Vertical take-off and landing and fixed wing aerocar

文档序号：478830 发布日期：2022-01-04 浏览：41次中文

阅读说明：本技术 垂直起降与固定翼飞行汽车 (Vertical take-off and landing and fixed wing aerocar ) 是由张锐于 2020-07-04 设计创作，主要内容包括：本发明提供两种有人驾驶垂直起降与固定翼飞行汽车和两种兼具有人驾驶和无线遥控功能的垂直起降与固定翼飞行汽车；其采用多层连续翼面螺旋桨提供垂直方向上的升力,且利用其螺旋翼面结构来切割和适应迎风快速层流或横风层流,避免了采用一般叶式螺旋桨时迎风或横风层流直接对桨叶产生气流冲击和桨叶翼尖产生激波震颤,所带来的风阻较大、飞行不稳或悬停风吹偏航问题,升空后采用飞行驱进装置提供平飞动力,快速平飞行时停止多层连续翼面螺旋桨的运转后依靠主机翼产生升力维持平飞,以节省燃料或电力并提高续航时长,依靠机翼舵面动作调整飞行汽车姿态,降低飞控难度；可实现垂直起降、滑翔起降等混合起降方式,提高起降场地适应性。(The invention provides two manned vertical take-off and landing and fixed wing aerocars and two manned and wireless remote control vertical take-off and landing and fixed wing aerocars; the multi-layer continuous wing surface propeller is adopted to provide lift force in the vertical direction, and the spiral wing surface structure of the multi-layer continuous wing surface propeller is utilized to cut and adapt to windward fast laminar flow or crosswind laminar flow, so that the problems of large wind resistance, unstable flight or hovering wind blowing yaw caused by airflow impact on a blade directly caused by windward or crosswind laminar flow when a general blade type propeller is adopted are solved, a flight driving device is adopted to provide level flight power after the lift is lifted, the lift force generated by a main wing is utilized to maintain level flight after the operation of the multi-layer continuous wing surface propeller is stopped during fast level flight, so that fuel or electric power is saved, the duration is prolonged, the attitude of a flying automobile is adjusted by the action of a wing surface, and the flight control difficulty is reduced; can realize the mixed take-off and landing modes such as vertical take-off and landing, gliding take-off and landing and the like, and improve the adaptability of the take-off and landing site.)

1. A VTOL and fixed wing aerocar, comprising: the airplane comprises two multi-layer continuous wing surface propellers (1), two power units (11), a car body (2), a buffer suspension (20), a cockpit and a passenger cabin (21), front wheels (22), rear wheels (23), a brake device (24), a land driving device (25), a main wing (3), a tail wing (4), a flight driving device (5), a driver control device (6) and an electronic instrument and sensor (61); wherein the main wing (3) in turn comprises: a flap (31) and an aileron (32); the tail (4) in turn comprises: a horizontal tail (41), an elevator (42), a vertical tail (43), and a rudder (44); the flap (31) is arranged at the position, close to the vehicle body (2), of the rear edge of the main wing (3), and the aileron (32) is arranged at the position, far away from the vehicle body (2), of the rear edge of the main wing (3); the elevator (42) is arranged at the rear edge of a horizontal tail wing (41), and the rudder (44) is arranged at the rear edge of a vertical tail wing (43);

the flight driving device (5) is fixed on the vehicle body (2) and generates traction force or thrust to drive the whole flying vehicle to realize level flight; in the flying process, the multilayer continuous wing surface propeller (1) utilizes the spiral wing surface structure to cut and adapt to the windward rapid laminar flow or the crosswind laminar flow, thereby avoiding the problems of large wind resistance and unstable flight caused by the direct airflow impact on the blades and shock wave vibration generated at the wing tips of the blades caused by the windward or crosswind laminar flow when the common blade type propeller is adopted; the land driving device (25) is fixed on the vehicle body (2) and is connected with and drives the front wheel (22) and/or the rear wheel (23) to drive the whole aerocar to realize land driving; the main wings (3) on the two sides of the vehicle body (2) are symmetrically connected with a plurality of layers of continuous airfoil propellers (1) and a power unit (11) respectively, and the power unit (11) drives the plurality of layers of continuous airfoil propellers (1) to rotate and provide vertical lift;

the pilot control device (6) is also connected with a front wheel (22) or a rear wheel (23), a power unit (11), a flight driving device (5), a land driving device (25), a flap (31), an aileron (32), an elevator (42) and a rudder (44); when a driver drives, the driver operating device (6) is operated to control the rotation of the front wheels (22) or the rear wheels (23) to realize the land driving steering of the flying automobile; when a pilot drives, the pilot control device (6) is operated by the pilot to control the driving power of the driving unit (72), the power unit (11) and the flight driving device (5), the rotating speed of the multi-layer continuous wing propeller (1) is adjusted, and the deflection actions of the flap (31), the aileron (32), the elevator (42) and the rudder (44) are controlled, so that the flying automobile can realize the lifting, the landing, the hovering, the accelerating and decelerating flight, the flight rolling, the flight steering and the flight attitude adjustment.

2. A VTOL and fixed wing aerocar, comprising: the airplane comprises two multi-layer continuous wing surface propellers (1), two power units (11), a vehicle body (2), a buffer suspension (20), a cockpit and a passenger cabin (21), front wheels (22), rear wheels (23), a brake device (24), a land driving device (25), a main wing (3), a tail wing (4), a flight driving device (5), a driver control device (6), an electronic instrument and sensor (61) and a power supply and control device (7); wherein the main wing (3) in turn comprises: a flap (31) and an aileron (32); the tail (4) in turn comprises: a horizontal tail (41), an elevator (42), a vertical tail (43), and a rudder (44); the power supply and control device (7) further comprises: a battery unit (71), a drive unit (72), and a control unit (73); the flap (31) is arranged at the position, close to the vehicle body (2), of the rear edge of the main wing (3), and the aileron (32) is arranged at the position, far away from the vehicle body (2), of the rear edge of the main wing (3); the elevator (42) is arranged at the rear edge of a horizontal tail wing (41), and the rudder (44) is arranged at the rear edge of a vertical tail wing (43);

the multilayer continuous airfoil propeller (1) is of a multilayer continuous spiral airfoil structure and is connected and driven to rotate by a power unit (11); the wing root of the main wing (3) is fixed on two sides of the vehicle body (2); the tail wing (4) is fixed at the tail part of the vehicle body (2); the front wheel (22) is connected with the front part of the vehicle body (2) through a buffer suspension (20); the rear wheel (23) is connected to the rear part of the vehicle body (2) through a buffer suspension (20); the cockpit and the passenger cabin (21) are fixed on the vehicle body (2) and provide an operation position for a driver; the driver operating device (6) is arranged at a driving position in a driving cabin and a passenger cabin (21) and is used for the driver to operate and drive; the brake device (24) is arranged at the brake positions of the front wheel (22) and the rear wheel (23) nearby and is fixed on the buffer suspension (20); the brake device (24) is connected with the driver operating device (6) so that a driver operates the driver operating device (6) to drive the brake device (24) to perform brake action on the front wheel (22) and the rear wheel (23); the electronic instrument and sensor (61) is arranged in the cockpit and the passenger cabin (21), is fixed on the vehicle body (2) and is electrically connected with the control unit (73); the electronic instrument and the sensor (61) detect and display the land driving speed, the driving mileage, the endurance mileage, the flying height, the flying airspeed, the climbing and descending speed, the flying attitude, the flying course data and the operation data parameters and the control parameters of the power unit (11), the flying driving device (5), the land driving device (25) and the power supply and control device (7), and provide data reference for the driver to assist the driver in driving or flying; the flight driving device (5) is fixed on the vehicle body (2) and generates traction force or thrust to drive the whole flying vehicle to realize level flight; in the flying process, the multilayer continuous wing surface propeller (1) utilizes the spiral wing surface structure to cut and adapt to the windward rapid laminar flow or the crosswind laminar flow, thereby avoiding the problems of large wind resistance and unstable flight caused by the direct airflow impact on the blades and shock wave vibration generated at the wing tips of the blades caused by the windward or crosswind laminar flow when the common blade type propeller is adopted; the land driving device (25) is fixed on the vehicle body (2) and is connected with and drives the front wheel (22) and/or the rear wheel (23) to drive the whole aerocar to realize land driving; the main wings (3) on the two sides of the vehicle body (2) are symmetrically connected with a plurality of layers of continuous airfoil propellers (1) and a power unit (11) respectively, and the power unit (11) drives the plurality of layers of continuous airfoil propellers (1) to rotate and provide vertical lift;

the driving unit (72), the control unit (73), the driver operating device (6), the electronic instrument and the sensor (61) are electrically connected with the battery unit (71) and powered by the battery unit; the driving unit (72) is electrically connected with each power unit (11) and/or the flight driving device (5) and/or the land driving device (25) through different output channels to drive the power units to operate at output power; the control unit (73) is electrically connected with the driving unit (72) and the driver operating device (6) to output a control signal to the driving unit (72) and receive a control instruction from the driver operating device (6);

the driver control device (6) is also connected with a front wheel (22) or a rear wheel (23), a flap (31), an aileron (32), an elevator (42) and a rudder (44); the driver operating device (6) is also connected with each power unit (11) and/or flight driving device (5) and/or land driving device (25) to control the output of the power thereof; when a driver drives, the driver operating device (6) is operated to control the rotation of the front wheels (22) or the rear wheels (23) to realize the land driving steering of the flying automobile; when a pilot drives, the pilot control device (6) is operated by the pilot to control the driving power of the driving unit (72), the power unit (11) and the flight driving device (5), the rotating speed of the outer edge ring wing blade type propeller (1) is adjusted, and the deflection actions of the flap (31), the aileron (32), the elevator (42) and the rudder (44) are controlled, so that the flying automobile can realize lift-off, landing, hovering, accelerated and decelerated flight, flight rolling, flight steering and flight attitude adjustment.

3. A VTOL and fixed wing aerocar, comprising: the airplane comprises two multi-layer continuous wing surface propellers (1), two power units (11), a vehicle body (2), a buffer suspension (20), a cockpit and a passenger cabin (21), front wheels (22), rear wheels (23), a brake device (24), a land driving device (25), a main wing (3), a tail wing (4), a flight driving device (5), a driver control device (6), an electronic instrument and sensor (61), a power supply and driving control device (7), a plurality of steering engines (8), a communication transceiving unit (9) and a wireless remote control device (90); wherein the main wing (3) in turn comprises: a flap (31) and an aileron (32); the tail (4) in turn comprises: a horizontal tail (41), an elevator (42), a vertical tail (43), and a rudder (44); the power supply and control device (7) further comprises: a battery unit (71), a drive unit (72), and a control unit (73); the flap (31) is arranged at the position, close to the vehicle body (2), of the rear edge of the main wing (3), and the flap (31) is connected with a group of steering engines (8); the ailerons (32) are arranged at the positions, far away from the vehicle body (2), of the rear edge of the main wing (3), and the ailerons (32) are connected with a group of steering engines (8); the elevator (42) is arranged on the rear edge of the horizontal tail wing (41), the elevator (42) is connected with a group of steering engines (8), the rudder (44) is arranged on the rear edge of the vertical tail wing (43), and the rudder (44) is connected with a group of steering engines (8); meanwhile, the flap (31), the aileron (32), the elevator (42) and the rudder (44) are also connected with a driver operating device (6);

the driving unit (72), the control unit (73), the driver operating device (6), the communication transceiving unit (9) and the electronic instrument and sensor (61) are electrically connected with the battery unit (71) and powered by the battery unit; the driving unit (72) is electrically connected with each group of steering engines (8) through different output channels to drive and control the control surface deflection actions of the flaps (31), the ailerons (32), the elevators (42) and the rudders (44); the driving unit (72) is electrically connected with the power unit (11) and/or the flight driving device (5) and/or the land driving device (25) by different output channels so as to drive and control the operation of the power unit and/or the flight driving device with output power; the control unit (73) is electrically connected with the driving unit (72) and the driver operating device (6) to output a control signal to the driving unit (72) and receive a control instruction from the driver operating device (6); the control unit (73) is also electrically connected with the communication transceiving unit (9) to receive a control instruction from the communication transceiving unit (9);

the driver operating device (6) is also connected with each power unit (11) and/or flight driving device (5) and/or land driving device (25) to control the output of the power thereof; the driver operating device (6) is also connected with a front wheel (22) or a rear wheel (23); when a driver drives, the driver operating device (6) is operated to control the rotation of the front wheels (22) or the rear wheels (23) to realize the land driving steering of the flying automobile; when a pilot drives, the pilot control device (6) is operated by the pilot to control the output power of the driving unit (72) and/or the power unit (11) and/or the flight driving device (5) and/or the land driving device (25), the rotating speed of the outer edge ring wing blade type propeller (1) is adjusted, and the deflection actions of the flap (31), the aileron (32), the elevator (42) and the rudder (44) are controlled, so that the aerocar can realize land advancing, backing and accelerating and decelerating running, and the ascending, landing, hovering, accelerating and decelerating flight, flight rolling, flight steering and flight attitude adjustment;

when remotely controlling the aerial flight, a user operates the wireless remote control device (90) to wirelessly control the driving power of the flight driving device (5) through the communication transceiving unit (9), adjusts the rotating speed of the outer edge ring wing blade type propeller (1), and controls the deflection actions of the flap (31), the aileron (32), the elevator (42) and the rudder (44), so that the flying automobile realizes the lifting, the landing, the hovering, the accelerating and decelerating flight, the flight rolling, the flight steering and the flight attitude adjustment; when the flying automobile is remotely controlled to run on the land, a user operates the wireless remote control device (90) and the control unit (73) to send an operation instruction to the driver operation device (6), and the driving power of the land driving device (25) is adjusted through the driver operation device (6), so that the flying automobile can realize forward running, reverse running and acceleration and deceleration running on the land.

4. A VTOL and fixed wing aerocar, comprising: the airplane comprises two multi-layer continuous wing surface propellers (1), two power units (11), a vehicle body (2), a buffer suspension (20), a cockpit and a passenger cabin (21), front wheels (22), rear wheels (23), a brake device (24), a land driving device (25), a main wing (3), a tail wing (4), a flight driving device (5), a driver control device (6), an electronic instrument and sensor (61), a power supply and driving control device (7), a plurality of steering engines (8), a communication transceiving unit (9) and a wireless remote control device (90); wherein the main wing (3) in turn comprises: a flap (31) and an aileron (32); the tail (4) in turn comprises: a horizontal tail (41), an elevator (42), a vertical tail (43), and a rudder (44); the power supply and control device (7) further comprises: a battery unit (71), a drive unit (72), and a control unit (73); the flap (31) is arranged at the position, close to the vehicle body (2), of the rear edge of the main wing (3), and the flap (31) is connected with a group of steering engines (8); the ailerons (32) are arranged at the positions, far away from the vehicle body (2), of the rear edge of the main wing (3), and the ailerons (32) are connected with a group of steering engines (8); the elevator (42) is arranged on the rear edge of the horizontal tail wing (41), the elevator (42) is connected with a group of steering engines (8), the rudder (44) is arranged on the rear edge of the vertical tail wing (43), and the rudder (44) is connected with a group of steering engines (8); meanwhile, the flap (31), the aileron (32), the elevator (42) and the rudder (44) are also connected with a driver operating device (6);

each group of steering engines (8), driving units (72), control units (73), driver operating devices (6), communication transceiving units (9) and electronic instruments and sensors (61) are electrically connected with a battery unit (71) and powered by the battery unit; the driving unit (72) is electrically connected with the power unit (11) and/or the flight driving device (5) and/or the land driving device (25) by different output channels so as to drive and control the operation of the power unit and/or the flight driving device with output power; the control unit (73) is electrically connected with the driving unit (72) and the driver operating device (6) to output a control signal to the driving unit (72) and receive a control instruction from the driver operating device (6); the control unit (73) is also electrically connected with the communication transceiving unit (9) to receive a control instruction from the communication transceiving unit (9);

the driver operating device (6) is also connected with each power unit (11) and/or flight driving device (5) and/or land driving device (25) to control the output of the power thereof; the driver control device (6) is also electrically connected with each group of steering engines (8) and directly electrically controls each group of steering engines (8), so that each group of steering engines (8) is directly controlled to drive and control the deflection action of the control surfaces of the flaps (31), the ailerons (32), the elevators (42) and the rudders (44); the driver operating device (6) is also connected with a front wheel (22) or a rear wheel (23); when a driver drives, the driver operating device (6) is operated to control the rotation of the front wheels (22) or the rear wheels (23) to realize the land driving steering of the flying automobile; when a pilot drives, the pilot control device (6) is operated by the pilot to control the output power of the driving unit (72) and/or the power unit (11) and/or the flight driving device (5) and/or the land driving device (25), the rotating speed of the outer edge ring wing blade type propeller (1) is adjusted, and the deflection actions of the flap (31), the aileron (32), the elevator (42) and the rudder (44) are controlled, so that the aerocar can realize land advancing, backing and accelerating and decelerating running, and the ascending, landing, hovering, accelerating and decelerating flight, flight rolling, flight steering and flight attitude adjustment;

5. The VTOL and fixed-wing flying automobile of any one of claims 1-4, further comprising: a clutch and gearbox (26) and/or a camera device (64) and/or a pan-tilt (65) and/or an inertial measurement unit (62) and/or an electronic compass (66) and/or a barometer (67) and/or a satellite positioning module (63); the clutch and gearbox (26), the clutch and gearbox (26) and the land driving device (25) are fixed on the vehicle body (2), the land driving device (25) is connected with the clutch and gearbox (26), the clutch and gearbox (26) is connected with the driving front wheels (22) and/or the rear wheels (23), the land driving device (25) provides driving force to drive the front wheels (22) and/or the rear wheels (23) to drive the whole aerocar to realize land driving through the clutch and speed change link of the clutch and gearbox (26); the clutch and gearbox (26) is also connected with a driver operating device (6), so that a driver operates the clutch and gearbox (26) through the driver operating device (6) to perform clutch action and adjust the power transmission ratio of the land driving device (25) to the front wheels (22) and/or the rear wheels (23); the camera device (64) is fixed on the vehicle body (2), the camera device (64) is electrically connected to the power supply and the driving and controlling device (7), the power supply of the camera device (64) is controlled by the camera device (64) to be powered on and shoot, and the camera device (64) is used for recording, shooting and locally storing images or videos; or the camera device (64) is also arranged on the tripod head (65), the tripod head (65) is fixed on the vehicle body (2), the tripod head (65) provides fixing, supporting and mounting positions for the camera device (64), provides stability-increasing and anti-shaking functions for the camera device (64), and adjusts the horizontal and pitching shooting angles of the camera device (64), and the tripod head (65) is electrically connected with the power supply and the driving and controlling device (7) and is used for supplying power and controlling the electrifying and rotating shooting actions of the tripod head (65); or the camera device (64) also realizes wireless image transmission through the communication transceiving unit (9) and the wireless remote control device (90) and is used for realizing auxiliary flight under the wireless remote control remote monitoring operation of the hovercar in a remote control flight mode; the inertial measurement unit (62) is arranged on the vehicle body (2) and is electrically connected to the control unit (73), the inertial measurement unit (62) measures three-dimensional position, three-dimensional speed, three-dimensional acceleration, three-axis angle, three-dimensional angular velocity, flight direction and flight altitude signals and transmits the signals to the control unit (73), and the control unit (73) resolves, optimizes and compensates the current flying vehicle attitude according to the flight motion data; the control unit (73) is also electrically connected with the communication transceiving unit (9) and wirelessly transmits the flight motion data of the aerocar to the wireless remote control device (90) through the communication transceiving unit (9) for parameter display; the electronic compass (66) is fixed on the vehicle body (2), is electrically connected with the control unit (73) and the battery unit (71), and is used for separately measuring flight direction data and transmitting the flight direction data to the control unit (73) for being used as a flight direction data reference; the barometer (67) is also fixed on the vehicle body (2), is electrically connected with the control unit (73) and the battery unit (71), and is used for separately measuring the flying height data and transmitting the flying height data to the control unit (73) to be used as a flying height data reference; the satellite positioning module (63) is also fixed on the vehicle body (2) and is electrically connected with the control unit (73) and the battery unit (71), and the satellite positioning module measures satellite positioning data to provide data reference for a driver to assist the driver in realizing navigation flight; or the control unit (73) wirelessly transmits the satellite positioning data to the wireless remote control device (90) through the communication transceiving unit (9) for providing data reference for a user to assist the user in realizing wireless remote control flight and facilitating positioning and recovery after loss in a remote control flight mode of the aerocar.

6. The VTOL and fixed-wing flying automobile of any one of claims 2-4, further comprising: a fuel power generation device (70); the fuel oil power generation device (70) is fixedly arranged on the vehicle body (2); the fuel oil power generation device (70) is electrically connected with a battery unit (71) in the power supply and control unit (7); the fuel oil power generation device (70) mainly comprises a fuel oil engine and a generator, and the fuel oil engine and the generator are driven to generate power by burning the carried fuel to charge the battery unit (71) in an extended range mode.

7. A VTOL and fixed wing hovercar according to any of claims 1 to 4 characterized in that the main wing (3) is a single layer wing, or a double layer wing, or a multi-layer wing; the main wing (3) is an unfoldable wing or a foldable wing; the buffer suspension (20) adopts a non-independent suspension system, an independent suspension system or a folding suspension system; the tail wing (4) also adopts a V-shaped tail wing, the V-shaped tail wing is formed by a left wing surface and a right wing surface which are in a V shape, the V-shaped tail wing has the functions of a vertical tail and a horizontal tail, and the rear edges of the two wing surfaces of the V-shaped tail wing are provided with deflection control surfaces; the deflection control surface is connected with a driver control device (6) or a steering engine (8) for controlling the action of the deflection control surface of the tail wing (4); the number of the front wheels (22) is one, or two or more; the number of the rear wheels (23) is one, two or more.

8. The VTOL and fixed-wing hovercar according to any one of claims 1 to 4, wherein the airfoil of the multi-layer continuous airfoil propeller (1) is provided with continuous guide grooves, continuous guide bosses, continuous guide winglets, intermittent guide grooves, intermittent guide bosses, intermittent guide winglets, intermittent guide through holes, scattered guide grooves, scattered guide bosses, scattered guide winglets or scattered guide through holes near the edge of the airfoil to prevent the airflow boundary layer from centrifugally flowing towards the edge of the airfoil during the high-speed rotation of the multi-layer continuous airfoil propeller (1) and inhibit the separation of the boundary layer at the edge of the airfoil; the continuous airfoil of the multilayer continuous airfoil propeller (1) is a single-sheet spiral continuous airfoil, or a double-sheet oppositely-overlapped spiral continuous airfoil, or a plurality of axisymmetric overlapped spiral continuous airfoils; the number of the spiral airfoil layers of the multilayer continuous airfoil propeller (1) is two, three or more; the axial vertical projection shape of the multilayer continuous airfoil propeller (1) is circular, or oval, or regular polygon, or triangle with round angle, or square with round angle; the side vertical projection shape of the multilayer continuous airfoil propeller (1) is square, or diamond, or shuttle, or triangle, or 8-shaped, or square with wavy teeth on two sides.

9. A VTOL and fixed wing aerocar according to any of claims 1-4, wherein the power unit (11) or land drive (25) is a piston engine, or a rotary engine, or a turboshaft engine, or an electric motor; the flight driving device (5) adopts a pulse jet engine, a turbojet engine, a turbofan engine, a turboprop engine, an electric turbojet engine, a piston engine driving blade type propeller, a rotor engine driving blade type propeller, a turbine shaft engine driving blade type propeller, a motor driving blade type propeller, a battery driving motor driving blade type propeller, or a fuel power generation device driving motor driving blade type propeller; the number of the multilayer continuous airfoil propellers (1) or the power units (11) is two or more; the multilayer continuous wing surface propellers (1) are arranged on two sides of the vehicle body (2), or arranged on the main wings (3) on two sides of the vehicle body (2) and the horizontal tail wing (41) at the same time; the power unit (11) drives one multilayer continuous airfoil propeller (1) one by one, or the power unit (11) drives two multilayer continuous airfoil propellers (1) one by one; the number of the flight driving devices (5) is one, or two, or more; the flight driving device (5) is arranged at the nose position of the vehicle body (2), or in the middle of the vehicle body (2), or at the top of the vehicle body (2), or at the two sides of the vehicle body (2), or at the tail of the vehicle body (2), or on the main wings (3) at the two sides of the vehicle body (2).

10. The VTOL and fixed wing hovercar of claim 3 or 4 characterized in that, the communication transceiver unit (9) and the wireless remote control device (90) adopt a passive remote control circuit of a mineral radio, or a WLAN communication module, or a Bluetooth communication module, or a ZigBee communication module, or a 4G/5G communication module to realize wireless communication and control between the two; the wireless remote control device (90) comprises a mobile phone, a remote control wrist strap, brain wave control glasses, remote control VR glasses, a remote control VR helmet, an image control helmet, a ground remote control station, a flight control remote controller or a flight control network platform.

Technical Field

The invention relates to the field of vehicles and flying automobiles, in particular to two manned vertical take-off and landing and fixed-wing flying automobiles and two manned vertical take-off and landing and fixed-wing flying automobiles with wireless remote control functions.

Background

With the development of science and technology, automobiles become the main means of transportation for people to go out daily, traffic jam at working peaks becomes a common problem. The flying automobile is born, can become an ideal vehicle, and can be converted into a flying mode to realize travel when the surface is blocked. Most of the conventional flying automobiles are multi-rotor flying automobiles and fixed-wing flying automobiles. The multi-rotor type hovercar still needs multi-rotor rotation to maintain after being lifted off, so that the air endurance time of the hovercar is not prolonged, and the fixed-wing hovercar needs to take off from a runway to be lifted off, so that the use is inconvenient.

Therefore, a vertical take-off and landing and fixed-wing aerocar which has the advantages of better consideration of vertical take-off and landing, fixed-wing flight, high endurance, realization of medium-high-speed stable flight, simple structure, easiness in control and lower cost needs to be provided.

If a new aerocar adopts a general blade type propeller lift unit, the blade type propeller needs to be stopped to ensure high endurance, and at the moment, the static blade type propeller faces airflow impact during high-speed flat flight to generate turbulence, so that the flight is unstable; in addition, when the aerocar flies at high speed, the laminar flow of the windward or crosswind can directly generate airflow impact on the blades, the wing tips of the blades can also generate shock wave vibration, and the aerocar is easy to fly unstably; the problems of large wind resistance and easy yaw caused by wind blowing during hovering exist; therefore, the aerocar needs to adopt a new structural scheme on the vertical lift unit to adapt to high-speed laminar flow in the process of flat flight, and can simply decompose the flight motion control into vertical take-off and landing control and flat flight acceleration and deceleration control from the control aspect so as to realize vertical take-off and landing, fixed wing horizontal flight and land acceleration and deceleration landing running.

Disclosure of Invention

The invention provides four types of vertical take-off and landing and fixed-wing flying automobiles, which are respectively two types of manned vertical take-off and landing and fixed-wing flying automobiles and two types of vertical take-off and landing and fixed-wing flying automobiles with manned and wireless remote control functions, and the technical scheme is realized as follows:

scheme 1, a VTOL and fixed wing hovercar includes: two multi-layer continuous wing surface propellers 1, two power units 11, a vehicle body 2, a buffer suspension 20, a cockpit and passenger cabin 21, a front wheel 22, a rear wheel 23, a brake device 24, a land driving device 25, a main wing 3, a tail wing 4, a flight driving device 5, a driver operating device 6, an electronic instrument and a sensor 61; wherein the main wing 3 in turn comprises: flaps 31 and ailerons 32; said tail 4 in turn comprises: horizontal tail 41, elevator 42, vertical tail 43, and rudder 44; the flap 31 is arranged at the position where the rear edge of the main wing 3 is close to the vehicle body 2, and the aileron 32 is arranged at the position where the rear edge of the main wing 3 is far away from the vehicle body 2; the elevator 42 is arranged at the rear edge of the horizontal tail 41, and the rudder 44 is arranged at the rear edge of the vertical tail 43;

the multilayer continuous airfoil propeller 1 is of a multilayer continuous spiral airfoil structure and is connected and driven to rotate by a power unit 11; the wing root of the main wing 3 is fixed on two sides of the vehicle body 2; the tail wing 4 is fixed at the tail part of the vehicle body 2; the front wheel 22 is connected to the front part of the vehicle body 2 through a buffer suspension 20; the rear wheel 23 is connected to the rear part of the vehicle body 2 through a buffer suspension 20; the cockpit and the passenger cabin 21 are fixed on the vehicle body 2 and provide a control position for a driver; the driver operating device 6 is arranged in a driving position in the cab and the passenger compartment 21 and is used for operating and driving by a driver; the brake device 24 is arranged at the brake positions of the front wheel 22 and the rear wheel 23 nearby and is fixed on the buffer suspension 20; the brake device 24 is connected to the driver operating device 6, so that the driver operates the driver operating device 6 to drive the brake device 24 to perform braking action on the front wheels 22 and the rear wheels 23; the electronic instrument and sensor 61 is arranged in the cockpit and the passenger cabin 21 and fixed on the vehicle body 2, the electronic instrument and sensor 61 detects and displays the land driving speed, the driving mileage, the endurance mileage, the flying height, the flying airspeed, the climbing and descending speed, the flying attitude, the flying course data and the operation data parameters and the control parameters of the power unit 11 and the flying drive-in device 5, and provides data reference for the driver to assist the driver in driving or flying; the flight driving device 5 is fixed on the vehicle body 2 and generates traction or thrust to drive the whole flying vehicle to realize level flight; in the flying process, the multilayer continuous wing surface propeller 1 utilizes the spiral wing surface structure to cut and adapt to the windward rapid laminar flow or the crosswind laminar flow, thereby avoiding the problems of large wind resistance and unstable flight caused by the direct airflow impact on the blades and shock wave vibration generated at the wing tips of the blades caused by the windward or crosswind laminar flow when the common blade type propeller is adopted; the land driving device 25 is fixed on the vehicle body 2 and is connected with and drives the front wheel 22 and/or the rear wheel 23 to drive the whole hovercar to realize land driving; the main wings 3 on two sides of the vehicle body 2 are symmetrically connected with a plurality of layers of continuous airfoil propellers 1 and a power unit 11 respectively, and the power unit 11 drives the plurality of layers of continuous airfoil propellers 1 to rotate and provide vertical lift force;

the pilot control device 6 is also connected with a front wheel 22 or a rear wheel 23, a power unit 11, a flight propulsion device 5, a land driving device 25, a flap 31, an aileron 32, an elevator 42 and a rudder 44; when driving, the driver operates the driver operating device 6 to control the rotation of the front wheels 22 or the rear wheels 23 to realize the land driving steering of the aerocar; when a pilot operates the pilot operating device 6 to control the driving power of the driving unit 72, the power unit 11 and the flight driving device 5, adjust the rotating speed of the multi-layer continuous wing propeller 1, and operate the deflection actions of the flaps 31, the ailerons 32, the elevators 42 and the rudders 44, so that the flying automobile can realize lift-off, landing, hovering, acceleration and deceleration flight, flying and rolling, flight steering and flight attitude adjustment.

Scheme 2, a VTOL and fixed wing hovercar includes: the system comprises two multi-layer continuous wing surface propellers 1, two power units 11, a vehicle body 2, a buffer suspension 20, a cockpit and passenger cabin 21, front wheels 22, rear wheels 23, a brake device 24, a land driving device 25, a main wing 3, a tail wing 4, a flight driving device 5, a driver operating device 6, an electronic instrument and sensor 61 and a power supply and control device 7; wherein the main wing 3 in turn comprises: flaps 31 and ailerons 32; said tail 4 in turn comprises: horizontal tail 41, elevator 42, vertical tail 43, and rudder 44; the power supply and control device 7 further comprises: a battery unit 71, a drive unit 72, a control unit 73; the flap 31 is arranged at the position where the rear edge of the main wing 3 is close to the vehicle body 2, and the aileron 32 is arranged at the position where the rear edge of the main wing 3 is far away from the vehicle body 2; the elevator 42 is arranged at the rear edge of the horizontal tail 41, and the rudder 44 is arranged at the rear edge of the vertical tail 43;

the multilayer continuous airfoil propeller 1 is of a multilayer continuous spiral airfoil structure and is connected and driven to rotate by a power unit 11; the wing root of the main wing 3 is fixed on two sides of the vehicle body 2; the tail wing 4 is fixed at the tail part of the vehicle body 2; the front wheel 22 is connected to the front part of the vehicle body 2 through a buffer suspension 20; the rear wheel 23 is connected to the rear part of the vehicle body 2 through a buffer suspension 20; the cockpit and the passenger cabin 21 are fixed on the vehicle body 2 and provide a control position for a driver; the driver operating device 6 is arranged in a driving position in the cab and the passenger compartment 21 and is used for operating and driving by a driver; the brake device 24 is arranged at the brake positions of the front wheel 22 and the rear wheel 23 nearby and is fixed on the buffer suspension 20; the brake device 24 is connected to the driver operating device 6, so that the driver operates the driver operating device 6 to drive the brake device 24 to perform braking action on the front wheels 22 and the rear wheels 23; the electronic instrument and sensor 61 is arranged in the cockpit and the passenger compartment 21, fixed to the vehicle body 2, and electrically connected to the control unit 73; the electronic instrument and sensor 61 detects and displays the land driving speed, the driving mileage, the endurance mileage, the flying height, the flying airspeed, the climbing and descending speed, the flying attitude, the flying course data and the operation data parameters and the control parameters of the power unit 11, the flying driving device 5, the land driving device 25 and the power supply and control device 7, and provides data reference for the driver to assist the driver in driving or flying; the flight driving device 5 is fixed on the vehicle body 2 and generates traction or thrust to drive the whole flying vehicle to realize level flight; in the flying process, the multilayer continuous wing surface propeller 1 utilizes the spiral wing surface structure to cut and adapt to the windward rapid laminar flow or the crosswind laminar flow, thereby avoiding the problems of large wind resistance and unstable flight caused by the direct airflow impact on the blades and shock wave vibration generated at the wing tips of the blades caused by the windward or crosswind laminar flow when the common blade type propeller is adopted; the land driving device 25 is fixed on the vehicle body 2 and is connected with and drives the front wheel 22 and/or the rear wheel 23 to drive the whole hovercar to realize land driving; the main wings 3 on two sides of the vehicle body 2 are symmetrically connected with a plurality of layers of continuous airfoil propellers 1 and a power unit 11 respectively, and the power unit 11 drives the plurality of layers of continuous airfoil propellers 1 to rotate and provide vertical lift force;

the driving unit 72, the control unit 73, the driver operating device 6, the electronic meter and the sensor 61 are electrically connected with the battery unit 71 to supply power; the driving unit 72 is electrically connected with each power unit 11 and/or the flight driving device 5 and/or the land driving device 25 through different output channels to drive the operation of the flight driving device and/or the land driving device with output power; the control unit 73 electrically connects the drive unit 72 and the driver manipulating device 6 to output a control signal to the drive unit 72 and receive a control instruction from the driver manipulating device 6;

the pilot control device 6 is also connected with a front wheel 22 or a rear wheel 23, a flap 31, an aileron 32, an elevator 42 and a rudder 44; the pilot control device 6 is also connected to the respective power unit 11 and/or to the flight propulsion device 5 and/or to the land propulsion device 25 to control the output of their power; when driving, the driver operates the driver operating device 6 to control the rotation of the front wheels 22 or the rear wheels 23 to realize the land driving steering of the aerocar; when a pilot drives, the pilot control device 6 is operated by the pilot to control the driving power of the driving unit 72, the power unit 11 and the flight driving device 5, the rotating speed of the outer edge ring wing blade type propeller 1 is adjusted, and the deflection actions of the flaps 31, the ailerons 32, the elevators 42 and the rudders 44 are controlled, so that the flying automobile can realize the functions of lifting, landing, hovering, accelerating and decelerating flight, flying and rolling, flight steering and flight attitude adjustment.

Scheme 3, a VTOL and fixed wing hovercar includes: the system comprises two multi-layer continuous wing surface propellers 1, two power units 11, a vehicle body 2, a buffer suspension 20, a cockpit and passenger cabin 21, front wheels 22, rear wheels 23, a brake device 24, a land driving device 25, a main wing 3, a tail wing 4, a flight driving device 5, a driver operating device 6, an electronic instrument and sensor 61, a power supply and control device 7, a plurality of steering engines 8, a communication transceiving unit 9 and a wireless remote control device 90; wherein the main wing 3 in turn comprises: flaps 31 and ailerons 32; said tail 4 in turn comprises: horizontal tail 41, elevator 42, vertical tail 43, and rudder 44; the power supply and control device 7 further comprises: a battery unit 71, a drive unit 72, a control unit 73; the flap 31 is arranged at the position, close to the vehicle body 2, of the rear edge of the main wing 3, and the flap 31 is connected with a group of steering engines 8; the ailerons 32 are arranged at the positions, far away from the vehicle body 2, of the rear edge of the main wing 3, and the ailerons 32 are connected with a group of steering engines 8; the elevator 42 is arranged on the rear edge of the horizontal tail wing 41, the elevator 42 is connected with a group of steering engines 8, the rudder 44 is arranged on the rear edge of the vertical tail wing 43, and the rudder 44 is connected with a group of steering engines 8; meanwhile, the flap 31, the aileron 32, the elevator 42 and the rudder 44 are also connected with a pilot control device 6;

the flight driving device 5 is fixed on the vehicle body 2 and generates traction or thrust to drive the whole flying vehicle to realize level flight; in the flying process, the multilayer continuous wing surface propeller 1 utilizes the spiral wing surface structure to cut and adapt to the windward rapid laminar flow or the crosswind laminar flow, thereby avoiding the problems of large wind resistance and unstable flight caused by the direct airflow impact on the blades and shock wave vibration generated at the wing tips of the blades caused by the windward or crosswind laminar flow when the common blade type propeller is adopted; the land driving device 25 is fixed on the vehicle body 2 and is connected with and drives the front wheel 22 and/or the rear wheel 23 to drive the whole hovercar to realize land driving; the main wings 3 on two sides of the vehicle body 2 are symmetrically connected with a plurality of layers of continuous airfoil propellers 1 and a power unit 11 respectively, and the power unit 11 drives the plurality of layers of continuous airfoil propellers 1 to rotate and provide vertical lift force;

the driving unit 72, the control unit 73, the driver operating device 6, the communication transceiving unit 9, the electronic instrument and the sensor 61 are electrically connected with the battery unit 71 to supply power; the driving unit 72 is electrically connected with each group of steering engines 8 through different output channels to drive and operate the control surface deflection actions of the flaps 31, the ailerons 32, the elevators 42 and the rudders 44; the driving unit 72 is electrically connected with the power unit 11 and/or the flight driving device 5 and/or the land driving device 25 by different output channels, so as to output power to drive and control the operation of the flight driving device and/or the land driving device; the control unit 73 electrically connects the drive unit 72 and the driver manipulating device 6 to output a control signal to the drive unit 72 and receive a control instruction from the driver manipulating device 6; the control unit 73 is also electrically connected with the communication transceiving unit 9 to receive a control instruction from the communication transceiving unit 9;

when remotely controlling the air flight, a user operates the wireless remote control device 90 to wirelessly control the driving power of the flight driving device 5 through the communication transceiving unit 9, adjusts the rotating speed of the outer edge ring wing blade type propeller 1, and controls the deflection actions of the wing flap 31, the aileron 32, the elevator 42 and the rudder 44, so that the hovercar realizes the lift-off, landing, hovering, acceleration and deceleration flight, flight rolling, flight steering and flight attitude adjustment; when the flying vehicle is remotely controlled to travel on land, a user operates the wireless remote control device 90 and the control unit 73 to send an operation instruction to the driver operation device 6, and the driving power of the land driving device 25 is adjusted through the driver operation device 6, so that the flying vehicle can travel on land in a forward, reverse and acceleration and deceleration mode.

Scheme 4, a VTOL and fixed wing hovercar includes: the system comprises two multi-layer continuous wing surface propellers 1, two power units 11, a vehicle body 2, a buffer suspension 20, a cockpit and passenger cabin 21, front wheels 22, rear wheels 23, a brake device 24, a land driving device 25, a main wing 3, a tail wing 4, a flight driving device 5, a driver operating device 6, an electronic instrument and sensor 61, a power supply and control device 7, a plurality of steering engines 8, a communication transceiving unit 9 and a wireless remote control device 90; wherein the main wing 3 in turn comprises: flaps 31 and ailerons 32; said tail 4 in turn comprises: horizontal tail 41, elevator 42, vertical tail 43, and rudder 44; the power supply and control device 7 further comprises: a battery unit 71, a drive unit 72, a control unit 73; the flap 31 is arranged at the position, close to the vehicle body 2, of the rear edge of the main wing 3, and the flap 31 is connected with a group of steering engines 8; the ailerons 32 are arranged at the positions, far away from the vehicle body 2, of the rear edge of the main wing 3, and the ailerons 32 are connected with a group of steering engines 8; the elevator 42 is arranged on the rear edge of the horizontal tail wing 41, the elevator 42 is connected with a group of steering engines 8, the rudder 44 is arranged on the rear edge of the vertical tail wing 43, and the rudder 44 is connected with a group of steering engines 8; meanwhile, the flap 31, the aileron 32, the elevator 42 and the rudder 44 are also connected with a pilot control device 6;

each group of steering engines 8, driving units 72, control units 73, driver operating devices 6, communication transceiving units 9, electronic instruments and sensors 61 are electrically connected with and powered by a battery unit 71; the driving unit 72 is electrically connected with the power unit 11 and/or the flight driving device 5 and/or the land driving device 25 by different output channels so as to output power to drive and control the operation of the flight driving device and/or the land driving device 25; the control unit 73 electrically connects the drive unit 72 and the driver manipulating device 6 to output a control signal to the drive unit 72 and receive a control instruction from the driver manipulating device 6; the control unit 73 is also electrically connected with the communication transceiving unit 9 to receive a control instruction from the communication transceiving unit 9;

the pilot control device 6 is also connected to the respective power unit 11 and/or to the flight propulsion device 5 and/or to the land propulsion device 25 to control the output of their power; the driver control device 6 is also electrically connected with each group of steering engines 8, and direct electric control is implemented on each group of steering engines 8, so that each group of steering engines 8 is directly controlled to drive and control the deflection action of the control surfaces of the flaps 31, the ailerons 32, the elevators 42 and the rudders 44; the driver operating device 6 is also connected with a front wheel 22 or a rear wheel 23; when driving, the driver operates the driver operating device 6 to control the rotation of the front wheels 22 or the rear wheels 23 to realize the land driving steering of the aerocar; when a pilot operates the pilot operating device 6 to control the output power of the driving unit 72 and/or the power unit 11 and/or the flight driving device 5 and/or the land driving device 25, adjust the rotating speed of the outer edge ring wing blade type propeller 1, and operate the deflection actions of the flaps 31, the ailerons 32, the elevator 42 and the rudder 44, so that the flying automobile realizes land advancing, backing and accelerating and decelerating running, and realizes lift-off, landing, hovering, accelerating and decelerating flight, flying roll, flight steering and flight attitude adjustment;

Further, the four types of vtol and fixed-wing hovercar described in schemes 1-4 further include: clutch and gearbox 26 and/or camera device 64 and/or pan-tilt 65 and/or inertial measurement unit 62 and/or electronic compass 66 and/or barometer 67 and/or satellite positioning module 63; the clutch and gearbox 26, the clutch and gearbox 26 and the land driving device 25 are fixed on the vehicle body 2, the land driving device 25 is connected with the clutch and gearbox 26, the clutch and gearbox 26 is connected with the front wheel 22 and/or the rear wheel 23, the land driving device 25 provides driving force to drive the front wheel 22 and/or the rear wheel 23 to drive the whole hovercar to realize land driving through the clutch and gearbox 26 in the clutch and speed change link; the clutch and gearbox 26 is also connected with the driver operating device 6, so that the driver can operate the clutch and gearbox 26 through the driver operating device 6 to perform clutch action and adjust the power transmission ratio of the land driving device 25 to the front wheels 22 and/or the rear wheels 23; camera 64 and/or pan-tilt 65 and/or inertial measurement unit 62 and/or electronic compass 66 and/or barometer 67 and/or satellite positioning module 63; the camera device 64 is fixed on the vehicle body 2, the camera device 64 is electrically connected to the power supply and the control device 7, the power supply of the camera device 64 is controlled by the camera device 64, and the camera device 64 is used for recording, shooting and locally storing images or videos; or, the camera device 64 is further arranged on the cradle head 65, the cradle head 65 is fixed on the vehicle body 2, the cradle head 65 provides fixing, supporting and mounting positions for the camera device 64, provides stability-enhancing and anti-shake functions for the camera device 64, and adjusts the horizontal and pitching shooting angles of the camera device 64, and the cradle head 65 is electrically connected to the power supply and the control device 7 to supply power thereto and controls the electrifying and rotating shooting actions of the cradle head 65; or, the camera 64 also realizes wireless image transmission with the wireless remote control device 90 through the communication transceiver unit 9, and is used for realizing auxiliary flight under wireless remote control remote monitoring operation of the hovercar in a remote control flight mode; the inertial measurement unit 62 is arranged on the vehicle body 2 and is electrically connected to the control unit 73, the inertial measurement unit 62 measures three-dimensional position, three-dimensional velocity, three-dimensional acceleration, three-axis angle, three-dimensional angular velocity, flight direction and flight altitude signals and transmits the signals to the control unit 73, and the control unit 73 performs resolving, optimizing and error compensating on the current flying vehicle attitude according to the flight motion data; the control unit 73 is also electrically connected with the communication transceiving unit 9, and wirelessly transmits the flight motion data of the hovercar to the wireless remote control device 90 through the communication transceiving unit 9 for parameter display; the electronic compass 66 is fixed on the vehicle body 2, is electrically connected with the control unit 73 and the battery unit 71, and is used for separately measuring flight direction data and transmitting the flight direction data to the control unit 73 to be used as a flight direction data reference; the barometer 67 is also fixed to the vehicle body 2, is electrically connected to the control unit 73 and the battery unit 71, and separately measures the flying height data and transmits the flying height data to the control unit 73 to be used as a flying height data reference; the satellite positioning module 63 is also fixed to the vehicle body 2, is electrically connected to the control unit 73 and the battery unit 71, and is used for measuring satellite positioning data to provide data reference for a driver to assist the driver in realizing navigation flight; or, the control unit 73 wirelessly transmits the satellite positioning data to the wireless remote control device 90 through the communication transceiving unit 9, so that the hovercar provides data reference for the user to assist the user in realizing wireless remote control flight and facilitating positioning and recovery after loss in the remote control flight mode.

Further, the three types of vtol and fixed-wing hovercar described in schemes 2-4 further include: a fuel power generation device 70; the fuel oil power generation device 70 is fixedly mounted on the vehicle body 2; the fuel power generation device 70 is electrically connected to the battery unit 71 in the power supply and control unit 7; the fuel power generation device 70 mainly comprises a fuel engine and a generator, and generates power to drive the generator to generate power by burning fuel carried by the fuel engine, so as to charge the battery unit 71 in an extended range manner.

Preferably, in the embodiments 1 to 4, the main wing 3 is a single-layer wing, or a double-layer wing, or a multi-layer wing; the main wing 3 is an unfoldable wing or a foldable wing; the buffer suspension 20 adopts a non-independent suspension system, or an independent suspension system, or a folding suspension system; the tail 4 also adopts a V-shaped tail which is formed by a left wing surface and a right wing surface in a V shape, the V-shaped tail has the functions of a vertical tail and a horizontal tail, and the rear edges of the two wing surfaces of the V-shaped tail are provided with deflection control surfaces; the deflection control surface is connected with a driver control device 6 or a steering engine 8 for controlling the action of the deflection control surface of the tail wing 4; the number of the front wheels 22 is one, two or more; the number of the rear wheels 23 is also one, two or more.

Preferably, in the schemes 1 to 4, the continuous guide grooves, or the continuous guide bosses, or the continuous guide blades, or the intermittent guide grooves, or the intermittent guide bosses, or the intermittent guide blades, or the intermittent guide through holes, or the scattering guide grooves, or the scattering guide bosses, or the scattering guide blades, or the scattering guide through holes are arranged on the airfoil surface of the multilayer continuous airfoil propeller 1 near the airfoil edge, so as to prevent the airflow boundary layer from centrifugally flowing towards the airfoil edge direction during the high-speed rotation of the multilayer continuous airfoil propeller 1 and inhibit the boundary layer separation at the airfoil edge part; the continuous airfoil of the multilayer continuous airfoil propeller 1 is a single-sheet spiral continuous airfoil, or a double-sheet oppositely-overlapped spiral continuous airfoil, or a plurality of axisymmetric overlapped spiral continuous airfoils; the number of the spiral airfoil layers of the multilayer continuous airfoil propeller 1 is two, three or more; the axial vertical projection shape of the multilayer continuous airfoil propeller 1 is circular, or oval, or regular polygon, or triangle with round angle, or square with round angle; the side vertical projection shape of the multilayer continuous airfoil propeller 1 is square, or diamond, or shuttle, or triangle, or 8-shaped, or square with wavy teeth on two sides.

Preferably, in the embodiments 1 to 4, the power unit 11 or the land drive device 25 is a piston engine, a rotary engine, a turboshaft engine, or an electric motor; the flight driving device 5 adopts a pulse jet engine, a turbojet engine, a turbofan engine, a turboprop engine, an electric turbojet engine, a piston engine driving blade type propeller, a rotor engine driving blade type propeller, a turboshaft engine driving blade type propeller, a motor driving blade type propeller, a battery driving motor driving blade type propeller, or a fuel power generation device driving motor driving blade type propeller; the number of the multilayer continuous airfoil propellers 1 or the power units 11 is two or more; the multilayer continuous wing surface propellers 1 are arranged on two sides of the vehicle body 2, or arranged on the main wings 3 on two sides of the vehicle body 2 and the horizontal tail wing 41 at the same time; the power unit 11 drives one multilayer continuous airfoil propeller 1 one by one, or the power unit 11 drives two multilayer continuous airfoil propellers 1 one by one; the number of the flight driving devices 5 is one, or two or more; the flight driving device 5 is arranged at the nose position of the vehicle body 2, or arranged in the middle of the vehicle body 2, or arranged at the top of the vehicle body 2, or arranged at two sides of the vehicle body 2, or arranged at the tail of the vehicle body 2, or arranged on the main wings 3 at two sides of the vehicle body 2.

Preferably, in the embodiment 3 or 4, the communication transceiver unit 9 and the wireless remote control device 90 adopt a passive remote control circuit of a mineral radio, or a WLAN communication module, or a bluetooth communication module, or a ZigBee communication module, or a 4G/5G communication module to realize wireless communication and control between the two; the wireless remote control device 90 comprises a mobile phone, a remote control wrist strap, brain wave control glasses, remote control VR glasses, a remote control VR helmet, an image control helmet, a ground remote control station, a flight control remote controller, or a flight control network platform.

Specifically, when the hovercar in the schemes 1-4 is ready to take off vertically, a driver or a user controls the power unit 11 to drive the multilayer continuous airfoil propeller 1 to run at full speed and reach a set rotating speed, the multilayer continuous airfoil propeller 1 rapidly stirs air to generate lift force, the multilayer continuous airfoil propeller 1 drives the whole hovercar to lift off, and the hovercar realizes climbing or hovering; after the flying automobile is lifted off, a driver or a user controls the flying driving device 5 to generate traction force or thrust force forwards to drive the whole flying automobile to fly forwards, in the accelerating process, surface airflows of the main wing 3 and the horizontal tail wing 41 flow along the wing surface to generate lift force, meanwhile, the airflow flow rate of each layer of slope layer on the windward side of the multilayer continuous wing surface propeller 1 is accelerated, the airflow flow rate of each layer of slope layer on the windward side of the multilayer continuous wing surface propeller 1 is reduced, the multilayer continuous wing surface propeller 1 still provides the lift force, and the lift force of the whole flying automobile is provided by the multilayer continuous wing surface propeller 1, the main wing 3 and the horizontal tail wing 41 together; the multi-layer continuous airfoil propellers 1 symmetrically arranged on the two sides of the wing axially run to generate a gyro effect, so that the stability of the flying automobile in the rising process is improved; after a driver or a user controls the flying automobile to accelerate to reach a set flying speed, the multi-layer continuous wing propeller 1 is adjusted to decelerate and run to stop, and the lift force of the whole flying automobile is only provided by the main wing 3 and the horizontal tail wing 41 together; the multilayer continuous spiral wing surface structure of the multilayer continuous wing surface propeller 1 can still cut airflow by means of the spiral wing surface on the windward side after stalling and adapt to the rapid laminar flow brought by the whole flying automobile after acceleration, thereby avoiding the problems of large wind resistance and unstable flight caused by the fact that the windward or crosswind laminar flow directly generates airflow impact on the blades and the shock wave vibration is generated at the wing tips of the blades when a common blade type propeller is adopted;

when the aerocar is ready to vertically land, a driver or a user controls the flight driving device 5 to decelerate the aerocar to reach a set flight speed, then the power unit 11 is controlled to drive the multilayer continuous airfoil propeller 1 to run at an accelerated speed, and the lift force of the whole aerocar is provided by the multilayer continuous airfoil propeller 1, the main wing 3 and the horizontal tail wing 41; after a driver or a user controls the rotating speed of the multilayer continuous airfoil propeller 1 to reach a set rotating speed, the flight driving device 5 is controlled to decelerate until the lift force of the main wing 3 and the horizontal tail wing 41 is gradually reduced to zero, and the lift force of the whole flying automobile is mainly provided by the multilayer continuous airfoil propeller 1; a driver or a user controls the multilayer continuous airfoil propeller 1 to decelerate and run, and the aerocar gradually realizes running landing or vertical landing;

when the aerocar is ready to take off in a gliding way, a driver or a user controls the flight driving device 5 to accelerate the aerocar and reach a set flight speed, then the control surface action of the elevator 42 on the horizontal tail wing 41 is adjusted to enable the elevator to deflect upwards so as to enable the aerocar to raise the head and enter the gliding way, and the control surface action of the flap 31 on the main wing 3 is controlled to enable the elevator to deflect downwards so as to enable the wing surface lift force of the main wing 3 to be increased so as to enable the aerocar to take off in a gliding way; when the aerocar is ready to glide and land, a driver or a user controls the flight driving device 5 to decelerate the aerocar, adjusts the control surface action of the elevator 42 on the horizontal tail wing 41 to deflect downwards to realize that the aerocar lowers head and enters into a glide attitude, and controls the control surface action of the flap 31 on the main wing 3 to deflect upwards to reduce the lift force generated by the wing surface of the main wing 3 to realize the glide and land;

when the aerocar prepares for heavy-load short-distance gliding takeoff, a driver or a user controls the power unit 11 to drive the multilayer continuous airfoil propeller 1 to run at full speed and reach a set rotating speed, then the multilayer continuous airfoil propeller 1 rapidly stirs air to generate lift force, and meanwhile, the driver or the user controls the flight driving device 5 to accelerate the aerocar and reach the set flying speed, and then the lift force of the whole aerocar is provided by the multilayer continuous airfoil propeller 1, the main wing 3 and the horizontal tail 41 together; a driver or a user adjusts the control surface action of the elevator 42 on the horizontal tail wing 41 to enable the elevator to deflect upwards to realize that the flying automobile raises the head and enters a gliding attitude, and controls the control surface action of the flap 31 on the main wing 3 to deflect downwards, so that the wing surface lift force of the main wing 3 is increased to realize heavy-load short-distance gliding takeoff; after the driver or the user controls the flight driving device 5 to accelerate the flying automobile to reach the set flying speed and adjusts the multi-layer continuous wing surface propeller 1 to decelerate and stop, the lift force of the whole flying automobile is only provided by the main wing 3 and the horizontal tail wing 41 together to maintain the flat flight.

Compared with the prior art, the invention has the beneficial effects that:

1. the invention provides two new schemes of a vertical take-off and landing and fixed wing aerocar driven by people in the schemes 1 and 2; schemes 3 and 4 provide two schemes of a vertical take-off and landing and fixed-wing aerocar with manned and wireless remote control functions, so that the vertical take-off and landing can be remotely controlled, the fixed-wing flight is taken into consideration, and the workload of a driver is reduced; when an emergency situation occurs in the process of remote control driving, the vehicle can be switched to a manned state so that personnel in the vehicle can take over driving;

2. in the schemes 1-4 of the invention, the multilayer continuous airfoil surface propeller is adopted to replace the traditional blade-type propeller, the multilayer continuous airfoil surface propeller is adopted to provide the lift force in the vertical direction, and the spiral airfoil surface structure is utilized to cut and adapt to the windward fast laminar flow or cross-wind laminar flow, so that after the high-speed airflow is cut and guided by the spiral airfoil surface, the problems of larger wind resistance, unstable flight or hovering wind yaw blowing caused by the fact that the windward or cross-wind laminar flow directly generates airflow impact on the blades and the blade wing tips generate shock wave vibration when the common blade-type propeller is adopted are avoided; particularly in the high-speed flat flight process, after the multilayer continuous airfoil propeller stops rotating for improving the endurance, the multilayer airfoil structure of the static multilayer continuous airfoil propeller can still well adapt to the rapid laminar flow and keep the flight stability;

3. in the schemes 1-4 of the invention, the multilayer continuous wing surface propellers are adopted to provide the lift force in the vertical direction of the aerocar, the flight driving device is adopted to provide the traction force or the thrust force during the flat flight, and the spiral wing surface structure is utilized to cut and adapt to the rapid laminar flow, so that the problem of the wing tip tremble of the middle and high speed flight is avoided, the vertical take-off and landing can be better considered, and the middle and high speed flat flight can be realized;

4. in the schemes 1-4 of the invention, the multilayer continuous airfoil propeller can provide larger lift force in unit radius compared with a single-layer blade propeller;

5. in the schemes 1-4 of the invention, a plurality of layers of continuous airfoil propellers are adopted to add a guide groove, a boss, a wing cutter and a through hole on a flat outer edge ring wing so as to further weaken the interference impact of the head-on high-speed impact airflow on the lift airflow of the blade when the aerocar flies flatly and the blade rotates, and enhance the cutting and drainage effect of the spiral airfoil structure on the windward laminar flow or the cross wind laminar flow;

6. in the schemes 1-4 of the invention, the multilayer continuous airfoil propellers are adopted to provide the lift force when the aerocar vertically takes off and lands, the flight driving device is adopted to enable the aerocar to fly horizontally so as to enable the main wing to generate the lift force, the flight motion control can be simply decomposed into vertical take-off and landing control and flying acceleration and deceleration control from the control aspect, particularly the attitude of the aerocar is adjusted by the action of the wing control surface during flying horizontally, the flying control difficulty is reduced, and the unmanned remote control software method is simplified under the schemes 3 and 4; compared with the American V-22 osprey tilt wing aircraft, the control structure of the schemes 1 and 2 is relatively simpler;

7. in the schemes 1-4 of the invention, the flying vehicle is driven by the flying drive device to obtain the power when flying horizontally, and the horizontal flying is maintained by the lift force generated by the main wing after the operation of the multi-layer continuous airfoil propeller is stopped, so that compared with a multi-rotor unmanned aerial vehicle which needs to maintain the rotation and the stagnation of the blades, the flying vehicle can save fuel or electric power, thereby prolonging the endurance time;

8. the scheme 1-4 of the invention can freely select several mixed take-off and landing modes of gliding take-off and gliding landing, gliding take-off and vertical landing, vertical take-off and gliding landing, vertical take-off and vertical landing; in particular, the manned vertical take-off and landing and fixed wing aerocar of the scheme 1 can take off in a gliding way only by depending on the lift force of the main wing when a runway exists; the multi-layer continuous airfoil propellers can be operated simultaneously to increase the auxiliary lift force when the runway is short, so that the short-distance running takeoff is realized; the multi-layer continuous airfoil propellers can be operated simultaneously to increase the auxiliary lift force when the runway is longer, so that the overweight load gliding takeoff is realized; the vertical take-off and landing under light load can be realized in the field without a runway, and the adaptability of a battlefield or a field is stronger;

9. in the schemes 1-4 of the invention, the fixed-wing aerocar is taken into consideration during vertical take-off and landing by adopting the cradle head and the camera device, the vertical take-off and landing can adapt to the field of the field battlefield, the endurance time can be prolonged by adopting the fixed-wing flight mode, so that the long-endurance remote patrol monitoring under the field battlefield environment can be realized by adopting the cradle head and the camera device, and the fixed-point monitoring function in the air can be realized when the flight mode is switched to the suspension in the air.

Drawings

FIG. 1 is a schematic view of a VTOL and fixed wing flying vehicle embodiment 1 of the present invention;

FIG. 2 is a schematic view of embodiment 2 of the VTOL and fixed wing aerocar of the present invention;

FIG. 3 is a schematic view of embodiment 3 of the VTOL and fixed wing hovercar of the present invention;

FIG. 4 is a schematic view of embodiment 4 of the VTOL and fixed wing hovercar of the present invention;

FIG. 5 is a schematic diagram of a system for a VTOL and fixed wing hovercar embodiment 1 of the present invention;

FIG. 6 is a schematic diagram of a system for a VTOL and fixed wing hovercar embodiment 2 of the present invention;

FIG. 7 is a schematic diagram of a system for a VTOL and fixed wing hovercar embodiment 3 of the present invention;

FIG. 8 is a schematic diagram of a system for a VTOL and fixed wing hovercar embodiment 4 of the present invention;

FIG. 9 is a schematic diagram of a system for a VTOL and fixed wing hovercar embodiment 5 of the present invention;

FIG. 10 is a schematic diagram of a system for a VTOL and fixed wing hovercar embodiment 6 of the present invention;

FIG. 11 is a schematic view of embodiment 5 of the VTOL and fixed wing hovercar of the present invention;

FIG. 12 is a schematic view of embodiment 6 of a VTOL and fixed wing flying vehicle of the present invention;

FIG. 13 is a structural style drawing of a multi-layer continuous airfoil propeller and its airfoil flow guiding structure style 1;

FIG. 14 is a structural style drawing of a multi-layer continuous airfoil propeller and its airfoil flow guiding structural style 2;

FIG. 15 is a two-piece opposed overlapping helical continuous airfoil configuration of a multi-layer continuous airfoil propeller;

FIG. 16 is a laminar flow adaptation demonstration and a side elevation profile view of a multi-layer continuous airfoil propeller.

Description of reference numerals:

a multi-layer continuous airfoil propeller 1; a power unit 11; a vehicle body 2; a buffer suspension 20; a cockpit and passenger cabin 21; a front wheel 22; a rear wheel 23; a brake device 24; a land drive 5; a clutch and gearbox 26; a main wing 3; a flap 31; the flap 32; a tail fin 4; a horizontal rear wing 41; an elevator 42; a vertical rear wing 43; a rudder 44; a flight drive 5; a driver operating device 6; electronic instruments and sensors 61; an inertial measurement unit 62; a satellite positioning module 63; a power supply and drive control device 7; a battery unit 71; a drive unit 72; a control unit 73; a fuel power generation device 70; a steering engine 8; a communication transceiver unit 9; a wireless remote control device 90; an image pickup device 100; a pan-tilt 101; a flow guide groove 111; a flow guide boss 112; a guide vane 113; a flow guide through hole 114; a V-shaped tail 400; a beveled rudder 420.

Detailed Description

The embodiments of the present invention will be further described with reference to the accompanying drawings.

FIG. 1 shows a VTOL and fixed wing flying vehicle embodiment 1 of the present invention. It is suitable for using the engine to provide all the driving power. As shown in the figure, the flap 31 is provided at a position where the rear edge of the main wing 3 is close to the vehicle body 2, and the aileron 32 is provided at a position where the rear edge of the main wing 3 is far from the vehicle body 2; an elevator 42 is provided at the rear edge of the horizontal rear wing 41, and a rudder 44 is provided at the rear edge of the vertical rear wing 43; the multilayer continuous airfoil propeller 1 is of a multilayer continuous spiral airfoil structure and is connected and driven to rotate by a power unit 11; the wing root of the main wing 3 is fixed on the two sides of the vehicle body 2; the tail wing 4 is fixed at the tail part of the vehicle body 2; the front wheel 22 is connected to the front portion of the vehicle body 2 through the cushion suspension 20; the rear wheel 23 is connected to the rear portion of the vehicle body 2 through a cushion suspension 20; the cockpit and the passenger cabin 21 are fixed on the vehicle body 2 and provide a control position for a driver; the driver operating device 6 is arranged at a driving position in the cab and the passenger compartment 21 and is operated and driven by a driver; the brake device 24 is arranged at the brake position of the front wheel 22 and the rear wheel 23 nearby and is fixed on the buffer suspension 20; the brake device 24 is connected with the driver operating device 6, so that the driver operates the driver operating device 6 to drive the brake device 24 to perform braking action on the front wheels 22 and the rear wheels 23; the electronic instrument and sensor 61 is arranged in the cockpit and the passenger cabin 21 and fixed on the vehicle body 2, the electronic instrument and sensor 61 detects and displays the land driving speed, the driving mileage, the endurance mileage, the flying height, the flying airspeed, the climbing and descending speed, the flying attitude, the flying course data and the operation data parameters and the control parameters of the power unit 11 and the flying drive-in device 5, and provides data reference for the driver to assist the driver in driving or flying; the flying drive-in device 5 is fixed on the vehicle body 2 and generates traction or thrust to drive the whole flying vehicle to realize level flight; in the flying process, the multilayer continuous wing surface propeller 1 utilizes the spiral wing surface structure to cut and adapt to the windward rapid laminar flow or the crosswind laminar flow, thereby avoiding the problems of large wind resistance and unstable flight caused by the direct airflow impact on the blades and shock wave vibration generated at the wing tips of the blades caused by the windward or crosswind laminar flow when the common blade type propeller is adopted; the land driving device 25 is fixed on the vehicle body 2 and is connected with and drives the front wheel 22 and/or the rear wheel 23 to drive the whole aerocar to realize land driving; the main wings 3 on two sides of the vehicle body 2 are symmetrically connected with a multilayer continuous wing propeller 1 and a power unit 11 respectively, and the multilayer continuous wing propeller 1 is driven by the power unit 11 to rotate and provide vertical lift force.

FIG. 2 is a schematic view of embodiment 2 of the VTOL and fixed-wing aerocar of the present invention. Which is adapted to provide some or all of the driving power using an electric motor. As shown in the figure, the flap 31 is provided at a position where the rear edge of the main wing 3 is close to the vehicle body 2, and the aileron 32 is provided at a position where the rear edge of the main wing 3 is far from the vehicle body 2; an elevator 42 is provided at the rear edge of the horizontal rear wing 41, and a rudder 44 is provided at the rear edge of the vertical rear wing 43; the multilayer continuous airfoil propeller 1 is of a multilayer continuous spiral airfoil structure and is connected and driven to rotate by a power unit 11; the wing root of the main wing 3 is fixed on the two sides of the vehicle body 2; the tail wing 4 is fixed at the tail part of the vehicle body 2; the front wheel 22 is connected to the front portion of the vehicle body 2 through the cushion suspension 20; the rear wheel 23 is connected to the rear portion of the vehicle body 2 through a cushion suspension 20; the cockpit and the passenger cabin 21 are fixed on the vehicle body 2 and provide a control position for a driver; the driver operating device 6 is arranged at a driving position in the cab and the passenger compartment 21 and is operated and driven by a driver; the brake device 24 is arranged at the brake position of the front wheel 22 and the rear wheel 23 nearby and is fixed on the buffer suspension 20; the brake device 24 is connected with the driver operating device 6, so that the driver operates the driver operating device 6 to drive the brake device 24 to perform braking action on the front wheels 22 and the rear wheels 23; the electronic instrument and sensor 61 is disposed in the cockpit and the passenger compartment 21 and fixed to the vehicle body 2; the electronic instrument and sensor 61 detects and displays the land driving speed, the driving mileage, the endurance mileage, the flying height, the flying airspeed, the climbing and descending speed, the flying attitude, the flying course data and the operation data parameters and the control parameters of the power unit 11, the flying driving device 5, the land driving device 25 and the power supply and control device 7, and provides data reference for the driver to assist the driver in driving or flying; the flying drive-in device 5 is fixed on the vehicle body 2 and generates traction or thrust to drive the whole flying vehicle to realize level flight; in the flying process, the multilayer continuous wing surface propeller 1 utilizes the spiral wing surface structure to cut and adapt to the windward rapid laminar flow or the crosswind laminar flow, thereby avoiding the problems of large wind resistance and unstable flight caused by the direct airflow impact on the blades and shock wave vibration generated at the wing tips of the blades caused by the windward or crosswind laminar flow when the common blade type propeller is adopted; the land driving device 25 is fixed on the vehicle body 2 and is connected with and drives the front wheel 22 and/or the rear wheel 23 to drive the whole aerocar to realize land driving; the main wings 3 on two sides of the vehicle body 2 are symmetrically connected with a multilayer continuous wing propeller 1 and a power unit 11 respectively, and the multilayer continuous wing propeller 1 is driven by the power unit 11 to rotate and provide vertical lift force.

FIG. 3 is a schematic view of embodiment 3 of the VTOL and fixed-wing aerocar of the present invention. Which is adapted to provide some or all of the driving power using an electric motor. As shown in the figure, the flap 31 is arranged at the position close to the vehicle body 2 at the rear edge of the main wing 3, and the flap 31 is connected with a group of steering engines 8; the ailerons 32 are arranged at the positions, far away from the vehicle body 2, of the rear edge of the main wing 3, and the ailerons 32 are connected with a group of steering engines 8; the elevator 42 is arranged at the rear edge of the horizontal tail wing 41, the elevator 42 is connected with a group of steering engines 8, the rudder 44 is arranged at the rear edge of the vertical tail wing 43, and the rudder 44 is connected with a group of steering engines 8; meanwhile, the flap 31, the aileron 32, the elevator 42 and the rudder 44 are also connected with the pilot control device 6; the multilayer continuous airfoil propeller 1 is of a multilayer continuous spiral airfoil structure and is connected and driven to rotate by a power unit 11; the wing root of the main wing 3 is fixed on the two sides of the vehicle body 2; the tail wing 4 is fixed at the tail part of the vehicle body 2; the front wheel 22 is connected to the front portion of the vehicle body 2 through the cushion suspension 20; the rear wheel 23 is connected to the rear portion of the vehicle body 2 through a cushion suspension 20; the cockpit and the passenger cabin 21 are fixed on the vehicle body 2 and provide a control position for a driver; the driver operating device 6 is arranged at a driving position in the cab and the passenger compartment 21 and is operated and driven by a driver; the brake device 24 is arranged at the brake position of the front wheel 22 and the rear wheel 23 nearby and is fixed on the buffer suspension 20; the brake device 24 is connected with the driver operating device 6, so that the driver operates the driver operating device 6 to drive the brake device 24 to perform braking action on the front wheels 22 and the rear wheels 23; the electronic instrument and sensor 61 is disposed in the cockpit and the passenger compartment 21 and fixed to the vehicle body 2; the electronic instrument and sensor 61 detects and displays the land driving speed, the driving mileage, the endurance mileage, the flying height, the flying airspeed, the climbing and descending speed, the flying attitude, the flying course data and the operation data parameters and the control parameters of the power unit 11, the flying driving device 5, the land driving device 25 and the power supply and control device 7, and provides data reference for the driver to assist the driver in driving or flying;

the flying drive-in device 5 is fixed on the vehicle body 2 and generates traction or thrust to drive the whole flying vehicle to realize level flight; in the flying process, the multilayer continuous wing surface propeller 1 utilizes the spiral wing surface structure to cut and adapt to the windward rapid laminar flow or the crosswind laminar flow, thereby avoiding the problems of large wind resistance and unstable flight caused by the direct airflow impact on the blades and shock wave vibration generated at the wing tips of the blades caused by the windward or crosswind laminar flow when the common blade type propeller is adopted; the land driving device 25 is fixed on the vehicle body 2 and is connected with and drives the front wheel 22 and/or the rear wheel 23 to drive the whole aerocar to realize land driving; the main wings 3 on two sides of the vehicle body 2 are symmetrically connected with a multilayer continuous wing propeller 1 and a power unit 11 respectively, and the multilayer continuous wing propeller 1 is driven by the power unit 11 to rotate and provide vertical lift force.

FIG. 4 shows an embodiment 4 of the VTOL and fixed-wing aerocar of the present invention. The remote control device is suitable for adopting the motor to provide partial or all driving power and has the functions of manned driving and wireless remote control. As shown in the figure, the flap 31 is arranged at the position close to the vehicle body 2 at the rear edge of the main wing 3, and the flap 31 is connected with a group of steering engines 8; the ailerons 32 are arranged at the positions, far away from the vehicle body 2, of the rear edge of the main wing 3, and the ailerons 32 are connected with a group of steering engines 8; the elevator 42 is arranged at the rear edge of the horizontal tail wing 41, the elevator 42 is connected with a group of steering engines 8, the rudder 44 is arranged at the rear edge of the vertical tail wing 43, and the rudder 44 is connected with a group of steering engines 8; meanwhile, the flap 31, the aileron 32, the elevator 42 and the rudder 44 are also connected with the pilot control device 6; the multilayer continuous airfoil propeller 1 is of a multilayer continuous spiral airfoil structure and is connected and driven to rotate by a power unit 11; the wing root of the main wing 3 is fixed on the two sides of the vehicle body 2; the tail wing 4 is fixed at the tail part of the vehicle body 2; the front wheel 22 is connected to the front portion of the vehicle body 2 through the cushion suspension 20; the rear wheel 23 is connected to the rear portion of the vehicle body 2 through a cushion suspension 20; the cockpit and the passenger cabin 21 are fixed on the vehicle body 2 and provide a control position for a driver; the driver operating device 6 is arranged at a driving position in the cab and the passenger compartment 21 and is operated and driven by a driver; the brake device 24 is arranged at the brake position of the front wheel 22 and the rear wheel 23 nearby and is fixed on the buffer suspension 20; the brake device 24 is connected with the driver operating device 6, so that the driver operates the driver operating device 6 to drive the brake device 24 to perform braking action on the front wheels 22 and the rear wheels 23; the electronic instrument and sensor 61 is disposed in the cockpit and the passenger compartment 21 and fixed to the vehicle body 2; the electronic instrument and sensor 61 detects and displays the land driving speed, the driving mileage, the endurance mileage, the flying height, the flying airspeed, the climbing and descending speed, the flying attitude, the flying course data and the operation data parameters and the control parameters of the power unit 11, the flying driving device 5, the land driving device 25 and the power supply and control device 7, and provides data reference for the driver to assist the driver in driving or flying;

FIG. 5 is a schematic diagram of a system for a VTOL and fixed wing hovercar embodiment 1 of the present invention. As shown in the figure, the electronic instrument and sensor 61 is connected to the power unit 11, the flight driving device 5 and the land driving device 25, and is used for detecting and displaying the operation data parameters and the control parameters of the three and various necessary driving reference information; the pilot control device 6 is connected with the front wheels 22 or the rear wheels 23, the power unit 11, the flight driving device 5, the land driving device 25, the flaps 31, the ailerons 32, the elevator 42 and the rudder 44; the driver operating device 6 is also connected with a brake device 24, so that the driver operates the driver operating device 6 to drive the brake device 24 to perform braking action on the front wheels 22 and the rear wheels 23; when driving, the driver operates the driver operating device 6 to control the rotation of the front wheels 22 or the rear wheels 23 to realize the land driving steering of the aerocar; when a pilot operates the pilot operating device 6 to control the driving power of the driving unit 72, the power unit 11 and the flight driving device 5, adjust the rotating speed of the multi-layer continuous wing propeller 1, and operate the deflection actions of the flaps 31, the ailerons 32, the elevators 42 and the rudders 44, so that the flying automobile can realize lift-off, landing, hovering, acceleration and deceleration flight, flying and rolling, flight steering and flight attitude adjustment.

FIG. 6 is a schematic diagram of a system for a VTOL and fixed wing hovercar embodiment 2 of the present invention. As shown in the figure, the electronic meter and sensor 61 is electrically connected to the control unit 73 for detecting and displaying the operation data parameters and control parameters of the power supply and control device 7 and various necessary driving reference information; the drive unit 72, the control unit 73, the driver operating device 6, the electronic meter and the sensor 61 are electrically connected to the battery unit 71 to be powered thereby; the driving unit 72 is electrically connected with each power unit 11 and/or the flight driving device 5 and/or the land driving device 25 by different output channels to drive the operation of the power units with output power; the control unit 73 electrically connects the drive unit 72 and the driver manipulating device 6 to output a control signal to the drive unit 72 and receive a control instruction from the driver manipulating device 6;

the pilot control device 6 is also connected to the front or rear wheel 22, 23, the flap 31, the aileron 32, the elevator 42, the rudder 44; the driver operating device 6 is also connected with a brake device 24, so that the driver operates the driver operating device 6 to drive the brake device 24 to perform braking action on the front wheels 22 and the rear wheels 23; the pilot control device 6 is also connected to the respective power unit 11 and/or to the flight propulsion device 5 and/or to the land propulsion device 25 to control the output of their power; when driving, the driver operates the driver operating device 6 to control the rotation of the front wheels 22 or the rear wheels 23 to realize the land driving steering of the aerocar; when a pilot drives, the pilot control device 6 is operated by the pilot to control the driving power of the driving unit 72, the power unit 11 and the flight driving device 5, the rotating speed of the outer edge ring wing blade type propeller 1 is adjusted, and the deflection actions of the flaps 31, the ailerons 32, the elevators 42 and the rudders 44 are controlled, so that the flying automobile can realize the functions of lifting, landing, hovering, accelerating and decelerating flight, flying and rolling, flight steering and flight attitude adjustment.

FIG. 7 is a schematic diagram of a system for vertical takeoff and landing and fixed wing flying vehicle embodiment 3 of the present invention. As shown in the figure, the electronic meter and sensor 61 is electrically connected to the control unit 73 for detecting and displaying the operation data parameters and control parameters of the power supply and control device 7 and various necessary driving reference information; the driving unit 72, the control unit 73, the driver operating device 6, the communication transceiving unit 9, the electronic meter and sensor 61 are electrically connected with the battery unit 71 to be powered by the battery unit; the driving unit 72 is electrically connected with each group of steering engines 8 through different output channels to drive and operate the control surface deflection actions of the flaps 31, the ailerons 32, the elevators 42 and the rudders 44; the driving unit 72 is electrically connected with the power unit 11 and/or the flight driving device 5 and/or the land driving device 25 by different output channels so as to drive and control the operation of the power unit and/or the flight driving device with output power; the control unit 73 electrically connects the drive unit 72 and the driver manipulating device 6 to output a control signal to the drive unit 72 and receive a control instruction from the driver manipulating device 6; the control unit 73 is also electrically connected with the communication transceiving unit 9 to receive the control instruction from the communication transceiving unit 9;

the pilot control device 6 is also connected to the respective power unit 11 and/or to the flight propulsion device 5 and/or to the land propulsion device 25 to control the output of their power; the driver operating device 6 is also connected with a brake device 24, so that the driver operates the driver operating device 6 to drive the brake device 24 to perform braking action on the front wheels 22 and the rear wheels 23; the driver operating device 6 is also connected to front wheels 22 or rear wheels 23; when driving, the driver operates the driver operating device 6 to control the rotation of the front wheels 22 or the rear wheels 23 to realize the land driving steering of the aerocar; when a pilot operates the pilot operating device 6 to control the output power of the driving unit 72 and/or the power unit 11 and/or the flight driving device 5 and/or the land driving device 25, adjust the rotating speed of the outer edge ring wing blade type propeller 1, and operate the deflection actions of the flaps 31, the ailerons 32, the elevator 42 and the rudder 44, so that the flying automobile realizes land advancing, backing and accelerating and decelerating running, and realizes lift-off, landing, hovering, accelerating and decelerating flight, flying roll, flight steering and flight attitude adjustment;

FIG. 8 is a schematic diagram of a system for a VTOL and fixed wing hovercar embodiment 4 of the present invention. As shown, the electronic meter and sensor 61 is electrically connected to the control unit 73; each group of steering engine 8, driving unit 72, control unit 73, driver operating device 6, communication transceiving unit 9, electronic instrument and sensor 61 are electrically connected with battery unit 71 and powered by the battery unit; the driving unit 72 is electrically connected with the power unit 11 and/or the flight driving device 5 and/or the land driving device 25 by different output channels to drive and control the operation of the power unit and/or the flight driving device with output power; the control unit 73 electrically connects the drive unit 72 and the driver manipulating device 6 to output a control signal to the drive unit 72 and receive an instruction from the driver manipulating device 6; the control unit 73 is also electrically connected to the communication transceiving unit 9 to receive instructions from the communication transceiving unit 9;

the pilot control device 6 is also connected to the respective power unit 11 and/or to the flight propulsion device 5 and/or to the land propulsion device 25 to control the output of their power; the driver operating device 6 is also connected with a brake device 24, so that the driver operates the driver operating device 6 to drive the brake device 24 to perform braking action on the front wheels 22 and the rear wheels 23; the driver control device 6 is also electrically connected with each group of steering engines 8 and directly electrically controls each group of steering engines 8, so that each group of steering engines 8 is directly controlled to drive and control the deflection action of the control surfaces of the flaps 31, the ailerons 32, the elevators 42 and the rudders 44; the driver operating device 6 is also connected to front wheels 22 or rear wheels 23; when driving, the driver operates the driver operating device 6 to control the rotation of the front wheels 22 or the rear wheels 23 to realize the land driving steering of the aerocar; when a pilot operates the pilot operating device 6 to control the output power of the driving unit 72 and/or the power unit 11 and/or the flight driving device 5 and/or the land driving device 25, adjust the rotating speed of the outer edge ring wing blade type propeller 1, and operate the deflection actions of the flaps 31, the ailerons 32, the elevator 42 and the rudder 44, so that the flying automobile realizes land advancing, backing and accelerating and decelerating running, and realizes lift-off, landing, hovering, accelerating and decelerating flight, flying roll, flight steering and flight attitude adjustment;

Specifically, the system in fig. 7 differs from the system in fig. 8 in that the action control of each group of steering engines 8 in fig. 7 is driven and executed by the driving unit 72, the control unit 73 sends out a program control command for control, and the control unit 73 is commanded and controlled by the driver operating device 6; or the communication transceiver 9 receives and transmits the command from the wireless remote control device 90 for control. In fig. 8, the action control of each group of steering engines 8 is uniformly driven and executed by the driver control device 6, and meanwhile, the driver control device 6 can adopt circuits such as a circuit switch and a relay to directly control the power on-off of each group of steering engines 8; a user directly operates the driver control device 6 to control the operation of each group of steering engines 8; or the communication transceiver 9 receives and transmits the command from the wireless remote control device 90, and the control unit 73 analyzes the command and then sends a control signal to the driver control device 6, so that the steering engines 8 are directly controlled electrically.

In addition, the connection relationship indicated by the dotted line in fig. 6, 7, and 8 includes various system solutions: in the first scheme of the system, the two power units 11, the flight driving device 7 and the land driving device 25 can all adopt motors to provide power; in the second scheme of the system, two of the two power units 11, the flight driving device 7 and the land driving device 25 are powered by the motors, and when the rest one of the power units adopts the engine to output power, the rest power unit is connected to the driver control device 7 and controls the output power of the driver control device; in the third scheme of the system, one of the two power units 11, the flight driving device 7 and the land driving device 25 adopts the electric motor to provide power, and when the rest two adopt the output power of the engine, the rest two are connected with the driver control device 7 to control the output power.

FIG. 9 is a schematic diagram of a system for a VTOL and fixed wing hovercar embodiment 5 of the present invention. As shown in the figure, a clutch and a gearbox 26 are added on the basis of figure 5, so that the aerocar has the functions of clutch and speed change when running on the land. The electronic instrument and sensor 61 is connected to the power unit 11, the flight driving device 5 and the land driving device 25, and is used for detecting and displaying the operation data parameters, the control parameters and various necessary driving reference information of the three; the land driving device 25 is connected with a clutch and a gearbox 26, the clutch and the gearbox 26 are connected with the rear driving wheel 23, the land driving device 25 provides driving force to drive the rear driving wheel 23 to drive the whole aerocar to realize land driving through the clutch and the speed change link of the clutch and the gearbox 26; the pilot control device 6 is connected with a front wheel 22 or a rear wheel 23, a power unit 11, a flight driving device 5, a land driving device 25, a clutch and gearbox 26, a flap 31, an aileron 32, an elevator 42 and a rudder 44; the driver operating device 6 is also connected with a brake device 24, so that a driver operates the driver operating device 6 to drive the brake device 24 to brake the front wheels 22 and the rear wheels 23; when driving, a driver operates the driver operating device 6 to control the rotation of the front wheels 22 or the rear wheels 23 to realize land driving steering; when a pilot operates the pilot operating device 6 to control the driving power of the driving unit 72, the power unit 11 and the flight driving device 5, adjust the rotating speed of the multi-layer continuous wing propeller 1, and operate the deflection actions of the flaps 31, the ailerons 32, the elevators 42 and the rudders 44, so that the flying automobile can realize lift-off, landing, hovering, acceleration and deceleration flight, flying and rolling, flight steering and flight attitude adjustment.

FIG. 10 is a schematic diagram of a system for a VTOL and fixed wing hovercar embodiment 6 of the present invention. As shown, the system schematic is reduced by a flight propulsion device 5 on the basis of fig. 6; and a ramp rudder 420 is newly adopted; the inclined plane rudder 420 is connected with a pilot operating device 6, and a pilot controls the action of a control plane of the inclined plane rudder 420 through the pilot operating device 6 to generate a deflection moment so as to adjust the pitching attitude and direction of the whole aerocar during fast flight;

in addition, the system schematic diagram is additionally provided with a camera device 100, a holder 101, an inertia measurement unit 62, a satellite positioning module 63 and a fuel power generation device 70, wherein the five are electrically connected with a battery unit 71 and a control unit 73 in the power supply and control device 7; the camera device 100 is electrically connected to the power supply and the driving and controlling device 7, and is powered by the power supply and the driving and controlling device, and the camera device 100 is used for recording, shooting and locally storing images or videos; the holder 101 is electrically connected to the power supply and the driving and controlling device 7, and the power supply and the control of the camera device 100 on the holder 101 are carried out; the moving inertia measurement unit 62 is electrically connected to the control unit 73, the inertia measurement unit 62 measures three-dimensional position, three-dimensional velocity, three-dimensional acceleration, three-axis angle, three-dimensional angular velocity and flight altitude signals and transmits the signals to the control unit 73, and the control unit 73 performs resolving, optimizing and error compensating on the attitude of the current flying automobile during flying according to the flight motion data; the satellite positioning module 63 is electrically connected to the control unit 73, and it measures the satellite positioning data to provide data reference for the pilot to assist the pilot in navigating or flying.

FIG. 11 shows embodiment 5 of the VTOL and fixed-wing aerocar of the present invention. In the embodiment, a clutch and a gearbox 26 are added on the basis of fig. 1, so that the manned vertical take-off and landing and fixed wing flying automobile capable of realizing clutch speed change by means of the clutch and the gearbox is formed. As shown in the figure, the clutch and gearbox 26 is fixed on the vehicle body 2, the land driving device 25 is connected with the clutch and gearbox 26, the clutch and gearbox 26 is connected with the driving rear wheel 23, the land driving device 25 provides driving force to drive the rear wheel 23 to drive the whole hovercar to realize land driving through the clutch and speed change links of the clutch and gearbox 26; the driver operates the clutch and the gearbox 26 through the driver operating device 6 to execute clutch action and speed change action so as to cut off or switch on the power connection from the land driving device 25 to the rear wheel 23 and adjust the power transmission ratio from the land driving device 25 to the rear wheel 23, thereby driving the whole flying automobile to realize forward running, reverse running and acceleration and deceleration running on land, and cutting off the power connection to the front wheel and the rear wheel after the flying automobile leaves the ground so as to save energy.

FIG. 12 shows embodiment 6 of the VTOL and fixed-wing hovercar of the present invention. The flying automobile with V-shaped tail wings, which is driven by people, has vertical take-off and landing and fixed wings. As shown, this embodiment is similar to the embodiment of fig. 1, with the difference that only one flight propulsion device 5 is used, this flight propulsion device 5 being arranged at the front of the vehicle body 2; the tail 4 adopts a V-shaped tail 420, the V-shaped tail is formed by a left wing surface and a right wing surface which are in a V shape, the V-shaped tail has the functions of a vertical tail and a horizontal tail, and the rear edges of the two wing surfaces of the V-shaped tail are provided with deflection control surfaces formed by inclined plane rudders 420; the front wheel 22 only adopts one wheel, so that the whole flying automobile is a front three-point wheeled land driving and landing mechanism;

in addition, in the present embodiment, an imaging device 100, a pan/tilt head 101, an inertia measurement unit 62, a satellite positioning module 63, and a fuel power generation device 70 are additionally provided. Specifically, the cradle head 101 is fixed on the vehicle body 2, and the camera device 100 is fixed on the cradle head 101 and used for flight shooting and flight recording; the dynamic inertia measurement unit 62 is arranged on the vehicle body 2 and is used for measuring flight motion data such as a three-dimensional position, a three-dimensional velocity, a three-dimensional acceleration, a three-axis angle, a three-dimensional angular velocity, a flight altitude signal and the like, and the power supply and control device 7 of the flying vehicle resolves, optimizes and compensates the attitude of the current flying vehicle during flying according to the flight motion data; the satellite positioning module 63 is fixed on the vehicle body 2, and measures satellite positioning data to provide data reference for a driver to assist the driver in realizing navigation driving or flying; the fuel power generation device 70 is electrically connected to the power supply and control unit 7 for charging the range of the fuel power generation device.

Fig. 13 is a structural style diagram of a multi-layer continuous airfoil propeller and an airfoil flow guiding structural style 1 thereof. As shown, the multi-layer continuous airfoil propeller 1 is configured as a single spiral continuous airfoil. The continuous guide groove 111, or the continuous guide boss 112, or the continuous guide wing knife 113 is arranged on the airfoil surface of the multilayer continuous airfoil propeller 1 and close to the edge of the airfoil surface; the guide grooves 111, the guide bosses 112, or the guide winglets 113 are used for inhibiting separation of boundary layers at the edge of the airfoil and preventing the boundary layers of the airflow from centrifugally flowing to the edge when the multi-layer continuous airfoil propeller 1 rotates at a high speed. Accordingly, the guide grooves 111, the guide bosses 112, or the guide vanes 113 may also be discontinuous.

Fig. 14 is a structural pattern diagram of a multi-layer continuous airfoil propeller and an airfoil flow guiding structure pattern 2 thereof. As shown, the multi-layer continuous airfoil propeller 1 is configured as a single spiral continuous airfoil. Scattering-shaped guide grooves 111, or scattering-shaped guide bosses 112, or scattering-shaped guide wings 113, or scattering-shaped guide through holes 114 are arranged on the airfoil surface of the multilayer continuous airfoil propeller 1 and close to the edge of the airfoil surface; the scattered flow guide grooves 111, flow guide bosses 112, flow guide wing knives 113 or flow guide through holes 114 also have the function of inhibiting boundary layer separation at the edge part of the airfoil and preventing the boundary layer of the airflow from centrifugally flowing to the edge when the multi-layer continuous airfoil propeller 1 rotates at high speed.

FIG. 15 is a block diagram of a two-piece opposed overlapping helical continuous airfoil of a multi-layer continuous airfoil propeller. As shown, the continuous airfoil of the multi-layer continuous airfoil propeller 1 is a two-piece opposed overlapping helical continuous airfoil. Correspondingly, the continuous spiral airfoil surface can also be a single-sheet spiral continuous airfoil surface or a plurality of axisymmetric overlapped spiral continuous airfoil surfaces; and the number of layers of the continuous helical airfoil surface can be two, three, or more.

FIG. 16 is a laminar flow adaptation demonstration and a side elevation profile view of a multi-layer continuous airfoil propeller. As shown in the figure, the multilayer airfoil structure of the multilayer continuous airfoil propeller 1 can adapt to the rapid laminar flow brought by the whole aerocar after acceleration, and airflow on two sides of the axis of the multilayer continuous airfoil propeller 1 flows along the edge of each layer of slope layer in a laminar flow mode; because the spiral airfoil of the multilayer continuous airfoil propeller 1 is of a continuous spiral airfoil structure, based on the structural characteristics, compared with the stress tremble generated by concentrating on the tip of the blade when the tip of the blade propeller impacts high-speed airflow, the multilayer continuous airfoil can meet the impact of the high-speed airflow with the whole edge side, and the continuous spiral airfoil can better adapt to high-speed laminar flow than the blade propeller because the continuous arc-shaped edge of the edge side has better cutting airflow and drainage effects.

In addition, the figure also shows that the lateral vertical projection shape of the multilayer continuous airfoil propeller 1 is a diamond shape. Correspondingly, the lateral vertical projection shape can also be square, or diamond, or fusiform, or triangle, or 8-shaped, or square with wavy teeth on two sides. It should be noted that the square shape with wavy teeth on both sides is a continuous and overlapped scheme of the large-diameter spiral airfoil and the small-diameter spiral airfoil, that is, a scheme of alternating length of the vertical projection of the airfoil on the left side of the shaft and the vertical projection of the airfoil on the right side of the shaft, and the scheme is favorable for improving the lift efficiency of the edge side of the large-diameter spiral airfoil.

The above examples are only for describing the preferred embodiments of the present invention, and are not intended to limit the scope of the present invention, and various modifications and improvements of the technical solution of the present invention by those skilled in the art should be made within the protection scope defined by the claims of the present invention without departing from the spirit of the present invention.

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Vertical take-off and landing and fixed wing aerocar

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