Air-land-water flight vehicle

Abstract

The present invention relates to an air-land-water flight vehicle. Within a main frame, the front and rear ends of an upper frame are provided with propeller compartments for placement of folding propeller assemblies, a parachute compartment being provided between the folding propeller compartments; the front section of a lower frame is provided with a control cabin for piloting and loading of passengers and cargo, two sides of the middle rear section of the lower frame are provided with wing compartments for placement of retractable folding wing assemblies, two rear sides of the rear section of the lower frame are respectively provided with storage compartments, an integrated compartment being provided between the storage compartments, and a balloon compartment for placement of a balloon deployment and retraction system is provided below the middle of the lower frame; the folding propeller assemblies are mounted on the main frame, the retractable folding wing assemblies are symmetrically mounted on two sides at the rear of the main frame by means of connecting structures, and traveling wheels are provided below the main frame. The air-land-water fight vehicle has a compact structure, can travel and park on land and water and can perform vertical take-off and landing on land and water, and can change the form in mid-air; the flight vehicle is an electric flight vehicle that maintains long endurance with a certain payload, and ensures safe flight.

Description

A type of amphibious and air-to-ground aircraft Technical Field

[0001] This invention belongs to the field of aircraft technology, specifically relating to an amphibious and airborne aircraft. Background Technology

[0002] Currently, with social development, people have increasingly higher needs for transportation tools for travel and cargo transport. Existing cars and airplanes cannot meet some personalized needs, including the ability to drive and park on roads and water, take off and land vertically on roads and water, and have a certain payload and long endurance in the air. Existing aircraft such as fixed-wing aircraft, helicopters with huge propellers, gyroplanes, flying cars (enlarged versions of drones), and tiltrotor helicopters cannot meet these requirements. Therefore, this invention designs a multifunctional aircraft. Summary of the Invention

[0003] The purpose of this invention is to provide an amphibious and air-to-ground aircraft in order to avoid the shortcomings of the prior art.

[0004] To achieve the above objectives, the technical solution adopted by the present invention is as follows: a amphibious and air-to-ground aircraft, characterized in that: the main support is divided into an upper frame and a lower frame; the upper frame has symmetrically arranged propeller compartments at both ends for mounting folding propeller assemblies, with the mounting point located at one corner inside the propeller compartment; a parachute compartment for mounting parachute assemblies is located between the folding propeller compartments; the lower frame has a control room at the front for piloting and passenger / cargo transport; wing compartments for mounting retractable folding wing assemblies are symmetrically arranged on the two sides of the middle and rear section of the lower frame; storage compartments are respectively arranged on the two rear sides of the rear section of the lower frame; a combined compartment is arranged between the two storage compartments; an airbag compartment for mounting an airbag deployment and retraction system is located in the middle of the lower frame; folding propeller assemblies are respectively mounted at the four corners of the upper main support; retractable folding wing assemblies providing lift are symmetrically mounted on both sides of the rear of the main support through a connecting structure; a wing propeller is mounted at the front end of the retractable folding wing assembly; and wheels are provided under the main support.

[0005] The folding propeller assembly structure is as follows: a main boom is hinged to the main support, a servo motor is connected at the hinge, multiple shaft tubes parallel to the main boom are installed on the outer periphery of the end of the main boom, connecting shafts are respectively sleeved on the shaft tubes, the connecting shafts are vertically connected to the secondary boom, the servo motor is connected at the vertical connection, and motors are fixedly installed at the top and bottom of the end of the secondary boom, and the output shaft of the motor drives the propeller blades.

[0006] The connection structure is as follows: parallel connecting plates are vertically installed on the main support, with a certain distance between the two connecting plates; a connecting piece is fixed on the telescopic folding wing assembly; one end of each of the two connecting plates is hinged to the main support, and the other end is hinged to the end of the connecting piece; one end of the first hydraulic cylinder is hinged to the main support, and the other end is hinged to the middle of one side of the connecting piece; one end of the second hydraulic cylinder is hinged to the hinge point between the connecting plate and the connecting piece, and the other end is hinged to the main support between the two connecting plates.

[0007] The airbag deployment system consists of four hollow support rods installed at the four corners of the bottom of the main support frame. The hollow support rods are fixed by a fixed tube shaft and are connected to the fixed tube shaft. The axis of the hollow support rod is at a 45-degree angle to the axis of the fixed tube shaft. The two ends of the fixed tube shaft are hinged to the main support frame by stabilizing bushings. A swing arm is also connected to the fixed tube shaft. The swing arm is hinged to the linkage rod of the third hydraulic cylinder. The third hydraulic cylinder is hinged in the middle of the bottom of the main support frame. The outer end of the hollow support rod is connected to the airbag through the deployment wheel structure. The airbag consists of multiple small airbags, which are arranged in a fan shape around the deployment wheel structure.

[0008] The retractable wheel structure consists of an inner shaft tube fitted inside an outer shaft tube, with a sealing plate installed at the end of the inner shaft tube. Both ends of the outer shaft tube are fixedly connected to retaining rings. The end of a hollow support rod is connected and fixed to the inner shaft tube. A reduction motor is installed inside the inner shaft tube, and the output shaft of the reduction motor meshes with a gear ring connected to the end of the outer shaft tube. Multiple small holes are opened on the wall of the inner shaft tube, with flexible hoses connected to the inner ends of these holes. The flexible hoses pass through the hollow support rod to the fixed shaft and then out to connect to an air nozzle in the integrated chamber. Ventilation channels corresponding to the small holes are opened on the wall of the outer shaft tube. Inflation holes are opened at different locations on the outer shaft tube wall, and these inflation holes communicate with small airbags.

[0009] The integrated room is equipped with two slot tracks running in the front-to-back direction of the aircraft. The trolley is mounted on the slot tracks via track wheels at its bottom. Multiple servo motors are linked to the track wheels. The forward and reverse rotation of the servo motors drives the trolley to slide back and forth, thereby adjusting the horizontal balance of the aircraft. The battery assembly that provides power to the aircraft is installed on the trolley.

[0010] The top surface of the folding propeller compartment is equipped with an automatically opening and closing top cover; the top surface of the parachute compartment is embedded with a parachute chamber cover; the outer side of the wing compartment is equipped with a sliding side door that opens and closes; the airbag chamber has a bottom door that opens downwards; the control room has a windshield window at one end of the control room body, and multiple side doors are provided on both sides of the control room; the rear of the integrated room has an automatic rear door, and the integrated room houses the hydraulic system assembly, aerodynamic system assembly, power system, battery, software, control linkage, and balance linkage for controlling and operating the aircraft.

[0011] The top cover has four hinged support rods at the four corners of its back. The other end of each support rod is hinged to the main support and connected to the first servo motor. The first servo motor drives the support rods to swing, thereby moving the top cover to open and close.

[0012] The wing compartment has parallel slide rails installed on its upper and lower sides. The sliding side door has pulleys on its upper and lower sides respectively. An inner slide rail and its matching inner pulley are installed horizontally in the middle of the inner side of the sliding side door. The pulleys and inner pulleys are driven by a geared motor. The sliding side door moves along the slide rails and inner slide rails to open and close the wing compartment.

[0013] The beneficial effects of this invention are: it has a compact structure, can travel and park on land and water, can take off and land vertically on land and water, can transform in the air, and is an electric aircraft with a certain load capacity, long endurance, and safe flight. It is in a retracted state when traveling and parking on the ground, in a semi-deployed state when traveling and parking on water, in a semi-deployed state when preparing for takeoff and landing, in a deployed state when hovering and flying, and in a fully deployed state during emergency landings. Attached Figure Description

[0014] Figure 1 is a right view of the ground where the present invention is parked;

[0015] Figure 2 is a schematic diagram of the opening of the top cover of the folding propeller storage compartment and the side door of the telescopic folding wing storage compartment of the present invention.

[0016] Figure 3 is a right view of the present invention in its water surface parking state;

[0017] Figure 4 is a top view of the vertical takeoff and landing states of the present invention;

[0018] Figure 5 is a front view of the vertical takeoff and landing states of the present invention.

[0019] Figure 6 is a right view of the vertical takeoff and landing states of the present invention;

[0020] Figure 7 is a top view of the present invention in level flight state;

[0021] Figure 8 is a right view of the present invention in level flight state;

[0022] Figure 9 is a bottom view of the airbag of the present invention in the deployed state;

[0023] Figure 10 is a schematic diagram of the retractable and extendable wheel structure of the present invention;

[0024] In the diagram: 1-Main support frame, 2-Propeller compartment; 21-Top cover, 22-Support rod, 23-First servo motor, 3-Parachute compartment, 4-Wing compartment, 41-Sliding side door, 42-Slide rail, 43-Pulley, 44-Inner slide rail, 45-Inner pulley; 5-Airbag chamber, 6-Folding propeller assembly, 61-Main boom, 62-Shaft tube, 63-Secondary boom, 64-Connecting shaft, 65-Motor, 66-Propeller blade; 7-Retractable folding wing assembly, 71-Connecting plate, 72-First hydraulic cylinder, 73-Second hydraulic cylinder, 74-Wing propeller, 75-Connector; 8-Airbag deployment and retraction system 80-Airbag, 801-Small airbag, 81-Hollow support rod, 82-Fixed tube shaft, 83-Stabilizing bushing, 84-Swing arm, 85-Linkage rod, 86-Third hydraulic cylinder; M-Retracting and extending wheel mechanism, M1-Stop ring, M2-Outer shaft tube, M3-Inner shaft tube, M4-Small hole, M5-Ventilation ring channel, M6-Hose, M7-Reduction motor, M8-Output shaft, M9-Gear, M10-Gear ring, M11-Sealing plate, M12-Inflation hole; 9-Comprehensive compartment, 91-Slotted track, 92-Trolley, 93-Track wheel; 10-Walking wheel, 11-Control room, 12-Storage room. Detailed Implementation

[0025] As shown in Figures 1-10, a land-sea-air aircraft is characterized by: a main support frame 1 consisting of an upper frame and a lower frame; the upper frame has symmetrically arranged propeller compartments 2 at its front and rear ends for mounting folding propeller assemblies 6, with the mounting point located at one corner inside the propeller compartment 2; a parachute compartment 3 for mounting a parachute assembly is located between the folding propeller compartments 2; the lower frame has a control room 11 at its front for piloting and passenger / cargo transport; wing compartments 4 symmetrically arranged on the two sides of the middle and rear section of the lower frame for mounting telescopic folding wing assemblies 7; storage compartments 12 are respectively arranged on the two rear sides of the rear section of the lower frame; a combined room 9 is arranged between the two storage compartments 12; and an airbag compartment 5 for mounting an airbag deployment system 8 is located in the middle of the lower frame; folding propeller assemblies 6 are respectively mounted at the four corners of the main support frame 1; telescopic folding wing assemblies 7 providing lift are symmetrically mounted on both sides of the rear of the main support frame 1 via connecting structures; a wing-propeller 74 is mounted at the front end of the telescopic folding wing assembly 7; and wheels 10 are provided under the main support frame 1.

[0026] The folding propeller assembly 6 is specifically structured as follows: a main boom 61 is hinged to the main support 1, and a servo motor is connected at the hinge. Multiple shaft tubes 62 parallel to the main boom 61 are installed on the outer periphery of the end of the main boom 61. Connecting shafts 64 are respectively sleeved on the shaft tubes 62. The connecting shafts 64 are vertically connected to the secondary boom 63, and a servo motor is connected at the vertical connection. Motors 65 are fixedly installed at the upper and lower ends of the secondary boom 63, and the output shafts of the motors 65 drive the propeller blades 66.

[0027] Parallel connecting plates 71 are vertically mounted on the main support 1, with a certain distance between the two connecting plates 71. A connecting piece 75 is fixed on the telescopic folding wing assembly 7. One end of each of the two connecting plates 71 is hinged to the main support 1, and the other end is hinged to the end of the connecting piece 75. One end of the first hydraulic cylinder 72 is hinged to the main support 1, and the other end is hinged to the middle of one side of the connecting piece 75. One end of the second hydraulic cylinder 73 is hinged to the hinge point between the connecting plate 71 and the connecting piece 75, and the other end is hinged to the main support 1 between the two connecting plates 71.

[0028] The airbag deployment system 8: Hollow support rods 81 are installed at the four corners of the bottom of the main support 1. The hollow support rods 81 are fixed by and pass through the fixed tube shaft 82. The axis of the hollow support rods 81 is about 45 degrees from the axis of the fixed tube shaft 82. The two ends of the fixed tube shaft 82 are hinged to the main support 1 by the stabilizing bushings 83. The fixed tube shaft 82 is also connected to the swing arm 84. The swing arm 84 is hinged to the linkage rod 85 of the third hydraulic cylinder 86. The third hydraulic cylinder 86 is hinged in the middle of the bottom of the main support 1. The outer end of the hollow support rods 81 is connected to the airbag 80 through the deployment wheel structure M. The airbag 80 is composed of multiple small airbags 801. The small airbags 801 are arranged in a fan shape around the deployment wheel structure M.

[0029] The take-up and release wheel structure M consists of an inner shaft tube M3 fitted inside an outer shaft tube M2, a sealing plate M11 installed at the end of the inner shaft tube M3, retaining rings M1 fixedly connected to both ends of the outer shaft tube M2, the end of the hollow support rod 81 being connected and fixed to the inner shaft tube M3, a reduction motor M7 installed inside the inner shaft tube M3, and the output shaft M8 of the reduction motor M7 meshing with a gear ring M10 connected to the end of the outer shaft tube M2.

[0030] The inner shaft tube M3 has multiple small holes M4 on its wall. The inner end of the small hole M4 is connected to a flexible hose M6. The flexible hose M6 passes through the hollow support rod 81 to reach the fixed tube shaft 82 and then passes through it to connect with the air nozzle in the integrated chamber 9. The outer shaft tube M2 has ventilation channels M5 that are connected to the small holes M4. The ventilation channels M5 have inflation holes M12 at different positions on the outer shaft tube M2 wall. The inflation holes M12 are connected to the small airbag 801.

[0031] The integrated room 9 is equipped with two slot tracks 91 running in the front-to-back direction of the aircraft. The trolley 92 is mounted on the slot tracks 91 via track wheels 93 at its bottom. Multiple servo motors are linked to the track wheels 93. The forward and reverse rotation of the servo motors drives the trolley 92 to slide back and forth, thereby adjusting the horizontal balance of the aircraft. The battery assembly that provides power to the aircraft is installed on the trolley 92.

[0032] The top surface of the folding propeller compartment 2 is provided with an automatically opening and closing top cover 21; the top surface of the parachute compartment 3 is embedded with a parachute chamber cover; the outer side of the wing compartment 4 is provided with a sliding side door 41 that opens and closes; the airbag chamber 5 has a bottom door that opens downwards; the control room 11 is provided with a windshield window at the end of the chamber body, and multiple side doors are provided on both sides of the control room 11; the rear of the integrated room 9 has an automatic rear door, and the integrated room 9 houses the hydraulic system assembly, aerodynamic system assembly, power system, battery, software, control linkage, and balance linkage for controlling and operating the aircraft.

[0033] The top cover 21 is hinged to four corners on the back of the top cover 21, and the other end of the support rod 22 is hinged to the main bracket 1 and connected to the first servo motor 23. The first servo motor 23 drives the support rod 22 to swing, thereby moving the top cover 21 to realize the opening and closing of the top cover 21.

[0034] The wing compartment 4 has parallel slide rails 42 installed on its upper and lower sides respectively. The sliding side door 41 has pulleys 43 on its upper and lower sides respectively. The inner slide rail 44 and its matching inner pulley 45 are horizontally installed in the middle of the inner side of the sliding side door 41. The pulleys 43 and the inner pulleys 45 are driven by a geared motor. The sliding side door 41 moves along the slide rails 42 and the inner slide rails 44 to open and close the wing compartment 4.

[0035] I. Working process of each component:

[0036] 1. Working process of the folding propeller assembly:

[0037] Upon receiving the command to extend, the top covers 21 of the two propeller compartments 2 respond sequentially. The first servo motor 23, connected to the support rod 22, responds, causing the top covers 21 to move open, creating space. The servos on the main boom 61 and secondary boom 63 of the folding propeller assembly 6 respond, causing them to swing and twist, thus extending the propeller compartments 2 of the folding propeller assembly 6 and distributing them around the main support 1. The propeller blades 66 on the folding propeller assembly 6 are symmetrically stacked vertically and rotate freely on the horizontal plane. Subsequently, the top covers 21 retract and return to their original position.

[0038] When the folding propeller assembly 6 needs to be retracted and reset, it is the reverse of the above-described unfolding process.

[0039] 2. Working process of the telescopic folding wing assembly 7:

[0040] Upon receiving the command, both retractable folding wing assemblies 7 operate simultaneously. First, the sliding side doors 41 of both wing bays 4 respond simultaneously. The servo motors on the sliding side doors 41, which are linked to pulleys 43, start and drive the pulleys 43 to rotate, simultaneously causing the sliding side doors 41 to slide open. Then, the retractable folding wings, driven by the linkage mechanism, move out of their respective wing bays 4, extend out of the main support 1, and move around to stand upright on both sides of the middle section of the main support 1. The sliding side doors 41 then close. When the aircraft ascends vertically to a safe altitude, the retractable folding wings receive the command again and begin to operate. First, they level off, then unfold, and the wing propellers 74 start to accelerate and rotate, and the aircraft begins to fly horizontally. When the aircraft receives the command to prepare for vertical landing, the retractable folding wing assemblies 7 complete the process in reverse order.

[0041] 3. Airbag inflation process:

[0042] When the aircraft is in flight, the airbag 80 is in the retracted state. At this time, the hollow support rod 81 is close to the bottom of the main support 1, the retraction wheel mechanism M is placed in the airbag chamber 5, and the airbag 80 is wrapped around the outer shaft tube M2. When the aircraft receives the opening command, the two third hydraulic cylinders 86 work simultaneously, and the linkage rod 85 and the swing arm 84 are linked together, causing the hollow support rod 81 and the airbag 80 to swing downward and to both sides, while the airbag 80 inflates.

[0043] Upon receiving the retraction command, there are two scenarios: First, the airbag 80 supports the aircraft as it floats on the water. When the aircraft takes off from the water and receives the retraction command, the deployment process is completed in reverse. Second, the airbag 80 contacts the ground to cushion the landing, providing a soft landing for the aircraft. In this case, the airbag 80 cannot automatically retract.

[0044] 4. The parachute's closing process:

[0045] Upon receiving the command, the parachute assembly rapidly ejects from parachute compartment 3, soars into the air, and quickly deploys. The parachute does not retract automatically; it must be manually handled after the aircraft lands.

[0046] II. Implementation Process of Various Models

[0047] 1. Ground parking mode:

[0048] With the wheels 10 on the ground, the aircraft is in a retracted state. All doors in all compartments except the control room 11 are closed. At this time, the telescopic folding wing assembly 7 is retracted and placed upright in the wing compartment 4, the folding propeller assembly 6 is retracted in the propeller compartment 2, the airbag 80 and the airbag deployment system are retracted in the airbag compartment 5 under the main support 1, and the emergency parachute is in a dormant state and is placed in the parachute compartment 3.

[0049] 2. Ground vertical takeoff mode:

[0050] At this point, the aircraft is stationary on the ground, with the wheels 10 in contact with the ground. The pilot issues the takeoff command, and the two sliding side doors 41 of the two wing bays 4 simultaneously slide open. The retractable folding wings move out of their respective wing bays 4, extend from the main support 1, and move around to stand upright on both sides of the middle section of the main support. Subsequently, the sliding side doors 41 return to their original positions and close. At the same time, the top cover 21 of the propeller bay 2 opens sequentially, and the four sets of folding propeller assemblies 6 extend and unfold sequentially, providing rotation space for the propeller blades 66 around the four corners of the upper part of the main support 1. Afterwards, the top cover 21 resets and closes. Immediately afterwards, the propellers start and rotate rapidly, generating sufficient lift to vertically lift the aircraft to a safe hovering altitude. Simultaneously, the trolley 92 inside the control room 9 slides back and forth on command, adjusting the aircraft's balance. Then, the two retractable folding wings extend horizontally in opposite directions symmetrically. The wing propellers 74 at the leading edges of the retractable folding wings start and rotate rapidly under the drive of their motors, pulling the aircraft horizontally. The multiple propeller blades 66 gradually stop rotating, and the aircraft is in level flight. When the aircraft needs to turn in the air, commands are used to control the speed difference (i.e., the thrust difference) between the two wing propellers 74, thus forcing the aircraft to turn.

[0051] 3. Ground vertical descent mode:

[0052] After receiving the landing command, the folding propellers restart to generate enough lift to keep the aircraft in the air. The wing propellers 74 stop rotating, and the aircraft gradually transitions from level flight to hovering. Subsequently, the retractable folding wings 7 retract and droop, and the four sets of folding propellers that provide lift automatically adjust their speeds. The aircraft slowly and vertically descends to the ground. Then, the folding propellers stop rotating and automatically fold back into the propeller bay 2, and the retractable folding wings retract into the wing bay 4, completing the flight.

[0053] 4. Vertical takeoff mode from water surface:

[0054] The aircraft transitions from water surface mode to flight mode. At this point, the aircraft is stationary on the water surface. The airbags 80, driven by the airbag deployment system 8, unfold and extend from under the main support 1, inflating and floating on the water surface to support the aircraft. The pilot controls the aircraft, inputs the destination, and issues a takeoff command. The retractable and folding wings simultaneously move out from their respective wing bays 4, extending out of the main support 1 and moving around to stand upright on both sides of the middle section of the main support. Subsequently, the sliding side doors 41 return to their original positions and close. At the same time, the top cover 21 of the propeller bay 2 opens sequentially, and the four sets of folding propeller assemblies 6 extend and unfold sequentially, providing rotation space for the propeller blades 66 around the four corners of the upper part of the main support 1. Then, the top cover 21 closes again, and the propellers start and rotate rapidly to generate sufficient lift to vertically lift the aircraft to a safe altitude and hover. Simultaneously, the trolley 92 in the control room 9 slides back and forth on command to adjust the aircraft's balance. Subsequently, the airbag 80 deflates and the airbag retraction system 8 retracts into the support chamber 5. The telescopic folding wings are stretched horizontally in opposite directions, and the wing propeller 74 starts to rotate, pulling the aircraft into horizontal flight. As the aircraft's level flight speed increases, when the lift generated by the telescopic folding wings is sufficient to lift the aircraft, the folding propeller stops rotating, and the aircraft enters level flight.

[0055] 5. Vertical descent mode:

[0056] When the aircraft receives a command to descend vertically onto the water during flight, the folding propeller restarts to generate sufficient lift to keep the aircraft suspended in the air. The wing propeller 74 stops rotating, and the aircraft gradually transitions from level flight to hovering. The retractable folding wing retracts and droops, and the airbag 80 unfolds and inflates with the airbag deployment system 8. The folding propeller automatically adjusts its speed, and the aircraft slowly descends vertically onto the water. Afterward, the folding propeller stops rotating and automatically folds back into the propeller compartment 2, and the retractable folding wing retracts into the wing compartment 4, completing the flight.

[0057] 6. In-flight mode:

[0058] When the aircraft is level in the air and turning, the rotation speed of the two propellers 74 is changed to create a speed difference, which makes the thrust of the two propellers unequal and thus changes the direction of the aircraft's flight. When pitching, the trolley 92 installed in the integrated room 9 is controlled by the command to slide back and forth, adjust the aircraft's front and rear balance, and make the aircraft pitch back and forth.

[0059] 7. In emergency landing mode:

[0060] When an aircraft is flying in the air and an emergency landing is required, the airbag 80 will quickly deploy and inflate upon receiving the emergency landing command. The parachute will then pop out from the parachute compartment 3 at the top center of the main support 1. The parachute will pull the aircraft down slowly, allowing it to land on the ground or on the water. The aircraft will then land safely.

Claims

1. An amphibious aerial vehicle, characterized by: The main support (1) is divided into two layers of upper layer and lower layer, the upper layer is symmetrically provided with propeller warehouses (2) for installing and placing folding propeller assemblies (6) at the front and rear ends, and a parachute warehouse (3) for placing a parachute assembly is arranged between the folding propeller warehouses (2); the front section of the lower layer is provided with a control room (11) for driving control and carrying passengers and goods, the middle and rear sections of the lower layer are symmetrically provided with wing warehouses (4) for placing telescopic folding wing assemblies (7) on the two sides, the rear sections of the lower layer are respectively provided with storage rooms (12) on the two side rear surfaces, a comprehensive room (9) is arranged between the two storage rooms (12), and a gasbag room (5) for placing a gasbag folding system (8) is arranged in the middle of the lower surface of the main support (1); folding propeller assemblies (6) are respectively arranged on the four corners of the upper surface of the main support (1); telescopic folding wing assemblies (7) for providing lifting force are symmetrically arranged on the two sides of the rear surface of the main support (1) through a connecting structure, and wing propellers (74) are arranged at the front ends of the telescopic folding wing assemblies (7); walking wheels (10) are arranged on the lower surface of the main support (1); The gasbag folding system (8) comprises: hollow support rods (81) arranged at four corners of the bottom of the main support (1), the hollow support rods (81) are fixed to and penetrate through fixed shafts (82), the axis of the hollow support rod (81) is at an angle of 45 degrees with the axis of the fixed shaft (82), the two ends of the fixed shaft (82) are hingedly connected to the main support (1) through stabilizing shaft sleeves (83), the fixed shaft (82) is further connected to a swing arm (84), the swing arm (84) is hingedly connected to a linkage rod (85) of a third hydraulic cylinder (86), the third hydraulic cylinder (86) is hingedly connected to the middle of the bottom of the main support (1), the outer end of the hollow support rod (81) is connected to a gasbag (80) through a folding wheel structure (M), and the gasbag (80) is composed of a plurality of small gasbags (801) which are arranged in a fan shape around the folding wheel structure (M). The folding wheel structure (M) comprises: an outer shaft tube (M2) sleeved with an inner shaft tube (M3), a sealing plate (M11) arranged at the end of the inner shaft tube (M3), a ratchet ring (M1) fixedly connected to the two ends of the outer shaft tube (M2), the end of the hollow support rod (81) is fixedly connected to the inner shaft tube (M3), a speed reducer motor (M7) is arranged in the inner shaft tube (M3), the output shaft (M8) of the speed reducer motor (M7) is engaged with a gear ring (M10) connected to the end of the outer shaft tube (M2), a plurality of small holes (M4) are formed in the wall of the inner shaft tube (M3), the inner end of the small hole (M4) is connected to a hose (M6), the hose (M6) penetrates into the hollow support rod (81) and reaches the fixed shaft (82) and penetrates out of the fixed shaft (82) to be connected to an air nozzle in the comprehensive room (9), and air circulation channels (M5) corresponding to the small holes (M4) are formed in the wall of the outer shaft tube (M2), inflation holes (M12) are formed in different positions of the wall of the outer shaft tube (M2), and the inflation holes (M12) are communicated with the small gasbags (801).

2. An amphibious aerial vehicle as claimed in claim 1, characterized in that: The folding propeller assembly (6) is characterized in that a main arm rod (61) is hingedly connected to the main support (1), a rudder is connected to the hinge, a plurality of shaft tubes (62) parallel to the main arm rod (61) are mounted on the outer periphery of the end of the main arm rod (61), a connecting shaft (64) is respectively connected to the shaft tubes (62), a sub-arm rod (63) is perpendicularly connected to the connecting shaft (64), a rudder is connected to the perpendicular connection, a motor (65) is respectively fixedly mounted on the upper and lower ends of the sub-arm rod (63), and the output shaft of the motor (65) drives a propeller blade (66).

3. An amphibious aerial vehicle as claimed in claim 1, wherein: The connecting structure is characterized in that parallel connecting plates (71) are vertically mounted on the main support (1), the two connecting plates (71) are spaced apart by a certain distance, a connecting piece (75) is fixedly connected to the folding and retractable wing assembly (7), one end of each of the two connecting plates (71) is hingedly connected to the main support (1), and the other end is hingedly connected to the end of the connecting piece (75); one end of a first hydraulic cylinder (72) is hingedly connected to the main support (1), and the other end is hingedly connected to the middle of one side of the connecting piece (75); one end of a second hydraulic cylinder (73) is hingedly connected to the hinge point of the connecting plate (71) and the connecting piece (75), and the other end is hingedly connected to the main support (1) between the two connecting plates (71).

4. An amphibious aerial vehicle as claimed in claim 1, characterized in that: The comprehensive room (9) is provided with two clamping groove tracks (91) along the front and rear directions of the aircraft, a trolley (92) is arranged on the clamping groove tracks (91) through track wheels (93) at the bottom of the trolley (92), a plurality of servo motors are connected to the track wheels (93), the servo motors are reversibly driven to drive the trolley (92) to slide forward and backward, so as to adjust the horizontal balance of the aircraft, and a battery assembly for providing electric energy for the aircraft is mounted on the trolley (92).

5. An amphibious aerial vehicle as claimed in claim 1, characterized in that: The folding propeller compartment (2) is provided with a top cover (21) capable of being automatically opened and closed on the top surface; the landing parachute compartment (3) is embedded with a landing parachute compartment cover on the top surface; the wing compartment (4) is provided with a sliding side door (41) capable of being slidably opened and closed on the outer side; the airbag compartment (5) is provided with a bottom door opening downward, the control room (11) is provided with a windshield window at the end of the room body, and a plurality of side doors are arranged on both sides of the control room (11); the comprehensive room (9) is provided with an automatic back door at the back, and the comprehensive room (9) is internally provided with a hydraulic system assembly, a pneumatic system assembly, a power system, a battery, a software part, a control linkage part and a balance linkage part for controlling and operating the aircraft.

6. An amphibious aerial vehicle as claimed in claim 5, characterized in that: The top cover (21) is hingedly connected with a support rod (22) at four corners on the back, the other end of the support rod (22) is hingedly connected to the main support (1) and connected to a first rudder (23), the first rudder (23) drives the support rod (22) to swing, and then drives the top cover (21) to move, so as to realize the opening and closing of the top cover (21).

7. An amphibious aerial vehicle as claimed in claim 5, wherein: The wing compartment (4) is respectively provided with parallel slideways (42) on the upper and lower sides of the side surface, the sliding side door (41) is respectively provided with pulleys (43) on the upper and lower sides, an inner slideway (44) and a matching inner pulley (45) are horizontally mounted on the inner side of the sliding side door (41), the pulleys (43) and the inner pulley (45) are respectively driven by reduction motors, and the sliding side door (41) is moved along the slideways (42) and the inner slideway (44) to realize the opening and closing of the wing compartment (4).

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