All-electric-drive multifunctional rodless aircraft tractor

Abstract

The utility model discloses an all-electric drive multifunctional rodless aircraft tractor, which belongs to the technical field of aircraft traction equipment and comprises a tractor body, a wheel holding mechanism and a control system, the wheel holding mechanism used for pressing front wheels of an aircraft is arranged on the tractor body, and the wheel holding mechanism is electrically connected with the control system. The baffle abuts against the front wheel of the airplane, the baffle is disassembled and assembled according to the diameter of the front wheel of the airplane, the tire pressing rod tightly presses the front wheel of the airplane, the tire pressing rod can be disassembled and assembled according to the front wheels of the airplane with different sizes, the front wheel of the airplane can be effectively prevented from jumping up and down in the traction process, and it is guaranteed that the front wheel of the airplane is tightly attached to the front wheel of the airplane. The oversteering protection device has an oversteering protection function and can effectively prevent an undercarriage from being sprained due to an overlarge steering angle in the airplane traction process. When the tractor turns, the front wheels of the airplane apply different pressures on the inner and outer sides of the wheel holding mechanism, and the supporting main body plate deflects left and right relative to the cross beam, so that the airplane is kept in a normal state and is dragged by the tractor.

Description

Technical Field

[0001] The utility model belongs to the technical field of aircraft towing equipment, and in particular relates to a fully electric driven multifunctional rodless aircraft towing vehicle. Background Art

[0002] With the development of the aviation industry, the demand for aircraft tugs with higher efficiency, flexibility, and safety continues to increase. This has led to the emergence of electric towbarless aircraft tugs. These tugs utilize an advanced wheel-clamping design, which achieves towing by clamping onto the aircraft's wheels, eliminating the need for a towbar. This significantly reduces ground towing preparation time and improves towing efficiency. Furthermore, electric drive is more environmentally friendly and quieter than traditional fuel-powered systems, reducing noise and exhaust pollution on the airport ground, in line with the development philosophy of modern green airports.

[0003] In the prior art, a Chinese utility model patent with publication number CN221776047U discloses an aircraft tractor, comprising: a frame having an installation space with an opening on one side; a wheel-holding mechanism arranged in the installation space, comprising a fixing frame, a pushing assembly, a clamping assembly and a barrier assembly; the fixing frame having an operating space with an opening on one side; the barrier assembly being arranged on the fixing frame for opening and closing the operating space; the pushing assembly being arranged on the fixing frame and being movable horizontally along the fixing frame in the operating space; the pushing assembly and the barrier assembly cooperating with each other for lifting the front nose wheel of the aircraft; the clamping assembly being arranged on the pushing assembly for clamping the lifted front nose wheel of the aircraft; a lifting mechanism for driving the wheel-holding mechanism to move up and down in the installation space; the pushing assembly, the barrier assembly and the clamping assembly cooperating with each other for clamping the front nose wheel of the aircraft, thereby achieving stable clamping of the front nose wheel of the aircraft, and effectively preventing the front nose wheel of the aircraft from bouncing and disengaging from the wheel-holding mechanism during the towing process.

[0004] The existing technology has the following problems: the existing tractors do not have an adaptive left and right yaw function. When the towbarless tractor drives the aircraft's front landing gear to turn together, the inner wheel of the turn exerts a large pressure on the inner side of the towbarless tractor's wheel holding mechanism, while the outer wheel exerts a small pressure. The two wheels of the aircraft's front landing gear are unbalanced. At this time, it is necessary to adjust the left and right yaw of the tractor wheel box itself to keep the aircraft in a normal state of passive traction to prevent damage to the aircraft. The existing tractors do not have an oversteering protection function. When the towbarless tractor is towing an aircraft, it is easy for the towing steering angle to be too large and the landing gear to be twisted. Utility Model Content

[0005] The technical problem to be solved by the present invention is to overcome the shortcomings of the above-mentioned prior art and provide a fully electric driven multifunctional rodless aircraft tractor.

[0006] The technical solution adopted to solve the above technical problems is: a fully electric driven multifunctional rodless aircraft tractor, including a vehicle body, a wheel holding mechanism and a control system. The wheel holding mechanism for pressing the front wheels of the aircraft is arranged on the vehicle body, and the wheel holding mechanism is electrically connected to the control system; the vehicle body is: universal wheels are respectively arranged at the bottom of both sides of the front end of the frame, and driving wheels are respectively arranged at the bottom of both sides of the rear end of the frame, and the driving wheels are driven by driving wheel motors; the wheel holding mechanism is: the vehicle body is rotatably connected to the first axle pin on the supporting main plate through a first axle pin sleeve, the front end of the supporting main plate is rotatably connected to the crossbeam through a second pin shaft, a baffle for blocking the movement of the front wheels of the aircraft is detachably arranged on the supporting main plate, arc-shaped support rods are respectively arranged on both sides of the supporting main plate, and the two arc-shaped support rods are detachably connected. A tire pressing rod for tightening the front wheel of the aircraft is provided, a door opening electric cylinder is provided on one side of the rear end of the supporting main body plate, the output end of the door opening electric cylinder is fixedly connected to the second shaft pin sleeve, a first fixed shaft is provided on the supporting main body plate, a connecting plate is rotatably installed on the first fixed shaft, the connecting plate is fixedly connected to one side of the main body plate door, a third pin shaft rotatably connected to the second shaft pin sleeve is provided on the connecting plate, a door locking electric cylinder is provided on the other side of the rear end of the supporting main body plate, the output end of the door locking electric cylinder is fixedly connected to the third shaft pin sleeve, a second fixed shaft is provided on the supporting main body plate, a buckle plate is rotatably installed on the second fixed shaft, a fourth pin shaft rotatably connected to the third shaft pin sleeve is provided on the buckle plate, a buckle column engaged with the buckle plate is provided on the other side of the main body plate door, the door locking electric cylinder and the door opening electric cylinder are electrically connected to the control system respectively.

[0007] Furthermore, laser radars are respectively provided on both sides of the front end of the frame.

[0008] Furthermore, a battery for providing power to the tractor is provided inside the vehicle frame, and an upper cover plate located above the battery is provided on the vehicle frame.

[0009] Furthermore, a traction ring is provided at the front end of the frame.

[0010] Furthermore, a pin sensor is provided on the first pin collar, the pin sensor is electrically connected to the control system, and the control system is electrically connected to the drive wheel motor.

[0011] Furthermore, the frame is respectively provided with lifting electric cylinders located at both ends of the crossbeam, the lifting electric cylinders are electrically connected to the control system, the output end of each lifting electric cylinder is respectively rotatably connected to one end of the first connecting rod, the other end of each first connecting rod is respectively rotatably connected to one end of the second connecting rod, and each second connecting rod is respectively rotatably connected to one end of the crossbeam.

[0012] The beneficial effects of the present invention are as follows: (1) The present invention adopts a baffle that contacts the front wheel of the aircraft. The baffle is disassembled and assembled according to the diameter of the front wheel of the aircraft. The tire pressing rod presses the front wheel of the aircraft. The tire pressing rod can be disassembled and assembled according to the front wheels of the aircraft of different sizes, which can effectively prevent the front wheel of the aircraft from jumping up and down during the traction process and ensure a close fit with the front wheel of the aircraft.

[0013] (2) The vehicle body of the present invention is rotatably connected to the first axle pin on the supporting main body plate through an axle pin collar. When the tractor turns, the force change trend of the pin sensor on the axle pin collar is increasing at one end and decreasing at the other end. As the turning angle increases, the difference of the pin sensor becomes larger and larger. When the difference corresponding to the set maximum turning angle is reached, a signal is sent to the control system to limit the drive wheel motor so that it can no longer increase the turning angle. It has an oversteering protection function and can effectively prevent the landing gear from being twisted due to excessive steering angle during the towing process. At the same time, when approaching an obstacle, the control system sends a signal to control the drive wheel motor to stop and activate the emergency automatic braking function. At this time, the tractor stops immediately to ensure the safety of the aircraft.

[0014] (3) The driving wheel motor of the utility model controls the precise movement of the tractor, so that the tractor can be moved safely and reliably in a narrow space.

[0015] (4) The front end of the support main plate of the utility model is rotatably connected to the crossbeam through the second pin shaft. When the tractor turns, the front wheels of the aircraft exert different pressures on the inside and outside of the wheel holding mechanism. At this time, the support main plate will swing left and right relative to the crossbeam itself, so that the aircraft can remain in a normal state when towed by the tractor, avoiding the situation where the front wheels of the aircraft cannot effectively contact the wheel holding mechanism and cause damage to the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 The utility model is a structural schematic diagram of an embodiment of a fully electric drive multifunctional rodless aircraft tractor.

[0017] Figure 2 It is a structural diagram of the vehicle body.

[0018] Figure 3 This is a schematic diagram of the bottom structure of the vehicle body.

[0019] Figure 4 It is a structural diagram of the wheel holding mechanism.

[0020] Figure 5 yes Figure 4 Schematic diagram of the structure from another angle.

[0021] Figure 6 It is a schematic diagram of the connection structure of the door opening electric cylinder, connecting plate and main panel door.

[0022] Figure 7 This is a schematic diagram of the connection structure of the door locking electric cylinder, buckle plate, buckle column and main panel door.

[0023] Reference numerals: 1, vehicle body; 101, vehicle frame; 102, universal wheel; 103, driving wheel; 104, upper cover; 105, laser radar; 106, traction ring; 2, wheel holding mechanism; 201, supporting main plate; 202, crossbeam; 203, baffle; 204, main plate door; 205, tire pressure rod; 206, first connecting rod; 207, buckle plate; 208, first axle pin ring; 209, lifting Lifting cylinder; 210, second connecting rod; 211, door locking cylinder; 212, door opening cylinder; 213, connecting plate; 214, arc-shaped support rod; 215, second pin shaft; 216, second shaft pin collar; 217, third pin shaft; 218, first fixed shaft; 219, second fixed shaft; 220, buckle column; 221, fourth pin shaft; 222, third shaft pin collar; 3. control system; 4. aircraft front wheel. DETAILED DESCRIPTION

[0024] In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.

[0025] like Figure 1 As shown, the all-electrically driven multifunctional towbarless aircraft tractor of this embodiment includes a vehicle body 1 , a wheel-holding mechanism 2 , and a control system 3 .

[0026] A wheel holding mechanism 2 for clamping the front wheel 4 of the aircraft is provided on the vehicle body 1 , and the wheel holding mechanism 2 is electrically connected to the control system 3 .

[0027] like Figures 2 to 3 As shown, the vehicle body 1 is composed of a vehicle frame 101, a universal wheel 102, a driving wheel 103, an upper cover 104, a laser radar 105, and a traction ring 106.

[0028] The vehicle body 1 comprises a frame 101 with universal wheels 102 mounted on either side of the front bottom. Drive wheels 103 are mounted on either side of the rear bottom. These are driven by a drive wheel motor, controlling the precise movement of the tractor, enabling safe and reliable towing in confined spaces. The drive wheel motor is equipped with a manual brake release mechanism. Laser radars 105 are mounted on either side of the front end of the frame 101, generating an alarm when the tractor approaches an obstacle. A battery is housed within the frame 101 to power the tractor, and an upper cover 104 is located above the battery. A towing eye 106 is located at the front end of the frame 101. In the event of a power outage or equipment failure, the aircraft's front wheels 4 can be manually and quickly released, allowing the aircraft to be quickly towed away from the airport.

[0029] like Figures 4 to 7 As shown, the wheel holding mechanism 2 is composed of a supporting main plate 201, a cross beam 202, a baffle 203, a main plate door 204, a tire pressing rod 205, a first connecting rod 206, a buckle plate 207, a first axle pin collar 208, a lifting electric cylinder 209, a second connecting rod 210, a door locking electric cylinder 211, a door opening electric cylinder 212, a connecting plate 213, an arc-shaped support rod 214, a second pin shaft 215, a second axle pin collar 216, a third pin shaft 217, a first fixed shaft 218, a second fixed shaft 219, a buckle column 220, a fourth pin shaft 221, and a third axle pin collar 222.

[0030] The wheel-holding mechanism 2 is as follows: the vehicle body 1 is rotatably connected to the first axle pin on the supporting main plate 201 through the first axle pin collar 208, and a pin sensor is provided on the first axle pin collar 208, and the pin sensor is electrically connected to the control system 3, and the control system 3 is electrically connected to the drive wheel motor. When the tractor turns, the force change trend of the pin sensor is to increase at one end and decrease at the other end. As the turning angle increases, the difference of the pin sensor becomes larger and larger. When the difference corresponding to the set maximum turning angle is reached, a signal will be sent to the control system 3 to limit the drive wheel motor so that it can no longer increase the turning angle. At the same time, when approaching an obstacle, the control system 3 sends a signal to control the drive wheel motor to stop and start the emergency automatic braking function. At this time, the tractor stops immediately.

[0031] The control system 3 is electrically connected to the lifting electric cylinder 209 , the door locking electric cylinder 211 , and the door opening electric cylinder 212 respectively. The control system 3 adopts the existing technology, and the control system 3 controls the opening and closing of the lifting electric cylinder 209 , the door locking electric cylinder 211 , and the door opening electric cylinder 212 .

[0032] The front end of the support plate 201 is rotatably connected to the crossbeam 202 via a second pin 215. When the tractor turns, the aircraft's front wheels 4 exert different pressures on the inside and outside of the wheel-holding mechanism 2. At this time, the support plate 201 will swing left and right relative to the crossbeam 202 itself, allowing the aircraft to remain in a normal state for towing by the tractor. Lifting electric cylinders 209 are respectively provided on both sides of the frame 101, located at both ends of the crossbeam 202. The lifting electric cylinders 209 have a mechanical self-locking function. The output end of each lifting electric cylinder 209 is respectively rotatably connected to one end of the first connecting rod 206. The other end of each first connecting rod 206 is respectively rotatably connected to one end of the second connecting rod 210. Each second connecting rod 210 is respectively rotatably connected to one end of the crossbeam 202.

[0033] A baffle 203 for blocking the movement of the aircraft's front wheel 4 is detachably provided on the support main body plate 201. The baffle 203 is disassembled and assembled according to the diameter of the aircraft's front wheel 4. Arc-shaped support rods 214 are respectively provided on both sides of the support main body plate 201. A tire pressing rod 205 for pressing the aircraft's front wheel 4 is detachably provided between the two arc-shaped support rods 214. The tire pressing rod 205 can adapt to aircraft's front wheels 4 of different sizes, and can effectively prevent the aircraft's front wheel 4 from jumping up and down during the traction process, ensuring a close fit with the aircraft's front wheel 4.

[0034] A door opening electric cylinder 212 is provided on one side of the rear end of the support main body plate 201, and the output end of the door opening electric cylinder 212 is fixedly connected to the second shaft pin ring 216. A first fixed shaft 218 is provided on the support main body plate 201, and a connecting plate 213 is rotatably installed on the first fixed shaft 218. The connecting plate 213 is fixedly connected to one side of the main body plate door 204, and a third pin shaft 217 rotatably connected to the second shaft pin ring 216 is provided on the connecting plate 213. A door locking electric cylinder 211 is provided on the other side of the rear end of the support main body plate 201, and the output end of the door locking electric cylinder 211 is fixedly connected to the second shaft pin ring 216. The third shaft pin ring 222 is fixedly connected, and a second fixed shaft 219 is provided on the supporting main body plate 201, and a buckle plate 207 is rotatably installed on the second fixed shaft 219. The buckle plate 207 is provided with a fourth pin shaft 221 rotatably connected to the third shaft pin ring 222. A buckle column 220 is provided on the other side of the main body panel door 204, which is clamped with the buckle plate 207. The door locking electric cylinder 211 and the door opening electric cylinder 212 are electrically connected to the control system 3 respectively to complete the door opening and locking actions of the wheel holding mechanism 2. The door locking electric cylinder 211 and the door opening electric cylinder 212 have a mechanical self-locking function.

[0035] The working principle of this embodiment is as follows: turn on the power switch on the vehicle body 1, and control the control system 3 through a single-person wireless remote control. The control system 3 controls the driving wheel motor to drive the rodless tractor to move, so that the rodless tractor travels close to the front wheel 4 of the aircraft, and the wheel holding mechanism 2 is aligned with the front landing gear of the aircraft. The baffle 203 and the tire pressing rod 205 are adjusted to the appropriate position, and the door locking electric cylinder 211 drives the buckle plate 207 to move to separate from the buckle column 220 of the main panel door 204, and the buckle plate 207 rotates on the second fixed shaft 219. The door opening electric cylinder 212 drives the main panel door 204 to open through the connecting plate 213, and the connecting plate 213 rotates on the first fixed shaft 218, aligning the center line of the tractor with the front wheel 4 of the aircraft until the baffle 203 touches the aircraft. The front wheel 4 and the door opening electric cylinder 212 drive the main panel door 204 to be closed through the connecting plate 213, and the door locking electric cylinder 211 drives the buckle plate 207 to move to engage with the buckle column 220 of the main panel door 204. The control system 3 controls the lifting electric cylinder 209 to start, and drives the supporting main panel 201 to be lifted through the output end of the lifting electric cylinder 209 in sequence through the first connecting rod 206, the second connecting rod 210, and the crossbeam 202. After it is lifted to the highest position, the tractor can tow the aircraft normally. After the tractor drives to the predetermined position, the wheel holding mechanism 2 descends, and the main panel door 204 is opened. After the rodless tractor is operated to drive away a certain distance, the main panel door 204 is closed, the buckle plate 207 is locked with the main panel door 204, and the wheel holding mechanism 2 is lifted to the highest position and then drives away from the scene.

[0036] When the tractor towing the aircraft breaks down or runs out of power and needs to be disengaged from the aircraft's front wheel 4, the manual emergency operation method of the tractor is as follows: the staff uses an Allen wrench to simultaneously rotate the manual emergency device at the tail of the lifting cylinder 209, and the wheel holding mechanism 2 slowly descends. When the wheel holding mechanism 2 descends to the lowest position, the manual emergency devices at the tail of the door locking cylinder 211 and the door opening cylinder 212 are rotated in sequence to unlock and open the door, and the towing ring 106 at the front end of the vehicle body 1 is used to connect with the trailer to quickly leave the aircraft area, and then the manual emergency devices at the tail of the door locking cylinder 211, the door opening cylinder 212 and the lifting cylinder 209 are rotated in sequence to close the door, lock and lift.

[0037] The above description is merely a preferred embodiment of the present invention and is not intended to limit the scope of protection of the present invention.

Claims

1. A fully electric multifunctional towbarless aircraft tractor, characterized by: The invention comprises a vehicle body (1), a wheel-holding mechanism (2), and a control system (3); the wheel-holding mechanism (2) for pressing the front wheel (4) of an aircraft is provided on the vehicle body (1); the wheel-holding mechanism (2) is electrically connected to the control system (3); The vehicle body (1) is provided with universal wheels (102) at the bottom of both sides of the front end of the vehicle frame (101), and driving wheels (103) at the bottom of both sides of the rear end of the vehicle frame (101), and the driving wheels (103) are driven by a driving wheel motor. The wheel holding mechanism (2) is as follows: the vehicle body (1) is rotatably connected to the first axle pin on the support main plate (201) through the first axle pin ring (208); the front end of the support main plate (201) is rotatably connected to the crossbeam (202) through the second pin shaft (215); a baffle (203) for blocking the movement of the aircraft front wheel (4) is detachably provided on the support main plate (201); arc-shaped support rods (214) are respectively provided on both sides of the support main plate (201); a tire pressing rod (205) for pressing the aircraft front wheel (4) is detachably provided between the two arc-shaped support rods (214); a door opening electric cylinder (212) is provided on one side of the rear end of the support main plate (201); the output end of the door opening electric cylinder (212) is fixedly connected to the second axle pin ring (216); a first fixed shaft (218) is provided on the support main plate (201); A connecting plate (213) is rotatably mounted, the connecting plate (213) being fixedly connected to one side of the main panel door (204), a third pin shaft (217) rotatably connected to a second shaft pin collar (216) being provided on the connecting plate (213), a door locking electric cylinder (211) being provided on the other side of the rear end of the supporting main panel (201), an output end of the door locking electric cylinder (211) being fixedly connected to the third shaft pin collar (222), a second fixed shaft (219) being provided on the supporting main panel (201), a pinch plate (207) being rotatably mounted on the second fixed shaft (219), a fourth pin shaft (221) being rotatably connected to the third shaft pin collar (222) being provided on the pinch plate (207), a pinch column (220) being clamped to the pinch plate (207) being provided on the other side of the main panel door (204), the door locking electric cylinder (211) and the door opening electric cylinder (212) being electrically connected to the control system (3) respectively.

2. The all-electric multifunctional towbarless aircraft tractor according to claim 1, characterized in that: Laser radars (105) are respectively provided on both sides of the front end of the vehicle frame (101).

3. The all-electric multifunctional towbarless aircraft tractor according to claim 1, characterized in that: A battery for providing power to the tractor is arranged inside the vehicle frame (101), and an upper cover plate (104) located above the battery is arranged on the vehicle frame (101).

4. The all-electric multifunctional towbarless aircraft tractor according to claim 1, characterized in that: The front end of the vehicle frame (101) is provided with a traction ring (106).

5. The all-electric multifunctional towbarless aircraft tractor according to claim 1, characterized in that: A pin sensor is provided on the first pin collar (208), the pin sensor is electrically connected to the control system (3), and the control system (3) is electrically connected to the drive wheel motor.

6. The all-electric multifunctional towbarless aircraft tractor according to claim 1, characterized in that: The vehicle frame (101) is provided with lifting electric cylinders (209) at both ends of the crossbeam (202) on both sides, and the lifting electric cylinders (209) are electrically connected to the control system (3). The output end of each lifting electric cylinder (209) is respectively rotatably connected to one end of the first connecting rod (206), and the other end of each first connecting rod (206) is respectively rotatably connected to one end of the second connecting rod (210), and each second connecting rod (210) is respectively rotatably connected to one end of the crossbeam (202).

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