Electric land-air amphibious hovercar

Abstract

The invention relates to the technical field of automobiles, in particular to an electric land-air amphibious flying automobile which comprises an automobile body, a cockpit is installed in the middle of the top of the automobile body, and a battery and an amphibious running controller are installed on the rear portion in the automobile body. A horizontal tail 5 is mounted at the rear part of the vehicle body; two front wings and two rear wings are correspondingly installed on the two sides of the front portion and the two sides of the rear portion of the vehicle body respectively, semicircular front hub grooves are formed in the outer sides of the two front wings, and semicircular rear hub grooves are formed in the outer sides of the two rear wings. The air-ground power system is used for driving wheels, lifting force and thrust, and the solid-state battery is used as an energy system and is used for air-ground control. The mobile power supply has the advantages of low noise, good safety, fixed use of a solid-state battery, small size, light weight, fast charging, less use and the like.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of automobile technology, in particular to an electric amphibious flying automobile. BACKGROUND

[0002] The electric amphibious flying automobile is a complex system integration of aviation, vehicle, electrification, lightweight material and information technology. How to realize deep collaboration and extreme optimization of land travel and flight power, energy land and air function control, structure, avionics, environmental control, safety and task load and other systems is a problem to be solved. SUMMARY

[0003] The present application aims at the defects and deficiencies of the prior art, and provides an electric amphibious flying automobile.

[0004] The electric amphibious flying automobile comprises a vehicle body, a cockpit is installed at the top of the vehicle body, and a battery and an amphibious driving controller are installed at the rear of the vehicle body; a horizontal tail is installed at the rear of the vehicle body; two front wings and two rear wings are respectively installed at the front and rear sides of the vehicle body, half-round front hub grooves are formed at the outer sides of the two front wings, and half-round rear hub grooves are formed at the outer sides of the two rear wings; rotatable front wheel components are respectively installed in the two half-round front hub grooves; the two front wheel components are respectively installed at the two ends of a front wheel steering mechanism; rotatable rear wheel components are respectively installed in the two half-round rear hub grooves. As shown in FIG. - FIG., control compartments are respectively arranged in the two front wings and the two rear wings, two half-round paddle outer support rotating servo motors are installed in each control compartment, a control mechanism for controlling the action of the half-round paddle outer support rotating servo motor is installed in each control compartment, and a rotating servo motor control mechanism is formed; four strip strong magnetic shock absorbers are installed on one side of each control compartment, and a combined strong magnetic shock absorbing mechanism is formed. The wheels in each front wheel component or rear wheel component are wheels with two built-in propellers, forming a multi-duct wheel A; eight half-round paddle outer support rotating servo motors in four control compartments drive two propellers in each front wheel component or rear wheel component, forming eight half-round paddle outer support rotating servo motors driving eight propellers at the corresponding positions, and a control computer B in the amphibious driving controller controls the eight half-round paddle outer support rotating servo motors, which are four first propeller motors installed in the two front wheel components and four second propeller motors installed in the two rear wheel components, forming a land and air power mechanism with duct effect.

[0005] Further, the propellers in the front wheel components and the rear wheel components on the same side of the vehicle body are coaxial counter-rotating propellers.

[0006] Further, a plurality of first wing ribs are mounted on the two front wings and the two rear wings.

[0007] Further, a plurality of second wing ribs are mounted on the horizontal tail 5.

[0008] Further, the half-circular paddle outer support rotating servo motor is an axial flux motor.

[0009] Further, the vehicle body material is carbon fiber composite material.

[0010] Further, the amphibious driving controller comprises a fly-by-wire control mechanism C, a control computer B, and a sensing and navigation inertial measurement unit D, a magnetometer E, GPS data F, atmospheric data G, and a laser radar H mounted in the cockpit; the control computer B controls eight half-circular paddle outer support rotating servo motors through the fly-by-wire control mechanism C to form a land-air control system.

[0011] In the design, the sensing and navigation inertial measurement unit D, the magnetometer E, the GPS data F, the atmospheric data G, and the laser radar H form a sensor suite to provide various data information for the land-air control system.

[0012] Further, a multifunctional touch display screen B for human-computer interaction is mounted on the control computer B, the control computer B is connected with a battery management system L and a task management system M through data wires to control the use and protection of the battery; the control computer B is connected with an air-ground information radio station and a ground other terminal J through satellite communication I to realize information interaction; the ground other terminal J is used for other vehicles and aircrafts to realize information interaction; the control computer B is connected with a user K through a 5G cellular network to complete the access of human-computer interaction and interconnected objects to form an avionics and task management system.

[0013] Further, the battery is a solid-state battery.

[0014] After the above structure is adopted, the electric amphibious flying vehicle has the advantages of low noise, good safety, fixed solid-state battery use, small size, light weight, fast charging, and less use, etc. BRIEF DESCRIPTION OF DRAWINGS

[0015] The drawings described herein are used to provide further understanding of the present application, and form a part of the present application, but do not constitute improper limitations on the present application, and in the drawings: Figure 1 is a perspective structural schematic view of the land driving mode of the present application; Figure 2 is a front view structural schematic view of the present application; Figure 3 is a side view structural schematic diagram of the present application; Figure 4 is a rear wheel side view structural schematic diagram of the present application; Figure 5 is a rear wheel top view structural schematic diagram of the present application; Figure 6 is a front wheel side view structural schematic diagram of the present application; Figure 7 is a front wheel top view structural schematic diagram of the present application; Figure 8 is a top view structural schematic diagram of the present application; Figure 9 is a bottom view structural schematic diagram of the present application; Figure 10 is a horizontal flight state structural schematic diagram of the present application; Figure 11 is a structural schematic diagram of one state of the vertical take-off mode process of the present application; Figure 12 is a structural schematic diagram of another state of the vertical take-off mode process of the present application; Figure 13 is a wing profile cross-sectional structural schematic diagram of the relatively symmetrical front wing and rear wing of the present application; Figure 14 is a topological diagram of the land-air power system of the present application; Figure 15 is a topological diagram of the land-air control of the present application; Figure 16 is a topological diagram of the avionics management system of the present application.

[0016] Explanation of reference signs: vehicle body 1; cockpit 2; rear wheel component 3; front wheel component 4; horizontal tail 5; front wing 6; rear wing 7; battery and amphibious travel controller 8; front wheel steering mechanism 9; strip type strong magnetic shock absorber 10; servo motor control mechanism 11; first propeller motor control mechanism 12. DETAILED DESCRIPTION

[0017] In order to make the purpose, technical scheme and advantages of the embodiments of the present application clearer, the technical scheme in the embodiments of the present application will be described clearly and completely below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are some of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application.

[0018] In the description of this invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0019] like Figures 1-3 As shown in the figure, the electric amphibious flying car described in this specific embodiment includes a body 1, a cockpit 2 installed in the middle of the top of the body 1, and a battery and amphibious driving controller 8 installed in the rear of the body 1; a horizontal tail fin 5 is installed in the rear of the body 1; two front wings 6 and two rear wings 7 are respectively installed on the front and rear sides of the body 1, and semi-circular front wheel hub grooves 61 are opened on the outer side of the two front wings 6, and semi-circular rear wheel hub grooves 71 are opened on the outer side of the two rear wings 7; rotatable front wheel components 4 are respectively installed in the two semi-circular front wheel hub grooves 61; the two front wheel components 4 are respectively installed at both ends of the front wheel steering mechanism; rotatable rear wheel components 3 are respectively installed in the two semi-circular rear wheel hub grooves 71. like Figures 14-16 Each of the two front wings 6 and the two rear wings 7 is equipped with a control compartment. Each control compartment is equipped with two semi-circular propeller wheel outer support rotary servo motors and a control mechanism that controls the operation of the semi-circular propeller wheel outer support rotary servo motors, forming a rotary servo motor control mechanism 11. Each control compartment is equipped with a strip-type strong magnetic vibration damper 10 on one side, and the four strip-type strong magnetic vibration dampers form a combined strong magnetic vibration damping mechanism. Each wheel in the front wheel assembly 4 or rear wheel assembly 3 is a wheel with two built-in propellers, forming a multi-ducted wheel A; the eight semi-circular propeller wheel external bracket rotary servo motors in the four control compartments drive the two propellers in the corresponding wheels of each front wheel assembly 4 and rear wheel assembly 3, forming eight semi-circular propeller wheel external bracket rotary servo motors driving the eight propellers at the corresponding locations; the control computer B in the amphibious driving controller 8 controls the eight semi-circular propeller wheel external bracket rotary servo motors, which are four first propeller motors 44 installed in the two front wheel assemblies 4 and four second propeller motors 32 installed in the two rear wheel assemblies 3, forming a land-air propulsion mechanism with duct effect.

[0020] Furthermore, the propellers in the front wheel component 4 and the rear wheel component 3 on the same side of the vehicle body are coaxial counter-rotating propellers.

[0021] Furthermore, several first wing ribs are installed on the surfaces of the two front wings 6 and the two rear wings 7.

[0022] Further, the horizontal tail 5 is provided with a plurality of second wing ribs.

[0023] Further, the semi-circular propeller wheel outer support rotating servo motor is an axial flux motor.

[0024] Further, the vehicle body 1 is made of carbon fiber composite material.

[0025] Further, the amphibious driving controller 8 comprises a fly-by-wire control mechanism C, a control computer B and sensing and navigation inertial measurement units D, magnetometers E, GPS data F, atmospheric data G and laser radars H installed in the cockpit 2; the control computer B controls eight semi-circular propeller wheel outer support rotating servo motors through the fly-by-wire control mechanism C to form a land-air control system.

[0026] In the design, the sensing and navigation inertial measurement units D, magnetometers E, GPS data F, atmospheric data G and laser radars H form a sensor suite to provide various data information for the land-air control system.

[0027] Further, the control computer B is provided with a multifunctional touch display screen B1 for human-computer interaction, the control computer B is connected with a battery management system L and a task management system M through data wires to control battery use and protection; the control computer B is connected with an air-ground information radio and other ground terminals J through satellite communication I; the other ground terminals J are used for information interaction of other vehicles and aircrafts; the control computer B is connected with a user K through a 5G cellular network to complete human-computer interaction and access of interconnected objects to form an avionics and task management system.

[0028] Further, the battery is a solid-state battery.

[0029] The working principle of the present application is described as follows: In the present application, the rear wheel component 3 comprises a semi-circular hub support rotatable shaft one 37 installed in the middle of the inner wall of the semi-circular front hub groove 61, a semi-circular hub support one 38 installed on the semi-circular hub support rotatable shaft one 37, an inner hub rotatable shaft one 39 installed on the outer end of the inner wall of the semi-circular hub support one 38, a support inner hub one 35 installed on each side of the inner hub rotatable shaft one 39, a motor support one 36 installed on the inner wall of each of the two support inner hubs one 35, a rotating hub one 33 installed on the outer side of each of the two support inner hubs one 35, and a rotating tire one 34 installed on the rotating hub one 33; four second propeller motors 32 are installed on the outer and inner sides of the center of the two motor supports one 36 of the two front wheels to control the action of the first propeller motor 44 through a second propeller motor control mechanism 12. Four second propellers 31 are installed on the four second propeller motors 32, and the four second propeller motors 32 are all semi-circular propeller wheel outer support rotating servo motors.

[0030] In the application, the front wheel component 4 comprises a semicircular hub support rotatable shaft two 411 installed in a semicircular hub slot 71, a semicircular hub support two 412 installed on the semicircular hub support rotatable shaft two 411, and an inner hub rotatable shaft two 413 installed on the outer wall of the semicircular hub support two 412 on both sides; the inner hub rotatable shaft two 413 is provided with a support inner hub two 49 on both sides; and the inner wall of the two support inner hub two 49 is provided with a motor support two 410. The two motor supports two 410 of the two rear wheels are provided with four first propeller motors 44 and a first propeller motor control mechanism 13 for controlling the action of the first propeller motors 44. The four first propeller motors 44 are respectively provided with four first propellers 41; the four first propeller motors 44 are all semicircular propeller outer support rotating servo motors; the first propeller motor control mechanism 13 and the second propeller motor control mechanism 12 in the design are control mechanisms for controlling the operation of the motors, and the control circuit involved is prior art.

[0031] In the design, the four second propeller motors 32 and the four first propeller motors 44 are all semicircular propeller outer support rotating servo motors, which has the advantages of unified motor specifications, convenient management and maintenance in the later stage, batch purchase at a low cost, and reduced procurement cost.

[0032] The outer sides of the two support inner hub two 49 are respectively provided with a rotating hub two 47, and the rotating hub two 47 is provided with a rotating tire two 48 on the outer side; the surface of the two rotating hub two 47 is provided with a hyperboloid outer gear disc 43 matched therewith.

[0033] In the application, the two inner hub rotatable shaft two 411 in the front of the vehicle body 1 are respectively provided with a power transmission shaft mechanism; the power transmission shaft mechanism comprises a hyperboloid inner gear disc 43 installed on the semicircular hub support rotatable shaft two, the hyperboloid inner gear disc 43 is engaged with a movable inner gear shaft one 45, the movable inner gear shaft one 45 is connected with an inner end of a power transmission shaft 46, an outer end of the power transmission shaft 46 is provided with a movable inner gear shaft two, the movable inner gear shaft two and the movable inner gear shaft one are the same in structure; the movable inner gear shaft two is engaged with a hyperboloid outer gear disc 42 to form a power transmission shaft system for driving the front wheels; when driving on land, the movable inner gear is engaged with the gear disc; when flying in the air, the movable inner gear is separated from the gear disc.

[0034] In the application, the rotation speed of the two front wheel motors is adjusted by a driving computer controller to complete the steering action.

[0035] In the application, the motor support one includes three connecting rods 361 evenly installed around the inner wall of the inner hub, the inner ends of the three connecting rods 361 are connected with the middle disc, forming the motor support.

[0036] In the application, the battery and amphibious running controller 8 are installed in the lower part of the vehicle body 1. The battery and amphibious running controller 8 are prior art as the existing equipment of the electric vehicle.

[0037] In the application, the electric land-air amphibious vehicle is a complex system integration of aviation, vehicle, electrification, light material and information technology. Eight systems, i.e. land running and flight power, energy land-air dual function control, structure, avionics, environmental control, safety and task load, must realize deep cooperation and extreme optimization of the eight systems.

[0038] 1. Land-air power system: the core of driving wheels and lift thrust. The core features are that eight independent axial flux motors drive four built-in propeller wheels to replace similar duct effect. In the land running state, two motors drive two front wheels to run, the vertical take-off and landing unit starts eight propellers at the same time, four wheels change into the horizontal direction to provide lift through the similar duct, the horizontal cruise propulsion makes the four semi-circular wheel hubs tilt to the forward direction, so that the propellers generate forward pulling force and upward lift, and the fixed wing also generates a certain lift. The axial flux motor has the advantages of high density, high efficiency, high reliability, small size and light weight, the four duct propellers replaced by the wheels use optimized shape and composite materials to complete the characteristics of low noise, safety and compactness. The latest motor controller and electronic governor can accurately control the motor speed, torque and steering.

[0039] 2. Energy system: the blood of land-air running and flight: the use of solid-state battery, small size, light weight, fast charging, high energy, high power, super long cycle service life and endurance power is the best choice at present. 3. Land-air control system: the "nerve center" of safe running and flight: (1) land-air control computer: multi-channel design, processing sensor data, solving control instructions, managing the switching of various modes (land running, vertical take-off, hovering, transition, cruising). (2) Sensor suite: sensing and navigation inertial measurement unit provides high-precision acceleration and angular rate, attitude heading reference IMU, magnetometer, GPS data, atmospheric data, laser radar. (3) Actuator: fly-by-wire system converts computer control instructions into physical actions, and motor controller receives control to control the speed and thrust vector of each electric propulsion unit. Guidance system plans the running and flight path and completes autonomous driving.

[0040] 4. Machine structure and material: the cornerstone of light weight and strength (1) Lightweight structural design: Extremely optimized topology structure, using carbon fiber composite materials to achieve the most ideal strength, stiffness and weight. (2) Aerodynamic shape design: conforms to aerodynamic shape, fixed wing + multi-ducted wheels, can realize land driving, vertical take-off and landing, and efficient cruise. (3) Simple landing gear system: used in conjunction with the completed state during vertical take-off and landing.

[0041] 5. Avionics and Mission Management System: The brain of driving and flight: (1) Integrated avionics system: integrates display, communication, navigation and monitoring functions; (2) Human-machine interface, which can provide timely feedback on relevant adjustments and references; (3) The cockpit is equipped with a multi-functional touch screen and visual operation; (4) Data link and communication professional platform to complete information interaction; (5) Air-to-ground communication radio; (6) 5G cellular network to complete the access and transmission of human-machine and interconnected objects; (7) Battery management system: maximizes the use of battery capacity, life, safety monitoring, protection, real-time monitoring of voltage, current and temperature, diagnosis of faults, and execution of isolation and protection; (8) Satellite communication to realize information interaction between the vehicle and the ground, other vehicles and aircraft; (9) Mission management system: mission planning, execution monitoring, data recording, health management, passenger scheduling, etc.

[0042] 6. Environmental control system: Ensures cabin environmental control, equipment cooling, comfort, and safety.

[0043] 7. Safety and Airworthiness Systems: Survival baseline, vehicle-mounted parachute system, independent emergency power supply, advanced collision avoidance system, health prediction and management system, and fire protection system.

[0044] 8. Passenger and Cargo System: The carrier for realizing mission functions.

[0045] Specific embodiment one of the present invention: as follows Figures 1-3 As shown, this design is initially used in land driving mode. In this mode, the design functions as an electric vehicle. When turning, the rear wheels are de-powered. A power drive shaft system is installed on the front wheels of the vehicle body 1, driving the front wheels and thus propelling the electric vehicle. When the power drive shaft system is working, the first propeller motor drives a hyperboloid internal gear disk, which in turn drives a meshing movable internal gear shaft one. The movable internal gear shaft one drives the power drive shaft to rotate, which in turn drives a movable internal gear shaft two at its outer end to rotate. The movable internal gear shaft two then drives a meshing hyperboloid external gear disk to rotate, which in turn drives an inner frame inner hub two to rotate. The inner frame inner hub two then drives the rotating tires, thus providing the electric vehicle with driving power and enabling its use as an electric vehicle.

[0046] Specific implementation method two: such as Figures 11-12This design transitions the vehicle from driving mode to lift mode. The power transmission shaft drives a movable internal gear shaft to disengage from the hyperboloid internal gear disc. At this point, eight motors (two first propeller motors built into each front wheel, two first propeller motors built into each rear wheel, four first propeller motors built into the two front wheels, and four first propeller motors built into the two rear wheels) drive the eight propellers simultaneously to rotate horizontally. During this transition, the propeller rotation generates lift, enabling the entire vehicle to lift into the air.

[0047] Specific implementation method three: such as Figure 10 As shown, this design transitions from takeoff mode to level flight mode. The rotatable shaft 2 of the semi-circular hub bracket is installed in the semi-circular rear hub groove 71. The rotation of the semi-circular hub bracket 2 is controlled by rotating the rotatable shaft 2, thereby rotating the connected semi-circular hub bracket 2. The rotation angle can be controlled by the flight control system. The semi-circular hub bracket 2 synchronously drives the connected front wheel component 4 and rear wheel component 3 to move, generating a horizontal forward thrust by changing different angles.

[0048] In this design, the two front wings 6 and two rear wings 7 on the front and rear sides of the vehicle body 1 are in a symmetrical structural relationship. The four wings generate lift, which, together with the pull generated by the front wheel assembly 4 and the rear wheel assembly 3, forms a resultant force that enables horizontal flight.

[0049] In this design, such as Figure 13 The diagram shown is a structural schematic of the symmetrical front and rear wings of this invention. The front and rear wings are symmetrical plano-convex wings. In operation, the four front and rear wings and the horizontal tail generate lift during horizontal flight, greatly reducing the lift and horizontal thrust generated by the eight propellers.

[0050] The above embodiments are only used to illustrate the technical solutions of the present invention, and are not intended to limit it. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. An electric amphibious flying vehicle, comprising a vehicle body, a cockpit mounted in the middle of the top of the vehicle body, a battery and an amphibious driving controller mounted in the rear of the vehicle body; a horizontal tail fin mounted in the rear of the vehicle body; two front wings and two rear wings respectively mounted on the front and rear sides of the vehicle body, the outer sides of the two front wings having semi-circular front wheel hub grooves, and the outer sides of the two rear wings having semi-circular rear wheel hub grooves; rotatable front wheel components are respectively mounted in the two semi-circular front wheel hub grooves; the two front wheel components are respectively mounted at both ends of a front wheel steering mechanism; rotatable rear wheel components are respectively mounted in the two semi-circular rear wheel hub grooves. Its features are: Each of the two front wings and two rear wings has a control compartment. Each control compartment is equipped with two semi-circular propeller wheel outer support rotary servo motors and a control mechanism that controls the operation of the semi-circular propeller wheel outer support rotary servo motors, forming a rotary servo motor control mechanism. Each control compartment has a strip-type strong magnetic vibration damper installed on one side. The four strip-type strong magnetic vibration dampers form a combined strong magnetic vibration damping mechanism. Each wheel in the front or rear wheel assembly has two built-in propellers, forming a multi-ducted wheel A. Eight semi-circular propeller wheel external brackets in the four control compartments drive the two propellers in the corresponding wheels of each front and rear wheel assembly, forming eight semi-circular propeller wheel external brackets driving eight propellers at corresponding locations. The control computer B in the amphibious driving controller controls the eight semi-circular propeller wheel external brackets rotating servo motors. The eight semi-circular propeller wheel external brackets rotating servo motors are four first propeller motors installed in the two front wheel assemblies and four second propeller motors installed in the rear wheel assembly, forming a land-air propulsion mechanism with ducted effect.

2. The electric amphibious flying vehicle according to claim 1, characterized in that: The propellers in the front wheel assembly and rear wheel assembly on the same side of the vehicle body are coaxial counter-rotating propellers.

3. The electric amphibious flying vehicle according to claim 1, characterized in that: Several first wing ribs are installed on the surfaces of the two front wings and the two rear wings.

4. The electric amphibious flying vehicle according to claim 1, characterized in that: Several second wing ribs are mounted on the horizontal tail.

5. An electric amphibious flying vehicle according to claim 1, characterized in that: The feature is that the body material is a carbon fiber composite material.

6. An electric amphibious flying vehicle according to claim 1, characterized in that: The amphibious driving controller includes a fly-by-wire control mechanism C, a control computer B, a sensing and navigation inertial measurement unit D, a magnetometer E, GPS data F, atmospheric data G, and a lidar H, all installed in the cockpit. The control computer B controls eight servo motors rotating on the outer supports of the semi-circular propeller wheels through the fly-by-wire control mechanism C, forming a land-air control system.

7. An electric amphibious flying vehicle according to claim 1, characterized in that: The control computer B is equipped with a multi-functional touchscreen display B for human-machine interaction. The control computer B is connected to the battery management system L and the mission management system M via data cables to control battery usage and protection. The control computer B also interacts with air-to-ground communication radios and other ground terminals J via satellite communication I. These other ground terminals J represent other vehicles and aircraft, enabling information exchange. Furthermore, the control computer B communicates with user K via a 5G cellular network, facilitating human-machine and interconnected communication and forming an avionics and mission management system.

8. An electric amphibious flying vehicle according to claim 1, characterized in that: The battery is a solid-state battery.

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