A portable aircraft towing apparatus incorporating boost braking

Abstract

This invention discloses a portable aircraft towing device combining booster and brake, comprising a main body with an inclined support plate on the main body and lateral support arms on both sides of the inclined support plate. Each lateral support arm includes an electric actuator and a support plate. This invention solves the problem of existing small portable aircraft booster towing devices being able to tow but not brake, while avoiding the problems of traditional heavy-duty towing vehicles being too large, having complex hydraulic lines, and being difficult to operate. Unlike the hydraulic braking method of traditional towing vehicles, this invention achieves braking of the aircraft through the friction of each set of triangular wedge-shaped structures. It is not limited to the field of aircraft ground towing but can also be applied to the towing of small aircraft or vehicles in hangars or production workshops. It has good site adaptability, is portable, has a simple and feasible solution, and is low in cost. It can realize the towing and braking of aircraft during ground transportation and has strong practicality.

Description

Technical Field

[0001] This invention relates to the field of aircraft ground transportation technology, specifically a portable aircraft towing device that combines booster braking. Background Technology

[0002] A wheel-lift aircraft towing vehicle is an airport ground device that lifts the nose landing gear tire of an aircraft, pushing or towing it to a designated position on the apron. Due to the large mass of aircraft, resulting in significant inertia, the towing vehicle must possess excellent braking performance to ensure accurate parking. Currently, most airports still use this traditional wheel-lift towing vehicle, which has two main problems: 1. Complex hydraulic piping, occupying a large space, and numerous hose and pipe joint connections lead to a high failure rate, making system troubleshooting and maintenance inconvenient. 2. The large size of the aircraft towing vehicle limits its application to large outdoor environments such as airports, resulting in poor site adaptability and difficulty in meeting the needs of applications in confined spaces, such as towing and turning small aircraft in hangars. In recent years, some smaller aircraft towing devices have been developed domestically and internationally, but these devices still suffer from the problem of only being able to push the aircraft and lacking braking capabilities. Therefore, existing equipment cannot perform these functions while maintaining a small weight, failing to meet the application requirements of multiple scenarios and exhibiting poor versatility.

[0003] Existing technologies, such as patent document CN202175201U, disclose a novel braking system for a four-wheel steering and drive aircraft towing vehicle. This technology uses a fully hydraulic braking device for the wheel-mounted aircraft towing vehicle, equipped with a brake pedal valve, a filling valve, and an accumulator, all connected by hydraulic lines. A hydraulic pump fills the accumulator through the filling valve, and the accumulator provides a relatively stable hydraulic oil source for vehicle braking. This oil is connected to the brake pedal valve in the driver's cab via pipelines, and then from the brake valve to the brake via pipelines, achieving the braking function. However, because the fully hydraulic braking device relies entirely on hydraulic pipeline connections, it has a high failure rate, is inconvenient to maintain and repair, and is expensive to maintain. Existing technologies, such as patent document CN206750172U, disclose a leverless aircraft towing vehicle wheel-mounted door opening and closing device, a lifting mechanism, and a towing vehicle. The towing vehicle includes a main frame under the vehicle, within which is an interface for connecting the wheel-mounted lifting mechanism. This interface allows the wheel-mounted lifting mechanism to be fixed inside the main frame, providing a supporting carrier for its operation. This device can control the simultaneous raising and lowering of the front and rear ends of the bracket using three sets of hydraulic cylinders, enabling the raising and lowering of the aircraft landing gear. However, the overall drive system is complex and costly. Existing technology, such as patent document CN203111918U, discloses a roller-shaped material transport device. This device can solve the problems of wasted labor and low efficiency in transporting large roller-shaped materials. Furthermore, this type of small-scale traction device can well meet the working needs of small aircraft in confined spaces. However, it can only propel the aircraft or vehicle forward and cannot brake on its own, requiring wheel chocks for assistance, making operation inconvenient.

[0004] Therefore, existing airport ground towing equipment and its usage methods have many shortcomings and need to be improved. The purpose of this invention is to solve the above problems by providing a portable aircraft towing device that combines booster braking, which can be used in limited spaces, has good portability, and can achieve braking and steering on its own. Summary of the Invention

[0005] The purpose of this invention is to provide a portable aircraft traction device that combines booster braking to solve the problems mentioned in the background art.

[0006] To achieve the above objectives, the present invention provides the following technical solution: a portable aircraft traction device combining booster and brake, comprising a device body, an inclined support plate provided on the device body, lateral support arms provided on both sides of the inclined support plate, each lateral support arm comprising an electric push rod and a support plate, a groove provided on one side of the two support plates close to each other, a front-end triangular wedge-type structural component provided on the side of the groove away from the device body, and a rear-end triangular wedge-type structural component provided on the side of the groove away from the front-end triangular wedge-type structural component, a battery provided inside the device body, and an operating push rod provided on the device body.

[0007] Preferably, the main body of the device includes a supporting shell and a cover plate. The supporting shell is provided with a battery removal slot, the cover plate is disposed on the battery removal slot, and the battery is disposed in the battery removal slot.

[0008] Preferably, the inclined support plate is disposed on the support housing, and the operating push rod is disposed on the support housing.

[0009] Preferably, the upper end of the control push rod is provided with control switch A and control switch B, and the side of the support housing is provided with a plurality of auxiliary wheels.

[0010] Preferably, the inclined support plate has two receiving slots, the electric actuator is disposed in the receiving slots, and the support plate is disposed at the end of the electric actuator.

[0011] Preferably, the front-end triangular wedge-shaped structure assembly includes an electric push rod II, a U-shaped frame I, a drive motor I, a friction roller I, and two traveling rollers I. The electric push rod II is disposed in the groove, the U-shaped frame I is disposed at the end of the electric push rod II, the drive motor I is disposed inside the U-shaped frame I, the friction roller I is rotatably disposed inside the U-shaped frame I, and the two traveling rollers I are disposed inside the U-shaped frame I, with the friction roller I located inside the two traveling rollers I.

[0012] Preferably, the diameter of the first traveling roller is smaller than the diameter of the first friction roller, and both the first traveling roller and the first drive motor are provided with a transmission wheel, and the two transmission wheels are connected by a matching belt.

[0013] Preferably, the rear triangular wedge-shaped structure assembly includes an electric push rod three, a U-shaped frame two, a drive motor two, a friction roller two, and two traveling rollers two. The electric push rod three is disposed in the groove, the U-shaped frame two is disposed at the end of the electric push rod three, the drive motor two is disposed in the U-shaped frame two, the traveling roller two is rotatably disposed in the U-shaped frame two, the two traveling rollers two are disposed in the U-shaped frame two, and the friction roller two is located inside the two traveling rollers two.

[0014] Preferably, the diameter of the second traveling roller is smaller than the diameter of the second friction roller. Both the second traveling roller and the second drive motor are equipped with a second transmission wheel. The two second transmission wheels are connected by a matching belt. The front-end triangular wedge structure assembly and the rear-end triangular wedge structure assembly have the same size specifications.

[0015] Compared with the prior art, the beneficial effects of the present invention are:

[0016] This invention utilizes the combined use of the main body of the equipment, the inclined support plate, the lateral support arm, the operating push rod, and control switch A and control switch B. It uses a storage battery to power the electric push rod to adjust its position, and uses control switch A and control switch B to control the drive motor to achieve traction. This avoids the problems of traditional heavy-duty tractors being too large, having complex hydraulic lines, and being difficult to operate.

[0017] This invention also uses the combined use of a front-end triangular wedge structure component and a rear-end triangular wedge structure component, which is different from the traditional hydraulic braking method of tractor vehicles. It achieves braking of the aircraft through the friction of each set of triangular wedge structures, and is not limited to the field of aircraft ground towing.

[0018] This invention also utilizes lateral support arms to adjust the position of the support plate according to the size and width of the aircraft wheels, making it suitable for towing small aircraft or vehicles in hangars or production workshops. It has good site adaptability, is portable, has a simple and feasible solution, and is low in cost. It can realize the towing and braking of aircraft ground transportation and is highly practical. Attached Figure Description

[0019] Figure 1 This is a first-view three-dimensional structural diagram of the present invention;

[0020] Figure 2 This is a schematic diagram of the second-view three-dimensional structure of the present invention;

[0021] Figure 3 This is a top view of the present invention;

[0022] Figure 4 This is a schematic diagram of the third-view three-dimensional structure of the present invention;

[0023] Figure 5 This is a side sectional view of the support plate in this invention;

[0024] Figure 6 This is a three-dimensional structural diagram of the support plate in this invention.

[0025] In the diagram: 1. Main body of the equipment; 101. Support shell; 102. Cover plate; 2. Inclined support plate; 3. Lateral support arm; 301. Electric push rod one; 302. Support plate; 4. Front-end triangular wedge-shaped structure assembly; 401. Electric push rod two; 402. U-shaped frame one; 403. Drive motor one; 404. Friction roller one; 405. Traveling roller one; 5. Rear-end triangular wedge-shaped structure assembly; 501. Electric push rod three; 502. U-shaped frame two; 503. Drive motor two; 504. Friction roller two; 505. Traveling roller two; 6. Battery; 7. Control push rod; 8. Control switch A; 9. Control switch B; 10. Auxiliary wheel; 11. Transmission wheel one; 12. Transmission wheel two. Implementation

[0026] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0027] Please see Figure 1-6 The present invention provides a technical solution: a portable aircraft traction device combining booster and brake, comprising a device body 1, an inclined support plate 2 is bolted to the device body 1, and lateral support arms 3 are installed on both sides of the inclined support plate 2. The lateral support arms 3 include an electric push rod 301 and a support plate 302. The two support plates 302 have grooves on their sides close to each other. A front triangular wedge-type structural component 4 is installed in the groove on the side away from the device body 1, and a rear triangular wedge-type structural component 5 is installed in the groove on the side away from the front triangular wedge-type structural component 4. A battery 6 is installed in the device body 1, and an operating push rod 7 is installed on the device body 1.

[0028] The main body of the equipment 1 includes a support shell 101 and a cover plate 102. The support shell 101 has a battery removal slot, and the cover plate 102 is installed on the battery removal slot. The battery 6 is installed in the battery removal slot. The power source of the portable aircraft towing equipment that combines booster and braking is provided by the battery. The model of the battery 6 is 6-DZM-28. The battery's working time is approximately 45 minutes. When the power is exhausted, a spare battery can be directly replaced at the work site through the battery removal slot, which is simple and easy.

[0029] The inclined support plate 2 is bolted to the support housing 101, and the control push rod 7 is mounted on the support housing 101. The mechanical structure of the whole machine uses a detachable structure design. The control push rod and the support housing 101 are connected by a simple mechanical buckle structure, which is easy to carry and its application is not limited to aircraft.

[0030] The upper end of the control lever 7 is equipped with control switch A8 and control switch B9, and several auxiliary wheels 10 are installed on the side of the support housing 101.

[0031] Two receiving slots are provided on the inclined support plate 2. The electric actuator 301 is installed in the receiving slot by bolts, and the support plate 302 is installed at the end of the electric actuator 301 by bolts.

[0032] The front-end triangular wedge-type structural component 4 includes an electric push rod 401, a U-shaped frame 402, a drive motor 403, a friction roller 404, and two traveling rollers 405. The electric push rod 401 is installed in the groove by bolts. The U-shaped frame 402 is installed at the end of the electric push rod 401. The drive motor 403 is installed in the U-shaped frame 402. The friction roller 404 is installed in the U-shaped frame 402 by bearings. The two traveling rollers 405 are installed in the U-shaped frame 402 by bearings, and the friction roller 404 is located inside the two traveling rollers 405.

[0033] The diameter of the traveling roller 405 is smaller than that of the friction roller 404. Both the traveling roller 405 and the drive motor 403 are equipped with transmission wheels 11. The two transmission wheels 11 are connected by a matching belt. The drive motor 403 is controlled by control switch A.

[0034] The rear triangular wedge-type structural assembly 5 includes an electric push rod 3 501, a U-shaped frame 2 502, a drive motor 2 503, a friction roller 2 504, and two traveling rollers 2 505. The electric push rod 3 501 is installed in the groove, the U-shaped frame 2 502 is installed at the end of the electric push rod 3 501, the drive motor 2 503 is installed in the U-shaped frame 2 502, the traveling roller 2 505 is installed in the U-shaped frame 2 502 through bearings, the two traveling rollers 2 505 are installed in the U-shaped frame 2 502 through bearings, and the friction roller 2 504 is located inside the two traveling rollers 2 505.

[0035] The diameter of the second traveling roller 505 is smaller than that of the second friction roller 504. Both the second traveling roller 505 and the second driving motor 503 are equipped with transmission wheels 12. The two transmission wheels 12 are connected by a matching belt. The front triangular wedge structure component 4 and the rear triangular wedge structure component 5 have the same size specifications. The second driving motor 503 is controlled by the control switch B.

[0036] Working principle: During use, the control switch A8 controls the front triangular wedge structure component 4, and the control switch B9 controls the rear triangular wedge structure component 5. Before the motor starts, the rear triangular wedge structure component 5 needs to be pressed tightly against the rear end of the aircraft wheel. Then, the lateral support arm 3 is adjusted along the friction wheel axis, and the spacing of the support plate 302 is adjusted so that the front triangular wedge structure component 4 is pressed tightly against the front side of the aircraft wheel, thereby realizing the subsequent traction and braking of the aircraft.

[0037] The specific operation and usage methods are as follows:

[0038] Step 1: After adjusting the position of the support plate 302 according to the size and width of the aircraft wheel, keep the position of the rear triangular wedge-type structure component 5 unchanged, so that the friction roller 2 504 is in close contact with the rear side of the aircraft wheel.

[0039] Step 2: Control the extension and retraction of the electric push rod 301 along the friction wheel axis, adjust the position of the support plate 302 to change the position and angle of the front triangular wedge structure component 4, so that the traveling roller 405 is in close contact with the front side of the aircraft wheel.

[0040] Step 3: When the aircraft towing function is activated, turn on the control switch B9. At this time, the rear triangular wedge structure component 5 is in working condition. The two drive motors 503 drive the transmission wheel 12 to rotate, which in turn drives the friction roller 504 at the apex of the triangular wedge structure to rotate. Then, by continuously applying wedge force on both sides of the rear end of the aircraft wheels, the aircraft moves forward. At this time, the control switch A8 is not turned on. The front triangular wedge structure component 4 only relies on the friction force of the aircraft's forward movement to drive the friction roller 404 below to move forward.

[0041] Step four: When the aircraft braking function is activated, disconnect the control switch B9 of the rear triangular wedge structure component 5 to cut off the driving force that propels the aircraft forward during traction; open the control switch A8, and drive the transmission wheel 11 to rotate through the reverse rotation of the two drive motors 403, which in turn drive the friction roller 404 at the apex of the triangular wedge structure to rotate in the opposite direction. This causes the direction of movement of the aircraft wheels to be opposite to the direction of movement of the front triangular wedge structure component 4. The operator pulls the control lever 7 with a little force to ensure that the front triangular wedge structure component 4 is in close contact with the wheels, thus counteracting the rotation of the aircraft wheels. When the aircraft is about to stop, reduce the speed of the friction roller 404 appropriately. At this time, since the main body of the equipment 1 is a trapezoidal cube, the entire equipment behind the aircraft wheels can act as a wheel stop, ensuring that the aircraft will not slide backward after reaching the designated position.

[0042] Step 5: When the aircraft reaches the preset position, the support plate 302 is moved outward along the friction wheel axis to change the position of the four sets of triangular wedge-type structures, thereby releasing the "wheel-holding" function of the aircraft wheels and realizing the traction and braking of the aircraft within a certain space; it has the advantages of simple structure, convenient use and good performance.

[0043] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0044] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A portable aircraft traction device combining booster and braking, comprising a main body (1), characterized in that: The main body (1) of the equipment is provided with an inclined support plate (2), and lateral support arms (3) are provided on both sides of the inclined support plate (2). The lateral support arms (3) include an electric push rod (301) and a support plate (302). The two support plates (302) are provided with a groove on one side close to each other. A front-end triangular wedge structure component (4) is provided on the side of the groove away from the main body (1). A rear-end triangular wedge structure component (5) is provided on the side of the groove away from the front-end triangular wedge structure component (4). A storage battery (6) is provided inside the main body (1). An operating push rod (7) is provided on the main body (1). The front-end triangular wedge-type structural component (4) includes an electric push rod two (401), a U-shaped frame one (402), a drive motor one (403), a friction roller one (404), and two walking rollers one (405). The electric push rod two (401) is disposed in the groove. The U-shaped frame one (402) is disposed at the end of the electric push rod two (401). The drive motor one (403) is disposed in the U-shaped frame one (402). The friction roller one (404) is rotatably disposed in the U-shaped frame one (402). The two walking rollers one (405) are disposed in the U-shaped frame one (402), and the friction roller one (404) is located inside the two walking rollers one (405). The diameter of the first walking roller (405) is smaller than the diameter of the first friction roller (404). Both the first walking roller (405) and the first drive motor (403) are provided with a transmission wheel (11). The two transmission wheels (11) are connected by a matching belt. The rear triangular wedge-type structural assembly (5) includes an electric push rod three (501), a U-shaped frame two (502), a drive motor two (503), a friction roller two (504), and two walking rollers two (505). The electric push rod three (501) is disposed in the groove. The U-shaped frame two (502) is disposed at the end of the electric push rod three (501). The drive motor two (503) is disposed inside the U-shaped frame two (502). The walking rollers two (505) are rotatably disposed inside the U-shaped frame two (502). The two walking rollers two (505) are disposed inside the U-shaped frame two (502), and the friction roller two (504) is located inside the two walking rollers two (505).

2. A portable aircraft towing apparatus incorporating boost braking according to claim 1 wherein: The main body (1) of the equipment includes a support shell (101) and a cover plate (102). The support shell (101) is provided with a battery removal slot, the cover plate (102) is provided on the battery removal slot, and the battery (6) is provided in the battery removal slot.

3. A boost-brake integrated portable aircraft towing apparatus according to claim 2, wherein: The inclined support plate (2) is mounted on the support housing (101), and the operating push rod (7) is mounted on the support housing (101).

4. A boost-brake integrated portable aircraft towing apparatus according to claim 3, wherein: The upper end of the control push rod (7) is provided with control switch A (8) and control switch B (9), and the side of the support housing (101) is provided with several auxiliary wheels (10).

5. A boost-brake integrated portable aircraft towing apparatus according to claim 4, wherein: The inclined support plate (2) has two receiving slots, the electric push rod (301) is installed in the receiving slots, and the support plate (302) is installed at the end of the electric push rod (301).

6. A boost-braking combined portable aircraft towing apparatus according to claim 1, characterized in that: The diameter of the second walking roller (505) is smaller than that of the second friction roller (504). Both the second walking roller (505) and the second drive motor (503) are equipped with a second transmission wheel (12). The two second transmission wheels (12) are connected by a matching belt. The front triangular wedge structure component (4) and the rear triangular wedge structure component (5) have the same size specifications.

Images