Electric, long-endurance and simple aircraft

Abstract

The invention discloses an electric, long-endurance and simple aircraft, and belongs to the technical field of light aircrafts. 1-2 rotating cylinders are arranged on the front portion and the rear portion of the airfoil respectively and driven by ultralight motors, the upper airfoil is coated with a perovskite photovoltaic cell, electric energy is stored in a super-capacitor cell, and the super-capacitor cell and a quantum cell are connected in parallel to supply power to all electric equipment on the aircraft; the pitching of the airplane is controlled by different rotating speeds of the front and rear rotating cylinders; the left and right wing rotating cylinders are different in rotating speed to control the left and right wing rotating cylinders to tilt, a propeller rear grid plate swings left and right to turn, rotation of the rotating cylinders in the wings interacts with airflow to generate 'Magnus effect' lift force, lift force is generated with traditional wings, and the safety of passengers can be guaranteed; the wings are connected with the cabin through components, are frame-type and detachable, are coated with transparent plastic films, are opened on the upper, lower, left and right sides, can extend two legs of a passenger out of a lower opening cover, carry straps and hold a handle, control the direction of the airplane, run windward and assist the airplane to take off and land, are positioned by a Beidou satellite, and can be driven in an unmanned manner.

Description

Technical Field

[0001] The present invention belongs to the technical field of light aircraft, particularly the field of low-altitude, human-assisted aircraft that utilizes a combined wing as an upper monoplane, with different combinations of rotor speeds controlling the aircraft's maneuverability. The invention has no tail, and allows the crew to extend their legs outside the cabin and run to assist in takeoff and landing. The invention utilizes quantum batteries and perovskite photovoltaic cells coated on the upper wing surface to charge supercapacitor batteries, which are connected in parallel to provide power to drive the propeller in the annular ring behind the cabin. Background Art

[0002] 1. Existing artificial aircraft all have a long wingspan, which is 13.7-14 meters long, and have a long tail strut and tail fin, on which a vertical stabilizer and rudder are installed vertically, and a horizontal stabilizer and horizontal rudder are installed horizontally. The width and length make it inconvenient for takeoff, landing, and storage in residential areas, and even more difficult to operate on the road.

[0003] 2. Take off by sliding down a hillside or running on the grass while pedaling the propeller. It is used for sports gliding, but cannot be used as a means of transportation.

[0004] 3. The wing has a large wing area and can take off at a low speed without any other lift-increasing equipment.

[0005] 4. The wing is directly attached to the cabin, which reduces the effective lift area of ​​the wing.

[0006] 5. The flight power depends entirely on humans, whose maximum power is only 0.4 kilowatts, which cannot be sustained for a long time, so the range is short.

[0007] 6. Solar energy is rarely used for power.

[0008] 7. The user carries the aircraft by hand and runs with legs, without using a strap to bear the weight. This makes it unsuitable for heavier equipment and more sophisticated aircraft.

[0009] Its disadvantages are as follows: it is only suitable for sports and entertainment, not suitable for normal transportation, cannot work for long flight time, and is not suitable for take-off, landing and storage in residential areas within cities. Summary of the Invention

[0010] In order to overcome the shortcomings of the background technology, the purpose of the present invention is to provide a new "electric, long-flight, simple aircraft" technology that can solve the technical problems listed above.

[0011] The technical solution adopted by the present invention to solve the above technical problems is:

[0012] The high-lift composite wing is used as an upper monoplane, but the wing is separated from the cabin by 150-500 mm to fully utilize the lift of the wing area. The wing is short and wide. The composite wing is a traditional wing with 2-4 rotating cylinders inserted perpendicular to its chord line. The rotation of the cylinders is driven by an ultra-light motor. The front and rear rotors have different rotation speeds, and the left and right rotors have different rotation speeds. This combination is used as a means to control the aircraft to climb, descend, bank left and right, and turn. The propeller rear grille swings left and right to turn. The "Mars" lift generated by the rotation of the rotor and the lift of the traditional wing ensure the flight safety of the crew and eliminate the need for tail lift and left and right turning structures. The wings are coated with perovskite photovoltaic cells, which convert sunlight into electricity and store it in supercapacitor batteries. This is then connected in parallel with quantum batteries with a working life of ten years to power the motor behind the cabin to drive the propeller. As the aircraft's flight power; the cabin uses a lightweight high-strength pipe frame and is covered with a transparent thick plastic film. The cabin is open up, down, left and right. The upper opening cover can be hung on the underwing structure and serves as a speed brake to shorten the glide distance. The lower opening cover allows the crew to stretch out their legs and run to assist in flying. There are handles on both sides to control the direction of the aircraft, and there are straps to bear weight, and the rubber wheels on both sides of the cabin are on the ground to bear 1 / 2 of the weight. There is an autopilot at the front of the cabin, a Beidou navigation and positioning system, and control switches for controlling the aircraft to climb, descend, turn left and right, etc., and a laser altimeter and rangefinder, and an anti-collision radar. It can be driven automatically or switched to manual control. A battery is installed under the seat, and an electric motor is installed at the rear of the cabin to drive the rear propeller of the cabin. There is a grid on the annular ring of the propeller that can swing left and right to assist in turning left and right; the destination coordinates can be directly entered, and the aircraft will automatically go directly to the destination or go to the neighboring area to work.

[0013] An "electric, long-endurance, simple aircraft" is made of:

[0014] 1. Vertical support rod 2. Autopilot 3. Cabin 4. Handle 5. Door 6. Crew 7. Rotor 8. Upper opening cover 9. Gap 10. Pulley 11. Synchronous belt 12. Light motor 13. Upper cabin ring 14. Perovskite photovoltaic cell 15. Seat 16. Combined wing 17. Motor 18. Coupling 19. Ring 20. Propeller 21. Grid 22. Strap 23. Actuator 24. Cross support rod 25. Supercapacitor battery 26. Quantum battery 27. Lower cabin ring 28. Rubber wheel 29. Lower opening cover 30. Component 31. Thick plastic film are connected in sequence to form the structure.

[0015] 1. Its characteristics are: a combined wing is used as the upper wing, which is connected to the cabin with a component, the chord of the airfoil is long, and the aspect ratio is small.

[0016] The combined wing (16) is a wing in which 2-4 rotating cylinders are inserted perpendicularly to the chord of a conventional wing. The wing is short and wide, so the chord length is long and the aspect ratio is small, which allows for flexible turning and facilitates takeoff and landing in urban residential areas. The upper surface of the wing is covered with aramid fiber material, which is then painted and coated with flexible perovskite photovoltaic cells (14). Electric energy is accumulated and stored in a supercapacitor battery (25), which is connected in parallel with a quantum battery (26) with a working life of ten years to supply power to the rotor (7), propeller (20) and all electrical equipment on the aircraft. The wing is 150-500 mm away from the top of the cabin (3) to fully utilize the wing lift area without being covered. The connecting member (30) is a high-strength pipe. The aircraft uses a high-wing. The combined wing (16) can simplify the control mechanism during maneuvering, save the rudder, horizontal rudder and vertical stabilizer, horizontal stabilizer, and double the lift, so the wing area can be reduced.

[0017] 2. Its characteristics are: the cabin is of detachable frame type, with openings on the top, bottom, left and right sides. The lower opening can expose the legs of the crew for running, replacing the landing gear and assisting takeoff.

[0018] The cabin (3) is made of carbon fiber tubing as a frame, which can be disassembled and folded for easy transportation. It consists of upper and lower cabin rings (13) (27) and vertical support rods (1) and horizontal support rods (24), and is covered with thick transparent plastic film (31). The cabin (3) is a small cabin with a pointed nose and is open at the top, bottom, left and right. The lower opening cover (29) allows the passengers to stretch their legs to the ground and run to assist the aircraft to take off, replacing the landing gear. The left and right doors (5) are open for easy entry and exit of the passengers. The autopilot (2) is arranged in the front of the cabin, and a simple seat (15) is arranged at the back. Quantum batteries (26) and supercapacitor batteries (25) are placed under the seat. A motor (17) is installed behind the seat to drive the propeller (20) in the annular ring behind the cabin. A grid plate (21) is installed behind it, which can swing left and right to assist the aircraft to turn.

[0019] 3. It is characterized in that the aircraft's maneuvering flight is controlled by the combined rotation speed difference of the rotors in the combined wings.

[0020] The aircraft's climbing and descending maneuvers are controlled by the rotors (7) in the combined wing (16). When the rotation speeds of the left and right wings and the front and rear rotors (7) are different, the wings tilt up or down, causing the aircraft to climb or descend. When the rotation speeds of the left and right wing rotors (7) are different, the end with a higher rotation speed rises and the side with a lower rotation speed sinks, forming a tilted shape. In conjunction with the grid plate (21) behind the propeller (20), the propeller swings left and right under the strong wind blown by the propeller (20), and can turn left and right in conjunction with the aircraft's tilt. Therefore, the components behind the cabin (3) are omitted, the structural weight is greatly reduced, the aircraft's moment of inertia is reduced, and the aircraft is flexible and maneuverable to avoid obstacles. The motor (17) installed behind the cabin (3) drives the propeller (20) in the annular ring.

[0021] 4. The feature is that the aircraft's navigation power is a propeller in an annular ring driven by an electric motor, and there is a grid plate behind the annular ring.

[0022] The power for the aircraft to navigate in the air is a propeller (20) in an annular ring (19) driven by a motor (17). The motor (17) is powered by a quantum battery (26) connected in parallel with a supercapacitor battery (25). The upper surface of the wing is coated with a perovskite photovoltaic cell (14), which converts solar energy into electrical energy, gradually accumulates it, and stores it in the supercapacitor battery (25). It can power the motor (17) with an ultra-large current to drive the propeller (20) in a short period of time, work in a take-off state or climb, and overdrive the rotor (7) to rotate when turning. The quantum battery (26) can only work at a constant current and constant voltage. The supercapacitor battery (25) can also store excess electrical energy when the quantum battery (26) is working. The annular ring (19) is placed on the propeller to prevent the high-speed airflow from being affected by the natural airflow outside the ring. It can also concentrate the high-speed airflow backward, thereby increasing the thrust.

[0023] 5. Its characteristics are: the upper surface of the wing is coated with flexible ultra-thin perovskite photovoltaic cells, which can store the electrical energy converted from solar energy in supercapacitor batteries.

[0024] During flight, the electric energy converted by the perovskite photovoltaic cell (14) is connected in parallel with the supercapacitor battery (25) and the quantum battery (26) to supply power to the propeller (20), the rotor (7) and all the electrical equipment on board. When the aircraft is not flying, the aircraft is parked in the open air. At this time, the perovskite photovoltaic cell (14) continues to work and stores the electric energy in the supercapacitor battery (25) to meet the power supply needs when high current is working. The double insurance power supply of the two can ensure flight safety, which can also reduce the capacity of the quantum battery (26).

[0025] 6. Its characteristics are as follows: the cabin has upper and lower opening covers, and doors on the left and right. When the upper and lower opening covers are fully opened, air flows directly through the upper and lower parts of the cabin, which can release slightly high ground effect pressure and shorten the landing distance; the upper opening cover is hung vertically on the component and can also serve as a speed brake.

[0026] The cabin (3) is provided with upper and lower opening covers (8) and (29). When all are opened, air flows straight through the cabin (3) from top to bottom, thereby releasing slightly higher ground effect pressure and shortening the landing distance. The upper opening cover (8) is vertically hung on the component (30) and can also serve as a speed brake. The cabin has left and right doors (5) for easy access for passengers (6) to the doors (5).

[0027] 7. Its characteristics are: there is a lower cabin ring on the cabin, with two rubber wheels installed on the front and rear sides respectively, and handles and shoulder straps are installed at appropriate load-bearing points in the cabin.

[0028] The cabin (3) is provided with a lower cabin ring (27) with two rubber wheels respectively installed on the front and rear sides of the left and right sides, and a handle (4) and a shoulder strap (22) are installed at a suitable height bearing point of the cabin (3). When taking off or landing, the crew (6) can hold the handle (4) and carry the shoulder strap (22) to control the direction of the aircraft, carry the entire aircraft on their back, make the rear two rubber wheels (28) touch the ground, run forward against the wind, and help the aircraft take off or land. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 This invention is "electric, long-flight, simple aircraft"

[0030] The diagram shows: 1. Vertical support rod 2. Autopilot 3. Cabin 4. Handle 5. Door 6. Crew 7. Rotor 8. Upper opening cover 9. Gap 10. Pulley 11. Synchronous belt 12. Light motor 13. Upper cabin ring 14. Perovskite photovoltaic cell 15. Seat 16. Combined wing 17. Motor 18. Coupling 19. Ring 20. Propeller 21. Grid plate 22. Back strap 23. Actuator 24. Cross support rod 25. Supercapacitor battery 26. Quantum battery 27. Lower cabin ring 28. Rubber wheel 29. Lower opening cover 30. Component 31. Thick plastic film. DETAILED DESCRIPTION

[0031] The following is a further detailed description of the schematic diagram of the embodiment of the present invention.

[0032] The "electric, long-flight simple aircraft" shown in the figure is composed of:

[0033] 1. Vertical support 2. Autopilot 3. Cabin 4. Handle 5. Door 6. Crew 7. Rotor 8. Upper opening cover 9. Gap 10. Pulley 11. Timing belt 12. Light motor 13. Upper cabin ring 14. Perovskite photovoltaic cell 15. Seat 16. Combined wing 17. Motor 18. Coupling 19. Ring 20. Propeller 21. Grid 22. Strap 23. Actuator 24. Cross support 25. Supercapacitor 26. Quantum battery 27. Lower cabin ring 28. Rubber wheel 29. Lower opening cover 30. Component 31. Thick plastic film. Connect them in sequence to form the structure.

[0034] 1. The invention relates to a structure in which a combined wing is used as an upper wing and a fuselage is connected with a component. The chord line of the airfoil is long and the aspect ratio is small.

[0035] The combined wing is a traditional wing with 2-4 rotors installed perpendicular to its chord. Two ultra-light motors drive the front and rear 1-2 rotors. The shaft is equipped with bearings and is installed at the intersection of the I-shaped or X-shaped components connecting adjacent wings as its axis. Quantum batteries are connected in parallel with supercapacitor batteries to drive the synchronous pulleys on each rotor. The wing is short and wide, so its chord is long and the aspect ratio is small. The internal ribs and girders of the wing are preferably made of bamboo fiber composite materials, which are light and cheap. They are covered with fire-resistant and high-temperature resistant aramid fiber cloth and then painted. The outer surface Coated with flexible perovskite photovoltaic cells, it converts solar energy into electrical energy, which is gradually accumulated and stored in supercapacitor batteries for use when ultra-large current is needed in a short period of time, such as taking off or climbing rapidly when encountering a mountain; the wings are 150-500 mm away from the cabin to fully utilize the lift of the wing area without being blocked; the connecting parts are preferably made of carbon fiber composite material pipes, and the wings are short and do not occupy much area in the courtyard or road, which facilitates flexible and maneuverable flight in the air and is also easy to carry. The rotation of the rotor in the airflow will produce a "Magnus effect", which doubles the lift and increases the load.

[0036] 2. The cabin is a frame type with openings on the top, bottom, left and right. When the lower opening cover is opened, the occupant can stretch out his legs and run into the wind, assisting takeoff and replacing the landing gear. The characteristics are:

[0037] The cabin is a frame-type structure, with closed, circular rings at the top and bottom, a pointed nose and a converging tail. The preferred material is carbon fiber tubing, which is detachable for easy packaging. The rings are supported by vertical struts at the top and bottom. The upper opening allows for easy observation, while the lower openings flare to the sides, allowing passengers to extend their legs to the ground and control the aircraft by grasping cabin handles. The entire aircraft is carried on a backpack, and two small wheels at the rear touch the ground, dragging the entire aircraft to assist in takeoff. The propellers should then be coordinated to achieve maximum takeoff speed. Left and right openings facilitate passenger entry and exit. The front of the cabin is equipped with an autopilot panel, and the rear has a simple seat for easy piloting. Quantum batteries and supercapacitor batteries are installed under the seat. The rear of the seat houses the motor and outboard propeller, which are housed within the ring to improve efficiency. Four grid plates are installed at the rear of the ring, which can swing left and right under the action of actuators to assist the aircraft in turning. The instrument panel is equipped with a radar collision avoidance system, a laser altimeter that rotates 90 degrees and also serves as a laser rangefinder, and switches for the airspeed indicator and Beidou satellite positioning system, allowing the aircraft to maneuver and reach its destination.

[0038] 3. The rear of the cabin is equipped with only a propeller with an annular ring and a rear grid; the aircraft's maneuvering is controlled by the speed difference of the rotors in the combined wings, which greatly reduces the weight of the aircraft.

[0039] The maneuverability of the aircraft is controlled by the difference in rotor speed within the combined wing. When the rotor speed in front of the left and right wings is faster than that of the rear rotor, the lift increases due to the increase in the speed of the front group, causing the front of the aircraft wing to pitch up at a positive angle of attack, and the aircraft to climb, otherwise it will descend. When the speed of 2-4 rotors on the left wing is faster than that of 2-4 rotors on the right wing, the left wing will tilt up and the right wing will sink, and the aircraft will tilt. Combined with the swinging of the grid behind the rear annular ring of the propeller to the right, the aircraft will turn right, and vice versa. Therefore, the long support rods, rudders, horizontal rudders, etc. behind the fuselage are eliminated, and the fuselage is simple, light in weight, with a small turning radius, and flexible climbing and descending maneuvers.

[0040] 4. The aircraft is powered by a motor driving a propeller in an annular ring, with a grid plate installed behind the annular ring. The characteristics are:

[0041] The aircraft's propulsion is powered by an electric motor-driven propeller covered with a ring-shaped outer cover. Behind it are four grid plates that can swing left and right under the control of an actuator. This helps the aircraft turn left and right. Since there is no structure behind the fuselage except the propeller, the fuselage's moment of inertia is greatly reduced, making the aircraft more maneuverable. The propeller is driven by a quantum battery in parallel with a supercapacitor battery, which can store the electrical energy converted by the perovskite photovoltaic cells coated on the upper surface of the wing to meet short-term high-current needs. The quantum battery has a power-to-weight ratio of 2.5 kilowatts per kilogram and a service life of ten years.

[0042] 5. The upper surface of the wing is coated with flexible perovskite photovoltaic cells, which can convert solar energy into electrical energy and store it in supercapacitor batteries. The characteristics are:

[0043] The upper surface of the wing is coated with flexible perovskite photovoltaic cells. These cells are flexible enough to be applied to curved surfaces, are thin, light, and inexpensive, and have a light conversion rate of 26.1%. This makes them a preferred choice because they significantly increase the weight of the aircraft and reduce the total capacity of the quantum cells, thereby reducing the aircraft's weight. When not in flight, these cells can be placed outdoors, gradually accumulating solar energy and storing it in supercapacitors to power the propellers, rotors, and all other onboard electrical equipment. The quantum cells, supercapacitors, and the continuous flow of solar-converted electricity—three different power sources operating simultaneously in parallel—provide a double guarantee for the safe operation of the propeller motors.

[0044] 6. The cabin is provided with upper and lower opening covers. When fully opened, airflow can flow directly through to release slightly higher ground effect pressure, thereby shortening the landing distance. The upper opening cover is hung vertically on the component and can also serve as a speed brake, thereby shortening the landing distance. The characteristics are as follows:

[0045] There are upper and lower opening covers on the cabin. When both opening covers are fully opened, the airflow passes directly through the upper and lower parts of the cabin, weakening the slightly higher air pressure caused by the ground effect and shortening the landing distance. When the upper opening cover is opened and hung vertically on the component, it can also serve as a speed brake and shorten the landing distance.

[0046] 7. The cabin has a lower cabin ring with two rubber wheels on both sides, and handles and shoulder straps are installed at the load-bearing points at appropriate heights in the cabin. The characteristics are:

[0047] There is a lower cabin ring in the cabin, with rubber wheels installed on the left and right sides, front and back, and handles and straps installed at load-bearing points at appropriate heights in the cabin. Before takeoff and landing, the left and right lower opening covers are opened, and the legs are stretched out. The crew can hold the handles and carry the straps to control the direction of the aircraft, running forward into the wind to obtain a relative airflow speed of more than 2.5-4 meters per second, dragging the two rubber wheels on the ground behind to reduce the weight carried and assist the aircraft in takeoff. At this time, the propeller will work at its maximum working state. When landing, the upper and lower opening covers should be opened to allow airflow to pass through the cabin from top to bottom, and the upper opening cover should be hung on the structure to act as a speed brake to shorten the landing distance. The crew should slightly bend their knees and slowly brake according to the inertia of the aircraft, and the aircraft should be pitched down, automatically slowing the propeller and rotor until the aircraft stops with all four wheels touching the ground.

Claims

1. The present invention discloses an "electric, long-endurance, simple aircraft" comprising:

1. vertical struts 2. autopilot 3. cabin 4. handle 5. cabin door 6. crew 7. rotor 8. upper opening cover 9. gap 10. pulley 11. synchronous belt 12. lightweight motor 13. upper cabin ring 14. perovskite photovoltaic cell 15. seat 16. combined wing 17. motor 18. coupling 19. annular ring 20. propeller 21. grid 22. shoulder strap 23. actuator 24. cross struts 25. supercapacitor battery 26. quantum battery 27. lower cabin ring 28. rubber wheel 29. lower opening cover 30. structural member 31. thick plastic film, connected in sequence. The "electric, long-endurance, simple aircraft" is characterized by: The upper wing is a composite wing, connected to the cabin by structural members. It has a long chord and a small aspect ratio. The upper surface of the wing is coated with perovskite photovoltaic cells, which can convert solar energy into electricity and store it in supercapacitor batteries. These cells are connected in parallel with quantum batteries to power the rotor, propellers, and all electrical equipment on board. The wings are short and wide, allowing for flexible takeoff from roads and courtyards. The underwing cabins are 150-500 mm apart and connected by high-strength tubing. The wing and fuselage are separated to fully utilize the wing area to generate lift. The cabin is a frame type and can be disassembled for packaging and transportation. The two pointed boat-shaped frames on the upper and lower cabin circles are load-bearing frames, with a cabin door and a cross brace in the middle, and detachable vertical brace supports on both sides. The outside is covered with a transparent thick plastic film. The cabin has openings on the top, bottom, left and right. The upper opening is for observation and can be hung vertically on the structure to serve as a speed brake. It is also convenient for ventilation up and down the cabin to reduce the ground effect. The lower opening is conducive to extending the feet, and the direction is controlled by the handles in the cabin. The whole aircraft is carried on the back with a strap. There are 2 rubber wheels on the front and back of each side of the lower cabin circle. The rear two wheels can touch the ground, which reduces the weight of the whole aircraft by 1 / 2. Therefore, the whole aircraft can be easily carried on the back with a strap, and running helps to fly. The cabin has an autopilot in the front and a simple seat in the back. Two types of batteries are placed under the chair, and the chair is placed behind. The motor can drive the propeller with an annular ring outside the cabin. There is a grid behind the annular ring, which can assist the aircraft in turning left and right through the actuator; the combination of high speed of the left wing rotor, low speed of the right wing rotor, and high speed of the rotors in front of the left and right wings and low speed of the rotors behind them enables the aircraft to maneuver and can also turn by swinging the grid left and right; the high speed of the front rotor produces great lift, so the front wing will tilt up and the rear wing will sink to climb, and vice versa, it will glide and land; the aircraft has "Mars" and traditional wing lift, these two types of lift can provide double insurance to ensure flight safety, three power sources ensure the operation of the rotors and propellers, so that the flight safety of the passengers is reliably guaranteed; the rear of the aircraft cabin is simple, which greatly reduces the weight of the aircraft, and the moment of inertia is small, so it is flexible and has a much larger load capacity.

2. The "unlimited range, low fuel consumption, manually assisted aircraft" as claimed in claim 1, characterized in that: The combined wing is used as the upper monoplane: the wing is separated from the cabin, 150-500 mm apart, and is fixedly connected with components. The chord is long and the aspect ratio is small. The combined wing is a traditional wing section with 2-4 rotatable cylinders inserted perpendicular to its chord to form an upper wing. It is 150-500 mm away from the cabin and is fixedly connected with high-strength pipes. The wing is wide and short, with a long chord and a small aspect ratio. The purpose is to reduce the length of the cantilever beam, which can reduce structural strength and weight, making it easier to take off and land in a small space. The cabin is relatively stable near the ground, making it easy for the crew to stretch out their legs and run to help fly. The separation of the wing and the cabin allows airflow over the entire wing, ensuring that the entire wing area fully generates lift. The wing's load-bearing parts such as beams and ribs are light and inexpensive. The upper surface of the wing is coated with flexible perovskite photovoltaic cells. After collecting current, it is gradually stored in supercapacitor batteries and connected in parallel with quantum batteries to drive all electrical equipment on the aircraft. The supercapacitor battery can supply large current in a short period of time to prepare for urgent needs such as takeoff and emergency climb. It is connected in parallel with the quantum battery and photovoltaic cell to form a triple insurance to ensure the flight safety of the crew.

3. The "unlimited range, low fuel consumption, manually assisted aircraft" as claimed in claim 1, characterized in that: The cabin is shaped like a small boat with pointed ends, supported by a frame structure, detachable for easy transportation, and has openings up, down, left and right. The cabin is shaped like a small boat with pointed ends to reduce air resistance. It has two closed cabin circles, one above and one below, with a vertical strut in the middle. The strut is made of carbon fiber tubes and is detachable. The cabin doors are opened on the left and right for entry and exit. The upper opening cover can be used for observation. When it is hung vertically on the component between the wing and the body, it also serves as a speed brake. It can also allow the upper and lower openings to directly ventilate the air, weakening the slightly higher ground pressure due to the ground effect, making it easier for the aircraft to land quickly and shortening the taxiing distance. The lower opening cover is a left and right cabin door. There are four rubber wheels on the front and back of the lower cabin circle, and handles and straps are installed on the frame at an appropriate height for handholding. The handlebars control the direction, and the entire aircraft is carried on the back with a harness, leaving only the two small wheels at the back to drag on the ground, reducing the weight and making it easier for the crew to run forward. The wings have a relative airflow speed of more than 2.5-4 meters per second, and are positioned against the wind to assist in takeoff. At this time, the propeller should work at maximum power. The cabin is wrapped in thick, transparent plastic film, with an autopilot at the front and a simple seat fixed at the back. Two types of batteries are installed under the seat, and a motor is installed at the back to drive the propeller outside the cabin. The propeller is covered with a ring, and a grid is installed behind it. It can be swung left and right by an actuator to help the aircraft turn. There is no other structure behind the cabin, saving aircraft weight and moment of inertia.

4. The "unlimited range, low fuel consumption, manually assisted aircraft" as claimed in claim 1, characterized in that: The aircraft's maneuvering flight is achieved by controlling the rotor speed difference combination on the combined wing. It can not only produce the (Mars) effect to increase lift, but also make the aircraft pitch and turn left and right. The aircraft's maneuvering flight is accomplished by combining different rotor speeds on the left and right wings, and different front and rear groups. If the front 1-2 rotors on the left and right wings of the aircraft's combined wings rotate faster than the rear 1-2 rotors, the faster rotation speed and greater lift will cause the front end of the combined wing to tilt up and the rear end to sink, forming a climbing posture. Otherwise, it will descend. If the two rotor groups on the left combined wing rotate faster than the two rotor groups on the right combined wing, the left wing will tilt up and the right wing will sink, turning to the right in an inclined manner, and then coordinating with the grid to swing to the right, otherwise it will turn to the left, thus completing the aircraft's maneuvering flight. The aircraft can eliminate the need for rudders and horizontal rudders, making the aircraft structure simple, flexible, and lightweight, making it convenient for takeoff and landing in courtyards, small spaces on highways, and on roads.

5. The "unlimited range, low fuel consumption, manually assisted aircraft" as claimed in claim 1, characterized in that: The aircraft is propelled by an ultra-light motor that drives a ring-shaped propeller, followed by a grid that can swing left and right. The aircraft's propulsion power is an ultra-light motor driving a propeller inside an annular ring, behind which is a grid that can swing left and right to assist the aircraft in turning left and right; the motor is placed behind the seats in the cabin to protect it from frost, rain, snow and salt spray. Its shaft is connected to the propeller inside the annular ring through a coupling, behind which is a grid that can swing left and right to assist the aircraft in turning.

6. The "unlimited range, low fuel consumption, manually assisted aircraft" as claimed in claim 1, characterized in that: The upper surface of the wing is coated with perovskite photovoltaic cells to accumulate and convert electrical energy and store it in supercapacitor batteries and quantum batteries in parallel to supply power to all electrical equipment on the aircraft. Perovskite photovoltaic cells are coated on the upper surface of the wing. They are inexpensive and adaptable to curved surfaces. When not in flight, the upper surface of the aircraft's wing remains exposed to sunlight. The photovoltaic cells can then continue to store energy in supercapacitors for short-term, high-current, and emergency use, reducing the capacity of the quantum battery. Parallel quantum batteries can provide a continuous constant current over a ten-year lifespan, achieving a power-to-weight ratio of 2.5 kilowatts per kilogram. They can also be inverted to power household appliances using the home grid. With these three power sources, the aircraft has an unlimited range.

7. The "unlimited range, low fuel consumption, manually assisted aircraft" as claimed in claim 1, characterized in that: The cabin is provided with an upper opening cover and a lower opening cover, the lower opening cover can be opened to the left and the right, and cabin doors are opened on the left and the right. There are upper and lower opening covers on the cabin. When both covers are fully opened, air flows directly up and down through the cabin, weakening the ground effect of slightly higher air pressure, thereby reducing the landing distance. When the upper opening cover is hung vertically on the structure, it can also serve as a speed brake, thereby shortening the landing distance.

8. The "unlimited range, low fuel consumption, manually assisted aircraft" as claimed in claim 1, characterized in that: There is a lower cabin ring on the cabin, with two rubber wheels on the front and rear sides respectively, and handles and shoulder straps are installed at load-bearing points at appropriate heights in the cabin. The cabin is equipped with a lower cabin ring, with two rubber wheels on the front and rear sides respectively, and handles and straps are installed at the load-bearing points at appropriate heights in the cabin, so that the crew can open the left and right lower opening covers before takeoff, stretch out their legs, put on the straps, hold the handles with both hands, control the direction of the aircraft, and carry the aircraft on their backs. After that, the two wheels can touch the ground to share 1 / 2 of the aircraft's weight, and the aircraft can run 15-35 meters with the load. When the propeller is working at full power, it can take off from the ground. At this time, the crew can sit in a simple seat, turn on the autopilot, and complete the maneuver. The aircraft is assisted by a human operator for takeoff; for landing, the opposite is true. The upper and lower covers are opened to allow direct airflow over and under the cabin to reduce the impact of the ground effect. The upper cover is hung vertically on the structure and serves as a speed brake to shorten the landing distance. The operator puts on the harness and controls the direction with both hands. The rotor and propeller speeds are automatically reduced and the wings slowly descend toward the ground, allowing the aircraft to descend slowly. Pay attention to the direction and distance of people and vehicles at the landing site so that a go-around can be made if necessary. The crew runs with the inertia of the cabin and slowly brakes until it stops before turning off the motor.

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