Saucer-shaped aircraft

Abstract

The saucer-shaped aircraft comprises an upper saucer wing, a lower saucer wing and an inner cabin, air guiding and compressing blades are arranged in the upper saucer wing, air guiding and rectifying blades are arranged in the lower saucer wing, a hydrogen energy source driving motor is eccentrically and fixedly arranged in the inner cabin, the driving motor is provided with an upper output shaft and a lower output shaft, the upper output shaft is connected with a coaxial reverse rotating mechanism, and the lower output shaft is connected with a coaxial reverse rotating mechanism. The coaxial reverse rotation mechanism is connected with a power output gear, air inlet channels are formed between the air guide compression blades in the upper disc wing, air enters the air inlet channels, is subjected to acceleration and pressurization of the compression blades and deceleration and pressurization of the diffusion blades outside the inner cabin, then enters the lower disc wing, is guided by the lower disc wing and is subjected to expansion flow channels on the outer side of the lower portion of the inner cabin, and finally enters the lower disc wing. The high-pressure supplied air is completely expanded and is separated out from the air spraying opening at the maximum speed, and lifting force is generated. The impeller blades for generating lift force are hidden in the fuselage, all sucked gas can be used for generating the lift force, efficiency is greatly improved, and arrangement of equipment and loads is more convenient through the inner cabin space.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and specifically 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. The disc-shaped aircraft has a special shape and has the characteristics of vertical takeoff and landing, hovering and staying in the air, flying in any direction, fast response speed, etc. When flying horizontally, the resistance is small, and by adjusting the attitude to face the wind with the disc surface, it can quickly decelerate, highlighting novel flight characteristics and maneuverability. Disc-shaped aircraft can be applied to multiple fields such as civil aviation, military reconnaissance, and logistics transportation, and have huge market potential and application value.

[0003] However, most of the existing disc-shaped aircraft designs are equipped with coaxial contra-rotating rotors in the center of the fuselage to generate lift. Although this design can achieve vertical takeoff and landing and hovering, the rotors occupy a large area and volume, resulting in a low payload. In addition, this type of disc-shaped aircraft is essentially still a rotorcraft and does not utilize the aerodynamic performance advantages of the disc wings. Again, its open rotor airflow, and the high-pressure air under the rotor diffuses around, resulting in relatively low airflow efficiency and small lift.

[0004] Currently, the common disc-shaped aircraft on the market are mostly rotorcraft (such as quadcopters, hexacopters, and coaxial contra-rotating bi-rotors, etc.). Although they can achieve vertical takeoff and landing and hovering, their shapes and flight principles are quite different from those of disc-shaped aircraft. Multi-rotor aircraft usually rely on multiple independent motors and rotors, with complex structures and high energy consumption, and a small payload ratio. While disc-shaped aircraft are driven by a single or a small number of power sources to drive the entire aircraft, and disc-shaped aircraft have a large proportion of regular wing surfaces. As long as they are well utilized, the disc-wing aircraft can have higher energy utilization efficiency and a more concise structure.

[0005] In recent years, with the rapid development of new energy technologies, hydrogen energy, as a clean and efficient energy form, has gradually been applied in the aviation field. Hydrogen energy motors have advantages such as high energy density and low emissions, and can provide continuous and stable power output for aircraft. The wide application of hydrogen energy makes it possible for the rapid development and application of disc-shaped aircraft. Most importantly, it is more conducive to structural optimization design, significantly improving the payload, endurance, and environmental friendliness of the aircraft.

[0006] In summary, the existing disc-shaped aircraft designs still have certain 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 disc-shaped flying vehicle to solve the problems raised in the above-mentioned background technology.

[0008] To achieve the above object, the present invention provides the following technical solution: A disc-shaped flying vehicle, comprising: an upper disc wing, a lower disc wing and an inner cabin. The upper and lower ends of the inner cabin are respectively rotatably connected to the upper disc wing and the lower disc wing through bearings. The inner cabin is fixedly connected to a rudder ring, and the rudder ring is located at the edge connection of the upper disc wing and the lower disc wing; An eccentric hydrogen energy-driven motor is fixedly arranged in the inner cabin. The hydrogen energy-driven motor is provided with two output shafts rotating in the same direction up and down. The upper output shaft is connected to a coaxial reverse rotation mechanism to output power, so as to drive in reverse rotation with the lower output shaft, and provide reverse rotation power for the upper disc wing and the lower disc wing; The output end of the coaxial reverse rotation mechanism and the lower output shaft of the hydrogen energy-driven motor are both connected to a power output gear; The upper disc wing and the lower disc wing are respectively provided with a transmission gear ring one and a transmission gear ring two at the connection with the bearing. The transmission gear ring one is meshed with the power output gear, the transmission gear ring two is meshed with the output gear of the lower output shaft of the hydrogen energy motor, and a differential is arranged between the transmission gear ring two and the lower gear of the motor, so that the upper disc wing and the lower disc wing rotate at a differential speed; The upper disc wing is provided with air guiding and pressurizing blades, and the space between the air guiding and pressurizing blades is an air inlet channel. The lower disc wing is provided with air guiding and rectifying blades, and a speed increasing and pressure reducing blade and a jet port are arranged at the bottom of the inner cabin.

[0009] Preferably, diffuser blades are arranged around the outer side of the inner cabin to decelerate and pressurize the incoming high-speed air flow and guide the air flow back to the lower disc wing.

[0010] Preferably, the inner cabin is connected with four attitude control guide pipes, and the attitude control guide pipes are connected with vector nozzles at the edge of the inner cabin.

[0011] Preferably, the end of the attitude control guide pipe is connected to four evenly distributed vector nozzles at the edge of the inner cabin through a hose. The high-pressure air in the attitude control guide pipe is ejected through the vector nozzles. The vector nozzles are driven by a driving motor installed in the edge of the inner cabin to deflect, so as to change the direction of the air flow ejected from the vector nozzles and realize the control of the attitude and movement direction of the flying vehicle.

[0012] Preferably, a flow control valve is arranged at the front end of the attitude control guide pipe, which can control the size and intensity of the air flow ejected from the vector nozzle, so as to realize the control of the attitude and direction of the flying vehicle.

[0013] Preferably, a load hatch is opened at the bottom of the inner cabin, and a bearing is sleeved outside the load hatch.

[0014] Compared with the prior art, the beneficial effects of the present invention are: The upper and lower disc wings rotate in opposite directions, which can self-balance the torque and keep the inner cabin stable in the axial direction; Air enters the air flow channel from the air inlet of the upper disc wing, and then passes through the compression impeller to do work, making the air have a high pressure energy. Then, through the diversion of the internal blades of the lower disc wing, it is all ejected from the nozzle of the lower disc wing, with high efficiency; Since the blades for work and pressurization are hidden inside the upper and lower disc wings, the outer shape of the disc wings is regular and clean, which can well exert the aerodynamic performance of the disc wing surface. At the same time, using the Coanda effect, a part of the lift is increased, thereby increasing the endurance; The upper and lower disc wings rotating in opposite directions have a large moment of inertia, and their gyroscopic effect makes the aircraft have high axial stability; The compression blades generating power are arranged on the outside of the aircraft, leaving a complete and regular internal space for the inner cabin, which can facilitate the arrangement of airborne equipment and payloads; Using the attitude control compression motor to drive the attitude control compression impeller to inhale and pressurize the air, and spraying it out from the vector nozzle through the attitude control diversion pipe to change the horizontal direction and pitch attitude of the aircraft; The differential rotation of the upper and lower disc wings can be used to achieve the axial rotation of the fuselage. Brief Description of the Drawings

[0015] Figure 1 is a schematic structural diagram of the present invention; Figure 2 is a side sectional view of the present invention; Figure 3 is the present invention Figure 2 an enlarged view of part A; Figure 4 is the present invention Figure 2 an enlarged view of part B; Figure 5 is the present invention Figure 2 an enlarged view of part C; Figure 6 is a top view of the cooperation between the first transmission gear ring and the power output gear in the present invention; Figure 7 is a schematic diagram of the air flow direction of the present invention.

[0016] In the figure: 1. Upper disc wing; 11. Air guiding and compressing blade; 12. First transmission gear ring; 2. Lower disc wing; 21. Air guiding and rectifying blade; 22. Second transmission gear ring; 3. Inner cabin; 31. Payload hatch; 32. Jet port; 33. Diffuser blade; 34. Differential; 35. Pressure reducing blade; 6. Bearing; 8. Hydrogen energy drive motor; 81. Coaxial counter-rotating mechanism; 82. Power output gear; 9. Rudder ring; 91. Vector nozzle; 92. Hose; 93. Drive motor; 94. Attitude control diversion pipe; 95. Flow control valve. Detailed Description of the Invention

[0017] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0018] Please refer to Figure 1-7 , the present invention provides a technical solution: a disc-shaped aircraft, including: an upper disc wing 1, a lower disc wing 2, an inner cabin 3, and a rudder ring 9.

[0019] The upper and lower ends of the inner cabin 3 are respectively rotationally connected to the upper disc wing 1 and the lower disc wing 2 through bearings 6, realizing the rotation of the upper disc wing 1 and the lower disc wing 2 relative to the inner cabin 3; A hydrogen energy-driven motor 8 is eccentrically and fixedly arranged inside the inner cabin 3. The hydrogen energy-driven motor 8 is provided with two coaxial output shafts up and down, and the upper output shaft thereof is connected to a coaxial reverse rotation mechanism 81; The lower output shaft of the hydrogen energy-driven motor 8 is directly connected to a power output gear 82, and the output end of the coaxial reverse rotation mechanism 81 is connected to another power output gear 82; A transmission gear ring 12 is arranged at the joint of the upper disc wing 1 and the bearing 6, and the transmission gear ring 12 meshes with the power output gear 82 driven by the coaxial reverse rotation mechanism 81; A transmission gear ring 22 is arranged at the joint of the lower disc wing 2 and the bearing 6, and the transmission gear ring 22 is transmission-connected to the power output gear 82 directly connected to the hydrogen energy-driven motor 8 through a differential 34; When driving the lower disc wing 2 to rotate, the rotation speed of the lower disc wing 2 can be adjusted through the differential 34 to realize the speed difference from the upper disc wing 1. The upper disc wing 1 and the lower disc wing 2 rotate in opposite directions, and the gyroscopic effect is used to provide stability for the aircraft.

[0020] The upper disc wing 1 is provided with air guiding and pressurizing vanes 11. The space between the air guiding and pressurizing vanes 11 is an air inlet passage. Diffuser vanes 33 are arranged around the outer side of the inner cabin 3. A speed increasing and pressure reducing vane 35 is arranged on the lower side of the outside of the inner cabin 3. An increasing and reducing flow passage is formed between the speed increasing and pressure reducing vanes 35. Air guiding and rectifying vanes 21 are arranged inside the lower disc wing 2. The upper disc wing 1 rotates at a high speed, sucking air into the air inlet passage, accelerating and pressurizing the air. The high-speed and high-pressure air flows into the diffuser vanes 33 arranged around the outer side of the inner cabin 3. The air is further decelerated and pressurized, and then flows back to the air guiding and rectifying vanes 21 inside the lower disc wing 2. Through the rotation of the air guiding and rectifying vanes 21, the air is pressed into the increasing and reducing flow passage at the lower part of the outer side 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 hatch 31 at the lower part of the inner cabin 3 to generate lift.

[0021] There are four evenly distributed attitude control guide pipes 94 at the connection between the outside and the edge of the inner cabin 3. The other end of the attitude control guide pipe 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 pipe 94 and is ejected from the vector nozzle 91.

[0022] The four vector nozzles 91 can be driven by drive motors 93 arranged on the edge to deflect the vector nozzles 91, so as to control the attitude of the aircraft.

[0023] A flow control valve 95 is arranged between the front end of the attitude control guide pipe 94 and the vector nozzle 91, which can control the size and intensity of the airflow ejected from the vector nozzle 91.

[0024] A load hatch 31 is opened at the bottom of the inner cabin 3. A bearing 6 is sleeved outside the load hatch 31. The load hatch 31 is used to load equipment and loads into the inner cabin 3.

[0025] Working principle: After the hydrogen energy drive motor 8 is started, the output end on 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 realize the reverse rotation of the upper disc wing 1 and the lower disc wing 2. The air guide and pressurizing blades 11 inside the upper disc wing 1 suck in air, and after processes such as speed increase and pressure increase, speed reduction and pressure expansion, and return flow rectification, it is ejected from the jet nozzle 32 of the lower disc wing 2 to provide lift for the aircraft, provide stability for the aircraft by using the gyroscopic effect, and at the same time use the Coanda effect to increase a part of the lift; During flight, the high-pressure air in the flow channel is ejected from the vector nozzle 91 through the four evenly distributed attitude control guide pipes 94 to change the flight attitude of the aircraft.

[0026] The content not described in detail in this specification belongs to the prior art well-known to those skilled in the art.

[0027] Although the embodiments of the present invention have been shown and described, for those of ordinary skill in the art, it can be understood that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principle and spirit of the present invention. The scope of the present 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 disposed 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, the upper output shaft being connected to a coaxial reverse rotation mechanism (81) to output power, thereby realizing a drive that rotates in the opposite direction to the lower output shaft, and providing the upper disc wing (1) and the lower disc wing (2) with rotational power in opposite directions to each other; 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 1 (12) and a transmission gear 2 (22) at the connection points 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 arranged around the outer side of the inner cabin (3) to decelerate and pressurize the incoming high-speed airflow and guide the airflow to flow 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 flow guide tube (94) is connected to four evenly distributed vector nozzles (91) on the edge (9) of the inner cabin via a hose (92); the high-pressure air in the attitude control flow 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), thereby achieving 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 by the vector nozzle (91), thereby achieving control of the attitude and direction of the aircraft.

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

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