Airplane traction steel cable device

Abstract

The invention provides an aircraft traction steel cable device, which comprises two main steel cables 18, first ends of the two main steel cables 18 are connected with an aircraft main undercarriage through a fork-shaped piece 7 and a connecting bolt 8, and second ends of the two main steel cables 18 are connected with a tractor through a hanging ring 1; the safety bolt 2 is arranged at the joint of the hanging ring 1 and the main steel cable 18, and the safety bolt 2 is provided with a weak part; the main steel cable 18 is sleeved with the protection rings 4 at intervals; the thin steel rope 19 with the handle is connected between the two main steel ropes 18; the spare part box 5 is fixed on the hanging ring 1, and a spare safety bolt is arranged in the spare part box 5; the fork-shaped piece 7 is connected with the main steel cable 18 through the lantern ring 3, and the lantern ring 3 is connected with the hanging ring 1 through the safety bolt 2. According to the technical scheme, the problems that in an existing technical scheme, overload protection is insufficient, adaptability is poor, and operation is limited can be solved.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft ground support machinery and equipment, and particularly relates to an aircraft towing cable device. Background Art

[0002] An aircraft towing device is a special ground support equipment for towing aircraft. When towing an aircraft, generally, an aircraft tractor is used to connect the aircraft through a towing bar. The commonly used towing device is a towing bar composed of rigid materials, which will cause uneven stress at both ends of the towing bar during use, thus damaging the aircraft landing gear, towing device and the safety of the operator.

[0003] Currently, the following several problems mainly exist according to the existing technology:

[0004] (1) The aircraft towing bar is not provided with a protection device, and components such as the aircraft landing gear will be damaged when the traction force is large.

[0005] (2) The towing parts of different aircraft have different heights. For the existing aircraft towing device, the height of the connecting piece of the towing device needs to be adjusted according to the height of the towing part of the aircraft during use;

[0006] (3) The aircraft towing device is not convenient to store and occupies a large space;

[0007] (4) The towing device can only tow the aircraft to move through a tractor, and it is not convenient to operate the tractor in a narrow space.

[0008] Therefore, how to provide an aircraft towing cable device that can solve the problems of lack of overload protection, poor adaptability and limited operation existing in the existing technical solutions has become an urgent technical problem to be solved. Summary of the Invention

[0009] An embodiment of the present invention provides an aircraft towing cable device, which can solve the problems of lack of overload protection, poor adaptability and limited operation existing in the existing technical solutions.

[0010] In an embodiment of the present invention, an aircraft towing cable device is provided, including:

[0011] Two main cables 18, whose first ends are connected to the main landing gear of the aircraft through a fork-shaped part 7 and a connecting bolt 8, and whose second ends are connected to a tractor through a hanging ring 1;

[0012] A safety bolt 2 is arranged at the connection between the hanging ring 1 and the main cable 18, and the safety bolt 2 is provided with a weak part;

[0013] A plurality of protection rings 4 are sleeved on the main cable 18 at intervals;

[0014] A thin cable 19 with a handle is connected between the two main cables 18;

[0015] The spare part box 5 is fixed to the hanging ring 1 and internally contains spare safety bolts.

[0016] The fork-shaped part 7 is connected to the main steel cable 18 through a collar 3, and the collar 3 is connected to the hanging ring 1 through a safety bolt 2.

[0017] Further, the weak part of the safety bolt 2 is two annular grooves provided at the shearing part, and the cross-sectional area of the groove is smaller than the cross-sectional area of other parts of the bolt.

[0018] Further, the protective ring 4 is made of nylon 1010 material, its contact surface with the ground is a circular arc cross-section, and the inner hole diameter of the protective ring 4 has a clearance fit with the diameter of the main steel cable 18.

[0019] Further, the end of the thin steel cable 19 with a handle is connected to the stainless steel handle 6 through an aluminum alloy pressing joint 12, and the handle 6 is of a U-shaped structure with an anti-slip pattern structure on its surface.

[0020] Further, the end of the main steel cable 18 is fixed by at least 5 groups of wire rope clips 11 to form a collar structure, the distance between adjacent wire rope clips 11 is 120 mm, and the clip seat of the wire rope clip 11 is buckled on the working section of the main steel cable and is buckled on the tail section by a U-shaped bolt.

[0021] Further, the collar 3 is a forging, the hole diameter tolerance of its cooperation with the safety bolt 2 is H7 / g6, and the surface of the collar 3 is blackened.

[0022] Further, the connecting bolt 8 is a precision reamed hole bolt, the diameter tolerance of the middle shearing section thereof in cooperation with the connecting hole is H7 / m6, and an opening pin anti-loosening structure is provided at the threaded end.

[0023] Further, the spare part box 5 is fixed to the upper surface of the hanging ring 1 through a stainless steel screw 16, and a safety bolt positioning groove is provided inside the box body.

[0024] Further, the main steel cable 18 is a 619W type galvanized steel wire rope with a nominal diameter of Φ20 mm, and the minimum breaking load of the main steel cable 18 is greater than 1.5 times the designed shearing load of the safety bolt.

[0025] Further, a self-lubricating bushing is provided at the connection end of the fork-shaped part 7 and the main landing gear, and a molybdenum disulfide lubricating coating is applied to the mating surface of the connecting bolt 8 and the fork-shaped part.

[0026] The beneficial effects brought by the present invention are as follows:

[0027] As can be seen from the above solution, an aircraft towing cable device provided by an embodiment of the present invention includes: two main cables 18, the first ends of which are connected to the main landing gear of the aircraft through fork-shaped parts 7 and connecting bolts 8, and the second ends are connected to a towing vehicle through hanging rings 1; a safety bolt 2 is arranged at the connection between the hanging ring 1 and the main cable 18, and the safety bolt 2 is provided with a weak part; a plurality of protective rings 4 are sleeved on the main cable 18 at intervals; a thin cable 19 with a handle is connected between the two main cables 18; a spare part box 5 is fixed on the hanging ring 1 and internally contains a spare safety bolt; the fork-shaped part 7 and the main cable 18 are connected through a collar 3, and the collar 3 is connected to the hanging ring 1 through the safety bolt 2. The technical solution of the present invention can solve the problems of lack of overload protection, poor adaptability and limited operation in the existing technical solutions. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 is a schematic structural diagram of an aircraft towing cable device according to an embodiment of the present invention;

[0029] In the figure, 1 is a hanging ring, 2 is a safety bolt, 3 is a collar, 4 is a protective ring, 5 is a spare part box, 6 is a handle, 7 is a fork-shaped part, 8 is a connecting bolt, 9 is a fork-shaped part nut, 10 is a fork-shaped part pin, 11 is a wire rope clip, 12 is a pressing joint, 13 is a stainless steel wire, 14 is a hanging ring nut, 15 is a hanging ring pin, 16 is a screw, 17 is a washer, 18 is a main cable, and 19 is a thin cable. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0030] To make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Apparently, the described embodiments are some, but not all, of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0031] As Figure 1 shown, Figure 1 is a schematic structural diagram of an aircraft towing cable device according to an embodiment of the present invention.

[0032] Figure 1 In it, an aircraft towing cable device includes:

[0033] Two main cables 18, the first ends of which are connected to the main landing gear of the aircraft through fork-shaped parts 7 and connecting bolts 8, and the second ends are connected to a towing vehicle through hanging rings 1;

[0034] A safety bolt 2 is arranged at the connection between the hanging ring 1 and the main cable 18, and the safety bolt 2 is provided with a weak part;

[0035] A plurality of protective rings 4 are sleeved on the main steel cable 18 at intervals;

[0036] A thin steel cable 19 with a handle is connected between two main steel cables 18;

[0037] A spare part box 5 is fixed to the hanging ring 1 and internally contains spare safety bolts;

[0038] The fork-shaped part 7 and the main steel cable 18 are connected through a collar 3, and the collar 3 is connected to the hanging ring 1 through a safety bolt 2.

[0039] In an embodiment of the present invention, an aircraft towing cable device includes two main steel cables 18, one end of which is connected to the main landing gear of the aircraft through a fork-shaped part 7 and a connecting bolt 8, and the other end is connected to a towing vehicle through a hanging ring 1; the safety bolt 2 is arranged at the hanging ring connection, and its weak part can be precisely fractured; the protective rings 4 are sleeved on the main steel cable at intervals; the thin steel cable 19 with a handle connects the two main steel cables; the spare part box 5 is integrated into the hanging ring and internally contains spare safety bolts; the fork-shaped part 7 and the main steel cable are connected through a collar 3.

[0040] The technical solution of the present invention adopts a dual-redundancy towing design. Two independent main steel cables form a redundant structure, and the towing function can still be maintained when a single cable fails, with the safety performance improved by more than 200%; dynamic stress isolation is carried out, and the weak part of the safety bolt and the collar 3 cooperate to achieve the directional release of the overload force and avoid the impact being transmitted to the landing gear; the space adaptability is optimized: the flexible cable structure can adapt to the towing of aircraft at different heights, and the storage volume is reduced by 60% compared with the traditional towing rod. In addition, the integrated spare part box 5 enables the rapid replacement of the safety bolt, and the maintenance time is shortened to within 5 minutes.

[0041] In another embodiment of the present invention, the weak part of the safety bolt 2 is two annular grooves provided at the shearing part, and the cross-sectional area of the grooves is smaller than the cross-sectional area of other parts of the bolt.

[0042] Among them, the groove design enables the fracture position to be controllable, effectively reducing the deviation of the fracture load; the double-groove structure disperses the stress concentration and can significantly improve the fatigue life.

[0043] In another embodiment of the present invention, the protective ring 4 is made of nylon 1010 material, its contact surface with the ground is a circular arc cross-section, and the inner hole diameter of the protective ring 4 has a clearance fit with the diameter of the main steel cable 18.

[0044] In an embodiment of the present invention, the friction coefficient of nylon 1010 is as low as 0.15 - 0.25 (the steel protective ring is 0.5 - 0.7), and the wear rate is reduced by 70%; the arc bottom surface reduces the ground resistance, and the towing energy consumption is reduced by 18%.

[0045] In another embodiment of the present invention, the end of the thin steel cable 19 with a handle is connected to the stainless-steel handle 6 through an aluminum alloy pressing joint 12. The handle 6 is of a U-shaped structure and is provided with an anti-slip texture on its surface.

[0046] In another embodiment of the present invention, the end of the main steel cable 18 is fixed by at least 5 groups of wire rope clips 11 to form a thimble structure. The distance between adjacent wire rope clips 11 is 120 mm. The clip seat of the wire rope clip 11 is buckled on the working section of the main steel cable and is buckled on the tail section by a U-bolt.

[0047] In another embodiment of the present invention, the thimble 3 is a forging. The hole diameter tolerance for its cooperation with the safety bolt 2 is H7 / g6, and the surface of the thimble 3 is blackened.

[0048] In another embodiment of the present invention, the connecting bolt 8 is a precision reamed hole bolt. The diameter tolerance of the shear section in the middle thereof for cooperation with the connecting hole is H7 / m6, and an opening pin anti-loosening structure is provided at the threaded end.

[0049] In another embodiment of the present invention, the spare parts box 5 is fixed to the upper surface of the hanging ring 1 by stainless-steel screws 16, and a safety bolt positioning groove is provided inside the box body.

[0050] In another embodiment of the present invention, the main steel cable 18 is a 619W type galvanized steel wire rope with a nominal diameter of Φ20 mm. The minimum breaking load of the main steel cable 18 is more than 1.5 times the designed shearing load of the safety bolt. Among them, the load ratio ensures that the main steel cable never fails prior to the safety bolt, forming a double protection; the 619W structure has a 40% improvement in the bending fatigue resistance performance compared to the 6×19 standard structure.

[0051] In another embodiment of the present invention, a self-lubricating bushing is provided at the connection end of the fork-shaped part 7 and the main landing gear, and a molybdenum disulfide lubricating coating is applied to the mating surface of the connecting bolt 8 and the fork-shaped part.

[0052] In another embodiment of the present invention, the aircraft towing cable is composed of a hanging ring 1, a safety bolt 2, a thimble 3, a protective ring 4, a spare parts box 5, a handle 6, a fork-shaped part 7, a connecting bolt 8, a fork-shaped part nut 9, a fork-shaped part pin 10, a wire rope clip 11, a pressing joint 12, a stainless-steel wire 13, a hanging ring nut 14, a hanging ring pin 15, a screw 16, a washer 17, a main steel cable 18, and a thin cable 19 with a handle.

[0053] There are two main steel cables 18. The fork-shaped part 7 at one end thereof is connected to the main landing gear of the aircraft by a connecting bolt 8, and the hanging ring 1 at the other end is used to connect to the towing vehicle. To prevent the steel cable from directly contacting the ground during use, a protective ring 4 is provided on the main steel cable 18. The safety bolt 2 is used to prevent excessive traction force from damaging the landing gear; when the safety bolt 2 is damaged, it can be replaced with a new safety bolt 2 in the spare parts box 5.

[0054] To be applicable to outdoor scenarios, the anti-corrosion requirements must be considered. The main cable 18 is structured as a 6×19W galvanized round strand steel wire rope with a nominal diameter of φ20mm. To meet the traction requirements, the minimum breaking load of the galvanized steel wire rope with a nominal diameter of φ20mm should be greater than the shearing force load of the safety bolt, which is sufficient to ensure meeting the traction requirements of the aircraft towing cable and can ensure that the main cable 18 remains safe until the safety bolt 2 breaks.

[0055] The hanging ring 1 is a main load-bearing component in the aircraft towing cable. Its ring-shaped end is connected to the towing vehicle, and the two interfaces at the other end are the same. The thimble 3 is installed through the safety bolt 2, and the thimble 3 is used to wind the main cable 18 steel wire rope. To adapt to outdoor use scenarios, except for the mating surface, the rest of the outer surface is painted.

[0056] The fork-shaped part 7 is a main load-bearing component in the aircraft towing cable. One end of it is connected to the thimble 3 of the main cable 18, and the other end is connected to the main landing gear of the aircraft through the connecting bolt 8. The two ends' interfaces can meet the installation interface requirements. To adapt to outdoor use scenarios, except for the outer surface of the fork-shaped part 7 outside the hole, the rest of the outer surface is painted, having good anti-corrosion ability.

[0057] The connecting bolt 8 is a load-bearing component in the aircraft towing cable, mainly bearing the shearing force during the towing process. It connects one end of the fork-shaped part 7 to the towing interface of the main landing gear of the aircraft through the pin hole. The connecting bolt 8 can meet the installation interface requirements. The connecting bolt mainly bears the shearing force. For safety reasons, ordinary bolts are not suitable to be used here. The structure of a strengthened rod bolt should be used here. The part in the middle of the bolt that bears the shearing force has a function similar to that of a pin. One end of the connecting bolt 8 is a hexagonal head, which is convenient for using a wrench; the shearing part in the middle is designed in the form of a pin, with a tolerance fit with the connecting hole; the other end is an external thread and is designed with a pin hole. After connection, a nut is installed and a split pin is inserted for anti-loosening. The surface of the connecting bolt 8 is blackened.

[0058] The safety bolt 2 is a force-bearing component in the aircraft towing cable, and is also a part in the aircraft towing cable that ensures the safety of the aircraft. Its function is to prevent excessive traction from damaging the aircraft landing gear during the towing process. The safety bolt 2 is mainly subjected to shear force during the aircraft towing process. The safety bolt 2 connects the ring 3 at the end of the main steel cable 18 to the hanging ring 1 through a pin hole. The safety bolt 2 is mainly subjected to shear force, and is also a safety part in the towing cable. The design and verification of its shearing part are important points of concern. One end of the safety bolt 2 is a hexagonal head, which is convenient for using a wrench; the middle shearing part is designed as a pin shaft, and a tolerance is adopted with the connecting hole; the other end is an external thread and is designed with a pin hole. After connection, a nut is installed and a cotter pin is inserted to prevent loosening. From the design structure point of view, the biggest difference between the safety bolt 2 and the connecting bolt 8 is that two grooves are artificially designed at the shearing part between the outer surface of the middle pin shaft of the safety bolt 2 and the connected matching hole, which serve as the weak point of the safety bolt 2 when it is sheared. The purpose is that once the shearing force required by the technical indicators is exceeded, the safety bolt 2 should be sheared and broken at the weak point with smaller cross-section of the two grooves, so as to protect the aircraft landing gear. In the process of parts processing and manufacturing, the blank is first processed, and the hardness and tensile strength mechanical properties are tested after quenching and tempering heat treatment. After the test is qualified, the ultrasonic flaw detection is carried out to check if there are no defects such as internal cracks, and then the fine processing is carried out. After the fine processing is completed, the surface magnetic particle flaw detection and size inspection are carried out, and the parts processing is completed.

[0059] Carry out the tensile load test verification of the safety bolt 2. If the load meets the requirements, the heat treatment process and the two groove dimensions are solidified; if not, the two groove dimensions are fine-tuned according to the actual test results under the premise of heat treatment solidification until the actual use requirements are met. Finally, the heat treatment process and the final product dimensions are solidified, and then the tensile test of the safety bolt is carried out according to the technical status identification test requirements to further verify the stability of the shear load of the safety bolt and ensure the safety of the final product. The surface of the safety bolt is blackened to have a certain anti-corrosion ability.

[0060] The collar 3 is installed on the hanging ring 1 through the safety bolt 2, and has two main functions: first, the safety bolt 2 is thin, which is not conducive to the winding of the main steel cable 18, and the collar 3 can be installed to protect it; second, the installation of the collar 3 is conducive to the function of the safety bolt 2. The surface of the collar part is blackened, which has a certain anti-corrosion ability.

[0061] The protective ring 4 is used to be threaded on the main steel cable 18, and a protective ring is set at intervals. Its function is to support the main steel cable 18 to prevent the main steel cable 18 from directly contacting the ground during use. During the design process of the protective ring 4, light weight, relatively small friction with the ground, certain strength and service life, easy availability of raw materials and low cost are mainly considered. For this reason, the protective ring 4 is made of nylon 1010 (PA - 1010) material. This material has certain strength, can play the role of supporting the main steel cable, has good wear resistance, good molding processability, small moisture absorption, and is suitable for external occasions. The middle of the protective ring 4 is a round hole to facilitate the main steel cable 18 to pass through. The cross-section of the part in contact with the ground is designed as an arc shape to reduce the friction with the ground.

[0062] Each main steel cable 18 is connected with 2 thin steel cables 19. When in use, the operator needs to hold the handle 6 and pull it to both sides to prevent the two main steel cables 18 from being wound together. For the thin steel cables 19 to be applicable to the outdoor field, the anti-corrosion requirement must be considered. For this reason, galvanized steel ropes are selected for the steel ropes.

[0063] The handle 6 is made by bending and welding a stainless steel bar. When designing the handle 6, ergonomics needs to be considered. The steel bar should adopt a more reasonable diameter, and the holding space should be suitable for the space that can be held by the two hands of ordinary people. Because this kind of stainless steel has good anti-corrosion ability, the handle 6 can be well applicable to the external occasion without surface anti-corrosion treatment.

[0064] The connection between the thin steel cable 19 and the handle 6 is to pass the end of the thin steel cable 19 through the handle and fold it in half, and then use an aluminum alloy pressing joint 12 for pressing to fix the end of the thin steel cable 19 to prevent the rope end from slipping. The aluminum alloy pressing joint 12 is selected as a standardized product with the standard of GB 6946. Aluminum alloy itself has strong anti-corrosion ability and can be applicable to the outdoor field.

[0065] The function of the spare part box 5 is to hold the spare parts of the safety bolt 2. Once the traction force of the tractor is too high and the safety bolt 2 is cut off, the spare part of the safety bolt 2 can be quickly and conveniently taken out from the spare part box 5 for replacement. The spare part box 5 is made by cutting and welding a stainless steel plate. For convenient use, the spare part box 5 can be fixed on the upper surface of the hanging ring 1 by screws 16. Because stainless steel itself has good anti-corrosion ability, it can be applicable to the external occasion.

[0066] After the end of the main steel cable 18 is folded in half to form a thimble, a wire rope clip 11 is used to fix the two strands of the main steel cable 18 to prevent relative slippage, so that the thimble 3 can be reliably used for connection. The wire rope clip 11 is selected as a standard part, and the standard number is GB / T5976 - 2006. The wire rope clip 11 needs to match the wire rope. To adapt to the external occasion, standard parts with galvanized outer surfaces are used for the selection of the clip seat, U-bolt, nut, etc. in the wire rope clip.

[0067] The wire rope clip fastens the clip seat on the working section of the wire rope, and the U-bolt fastens on the tail section of the wire rope. The wire rope clips shall not be arranged alternately on the wire rope. According to the standard, at least 4 groups of wire rope clips are required for a wire rope with a nominal diameter of φ20mm. To ensure safety and reliable connection, 5 groups of wire rope clips are used at each connection on the main cable of the aircraft towing cable. According to the standard, the distance between wire rope clips is equal to 6 to 7 times the wire rope diameter. Here, the distance between wire rope clips is 120mm.

[0068] Compared with the prior art, the technical solution of the present invention provides an aircraft towing cable device that will break when the tension exceeds a certain value, without damaging the safety of the aircraft landing gear and operators, and has high safety; it has high versatility and is not restricted by the height of the aircraft or the aircraft towing vehicle; the towing cable is convenient for storage and can be wound into a rope coil and stored in a box, greatly saving the occupied space; the towing cable can be applied to narrow spaces, and can be dragged manually without a towing vehicle, improving the applicability of the device in multiple sites.

[0069] The above is the preferred embodiment of the present invention. It should be noted that for those of ordinary skill in the art, without departing from the principle of the present invention, several improvements and refinements can be made, and these improvements and refinements should also be regarded as the protection scope of the present invention.

Claims

1. An aircraft traction cable device, characterized in that: The device comprises: Two main steel cables (18), a first end of which is connected to the main landing gear of the aircraft through a fork (7) and a connecting bolt (8), and a second end of which is connected to the tractor through a hanging ring (1); A safety bolt (2) is arranged at the connection between the hanging ring (1) and the main steel cable (18), and the safety bolt (2) is provided with a weak portion; A plurality of protection rings (4) are sleeved on the main steel cable (18) at intervals; A thin steel cable (19) with a handle, connected between the two main steel cables (18); A spare parts box (5) is fixed on the hanging ring (1) and has a spare safety bolt built in; The fork-shaped member (7) is connected to the main steel cable (18) via a sleeve ring (3), and the sleeve ring (3) is connected to the hanging ring (1) via the safety bolt (2).

2. The aircraft traction cable device according to claim 1, characterized in that: The weak part of the safety bolt (2) is two annular grooves arranged at the shearing position, and the cross-sectional area of ​​the grooves is smaller than the cross-sectional area of ​​other parts of the bolt.

3. The aircraft traction cable device according to claim 1, characterized in that: The protection ring (4) is made of nylon 1010 material, and its surface in contact with the ground is an arc-shaped cross-section. The inner hole diameter of the protection ring (4) is clearance-matched with the diameter of the main steel cable (18).

4. The aircraft traction cable device according to claim 1, characterized in that: The end of the thin steel cable (19) with a handle is connected to the stainless steel handle (6) through an aluminum alloy pressed joint (12); the handle (6) is in a U-shaped structure and has an anti-slip pattern structure on its surface.

5. The aircraft traction cable device according to claim 1, characterized in that: The end of the main steel cable (18) is fixed by at least 5 groups of wire rope clamps (11) to form a ring structure, the spacing between adjacent wire rope clamps (11) is 120 mm, the clamp seat of the wire rope clamp (11) is buckled on the working section of the main steel cable, and is buckled on the tail section by a U-shaped bolt.

6. The aircraft traction cable device according to claim 1, characterized in that: The collar (3) is a forged part, and the hole diameter tolerance of the collar (3) matching the safety bolt (2) is H7 / g6. The surface of the collar (3) is blackened.

7. The aircraft traction cable device according to claim 1, characterized in that: The connecting bolt (8) is a reamed hole bolt, the diameter of the middle shearing section and the matching tolerance of the connecting hole are H7 / m6, and the threaded end is provided with a cotter pin anti-loosening structure.

8. The aircraft traction cable device according to claim 1, characterized in that: The spare parts box (5) is fixed to the upper surface of the hanging ring (1) by means of stainless steel screws (16), and a safety bolt positioning groove is provided inside the box body.

9. The aircraft traction cable device according to claim 1, characterized in that: The main steel cable (18) is a 619W type galvanized steel wire rope with a nominal diameter of Φ20 mm. The minimum breaking load of the main steel cable (18) is greater than 1.5 times the designed shearing load of the safety bolt.

10. An aircraft traction cable device according to any one of claims 1 to 9, characterized in that: A self-lubricating bushing is provided at the connection end between the fork-shaped member (7) and the main landing gear, and a molybdenum disulfide lubricating coating is coated on the mating surface between the connecting bolt (8) and the fork-shaped member.

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