A flexible self-detachable aircraft towing rod

Abstract

The invention discloses a flexible self-detachable aircraft traction rod, comprising a traction rod assembly, a wheel, a first double ball head force sensor, an axle pin, a detachment module, a landing gear connection module, and a control system. The wheel is installed below the traction rod assembly, one end of the traction rod assembly is connected to a tractor, and the other end is connected to the detachment module through an axle pin, one end of the first double ball head force sensor is connected to a side of the detachment module, and the other end is connected to one side of an end of the traction rod assembly, and the top of the detachment module is connected to the aircraft landing gear through the landing gear connection module. When the tractor drags the aircraft landing gear through the flexible self-detachable aircraft traction rod, a turning moment safety value and a pulling force safety value are set through the control system, the control system reads the value of the first double ball head force sensor to measure the real-time turning moment and reads the value of the second double ball head force sensor in the detachment module to measure the real-time pulling force, and when either the turning moment value or the pulling force value exceeds the safety value, the control system controls the landing gear connection module to detach from the detachment module.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft manufacturing, and in particular to a flexible self-detachable aircraft towing rod. Background Art

[0002] In aircraft production, a tow bar is often needed to tow the aircraft. However, due to the limited strength of the aircraft landing gear, there are strength requirements for the traction force and turning moment. Therefore, the tow bar must be able to automatically disengage from the aircraft landing gear when the traction force or turning moment exceeds the safety limit to prevent damage to the aircraft structure. The existing tow bar manufacturing technology is to set a tension pin and a turning moment pin on the tow bar. The diameter and material of the two pins are pre-designed according to the safety value of the aircraft traction force and turning moment, ensuring that the pins can be cut off when the traction force or turning moment exceeds the safety value, thereby disengaging the tow bar from the aircraft. However, this technology has many problems. On the one hand, the performance of the pin material fluctuates and is often different from the theoretical value, which will affect the maximum traction and maximum turning moment of the tow bar and affect the safe towing of the aircraft. On the other hand, the tow bar pin needs to be remanufactured and reinstalled after it breaks, which greatly reduces the aircraft production efficiency and delays the aircraft production cycle. On the other hand, the weight of the same aircraft in different states is different, and its traction and turning moment safety values ​​are also different. Therefore, multiple sets of tow bars are required to adapt to aircraft in different states, which undoubtedly increases the aircraft manufacturing cost. In addition, the traction and turning moment safety values ​​of different types of aircraft are also different, resulting in the tow bars of different types of aircraft being not universal, which also increases the aircraft manufacturing cost.

[0003] In order to meet the safety towing requirements, production efficiency requirements and economic requirements in the aircraft manufacturing process, a towing rod with stable performance, high safety and adaptability to aircraft of different models and different states is needed. Summary of the invention

[0004] The object of the present invention is to provide a flexible self-detaching aircraft towing rod which can be used for safe towing in aircraft production.

[0005] In order to achieve the above objectives, this application adopts the following technical solutions:

[0006] A flexible self-detachable aircraft traction rod comprises a traction rod assembly, a wheel, a first double ball head force sensor, an axle pin, a detachment module, a landing gear connection module, and a control system. The wheel is installed below the traction rod assembly, one end of the traction rod assembly is connected to a tractor, and the other end is connected to the detachment module through an axle pin. One end of the first double ball head force sensor is connected to the side of the detachment module, and the other end is connected to one side of the end of the traction rod assembly. The top of the detachment module is connected to the aircraft landing gear through the landing gear connection module. When the tractor drags the aircraft landing gear through the flexible self-detachable aircraft traction rod, a turning moment safety value and a tension safety value are set through the control system. The control system reads the value of the first double ball head force sensor to measure the real-time turning moment and reads the value of the second double ball head force sensor in the detachment module to measure the real-time tension. When any one of the turning moment value and the tension value exceeds the safety value, the control system controls the landing gear connection module to detach from the detachment module.

[0007] Furthermore, the pull rod assembly includes a pull rod, a side plate, a ball socket, and a wheel mounting frame. The pull rod is a rod-shaped structure. The front end of the pull rod is a fork ear structure forked with the tractor, and the rear end is a fork ear structure forked with the separation module. The rear end of the pull rod is provided with a side plate extending to the side, and the top of the side plate is provided with a ball socket connected to the first double ball head force sensor ball, and a wheel mounting frame with an inverted "T" shape structure is provided below the pull rod.

[0008] Furthermore, both end heads of the first double ball head force sensor are ball head structures, the axis of the first double ball head force sensor is perpendicular to the axis of the pin shaft, and the distance between the axes is the turning force arm.

[0009] Furthermore, the disengagement module includes a transfer tube, a second double-ball head force sensor, an adapter seat, and an electromagnet. The adapter seat includes a base plate, a cylindrical protrusion matching the inner diameter of the transfer tube is arranged at the center of the base plate, and the center of the protrusion is a ball socket structure matching the second double-ball head force sensor. An electromagnet is installed on the other side of the base plate. The transfer tube is a tubular structure with an opening on the middle side. A fork ear structure is arranged at the front end thereof forked with the pull rod through an axle pin, and a rear end is slidably connected with the cylindrical protrusion of the transfer seat, and a ball socket structure forming a ball joint with the first double-ball head force sensor is arranged on the side. The second double-ball head force sensor is located in the opening of the transfer tube, and the front end ball head forms a ball joint with the ball socket arranged at the front end of the transfer tube, and the rear end ball head forms a ball joint with the ball socket of the cylindrical protrusion of the transfer seat.

[0010] Furthermore, the landing gear connection module includes an armature and an adapter. The adapter is a plate-like structure with an armature installed on the front side. The armature forms a magnetic attraction relationship with the electromagnet in the disengagement module. A connection structure matching the aircraft landing gear connector is provided on the rear side of the adapter.

[0011] The advantage of the present application is that compared with the traditional traction rod, the first double ball head force sensor is at a certain distance from the axle pin in space, forming a turning lever arm, and the control system accurately calculates the turning moment by measuring the force value of the first double ball head force sensor; the cylindrical protrusion of the adapter seat forms a sliding fit connection with the rear end of the adapter tube, and the second double ball head force sensor is located in the adapter tube and connected to the adapter seat, and the control system accurately measures the tension state of the traction rod through the second double ball head force sensor; the disengagement module forms an electromagnetic attraction relationship with the armature in the landing gear joint through its electromagnet, and the control system calculates that when either the turning moment or the tension value exceeds the safety value, the control electromagnet will be controlled to cut off the power, so that the landing gear joint is disengaged from the disengagement module, and when it is used again, the electromagnet and the armature can be attached and energized, thereby improving the safety and use efficiency of the traction rod, and the traction safety value of the control system can be set according to different models, so that the traction rod has greater flexibility and reduces the cost of aircraft production and use.

[0012] The present application is further described in detail below in conjunction with the accompanying drawings and embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 A structural diagram of a flexible self-detachable aircraft towing rod;

[0014] Figure 2 Departure from the module structure diagram;

[0015] Figure 3 Landing gear joint structure diagram;

[0016] Figure 4 Schematic diagram of connecting modules.

[0017] Explanation of numbers in the figure: 1, tie rod assembly, 2, wheel, 3, first double ball head force sensor, 4, axle pin, 5, disengagement module, 6, landing gear connection module, 7, control system, 8, tie rod, 9, side plate, 10, ball socket, 11, wheel mounting frame, 12 adapter tube, 13 second double ball head force sensor, 14 adapter seat, 15 electromagnet, 16 armature, 17 adapter. DETAILED DESCRIPTION

[0018] In this embodiment, Figure 1-4As shown, a flexible self-detachable aircraft traction rod comprises a traction rod assembly 1, a wheel 2, a first double ball head force sensor 3, an axle pin 4, a detachment module 5, a landing gear connection module 6, and a control system 7. The wheel 2 is installed below the traction rod assembly 1. One end of the traction rod assembly 1 is connected to the tractor, and the other end is connected to the detachment module 5 through the axle pin 4. One end of the first double ball head force sensor 3 is connected to the side of the detachment module 5, and the other end is connected to one side of the end of the traction rod assembly 1. The top of the detachment module 5 is connected to the aircraft landing gear through the landing gear connection module 6. When the tractor drags the aircraft landing gear through the flexible self-detachable aircraft traction rod, the turning moment safety value and the pulling force safety value are set through the control system 7. The control system 7 reads the value of the first double ball head force sensor 3 to calculate the real-time turning moment and reads the value of the second double ball head force sensor 13 in the separation module 5 to calculate the real-time tension. When either the turning moment value or the tension value exceeds the safety value, the control system 7 controls the landing gear connection module 6 to disengage from the separation module 5; the pull rod assembly 1 includes a pull rod 8, a side plate 9, a ball socket 10, and a wheel mounting frame. The pull rod 8 is a rod-shaped structure. The front end of the pull rod 8 is a fork ear structure forked with the tractor, and the rear end is a fork ear structure forked with the separation module 5. The rear end of the pull rod 8 is provided with a side plate 9 extending to the side, and the top of the side plate 9 is provided with a ball socket 10 connected to the first double ball head force sensor 3. A wheel mounting frame with an inverted "T"-shaped structure is arranged below 8; both ends of the first double ball head force sensor 3 are ball head structures, the axis of the first double ball head force sensor 3 is perpendicular to the axis of the pin shaft, and the axis spacing is the turning force arm; the disengagement module 5 includes a transfer tube 12, a second double ball head force sensor 13, a transfer seat 14, and an electromagnet 15. The transfer seat 14 includes a bottom plate, a cylindrical protrusion matching the inner diameter of the transfer tube 12 is arranged at the center of the bottom plate, and the center of the protrusion is a ball socket structure matched with the second double ball head force sensor 13. An electromagnet 15 is installed on the other side of the bottom plate. The transfer tube 12 is a tubular structure with an opening on the middle side, and its front end is provided with a fork ear forked with the pull rod 8 through the axle pin 4. The structure has a rear end that is slidably connected with the cylindrical protrusion of the adapter seat 14, a ball socket structure that forms a ball joint with the first double ball head force sensor 3 is arranged on the side, the second double ball head force sensor 13 is located in the opening of the adapter tube 12, the front end ball head and the ball socket structure arranged at the front end of the adapter tube 12 form a ball joint, and the rear end ball head and the ball socket structure of the cylindrical protrusion of the adapter seat 14 form a ball joint; the landing gear connection module 6 includes an armature 16 and an adapter 17, the adapter 17 is a plate-like structure, the armature 16 is installed on the front side, the armature 16 forms a magnetic attraction relationship with the electromagnet 15 in the separation module 5, and the rear side of the adapter 17 is provided with a connection structure that matches the aircraft landing gear joint.

Claims

1. A flexible self-detaching aircraft towing rod, characterized in that It includes a tie rod assembly, a wheel, a first double ball head force sensor, an axle pin, a disengagement module, a landing gear connection module, and a control system. The wheel is installed under the tie rod assembly. One end of the tie rod assembly is connected to the tractor, and the other end is connected to the disengagement module through the axle pin. One end of the first double ball head force sensor is connected to the side of the disengagement module, and the other end is connected to one side of the end of the tie rod assembly. The top of the disengagement module is connected to the aircraft landing gear through the landing gear connection module. When the tractor drags the aircraft landing gear through the flexible self-detachable aircraft traction rod, the turning moment safety value and the tension safety value are set through the control system. The control system reads the value of the first double ball head force sensor to calculate the real-time turning moment and reads the value of the second double ball head force sensor in the disengagement module to calculate the real-time tension. When any one of the turning moment value and the tension value exceeds the safety value, the control system The control landing gear connection module is disengaged from the disengagement module, the disengagement module includes a transfer tube, a second double ball head force sensor, an adapter seat, and an electromagnet. The adapter seat includes a base plate, a cylindrical protrusion matching the inner diameter of the transfer tube is arranged at the center of the base plate, and the center of the protrusion is a ball socket structure matching the second double ball head force sensor. An electromagnet is installed on the other side of the base plate. The transfer tube is a tubular structure with an opening on the middle side. A fork ear structure is arranged at the front end thereof forked with the pull rod through an axle pin, and a rear end is slidably connected with the cylindrical protrusion of the adapter seat, and a ball socket structure forming a ball joint with the first double ball head force sensor is arranged on the side. The second double ball head force sensor is located in the opening of the transfer tube, and the front end ball head forms a ball joint with the ball socket structure arranged at the front end of the transfer tube, and the rear end ball head forms a ball joint with the ball socket structure of the cylindrical protrusion of the adapter seat.

2. A flexible self-detaching aircraft towing rod according to claim 1, characterized in that The pull rod assembly includes a pull rod, a side plate, a ball socket, and a wheel mounting frame. The pull rod is a rod-shaped structure. The front end of the pull rod is a fork ear structure forked with the tractor, and the rear end is a fork ear structure forked with the disengagement module. The rear end of the pull rod is provided with a side plate extending to the side, and the top of the side plate is provided with a ball socket connected to the first double ball head force sensor ball, and a wheel mounting frame with an inverted "T" shape structure is provided below the pull rod.

3. A flexible self-detaching aircraft towing rod according to claim 1, characterized in that Both ends of the first double ball head force sensor are ball head structures, the axis of the first double ball head force sensor is perpendicular to the axis of the pin shaft, and the distance between the axes is the turning force arm.

4. A flexible self-detaching aircraft towing rod according to claim 1, characterized in that The landing gear connection module includes an armature and an adapter. The adapter is a plate-like structure with an armature installed on the front side. The armature forms a magnetic attraction relationship with the electromagnet in the disengagement module. A connection structure matching the aircraft landing gear joint is arranged on the rear side of the adapter.

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