A land-water aircraft

Abstract

The present invention relates to an amphibious and airborne aircraft, wherein the main support is divided into an upper frame, and propeller compartments for placing a folding propeller assembly are provided at the front and rear ends of the upper frame, and a parachute compartment is provided between the folding propeller compartments; a control room for driving and carrying passengers and cargo is provided at the front section of the lower frame, and wing compartments for placing a telescopic folding wing assembly are provided at the two sides of the middle and rear sections of the lower frame, and storage rooms are provided at the rear of the two sides of the rear section of the lower frame, and a comprehensive room is provided between the storage rooms, and an airbag room for placing an airbag retracting and releasing system is provided in the middle below the lower frame; the folding propeller assembly is installed on the main support; the telescopic folding wing assembly is symmetrically installed on both sides behind the main support through a connecting structure, and running wheels are provided below the main support. The structure is compact, can travel and park on the ground and water, can take off and land vertically on the ground and water, can be deformed in the air, and is an electric aircraft with a certain load, long endurance, and safe flight.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft, and in particular relates to an amphibious, airborne aircraft. Background Art

[0002] At present, with the development of society, people have more and more needs for means of transportation such as travel and cargo transportation. Existing cars and airplanes cannot meet some personalized needs, including the ability to travel and park on roads and water surfaces, take off and land vertically on roads and water surfaces, and have a certain load and long endurance in the air. Existing aircraft such as fixed-wing aircraft, helicopters with huge propellers, rotorcraft, flying cars that are enlarged versions of drones, tilt-rotor helicopters, etc. cannot meet the above requirements. For this reason, the present invention designs an aircraft with multiple functions. Summary of the invention

[0003] The purpose of the present invention is to avoid the defects of the prior art and provide an amphibious and airborne aircraft.

[0004] To achieve the above-mentioned purpose, the technical solution adopted by the present invention is: an amphibious aircraft, characterized in that: a main support is divided into two layers, an upper frame and a lower frame, propeller compartments for installing and placing a folding propeller assembly are symmetrically arranged at the front and rear ends of the upper frame, and the installation point is arranged at a corner in the propeller compartment, and a parachute compartment for placing a parachute assembly is arranged between the folding propeller compartments; a control room for driving and carrying passengers and cargo is arranged at the front section of the lower frame, and wing compartments for placing a telescopic folding wing assembly are symmetrically arranged on the two side surfaces of the middle and rear sections of the lower frame, and storage rooms are respectively arranged on the rear two sides of the rear section of the lower frame, and a comprehensive room is arranged between the two storage rooms, and an airbag room for placing an airbag retracting and releasing system is arranged in the middle of the lower frame; folding propeller assemblies are respectively installed on the four corners above the main support; telescopic folding wing assemblies providing lift are symmetrically installed on both sides of the rear of the main support through a connecting structure, and a wing propeller is installed at the front end of the telescopic folding wing assembly; and running wheels are arranged under the main support.

[0005] The folding propeller assembly structure is specifically as follows: a main arm is hinged on the main bracket, and the hinge is connected to the steering gear. A plurality of shaft tubes parallel to the main arm are installed on the outer periphery of the main arm end, and connecting shafts are respectively sleeved on the shaft tubes. The connecting shafts are vertically connected to the auxiliary arm, and the vertical connection is connected to the steering gear. Motors are fixedly installed on the upper and lower ends of the auxiliary arm, and the output shafts of the motors drive the connected propeller blades.

[0006] The connection structure is specifically as follows: parallel connecting plates are vertically installed on the main bracket, the two connecting plates are spaced a certain distance apart, a connecting piece is fixed on the telescopic folding wing assembly, one end of the two connecting plates are respectively hinged on the main bracket, 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 bracket, 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 bracket between the two connecting plates.

[0007] The airbag retraction and deployment system: hollow support rods are respectively installed at the four corners of the bottom of the main bracket, the hollow support rods are fixed by a fixed pipe shaft and penetrate the fixed pipe shaft, and the axis of the hollow support rod is 45 degrees to the axis of the fixed pipe shaft; both ends of the fixed pipe shaft are hinged to the main bracket by a stabilizing shaft sleeve, and a swing arm is also connected to the fixed pipe shaft, and the swing arm is hinged to the linkage rod of the third hydraulic cylinder, and the third hydraulic cylinder is hinged in the middle of the bottom of the main bracket. The outer end of the hollow support rod is connected to the airbag through a retractable wheel structure. The airbag is composed of multiple small airbags, and the small airbags are installed in a fan-shaped arrangement around the retractable wheel structure.

[0008] The retractable and retractable wheel structure: the inner shaft tube is inserted into the outer shaft tube, a sealing plate is installed at the end of the inner shaft tube, the two ends of the outer shaft tube are respectively fixedly connected to the gear rings, the end of the hollow support rod is connected and fixed to the inner shaft tube, a reduction motor is installed in the inner shaft tube, and the output shaft of the reduction motor is meshed with the gear ring connected to the end of the outer shaft tube; a plurality of small holes are opened on the tube wall of the inner shaft tube, the ports in the small holes are connected to the hose, the hose passes through the inside of the hollow support rod to reach the fixed tube shaft and then passes out from it to be connected to the air nozzle in the integrated chamber; a ventilation ring channel connected to the small holes is opened on the tube wall of the outer shaft tube, and inflation holes are opened at different positions of the tube wall of the outer shaft tube in the ventilation ring channel, and the inflation holes are connected to the small air bag.

[0009] The integrated room is provided with two slot tracks along the front and rear directions of the aircraft. The trolley is set on the slot tracks through the track wheels at its bottom. Multiple servo motors are linked with the track wheels. The forward and reverse rotation of the servo motors drives the trolley to slide forward and backward, thereby adjusting the horizontal balance of the aircraft. A battery assembly is installed on the trolley to provide power for the aircraft.

[0010] The top surface of the folding propeller compartment is provided with a top cover that can be opened and closed automatically; the top surface of the parachute compartment is embedded with a parachute chamber cover; the outer side of the wing compartment is provided with a sliding side door that can be slid open and closed; the airbag compartment has a bottom door that opens downward, the end of the control room body is provided with a windshield window, and multiple side doors are provided on both sides of the control room; there is an automatic rear door at the rear of the integrated room, and the hydraulic system assembly, pneumatic system assembly, power system, battery, software part, control linkage part and balance linkage part for controlling and operating the aircraft are arranged inside the integrated room.

[0011] The four corners of the back side of the top cover are respectively hinged with support rods, and the other ends of the support rods are hinged with the main bracket and connected to the first steering gear. The first steering gear drives the support rods to swing, thereby linking the top cover to move, so as to realize the opening and closing of the top cover.

[0012] The upper and lower sides of the wing bin are respectively installed with slideways parallel to each other, the upper and lower sides of the sliding side door are respectively provided with pulleys, an inner slideway and an inner pulley matched therewith are horizontally installed in the middle position of the inner side of the sliding side door, the pulley and the inner pulley are respectively driven by a reduction motor, and the sliding side door moves along the slideway and the inner slideway to realize the opening and closing of the wing bin.

[0013] The beneficial effects of the present invention are: compact structure, capable of traveling and parking on the ground and water, capable of vertical take-off and landing on the ground and water, capable of deformation in the air, and an electric aircraft with a certain load, long endurance, and safe flight. It is in a folded state when traveling and parking on the ground, in a semi-expanded state when traveling and parking on the water, in a semi-expanded state when preparing for take-off and landing, in an expanded state when hovering and flying in the air, and in a fully expanded state when making an emergency landing in the air. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 This is a right side view of the parking ground of the present invention;

[0015] Figure 2 It is a schematic diagram of the folding propeller storage room top cover opened and the side door of the folding wing storage room retracted and retracted according to the present invention;

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

[0017] Figure 4 This is a top view of the vertical take-off and landing state of the present invention;

[0018] Figure 5 This is the front view of the vertical take-off and landing state of the present invention

[0019] Figure 6 This is a right view of the present invention in vertical take-off and landing state;

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

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

[0022] Fig. 9 A bottom view of the airbag of the present invention in a deployed state;

[0023] Fig.10 This is a schematic diagram of the retractable wheel structure of the present invention;

[0024] In the figure: 1-main support, 2-propeller compartment; 21-top cover, 22-support rod, 23-first steering gear, 3-parachute compartment, 4-wing compartment, 41-sliding side door, 42-slideway, 43-pulley, 44-inner slideway, 45-inner pulley; 5-airbag chamber, 6-folding propeller assembly, 61-main arm, 62-shaft tube, 63-auxiliary arm, 64-connecting shaft, 65-motor, 66-propeller blade; 7-telescopic folding wing assembly, 71-connecting plate, 72-first hydraulic cylinder, 73-second hydraulic cylinder, 74-wing propeller, 75-connecting piece; 8-airbag retracting and releasing system, 80-airbag Bag, 801-small air bag, 81-hollow support rod, 82-fixed pipe shaft, 83-stabilizing shaft sleeve, 84-swing arm, 85-linkage rod, 86-third hydraulic cylinder; M-retractable wheel mechanism, M1-gear ring, M2-outer shaft tube, M3-inner shaft tube, M4-small hole, M5-ventilation ring, M6-hose, M7-reduction motor, M8-output shaft, M9-gear, M10-gear ring, M11-sealing plate, M12-inflating hole; 9-integrated room, 91-groove track, 92-trolley, 93-track wheel; 10-travel wheel, 11-control room, 12-storage room. DETAILED DESCRIPTION

[0025] See Figure 1-10 , an amphibious and airborne aircraft, characterized in that: a main support 1 is divided into an upper frame and a lower frame, and propeller compartments 2 for installing and placing a folding propeller assembly 6 are symmetrically arranged at the front and rear ends of the upper frame, and the installation point is set at a corner in the propeller compartment 2, and a parachute compartment 3 for placing a parachute assembly is arranged between the folding propeller compartments 2; a control room 11 for driving and carrying passengers and cargo is arranged at the front section of the lower frame, and wing compartments 4 for placing a telescopic folding wing assembly 7 are symmetrically arranged on the two sides of the middle and rear sections of the lower frame, and storage rooms 12 are respectively arranged at the rear of the two sides of the rear section of the lower frame, and a comprehensive room 9 is arranged between the two storage rooms 12, and an airbag room 5 for placing an airbag retracting and releasing system 8 is arranged in the middle of the lower frame; folding propeller assemblies 6 are respectively installed on the four corners above the main support 1; telescopic folding wing assemblies 7 for providing lift are symmetrically installed on both sides of the rear of the main support 1 through a connecting structure, and a wing propeller 74 is installed at the front end of the telescopic folding wing assembly 7; and walking wheels 10 are arranged below the main support 1.

[0026] The structure of the foldable propeller assembly 6 is specifically as follows: a main arm 61 is hinged on the main bracket 1, and the hinge is connected to the steering gear. A plurality of shaft tubes 62 parallel to the main arm 61 are installed on the outer periphery of the end of the main arm 61, and connecting shafts 64 are respectively sleeved on the shaft tubes 62. The connecting shaft 64 is vertically connected to the auxiliary arm 63, and the vertical connection is connected to the steering gear. Motors 65 are fixedly installed on the upper and lower ends of the auxiliary arm 63, and the output shaft of the motor 65 drives the connected propeller blades 66.

[0027] Parallel connecting plates 71 are vertically installed on the main bracket 1, and the two connecting plates 71 are spaced a certain distance apart. A connecting piece 75 is fixed on the telescopic folding wing assembly 7. One end of the two connecting plates 71 are respectively hinged on the main bracket 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 bracket 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 bracket 1 between the two connecting plates 71.

[0028] The airbag retracting and deploying system 8: hollow support rods 81 are respectively installed at the four corners of the bottom of the main bracket 1, and the hollow support rods 81 are fixed by a fixed tube shaft 82 and penetrate the fixed tube shaft 82, and the axis of the hollow support rod 81 and the axis of the fixed tube shaft 82 are approximately 45 degrees; both ends of the fixed tube shaft 82 are hinged to the main bracket 1 by stabilizing shaft sleeves 83, and the fixed tube shaft 82 is also connected to a swing arm 84, and the swing arm 84 is hinged to the linkage rod 85 of the third hydraulic cylinder 86, and the third hydraulic cylinder 86 is hinged in the middle of the bottom of the main bracket 1, and the outer end of the hollow support rod 81 is connected to the airbag 80 through the retracting and deploying wheel structure M. The airbag 80 is composed of a plurality of small airbags 801, and the small airbags 801 are installed in a fan-shaped arrangement around the retracting and deploying wheel structure M.

[0029] The retractable wheel structure M: the inner shaft tube M3 is sleeved inside the outer shaft tube M2, the end of the inner shaft tube M3 is installed with a sealing plate M11, the two ends of the outer shaft tube M2 are respectively fixedly connected to the gear ring M1, the end of the hollow support rod 81 is connected and fixed to the inner shaft tube M3, the reduction motor M7 is installed in the inner shaft tube M3, and the output shaft M8 of the reduction motor M7 is meshed with the gear ring M10 connected to the end of the outer shaft tube M2;

[0030] A plurality of small holes M4 are provided on the wall of the inner shaft tube M3, and the inner ports of the small holes M4 are connected to a hose M6, which passes through the hollow support rod 81 to reach the fixed tube shaft 82 and passes out from it to be connected to the air nozzle in the integrated chamber 9; a ventilation ring M5 corresponding to the small holes M4 is provided on the wall of the outer shaft tube M2, and inflation holes M12 are provided at different positions on the wall of the outer shaft tube M2, and the inflation hole M12 is connected to the small air bag 801.

[0031] The integrated chamber 9 is provided with two slot rails 91 along the front and rear directions of the aircraft. The trolley 92 is set on the slot rails 91 through the track wheels 93 at its bottom. Multiple servo motors are linked with the track wheels 93. The forward and reverse rotation of the servo motor drives the trolley 92 to slide forward and backward, thereby adjusting the horizontal balance of the aircraft. A battery assembly for providing power to the aircraft is installed on the trolley 92.

[0032] The top surface of the folding propeller compartment 2 is provided with a top cover 21 that can be opened and closed automatically; 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 can be slid open and closed; the airbag compartment 5 has a bottom door that opens downward, the end of the control room 11 is provided with a windshield window, and multiple side doors are provided on both sides of the control room 11; the rear of the integrated room 9 is provided with an automatic rear door, and the hydraulic system assembly, pneumatic system assembly, power system, battery, software part, control linkage part and balance linkage part for controlling and operating the aircraft are arranged inside the integrated room 9.

[0033] The four corners of the back side of the top cover 21 are respectively hinged with support rods 22, and the other ends of the support rods 22 are hinged with the main support 1 and connected to the first steering gear 23. The first steering gear 23 drives the support rods 22 to swing, thereby linking the top cover 21 to move, thereby realizing the opening and closing of the top cover 21.

[0034] The upper and lower sides of the wing bin 4 are respectively installed with slideways 42 parallel to each other, the upper and lower sides of the sliding side door 41 are respectively provided with pulleys 43, an inner slideway 44 and an inner pulley 45 matched therewith are horizontally installed in the middle position of the inner side of the sliding side door 41, the pulley 43 and the inner pulley 45 are respectively driven by a reduction motor, and the sliding side door 41 moves along the slideway 42 and the inner slideway 44 to realize the opening and closing of the wing bin 4.

[0035] 1. Working process of each component:

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

[0037] After receiving the command to extend and deploy, the top covers 21 of the two propeller compartments 2 respond in turn, the support rod 22 connected to the first servo 23 responds, driving the top covers 21 to move away, leaving space, and the servos on the main arm 61 and the auxiliary arm 63 of the folding propeller assembly 6 respond to drive each to swing and twist, and the folding propeller assembly 6 is linked to extend the propeller compartment 2 and distribute around the main bracket 1. The propeller blades 66 on the folding propeller assembly 6 are stacked symmetrically up and down and rotate freely on the horizontal plane, and then the top cover 21 is folded and reset.

[0038] When the foldable propeller assembly 6 needs to be folded and reset, the process is the opposite of the above-mentioned extension and deployment process.

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

[0040] After receiving the command, the two telescopic folding wing assemblies 7 act simultaneously. First, the sliding side doors 41 of the two wing compartments 4 respond simultaneously, and the servo motor on the sliding side door 41 that is linked to the pulley 43 starts to drive the pulley 43 to rotate, and at the same time drives the sliding side door 41 to slide open, and then the telescopic folding wings are driven by the linkage connection mechanism to move out of their respective wing compartments 4, prop out the main bracket 1, go around and stand upright on both sides of the middle section of the main bracket 1, and the sliding side door 41 is then closed; when the aircraft is vertically lifted to a safe height, the telescopic folding wings receive the command again and start to act, first turn flat, then unfold, the wing propeller 74 starts to accelerate the rotation, and the aircraft begins to fly horizontally; when the aircraft receives the command to prepare for vertical landing, the telescopic folding wing assembly 7 is completed in sequence according to the reverse process of the above process.

[0041] 3. Airbag inflation process:

[0042] When the aircraft is flying in the air, the airbag 80 is in the folded state, at which time the hollow support rod 81 is close to the bottom of the main support 1, the retracting wheel mechanism M is placed in the airbag chamber 5, and the airbag 80 is wound around the outer shaft tube M2. When the aircraft receives an opening command, the two third hydraulic cylinders 86 work simultaneously, the linkage rod 85 and the swing arm 84 work in conjunction, driving the hollow support rod 81 and the airbag 80 to swing downward and to both sides, and the airbag 80 is inflated.

[0043] When receiving the folding command, in one case, the airbag 80 supports the aircraft to float on the water surface. When the aircraft is lifted off the water surface and receives the folding airbag command, the above-mentioned deployment process is completed in the opposite process. In another case, the airbag 80 contacts the ground for cushioning, which plays a role in the soft landing of the aircraft. At this time, the airbag 80 cannot automatically fold.

[0044] 4. Parachute folding process:

[0045] After the parachute assembly receives the command, the parachute quickly pops out from the parachute compartment 3, rushes to the sky and quickly unfolds. The parachute cannot be automatically folded, and it is manually handled after the aircraft lands.

[0046] 2. Implementation process of various models

[0047] 1. Ground parking mode:

[0048] The running wheels 10 are on the ground, the aircraft is in a folded state, and the doors of all rooms except the control room 11 are all closed. At this time, the telescopic folding wing assembly 7 is folded and placed upright in the wing compartment 4, the folding propeller assembly 6 is stored in the propeller compartment 2, the airbag 80 and the airbag retraction and deployment system are folded in the airbag chamber 5 under the main bracket 1, and the emergency parachute is in a dormant state and parked in the parachute compartment 3.

[0049] 2. Ground vertical take-off mode:

[0050] At this time, the aircraft is parked on the ground with the running wheels 10 touching the ground. The pilot issues a take-off command, and the two sliding side doors 41 of the two wing compartments 4 slide open at the same time. The retractable folding wings are simultaneously moved out of their respective wing compartments 4, extending out of the main bracket 1, and going around and standing upright on both sides of the middle section of the main bracket. Subsequently, the sliding side doors 41 are reset and closed. At the same time, the top cover 21 of the propeller compartment 2 is opened in turn, and the four sets of folding propeller assemblies 6 are extended and unfolded in turn, around the four corners on the upper part of the main bracket 1, so that the propeller blades 66 have rotation space. After that, the top cover 21 is reset and closed, and then the propeller starts and rotates rapidly to generate enough lift to vertically pull the aircraft up to a safe height in the air and hover. At the same time, the trolley 92 in the integrated room 9 slides forward and backward according to the command to adjust the front and rear balance of the aircraft. Subsequently, the two telescopic folding wings are flattened and symmetrically extended horizontally in opposite directions. The wing propeller 74 at the leading edge of the telescopic folding wing is started and rotated rapidly under the drive of its motor, pulling the aircraft to fly horizontally, and the multiple sets of propeller blades 66 gradually stop rotating, and the aircraft is in a level flight state. When the aircraft needs to turn in the air, the speed difference of the two wing propellers 74, that is, the pulling force difference, is controlled by the command to force the aircraft to turn in the air.

[0051] 3. Ground vertical landing mode:

[0052] After the aircraft receives the landing command, the folding propellers restart to generate enough lift to hold the aircraft in the air, the wing propellers 74 stop, and the aircraft gradually enters the hovering state from the level flight state. Then, the telescopic folding wings 7 retract and droop, and the four groups of folding propellers that provide lift automatically adjust the speed. The aircraft slowly lands vertically to the ground. Then, the folding propellers stop and automatically fold and retract into the propeller compartment 2, and the telescopic folding wings are retracted into the wing compartment 4, and the flight is completed.

[0053] 4. Water surface vertical take-off mode:

[0054] The aircraft changes from the surface mode to the flight mode. At this time, the aircraft stops on the water surface. The airbag 80 is deployed and extended from the bottom of the main support 1 under the drive of the airbag retracting and releasing system 8. The airbag is inflated and floats on the water surface, supporting the aircraft to stop on the water surface. The pilot controls the aircraft, inputs the destination, and issues a take-off command. The retractable folding wings are simultaneously moved out of their respective wing compartments 4, extend out of the main support 1, and go around and stand upright on both sides of the middle section of the main support. Then, the sliding side door 41 is reset and closed. At the same time, the top cover 21 of the propeller compartment 2 is opened in turn, and the four groups of folding propeller assemblies 6 are successively extended and deployed around the four corners of the upper part of the main support 1, so that the propeller blades 66 have rotation space. Then, the top cover 21 is reset and closed, and then the propeller starts and rotates rapidly to generate enough lift to vertically pull the aircraft up to a safe height in the air and hover. At the same time, the trolley 92 in the integrated room 9 slides forward and backward according to the command to adjust the front and rear balance of the aircraft. Subsequently, the airbag 80 is deflated and the airbag retracting and releasing system 8 is retracted into the supporting chamber 5, the retractable folding wings are leveled and extended horizontally symmetrically in opposite directions, the wing propellers 74 start to rotate, pulling the aircraft into horizontal flight. As the aircraft's level flight speed increases, the lift generated by the retractable folding wings is sufficient to lift the aircraft, the folding propellers stop rotating, and the aircraft enters a level flight state.

[0055] 5. Water surface vertical landing mode:

[0056] When the aircraft receives an order to land vertically on the water during flight, the folding propeller restarts to generate enough lift to hold the aircraft in the air, the wing propeller 74 stops, and the aircraft gradually enters a hovering state from a level flight state, the telescopic folding wing retracts and droops, the airbag 80 is unfolded and inflated with the airbag retraction and deployment system 8, the folding propeller automatically adjusts the speed, and the aircraft slowly lands vertically on the water. Then, the folding propeller stops and automatically folds and retracts into the propeller compartment 2, and the telescopic folding wing is retracted into the wing compartment 4, and the flight is completed.

[0057] 6. Air flight mode:

[0058] When the aircraft turns in level flight in the air, the rotation speed of the two wing propellers 74 is changed, resulting in a speed difference that makes the pulling force of the two propellers unequal, thereby changing the flight direction of the aircraft; when pitching, the trolley 92 installed in the integrated room 9 slides forward and backward under the control of instructions, adjusting the front and rear balance of the aircraft, so that the aircraft pitches forward and backward.

[0059] 7. In emergency landing mode:

[0060] When the aircraft is flying in the air and needs to make an emergency landing, the airbag 80 is quickly deployed and inflated when the aircraft receives the emergency landing command, and the parachute pops out from the parachute compartment 3 in the middle of the top of the main support 1. The parachute pulls the aircraft to slowly land, and the aircraft can land on the ground or on the water. The aircraft lands safely.

Claims

1. A amphibious and airborne vehicle, characterized in that: The main support (1) is divided into an upper frame and a lower frame. The upper frame is symmetrically provided with propeller compartments (2) for installing and placing a folding propeller assembly (6) at both ends, and a parachute compartment (3) for placing a parachute assembly is provided between the folding propeller compartments (2). The front section of the lower frame is provided with a control room (11) for driving and carrying passengers and cargo. The middle and rear sections of the lower frame are symmetrically provided with wing compartments (4) for placing a telescopic folding wing assembly (7). The rear sections of the lower frame are respectively provided with storage compartments (12) at the rear sides. ), a comprehensive room (9) is provided between the two storage rooms (12), an airbag room (5) for accommodating an airbag retracting and releasing system (8) is provided in the middle below the lower shelf; folding propeller assemblies (6) are respectively installed on the four corners above the main bracket (1); telescopic folding wing assemblies (7) for providing lift are symmetrically installed on both sides of the rear of the main bracket (1) through a connecting structure, and a wing propeller (74) is installed at the front end of the telescopic folding wing assembly (7); and running wheels (10) are provided below the main bracket (1); The airbag retracting and releasing system (8) comprises: hollow support rods (81) are respectively installed at the four corners of the bottom of the main support (1); the hollow support rods (81) are fixed by a fixed pipe shaft (82) and penetrate the fixed pipe shaft (82); the axis of the hollow support rod (81) and the axis of the fixed pipe shaft (82) are at 45 degrees; both ends of the fixed pipe shaft (82) are hinged to the main support (1) by stabilizing sleeves (83); the fixed pipe shaft (82) is also connected to a swing arm (84); the swing arm (84) is hinged to a linkage rod (85) of a 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 rod (81) is connected to the airbag (80) through a retracting and releasing wheel structure (M); the airbag (80) is composed of a plurality of small airbags (801); the small airbags (801) are arranged in a fan shape around the retracting and releasing wheel structure (M); The retractable wheel structure (M) comprises: an inner shaft tube (M3) is sleeved inside an outer shaft tube (M2), a sealing plate (M11) is installed at the end of the inner shaft tube (M3), both ends of the outer shaft tube (M2) are respectively fixedly connected to a gear ring (M1), the end of a hollow support rod (81) is connected and fixed to the inner shaft tube (M3), a reduction motor (M7) is installed in the inner shaft tube (M3), and an output shaft (M8) of the reduction motor (M7) is meshed with a gear ring (M10) connected to the end of the outer shaft tube (M2); the inner shaft tube (M3) is provided with a plurality of gears, wherein the gears are provided at the ends of the gears. A plurality of small holes (M4) are formed on the wall, the inner ports of the small holes (M4) are connected to a hose (M6), the hose (M6) penetrates into the hollow support rod (81) to reach the fixed tube shaft (82) and passes out from the fixed tube shaft to be connected to the air nozzle in the integrated chamber (9); a ventilation ring channel (M5) correspondingly connected to the small holes (M4) is formed on the wall of the outer shaft tube (M2), and the ventilation ring channel (M5) is provided with inflation holes (M12) at different positions on the wall of the outer shaft tube (M2), and the inflation hole (M12) is connected to the small air bag (801).

2. The amphibious aircraft according to claim 1, characterized in that: The structure of the foldable propeller assembly (6) is specifically as follows: a main arm (61) is hingedly connected to the main support (1), and the hinge is connected to the steering gear; a plurality of shaft tubes (62) parallel to the main arm (61) are installed on the outer periphery of the end of the main arm (61); connecting shafts (64) are respectively sleeved on the shaft tubes (62); the connecting shafts (64) are vertically connected to the auxiliary arm (63); the vertical connection is connected to the steering gear; motors (65) are fixedly installed on the upper and lower ends of the auxiliary arm (63); the output shaft of the motor (65) drives the connected propeller blades (66).

3. The amphibious aircraft according to claim 1, characterized in that: The connection structure specifically comprises: parallel connection plates (71) are vertically mounted on the main support (1), the two connection plates (71) are spaced a certain distance apart, a connection piece (75) is fixed on the telescopic folding wing assembly (7), one end of the two connection plates (71) are respectively hinged on the main support (1), and the other end is hinged to the end of the connection 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 connection piece (75); one end of the second hydraulic cylinder (73) is hinged to the hinge point between the connection plate (71) and the connection piece (75), and the other end is hinged to the main support (1) between the two connection plates (71).

4. The amphibious aircraft according to claim 1, characterized in that: The integrated chamber (9) is provided with two slot rails (91) along the front-rear direction of the aircraft. The trolley (92) is arranged on the slot rails (91) via rail wheels (93) at the bottom thereof. A plurality of servo motors are linked with the rail wheels (93). The servo motors rotate forward and reversely to drive the trolley (92) to slide forward and backward, thereby adjusting the horizontal balance of the aircraft. A battery assembly for providing electrical energy to the aircraft is installed on the trolley (92).

5. The amphibious aircraft according to claim 1, characterized in that: The top surface of the folding propeller compartment (2) is provided with a top cover (21) that can be opened and closed automatically; 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 can be slid open and closed; the airbag compartment (5) has a bottom door that opens downwards; the end of the control room (11) is provided with a windshield window, and a plurality of side doors are provided on both sides of the control room (11); the rear of the integrated room (9) is provided with an automatic rear door, and the integrated room (9) is 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. The amphibious aircraft according to claim 5, characterized in that: The four corners of the back side of the top cover (21) are respectively hinged to support rods (22); the other ends of the support rods (22) are hinged to the main support (1) and connected to a first steering gear (23); the first steering gear (23) drives the support rods (22) to swing, thereby linking the top cover (21) to move, thereby realizing the opening and closing of the top cover (21).

7. The amphibious aircraft according to claim 5, characterized in that: The wing bin (4) is provided with slideways (42) parallel to each other on the upper and lower sides, respectively, and pulleys (43) are provided on the upper and lower sides of the sliding side door (41) respectively. An inner slideway (44) and an inner pulley (45) matched therewith are horizontally installed at the middle position of the inner side of the sliding side door (41). The pulley (43) and the inner pulley (45) are driven by reduction motors respectively, and the sliding side door (41) moves along the slideway (42) and the inner slideway (44) to realize the opening and closing of the wing bin (4).

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