Fixing tool for aircraft front wheel turning bypass pin
By designing a fixture for the bypass pin of the aircraft nose wheel, using a T-shaped structure and positioning components, the problem of workers forgetting to insert the bypass pin was solved, ensuring the safety of the aircraft nose wheel and reducing the accident rate of towing operations.
Patent Information
- Application Number
- CN202422967516.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-02
- Publication Date
- 2025-11-04
- Estimated Expiration
- 2034-12-02
AI Technical Summary
During aircraft towing operations, workers may forget to insert the bypass pin, resulting in the nose wheel not being released from restraint, which may cause damage to the aircraft's nose wheel and turning system, leading to a high accident rate.
Design a fixing fixture for the bypass pin of an aircraft nose wheel turning. It adopts a T-shaped structure, a positioning component and a downward pressure stop. Through the cooperation of the positioning component and the tow bar structure, it ensures that the bypass pin cannot connect to the aircraft nose wheel after insertion, prompting the operator to insert the bypass pin to release the turning restriction.
This effectively prompts staff to insert the bypass pin, ensuring that the nose wheel turning restriction is released, reducing the accident rate during towing operations and protecting the safety of the aircraft's nose wheel and turning system.
Smart Images
Figure CN223507115U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of tooling technology, and in particular to a fixing tool for a steering bypass pin of an aircraft nose wheel. Background Technology
[0002] Currently, the nose wheel steering system of commercial passenger aircraft is usually controlled by a hydraulic system. During the towing process, the aircraft engine is started in advance, and pressure is supplied to the nose wheel hydraulic system during startup. The hydraulic action also restricts the nose wheel from maintaining a neutral position.
[0003] During towing of an aircraft, the nose wheel will deflect, creating a conflict between towing and nose wheel restraint. For example, the nose wheel hydraulic system of the A320 series aircraft mainly includes a hydraulic pump, main hydraulic circuit, nose wheel steering actuator, and the core control computer (BSCU) for the braking system and nose wheel steering system. The main hydraulic circuit connects the hydraulic pump and the nose wheel steering actuator, providing hydraulic pressure to the actuator and restricting the nose wheel to the neutral position when the engine starts. Furthermore, a bypass hydraulic circuit is located between the two ends of the nose wheel steering actuator, with a bypass valve installed on it. During towing, a bypass pin must be manually inserted, and the BSCU then sends an electrical signal to the bypass valve to open, allowing the bypass hydraulic circuit to open and releasing the nose wheel steering restraint.
[0004] In addition, the towing vehicle's tow bar is designed with a handle and a locking tongue assembly. Raising the handle opens the locking tongue, and lowering the handle closes it, connecting the tow bar to the aircraft's nose wheel. However, in actual towing operations, workers may easily overlook inserting the bypass pin, leaving the nose wheel unrestrained. This could damage the aircraft's nose wheel and turning system, resulting in a high accident rate during towing operations. Utility Model Content
[0005] The technical problem this invention aims to solve is that during actual towing operations, workers are prone to overlooking the insertion of the bypass pin, resulting in the front wheel not being released from its restraints, which may cause damage to the aircraft's front wheel and turning system, leading to a high accident rate in towing operations.
[0006] To solve the above-mentioned technical problems, this utility model provides a technical solution for fixing a bypass pin for an aircraft nose wheel:
[0007] The fixture for securing the bypass pin of the aircraft nose wheel includes a T-shaped structure, a positioning element, and a downward pressure stop. The T-shaped structure includes a transverse section and a longitudinal section, with the longitudinal section fixedly connected to the middle of the transverse section.
[0008] One end of the transverse section has a first through hole, which is arranged to correspond to the first mounting hole of the mop structure, and the positioning member is inserted into the first through hole and the first mounting hole of the mop structure.
[0009] The other end of the transverse section is provided with a second through hole, which is arranged to correspond with the second mounting hole of the mop structure, and the second through hole and the second mounting hole of the mop structure are used to insert a bypass pin.
[0010] The downward pressure stop is located at the end of the longitudinal section away from the transverse section, and the downward pressure stop protrudes from the side of the longitudinal section opposite to the mop structure. The downward pressure stop is used to cooperate with the handle to stop when the handle is pressed down.
[0011] Furthermore, the downward pressing stop is a stop inclined plate, which extends obliquely upward on the side facing away from the mop structure, and a vertical plate is fixedly connected between the stop inclined plate and the longitudinal section.
[0012] Furthermore, the angle between the stop plate and the longitudinal segment is any angle between 60° and 85°.
[0013] Furthermore, the longitudinal section is provided with a support portion on the side opposite to the downward pressing stop portion. The support portion protrudes towards the side close to the mop structure and is used to cooperate with the upper side of the mop structure for support.
[0014] Furthermore, the support portion is located on the longitudinal section near the downward stop portion, and the protrusion height of the support portion relative to the longitudinal section is any size between 20mm and 80mm.
[0015] Furthermore, the transverse segment is a transverse strip plate, and the longitudinal segment is a longitudinal strip plate. The surfaces of the transverse segment and the longitudinal strip plate are arranged parallel to and spaced apart from the upper side of the mop structure, respectively.
[0016] Furthermore, one end of the transverse segment is provided with a first support leg, and the other end of the transverse segment is provided with a second support leg, the first support leg and the second support leg being arranged symmetrically about the center of the transverse segment.
[0017] Furthermore, both the first and second legs are L-shaped components, and both the first and second legs include horizontal edges, which are spaced apart on the side of the transverse section closest to the mop structure. The first through hole is opened on the horizontal edge of the first leg, and the second through hole is opened on the horizontal edge of the second leg.
[0018] Furthermore, the positioning element is a positioning bolt, which is clearance-fitted with the first through hole, and is used for threaded engagement with the first mounting hole of the mop structure.
[0019] Compared with the prior art, the fixing fixture for the bypass pin of the aircraft nose wheel of this utility model has the following advantages: The fixing fixture for the bypass pin of the aircraft nose wheel adopts a T-shaped structure, a positioning component, and a downward pressure stop. The T-shaped structure includes a transverse section and a longitudinal section fixedly connected to the middle of the transverse section. One end of the transverse section has a first through hole. Correspondingly, the mop structure has a first mounting hole. The positioning component is inserted into the first through hole and the first mounting hole of the mop structure. The positioning component restricts the T-shaped structure to form a rotation center, so that the T-shaped structure rotates relative to the mop structure with the positioning component as the center to switch between the stop state and the unlock state.
[0020] Furthermore, a second through hole is provided at the other end of the transverse section, and correspondingly, a second mounting hole is provided on the mop structure. Additionally, a downward-pressing stop is located at the end of the longitudinal section away from the transverse section, protruding from the side of the longitudinal section opposite to the mop structure. When not using the mop for towing, a bypass pin can be inserted into the second through hole and the second mounting hole of the mop structure. The bypass pin acts as a stop for the T-shaped structure, preventing rotation. At this time, the downward-pressing stop is located below the handle and reliably stops the handle, preventing the locking tongue of the mop structure from closing and blocking the connection between the mop structure and the aircraft's nose wheel.
[0021] When using a mop for towing, the worker first removes the bypass pin. This action prompts the worker to install the bypass pin on the front wheel hydraulic system, opening the bypass oil circuit and releasing the turning restriction of the front wheel. Then, with the bypass pin's anti-rotation function released, the T-shaped structure can rotate around the positioning component. When the stop is pressed down and the handle is misaligned, it is in the unlocked state. At this point, the worker can smoothly press down the handle to close the locking tongue, achieving effective connection between the mop structure and the aircraft's front wheel. This fixing fixture reminds the worker to insert the bypass pin, ensuring effective release of the front wheel's turning restriction, preventing damage to the aircraft's front wheel and turning system during towing operations, and reducing the accident rate during towing operations. Attached Figure Description
[0022] Figure 1 This is a three-dimensional schematic diagram of the fixing fixture for the aircraft front wheel turning bypass pin applied to the mop structure (in the blocking state) in an embodiment of this utility model.
[0023] Figure 2 This is a front view schematic diagram of the fixing tool for the aircraft front wheel turning bypass pin applied to the mop structure (in the blocking state) in the embodiment of this utility model.
[0024] Figure 3 This is a top view of the fixing fixture for the aircraft front wheel turning bypass pin in this embodiment of the utility model applied to the mop structure (in the blocking state).
[0025] Figure 4 This is a top view of the fixing fixture for the aircraft front wheel turning bypass pin in this embodiment of the utility model applied to the mop structure (when the stop is released);
[0026] In the diagram: 1-T-shaped structure, 10-support part, 11-transverse section, 12-longitudinal section, 13-first through hole, 14-second through hole, 15-first support leg, 16-second support leg, 2-positioning part, 3-downward stop part, 30-stop inclined plate, 31-vertical plate, 4-mop structure, 40-handle, 41-second mounting hole of mop structure, 5-bypass pin. Detailed Implementation
[0027] The specific embodiments of this utility model will be described in further detail below with reference to the accompanying drawings and examples. The following examples are used to illustrate this utility model, but are not intended to limit its scope.
[0028] 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.
[0029] 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.
[0030] 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.
[0031] like Figures 1 to 4As shown, a fixing fixture for a turning bypass pin of an aircraft front wheel according to an embodiment of the present invention includes a T-shaped structure 1, a positioning member 2, and a downward pressing stop 3. The T-shaped structure 1 includes a transverse section 11 and a longitudinal section 12, with the longitudinal section 12 fixedly connected to the middle of the transverse section 11. One end of the transverse section 11 has a first through hole 13, which is arranged to correspond with the first mounting hole of the mop structure 4, and the positioning member 2 is inserted into the first through hole 13 and the first mounting hole of the mop structure 4.
[0032] A second through hole 14 is provided at the other end of the transverse section 11. The second through hole 14 is arranged to correspond with the second mounting hole 41 of the mop structure, and the second through hole 14 and the second mounting hole 41 of the mop structure are used to insert the bypass pin 5. The pressing stop part 3 is provided at the end of the longitudinal section 12 away from the transverse section 11, and the pressing stop part 3 protrudes from the side of the longitudinal section 12 facing away from the mop structure 4. The pressing stop part 3 is used to stop the handle 40 when the handle 40 is pressed down.
[0033] The fixing fixture for the aircraft nose wheel turning bypass pin adopts a design of T-shaped structure 1, positioning part 2, and downward pressure stop part 3. The T-shaped structure 1 includes a horizontal section 11 and a vertical section 12 fixedly connected to the middle of the horizontal section 11. One end of the horizontal section 11 has a first through hole 13. Correspondingly, the mop structure 4 has a first mounting hole. The positioning part 2 is inserted into the first through hole 13 and the first mounting hole of the mop structure 4. The positioning part 2 restricts the T-shaped structure 1 to form a rotation center, so that the T-shaped structure 1 rotates relative to the mop structure 4 with the positioning part 2 as the center, so as to switch between the stop state and the unlock state.
[0034] Furthermore, a second through hole 14 is provided at the other end of the transverse section 11, and correspondingly, a second mounting hole is provided for the mop structure 4. In addition, a downward stop part 3 is provided at the end of the longitudinal section 12 away from the transverse section 11, and the downward stop part 3 protrudes from the side of the longitudinal section 12 facing away from the mop structure 4. When the mop is not used for towing, the bypass pin 5 can be inserted into the second through hole 14 and the second mounting hole 41 of the mop structure. The bypass pin 5 acts as a stop for the T-shaped structure 1 to prevent rotation. At this time, the downward stop part 3 is located on the lower side of the handle 40 and provides a reliable stop for the handle 40, preventing the locking tongue of the mop structure 4 from closing and preventing the mop structure 4 from connecting with the aircraft's front wheel.
[0035] When using a mop for towing, the worker first pulls out the bypass pin 5. This action prompts the worker to install the bypass pin 5 onto the front wheel hydraulic system, thus opening the bypass oil circuit and releasing the turning restriction of the front wheel. Then, since the anti-rotation function of the bypass pin 5 is released, the T-shaped structure 1 can rotate around the positioning part 2. When the lower stop 3 is vertically misaligned with the handle 40, it is in the unlocked state. At this point, the worker can smoothly press down the handle 40 to close the locking tongue, achieving effective connection between the mop structure 4 and the aircraft's front wheel. This fixing fixture allows the worker to insert the bypass pin, ensuring effective release of the front wheel's turning restriction, preventing damage to the aircraft's front wheel and turning system during towing operations, and reducing the accident rate during towing operations.
[0036] In this embodiment, the downward-pressing stop 3 is a stop slope 30, which extends obliquely upward on the side facing away from the mop structure 4. A vertical plate 31 is also fixedly connected between the stop slope 30 and the longitudinal section 12. Specifically, the angle between the stop slope 30 and the longitudinal section 12 is any angle between 60° and 85°. The downward-pressing stop 3, being an obliquely upward-extending stop slope 30, can stop the handle 40 downward. Since the angle between the stop slope 30 and the longitudinal section 12 is between 60° and 85°, it can effectively stop the handle 40 and ensure that the handle 40 is stably kept in the raised state.
[0037] Furthermore, a support portion 10 is provided on the side of the longitudinal section 12 opposite to the downward pressing stop portion 3. The support portion 10 protrudes towards the side near the mop structure 4 and is used to cooperate with the upper side of the mop structure 4 for support. As a further preferred embodiment, the support portion 10 is located on the longitudinal section 12 near the downward pressing stop portion 3, and the protrusion height of the support portion 10 relative to the longitudinal section 12 is any size between 20mm and 80mm. When the T-shaped structure 1 is in the stopped position, the support portion 10 cooperates with the upper side of the mop structure 4 for support, ensuring that the longitudinal section 12 can reliably withstand the downward pressure from the handle 40, thereby ensuring the stability of the stop limit.
[0038] In this embodiment, the transverse segment 11 is a transverse strip plate, and the longitudinal segment 12 is a longitudinal strip plate. The surfaces of the transverse segment 11 and the longitudinal strip plate are arranged parallel to and spaced apart from the upper side of the mop structure 4. Both the transverse segment 11 and the longitudinal segment 12 are fixedly connected by strip plates, resulting in a simple structure that is easy to manufacture.
[0039] Furthermore, a first support leg 15 is provided at one end of the transverse segment 11, and a second support leg 16 is provided at the other end of the transverse segment 11. The first support leg 15 and the second support leg 16 are arranged symmetrically about the center of the transverse segment 11. Both the first support leg 15 and the second support leg 16 are L-shaped pieces, and both the first support leg 15 and the second support leg 16 include horizontal edges, which are spaced apart on the side of the transverse segment 11 near the mop structure 4. A first through hole 13 is opened on the horizontal edge of the first support leg 15, and a second through hole 14 is opened on the horizontal edge of the second support leg 16.
[0040] Since the ends of the transverse section 11 are respectively provided with a first support leg 15 and a second support leg 16, and both support legs are L-shaped, a certain gap can be formed between the transverse section 11 and the longitudinal section 12 and the upper side of the mop structure 4, so as to prevent the rotation of the T-shaped structure 1 from being affected by the protrusion on the upper side of the mop structure 4.
[0041] In addition, the positioning element 2 is a positioning bolt, which is clearance-fitted with the first through hole 13, and is used for threaded engagement with the first mounting hole of the mop structure 4. It should be noted that only the first mounting hole and the second mounting hole need to be machined on the upper side of the mop structure 4. The positioning element 2 passes through the first through hole 13 of the transverse section 11 and is threaded to the first mounting hole of the mop structure 4, thereby achieving the purpose of hinged assembly between the T-shaped structure 1 and the mop structure 4. The structural changes to the original mop structure 4 are minimal, which facilitates subsequent modification work.
[0042] The above description is only a preferred embodiment of the present 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 the present utility model, and these improvements and substitutions should also be considered within the protection scope of the present utility model.
Claims
1. A fixing fixture for a bypass pin on an aircraft nose wheel, characterized in that, It includes a T-shaped structure, a positioning component, and a downward pressure stop. The T-shaped structure includes a horizontal section and a vertical section, with the vertical section fixedly connected to the middle of the horizontal section. One end of the transverse section has a first through hole, which is arranged to correspond to the first mounting hole of the mop structure, and the positioning member is inserted into the first through hole and the first mounting hole of the mop structure. The other end of the transverse section is provided with a second through hole, which is arranged to correspond with the second mounting hole of the mop structure, and the second through hole and the second mounting hole of the mop structure are used to insert a bypass pin. The downward pressure stop is located at the end of the longitudinal section away from the transverse section, and the downward pressure stop protrudes from the side of the longitudinal section opposite to the mop structure. The downward pressure stop is used to cooperate with the handle to stop when the handle is pressed down.
2. The fixing fixture for the aircraft nose wheel turning bypass pin according to claim 1, characterized in that, The downward pressure stop is a stop slope plate, which extends obliquely upward on the side facing away from the mop structure. A vertical plate is also fixedly connected between the stop slope plate and the longitudinal section.
3. The fixing fixture for the aircraft nose wheel turning bypass pin according to claim 2, characterized in that, The angle between the stop plate and the longitudinal section is any angle between 60° and 85°.
4. The fixing fixture for the aircraft nose wheel turning bypass pin according to claim 1, characterized in that, The longitudinal section is also provided with a support part on the side opposite to the downward pressure stop. The support part protrudes towards the side close to the mop structure and is used to cooperate with the upper side of the mop structure for support.
5. The fixing fixture for the aircraft nose wheel turning bypass pin according to claim 4, characterized in that, The support portion is located on the longitudinal section near the downward stop portion, and the protrusion height of the support portion relative to the longitudinal section is any size between 20mm and 80mm.
6. The fixing fixture for the aircraft nose wheel turning bypass pin according to claim 1, characterized in that, The horizontal segment is a horizontal strip plate, and the vertical segment is a vertical strip plate. The surfaces of the horizontal segment and the vertical strip plate are arranged parallel to and spaced apart from the upper side of the mop structure, respectively.
7. The fixing fixture for the aircraft nose wheel turning bypass pin according to claim 6, characterized in that, One end of the transverse segment is provided with a first leg, and the other end of the transverse segment is provided with a second leg. The first leg and the second leg are arranged symmetrically about the center of the transverse segment.
8. The fixing fixture for the aircraft nose wheel turning bypass pin according to claim 7, characterized in that, Both the first support leg and the second support leg are L-shaped pieces. Both the first support leg and the second support leg include horizontal edges, and the horizontal edges are spaced apart on the side of the horizontal segment near the mop structure. The first through hole is opened on the horizontal edge of the first support leg, and the second through hole is opened on the horizontal edge of the second support leg.
9. The fixing fixture for the aircraft nose wheel turning bypass pin according to claim 1, characterized in that, The positioning element is a positioning bolt, which is clearance-fitted with the first through hole, and is also thread-fitted with the first mounting hole of the mop structure.