An aircraft ground transportation system and transportation method

Abstract

An aircraft ground transportation system and a transportation method. The transportation system includes a transport vehicle, a fixed bracket, and a mounting bracket. The fixed bracket is a steel truss structure, and its bottom is connected to the vehicle body of the transport vehicle. A liftable right support mechanism is installed on the right side of the fixed bracket, and a liftable left support mechanism is installed on the left side of the fixed bracket. The mounting bracket is also a steel truss structure. The right support mechanism of the fixed bracket is connected to the middle connection point and the right connection point of the mounting bracket, and the left support mechanism of the fixed bracket is connected to the left connection structure of the mounting bracket. By adjusting the support height of the right support mechanism or the left support mechanism of the fixed bracket, the mounting bracket can be tilted. On the surface of the mounting bracket, there are front landing gear connection joints, left landing gear connection joints, and right landing gear connection joints connected to the aircraft body.

Description

Technical Field

[0001] The present invention belongs to the technical field of transportation devices, and is an aircraft ground transportation system and transportation method. Background Art

[0002] Due to requirements such as aircraft damage repair or static tests, etc., it is necessary to transport the aircraft to a designated location far away through ground transportation. However, since the wings of a fixed-wing aircraft are not easily disassembled, the width of horizontal attitude transportation exceeds the limit and it cannot be transported through highways. The dimensions of commonly used special containers are difficult to meet the transportation requirements, and it is also impossible to pass through highway toll stations, ramps, and highway overpasses, etc. with a general trailer transportation due to the wide wings of the aircraft. The prior art transports by disassembling the fuselage and wings, and the existing transportation methods have problems such as high transportation cost, great difficulty, easy to cause additional damage to the aircraft body, and not easy to recover after disassembly. Summary of the Invention

[0003] The present invention provides an aircraft ground transportation system and transportation method, which only need to disassemble the front and main landing gears to transport the aircraft in the installed state over a long distance by road.

[0004] An aircraft ground transportation system includes a transport vehicle, a mounting bracket, and a fixed bracket. It is characterized in that the fixed bracket is a steel truss structure, the bottom of which is connected to the vehicle body of the transport vehicle. A liftable right support mechanism is installed on the right side of the fixed bracket, and a liftable left support mechanism is installed on the left side of the fixed bracket. The mounting bracket is also a steel truss structure. The right support mechanism of the fixed bracket is connected to the middle connection point and the right connection point of the mounting bracket, and the left support mechanism of the fixed bracket is connected to the left connection structure of the mounting bracket. By adjusting the support height of the right support mechanism or the left support mechanism of the fixed bracket, the mounting bracket can be tilted. On the surface of the mounting bracket, there are front landing connection joints, left landing connection joints, and right landing connection joints connected to the aircraft body.

[0005] The aircraft ground transportation system described above is characterized in that the right support mechanism of the fixed bracket includes two lift cylinders moving in the vertical direction, two fixed rotary shaft supports, two sliding struts, and two connecting tie rods. The telescopic end of the cylinder, the top of the fixed rotary shaft support, and the top of the sliding strut are respectively connected to the corresponding connection points in the middle of the mounting bracket, and both ends of the connecting tie rod are hinged to the joints at both ends of the right side of the fixed bracket and the mounting bracket.

[0006] The described aircraft ground transportation system is characterized in that the left support mechanism of the fixed bracket includes a scissor mechanism and two fixed columns. There is a lifting cross beam at the top of the scissor mechanism. The fixed columns are provided with longitudinal guide grooves with a cross-shaped cross-section, and a plurality of fixed pin holes with different heights are also provided on the fixed columns. The scissor mechanism is located between the two fixed columns. The two ends of the lifting cross beam of the scissor mechanism are cylindrical and are embedded in the longitudinal guide grooves of the fixed columns.

[0007] The described aircraft ground transportation system is characterized in that the left connection structure of the installation bracket is two protruding rigid cantilevers. A plurality of connection holes are provided on the rigid cantilevers. When connecting, the rigid cantilevers extend into the longitudinal guide grooves of the fixed columns of the left support mechanism of the fixed bracket. The rigid cantilevers and the ends of the lifting cross beam of the scissor mechanism form a cross-shaped intersection. The rigid cantilevers are supported by the ends of the lifting cross beam. The connection holes of the rigid cantilevers and the fixed pin holes on the fixed columns can be fixed by connection pins.

[0008] The described aircraft ground transportation system is characterized in that the sliding strut of the right support mechanism of the fixed bracket is an inclined strut. A sliding block with a ball socket connection is provided at the lower end of the sliding strut. The sliding block is embedded on the slide rail. The slide rail is connected to the fixed bracket. A plurality of limit holes matching the sliding block at the lower end of the sliding strut are provided on the slide rail. The locking pin of the sliding strut can limit the support height of the sliding strut through different limit holes. The top end of the sliding strut is connected to the lower connection point of the installation bracket through a ball socket structure.

[0009] The described aircraft ground transportation system is characterized in that the fixed rotating shaft support of the right support mechanism of the fixed bracket is a rigid support column, and a fork ear joint is provided at the top of the rigid support column. The fork ear joint is quickly detached and connected to the rotating shaft connected to the lower connection point of the installation bracket, and a quick detachment limit pin is provided on the fork ear joint.

[0010] The described aircraft ground transportation system is characterized in that the lifting actuating cylinder of the right support mechanism of the fixed bracket and the scissor mechanism of the left support mechanism of the fixed bracket are controlled to lift by a hydraulic system.

[0011] This application also provides an aircraft ground transportation method, which is characterized by including the following contents: 1) using the above-mentioned aircraft ground transportation system; 2) separating the front landing gear, left landing gear and right landing gear of the aircraft from the aircraft body; 3) connecting and fixing the aircraft body to the installation bracket through the front landing connection joint, left landing connection joint and right landing connection joint on the installation bracket; 4) adjusting the support heights of the right support mechanism and the left support mechanism of the fixed bracket for the installation bracket to change the transportation posture of the installation bracket and the aircraft body to adapt to the requirements of the external shape height and width of the aircraft body in different environments during aircraft ground transportation.

[0012] The described aircraft ground transportation method is characterized in that when the aircraft fuselage is installed or disassembled from the ground transportation system, the aircraft fuselage should be in a horizontal state, and the left connecting joint and the right connecting joint on the installation bracket are at the same height; in this state, the fork ear joint at the top of the fixed rotating shaft support of the lifting mechanism on the right side of the fixed bracket is connected and locked with the rotating shaft at the lower connecting point of the installation bracket through a quick-release limit pin. The horizontal state height of the aircraft is limited by the height of the fixed rotating shaft support. The hinge axis of the lifting actuator cylinder and the installation bracket is coaxial with the hinge axis of the fixed rotating shaft support and the installation bracket. The connecting tie rod of the right lifting mechanism is hinged to the joints at both ends on the right side of the installation bracket. The upper end of the sliding strut of the right lifting mechanism is connected to the lower connecting point of the installation bracket, and the lower end is connected to the sliding block. The sliding block is fixed to the slide rail through a locking pin; both ends of the lifting cross beam of the left lifting mechanism of the fixed bracket are in contact with the rigid cantilever of the installation bracket. The connecting hole of the rigid cantilever of the installation bracket is fixed to the fixed pin hole on the fixed column through a connecting pin.

[0013] The described aircraft ground transportation method is characterized in that when adjusting the height of the left support mechanism, the steps are as follows: 1) Separate the connecting tie rod of the right lifting mechanism from the joints at both ends on the right side of the installation bracket; 2) Release the locking of the lower end of the sliding strut of the right lifting mechanism and the limit hole of the slide rail by separating the locking pin; 3) Release the locking of the connecting hole of the rigid cantilever of the installation bracket and the fixed pin hole on the fixed column by separating the connecting pin; 4) Control the scissors mechanism to lift to an appropriate height position through the hydraulic system. The installation bracket rotates around the coaxial hinge axis of the lifting actuator cylinder and the installation bracket and the hinge axis of the fixed rotating shaft support and the installation bracket, so that the rigid cantilever on the left side of the installation bracket follows along the guide groove of the support column, and the left side height of the aircraft fuselage has been adjusted to an appropriate state; 5) When the left side height of the aircraft fuselage has been adjusted to an appropriate state, fix and lock the lower end of the sliding strut of the right lifting mechanism and the limit hole of the slide rail through a locking pin, and fix and lock the appropriate connecting hole on the rigid cantilever of the installation bracket and the corresponding fixed pin hole on the fixed column through a connecting pin.

[0014] The described aircraft ground transportation method is characterized in that when adjusting the height of the right support mechanism, the connecting pull rod of the right lifting mechanism is separated from the joints at both ends of the right side of the mounting bracket; 2) The locking of the lower end of the sliding strut of the right lifting mechanism with the slide rail limit hole is released by separating the locking pin; 3) The locking of the rigid cantilever connection hole of the mounting bracket with the fixed pin hole on the fixed column is released by separating the connecting pin; 4) The limit of the fork ear joint of the fixed rotating shaft support and the rotating shaft at the lower connection point of the mounting bracket is released by separating the quick-release limit pin; 5) The lifting actuator is controlled by the hydraulic system to rise to a suitable height position, so that the rigid cantilever on the left side of the mounting bracket follows along the guide groove of the support column, and the height of the right side of the aircraft body is adjusted to a suitable state; 6) When the height of the right side of the aircraft body has been adjusted to a suitable state, the lower end of the sliding strut of the right lifting mechanism is fixedly locked with the slide rail limit hole by the locking pin, and the appropriate connection hole on the rigid cantilever of the mounting bracket is fixedly locked with the corresponding fixed pin hole on the fixed column by the connecting pin.

[0015] The described aircraft ground transportation method is characterized in that when the aircraft body passes through normal road conditions through the ground transportation system, the left and right sides of the mounting bracket are adjusted to the lowest support height through the right support mechanism and the left support mechanism of the mounting bracket. In this state, the right side of the mounting bracket is higher than the left side.

[0016] The described aircraft ground transportation method is characterized in that when the aircraft body passes through an abnormal road condition checkpoint through the ground transportation system, according to the limitations of the road condition checkpoint, the left and right sides of the mounting bracket are respectively adjusted to appropriate heights through the right support mechanism and the left support mechanism of the mounting bracket to change the height and attitude of the aircraft body to pass through the road condition checkpoint. After passing through the road condition checkpoint, the aircraft body is adjusted to the height and attitude under normal road conditions for transportation.

[0017] The beneficial effects of this application are as follows: (1) The present invention can realize the transportation of the aircraft in the installed state only by removing the front and main landing gears of the aircraft, avoiding the disassembly and reinstallation work of the wings and reducing the work difficulty. (2) The present invention can adjust the tilt angle and height of the aircraft to pass through different highway toll stations, highway overpasses, etc. (3) The present invention is initially installed in the horizontal state of the aircraft, reducing the difficulty of loading and disassembling the aircraft. (4) The present invention is provided with a mechanical locking mechanism, and even if the hydraulic source of the actuator fails, it will not affect the safety of transporting the aircraft.

[0018] The following further describes this application in detail with reference to the accompanying drawings of the embodiments. Description of the Drawings

[0019] Figure 1 It is a schematic diagram of the overall structure of the aircraft ground transportation system.

[0020] Figure 2 It is a schematic diagram of the transport vehicle.

[0021] Figure 3 It is a schematic diagram of the fixed bracket structure.

[0022] Figure 4 It is a schematic diagram of the installation bracket structure.

[0023] Figure 5 It is a schematic diagram of the connection between the fixed rotation shaft support of the fixed bracket and the rotation shaft of the installation bracket.

[0024] Figure 6 It is a schematic diagram of the scissor mechanism and the lifting cross beam structure of the fixed bracket.

[0025] Figure 7 It is a schematic diagram of the connection between the upper end of the lifting actuator cylinder of the fixed bracket and the installation bracket.

[0026] Figure 8 It is a schematic diagram of the connection between the lower end of the sliding support rod of the fixed bracket and the upper slide rail on the fixed bracket.

[0027] Figure 9 It is a schematic diagram of the connection between the upper end of the sliding support rod of the fixed bracket and the installation bracket.

[0028] Figure 10 It is a schematic diagram of the connection between the rigid cantilever of the installation bracket and the fixed column.

[0029] Explanation of the reference numerals in the figure: transport vehicle 1, fixed bracket 2, installation bracket 3, left connection joint 4, right connection joint 5, front connection joint 6, fixed bracket base 21, connecting tie rod 22, fixed rotation shaft support 23, lifting actuator cylinder 24, sliding support rod 25, slide rail 26, fixed column 27, lifting cross beam 28, scissor mechanism 29, rigid cantilever 31, rotation shaft 32, lifting actuator cylinder connection joint 33, sliding support rod connection joint 34, tie rod connection joint 35, sliding support rod locking pin 201, sliding block 202, quick unloading limit pin 231, connecting pin 311. Detailed implementation method

[0030] Referring to the attached drawings, the aircraft ground transportation system of the present application includes a transport vehicle 1, a mounting bracket 3, and a fixed bracket 2. The fixed bracket 2 is a steel truss structure, and its bottom is connected to the vehicle body of the transport vehicle 1. A liftable right support mechanism is installed on the right side of the fixed bracket 2, and a liftable left support mechanism is installed on the left side of the fixed bracket. The mounting bracket 3 is also a steel truss structure. The right support mechanism of the fixed bracket 2 is connected to the middle connection point and the right connection point of the mounting bracket 3, and the left support mechanism of the fixed bracket 2 is connected to the left connection structure of the mounting bracket 3. By adjusting the support height of the right support mechanism or the left support mechanism of the fixed bracket 2, the mounting bracket 3 can be tilted. On the surface of the mounting bracket 3, there are a front landing connection joint 6, a left landing connection joint 4, and a right landing connection joint 5 connected to the aircraft fuselage.

[0031] In implementation, the right support mechanism of the fixed bracket 2 includes two lift cylinders 24 that move in the vertical direction, two fixed rotary shaft supports 23, two sliding struts 25, and two connecting tie rods 22. The telescopic end of the lift cylinder 24, the top of the fixed rotary shaft support 23, and the top of the sliding strut 25 are respectively connected to the corresponding connection points in the middle of the mounting bracket 3. The two ends of the connecting tie rod 22 are respectively hinged to the joints at both ends of the right side of the fixed bracket 2 and the mounting bracket 3.

[0032] The left support mechanism of the fixed bracket 2 includes a scissor mechanism 29 and two fixed columns 27. There is a lift cross beam 28 at the top of the scissor mechanism 29. The fixed columns 27 are provided with longitudinal guide grooves with a cross-shaped cross-section, and there are also multiple fixing pin holes with different heights on the fixed columns 27. The scissor mechanism 29 is located between the two fixed columns 27. The two ends of the lift cross beam 28 of the scissor mechanism are cylindrical and are embedded in the longitudinal guide grooves of the fixed columns 27.

[0033] The left connection structure of the mounting bracket 3 is two protruding rigid cantilevers 31. There are multiple connection holes on the rigid cantilevers 31. During connection, the rigid cantilevers 31 extend into the longitudinal guide grooves of the fixed columns 27 of the left support mechanism of the fixed bracket 2. The rigid cantilevers 31 and the ends of the lift cross beam 28 of the scissor mechanism form a cross shape. As Figure 10 shown, the rigid cantilevers 31 are supported by the ends of the lift cross beam 28, and the connection holes of the rigid cantilevers 31 and the fixing pin holes on the fixed columns can be fixed by connection pins 311.

[0034] The sliding strut 25 of the right support mechanism of the fixed bracket 2 is an inclined strut. The lower end of the sliding strut is provided with a sliding block 202 connected by a ball socket. The sliding block 202 is embedded on the slide rail 26. The slide rail 26 is connected to the fixed bracket 2. The slide rail 26 is provided with a plurality of limit holes matching the sliding block 202 at the lower end of the sliding strut 25. The sliding strut locking pin 201 can limit the support height of the sliding strut 25 through different limit holes. As Figure 8 shown, the top end of the sliding strut 25 is connected to the lower connection point of the mounting bracket 3 through a ball socket structure.

[0035] The fixed rotary shaft support 23 of the right support mechanism of the fixed bracket 2 is a rigid support column. The top of the rigid support column is provided with a fork ear joint. The fork ear joint is quickly detached and connected to the rotary shaft 32 connected to the lower connection point of the mounting bracket 3, and a quick detachment limit pin 231 is provided on the fork ear joint. As Figure 5 shown.

[0036] The lifting actuator 24 of the right support mechanism of the fixed bracket and the scissor mechanism 29 of the left support mechanism of the fixed bracket are controlled by a hydraulic system for lifting.

[0037] An aircraft ground transportation method includes the following steps: using the above-mentioned aircraft ground transportation system; separating the front landing gear, left landing gear, and right landing gear of the aircraft from the aircraft body; connecting and fixing the aircraft body to the mounting bracket 3 through the front landing connection joint 6, left landing connection joint 4, and right landing connection joint 5 on the mounting bracket 3; adjusting the support height of the right support mechanism and the left support mechanism of the fixed bracket 2 for the mounting bracket 3 to change the transportation attitude of the mounting bracket 2 and the aircraft body, so as to adapt to the requirements of the aircraft body shape height and width in different environments during aircraft ground transportation.

[0038] When installing or disassembling the aircraft body and the ground transportation system, the aircraft body should be in a horizontal state, and the left landing connection joint 4 and the right landing connection joint 5 on the mounting bracket 3 are at the same height; in this state, the fork ear joint at the top of the fixed rotary shaft support 23 of the right lifting mechanism of the fixed bracket 2 is connected and locked to the rotary shaft 32 at the lower connection point of the mounting bracket through the quick detachment limit pin 231. The height of the aircraft in the horizontal state is limited by the height of the fixed rotary shaft support 23. The hinge axis of the lifting actuator 24 and the mounting bracket 3 is coaxial with the hinge axis of the fixed rotary shaft support 23 and the mounting bracket 3. The connecting tie rod 22 of the right lifting mechanism is hinged to the joints at both ends on the right side of the mounting bracket 3. The upper end of the sliding strut 25 of the right lifting mechanism is connected to the lower connection point of the mounting bracket 3 through a sliding strut connection joint 34. The sliding strut connection joint 34 is a ball socket structure. As Figure 9As shown in the figure, the lower end of the sliding strut 25 is connected to the sliding block 202, and the sliding block 202 is fixed to the slide rail 26 through the locking pin 201; both ends of the lifting cross beam 28 of the lifting mechanism on the left side of the fixed bracket 2 are in contact with the rigid cantilever 31 of the mounting bracket 3. The connecting hole of the rigid cantilever 31 of the mounting bracket is fixed to the fixing pin hole on the fixed column 27 through the connecting pin 311. The fixed rotating shaft support 23 is the lowest support on the right side of the mounting bracket 3.

[0039] In the normal transportation state of the aircraft: After the aircraft is installed on the mounting bracket 3, remove the connecting tie rods 22 at both ends on the right side of the fixed bracket 2 and the mounting bracket 3, the connecting pin 311 between the rigid cantilever 31 of the mounting bracket and the fixed column 27, and the locking pin 201 of the sliding strut. Then, control the scissors mechanism 29 on the left side of the fixed bracket 2 to descend through the hydraulic system. After the rigid cantilever 31 of the mounting bracket 3 reaches the lowest point, install the connecting pin 311 between the rigid cantilever 31 and the fixed column 27, and the locking pin 201 of the sliding strut 201. This position is the normal state of the aircraft during ground transportation. In this state, the right side of the mounting bracket 3 is higher than the left side.

[0040] Attitude and height adjustment: When encountering abnormal road conditions such as highway toll stations or bridge openings, according to the limitations of the road conditions, adjust the left and right sides of the mounting bracket 3 to appropriate heights respectively through the right and left support mechanisms of the mounting bracket 3 to change the height and attitude of the aircraft body to pass through the road conditions. After passing through the road conditions, adjust the aircraft body to the height and attitude under normal road conditions for transportation. The adjustment steps of the right and left support mechanisms are as follows.

[0041] When adjusting the height of the left support mechanism, the steps are as follows: 1) Release the locking of the lower end of the sliding strut 25 of the right lifting mechanism and the limit hole of the slide rail 26 through the separation locking pin 201; 2) Release the locking of the connecting hole of the rigid cantilever 31 of the mounting bracket and the fixing pin hole on the fixed column 27 through the separation connecting pin 311; 3) Control the scissors mechanism 29 to lift and lower to an appropriate height position through the hydraulic system. The mounting bracket 3 rotates around the hinge axis of the coaxial lifting actuator 24 and the mounting bracket 3 and the hinge axis of the fixed rotating shaft support 23 and the mounting bracket 3, so that the rigid cantilever 31 on the left side of the mounting bracket follows along the guide groove of the fixed column 27, and the left side height of the aircraft body has been adjusted to an appropriate state; 4) When the left side height of the aircraft body has been adjusted to an appropriate state, fix and lock the lower end of the sliding strut 25 of the right lifting mechanism and the limit hole of the slide rail 26 through the locking pin 201, and fix and lock the appropriate connecting hole on the rigid cantilever 31 of the mounting bracket and the corresponding fixing pin hole on the fixed column 27 through the connecting pin.

[0042] When adjusting the height of the right support mechanism, the steps are as follows: 1) Release the locking of the lower end of the sliding strut 25 of the right lifting mechanism and the limit hole of the slide rail 26 by separating the locking pin 201; 3) Release the locking of the connecting hole of the rigid cantilever 31 of the mounting bracket and the fixed pin hole on the fixed column 27 by separating the connecting pin 311; 4) Release the limit of the fork ear joint of the fixed rotary shaft support 23 and the rotary shaft of the rotary shaft connecting joint 32 of the lower fixed rotary shaft support of the mounting bracket 3 by separating the quick-release limit pin 231; 5) Control the lifting actuator 24 to rise to the appropriate height position through the hydraulic system, so that the rigid cantilever 1 on the left side of the mounting bracket 3 follows the guide groove of the fixed column 27, and the right side height of the aircraft body is adjusted to the appropriate state; 6) When the right side height of the aircraft body has been adjusted to the appropriate state, fix and lock the lower end of the sliding strut 25 of the right lifting mechanism and the limit hole of the slide rail 26 with the locking pin 201, and fix and lock the appropriate connecting hole on the rigid cantilever 31 of the mounting bracket and the corresponding fixed pin hole on the fixed column 27 with the connecting pin 311.

Claims

1. An aircraft ground transportation system, comprising a transport vehicle, a mounting bracket, and a fixing bracket, characterized in that The fixed bracket is a steel truss structure, the bottom of which is connected to the body of the transport vehicle, a liftable right-side supporting mechanism is installed on the right side of the fixed bracket, and a liftable left-side supporting mechanism is installed on the left side of the fixed bracket. The mounting bracket is also a steel truss structure, the right-side supporting mechanism of the fixed bracket is connected to the middle connection point and the right-side connection point of the mounting bracket, and the left-side supporting mechanism of the fixed bracket is connected to the left-side connecting structure of the mounting bracket. The mounting bracket can be tilted by adjusting the supporting height of the right-side supporting mechanism or the left-side supporting mechanism of the fixed bracket, and a front connecting joint, a left connecting joint, and a right connecting joint connected to the aircraft body are provided on the surface of the mounting bracket. The right-side supporting mechanism of the fixed bracket includes two lifting actuators that move in the vertical direction, two fixed rotating shaft supports, two sliding struts, and two connecting pull rods, and the telescopic end of the actuator, the top end of the fixed rotating shaft support, and the top end of the sliding strut are respectively connected to the corresponding connecting rods in the middle of the mounting bracket. The scissor fork mechanism is located between the two fixed columns, and the two ends of the lifting beam of the scissor fork mechanism are cylindrical and embedded in the longitudinal guide grooves of the fixed columns. The sliding strut of the right support mechanism of the fixed bracket is an oblique strut, and the lower end of the sliding strut is provided with a sliding block connected with a ball and socket, and the sliding block is embedded in the slide rail, and the slide rail is connected to the fixed bracket. The slide rail is provided with a plurality of limiting holes matching the sliding block at the lower end of the sliding strut, and the sliding strut locking pin can limit the supporting height of the sliding strut through different limiting holes, and the top of the sliding strut is connected to the lower connection point of the mounting bracket through a ball and socket structure.

2. The aircraft ground transportation system according to claim 1, wherein The left side connection structure of the mounting bracket is two extended rigid cantilevers, which are provided with a plurality of connection holes. When connected, the rigid cantilever extends into the longitudinal guide groove of the fixed column of the left side support mechanism of the fixed bracket, and the rigid cantilever forms a "cross" shape with the end of the lifting beam of the scissor fork mechanism. The rigid cantilever is supported by the end of the lifting beam, and the connection hole of the rigid cantilever is fixed to the fixing pin hole on the fixed column through a connecting pin.

3. The aircraft ground transportation system according to claim 1, wherein, The fixed rotating shaft support of the right supporting mechanism of the fixed bracket is a rigid supporting column, a fork ear joint is provided on the top of the column, the fork ear joint is connected to the rotating shaft connected to the connection point below the mounting bracket by a quick-release connection, and a quick-release limit pin is provided on the fork ear joint.

4. The aircraft ground transportation system according to claim 1, characterized in that, The lifting and lowering actuator of the right support mechanism of the fixed bracket and the scissor fork mechanism of the left support mechanism of the fixed bracket are controlled by a hydraulic system.

5. An aircraft ground transportation method, characterized in that It includes the following: 1) using the aircraft ground transportation system described in any one of claims 1-4; 2) separating the nose landing gear, left landing gear, and right landing gear of the aircraft from the aircraft fuselage; 3) connecting and fixing the aircraft fuselage to the mounting bracket through the nose connection joint, left connection joint, and right connection joint on the mounting bracket; 4) adjusting the support height of the mounting bracket by adjusting the right support mechanism and the left support mechanism on the fixed bracket to change the transportation attitude of the mounting bracket and the aircraft fuselage, so as to meet the requirements of the height and width of the aircraft fuselage shape in different environments during aircraft ground transportation.

6. The aircraft ground transportation method according to claim 5, characterized in that, When installing or disassembling the aircraft fuselage from the ground transportation system, the aircraft fuselage should be in a horizontal state, and the left connection joint and the right connection joint on the mounting bracket are at the same height; in this state, the fork ear joint at the top of the fixed rotary shaft support of the right lifting mechanism of the fixed bracket is connected and locked with the rotary shaft at the lower connection point of the mounting bracket through a quick-release limit pin. The horizontal height of the aircraft is limited by the height of the fixed rotary shaft support. The hinge axis of the lifting actuator and the mounting bracket is coaxial with the hinge axis of the fixed rotary shaft support and the mounting bracket. The connecting tie rod of the right lifting mechanism is hinged to the joints at both ends on the right side of the mounting bracket. The upper end of the sliding strut of the right lifting mechanism is connected to the lower connection point of the mounting bracket, and the lower end is connected to the sliding block. The sliding block is fixed to the slide rail through a locking pin; both ends of the lifting cross beam of the left lifting mechanism of the fixed bracket are in contact with the rigid cantilever of the mounting bracket. The connection hole of the rigid cantilever of the mounting bracket is fixed to the fixed pin hole on the fixed column through a connection pin.

7. The aircraft ground transportation method according to claim 5, wherein When adjusting the height of the left support mechanism, the steps are as follows: 1) Separate the connecting tie rod of the right lifting mechanism from the joints at both ends on the right side of the mounting bracket; 2) Release the locking of the lower end of the sliding strut of the right lifting mechanism and the limit hole of the slide rail by separating the locking pin; 3) Release the locking of the connection hole of the rigid cantilever of the mounting bracket and the fixed pin hole on the fixed column by separating the connection pin; 4) Control the scissors mechanism to lift to the appropriate height position through the hydraulic system. The mounting bracket rotates around the coaxial hinge axis of the lifting actuator and the mounting bracket and the hinge axis of the fixed rotary shaft support and the mounting bracket, so that the rigid cantilever on the left side of the mounting bracket follows along the guide groove of the support column, and the left height of the aircraft fuselage has been adjusted to the appropriate state; 5) When the left height of the aircraft fuselage has been adjusted to the appropriate state, fix and lock the lower end of the sliding strut of the right lifting mechanism and the limit hole of the slide rail through a locking pin, and fix and lock the appropriate connection hole on the rigid cantilever of the mounting bracket and the corresponding fixed pin hole on the fixed column through a connection pin.

8. The aircraft ground transportation method according to claim 5, wherein, When adjusting the height of the right support mechanism, separate the connecting pull rod of the right lifting mechanism from the joints at both ends on the right side of the mounting bracket; 2) Release the locking of the lower end of the sliding strut of the right lifting mechanism and the rail limit hole by separating the locking pin; 3) Release the locking of the rigid cantilever connection hole of the mounting bracket and the fixed pin hole on the fixed column by separating the connecting pin; 4) Release the limit of the fork ear joint of the fixed rotating shaft support and the rotating shaft at the lower connection point of the mounting bracket by separating the quick-release limit pin; 5) Control the lifting actuator to rise to the appropriate height position through the hydraulic system, so that the rigid cantilever on the left side of the mounting bracket follows along the guide groove of the support column, and the right side height of the aircraft body is adjusted to the appropriate state; 6) When the right side height of the aircraft body has been adjusted to the appropriate state, fix and lock the lower end of the sliding strut of the right lifting mechanism and the rail limit hole with a locking pin, and fix and lock the appropriate connection hole on the rigid cantilever of the mounting bracket and the corresponding fixed pin hole on the fixed column with a connecting pin.

9. The aircraft ground transportation method according to claim 5, wherein When the aircraft body passes through normal road conditions via the ground transportation system, adjust both the left and right sides of the mounting bracket to the lowest support height through the right support mechanism and the left support mechanism of the mounting bracket. In this state, the right side of the mounting bracket is higher than the left side.

10. The aircraft ground transportation method according to claim 5, wherein When the aircraft body passes through an abnormal road condition checkpoint via the ground transportation system, according to the limitations of the road condition checkpoint, adjust the left and right sides of the mounting bracket to the appropriate heights respectively through the right support mechanism and the left support mechanism of the mounting bracket to change the height and attitude of the aircraft body to pass through the road condition checkpoint. After passing through the road condition checkpoint, adjust the aircraft body to the height and attitude during normal road conditions for transportation.

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