A fully automated piloted single-person aircraft

Abstract

The application discloses a full-automatic driving single-person aircraft, and belongs to the technical field of single-person aircrafts. The aircraft integrates the advantages of multi-rotor and fixed-wing aircrafts. Four large-size three-blade propellers are arranged on the left and right sides to provide main lift, and four small-size two-blade propellers are arranged on the front and back sides to adjust the attitude of the unmanned aerial vehicle. The aircraft can take off and land vertically, and is free from dependence on a runway.

Description

Technical Field

[0001] This invention belongs to the field of single-person aircraft, and in particular a fully automated single-person aircraft. Background Technology

[0002] In the field of aircraft, rotorcraft have advantages such as vertical takeoff and landing, simple structure, and ease of maintenance, but their shortcomings are also particularly obvious, including small payload and short endurance. Similarly, fixed-wing aircraft have advantages such as long endurance, high flight efficiency, and large payload, but their disadvantages include the need for a runway for takeoff and a taxiing motion for landing, requiring sufficient ground space and airspace, and needing experienced operators. Since both types of aircraft have their own advantages and disadvantages, vertical takeoff and landing fixed-wing aircraft, which combine the characteristics of both types, have become a popular research topic.

[0003] Currently, fixed-wing aircraft achieve vertical takeoff and landing (VTOL) primarily through the following methods: jet engine thrust steering, lift fan, rotor-fixed-wing combination, tiltrotor, and tail-seat configuration. The Harrier fighter jet is a prime example of jet engine thrust steering, which redirects the exhaust gas to generate vertical lift; this method requires a jet engine. Lift fans typically utilize ducted fans located in the fuselage or other parts to provide downward thrust for VTOL. Rotor-fixed-wing combinations are common in current small VTOL fixed-wing aircraft. This configuration often combines a multi-rotor and a fixed wing. During takeoff and landing, flight control is primarily achieved by the multi-rotor; during level flight, the multi-rotor stops, and the fixed ducted fan and rotor cannot provide power, thus reducing the aircraft's efficiency to some extent. The V-22 Osprey tiltrotor aircraft is a prime example of a tiltrotor aircraft. This aircraft features rotating rotors at its wingtips. In helicopter mode, its rotor shaft is vertical, enabling vertical takeoff and landing (VTOL). In fixed-wing mode, the V-22's rotor shaft is horizontal and parallel to the fuselage axis, with the rotor acting as a propeller to provide thrust for level flight. This allows the V-22 to combine the VTOL capabilities of a helicopter with the high speed, long range, and low fuel consumption of a fixed-wing aircraft. However, the tiltrotor mechanism is heavy, difficult to develop, and has complex aerodynamic characteristics, placing significant pressure on reliability and maintenance costs. Large tiltrotor aircraft and vector jet / lift fan VTOL aircraft have complex power systems and high technical difficulty, and are primarily used in the military field.

[0004] In recent years, a new type of compound wing vertical takeoff and landing fixed-wing aircraft has been developed. During vertical takeoff and landing, it uses multiple rotors to provide lift and control torque, and then switches to fixed-wing level flight mode under the propulsion of the fixed-wing propeller. Compared with helicopters and tiltrotor aircraft, it is simple to control and has stable flight. However, vertical takeoff and landing and level flight are carried out by two independent power systems, which results in excessive "dead weight" and easily generates large drag, which seriously limits the development of this type of aircraft.

[0005] Most aircraft are powered by either pure electric motors or pure gasoline engines. Pure electric aircraft are easy to control and have high stability, but their range is relatively short. Pure gasoline engines can easily solve the range problem, but their control response and sensitivity are poor, making it difficult to accurately control and coordinate the rotor pitch and speed, thus failing to effectively guarantee stable flight, high-altitude and high-speed performance, and precise positioning. Furthermore, range has always been the biggest weakness of single-person aircraft. To address these issues, hybrid electric aircraft have been developed. Summary of the Invention

[0006] The purpose of this invention is to provide a fully automated single-person aircraft capable of vertical takeoff and landing, eliminating the need for a runway.

[0007] The technical solution to achieve the purpose of this invention is as follows:

[0008] A fully automated intelligent piloted single-person aircraft includes a fuselage and wings disposed on the left and right sides of the fuselage; the wings are equipped with propellers, which provide the main lift of the aircraft.

[0009] The fuselage adopts a seesaw-type structure, with legs located at the front, middle, and rear of the lower end;

[0010] When the aircraft is stationary on the ground, the front legs and the middle legs are in contact with the ground;

[0011] Arms are provided on the front left and right sides and the rear left and right sides of the fuselage; propellers are provided on the arms for adjusting the attitude of the aircraft.

[0012] When the aircraft is stationary on the ground, the propeller disks of the two front arms face upwards, and the propeller disks of the two rear arms face downwards; the propeller disks of the wings face upwards.

[0013] During vertical takeoff, the propellers on the front arm rotate to generate upward lift, pulling the nose of the aircraft upward so that the rear legs of the fuselage can contact the ground; when the propeller disks on the wings are parallel to the ground, the propellers on the wings and the propellers on the arms rotate together to achieve the takeoff function.

[0014] When the aircraft takes off and reaches the predetermined altitude, the propellers on the front arm decelerate while the propellers on the rear arm accelerate, working together to adjust the angle between the propeller disks of the wings and the ground to close to 90 degrees in order to enter the fixed-wing aircraft flight mode.

[0015] During vertical descent, the propellers on the front arm accelerate while the propellers on the rear arm decelerate, working together to bring the angle between the propeller disks of the wings and the ground close to 0 degrees, thus entering multi-rotor landing mode. After landing stabilizes, the propellers on the wings and the propellers on the front arm stop rotating, while the propellers on the rear arm generate upward lift, pulling the tail of the aircraft upward and causing the front legs of the fuselage to contact the ground.

[0016] The significant advantages of this invention compared to existing technologies are:

[0017] (1) When the single-person aircraft is in flight, its four three-bladed propellers provide forward thrust, and its four two-bladed propellers also provide some thrust. It enters fixed-wing aircraft flight mode, relying on the wings to generate sufficient lift to increase range. When taking off and landing vertically at the destination, it enters multi-rotor takeoff and landing mode, using four brushless motors at the front and rear to drive four two-bladed propellers to control the aircraft's pitch and roll attitude, thus eliminating the aircraft's dependence on runways. Without a bulky rotor tilting mechanism, it avoids the disadvantages of aircraft like the Osprey, which repeatedly crashed due to equipment failures during rotor thrust conversion.

[0018] (2) When the aircraft is stationary on the ground and ready to take off, a seesaw-type fuselage is designed using the seesaw principle. This can cleverly change the angle between the wings and the ground, so that the disks of the four three-bladed propellers are nearly parallel to the horizontal plane. Therefore, the single-person aircraft takes off almost vertically.

[0019] (3) It adopts a hybrid power system, which has the advantages of long endurance of the fuel engine and fast response of the electric motor. It retains the high energy of the fuel by generating electricity through fuel. During flight, even if one fuel engine or brushless motor fails, the remaining fuel engines and brushless motors can ensure flight safety and landing. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the overall structure of a fully automated single-person aircraft.

[0021] Figure 2 This is a schematic diagram of the main external structure of a fully automated single-person aircraft according to the present invention;

[0022] Figure 3 This is a schematic diagram of the main internal structure of a fully automated single-person aircraft according to the present invention;

[0023] Figure 4 This is a schematic diagram of three working states of a fully automated single-person aircraft according to the present invention;

[0024] Figure 5This is a schematic diagram of a seesaw-shaped fuselage of a fully automated single-person aircraft that cleverly changes the angle between the wing and the ground using the seesaw principle.

[0025] Figure 6 This is a schematic diagram of the minimum folded size for land transportation of a fully automated single-person aircraft according to the present invention;

[0026] Figure 7 This is a schematic diagram showing the passengers seated in a fully automated single-person aircraft according to the present invention;

[0027] Figure 8 This is a schematic diagram of a passenger opening the luggage compartment and putting in personal belongings in a fully automated single-person aircraft according to the present invention.

[0028] Figure 9 This is a three-view and perspective view of a fully automated single-person aircraft with its transparent canopy closed, according to the present invention. Detailed Implementation

[0029] The present invention will be further described below with reference to the accompanying drawings and specific embodiments.

[0030] Combination Figures 1-9 This embodiment of a fully automated single-person aircraft includes a seesaw-shaped fuselage 5, wings 8 disposed on the left and right sides of the fuselage 5, arms 9 disposed on the left and right sides of the front end of the fuselage 5, and arms 9 disposed on the left and right sides of the rear end. The wings 8 are equipped with two three-bladed propellers 6, and the arms 9 are equipped with one two-bladed propeller 3.

[0031] The seesaw-shaped fuselage 5 mainly contains seats 13, fuel tanks 14, flight control systems 15, lithium batteries 16, and parachutes 1. The cockpit is located in the center of fuselage 5, equipped with a fully transparent canopy 4, providing passengers 10 with excellent and wide visibility. A whole-aircraft ejection parachute 1 is installed on the rear top of the cockpit, and a luggage compartment 12 is located under the cockpit seat 13. Passengers can open the transparent canopy 4 first, then open the luggage compartment cover 11 under the seat 13 to place their personal belongings. A larger luggage compartment can also be designed at the rear of the aircraft or on the back of the seat 13 to accommodate more items.

[0032] The 13 seats in the cockpit can be designed to rotate at a slightly adjustable angle of about 30 to 45 degrees, so that when passengers enter the cockpit and sit in the 13 seats, they will not be forced to lie down, thus further improving the riding experience.

[0033] Its front arm 9 is designed to be foldable, with folded dimensions of approximately 5800mm in length, 2060mm in width, and 1590mm in height, facilitating long-distance transport by truck to customers. The cockpit is widened by about half a meter laterally, transforming it from a single-person to a two-person aircraft. Of course, its wings 8 can also be designed to be foldable, with fully folded dimensions of approximately 4000mm in length, 2060mm in width, and 1590mm in height. It can also transport cargo to its destination for missions. For example, in the event of earthquakes or floods, it can quickly deliver drinking water, food, and medical supplies.

[0034] It has two brushless motors 2 mounted at the front and rear of its fuselage. Each brushless motor 2 drives two small two-bladed propellers 3 to control the aircraft's pitch forward and backward. When the aircraft is stationary on the ground, the two-bladed propellers 3 on the front two arms 9 have their disks facing upward, while the two-bladed propellers 3 on the rear two arms 9 have their disks facing downward, and their rotation directions are opposite. Furthermore, the three-bladed propellers 6 on the wings 8 have their disks facing upward.

[0035] Two 7 fuel engines are mounted on the front of each of the wings 8 on the left and right sides of the middle section to drive four large three-bladed propellers 6 as the main lift or thrust.

[0036] In terms of power, a hybrid powertrain can be used. During flight, the four fuel engines 7 can directly drive small generators inside the wings 8 to power the four brushless motors 2, thereby increasing power and range. Batteries 16 and flexible fuel tanks for storing fuel can also be placed inside the wings 8 on both sides, further increasing the range!

[0037] The fuselage has two shock-absorbing wheel legs at the front and middle of its lower section, and two shock-absorbing pad legs at the rear. The front and middle shock-absorbing wheel legs are equipped with small wheels for easy movement and transport. A folding, retractable step can also be designed in front of the cockpit for easy passenger access.

[0038] like Figure 4 As shown, when the aircraft is stationary on the ground, the two front shock-absorbing wheel legs 17 and the two middle shock-absorbing wheel legs 18 under the seesaw-shaped fuselage 5 are in contact with the ground, while the two rear shock-absorbing pad legs 19 are tilted backward and upward, with the angle between the line connecting their bottoms and the bottoms of the middle shock-absorbing wheel legs and the ground being 25 degrees. The nose of the wings 8 is tilted forward and upward at 65 degrees to the ground. The front main arm 9 of the seesaw-shaped fuselage 5 is tilted downward, forming a 10-degree angle with the ground and a 75-degree angle with the middle left and right wings 8. The rear main arm 9 of the seesaw-shaped fuselage 5 is tilted upward, forming a 40-degree angle with the ground and a 75-degree angle with the middle left and right wings 8.

[0039] During vertical takeoff and landing, the two rear shock-absorbing legs 19 and the two middle shock-absorbing wheel legs 18 under the seesaw-type fuselage 5 are in contact with the ground, while the two front shock-absorbing wheel legs 17 tilt forward and upward, with the angle between the line connecting their bottoms and the bottoms of the middle shock-absorbing wheel legs and the ground being 25 degrees. The nose of the wing 8 tilts forward and upward at an angle of up to 90 degrees to the horizontal plane, and the rotor disks of the four three-bladed propellers 6 on the wing 8 are parallel to the ground. The rotor disks of the two two-bladed propellers 3 on the front folding arm 9 and the rear main arm 9 also have an angle of 15 degrees to the ground.

[0040] When flying in the air, the wings 8 are parallel to the horizontal plane, the disk surfaces of the four three-bladed propellers 6 are perpendicular to the horizontal plane, and the angle between the disk surfaces of the two two-bladed propellers 3 on the front foldable arm 9 and the disk surfaces of the two two-bladed propellers 3 on the rear main arm 9 is 150 degrees.

[0041] Four fuel engines 7 are arranged laterally on the wings 8, directly driving four large three-bladed propellers 6 using a direct-drive fuel-powered system. Each fuel engine 7 drives one three-bladed propeller 6. The pitch of the three-bladed propellers 6 is fixed, and the lift is changed by adjusting the engine throttle. The three-bladed propellers 6 are directly mounted on the engine shafts, eliminating the need for a transmission structure. The two innermost three-bladed propellers 6 on the left and right sides have essentially constant speeds, serving as the primary forward thrust. The speeds and thrusts of the two outermost three-bladed propellers on the left and right sides can be changed at any time to control the aircraft's left or right turn attitude. During vertical takeoff and landing at the destination, the aircraft enters multi-rotor takeoff and landing mode, where the four three-bladed propellers 6 on the wings 8 provide the primary vertical lift. A brushless motor 2 is mounted on each of the two foldable arms 9 at the front and the two non-foldable arms 9 at the rear of the seesaw-shaped fuselage 5, for a total of four brushless motors 2, driving four small two-bladed propellers 3 to control the aircraft's pitching attitude.

[0042] When the single-person aircraft's wing 8 is tilted forward and upward at a 65-degree angle to the horizontal and comes to a stable stop on the ground, the two two-bladed propellers 3 on the foldable front arm 9 of the aircraft first rotate to generate upward lift. Supported by the two central shock-absorbing wheel legs 18 under the seesaw-type fuselage 5, these propellers pull the nose of the aircraft upward. Then, the two rear shock-absorbing pad legs 19 of the seesaw-type fuselage 5 contact the ground. When the rotor discs of the four three-bladed propellers 6 on the wing 8 are parallel to the ground, the four three-bladed propellers 6 and the four two-bladed propellers 3 rotate together, achieving takeoff.

[0043] Once the aircraft reaches a suitable altitude after takeoff, the two two-bladed propellers 3 on the front folding arm gradually reduce their speed, while the two two-bladed propellers 3 on the rear main arm gradually increase their speed. Together, they adjust and widen the forward angle between the rotor discs of the four three-bladed propellers 6 on the wing 8 and the ground, bringing the angle between the rotor discs of the four three-bladed propellers 6 on the wing 8 and the ground close to 90 degrees. At the same time, the four three-bladed propellers 6 gradually increase their speed, pulling the entire aircraft forward to enter fixed-wing aircraft flight mode, relying on the wings 8 to generate sufficient lift to increase range.

[0044] Upon reaching the destination and landing, the operation is reversed. The two two-bladed propellers 3 on the front folding arm gradually increase their speed, while the two two-bladed propellers 3 on the rear main arm gradually decrease their speed. Together, they adjust and reduce the rearward angle between the rotor discs of the four three-bladed propellers 6 on the wing 8 and the ground, bringing the angle between the rotor discs of the four three-bladed propellers 6 on the wing 8 and the ground close to 0 degrees. This initiates a multi-rotor landing mode, allowing the entire single-person aircraft to land smoothly and gently. After stabilizing, the four three-bladed propellers 6 and the two two-bladed propellers 3 on the front folding arm stop rotating. Then, the two two-bladed propellers 3 on the rear main arm of the aircraft begin rotating, generating upward lift. Supported by the two central shock-absorbing wheel legs 18 under the seesaw-type fuselage 5, they pull the tail of the aircraft upward. The two front shock-absorbing wheel legs 17 of the seesaw-type fuselage 5 then touch the ground, finally achieving a stable stop.

[0045] When this manned aircraft takes off vertically to a suitable altitude, it uses four brushless motors 3 to drive the propellers, changing its flight attitude so that its wings 8 are parallel to the ground, entering fixed-wing aircraft flight mode. The wings 8 generate sufficient lift to increase its range. Therefore, it eliminates the need for complex and cumbersome rotor tilting mechanisms, cleverly avoiding the shortcomings of other solutions. For vertical takeoff and landing, the operation is reversed, bringing the rotor discs of its four main propellers nearly parallel to the ground, entering helicopter takeoff and landing mode, thus freeing the aircraft from dependence on runways. The cockpit and wings are hollow and sealed, allowing the main body to float on water. Therefore, even if a malfunction occurs and the parachute deploys, landing in a river or lake is not a problem. Even in areas infested with wild animals, the cockpit can protect the passengers' safety!

[0046] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A full-automatic driving single-person aircraft, comprising a fuselage, wings arranged on the left and right sides of the fuselage, and a propeller arranged on the wing for providing main lift of the aircraft, characterized in that the fuselage adopts a seesaw structure, and a leg is arranged at the front, middle and rear of the lower end of the fuselage; when the aircraft is static on the ground, the front leg and the middle leg are in contact with the ground, the rear leg is raised upward, the head of the wing is tilted upward, the front arm is inclined downward, and the rear arm is raised upward; propellers are arranged on the left and right sides of the front and rear of the fuselage, and the propellers are used for adjusting the attitude of the aircraft; when the aircraft is static on the ground, the propeller discs of the two front arms face upward, the propeller discs of the two rear arms face downward, and the propeller discs of the wings face upward; when taking off vertically, the propellers of the front arms rotate to generate upward lift, which lifts the head of the aircraft upward to make the rear leg of the fuselage contact the ground; when the propeller discs of the wings are parallel to the ground, the propellers of the wings and the arms rotate and work together to achieve the function of taking off; when taking off to a predetermined height, the propellers of the front arms are decelerated, the propellers of the rear arms are accelerated, and the included angle between the propeller discs of the wings and the ground is adjusted to be close to 90 degrees to enter the flight mode of a fixed-wing aircraft; when landing vertically, the propellers of the front arms are accelerated, the propellers of the rear arms are decelerated, and the included angle between the propeller discs of the wings and the ground is adjusted to be close to 0 degrees to enter the landing mode of a multi-rotor aircraft; after landing is stable, the propellers of the wings and the front arms stop rotating, the propellers of the rear arms generate upward lift, which lifts the tail of the aircraft upward to make the front leg of the fuselage contact the ground. Two brushless motors are arranged at the front and rear of the fuselage, and each brushless motor drives two propellers of each arm.

2. The fully automated single-pilot aircraft of claim 1, wherein, Two fuel engines are arranged on the left and right wings to drive the propellers of the wings.

3. The fully automated single-pilot aircraft of claim 1, wherein, The four fuel engines directly drive generators inside the wings to supply power to the four brushless motors; lithium batteries and soft fuel tanks for storing fuel are arranged inside the wings.

4. The fully automated single-pilot aircraft of claim 3, wherein, The middle of the fuselage is a cockpit, which is provided with a full-transparent transparent canopy, a set of whole-machine ejection parachutes are arranged at the top of the cockpit, and a luggage compartment is arranged under the seat of the cockpit.

5. The fully automated single-pilot aircraft of claim 1, wherein, The propellers of the arms adopt two-blade propellers, and the propellers of the wings adopt three-blade propellers.

6. The fully automated single-pilot aircraft of claim 1, wherein, Wheels are arranged on the front and middle legs.

7. The fully automated single-pilot aircraft of claim 1, wherein, A luggage compartment is arranged at the rear of the aircraft or the back of the seat.

8. The fully automated single-pilot aircraft of claim 1, wherein, The arms and the wings are foldable structures.

9. The fully automated single-pilot aircraft of claim 1, wherein, ​

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