A disc-shaped aircraft

Abstract

The present invention discloses a disc-shaped aircraft comprising an upper disc wing, a lower disc wing, and an inner cabin. The upper disc wing is provided with air guide and air compressor blades, while the lower disc wing is provided with air guide and air flow straightening blades. A hydrogen-powered drive motor is eccentrically fixed within the inner cabin. The drive motor has upper and lower output shafts, the upper output shaft being connected to a coaxial counter-rotating mechanism, which is connected to a power output gear. An air inlet is formed between the air guide and air compressor blades within the upper disc wing. Air enters the inlet, is accelerated and pressurized by the compressor blades, decelerated and pressurized by the diffuser blades outside the inner cabin, and then enters the lower disc wing. The high-pressure air then flows through the guide of the lower disc wing and the expansion flow passage outside the lower portion of the inner cabin. The high-pressure air is fully expanded and discharged from the air jet at maximum velocity, generating lift. The present invention conceals the lift-generating impeller blades within the fuselage, allowing all inhaled air to be used for lift generation, significantly improving efficiency and making the inner cabin space more convenient for equipment and payload placement.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, in particular to a disc-shaped aircraft. Background Art

[0002] As a unique aircraft design, disc-shaped aircraft have long attracted widespread interest in the aviation field. Their distinctive shape allows for vertical takeoff and landing, hovering and hovering, flight in any direction, and rapid response. They also boast low drag during level flight and rapid deceleration by adjusting their attitude to face the wind with a disc-shaped surface, highlighting their novel flight characteristics and maneuverability. Disc-shaped aircraft have applications in a variety of fields, including civil aviation, military reconnaissance, and logistics, and possess enormous market potential and application value.

[0003] However, existing disc-shaped aircraft designs mostly feature coaxial, counter-rotating rotors in the center of the fuselage to generate lift. While this design enables vertical takeoff and landing and hovering, the rotors occupy a large area and volume, resulting in a low payload. Furthermore, these disc-shaped aircraft are essentially still rotorcraft and do not utilize the aerodynamic advantages of disc wings. Furthermore, their open rotor airflow diffuses the high-pressure air beneath the rotors, resulting in relatively low airflow efficiency and low lift.

[0004] Currently, the most common disc-shaped aircraft on the market are mostly rotorcraft (such as quadrotors, hexacopters, and coaxial counter-rotating twin rotors). While capable of vertical takeoff and landing and hovering, their appearance and flight principles differ significantly from those of disc-shaped aircraft. Multirotor aircraft typically rely on multiple independent motors and rotors, resulting in complex structures, high energy consumption, and a low payload ratio. In contrast, disc-shaped aircraft are driven entirely by a single or small number of power sources. Their large, regular wing surfaces, if properly utilized, can achieve higher energy efficiency and a simpler structure.

[0005] In recent years, with the rapid development of new energy technologies, hydrogen energy, as a clean and efficient form of energy, has gradually gained application in the aviation sector. Hydrogen-powered motors offer advantages such as high energy density and low emissions, providing continuous and stable power output for aircraft. The widespread use of hydrogen energy has enabled the rapid development and application of disc-shaped aircraft, primarily by facilitating structural optimization and significantly improving payload, endurance, and environmental friendliness.

[0006] In summary, the existing disc-shaped aircraft design still has room for improvement in terms of cost, structure and performance. Therefore, we propose a disc-shaped aircraft to solve the problems raised above. Summary of the Invention

[0007] The object of the present invention is to provide a saucer-shaped aircraft to solve the problems raised in the above background technology.

[0008] To achieve the above-mentioned object, the present invention provides the following technical solution: a disc-shaped aircraft, comprising: an upper disc wing, a lower disc wing, and an inner cabin, wherein the upper and lower ends of the inner cabin are rotatably connected to the upper disc wing and the lower disc wing respectively through bearings, and the inner cabin is fixedly connected to a rudder ring, which is located at the edge connection between the upper and lower disc wing;

[0009] A hydrogen energy drive motor is eccentrically fixed in the inner cabin. The hydrogen energy drive motor is provided with upper and lower output shafts rotating in the same direction. The upper output shaft is connected to a reverse rotation mechanism to output power, realizing reverse rotation drive with the lower output shaft, thereby providing reverse rotation power to the upper and lower disc wings.

[0010] The output end of the coaxial counter-rotating mechanism and the lower output shaft of the hydrogen energy drive motor are both connected to the power output gear;

[0011] The upper and lower disc wings are respectively provided with a transmission gear ring 1 and a transmission gear ring 2 at the connection with the bearing. The transmission gear ring 1 is meshed with the power output gear, and the transmission gear ring 2 is meshed with the output gear of the lower output shaft of the hydrogen energy motor. A differential is provided between the transmission gear ring 2 and the lower end gear of the motor to enable the upper and lower disc wings to rotate at a differential speed.

[0012] The upper disc wing is provided with air guide and compression blades, and the air inlet is between the air guide and compression blades. The lower disc wing is provided with air guide and straightening blades, and the bottom of the inner cabin is provided with speed increasing and pressure reducing blades and an air jet port.

[0013] Preferably, diffuser blades are provided around the outer side of the inner cabin to decelerate and pressurize the incoming high-speed airflow and guide the airflow back to the lower disc wing.

[0014] Preferably, the inner cabin is connected to four attitude control guide tubes, and the attitude control guide tubes are connected to the vector nozzles on the edge of the inner cabin.

[0015] Preferably, the end of the attitude control guide tube is connected to four evenly distributed vector nozzles on the edge of the inner cabin through a hose, and the high-pressure air in the attitude control guide tube is ejected through the vector nozzles. The vector nozzles are driven by a drive motor installed in the edge of the inner cabin to achieve deflection, thereby changing the direction of the airflow ejected from the vector nozzles, thereby achieving control of the attitude and movement direction of the aircraft.

[0016] Preferably, a flow control valve is provided at the front end of the attitude control flow guide tube, which can control the size and intensity of the airflow ejected from the vector nozzle, thereby achieving control of the attitude and direction of the aircraft.

[0017] Preferably, a load compartment door is provided at the bottom of the inner compartment, and a bearing is sleeved on the outer side of the load compartment door.

[0018] Compared with the prior art, the present invention has the following beneficial effects:

[0019] The upper and lower disc wings rotate in opposite directions to self-balance the torque, and the inner cabin is stable in the axial direction;

[0020] Air enters the air flow channel from the air inlet of the upper disc wing, then passes through the compressor impeller to produce high pressure energy, and then passes through the guide of the blades inside the lower disc wing, and is ejected from the nozzle of the lower disc wing with high efficiency.

[0021] Since the supercharging blades are hidden inside the upper and lower disc wings, the disc wings have a regular and clean shape, which can fully exert the aerodynamic performance of the disc wings. At the same time, it utilizes the Coanda effect to increase some lift, thereby increasing endurance.

[0022] The counter-rotating upper and lower disc wings have a large moment of inertia, and their gyroscopic effect gives the aircraft high axial stability;

[0023] The compressor blades that generate power are arranged on the outside of the aircraft, leaving a complete and regular internal space for the cabin, which can easily arrange the onboard equipment and payload;

[0024] The attitude control compressor motor drives the attitude control compressor impeller to inhale air and pressurize it, and then ejects it from the vector nozzle through the attitude control guide tube to change the horizontal direction and pitch attitude of the aircraft;

[0025] The axial steering of the aircraft can be achieved by utilizing the differential rotation of the upper and lower disc wings. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 It is a structural schematic diagram of the present invention;

[0027] Figure 2 is a side sectional view of the present invention;

[0028] Figure 3 For the present invention Figure 2 A magnified view of point A;

[0029] Figure 4 For the present invention Figure 2 Enlarged view of point B;

[0030] Figure 5 For the present invention Figure 2 Enlarged view of point C;

[0031] Figure 6 A top view of the coupling between the transmission gear ring 1 and the power output gear in the present invention;

[0032] Figure 7 Schematic diagram of airflow direction of the present invention.

[0033] In the figure: 1. Upper disc wing; 11. Air guide and compression blades; 12. Transmission gear ring 1; 2. Lower disc wing; 21. Air guide and straightening blades; 22. Transmission gear ring 2; 3. Inner cabin; 31. Payload bay door; 32. Jet nozzle; 33. Diffuser blades; 34. Differential; 35. Pressure reduction blades; 6. Bearing; 8. Hydrogen energy drive motor; 81. Coaxial counter-rotating mechanism; 82. Power take-off gear; 9. Rudder ring; 91. Vector nozzle; 92. Hose; 93. Drive motor; 94. Attitude control guide tube; 95. Flow control valve. DETAILED DESCRIPTION

[0034] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0035] See also Figure 1-7 The present invention provides a technical solution: a disc-shaped aircraft, comprising: an upper disc wing 1, a lower disc wing 2, an inner cabin 3 and a rudder ring 9.

[0036] The upper and lower ends of the inner cabin 3 are rotatably connected to the upper disc wing 1 and the lower disc wing 2 through bearings 6, respectively, to achieve the rotation of the upper disc wing 1 and the lower disc wing 2 relative to the inner cabin 3;

[0037] A hydrogen energy drive motor 8 is eccentrically fixed in the inner cabin 3. The hydrogen energy drive motor 8 is provided with two upper and lower coaxial output shafts, and the upper output shaft is connected to the coaxial counter-rotating mechanism 81.

[0038] The lower output shaft of the hydrogen energy drive motor 8 is directly connected to a power output gear 82, and the output end of the coaxial counter-rotating mechanism 81 is connected to another power output gear 82;

[0039] A transmission gear ring 12 is provided at the junction of the upper disc wing 1 and the bearing 6, and the transmission gear ring 12 is engaged with the power output gear 82 driven by the coaxial counter-rotating mechanism 81;

[0040] A transmission gear ring 22 is provided at the junction of the lower disc wing 2 and the bearing 6. The transmission gear ring 22 is connected to the power output gear 82 directly connected to the hydrogen energy drive motor 8 through the differential 34;

[0041] When driving the lower dish wing 2 to rotate, the speed of the lower dish wing 2 can be adjusted by the differential 34 to achieve a speed difference with the upper dish wing 1. The upper dish wing 1 and the lower dish wing 2 rotate in opposite directions, using the gyro effect to provide stability for the aircraft.

[0042] The upper disc wing 1 is provided with air guide and pressure vanes 11, and the air guide and pressure vanes 11 are between the air guide and pressure vanes 11. Diffuser vanes 33 are provided on the outer periphery of the inner cabin 3, and speed-increasing and pressure-reducing vanes 35 are provided on the outer lower side of the inner cabin 3. A pressure-increasing and pressure-reducing flow channel is formed between the speed-increasing and pressure-reducing vanes 35. The lower disc wing 2 is provided with air guide and straightening vanes 21. The upper disc wing 1 rotates at high speed, sucking air into the air intake channel, accelerating and pressurizing the air, and the high-speed and high-pressure air flows into the diffuser vanes 33 provided on the outer periphery of the inner cabin 3. The air is further decelerated and pressurized, and flows back to the air guide and straightening vanes 21 in the lower disc wing 2. Through the rotation of the air guide and straightening vanes 21, the air is pressed into the pressure-increasing and pressure-reducing flow channel on the outer lower part of the inner cabin 3, and then ejected from the annular jet port 32 formed by the center of the lower disc wing 2 and the load bay door 31 at the lower part of the inner cabin 3, generating lift.

[0043] There are four evenly distributed attitude control guide tubes 94 at the connection between the outside of the inner cabin 3 and the edge. The other end of the attitude control guide tube 94 is connected to the vector nozzle 91 through a hose 92. The high-pressure air in the flow channel passes through the attitude control guide tube 94 and is ejected from the vector nozzle 91.

[0044] The four vector nozzles 91 can be driven by a driving motor 93 provided on the edge to drive the deflection of the vector nozzles 91 to achieve control of the aircraft's attitude.

[0045] A flow control valve 95 is provided between the front end of the attitude control flow guide tube 94 and the vector nozzle 91 , which can control the size and intensity of the airflow ejected from the vector nozzle 91 .

[0046] A load bay door 31 is provided at the bottom of the inner cabin 3 , and a bearing 6 is sleeved on the outer side of the load bay door 31 . The load bay door 31 is used for loading equipment and loads into the inner cabin 3 .

[0047] Working principle: After the hydrogen energy drive motor 8 is started, the upper output end of the hydrogen energy drive motor 8 drives the upper disc wing 1 to rotate through the coaxial counter-rotating mechanism 81 and the power output gear 82 thereon. The output shaft of the hydrogen energy drive motor 8 directly drives the lower power output gear 82 and the differential 34 to drive the lower disc wing 2 to rotate. The coaxial counter-rotating mechanism 81 is used to achieve the reverse rotation of the upper disc wing 1 and the lower disc wing 2. The air guide and pressure blades 11 inside the upper disc wing 1 inhale air, and after the processes of speed increase and pressure boost, speed reduction and pressure expansion, and backflow rectification, the air is ejected from the jet port 32 of the lower disc wing 2 to provide lift for the aircraft. The gyroscopic effect is used to provide stability for the aircraft, and the Coanda effect is used to increase a portion of the lift.

[0048] During the flight, the high-pressure air in the flow channel is ejected from the vector nozzle 91 through four evenly distributed attitude control guide tubes 94 to change the flight attitude of the aircraft.

[0049] The contents not described in detail in this specification belong to the prior art known to those skilled in the art.

[0050] While embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions, and variations may be made to these embodiments without departing from the principles and spirit of the invention, and that the scope of the invention is defined by the appended claims and their equivalents.

Claims

1. A disc-shaped aircraft, comprising: An upper disc wing (1), a lower disc wing (2) and an inner cabin (3), characterized in that: the upper and lower ends of the inner cabin (3) are rotatably connected to the upper disc wing (1) and the lower disc wing (2) through bearings (6), the inner cabin (3) is fixedly connected to a rudder ring (9), and the rudder ring (9) is located at the edge connection of the upper disc wing (1) and the lower disc wing (2); A hydrogen energy drive motor (8) is eccentrically fixedly arranged in the inner cabin (3), and the hydrogen energy drive motor (8) is provided with two upper and lower output shafts rotating in the same direction, and the upper output shaft is connected to a coaxial reverse rotation mechanism (81) to output power, thereby realizing reverse rotation drive with the lower output shaft, and providing reverse rotation power for the upper disc wing (1) and the lower disc wing (2); The output end of the coaxial counter-rotating mechanism (81) and the lower output shaft of the hydrogen energy drive motor (8) are both connected to a power output gear (82); The upper disc wing (1) and the lower disc wing (2) are respectively provided with a transmission gear ring 1 (12) and a transmission gear ring 2 (22) at the connection position with the bearing (6); the transmission gear ring 1 (12) is meshedly connected to the power output gear (82); the transmission gear ring 2 (22) is meshedly connected to the power output gear (82) of the lower output shaft of the hydrogen energy drive motor (8); a differential (34) is provided between the transmission gear ring 2 (22) and the power output gear (82) at the lower end of the motor (8), so that the upper disc wing (1) and the lower disc wing (2) rotate at a differential speed; The upper disc wing (1) is provided with air guide and pressure blades (11), and an air inlet is provided between the air guide and pressure blades (11). The lower disc wing (2) is provided with air guide and flow straightening blades (21), and the bottom of the inner cabin (3) is provided with speed increasing and pressure reducing blades (35) and an air jet (32).

2. A disc-shaped aircraft according to claim 1, characterized in that: Diffuser blades (33) are provided around the outer side of the inner cabin (3) to decelerate and pressurize the incoming high-speed airflow and guide the airflow back to the lower disc wing (2).

3. A disc-shaped aircraft according to claim 2, characterized in that: The inner cabin (3) is connected to four attitude control flow guide pipes (94), and the attitude control flow guide pipes (94) are connected to the vector nozzles (91) of the rudder ring (9).

4. A disc-shaped aircraft according to claim 3, characterized in that: The end of the attitude control guide tube (94) is connected to four evenly distributed vector nozzles (91) on the edge of the inner cabin through a hose (92). The high-pressure air in the attitude control guide tube (94) is ejected through the vector nozzles (91). The vector nozzles (91) are driven by a drive motor (93) installed in the rudder ring (9) to achieve deflection, thereby changing the direction of the airflow ejected from the vector nozzles (91) to achieve control of the attitude and movement direction of the aircraft.

5. A disc-shaped aircraft according to claim 4, characterized in that: A flow control valve (95) is provided at the front end of the attitude control flow guide tube (94), which can control the size and intensity of the airflow ejected from the vector nozzle (91), thereby achieving control of the attitude and direction of the aircraft.

6. The disc-shaped aircraft according to claim 1, characterized in that: A load cabin door (31) is provided at the bottom of the inner cabin (3), and a bearing (6) is sleeved on the outer side of the load cabin door (31).

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