Fixing device for airplane front wheel turning bypass pin

Abstract

The utility model relates to the technical field of limiting tools, and discloses a fixing device for an airplane front wheel turning bypass pin, which comprises a limiting structure, the limiting structure comprises a cross beam and a support beam, one end of the support beam far away from a mop structure is fixedly connected with the cross beam, and the cross beam is horizontally arranged to abut against and limit a handle in the mop structure; a first through hole is formed in the bottom of the supporting beam, the first through hole is used for being arranged corresponding to a first mounting hole of a mop structure, and positioning pieces are inserted into the first through hole and the first mounting hole; a second through hole is formed in the side, away from the supporting beam, of the cross beam, the second through hole is used for being arranged corresponding to a second mounting hole in the mop structure, and a bypass pin is inserted into the second through hole and the second mounting hole; the device can prompt a worker to insert the bypass pin, so that turning limitation of a front wheel is effectively relieved, the front wheel and a turning system of an airplane are prevented from being damaged during traction operation, and the accident rate of traction operation is reduced.

Description

Technical Field

[0001] This utility model relates to the field of limiting tooling, and in particular to a fixing device for a bypass pin for turning aircraft nose wheels. Background Technology

[0002] Currently, the nose wheel steering system of commercial passenger aircraft is typically controlled by a hydraulic system. During towing, the aircraft engines are started in advance, pressurizing the nose wheel hydraulic system and limiting its neutral position. The bypass pin is used to send an electrical signal to the core control computer of the nose wheel steering system to disengage it. During towing, the tow truck causes the nose wheels to deflect. If the bypass pin is not properly inserted, the towing and the hydraulic limit of the nose wheels will conflict, leading to safety accidents and varying degrees of damage to the aircraft or equipment components, or even aborting takeoff.

[0003] In addition, the towing vehicle's tow bar is designed with a handle and a locking tongue assembly. The end of the handle engages with the locking tongue to lock the tow bar connecting shaft of the aircraft's nose wheel. The locking tongue is fixed, while the handle is movable and can rotate around the shaft. Locking is secured by the handle connected to it. When the handle is raised, the tow bar is in the unlocked position; when the handle is lowered, it is in the locked position. However, in actual operation, workers often overlook the bypass pin. After connecting the tow vehicle to the aircraft, they tow the aircraft without inserting the bypass pin to release the nose wheel lock, which can easily cause damage to the aircraft's nose wheel and turning system, resulting in a high accident rate during towing operations. Utility Model Content

[0004] The technical problem to be solved by this utility model is: how to improve the safety of aircraft towing and reduce the risk of accidents during aircraft towing. In order to solve the above technical problem, this utility model provides a fixing device for the turning bypass pin of the aircraft nose wheel, including a limiting structure. The limiting structure includes a crossbeam and a support beam. The end of the support beam away from the mop structure is fixedly connected to the crossbeam. The crossbeam is horizontally arranged to abut against the handle in the limiting mop structure.

[0005] The bottom of the support beam is provided with a first through hole, which is arranged to correspond to the first mounting hole of the mop structure. Positioning components are inserted into the first through hole and the first mounting hole.

[0006] The crossbeam is provided with a second through hole on the side away from the support beam. The second through hole is arranged to correspond to the second mounting hole in the mop structure. The second through hole and the second mounting hole are used to insert a bypass pin.

[0007] Preferably, the limiting structure is in a "U" - shaped structure. The limiting structure further includes a movable beam. The movable beam is arranged at one end of the cross - beam away from the support beam. A second through - hole is provided at one end of the movable beam away from the cross - beam.

[0008] Preferably, a first support foot is provided at one end of the support beam away from the cross - beam, and a second support foot is provided at one end of the movable beam away from the cross - beam.

[0009] Preferably, both the first support foot and the second support foot are plate - shaped parts. The plate surfaces of the first support foot and the second support foot are both in contact with the main body of the mop structure. A first through - hole is provided on the first support foot, and a second through - hole is provided on the second support foot.

[0010] Preferably, the limiting structure is in a "7" - shaped structure. The mop structure includes a fixed beam. The fixed beam is arranged on one side of the cross - beam away from the support beam. A second mounting hole is provided at one end of the fixed beam close to the cross - beam.

[0011] Preferably, a third support foot is provided at one end of the support beam away from the cross - beam, a fourth support foot is provided at one end of the fixed beam close to the cross - beam, and a fifth support foot is provided at one end of the fixed beam away from the cross - beam. The third support foot and the fifth support foot are symmetrically arranged about the center of the cross - beam, and the fourth support foot and the fifth support foot are symmetrically arranged about the center of the fixed beam.

[0012] Preferably, the third support foot, the fourth support foot, and the fifth support foot are all plate - shaped parts. The plate surfaces of the third support foot and the fifth support foot are both in contact with the main body of the mop structure, and the fourth support foot is in contact with the cross - beam;

[0013] The third support foot is provided with the first through - hole, the fourth support foot is provided with the second mounting hole, and the fifth support foot is fixedly connected to the main body of the mop structure.

[0014] Preferably, the mop structure includes a base main body, a lock, and the handle. A lock is provided on one side of the base main body away from the limiting structure. A lock tongue is movably arranged in the lock. The lock tongue is movably connected to the handle. A lock groove is also provided on the base main body corresponding to the lock tongue.

[0015] Preferably, the handle includes an obliquely arranged rod and a horizontal rod fixedly connected. The obliquely arranged rod is movably connected to the lock tongue, and the axis of the horizontal rod is perpendicularly intersected with the axis of the cross - beam.

[0016] In the embodiment of the present utility model, a fixing device for an aircraft nose - wheel steering bypass pin has the following beneficial effects compared with the prior art:

[0017] In this utility model, the limiting structure includes a crossbeam and a support beam. The first through hole on the support beam cooperates with the first mounting hole on the mop structure. The positioning member is installed through the first through hole and the first mounting hole. The positioning member restricts the support beam to form a rotation center, so that the limiting structure can rotate relative to the mop structure with the positioning member as the center, thereby switching between the blocking state and the unlocking state.

[0018] Furthermore, the second through hole at the other end of the crossbeam corresponds to the second mounting hole of the mop structure. During towing operations, the bypass pin is inserted into the second through hole and the second mounting hole to limit the crossbeam and prevent it from rotating. At this time, the mop handle is limited below the crossbeam and cannot be lifted. When towing is required, the bypass pin needs to be pulled out. This action of pulling out the bypass pin prompts the operator to install it on the front wheel hydraulic system to release the front wheel turning restriction and prevent accidents. After the bypass pin is pulled out, the limiting structure can rotate around the positioning part, so that the crossbeam no longer restricts the movement of the handle. The handle can be lifted to drive the locking tongue to close, achieving an effective connection between the mop structure and the aircraft's front wheel. Using this fixing fixture, the operator can be prompted to insert the bypass pin to ensure effective release of the front wheel turning restriction, avoid damage to the aircraft's front wheel and turning system during towing operations, and reduce the accident rate of towing operations. Attached Figure Description

[0019] Figure 1 This is a perspective view of the second embodiment of the present invention;

[0020] Figure 2 This is a perspective view of the first embodiment of this utility model.

[0021] In the diagram: 1. Crossbeam; 11. Second through hole; 2. Support beam; 21a. First leg; 21b. Third leg; 3. Positioning component; 4. Movable beam; 41. Second leg;

[0022] 5. Mop structure; 51. Base body; 511. Locking groove; 52. Lock; 521. Locking tongue; 53. Handle; 54. Fixing beam; 541. Fourth leg; 542. Fifth leg;

[0023] 6. Bypass sales. Detailed Implementation

[0024] The following embodiments are used to illustrate the present invention, but are not intended to limit the scope of the present invention.

[0025] In the description of this utility model, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," and "counterclockwise" used to indicate the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this utility model and simplifying the description, and are not intended to indicate or imply that the device or component referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.

[0026] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this utility model, "a plurality of" means two or more, unless otherwise explicitly specified.

[0027] In this utility model, unless otherwise explicitly specified and limited, the terms "installation," "connection," "joining," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. For those skilled in the art, the specific meaning of the above terms in this utility model can be understood according to the specific circumstances.

[0028] like Figure 1 and Figure 2 As shown, a preferred embodiment of the present invention provides a fixing device for a turning bypass pin of an aircraft front wheel, which includes a limiting structure. The limiting structure includes a crossbeam 1 and a support beam 2. The end of the support beam 2 away from the mop structure 5 is fixedly connected to the crossbeam 1. The crossbeam 1 is horizontally arranged to abut against the handle 53 in the limiting mop structure 5.

[0029] The bottom of the support beam 2 is provided with a first through hole, which is arranged to correspond with the first mounting hole of the mop structure 5. A positioning element 3 is inserted into the first through hole and the first mounting hole.

[0030] A second through hole 11 is provided on the side of the crossbeam 1 away from the support beam 2. The second through hole 11 is arranged to correspond to the second mounting hole in the mop structure 5. The second through hole 11 and the second mounting hole are used to insert the side pin 6.

[0031] Specifically, in this embodiment, the limiting structure adopts the structure of the cross beam 1 and the support beam 2. Through the support beam 2, the cross beam 1 is suspended above the mop structure 5, and the handle 53 is located below the cross beam 1. The cross bar of the cross beam 1 limits the movement range of the handle 53. The first through hole provided on the support beam 2 corresponds to the first mounting hole on the mop structure 5, and the positioning member 3 is inserted. Through the positioning member 3, the rotation center of the limiting structure is formed, enabling the cross beam 1 to rotate around the axis of the positioning member 3, thereby adjusting the limiting state of the cross beam 1 on the handle 53, that is, switching between the blocking state and the unlocking state.

[0032] Moreover, a second through hole 11 is provided at the other end of the cross beam 1. The second through hole 11 corresponds to the second mounting hole on the mop structure 5. When traction work is not required, a by-pass pin 6 can be inserted into the second through hole 11 and the second mounting hole, thereby restricting the rotation of the cross beam 1, and further restricting the rotation range of the handle 53 below the cross beam 1, and the handle 53 cannot be lifted. When traction work is required, the staff needs to first pull out the by-pass pin 6 from the second through hole 11. Just the action of pulling out the by-pass pin 6 can remind the staff to timely install the by-pass pin 6 on the hydraulic system of the aircraft front wheel, thereby解除 the restriction on the aircraft front wheel turning. At the same time, since the by-pass pin 6 in the second through hole 11 has been pulled out, the cross beam 1 can rotate around the positioning member 3 to move away from the handle 53, and the cross beam 1 no longer restricts the rotation range of the handle 53, and the handle 53 can be lifted and drive the locking tongue 521 to close, realizing the effective connection between the mop structure 5 and the aircraft front wheel. Using this fixing tooling can prompt the staff to insert the by-pass pin 6, ensure the effective解除 of the turning restriction of the front wheel, avoid damage to the aircraft front wheel and the turning system during traction operation, and reduce the accident rate of the traction operation.

[0033] In addition, in this embodiment, the positioning member 3 is a positioning bolt. The positioning member 3 has a clearance fit with the first through hole and a threaded fit with the first mounting hole on the mop structure 5. In some other embodiments, the positioning member 3 can adopt a detachable pin structure or a bolt and nut structure.

[0034] See Figure 2 , in the first embodiment, the limiting structure is in a "U" - shaped structure. The limiting structure further includes a movable beam 4. The movable beam 4 is arranged at one end of the cross beam 1 away from the support beam 2, and a second through hole 11 is provided at the end of the movable beam 4 away from the cross beam 1.

[0035] Furthermore, a first support leg 21a is provided at the end of the support beam 2 away from the cross beam 1, and a second support leg 41 is provided at the end of the movable beam 4 away from the cross beam 1.

[0036] It should be noted that there is an unclear expression "解除 the restriction on the aircraft front wheel turning" in the translation of item . It might be a specific term in the original text that needs to be further clarified according to the actual situation.Furthermore, both the first leg 21a and the second leg 41 are plate-shaped parts, and the plate surfaces of the first leg 21a and the second leg 41 are attached to the main body of the mop structure 5. The first leg 21a is provided with a first through hole, and the second leg 41 is provided with a second through hole 11.

[0037] Specifically, in this embodiment, the support beam 2 and the movable beam 4 support the two ends of the crossbeam 1, so that the crossbeam 1 is suspended above the handle 53. One end of the crossbeam 1 is connected to the support beam 2 and the mop structure 5, and the other end is movably connected to the mop structure 5 through the movable beam 4. When traction is not required, the two ends of the crossbeam 1 are fixed by the positioning part 3 and the bypass pin 6, respectively. When traction is required, the bypass pin 6 can be pulled out from the second through hole 11, and then the crossbeam 1 can rotate around the positioning part 3. The handle 53 can then rotate freely to drive the locking tongue 521 to lock and unlock. The first foot 21a and the second foot 41 increase the contact area between the support beam 2 and the movable beam 4 and the mop structure 5, making the position of the support beam 2 more stable. In particular, when the positioning part 3 and the bypass pin 6 are inserted and fixed to the support beam 2 and the movable beam 4, the force-bearing area is larger, the strength is better, and the force is more stable. The position of the crossbeam 1 is less likely to shake, and it is less likely to break at the connection due to external factors.

[0038] See Figure 1 In the second embodiment, the limiting structure is in the shape of a "7". The mop structure 5 includes a fixed beam 54, which is located on the side of the crossbeam 1 away from the support beam 2. The fixed beam 54 has a second mounting hole at the end near the crossbeam 1.

[0039] Furthermore, the supporting beam 2 is provided with a third leg 21b at the end away from the crossbeam 1, the fixed beam 54 is provided with a fourth leg 541 at the end near the crossbeam 1, and the fixed beam 54 is provided with a fifth leg 542 at the end away from the crossbeam 1. The third leg 21b and the fifth leg 542 are symmetrically arranged about the center of the crossbeam 1, and the fourth leg 541 and the fifth leg 542 are symmetrically arranged about the center of the fixed beam 54.

[0040] Furthermore, the third leg 21b, the fourth leg 541 and the fifth leg 542 are all plate-shaped parts, and the plate surfaces of the third leg 21b and the fifth leg 542 are attached to the main body of the mop structure 5, while the fourth leg 541 is attached to the crossbeam 1.

[0041] The third leg 21b has a first through hole, the fourth leg 541 has a second mounting hole, and the fifth leg 542 is fixedly connected to the main body of the mop structure 5.

[0042] Specifically, in this embodiment, compared to the previous embodiment, the movable beam 4, which is fixedly connected to the crossbeam 1, is replaced with a fixed beam 54, which is fixedly connected to the mop structure 5. Then, a fourth leg 541 is provided on the fixed beam 54 to support the crossbeam 1, making the structure of the crossbeam 1 more streamlined and easier to rotate. The fourth leg 541 can also better support the crossbeam 1 and the bypass pin 6, making the structure more stable and reliable. In addition, it can also allow the bypass pin 6 to be suspended and inserted above the main body of the mop structure 5, avoiding the damage to the strength and aesthetics of the main body of the mop structure 5 caused by opening an excessively large second mounting hole on the main body of the mop structure 5.

[0043] In some embodiments, the mop structure 5 includes a base body 51, a lock 52, and a handle 53. The base body 51 is provided with a lock 52 on the side away from the limiting structure. A locking tongue 521 is movably provided in the lock 52. The locking tongue 521 is movably connected to the handle 53. The base body 51 is also provided with a locking groove 511 corresponding to the locking tongue 521.

[0044] Furthermore, the handle 53 includes a fixedly connected diagonal bar and a crossbar, the diagonal bar being movably connected to the locking tongue 521, and the axis of the crossbar intersecting perpendicularly with the axis of the crossbeam 1.

[0045] Specifically, the aircraft's front wheel structure is placed into the locking groove 511, and then the handle 53 is lifted to push the locking tongue 521 toward the locking groove 511 and lock it, thus stably connecting the mop structure 5 to the aircraft. The crossbar is designed to be better supported and limited by the crossbeam 1, and the force distribution is more reasonable and aesthetically pleasing.

[0046] In summary, this utility model embodiment provides a fixing device for a bypass pin 6 for aircraft nose wheel turning. The limiting structure includes a crossbeam 1 and a support beam 2. A first through hole on the support beam 2 engages with a first mounting hole on the tow handle structure 5. A positioning member 3 is installed through both the first through hole and the first mounting hole. The positioning member 3 restricts the support beam 2, forming a rotation center, allowing the limiting structure to rotate relative to the tow handle structure 5 around the positioning member 3, thereby switching between a stopped state and an unlocked state. During towing operations, the bypass pin 6 is inserted into the second through hole 11 and the second mounting hole to limit the crossbeam 1, preventing it from rotating. At this time, the tow handle 53 is limited below the crossbeam 1 and cannot be lifted. When towing is required, the bypass pin 6 needs to be pulled out. This action prompts the operator to install the bypass pin 6 at the nose wheel hydraulic system to release the nose wheel turning restriction, preventing damage to the aircraft nose wheel and turning system during towing operations and reducing the accident rate during towing operations.

[0047] The above are merely preferred embodiments of this utility model. It should be noted that, for those skilled in the art, several improvements and substitutions can be made without departing from the technical principles of this utility model, and these improvements and substitutions should also be considered within the protection scope of this utility model.

Claims

1. A fixing device for a steering bypass pin on an aircraft nose wheel, characterized in that, It includes a limiting structure. The limiting structure includes a cross beam and a support beam. One end of the support beam far away from the mop structure is fixedly connected with the cross beam. The cross beam is horizontally arranged to abut against and limit the handle in the mop structure. A first through hole is provided at the bottom of the support beam. The first through hole is used to be arranged corresponding to the first mounting hole of the mop structure. A positioning member is inserted into the first through hole and the first mounting hole. A second through hole is provided on one side of the cross beam far away from the support beam. The second through hole is used to be arranged corresponding to the second mounting hole in the mop structure. The second through hole and the second mounting hole are used to insert a by-pass pin.

2. The fixing device for the bypass pin of an aircraft nose wheel according to claim 1, characterized in that, The limiting structure is in a "U" shaped structure. The limiting structure further includes a movable beam. The movable beam is arranged at one end of the cross beam far away from the support beam. The second through hole is provided at one end of the movable beam far away from the cross beam.

3. The fixing device for the bypass pin of an aircraft nose wheel according to claim 2, characterized in that, A first support foot is provided at one end of the support beam far away from the cross beam. A second support foot is provided at one end of the movable beam far away from the cross beam.

4. The fixing device for the bypass pin of an aircraft nose wheel according to claim 3, characterized in that, Both the first support foot and the second support foot are plate-shaped parts. And the plate surfaces of the first support foot and the second support foot are both in contact with the main body of the mop structure. The first through hole is provided on the first support foot. The second through hole is provided on the second support foot.

5. The fixing device for the bypass pin of an aircraft nose wheel according to claim 1, characterized in that, The limiting structure is in a "L" shaped structure. The mop structure includes a fixed beam. The fixed beam is arranged on one side of the cross beam far away from the support beam. The second mounting hole is provided at one end of the fixed beam close to the cross beam.

6. The fixing device for the bypass pin of an aircraft nose wheel according to claim 5, characterized in that, A third support foot is provided at one end of the support beam far away from the cross beam. A fourth support foot is provided at one end of the fixed beam close to the cross beam. A fifth support foot is provided at one end of the fixed beam far away from the cross beam. The third support foot and the fifth support foot are symmetrically arranged about the center of the cross beam. The fourth support foot and the fifth support foot are symmetrically arranged about the center of the fixed beam.

7. The fixing device for the bypass pin of an aircraft nose wheel according to claim 6, characterized in that, Both the third support foot, the fourth support foot and the fifth support foot are plate-shaped parts. And the plate surfaces of the third support foot and the fifth support foot are both in contact with the main body of the mop structure. The fourth support foot is in contact with the cross beam. The first through hole is provided on the third support foot. The second mounting hole is provided on the fourth support foot. The fifth support foot is fixedly connected with the main body of the mop structure.

8. The fixing device for the bypass pin of an aircraft nose wheel according to claim 1, characterized in that, The mop structure includes a base main body, a lock and the handle. The lock is provided on one side of the base main body far away from the limiting structure. A lock tongue is movably arranged in the lock. The lock tongue is movably connected with the handle. A lock groove is further provided on the base main body corresponding to the lock tongue.

9. The fixing device for the bypass pin of an aircraft nose wheel according to claim 8, characterized in that, The handle includes an obliquely arranged rod and a cross rod fixedly connected. The obliquely arranged rod is movably connected with the lock tongue. The axis of the cross rod is vertically intersected with the axis of the cross beam.

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