and having a first surface facing away from the support shaft; and an externally threaded shaft protruding from the first surface.

[0012] According to another aspect of the invention, the base of the multi-functional connector has an internal thread portion that matches the external thread shaft.

[0013] According to another aspect of the invention, the rotary locking member also has a plurality of stops arranged circumferentially on a first surface of the rotary locking member; and the base of the multi-functional connector has a mating stop that matches the stops to prevent the multi-functional connector from rotating relative to the rotary locking member.

[0014] According to another aspect of the invention, the stop portion includes a stop block and a stop frame for receiving the stop block, wherein the stop block is toothed at one end toward the external threaded shaft, and wherein the stop block is fixed to the stop frame by means of bolts.

[0015] According to another aspect of the invention, the mating stop of the multifunctional connector is shaped as a serrated shape surrounding the base.

[0016] According to another aspect of the invention, the short post of the multifunctional connector is inserted through the load-bearing frame and the double lugs for fixing, thereby installing the load-bearing frame onto the multifunctional connector.

[0017] The aircraft ground operation connection device of the present invention uses a support shaft with an adjustable diameter that passes through the landing gear of the aircraft, particularly the hollow axle of the landing gear, to secure the device to the landing gear. When the support shaft is in the retracted state, it can easily pass through the landing gear axle and avoid the protruding obstruction structure within the axle; when the support shaft is in the extended state, it fills the space of the landing gear axle and thus firmly abuts against the wall of the landing gear axle, thereby securely positioning the aircraft ground operation connection device at the landing gear. This allows for convenient installation and removal, enabling the elimination of traditional ground operation fixing joint structures on the aircraft, avoiding additional flight weight, and reducing operating costs. Furthermore, the aircraft ground operation connection device integrates multiple functions; specifically, it provides multi-functional joints at both ends of the support shaft to allow for lifting and lateral mooring; and it provides a load-bearing frame removably mounted to the support shaft or multi-functional joints to allow for forward or rearward mooring as needed. Furthermore, during ground operations such as towing, mooring, and lifting, the aircraft's ground operation connection device can adjust the installation angle, spatial position, and size of relevant components to meet the operational requirements of different ground equipment such as towing vehicles, towing rods, airport ground anchors, and jacks, demonstrating a high degree of flexibility and adaptability. Attached Figure Description

[0018] To gain a more complete understanding of this disclosure, reference can be made to the following description of exemplary embodiments taken in conjunction with the accompanying drawings. The drawings are not intended to limit this disclosure to the specific embodiments depicted therein, and are not necessarily to scale. In the drawings:

[0019] Figure 1 This is a perspective view of an aircraft ground operation connection device and landing gear on which it is installed, according to a preferred embodiment of the present invention.

[0020] Figure 2 yes Figure 1 The aircraft ground operation connection device;

[0021] Figure 3This is a perspective view of a ground operation connection device for an aircraft performing lateral tethering operations according to an embodiment of the present invention;

[0022] Figure 4 This is a three-dimensional representation of an aircraft ground operation connection device for performing lifting operations according to an embodiment of the present invention;

[0023] Figure 5a This is a perspective view of the support shaft of the aircraft ground operation connection device according to an embodiment of the present invention, wherein the support shaft is in a retracted state;

[0024] Figure 5b This is a perspective view of the support shaft of the aircraft ground operation connection device according to an embodiment of the present invention, wherein the support shaft is in an extended state;

[0025] Figure 6 yes Figure 5b A magnified detail view of region A;

[0026] Figures 7 to 8 The process of installing the multi-functional connector of the aircraft ground operation connection device according to an embodiment of the present invention onto the rotary locking member is shown; and

[0027] Figure 9 A schematic perspective view shows a rotary locking member with a multi-functional connector already installed, ready to be installed onto a support shaft. The structure of the rotating part of the support shaft and the bolts in the rotary locking member are shown in perspective to clarify the matching relationship between the two.

[0028] List of reference numerals

[0029] 100 Aircraft Ground Operation Connection Device

[0030] 1 Support shaft

[0031] 11 Obstacle Avoidance Department

[0032] 12 Inner Shaft

[0033] 13. Extension Section

[0034] 131 Support section

[0035] 132 movable parts

[0036] 133 Stop plate

[0037] 134 extension rod

[0038] 14 Rotating components

[0039] 141 Through slot

[0040] 2 Multi-functional connector

[0041] 21 Base

[0042] 212 Pairing stop

[0043] 22 Short Columns

[0044] 23 Bilateral auricular plates

[0045] 3. Load-bearing frame

[0046] 31 Axial rod

[0047] 32 Radial rod

[0048] 4 Rotary locking element

[0049] 41 bolts

[0050] 42 Main Body

[0051] 43 First Surface

[0052] 44 External threaded shaft

[0053] 45 Stop section

[0054] 451 Stop block

[0055] 452 Stop Frame

[0056] 200 landing gear

[0057] 201 Axle

[0058] 5. Tethering rope

[0059] 6 Ground mooring parts

[0060] 7 jacks

[0061] X-axis Detailed Implementation

[0062] The following description of specific embodiments of the invention refers to the accompanying drawings, which illustrate particular embodiments in which the invention can be practiced. The embodiments are intended to describe aspects of the invention in sufficient detail to enable those skilled in the art to practice it. Other embodiments may be utilized and changes may be made without departing from the scope of the invention. Therefore, the following description of specific embodiments should not be considered limiting. The scope of the invention is defined only by the appended claims and the full scope of their equivalents. The same reference numerals are used throughout the drawings and specific embodiments to refer to the same or similar parts.

[0063] In this text, the directional terms "axial" refer to the direction extending parallel to the central axis X, "radial" refer to the direction extending perpendicular to the central axis X, and "circumferential" refer to the direction around the central axis X. The directional terms "inner" and "outer" are defined relative to the central axis X. For example, if component A is more inner than component B, then component A is closer to the central axis X in the radial direction than component B.

[0064] Figure 1 A perspective view is shown of an aircraft ground operation connection device installed onto the landing gear of an aircraft according to a preferred embodiment of the present invention. Figure 2 The aircraft's ground operation connection device itself is shown.

[0065] As shown in the figure, the aircraft ground operation connection device 100 generally includes a support shaft 1, multi-functional connectors 2 installed at both ends of the support shaft 1, and a load-bearing frame 3 installed to the multi-functional connectors 2.

[0066] A support shaft 1 extends along its central axis X and is inserted into the landing gear 200, specifically through the wheel axle 201 of the landing gear 200. The diameter of the support shaft 1 is variable, allowing it to switch between a retracted state with a smaller diameter and an extended state with a larger diameter. The wheel axle 201 of the landing gear 200 has a hollow cavity; therefore, when in the retracted state, the diameter of the support shaft 1 is smaller than the inner diameter of the wheel axle 201, allowing the support shaft 1 to be easily inserted through the wheel axle 201 of the landing gear 200. When in the extended state, the diameter of the support shaft 1 expands until it is equal to the inner diameter of the wheel axle 201, allowing the support shaft 1 to fit tightly against the inner wall of the wheel axle 201 of the landing gear 200, thereby firmly fixing the support shaft 1 within the wheel axle 201 of the landing gear 200.

[0067] Figure 5a and Figure 5bThe support shaft 1 in its retracted state and its extended state are shown respectively. As shown, the support shaft 1 includes an inner shaft 12 at its radial center and two extensions 13 spaced apart around the inner shaft 12. Each extension 13 includes a support portion 131 fixed around the inner shaft 12, which includes a plurality of radially extending and circumferentially spaced segments (three in this embodiment). Further, the extension 13 also includes a plurality of movable members 132 circumferentially arranged on the support portion 131, the number of movable members 132 corresponding to the number of segments of the support portion 131, which is also three in this embodiment. Each movable member 132 is a radially extending arcuate sheet with a constant curvature that can fit tightly against the support portion 131, and includes a stop piece 133 and an extension rod 134 at opposite ends of the movable member 132. A stop plate 133 extends from the movable member 132 toward the inner shaft 12, while an extension rod 134 extends from the opposite end of the movable member 132 to the stop plate 133 and is integral with or fixed to the stop plate 133. Preferably, the extension rod 134 passes through corresponding axial gaps between multiple segments of the support portion 131. Thus, radial movement of the extension rod 134 within these axial gaps causes radial movement of the movable member 132 relative to the support portion 131. Specifically, when the extension rod 134 moves radially toward the inner shaft 12, the movable member 132 is driven by the extension rod 134 to move toward the inner shaft 12; when the extension rod 134 moves radially away from the inner shaft 12, the movable member 132 is driven by the extension rod 134 to move away from the inner shaft 12. To achieve synchronous movement of the multiple movable members 132, rotating members 14 are provided at both ends of the support shaft 1. The rotating members 14 are rotatably mounted to the support shaft 1, particularly to the inner shaft 12 of the support shaft 1. A number of through slots 141, corresponding to the number of extension rods 134, are provided in the rotating component 14. Each extension rod 134 passes through a corresponding through slot 141, thus limiting the travel of multiple extension rods 134. When the rotating component 14 is turned, the multiple through slots 141 simultaneously force multiple extension rods 134 to move simultaneously, causing multiple movable components 132 to move simultaneously closer to or away from the inner shaft 12, thereby changing the diameter of the support shaft 1. Figure 5a As shown, when in the retracted state, multiple movable parts 132 are tightly attached to the support portion 131 of the support shaft 1, making the overall diameter of the support shaft 1 smaller, allowing it to easily pass through a small-diameter space. Figure 5b As shown, when in the extended state, multiple movable members 132 are spaced a certain distance from the support portion 131 of the support shaft 1, thereby increasing the overall diameter of the support shaft 1, and the movable members 132 can closely abut against the inner wall of the wheel axle 201 of the landing gear 200 to fix the support shaft 1 in place.

[0068] Additionally, such as Figure 6As shown in detail, the support shaft 1 also includes a barrier portion 11. Specifically, the portion of the inner shaft 12 not covered by any extension portion 13 is designated as the barrier portion 11. Therefore, the diameter of the barrier portion 11 is smaller than the diameter of any other portion of the support shaft 1, and its diameter is fixed. An inwardly protruding structure is provided within the axle 201 of the landing gear 200, particularly at the axial midpoint of the axle 201. This protruding structure would prevent the movable member 132 of the support shaft 1 from abutting against the inner wall of the axle 201. Therefore, a barrier portion 11 with a smaller diameter is provided so that the protruding structure of the axle 201 of the landing gear 200 can extend towards the inner shaft 12 of the support shaft 1 without being blocked by the movable member 132. This further improves the stability of the support shaft 1 fixed to the axle 201 of the landing gear 200.

[0069] A rotary locking element 4 is provided to lock the support shaft 1 in its extended state into place, preventing the support shaft 1 from moving back to its retracted state. Specifically, Figure 9 A rotary locking member 4 is shown, prepared for engagement with a support shaft 1 in its extended state. The rotary locking member 4 has a body 42 and multiple holes (not shown) provided in the body 42 for receiving multiple extension rods 134 of the support shaft 1. The multiple extension rods 134 are inserted into the holes correspondingly, and the rotary locking member 4 is secured to the support shaft 1 using fasteners such as bolts 41, specifically to the rotating member 14 of the support shaft 1. Thus, the extension rods 134 are secured in place by the holes of the rotary locking member 4, thereby locking the support shaft 1 in its extended state.

[0070] Corresponding to the rotating parts 14 located at both ends of the support shaft 1, the rotating locking parts 4 are also located at both ends of the support shaft 1.

[0071] like Figure 1 and Figure 2 As shown, the aircraft ground operation connection device 100 also includes a pair of multi-functional connectors 2 disposed at both ends of the support shaft 1. Figures 7 to 9 The construction of the multi-functional connector 2 is shown in detail. The multi-functional connector 2 includes a base 21 with two lugs 23 at one end facing away from the support shaft 1, wherein the lugs 23 face away from the opening of the support shaft 1. As shown, the multi-functional connector 2 also includes a short post 22 inserted through the lugs 23, which can be secured to the lugs 23 using a combination of nuts and bolts.

[0072] The multi-functional connector 2 is preferably secured to the support shaft 1 by being fixed to the rotary locking member 4. Figure 7 and Figure 8The fixing structure and process involved in fixing the multi-functional connector 2 to the rotary locking member 4 are shown. Specifically, the rotary locking member 4 has an externally threaded shaft 44 protruding axially from the center of the first surface 43 on its body 42 opposite to the support shaft 1, and a plurality of circumferentially spaced stop portions 45. Each stop portion 45 includes a stop block 451 and a stop frame 452, wherein the stop block 451 can move radially in the stop frame 452 and is fixed in the stop frame 452 by a fastener such as a bolt 41 after reaching a predetermined position; and wherein the end of each stop block 451 facing the externally threaded shaft 44 is shaped as toothed or serrated.

[0073] Correspondingly, the base 21 of the multi-functional connector 2 is provided with an internal thread portion (not shown in the figure) at one end facing the support shaft 1, which matches the external thread shaft 44. The internal thread portion is recessed into the base 21 to receive the external thread shaft 44 of the rotary locking member 4. Furthermore, the base 21 of the multi-functional connector 2 is also provided with a mating stop portion 212 at one end facing the support shaft 1. The mating stop portion 212 is shaped as a sawtooth around the base 21 so that it can engage with the stop block 451 of the rotary locking member 4.

[0074] like Figure 8 As shown, after the multi-functional connector 2 is screwed onto the external threaded shaft 44 of the rotary locking member 4 to the desired position, each stop block 451 is passed through the corresponding stop frame 452 and engaged with the mating stop part 212 of the multi-functional connector 2, thus fixing the stop block 451 in place within the stop frame 452. This prevents the multi-functional connector 2 from continuing to rotate relative to the rotary locking member 4, thereby fixing the multi-functional connector 2 in place.

[0075] The design of the stop 45 of the rotary locking member 4 and the mating stop 212 of the multi-functional connector 2 allows the multi-functional connector 2 to be rotated to any position as needed, which greatly improves the operational flexibility of the multi-functional connector 2.

[0076] The multi-functional connector 2 enables a variety of operations such as lateral mooring and jacking. Figure 3 and Figure 4 The landing gear 200 for lateral hold using the aircraft ground operation connection 100 and the landing gear 200 for lifting using the aircraft ground operation connection 100 are shown respectively. Specifically, when lateral hold is required, the tether rope is passed through the short post 22, and then the tether rope 5 is connected to the ground hold 6 and tensioned. When lifting is required, the short post 22 of the multi-function connector 2 is adjusted to be parallel to the ground or any other suitable position, and then a lifting tool such as a jack 7 is engaged with the multi-function connector 2 to lift the landing gear 200 and thereby lift the aircraft.

[0077] Furthermore, the aircraft ground operation connection device 100 also includes a load-bearing frame 3. The load-bearing frame 3 is preferably concave in shape and includes an axial rod 31 and radial rods 32 at both ends of the axial rod 31. The load-bearing frame 3 can be mounted to the support shaft 1 on both sides by attaching it to the multi-functional connector 2. Specifically, each radial rod 32 of the load-bearing frame 3 preferably has an opening (not shown in the figures) at its end away from the axial rod 31. The axial rod 31 can extend into the double lugs 23 of the multi-functional connector 2, allowing the short posts 22 of the paired multi-functional connector 2 to pass through the openings of the corresponding radial rods 32 of the load-bearing frame 3 and subsequently through the double lugs 23 for fixation, thereby mounting the load-bearing frame 3 to the multi-functional connector 2.

[0078] like Figure 1 As shown, the load-bearing frame 3 can be installed such that its axial rod 31 is located on the front side of the landing gear 200, allowing the tether rope to be connected to the axial rod 31 and for forward tethering; of course, the load-bearing frame 3 can also be installed in the opposite direction such that its axial rod 31 is located on the rear side of the landing gear 200, thereby achieving rearward tethering.

[0079] The steps for installing the aircraft ground operation connection device 100 to the landing gear 200 are as follows:

[0080] - Insert the retracted support shaft 1 into the wheel axle 201 that passes through the landing gear 200;

[0081] - Twist the rotating parts 14 at both ends of the support shaft 1 to convert the support shaft 1 into an extended state, increasing its diameter until the movable part 132 of the support shaft 1 is tightly against the inner wall of the wheel axle 201.

[0082] - Secure the pair of rotary locking members 4 to the pair of rotary members 14 respectively to fix the support shaft 1 in the extended state;

[0083] - Install the paired multi-functional connectors 2 onto the rotary locking member 4 respectively. Rotate the multi-functional connectors 2 to the required orientation and position as needed, and then use the stop part 45 of the rotary locking member 4 to fix the multi-functional connectors 2 in place; and

[0084] - Depending on whether forward or backward mooring is required, install the load-bearing frame 3 onto the multi-functional connector 2.

[0085] The steps for removing the aircraft ground operation connection device 100 from the landing gear 200 are the reverse of the steps for installing it onto the landing gear 200, and will not be described again here for the sake of simplicity.

[0086] The aircraft ground operation connection device of the present invention uses a load-bearing frame to allow for forward or rearward mooring, and a multi-functional joint to allow for lateral mooring or lifting. Therefore, the aircraft ground operation connection device of the present invention allows for a variety of operations according to actual needs, solving the problem of insufficient operational flexibility caused by the directional fixation of existing connection devices. Furthermore, the aircraft ground operation connection device uses a variable-diameter support shaft to removably fix the device to the landing gear axle. The aircraft ground operation connection device can be removed when ground operation is not required; when ground operation is required, the device can be easily installed, solving the problem of increased aircraft weight caused by fixing existing connection devices to the aircraft.

[0087] As used herein, the terms “comprising,” “including,” “having,” or any other variation thereof are intended to cover non-exclusive inclusion. For example, a method, article, or apparatus that includes a list of elements is not necessarily limited to those elements and may also include other elements not expressly listed or inherent to the method, article, or apparatus.

[0088] This invention is not limited to the above embodiments, which are merely illustrative and not restrictive. Those skilled in the art, guided by the teachings of this invention, can make any possible variations and modifications without departing from the spirit and scope of the claims. Therefore, any modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of this invention, without departing from the scope of the invention, fall within the protection scope defined by the claims.

Claims

1. A ground operation connection device for an aircraft, wherein, The aircraft ground operation connection device is removably mounted to the aircraft's landing gear, including: A support shaft, which is inserted into the wheel axle of the landing gear; A pair of multi-functional connectors, each fixed to one end of the support shaft, wherein each of the pair of multi-functional connectors includes: A base, the base including two lugs facing away from the opening of the support shaft; and A short post, which is inserted through the double lugs; A load-bearing frame, which is removably mounted to the pair of multi-functional joints on both sides.

2. The aircraft ground operation connection device according to claim 1, characterized in that, The support shaft can switch between a contracted state and an expanded state, wherein the diameter of the support shaft in the expanded state is larger than the diameter of the support shaft in the contracted state.

3. The aircraft ground operation connection device according to claim 2, characterized in that, It also includes a pair of rotary locking elements, each of which is fixed to one end of the support shaft, wherein the rotary locking elements lock the support shaft in the extended state.

4. The aircraft ground operation connection device according to claim 2, characterized in that, The support shaft also includes an obstacle avoidance section, the diameter of which is smaller than the diameter of the rest of the support shaft, and the diameter of the obstacle avoidance section is fixed.

5. The aircraft ground operation connection device according to claim 3, characterized in that, The rotary locking member has: A main body, the main body being fixed to the support shaft, and having a first surface facing away from the support shaft; An externally threaded shaft that protrudes from the first surface.

6. The aircraft ground operation connection device according to claim 5, characterized in that, The base of the multi-functional connector has an internal thread portion that matches the external thread shaft.

7. The aircraft ground operation connection device according to claim 5, characterized in that, The rotary locking member also has a plurality of stop portions, which are circumferentially arranged on the first surface of the rotary locking member; and The base of the multi-functional connector has a mating stop that matches the stop to prevent the multi-functional connector from rotating relative to the rotary locking member.

8. The aircraft ground operation connection device according to claim 7, characterized in that, The stop portion includes a stop block and a stop frame that accommodates the stop block. The stop block has a toothed shape at one end facing the external threaded shaft. Furthermore, the stop block is fixed to the stop frame by means of bolts.

9. The aircraft ground operation connection device according to claim 8, characterized in that, The mating stop of the multi-functional connector is shaped into a sawtooth pattern surrounding the base.

10. The aircraft ground operation connection device according to claim 1, characterized in that, The short post of the multi-functional connector is inserted through the load-bearing frame and the double lugs for fixation, thereby installing the load-bearing frame onto the multi-functional connector.

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