Airplane traction hook structure
By designing the fast latch structure and skeleton structure, the problem of easy falling off of the pin connection of the existing aircraft traction device is solved, and the rapid and reliable connection of the aircraft traction hook structure is achieved, which improves the connection efficiency and safety.
Patent Information
- Application Number
- CN202421333667.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-06-12
- Publication Date
- 2025-03-14
- Estimated Expiration
- 2034-06-12
AI Technical Summary
The existing pull connection method of aircraft traction device is easy to fall off, poses safety risks, and is inconvenient to operate, resulting in low connection efficiency.
An aircraft traction hook structure is designed, using a fast pin structure to quickly articulate the aircraft and is connected to the traction rod through a skeleton structure to ensure the reliability of the articulation and the safety of the traction process.
The rapid and reliable connection between the traction hook structure and the traction rod and the aircraft is achieved, which improves the connection efficiency, reduces the operation complexity, and ensures the safety of the traction process.
Smart Images
Figure CN222611380U_ABST
Abstract
Description
Technical Field
[0001] The utility model belongs to the technical field of aircraft traction devices, and in particular relates to an aircraft traction hook structure. Background Art
[0002] During the aircraft maintenance or transportation process, a towing rod is needed. One end of the towing rod is connected to the aircraft, and the other end of the towing rod is connected to the tractor, and then the aircraft is moved by the tractor. Among them, the existing towing rod is connected to the aircraft at one end by a latch connection. This latch connection is easy to fall off during the specific operation process, which poses certain safety hazards. In addition, the latch uses a separate latch, which is inconvenient to operate, resulting in low efficiency and cumbersome operation of connecting the towing rod to the aircraft. Utility Model Content
[0003] The purpose of the utility model is to provide an aircraft towing hook structure, which can be conveniently connected to a towing rod, and the other end adopts a quick latch structure to be quickly hinged and connected to the aircraft, thereby ensuring the reliability of the hinge and the safety of the towing process, and the quick latch structure is easy to operate.
[0004] In order to realize the above-mentioned technical features, the purpose of the utility model is achieved as follows: an aircraft towing hook structure, including a cross beam, hinged ear plates are fixed at both ends of the cross beam, and a support arm is hinged on the hinged ear plate through a rotating shaft, and a skeleton structure for connecting to a towing rod is fixed on the back side of the cross beam; the end of the support arm is equipped with a quick latch structure for connecting to an aircraft.
[0005] The skeleton structure comprises a main rod, which is welded to the middle part of the back of the cross beam, and oblique reinforcing rods are installed between the two sides of the main rod and the cross beam.
[0006] The main rod is processed with a main connection hole for hinged connection with the traction rod, and auxiliary connection holes are arranged on both sides of the main connection hole.
[0007] A first latch is inserted between the hinged ear plate and the support arm, and the first latch is used to be in a vertical locking state with the cross beam after the support arm is unfolded.
[0008] A first latch hole is processed on the hinged ear plate, and the first latch hole cooperates with a second latch hole processed on the support arm. The first latch hole and the second latch hole are used to insert a second pin shaft, and the second pin shaft is used to be in a parallel locking state with the crossbeam after the support arm is folded.
[0009] The quick latch structure includes a latch sleeve fixed to the end of the support arm, a quick latch is slidably installed inside the latch sleeve, a handle is installed at the end of the quick latch, a spiral groove is processed on the latch sleeve, the spiral groove cooperates with the stop pin on the latch, and a spring is arranged outside the quick latch and between the handle and the end surface of the latch sleeve.
[0010] The latch sleeve and the quick latch are made of titanium alloy material.
[0011] The utility model has the following beneficial effects:
[0012] 1. The hook structure of the utility model can be conveniently connected to the towing rod, and the other end adopts a quick latch structure to be quickly hinged to the aircraft, thereby ensuring the reliability of the hinge and the safety of the towing process, and the quick latch structure is easy to operate.
[0013] 2. The above-mentioned skeleton structure can be used to connect the hook structure with the aircraft's towing rod, thereby improving the connection efficiency and ensuring the reliability of the connection.
[0014] 3. The main connection hole and the auxiliary connection hole are convenient for articulation with the traction rod.
[0015] 4. The arm can be locked in the unfolded state by means of the first latch.
[0016] 5. The second pin shaft can be used to lock the support arm in the folded state.
[0017] 6. The above-mentioned quick latch structure facilitates quick latch connection with the aircraft, thereby ensuring safety and reliability during the towing process.
[0018] 7. Made of the above materials, the structural strength is guaranteed. BRIEF DESCRIPTION OF THE DRAWINGS
[0019] The utility model is further described below in conjunction with the accompanying drawings and embodiments.
[0020] Figure 1 This is a three-dimensional diagram of the utility model from the first perspective.
[0021] Figure 2 This is a three-dimensional diagram from the second viewing angle of the present invention.
[0022] Figure 3 This is a three-dimensional diagram of the support arm of the utility model from the first perspective.
[0023] Figure 4 This is a three-dimensional diagram of the support arm of the utility model from a second viewing angle.
[0024] Figure 5 It is a three-dimensional diagram of the quick latch of the utility model.
[0025] In the figure: main rod 1, oblique reinforcing rod 2, secondary connecting hole 3, main connecting hole 4, hinged ear plate 5, first latch 6, rotating shaft 7, handle 8, quick latch 9, spring 10, latch sleeve 11, spiral groove 12, stop pin 13, support arm 14, first latch hole 15, cross beam 16, second latch hole 17. DETAILED DESCRIPTION
[0026] The embodiments of the present utility model are further described below in conjunction with the accompanying drawings.
[0027] See also Figure 1-5 An aircraft towing hook structure includes a crossbeam 16, hinged ear plates 5 are fixed at both ends of the crossbeam 16, and a support arm 14 is hinged on the hinged ear plate 5 through a rotating shaft 7. A skeleton structure for connecting to a towing rod is fixed on one side of the back of the crossbeam 16; a quick latch structure for connecting to an aircraft is installed at the end of the support arm 14. This hook structure can be conveniently connected to the towing rod, and the other end adopts a quick latch structure to be quickly hinged and connected to the aircraft, and the reliability of the hinge is ensured, the safety of the towing process is ensured, and the quick latch structure is easy to operate. During the working process, the quick latch structure at the end of the support arm 14 is hinged to the landing gear hole of the aircraft.
[0028] Furthermore, the skeleton structure includes a main rod 1, which is welded to the middle part of the back of the cross beam 16, and oblique reinforcing rods 2 are installed between the two sides of the main rod 1 and the cross beam 16. By adopting the above-mentioned skeleton structure, the hook structure can be connected to the aircraft's towing rod, thereby improving the connection efficiency and ensuring the reliability of the connection.
[0029] Furthermore, the main rod 1 is processed with a main connection hole 4 for articulating with the traction rod, and auxiliary connection holes 3 are arranged on both sides of the main connection hole 4. The main connection hole 4 and the auxiliary connection hole 3 facilitate articulation with the traction rod.
[0030] Furthermore, a first latch 6 is inserted between the hinged ear plate 5 and the support arm 14, and the first latch 6 is used to be in a vertical locking state with the cross beam 16 after the support arm 14 is unfolded. The first latch 6 can realize locking of the support arm 14 in the unfolded state.
[0031] Furthermore, a first latch hole 15 is processed on the hinged ear plate 5, and the first latch hole 15 matches with a second latch hole 17 processed on the support arm 14. A second pin shaft is inserted between the first latch hole 15 and the second latch hole 17, and the second pin shaft is used to be in a parallel locking state with the cross beam 16 after the support arm 14 is folded. The locking of the support arm 14 in the folded state can be achieved by the second pin shaft.
[0032] Furthermore, the quick latch structure includes a latch sleeve 11 fixed to the end of the support arm 14, a quick latch 9 is slidably installed inside the latch sleeve 11, a handle 8 is installed at the end of the quick latch 9, a spiral groove 12 is processed on the latch sleeve 11, the spiral groove 12 cooperates with the stopper 13 on the latch 9, and a spring 10 is arranged outside the quick latch 9 and between the handle 8 and the end surface of the latch sleeve 11. The quick latch structure facilitates quick latch connection with the aircraft, thereby ensuring safety and reliability during the towing process.
[0033] Furthermore, the latch sleeve 11 and the quick latch 9 are made of titanium alloy material. The structural strength is ensured by the above-mentioned material.
[0034] The specific working process and principle of this utility model:
[0035] During specific use, the towing hook structure is hingedly connected to the towing rod, and then the quick latch structure is connected to the aircraft. After the quick latch 9 is inserted into the landing gear hole, the handle 8 on the quick latch 9 is pulled to make the stop pin 13 rotate along the spiral groove 12 and get stuck in the positioning groove. Under the action of the spring 10, the latch 9 will not loosen, ensuring safety during use. This design is easy to operate, fast and safe.
Claims
1. An aircraft towing hook structure, characterized in that: The invention comprises a cross beam (16), hinged ear plates (5) are fixed at both ends of the cross beam (16), a support arm (14) is hingedly connected to the hinged ear plate (5) via a rotating shaft (7), a skeleton structure for connecting to a traction rod is fixed on one side of the back of the cross beam (16); and a quick latch structure for connecting to an aircraft is installed at the end of the support arm (14).
2. The aircraft towing hook structure according to claim 1, characterized in that: The skeleton structure comprises a main rod (1), the main rod (1) being welded to the middle part of the back of the cross beam (16), and oblique reinforcing rods (2) are installed between the two sides of the main rod (1) and the cross beam (16).
3. The aircraft towing hook structure according to claim 2, characterized in that: The main rod (1) is provided with a main connection hole (4) for hinged connection with the traction rod, and auxiliary connection holes (3) are arranged on both sides of the main connection hole (4).
4. The aircraft towing hook structure according to claim 2, characterized in that: A first latch (6) is inserted between the hinged ear plate (5) and the support arm (14), and the first latch (6) is used to be in a vertical locking state with the crossbeam (16) after the support arm (14) is unfolded.
5. The aircraft towing hook structure according to claim 4, characterized in that: The hinged ear plate (5) is provided with a first latch hole (15), the first latch hole (15) matches with a second latch hole (17) formed on the support arm (14), a second pin shaft is inserted between the first latch hole (15) and the second latch hole (17), and the second pin shaft is used to be in a parallel locking state with the crossbeam (16) after the support arm (14) is folded.
6. The aircraft towing hook structure according to claim 1, characterized in that: The quick latch structure comprises a latch sleeve (11) fixed to the end of a support arm (14), a quick latch (9) being slidably mounted inside the latch sleeve (11), a handle (8) being mounted at the end of the quick latch (9), a spiral groove (12) being machined on the latch sleeve (11), the spiral groove (12) being matched with a stop pin (13) on the latch (9), and a spring (10) being arranged outside the quick latch (9) and between the handle (8) and the end surface of the latch sleeve (11).
7. The aircraft towing hook structure according to claim 6, characterized in that: The latch sleeve (11) and the quick latch (9) are made of titanium alloy material.