Dish-shaped manned aircraft

Abstract

The disc-shaped manned aircraft is mainly formed by combining a plurality of turbine shaft engine devices and a turbine fan engine, each turbine shaft engine drives a propeller blade fan and a turbine fan of the turbine shaft engine and is provided with an anti-collision net and a disc-shaped wind collecting disc, and the appearance of the disc-shaped manned aircraft integrally forms a flying saucer shape; according to the saucer-shaped aircraft, the aerodynamic layout of an existing saucer-shaped aircraft is improved, a flight control device is optimized, and the flight safety is improved; the flying saucer is reasonable in structural design, easy to manufacture, low in cost and safe and reliable to use, has novelty and creativity, and shows the basic structure of the Chinese type flying saucer and the development direction of the flying saucer in the future.

Description

Technical Field

[0001] This invention relates to a disc-shaped manned aircraft, mainly consisting of a cockpit as the center, with six turboshaft engines evenly fixedly installed around the main support and the cockpit, and each engine drives a propeller blade fan and a small turbofan fan through its own through shaft. A turbofan engine is installed at the bottom of the main support. The whole is composed of a disc-shaped anti-collision net and a disc-shaped wind-gathering disc, etc., and belongs to the field of aviation technology. Background Technology

[0002] Disc-shaped aircraft are aircraft with a disc-shaped shape and an internal rotor as their main power component. They can achieve vertical take-off and landing and hovering like helicopters. Compared with helicopters, disc-shaped aircraft have unique advantages in aerodynamic efficiency and safety due to their special internal rotor structure. Research on disc-shaped aircraft is still in the development stage. There are still many problems in their structural design, aerodynamic optimization and flight control. Their flight performance cannot yet meet the requirements of practical applications. The configuration and flight control of disc-shaped aircraft still need further research and improvement. Summary of the Invention

[0003] The present invention aims to further update the design concept in the above-mentioned technical background, improve the aerodynamic layout of the disc-shaped aircraft, optimize the flight control device, and improve flight safety.

[0004] To achieve the above objectives, the present invention provides the following technical solution: a disc-shaped manned aircraft, comprising: a main support frame, a cockpit connected to the top of the main support frame, a cockpit canopy connected to the cockpit, and a spare parachute connected to the top of the cockpit canopy; an operation console and a manned seat are provided inside the cockpit, and a fly-by-wire control system is connected to the lower center of the cockpit, with the operation console connected to the fly-by-wire control system and fly-by-wire control equipment; a turbofan engine is connected to the bottom of the main support frame, and six turboshaft engines are evenly fixedly connected to the main support frame with the cockpit as the center, each turboshaft engine having a through shaft driving its own propeller blade fan and small turbofan, and a disc-shaped anti-collision net is connected to the top of the six propeller blade fans; a disc-shaped wind-gathering disc is connected to the bottom of the six small turbofans.

[0005] In an optional embodiment, the cockpit, fly-by-wire control system, fuel tank, and turbofan engine are all fixedly mounted on the central axis of the main support.

[0006] In an optional embodiment, the cockpit canopy is a pointed hexagon or a transparent dome-shaped canopy.

[0007] In an optional embodiment, each turboshaft engine has a central through shaft extending both vertically and horizontally. The upper part of the through shaft is connected to a drive propeller blade fan, and the lower part of the through shaft is connected to a drive small turbo fan. Each turboshaft engine is equipped with an electric transmission control device that connects to the electric transmission control system and the operation control console for operation control, and can control the power output of each turboshaft engine separately.

[0008] In an optional embodiment, the fuel tank connection pipeline will supply fuel to each turboshaft engine and turbofan engine separately.

[0009] In an optional embodiment, a disc-shaped air-gathering disc is installed below the main support, and the upper edge of the disc-shaped air-gathering disc is fixedly connected to the lower edge of the anti-collision net, forming an overall saucer shape.

[0010] In an alternative embodiment, the driver and passenger can enter the cabin from the bottom of the cabin.

[0011] In an optional embodiment, a backup parachute is installed on the top of the cockpit.

[0012] Compared with the prior art, the beneficial effects of the present invention are:

[0013] (1) In this invention, six turboshaft engines operate simultaneously. Each turboshaft engine drives its own propeller blade fan and small turbine fan to rotate at high speed through the through shaft, just like six small helicopters taking off at the same time, driving the overall structure to move upward. The control console is connected to the fly-by-wire control system and fly-by-wire control equipment. The power output of each turboshaft engine is controlled by artificial intelligence control algorithm, which can balance the overall structure of the aircraft and make the overall structure move up and down. When fuel is applied to the left turboshaft engine, the overall structure can tilt to the right, and vice versa. Similarly, when fuel is applied to the front turboshaft engine, the overall structure can tilt backward, and vice versa. Thus, the disc-shaped manned aircraft can take off and land vertically and move forward, backward, left and right.

[0014] (2) In this invention, a disc-shaped wind-collecting disc is used to collect all the air volume from the downward rotation of the six propeller blade fans. The air volume is then ejected at high speed by the six small turbine fans and the turbine fan engine installed at the center of the bottom of the disc-shaped wind-collecting disc. This is equivalent to a secondary boost, just like releasing a large balloon with its opening facing down, which can move quickly.

[0015] (3) In this invention, by combining existing artificial intelligence control algorithms, sensor fusion, high-efficiency turboshaft engines and other technologies, as well as the application of materials science, the propellers, rotor blades, fans and overall structure of the aircraft are mostly made of carbon fiber nanocomposite materials, which will reduce the overall weight of the aircraft and increase its flight speed.

[0016] Based on the above description, this invention is a disc-shaped manned aircraft, mainly composed of multiple turboshaft engine units and one turbofan engine. Each turboshaft engine drives its own propeller blade fan and turbofan, and is equipped with a collision protection net and a disc-shaped air-gathering disk. The overall appearance forms a flying saucer shape. It improves the aerodynamic layout of existing disc-shaped aircraft, optimizes the flight control device, and enhances flight safety. This invention has a reasonable structural design, is simple to manufacture, has low cost, is safe and reliable to use, and is novel and creative. It also demonstrates the basic structure of Chinese-style flying saucers and the future development direction of flying saucers. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 This is a schematic diagram of the overall structure provided in an embodiment of the present invention;

[0019] Figure 2 This is a cross-sectional aerodynamic principle schematic diagram provided in an embodiment of the present invention;

[0020] Figure 3 This is a schematic diagram of the transmission structure of a single turboshaft engine provided in an embodiment of the present invention;

[0021] Figure 4 This is a schematic diagram of the main support structure provided in an embodiment of the present invention;

[0022] Figure 5 This is a schematic diagram of the overall leftward movement provided in an embodiment of the present invention;

[0023] Figure 6 This is a schematic diagram of the overall rightward movement provided in an embodiment of the present invention;

[0024] Figure 7 This is a schematic diagram of emergency deployment of the backup parachute provided in an embodiment of the present invention;

[0025] Reference numerals: 1. Main support frame; 2. Cockpit; 3. Cockpit canopy; 4. Reserve parachute; 5. Turbofan engine; 6. Control console; 7. Fly-by-wire control system; 8. Turboshaft engine; 9. Through shaft; 10. Propeller blade fan; 11. Disc-shaped anti-collision net; 12. Disc-shaped air-collecting disc; 13. Small turbofan; 14. Fuel tank. Detailed Implementation

[0026] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions of this invention will be described in detail below. Obviously, the described embodiments are merely one example of the embodiments of this invention, and not all examples. Based on the embodiments of this invention, all other implementation methods obtained by those skilled in the art without creative effort are within the scope of protection of this invention.

[0027] This invention provides a disc-shaped manned aircraft.

[0028] The following is combined Figures 1 to 7 The technical solution provided by this invention will be described in more detail below.

[0029] like Figures 1 to 7 As shown in the embodiment of the present invention, a disc-shaped manned aircraft includes: a main support frame 1, a cockpit 2 connected to the top of the main support frame 1, a cockpit canopy 3 connected to the cockpit 2, a spare parachute 4 connected to the top of the cockpit canopy 3, an operation console 6 and a manned seat inside the cockpit 2, a fly-by-wire control system 7 connected to the lower center of the cockpit 2, and the operation console 6 connected to the fly-by-wire control system 7 and fly-by-wire control equipment; a turbofan engine 5 connected to the bottom of the main support frame 1, and six turboshaft engines 8 evenly fixedly connected to the main support frame 1 with the cockpit 2 as the center, each turboshaft engine 8 having a through shaft 9 driving its respective propeller blade fan 10 and small turbofan 13, and a disc-shaped anti-collision net 11 installed above the six propeller blade fans 10; and a disc-shaped wind-gathering disc 12 connected to the bottom of the six small turbofans 13.

[0030] As an optional implementation, the cockpit 2, spare parachute (4), fly-by-wire control system 7, fuel tank 14, and turbofan engine 5 are all fixedly installed on the central axis of the main support 1. The above structure is easy to process and manufacture, so that the overall center of gravity is concentrated, making it very easy to control the overall balance of the aircraft.

[0031] As an optional implementation, the cockpit canopy 3 is a pointed hexagonal or a transparent dome-shaped body. The above structure is easy to process and manufacture, and can provide a full-view perspective, making it convenient to control the forward direction of the aircraft.

[0032] As an optional implementation, each turboshaft engine 8 has a through shaft 9 extending vertically at its center. The upper part of the through shaft 9 is connected to the drive propeller blade fan 10, and the lower part of the through shaft 9 is connected to the drive small turbo fan 13. The turboshaft engine 8 can be an internal combustion engine or an aircraft turboshaft engine. Each turboshaft engine 8 is equipped with an electric fly-by-wire control device that connects to the electric fly-by-wire control system 7 and the operation control console 6 for operation control. It can control the power output of each turboshaft engine 8 separately. The above structure is easy to manufacture.

[0033] As an optional implementation, the blades of the propeller blade fan 10 are like helicopter blades or drone blades, with two or more blades. The above structure is easy to manufacture. The blades can generate upward lift when rotating at high speed. The six propeller blade fans 10 each use an even number of forward-rotating rotors and a number of reverse-rotating rotors to balance the anti-torque and operate simultaneously. The lift generated can lift the overall weight of the aircraft and balance the overall stable movement of the aircraft.

[0034] As an optional implementation, a disc-shaped air-collecting disc 12 is installed below the main support 1. The upper edge of the disc-shaped air-collecting disc 12 is fixedly connected to the lower edge of the disc-shaped anti-collision net 11, forming an overall flying saucer shape. This structure is easy to manufacture. The disc-shaped air-collecting disc 12 collects all the downward airflow from the six propeller-bladed fans 10, and then, through the high-speed rotation of the small turbine fan 13 and the turbine fan engine 5 at the bottom of the disc-shaped air-collecting disc 12, it is forcefully ejected.

[0035] As an optional implementation, the fuel tank 14 is connected to a fuel supply pipe to supply fuel to each turboshaft engine 8 and turbofan engine 5 respectively. The above structure is easy to manufacture. The amount of fuel supplied to each turboshaft engine 8 and turbofan engine 5 is controlled by the operation control console 6 and the electronic control system 7 to control the operating speed of each engine.

[0036] As an optional implementation, the driver and passengers can enter the cabin from the bottom of the cabin 2. The above structure is easy to manufacture, the cabin door can be opened from the bottom of the cabin 2, and a ladder is provided for easy access for passengers.

[0037] As an optional implementation, a backup parachute 4 is installed on the top of the cockpit 2. The above structure is easy to manufacture and can be deployed in the event of aircraft malfunction or emergency, so that the entire aircraft or the separated individual cockpit 2 can land safely and smoothly on the ground.

[0038] In this invention, six turboshaft engines 8 operate simultaneously. Each turboshaft engine 8 is driven by a through shaft 9, which drives its own propeller blade fan 10 and small turbofan 13 to rotate at high speed, much like six small helicopters taking off simultaneously. This causes the overall structure to move upwards. The control console 6 is connected to the fly-by-wire control system 7 and fly-by-wire control equipment. Artificial intelligence control algorithms are used to automatically control the power output of each turboshaft engine 8, which can balance the overall structure of the aircraft and enable the overall structure to move up and down. When fuel is applied to one of the left turboshaft engines 8, the overall structure can tilt to the right, and vice versa. Similarly, when fuel is applied to the front turboshaft engine 8, the overall structure can tilt backwards, and vice versa. This enables the disc-shaped manned aircraft to take off and land vertically and move forward, backwards, left, and right.

[0039] In this invention, a disc-shaped air-collecting disk 12 is used to collect all the air volume generated by the operation of the six propeller-bladed fans 10. The air volume is then generated by the high-speed operation of the six small turbine fans 13 and the turbine fan engine 5 installed at the bottom center of the disc-shaped air-collecting disk 12. The air volume is then ejected through the turbine fans with additional force, which is equivalent to secondary force, just like releasing a large balloon with its opening facing down, which can move quickly.

[0040] In this invention, by combining existing artificial intelligence control algorithms, sensor fusion, high-efficiency power engines and other technologies with the application of materials science, the propellers, rotor blades, fans 10 and the overall structure of the aircraft are mostly made of carbon fiber nanocomposite materials. This will reduce the overall weight of the aircraft, increase its flight speed, and enable the manufacture of large, medium and small disc-shaped aircraft for manned, unmanned or cargo transport.

[0041] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

[0042] In the description of this invention, it should be noted that, unless otherwise stated, "a plurality of" means two or more; the terms "upper," "lower," "left," "right," "inner," "outer," "front end," "rear end," "head," "tail," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention. Furthermore, the terms "first," "second," "third," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0043] In the description of this invention, it should also be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections or electrical connections; they can refer to direct connections or indirect connections through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

Claims

1. A saucer-shaped manned aerial vehicle, characterized in that, Mainly includes: A main support frame (1) is provided, and a cockpit (2) is connected above the main support frame (1). A cockpit canopy (3) is connected to the cockpit (2). A spare parachute (4) is connected to the top of the cockpit canopy (3). An operation console (6) and a passenger seat are provided inside the cockpit (2). A fly-by-wire control system (7) is connected to the middle position below the cockpit (2). The operation console (6) is connected to the fly-by-wire control system (7) and fly-by-wire control equipment. A turbofan engine (5) is connected to the bottom of the main support frame (1). Six turboshaft engines (8) are evenly fixedly connected to the main support frame (1) with the cockpit (2) as the center. The through shaft (9) on each turboshaft engine (8) drives its own propeller blade fan (10) and small turbofan (13). A disc-shaped anti-collision net (11) is connected to the top of the six propeller blade fans (10). A disc-shaped wind-gathering disc (12) is connected to the bottom of the six small turbofans (13).

2. The saucer-shaped manned aerial vehicle according to claim 1, characterized in that, The cockpit (1), fly-by-wire control system (7), fuel tank (14), turbofan engine (5), and spare parachute (4) are all fixedly installed on the central axis of the main support (1).

3. The saucer-shaped manned aerial vehicle according to claim 1, characterized in that, The cockpit canopy (3) is a transparent body that follows the dome canopy.

4. The disc-shaped manned aircraft according to claim 1, characterized in that, At the center of each turboshaft engine (8) is a through shaft (9) that extends both vertically and horizontally. The upper part of the through shaft (9) is connected to the drive propeller blade fan (10), and the lower part of the through shaft (9) is connected to the drive small turbo fan (13). Each turboshaft engine (8) is equipped with an electric transmission control device that connects to the electric transmission control system (7) and the operation control console (6) for operation control, and can control the power output of each turboshaft engine (8) separately.

5. The disc-shaped manned aircraft according to claim 1, characterized in that, A disc-shaped air-gathering disc (12) is installed below the main support (1). The upper edge of the disc-shaped air-gathering disc (12) is fixedly connected to the lower edge of the disc-shaped anti-collision net (11), and the overall appearance forms a flying saucer shape.

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