Inclined low-height-limit transportation truss for overall transportation of airplane

Abstract

The utility model provides an inclined low-height-limit transportation truss for overall transportation of an aircraft, and belongs to the technical field of transportation of aircrafts. The fuselage installation support comprises a connecting support installed on the base, the length direction of the connecting support is arranged in the front-back direction perpendicular to the transport vehicle, and butt joint matching frames are arranged at the two ends of the connecting support and used for being fixedly connected with wing inserting grooves reserved in the positions of engines on the two sides of a fuselage after aircraft wings are detached; the connecting bracket and the fuselage of the airplane are arranged at intervals; the wing fixing frame is mounted on the base and used for fixing wings separated from a fuselage of the aircraft; the connecting line of the butt joint matching frames at the two ends of the connecting support and the point positions where the aircraft body is in butt joint is a first connecting line, and the first connecting line is obliquely arranged on the horizontal plane. By means of the processing scheme, road occupation during aircraft transportation is reduced, and meanwhile the aircraft transportation efficiency is improved.

Description

Technical Field

[0001] The present application relates to the field of transport aircraft, and in particular to an oblique low-limit height transport truss for integrally transporting aircraft. Background Art

[0002] When using vehicles to transfer aircraft on the ground, due to the size and shape of the aircraft, during the transportation process, the aircraft occupies the road, affecting the passage of ordinary vehicles. It is also not easy for the aircraft to pass through locations with restricted width and height, such as toll stations, ramps and bridge tunnels, resulting in slower aircraft transportation efficiency. Utility Model Content

[0003] In view of this, the present application provides an inclined low-height-limit transport truss for overall transportation of an aircraft, which solves the problems in the prior art and transports the aircraft in an inclined state, thereby reducing road occupancy during aircraft transportation and improving the efficiency of aircraft transportation.

[0004] The present application provides an aircraft integral transport oblique low-limit height transport truss adopts the following technical solution:

[0005] An oblique low-limit height transport truss for integrally transporting an aircraft, comprising:

[0006] A base, used for mounting on the carriage of a transport vehicle;

[0007] A fuselage mounting bracket, comprising a connecting bracket mounted on a base, wherein the length direction of the connecting bracket is arranged perpendicular to the front-rear direction of the transport vehicle, and both ends of the connecting bracket are provided with docking matching frames, wherein the docking matching frames are used to be fixedly connected to wing slots reserved at the engines on both sides of the fuselage after the wings of the aircraft are disassembled, and the connecting bracket and the fuselage of the aircraft are arranged at intervals;

[0008] A wing fixing frame, mounted on the base, the wing fixing frame is used to fix the wing separated from the fuselage of the aircraft;

[0009] The connecting line of the points where the docking matching frames at both ends of the connecting bracket are used to dock with the fuselage of the aircraft is the first connecting line, and the first connecting line is arranged obliquely in the horizontal plane.

[0010] Optionally, with the direction on the pallet toward the front of the vehicle as the front, the center of the first connecting line and the center in the width direction of the transport vehicle are offset, the center of the line of the point where the docking cooperation frame is used to dock with the aircraft fuselage is biased toward the right side of the transport vehicle, and the right side of the fuselage mounting frame is lower than the left side.

[0011] Optionally, a direction on the carriage of the transport vehicle that is perpendicular to the direction in which the transport vehicle travels is a first direction, a fuselage support frame is provided on the base, a bottom of the fuselage support frame is connected to the base, an inclined mounting plate is provided on the top of the fuselage support frame, and the mounting plate is inclined relative to a horizontal plane in the first direction;

[0012] The connecting bracket includes two parallel beams, the beams are parallel to the first connecting line, the two beams and the middle parts of the beams are connected by a plurality of spaced connecting beams, a docking plate is provided in the middle part of the beam in the length direction, and the docking plate and the mounting plate are detachably connected.

[0013] Optionally, the docking frame includes a connecting section, a transition section and a matching section, the connecting section and the matching section are spaced apart in a direction perpendicular to the docking plate, the connecting section includes two connecting rods for docking with the two beams respectively, the matching section includes two docking rods, the docking rods, the beams and the connecting rods are parallel to each other, and the docking rods and the connecting rods are connected via the transition section;

[0014] An open slot is provided at one end of the docking rod away from the transition section, and a plug hole is provided at one end of the docking rod close to the transition section. The plug hole and the open slot are used for the positioning pin in the wing slot to pass through, so that the docking rod and the wing slot are matched and fixed;

[0015] Wherein, when the docking rod and the wing slot are matched and fixed, the crossbeam, transition section and connecting rod are all spaced apart from the outer surface of the aircraft.

[0016] Both ends of the crossbeam are provided with sleeves that slide along the length direction of the crossbeam, one end of the sleeve is used to be sleeved on the outer periphery of the end of the crossbeam, and the other end of the sleeve is used to be sleeved on the outer periphery of the end of the connecting rod, and the sleeve is fixedly connected to the crossbeam and the connecting rod through bolts;

[0017] A hanging plate is provided at the position where the matching section and the transition section are connected, and a hanging ear hole is provided on the hanging plate.

[0018] Optionally, the inclination angle of the first connecting line relative to the horizontal plane is 20-40 degrees.

[0019] Optionally, the wing fixing frame includes a mating slot corresponding to the wing, the opening of the mating slot faces upward, and in a plane projection perpendicular to the traveling direction of the transport vehicle, the mating slot is located below the left side docking mating frame on the left and left sides of the crossbeam.

[0020] Optionally, the oblique low-height-limited transport truss for transporting the entire aircraft also includes a nose support frame and a tail support frame, wherein the nose support frame is mounted on a base, and the bottom of the nose support frame is used to support the nose of the aircraft, and the tail support frame is mounted on a base, and the bottom of the nose support frame is used to support the tail of the aircraft, and the nose support frame and the tail support frame are distributed in sequence from the front to the rear of the transport vehicle.

[0021] Optionally, the nose support frame and the tail support frame both include a support structure and a matching block, the bottom end of the support structure is fixedly connected to the base, the top of the support structure is provided with a support plate, and the matching block is detachably mounted on the support plate, the top surface of the matching block of the nose support frame is an arc-shaped groove for matching with the nose surface of the aircraft, and the top surface of the matching block of the tail support frame is an arc-shaped groove for matching with the tail surface of the aircraft.

[0022] In summary, this application includes the following beneficial technical effects:

[0023] This application is aimed at aircraft that connect the engine and wing through a locating pin shaft. It only needs to disassemble the wing, and then the fuselage is tiltedly installed on the transport vehicle through the fuselage mounting bracket to reduce the size of the fuselage in the width and height directions, and control the overall height of the transport vehicle and the aircraft within 5 meters. Finally, the disassembled wing is fixed separately through the wing fixing frame to achieve the transportation of the fuselage and the wing on one transport vehicle. In addition, this application uses the fuselage mounting bracket and the wing slot for cooperation. Except for the docking point on the fuselage mounting frame that contacts the aircraft, there is a gap between the other positions and the fuselage. The shell below the fuselage does not contact the fuselage mounting frame, which avoids the problems of scratches and damage caused by the stress on the fuselage shell. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0025] Figure 1 This is a schematic diagram of the overall structure of the oblique low-limit height transport truss for overall transport of aircraft in this application;

[0026] Figure 2 This is a structural schematic diagram of another angle of view of the oblique low-limit height transport truss for overall transport of the aircraft in this application;

[0027] Figure 3 This is a schematic diagram of the structure of the base, fuselage support frame, wing fixing frame, nose support frame and tail support frame of this application;

[0028] Figure 4 This is a schematic diagram of the overall structure of the fuselage mounting bracket of this application;

[0029] Figure 5 This is a schematic diagram of the structure of the matching block of this application.

[0030] Explanation of the reference numerals: 1. base; 11. fuselage support frame; 12. mounting plate; 2. fuselage mounting bracket; 21. connecting bracket; 211. cross beam; 212. docking plate; 213. sleeve; 22. docking matching frame; 221. connecting rod; 222. docking rod; 223. transition section; 224. opening slot; 225. socket; 226. lifting plate; 227. lifting ear hole; 3. wing fixing frame; 31. matching slot; 4. nose support frame; 5. tail support frame; 6. support plate; 7. matching block; 71. arc groove; 8. drag plate. DETAILED DESCRIPTION

[0031] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0032] The following describes the implementation methods of the present application through specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the contents disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific implementation methods, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, in the absence of conflict, the following embodiments and the features in the embodiments can be combined with each other. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without making creative work belong to the scope of protection of the present application.

[0033] It should be noted that various aspects of the embodiments within the scope of the appended claims are described below. It should be apparent that the aspects described herein can be embodied in a wide variety of forms, and any specific structure and / or function described herein is merely illustrative. Based on the present application, it should be understood by those skilled in the art that an aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number of aspects described herein can be used to implement the device and / or practice the method. In addition, other structures and / or functionalities other than one or more of the aspects described herein can be used to implement this device and / or practice this method.

[0034] It should also be noted that the illustrations provided in the following embodiments are only schematic illustrations of the basic concept of the present application. The drawings only show components related to the present application rather than being drawn according to the number, shape and size of components in actual implementation. In actual implementation, the type, quantity and proportion of each component may be changed arbitrarily, and the component layout may also be more complicated.

[0035] Additionally, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects described may be practiced without these specific details.

[0036] An embodiment of the present application provides an oblique low-height-limited transport truss for integrally transporting an aircraft.

[0037] like Figure 1 and Figure 2 As shown, an oblique low-limit height transport truss for integrally transporting an aircraft comprises:

[0038] A base 1, used for mounting on a carriage 8 of a transport vehicle;

[0039] The fuselage mounting bracket 2 comprises a connecting bracket 21 mounted on the base 1, and docking frames 22 are provided at both ends of the connecting bracket 21. The docking frames 22 are used to be fixedly connected to the wing slots reserved at the engines on both sides of the fuselage after the wings of the aircraft are disassembled, and the connecting bracket 21 and the fuselage of the aircraft are spaced apart.

[0040] The wing fixing frame 3 is installed on the base 1, and the wing fixing frame 3 is used to fix the wing separated from the fuselage of the aircraft. The connecting line of the points where the docking matching frames 22 at both ends of the connecting bracket 21 are used to dock with the fuselage of the aircraft is the first connecting line, and the first connecting line is inclined in the horizontal plane.

[0041] The inclination angle of the line connecting the points where the docking frame 22 docks with the aircraft fuselage relative to the horizontal plane is 20-40 degrees. In the embodiment of the present application, the inclination angle of the line connecting the points where the docking frame 22 docks with the aircraft fuselage relative to the horizontal plane is 30 degrees.

[0042] The present application takes into account the problem of road occupation during disassembly and transportation of the aircraft, and separates the connection position of the aircraft wing and the engine. The connection structure of the wing and the engine is as follows: a plurality of rod-like structures are provided on the end surface of the wing close to the fuselage, and a plurality of connecting through holes are provided on the rod-like structure. Generally, two through holes are provided on a rod-like structure, and the axial direction of the through hole is parallel to the front and rear direction of the aircraft. A wing slot that cooperates with the wing is provided on the engine. After the rod-like structure is inserted into the wing slot of the engine, the wing and the engine are connected by passing the positioning pin shaft through the through hole, and the positioning pin shaft can be removed and installed inside the engine.

[0043] This application is aimed at aircrafts that connect the engine and wing through a locating pin shaft. It only needs to disassemble the wing, and then the fuselage is tiltedly installed on the transport vehicle through the fuselage mounting bracket 2 to reduce the size of the fuselage in the width and height directions, and control the overall height of the transport vehicle and the aircraft within 5 meters. Finally, the disassembled wing is fixed separately through the wing fixing frame 3, so that the fuselage and the wing can be transported on one transport vehicle. In addition, this application uses the fuselage mounting bracket 2 and the wing slot to cooperate. Except for the docking point on the fuselage mounting frame that contacts the aircraft, there is a gap between the other positions and the fuselage. The shell below the fuselage does not contact the fuselage mounting frame, which avoids the problems of scratches and damages caused by the stress on the fuselage shell.

[0044] Moreover, the length direction of the connecting bracket 21 is perpendicular to the front-rear direction of the transport vehicle, so that the two engines of the aircraft correspond to the left and right sides of the vehicle, that is, the front-rear direction of the aircraft is parallel to the front-rear direction of the transport vehicle, making full use of the length space of the transport vehicle.

[0045] like Figure 3 As shown, the oblique low-height-limited transport truss for transporting the entire aircraft also includes a nose support frame 4 and a tail support frame 5. The nose support frame 4 is installed on the base 1, and the bottom of the nose support frame 4 is used to support the nose of the aircraft. The tail support frame 5 is installed on the base 1, and the bottom of the nose support frame 4 is used to support the tail of the aircraft. The nose support frame 4 and the tail support frame 5 are distributed in sequence from the front to the rear of the transport vehicle.

[0046] The present application makes the nose support frame 4 correspond to the nose of the transport vehicle, so that the nose of the aircraft is directed toward the nose of the trailer 8, ensuring that the airflow direction of the fuselage is consistent with the flight state during the transportation of the aircraft.

[0047] With the direction on the pallet 8 facing the front of the vehicle as the front, the center of the first connecting line and the center in the width direction of the transport vehicle are offset, the center of the connecting line of the point where the docking frame 22 is used to dock with the aircraft fuselage is biased to the right side of the transport vehicle, and the right side of the fuselage mounting frame is lower than the left side. Considering that large trucks need to drive on the right side when transporting on the road, in order to ensure the safety of freight during long-distance transportation by trucks, the fuselage is offset to the right side so that the protruding part of the fuselage is arranged on the right side of the truck body, avoiding the left lane with dense traffic.

[0048] The direction perpendicular to the moving direction of the transport vehicle on the carriage 8 of the transport vehicle is the first direction. The base 1 is provided with a fuselage support frame 11, the bottom of the fuselage support frame 11 is connected to the base 1, and the top of the fuselage support frame 11 is provided with an inclined mounting plate 12, and the mounting plate 12 is inclined relative to the horizontal plane in the first direction; the connecting bracket 21 includes two parallel beams 211, the beams 211 are parallel to the first connecting line, the two beams 211 and the middle of the beams 211 are connected by a plurality of spaced connecting beams, and the middle of the beams 211 in the length direction is provided with a docking plate 212, and the docking plate 212 and the mounting plate 12 are detachably connected. Among them, the fuselage support frame 11 is welded to the base 1, the mounting plate 12 is welded to the top of the fuselage support frame 11, the beams 211 and the connecting beams are welded together, and the docking plate 212 is welded to the beams 211.

[0049] like Figure 4 As shown, the docking frame 22 includes a connecting section, a transition section 223 and a matching section, the connecting section and the matching section are spaced apart in a direction perpendicular to the docking plate 212, the connecting section includes two connecting rods 221 for docking with the two cross beams 211 respectively, the matching section includes two docking rods 222, the docking rods 222, the cross beams 211 and the connecting rods 221 are parallel to each other, the docking rods 222 and the connecting rods 221 are connected through the transition section 223; an open slot 224 is provided at one end of the docking rod 222 away from the transition section 223, and the docking rod 222 is close to the transition section 223. One end of the crossbeam 211 is provided with a socket 225, and the socket 225 and the open slot 224 are used for the positioning pin in the wing slot to pass through, so that the crossbeam 211 is connected. The two ends of the crossbeam 211 are provided with sleeves 213 that slide along the length direction of the crossbeam 211, one end of the sleeve 213 is used to be sleeved on the outer periphery of the end of the crossbeam 211, and the other end of the sleeve 213 is used to be sleeved on the outer periphery of the end of the connecting rod 221. The sleeve 213 is fixedly connected to the crossbeam 211 and the connecting rod 221 through bolts; the position where the matching section and the transition section are connected is provided with a hanging plate 226, and the hanging plate 226 is provided with a hanging ear hole 227. Among them, the connecting section, the transition section 223 and the matching section are connected by welding, and the hanging plate 226 is welded to the transition section 223 and the docking rod 222.

[0050] When installing the aircraft fuselage on the transport vehicle, first separate the wings and engines of the aircraft, separate the connecting rod 221 and the cross beam 211 of the docking frame 22, insert the docking rod 222 of the docking frame 22 into the engines on both sides of the aircraft, and fix the docking rod 222 and the wing slots together, then connect the cross beam 211 and the connecting rod 221 through the sleeve 213, connect the docking frame 22 and the crane through the lifting ear hole 227, use the crane to lift the aircraft fuselage and the fuselage mounting frame and move them above the base 1, match the mounting plate 12 with the docking plate 212, connect the mounting plate 12 and the docking complete , completing the connection between the fuselage mounting bracket 2 and the fuselage supporting frame 11; after the transportation is completed, the process of transferring the fuselage from the transport vehicle is as follows: connecting the docking frame 22 and the crane through the lifting ear hole 227, separating the mounting plate 12 and the docking plate 212, using the crane to lift the aircraft fuselage and the docking frame 22, lifting the fuselage and keeping the fuselage in a horizontal posture, removing the bolts of the sleeve 213 and the crossbeam 211 and the sleeve 213 and the connecting rod 221, removing the crossbeam 211, lowering the aircraft landing gear, and after the aircraft lands smoothly, removing the crane cable, and finally separating the docking rod 222 from the wing slot of the engine.

[0051] When the docking rod 222 and the wing slot are fixed together, the cross beam 211, the transition section 223 and the connecting rod 221 are all spaced apart from the outer surface of the aircraft. Specifically, the distance between the docking rod 222 and the cross beam 211 in a direction perpendicular to the mounting plate 12 is greater than the distance between the wing slot and the bottom end of the aircraft fuselage in the horizontal posture of the aircraft, and the distance between the docking rod 222 and the connecting rod 221 in a direction perpendicular to the mounting plate 12 is greater than the distance between the wing slot and the bottom end of the aircraft fuselage in the horizontal posture of the aircraft.

[0052] The wing fixing frame 3 includes a matching slot 31 corresponding to the wing, the opening of the matching slot 31 faces upward, and in the plane projection perpendicular to the moving direction of the transport vehicle, the matching slot 31 is located on the left side of the crossbeam 211 and below the left side docking matching frame 22 on the left side.

[0053] like Figure 5 As shown, the nose support frame 4 and the tail support frame 5 both include a support structure and a matching block 7, the bottom end of the support structure is fixedly connected to the base 1, the top of the support structure is provided with a support plate 6, and the matching block 7 is detachably mounted on the support plate 6, the top surface of the matching block 7 of the nose support frame 4 is an arc-shaped groove 71 for matching with the nose surface of the aircraft, and the top surface of the matching block 7 of the tail support frame 5 is an arc-shaped groove 71 for matching with the tail surface of the aircraft.

[0054] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. An oblique low-limit height transport truss for integral aircraft transport, characterized in that: include: A base (1) for mounting on a carriage (8) of a transport vehicle; A fuselage mounting bracket (2) comprises a connecting bracket (21) mounted on a base (1), wherein the length direction of the connecting bracket (21) is arranged perpendicular to the front-rear direction of the transport vehicle, and docking matching frames (22) are provided at both ends of the connecting bracket (21), wherein the docking matching frames (22) are used to be fixedly connected to wing slots reserved at the engines on both sides of the fuselage after the wings of the aircraft are disassembled, and the connecting bracket (21) and the fuselage of the aircraft are arranged at a distance; A wing fixing frame (3) is mounted on the base (1), and the wing fixing frame (3) is used to fix the wing separated from the fuselage of the aircraft; The connecting line of the points where the docking matching frames (22) at both ends of the connecting bracket (21) are docked with the fuselage of the aircraft is a first connecting line, and the first connecting line is arranged obliquely on a horizontal plane.

2. The aircraft integral transport oblique low-limit height transport truss according to claim 1, characterized in that: With the direction on the carriage (8) toward the front of the vehicle as the front, the center of the first connecting line and the center in the width direction of the transport vehicle are offset, the center of the connecting line of the point where the docking matching frame (22) is used to dock with the aircraft fuselage is biased towards the right side of the transport vehicle, and the right side of the fuselage mounting bracket (2) is lower than the left side.

3. The aircraft integral transport oblique low-limit height transport truss according to claim 1, characterized in that: A direction on the carriage (8) of the transport vehicle that is perpendicular to the direction in which the transport vehicle travels is a first direction, a fuselage support frame (11) is provided on the base (1), the bottom of the fuselage support frame (11) is connected to the base (1), an inclined mounting plate (12) is provided on the top of the fuselage support frame (11), and the mounting plate (12) is inclined relative to a horizontal plane in the first direction; The connecting bracket (21) comprises two mutually parallel crossbeams (211), the length direction of the crossbeams (211) is parallel to the first connecting line, the two crossbeams (211) and the middle part of the crossbeam (211) are connected by a plurality of spaced connecting beams, a docking plate (212) is provided in the middle part of the length direction of the crossbeam (211), and the docking plate (212) and the mounting plate (12) are detachably connected.

4. The aircraft integral transport oblique low-limit height transport truss according to claim 3, characterized in that: The docking and matching frame (22) comprises a connecting section, a transition section (223) and a matching section, wherein the connecting section and the matching section are arranged at intervals in a direction perpendicular to the docking plate (212), the connecting section comprises two connecting rods (221) for docking with the two crossbeams (211) respectively, the matching section comprises two docking rods (222), the docking rods (222), the crossbeams (211) and the connecting rods (221) are parallel to each other, and the docking rods (222) and the connecting rods (221) are connected via the transition section (223); An end of the docking rod (222) away from the transition section (223) is provided with an open slot (224), and an end of the docking rod (222) close to the transition section (223) is provided with a plug hole (225), and the plug hole (225) and the open slot (224) are used for allowing the positioning pin shaft in the wing slot to pass through, so that the docking rod (222) and the wing slot are matched and fixed; When the docking rod (222) and the wing slot are fixed in cooperation, the crossbeam (211), the transition section (223) and the connecting rod (221) are all spaced apart from the outer surface of the aircraft.

5. The aircraft integral transport oblique low-limit height transport truss according to claim 4, characterized in that: Both ends of the cross beam (211) are provided with sleeves (213) that slide along the length direction of the cross beam (211), one end of the sleeve (213) is used to be sleeved on the outer periphery of the end of the cross beam (211), and the other end of the sleeve (213) is used to be sleeved on the outer periphery of the end of the connecting rod (221), and the sleeve (213) is fixedly connected to the cross beam (211) and the connecting rod (221) by bolts; A hanging plate (226) is provided at the position where the matching section and the transition section are connected, and a hanging ear hole (227) is provided on the hanging plate (226).

6. The aircraft integral transport oblique low-limit height transport truss according to claim 1, characterized in that: The inclination angle of the first connecting line relative to the horizontal plane is 20-40 degrees.

7. The aircraft integral transport oblique low-limit height transport truss according to claim 2, characterized in that: The wing fixing frame (3) comprises a matching slot (31) corresponding to the wing, the opening of the matching slot (31) faces upward, and in a plane projection perpendicular to the moving direction of the transport vehicle, the matching slot (31) is located on the left side of the crossbeam (211) and below the left side docking matching frame (22) on the left side.

8. The aircraft integral transport oblique low-limit height transport truss according to claim 1, characterized in that: The aircraft overall transport oblique low-height limit transport truss also includes a nose support frame (4) and a tail support frame (5), wherein the nose support frame (4) is mounted on a base (1), and the bottom of the nose support frame (4) is used to support the nose of the aircraft, and the tail support frame (5) is mounted on the base (1), and the bottom of the nose support frame (4) is used to support the tail of the aircraft, and the nose support frame (4) and the tail support frame (5) are distributed in sequence from the front to the rear of the transport vehicle.

9. The aircraft integral transport oblique low-limit height transport truss according to claim 8, characterized in that: The nose support frame (4) and the tail support frame (5) both include a support structure and a matching block (7); the bottom end of the support structure is fixedly connected to the base (1); the top of the support structure is provided with a support plate (6); the matching block (7) is detachably mounted on the support plate (6); the top surface of the matching block (7) of the nose support frame (4) is an arc-shaped groove (71) for matching with the nose surface of the aircraft; the top surface of the matching block (7) of the tail support frame (5) is an arc-shaped groove (71) for matching with the tail surface of the aircraft.

Images