Disc-shaped manned aircraft with multiple bundled turbofan engines

Abstract

The invention relates to a disc-shaped manned aircraft with multiple bundled turbofan engines, which is mainly characterized in that a cockpit is taken as a center, the multiple turbofan engines are uniformly bundled and fixedly mounted around a main body bracket and the cockpit, and respective lift fans are driven to generate upward lift force; the bottom of the main body support is provided with a turbine shaft engine transmission turbine fan, the whole body is provided with a disc-shaped anti-collision net and a disc-shaped wind collection disc, the appearance of the whole body is in a flying saucer shape, the pneumatic 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 a modern flying saucer and the development direction of a future flying saucer.

Description

TECHNICAL FIELD

[0001] The present application relates to a kind of multi-turbine fan engine binding type disc-shaped manned aircraft, mainly with cabin as center, six turbine fan engines are evenly bound and fixed installation in the main support and cabin one week, and transmission respective lift fan generates upward lift, a turbine shaft engine is installed on the bottom of main support transmission turbine fan, it is integrally provided with a disc-shaped crash net and a disc-shaped wind collecting disc etc., it belongs to the field of aviation technology. BACKGROUND

[0002] With the innovation of science and technology and the development of low-altitude economy, various unmanned aerial vehicles develop rapidly, and light manned aircraft emerge in an endless stream. The disc-shaped aircraft is a kind of aircraft with built-in rotor as the main power component, which has a disc-shaped shape. It can realize vertical take-off and hovering like a helicopter. Compared with the helicopter, the disc-shaped aircraft has unique advantages in aerodynamic efficiency and safety due to its special built-in rotor structure. The research on disc-shaped aircraft is still in the development stage, and there are many problems in structure design, aerodynamic optimization and flight control. The flight performance cannot meet the requirements of practical application. The configuration and flight control of disc-shaped aircraft still need further research and improvement. SUMMARY

[0003] The present application further updates the design concept in the above technical background, and improves the aerodynamic layout of disc-shaped aircraft, optimizes the flight control device and improves the safety of flight.

[0004] In order to achieve the above purpose, the present application provides the following technical scheme: a kind of multi-turbine fan engine binding type disc-shaped manned aircraft, it includes: a main support, the upper portion of the main support is provided with a cabin connected, the cabin is connected and installed with a cabin cover, the top of the cabin cover is connected and installed with a backup parachute;The operating console and the manned seat are arranged in the cabin, the electro-hydraulic control system is arranged in the lower middle position of the cabin, and the operating console is connected with the electro-hydraulic control system and the electro-hydraulic control equipment;A turbine shaft engine is connected and installed on the bottom of the main support, and six turbine fan engines are evenly connected and fixedly installed around the main support with the cabin as center, each turbine fan engine is connected and fixedly installed with a respective lift fan, and a disc-shaped crash net is connected and installed above the six turbine fan engines;A disc-shaped wind collecting disc is connected and installed below the disc-shaped crash net.

[0005] In the optional embodiment, the cabin, the electro-hydraulic control system, the fuel tank and the turbine shaft engine are fixedly installed on the central axis of the main support.

[0006] In the optional embodiment, the cabin cover is a pointed hexagonal body or a transparent dome cover.

[0007] In an optional embodiment, each turbofan engine drives a lift fan, and the airflow is then ejected through its respective exhaust port. Each turbofan engine is equipped with an electric drive control device that connects to the electric drive control system and the operation console for operation control, and can control the power output of each turbofan engine separately.

[0008] In an optional embodiment, the fuel tank is an annular cylindrical shape and is fixed below the edge of the cockpit. The fuel tank is connected to a fuel supply pipe that supplies fuel to each turbofan engine and turboshaft engine respectively.

[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 disc-shaped anti-collision net, forming an overall saucer shape.

[0010] In an alternative embodiment, the driver and passenger can enter and exit 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 turbofan engines operate simultaneously. The lift fan on each turbofan engine generates upward force, and the airflow is then ejected through its respective exhaust port, just like six small helicopters taking off at the same time, which drives 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 turbofan engine is controlled by artificial intelligence control algorithm, which can balance the overall structure of the aircraft and enable the overall structure to hover, ascend and descend. When fuel is applied to the left turbofan engine, the overall structure can tilt to the right, and vice versa. Similarly, when fuel is applied to the front turbofan engine, the overall structure can tilt backward, and vice versa. Thus, the disc-shaped manned aircraft can perform vertical take-off and landing and forward, backward, left and right movement.

[0014] (2) In this invention, a disc-shaped air-collecting disc is used to collect all the air volume between the six turbofan engines, and then the turbofan driven by the turboshaft engine is used to spray it out with additional force, which is equivalent to secondary force, just like releasing a large balloon with its opening facing down, which can rise rapidly.

[0015] (3) In this invention, by combining existing artificial intelligence control algorithms, sensor fusion, high-efficiency aero-engines and other technologies with the application of materials science, the overall structure of the aircraft is 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 multi-turbofan engine bundled disc-shaped manned aircraft, mainly composed of multiple turbofan engine units and a turboshaft engine. Each turbofan engine drives its own lift fan and the turbofan driven by the turboshaft engine. It is equipped with a disc-shaped anti-collision net and a disc-shaped air-gathering disc. The overall appearance forms a flying saucer shape. It improves the aerodynamic layout of existing disc-shaped aircraft, optimizes the flight control device, and improves flight safety. This invention has a reasonable structural design, is simple to manufacture, has low cost, is safe and reliable to use, and has novelty and creativity. It also demonstrates the basic structure of modern 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 turbofan 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] Figure 8 This is a schematic diagram of various types of turbofan engines provided in the embodiments of the present invention;

[0026] Reference numerals: 1. Main support frame; 2. Cockpit; 3. Cockpit canopy; 4. Reserve parachute; 5. Turbor shaft engine; 6. Control console; 7. Fly-by-wire control system; 8. Turbofan engine; 9. Exhaust vent; 10. Lift fan; 11. Disc-shaped crash barrier; 12. Disc-shaped air collection disc; 13. Fuel pipeline; 14. Fuel tank. Detailed Implementation

[0027] 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.

[0028] This invention provides a disc-shaped manned aircraft with multiple turbofan engines strapped together.

[0029] The following is combined Figures 1-8 The technical solution provided by this invention will be described in more detail below.

[0030] like Figures 1-8 As shown in the embodiment of the present invention, a multi-turbofan engine bundled 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, and a spare parachute 4 connected to the top of the cockpit canopy 3; the cockpit 2 is equipped with an operation console 6 and a manned seat, and a fly-by-wire control system 7 is installed and connected to the lower center of the cockpit 2, the operation console 6 is connected to the fly-by-wire control system 7 and fly-by-wire control equipment; a turboshaft engine 5 is connected and installed at the bottom of the main support frame 1, and six turbofan engines 8 are evenly fixed and installed around the cockpit 2 around the main support frame 1, each turbofan engine 8 drives its own lift fan 10, and a disc-shaped anti-collision net 11 is connected and installed above the six turbofan engines 8; a disc-shaped wind-gathering disc 12 is connected and installed below the disc-shaped anti-collision net 11.

[0031] As an optional implementation, the cockpit 2, spare parachute 4, fly-by-wire control system 7, fuel tank 14, and turboshaft engine 5 are all fixedly mounted on the central axis of the main support 1. The above structure is easy to manufacture and makes the overall center of gravity concentrated, thus making it very easy to control the overall balance of the aircraft.

[0032] As an optional implementation, the cockpit canopy 3 is a pointed hexagonal or a transparent dome-shaped canopy. The above structure is easy to process and manufacture, and can provide a full-view perspective, making it convenient to control the direction of the aircraft's movement.

[0033] As an optional implementation, each turbofan engine 8 drives a lift fan 10, and the airflow is then ejected through its respective exhaust port 9. Each turbofan engine 8 is equipped with a fly-by-wire control device connected to the fly-by-wire control system 7 and the operation control console 6 for operation and control, and can control the power output of each turbofan engine 8 separately. The above structure is easy to manufacture. The lift fan 10 can generate upward lift when rotating at high speed. The six lift fans 10 respectively use an even number of forward-rotating rotors and a number of reverse-rotating rotors to balance the anti-torque. Alternatively, they can be composed of two stages of counter-rotating fans. When they 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, and the overall appearance forms a flying saucer shape. The above structure is easy to process and manufacture. The disc-shaped air-collecting disc 12 collects all the air volume between the six turbofan engines 8, and then sprays it out with force through the turbofan driven by the turboshaft engine 5.

[0035] As an optional implementation, the fuel tank 14 is an annular cylindrical shape and is installed and fixed below the edge of the cockpit 2. The fuel tank 14 is connected to the fuel supply pipe 13 to supply fuel to each turbofan engine 5 and turboshaft engine 8. The above structure is easy to manufacture. The control system 7 and the control equipment are connected by a cable to the control console 6 to control the amount of fuel supplied to each turboshaft engine 5 and turbofan engine 8, so as to control the operating speed of each engine.

[0036] As an optional implementation, the driver and passengers can enter and exit 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 to facilitate the movement of people up and down.

[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 turbofan engines 8 operate simultaneously. Each turbofan engine 8 generates upward lift through its lift fan 10, and the airflow is then expelled through its respective exhaust port 9, much like six small helicopters taking off simultaneously. This propels the overall structure upward. The control console 6 connects to the fly-by-wire control system 7 and fly-by-wire control equipment. Artificial intelligence control algorithms are used to control the power output of each turbofan engine 8, balancing the overall structure of the aircraft and enabling hovering, ascent, and descent. When fuel is applied to the left turbofan engine 8, the overall structure tilts to the right, and vice versa. Similarly, when fuel is applied to the front turbofan engine 8, the overall structure tilts backward, and vice versa. This allows the disc-shaped manned aircraft to perform vertical takeoff and landing and forward, backward, left, and right movement.

[0039] In this invention, a disc-shaped air-collecting disc 12 is used to collect all the air volume between the six turbofan engines 8, and then the air volume is ejected with additional force through the turbofan driven by the turboshaft engine 5, which is equivalent to secondary force, just like releasing a large balloon with its opening facing down, which can rise rapidly.

[0040] In this invention, by combining existing artificial intelligence control algorithms, sensor fusion, high-efficiency aero-engines and other technologies with the application of materials science, the overall structure of the aircraft is mostly made of carbon fiber nanocomposite materials, which 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 disc-shaped manned aircraft with multiple turbofan engines strapped together, characterized in that, Mainly includes: A main support frame (1) is provided, and a cockpit (2) is connected to the top of the main support frame (1). A cockpit canopy (3) is connected to the cockpit (2), and a spare parachute (4) is connected to the top of the cockpit canopy (3). The cockpit (2) is equipped with an operation console (6) and a passenger seat. A fly-by-wire control system (7) is installed in the middle of the lower part of the cockpit (2). The operation console (6) is connected to the fly-by-wire control system (7) and the fly-by-wire control equipment. A turboshaft engine (5) is connected to the bottom of the main support frame (1). Six turbofan engines (8) are evenly fixed and connected around the main support frame (1) with the cockpit (2) as the center. Each turbofan engine (8) drives its own lift fan (10). A disc-shaped anti-collision net (11) is connected and installed above the six turbofan engines (8). A disc-shaped wind-gathering disc (12) is connected and installed below the disc-shaped anti-collision net (11).

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

3. The multi-turbofan engine bundled disc-shaped manned aircraft according to claim 1, characterized in that, The cockpit canopy (3) is a transparent body that follows the dome canopy.

4. The multi-turbofan engine bundled disc-shaped manned aircraft according to claim 1, characterized in that, Each turbofan engine (8) drives a lift fan (10), and the airflow is then ejected through its respective exhaust port (9). Each turbofan 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 turbofan engine (8) separately.

5. The multi-turbofan engine bundled disc-shaped manned aircraft according to claim 1, characterized in that, 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). The overall appearance forms a flying saucer shape and the disc-shaped air-collecting disc (12) collects all the air volume between the six turbofan engines (8) and then sprays it out through the turbofan driven by the turboshaft engine (5).

6. The multi-turbofan engine bundled disc-shaped manned aircraft according to claim 1, characterized in that, The fuel tank (14) is an annular cylindrical shape and is installed and fixed below the edge of the cockpit (2). The fuel tank (14) is connected to the fuel supply pipe (13) to supply fuel to each turbofan engine (8) and turboshaft engine (5). The control console (6) is connected to the electric control system (7) and electric control equipment by cable connection to control the amount of fuel supplied to each turboshaft engine (5) and turbofan engine (8) to control the operating speed of each engine.

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