CN113879522A

CN113879522A - Multi-propeller aircraft

Info

Publication number: CN113879522A
Application number: CN202010635024.XA
Authority: CN
Inventors: 张锐
Original assignee: Individual
Current assignee: Individual
Priority date: 2020-07-04
Filing date: 2020-07-04
Publication date: 2022-01-04

Abstract

The invention provides two kinds of manned and two kinds of unmanned remote control multi-propeller aircrafts, which adopt outer edge ring wing blade propellers to generate lift force and flight power, utilize outer edge flat ring wings to cut and adapt to windward fast laminar flow or cross wind laminar flow, and after the windward or cross wind laminar flow is cut and guided by the outer edge flat ring wings, the direct airflow impact of the windward or cross wind laminar flow on blades at the inner sides of the ring wings is avoided, the shock wave vibration generated by the wing tips of the blades in the ring is avoided, and the problems of large wind resistance, unstable flight or hovering wind blowing yaw caused by the reasons are avoided or alleviated; in addition, the outer edge ring wing blade type propeller can prevent blades on the inner side of the ring wing from cutting fingers or flying obstacles, reduce the hooking of the blades by the obstacles such as branches, cables and the like during flying, and is favorable for protecting personal safety and further improving the flying safety; and compare the ordinary blade formula screw unmanned aerial vehicle that needs install the paddle guard circle additional, if do not install the paddle guard circle after adopting outer fringe ring wing blade formula screw still possess the security.

Description

Multi-propeller aircraft

Technical Field

The invention relates to the field of aircrafts and vehicles, in particular to two unmanned remote control multi-propeller aircrafts and two manned multi-propeller aircrafts.

Background

The multi-propeller aircrafts on the market at present are typified by a Xinjiang unmanned aerial vehicle, and unmanned aircrafts based on vane propellers for generating lift force and flight power, four rotors or even eight rotors, and manned aircrafts evolved from the unmanned aircrafts by adding a cockpit and a driving mechanism are developed. The aircrafts generally adopt bamboo dragonfly type blade propellers as a lift force power mechanism, and the blade propellers have the advantages of simple structure and low production cost; but the unfavorable side is that the blade propeller directly impacts and cuts air to generate lift force when rotating, the aircraft is naturally and easily kept stable when suspended in the air under the windless condition, and the crosswind directly impacts and rotates the blades under the crosswind condition through practical tests, and under the two-phase action, the unmanned aerial vehicle is very easy to deviate from the hovering position and is very not beneficial to hovering control under the windy condition; in addition, in the process of the aircraft going forward at high speed in a flat flying manner, when the aircraft flies in windward at high speed, the wingtips of the blade type propellers strike and impact each other with windward rapid laminar flow when the aircraft goes forward, and the wind resistance is increased, so that the flying speed is not further improved; and also shock waves are easily generated, and if the wing tip is soft, chatter is also induced, resulting in reduced flight stability. These problems are inherent in the properties of conventional vane propellers and cannot be avoided by means of an excellent control method.

In addition, these adopt many rotor crafts of blade propeller, when the blade propeller is rotatory at a high speed, the paddle point very easily cuts the finger, hurts people and strikes and damages the blade, so generally need install additional the guard ring and block and protect, but even install additional behind the guard ring, the aircraft also still easily breaks the paddle at a high speed when being close to non-planar object, hook branch when also still flying easily when sweeping near the branch, still cut the finger easily when promptly catching unmanned aerial vehicle hovers in the air.

Therefore, based on the problems, a new scheme of the aircraft is needed, wherein the new scheme can adapt to the rapid laminar flow or the cross-wind laminar flow facing the wind, and can reduce the injury of the blades and the problem of easy hooking of the blades.

Disclosure of Invention

The outer edge ring wing type propeller replaces the traditional blade type propeller, and is applied to a multi-propeller aircraft, so that the outer edge flat ring wing of the outer edge ring wing type propeller is used for cutting and adapting to the fast laminar flow or the cross-wind laminar flow of the windward in the high-speed flat flying process of the aircraft, the direct airflow impact of the laminar flow of the windward or the cross-wind on the blades on the inner side of the ring wing is avoided after the laminar flow of the windward or the cross-wind is cut and guided by the outer edge flat ring wing, the shock wave vibration generated by the wingtips of the blades in the ring is avoided, the problems of large wind resistance, unstable flight or hovering wind blowing yaw caused by the reasons are avoided or alleviated, and the blades in the ring are shielded by the outer edge flat ring wing, so that the blades can directly hurt people and can be prevented from hooking flight obstacles such as branch cables. Specifically, two unmanned remote control multi-propeller aircrafts and two manned multi-propeller aircrafts are provided, and the technical scheme is as follows:

scheme 1: a multi-propeller aircraft comprising: the system comprises a plurality of outer edge ring wing blade type propellers 1, a plurality of motors 2, a machine body 3, an undercarriage 31, a power supply and control unit 4, an inertia measurement unit 5, a communication transceiving unit 6 and a wireless remote control device 60; wherein, outer fringe ring wing blade formula screw 1 includes again: a flat outer edge ring wing 101, a plurality of blades 102, a hub 103, a rotating shaft 104; the power supply and control unit 4 further comprises: battery unit 41, drive unit 42, control unit 43; the flat outer edge ring wing 101 is of a flat circular ring structure, the blades 102 are uniformly distributed and connected between the flat outer edge ring wing 101 and the hub 103, the rotating shaft 104 is connected with the fixed hub 103, and the motor 2 is connected with and drives the rotating shaft 104 so as to drive the whole outer edge ring wing blade type propeller 1 to rotate;

the body 3 is uniformly distributed and connected with a plurality of outer edge ring wing blade type propellers 1 and a plurality of motors 2, and the motors 2 respectively drive the outer edge ring wing blade type propellers 1 to rotate to generate lift force and flight power; the landing gear 31 is fixed on the fuselage 3 and used for buffering taking off and landing; the inertia measurement unit 5 and the communication transceiving unit 6 are fixed on the body 3; the communication transceiver unit 6 is connected with the wireless remote control device 60 in a matching way through wireless communication;

the motor 2, the driving unit 42, the control unit 43, the inertia measuring unit 5 and the communication transceiving unit 6 are electrically connected with the battery unit 41; the battery unit 41 supplies power to the power consumption unit of the whole aircraft after charging and storing electricity, and recharges and stores energy when the electricity is insufficient; the driving unit 42 is electrically connected with each motor 2 by different output channels to drive and control the operation of the motors with output power; the driving unit 42 is electrically connected to the control unit 43, and the control unit 43 participates in power output control and operation control of the driving unit 42; the inertia measurement unit 5 is electrically connected to the control unit 43, the inertia measurement unit 5 measures three-dimensional position, three-dimensional velocity, three-dimensional acceleration, three-axis angle, three-dimensional angular velocity, flight direction and flight altitude data of the aircraft and transmits the data to the control unit 43, and the control unit 43 performs resolving, optimizing and error compensating on control parameters of the current aircraft attitude according to the flight motion data, and adjusts and optimizes the power output control of the driving unit 42; the communication transceiver unit 6 receives the operation action command and the input signal from the wireless remote control device 60 and transmits the operation action command and the input signal to the control unit 43; the control unit 43 outputs the operation parameters and the control parameters to the wireless remote control device 60 through the communication transceiving unit 6, and the user provides data reference to assist the user in realizing wireless remote control flight;

the wireless remote control device 60 is connected with the communication transceiver unit 6 in a wireless communication matching way, and a user operates the wireless remote control device 60 to control and adjust the operation parameters, operation and output power of the power supply and control unit 4 through the communication transceiver unit 6, so that the rotating speeds of the plurality of motors 2 and the plurality of outer edge ring wing blade type propellers 1 are controlled and adjusted, and the aircraft can realize acceleration and deceleration flight, hovering in the air and vertical take-off and landing; the rotation speed difference is generated among the outer edge ring wing blade type propellers 1, so that the flying rolling, the flying steering, the pitching flying and the yawing flying are realized; in the rapid flat flight process, the outer edge ring wing blade type propeller 1 utilizes the outer edge flat ring wing 101 to cut and adapt to the windward rapid laminar flow or the crosswind laminar flow, so that after the windward laminar flow or the crosswind laminar flow is cut and guided by the outer edge flat ring wing 101, the direct airflow impact of the windward laminar flow or the crosswind laminar flow on the inner side blades 102 of the ring wings is avoided, the shock wave vibration generated at the wing tips of the inner blades 102 is avoided, and the problems of large wind resistance, unstable flight or hovering wind blowing yaw caused by the reasons are avoided or alleviated.

Scheme 2: a multi-propeller aircraft comprising: the system comprises a plurality of outer edge ring blade type propellers 1, a plurality of motors 2, a fuselage 3, a landing gear 31, a cockpit 32, a power supply and control unit 4, an inertia measurement unit 5, a driver control device 7 and an electronic instrument device 71; wherein, outer fringe ring wing blade formula screw 1 includes again: a flat outer edge ring wing 101, a plurality of blades 102, a hub 103, a rotating shaft 104; the power supply and control unit 4 further comprises: battery unit 41, drive unit 42, control unit 43; the flat outer edge ring wing 101 is of a flat circular ring structure, the blades 102 are uniformly distributed and connected between the flat outer edge ring wing 101 and the hub 103, the rotating shaft 104 is connected with the fixed hub 103, and the motor 2 is connected with and drives the rotating shaft 104 so as to drive the whole outer edge ring wing blade type propeller 1 to rotate;

the body 3 is uniformly distributed and connected with a plurality of outer edge ring wing blade type propellers 1 and a plurality of motors 2, and the motors 2 respectively drive the outer edge ring wing blade type propellers 1 to rotate to generate lift force and flight power; the landing gear 31 is fixed on the fuselage 3 and used for buffering taking off and landing; the cockpit 32 is fixedly connected with the fuselage 3, and a pilot control position is arranged in the cockpit 32; the driver operating device 7 is arranged in the cab 32 for the driver to operate and drive; the inertia measurement unit 5 is fixed on the machine body 3; the electronic instrumentation 71 is fixed in the cockpit 32; the electronic instrument device 71 detects and displays the endurance mileage, the flying height, the flying airspeed, the climbing and descending speed, the flying attitude and the flying heading data as well as the operation data parameters and the control parameters of the motor 2 and the power supply and control device 4, and provides data reference for the driver to assist the driver in flying;

the electric motor 2, the driving unit 42, the control unit 43, the inertia measurement unit 5 and the driver operating device 7 are electrically connected with the battery unit 41; the battery unit 41 supplies power to the power consumption unit of the whole aircraft after charging and storing electricity, and recharges and stores energy when the electricity is insufficient; the driving unit 42 is electrically connected with each motor 2 by different output channels to drive and control the operation of the motors with output power; the driving unit 42 is electrically connected to the control unit 43, and the control unit 43 participates in power output control and operation control of the driving unit 42; the inertia measurement unit 5 is electrically connected to the control unit 43, the inertia measurement unit 5 measures three-dimensional position, three-dimensional velocity, three-dimensional acceleration, three-axis angle, three-dimensional angular velocity, flight direction and flight altitude data of the aircraft and transmits the data to the control unit 43, and the control unit 43 performs resolving, optimizing and error compensating on control parameters of the current aircraft attitude according to the flight motion data, and adjusts and optimizes the power output control of the driving unit 42; the driver operates the driver operating device 7 to send an operating action command and an input signal to the control unit 43; the control unit 43 controls the driving unit 42 to adjust the power output control of the plurality of motors 2 according to the operation action command so as to realize the control of the flight action of the aircraft; the control unit 43 outputs the operation parameters and the control parameters to the electronic instrument device 71, and provides data reference for the pilot to assist the pilot in piloting the flight;

the pilot operates the pilot control device 7 to control and adjust the operation parameters, operation and output power of the power supply and control unit 4, thereby controlling and adjusting the rotating speed of the plurality of motors 2 and the plurality of outer edge ring wing blade type propellers 1, and enabling the aircraft to realize acceleration and deceleration flight, air hovering and vertical take-off and landing; the rotation speed difference is generated among the outer edge ring wing blade type propellers 1, so that the flying rolling, the flying steering, the pitching flying and the yawing flying are realized; in the rapid flat flight process, the outer edge ring wing blade type propeller 1 utilizes the outer edge flat ring wing 101 to cut and adapt to the windward rapid laminar flow or the crosswind laminar flow, so that after the windward laminar flow or the crosswind laminar flow is cut and guided by the outer edge flat ring wing 101, the direct airflow impact of the windward laminar flow or the crosswind laminar flow on the inner side blades 102 of the ring wings is avoided, the shock wave vibration generated at the wing tips of the inner blades 102 is avoided, and the problems of large wind resistance, unstable flight or hovering wind blowing yaw caused by the reasons are avoided or alleviated.

Scheme 3: a multi-propeller aircraft comprising: the system comprises a plurality of outer edge ring wing blade type propellers 1, a plurality of engines 21, a plurality of steering engines 22, a fuselage 3, an undercarriage 31, a power supply and control unit 4, an inertia measurement unit 5, a communication transceiving unit 6 and a wireless remote control device 60; the outer edge ring blade type propeller 1 further comprises: a flat outer edge ring wing 101, a plurality of blades 102, a hub 103, a rotating shaft 104; the power supply and control unit 4 further comprises: battery unit 41, drive unit 42, control unit 43; the flat outer edge ring wing 101 is of a flat circular ring structure, the blades 102 are uniformly distributed and connected between the flat outer edge ring wing 101 and the hub 103, the rotating shaft 104 is connected with the fixed hub 103, and the engine 21 is connected with and drives the rotating shaft 104 so as to drive the whole outer edge ring wing blade type propeller 1 to rotate;

the body 3 is uniformly distributed and connected with a plurality of outer edge ring wing blade type propellers 1 and a plurality of engines 21, and the plurality of engines 21 respectively drive the plurality of outer edge ring wing blade type propellers 1 to rotate to generate lift force and flight power; the steering engines 22 are respectively and correspondingly connected with one engine 21, and the steering engines 22 control the accelerator pulling action of the engine 21; the landing gear 31 is fixed on the fuselage 3 and used for buffering taking off and landing; the inertia measurement unit 5 and the communication transceiving unit 6 are fixed on the body 3; the communication transceiver unit 6 is connected with the wireless remote control device 60 in a matching way through wireless communication;

the steering engine 22, the driving unit 42, the control unit 43, the inertia measurement unit 5 and the communication transceiving unit 6 are electrically connected with the battery unit 41; the battery unit 41 supplies power to the power consumption unit of the whole aircraft after charging and storing electricity, and recharges and stores energy when the electricity is insufficient; the driving unit 42 is electrically connected with each steering engine 22 through different output channels to output power to drive and control the operation and execution of the steering engines; the driving unit 42 is electrically connected to the control unit 43, and the control unit 43 participates in power output control and operation control of the driving unit 42; the inertia measurement unit 5 is electrically connected to the control unit 43, the inertia measurement unit 5) measures the three-dimensional position, three-dimensional speed, three-dimensional acceleration, three-axis angle, three-dimensional angular speed, flight direction and flight height data of the aircraft and transmits the data to the control unit 43, the control unit 43 performs resolving, optimizing and error compensation on the control parameters of the current aircraft attitude according to the flight motion data, adjusts and optimizes the power output control on the driving unit 42, and controls the output power of each engine 21 by adjusting the moment of the accelerator pulled by each steering engine 22 so as to adjust the rotating speed of each outer edge ring wing blade type propeller 1; the communication transceiver unit 6 receives the operation action command and the input signal from the wireless remote control device 60 and transmits the operation action command and the input signal to the control unit 43; the control unit 43 outputs the operation parameters and the control parameters to the wireless remote control device 60 through the communication transceiving unit 6, and the user provides data reference to assist the user in realizing wireless remote control flight;

the wireless remote control device 60 is connected with the communication transceiving unit 6 in a matching way through wireless communication, a user operates the wireless remote control device 60 to control and adjust the operation parameters, operation and output power of the power supply and control unit 4 through the communication transceiving unit 6, and finally the rotating speeds of the plurality of engines 21 and the plurality of outer edge ring wing blade type propellers 1 are controlled and adjusted by adjusting the moment of the action of pulling the accelerator by each steering engine 22, so that the aircraft can realize acceleration and deceleration flight, air hovering and vertical take-off and landing; the rotation speed difference is generated among the outer edge ring wing blade type propellers 1, so that the flying rolling, the flying steering, the pitching flying and the yawing flying are realized; in the rapid flat flight process, the outer edge ring wing blade type propeller 1 utilizes the outer edge flat ring wing 101 to cut and adapt to the windward rapid laminar flow or the crosswind laminar flow, so that after the windward laminar flow or the crosswind laminar flow is cut and guided by the outer edge flat ring wing 101, the direct airflow impact of the windward laminar flow or the crosswind laminar flow on the inner side blades 102 of the ring wings is avoided, the shock wave vibration generated at the wing tips of the inner blades 102 is avoided, and the problems of large wind resistance, unstable flight or hovering wind blowing yaw caused by the reasons are avoided or alleviated.

Scheme 4: a multi-propeller aircraft comprising: the system comprises a plurality of outer edge ring wing blade type propellers 1, a plurality of engines 21, a plurality of steering engines 22, a fuselage 3, an undercarriage 31, a cockpit 32, a power supply and driving and controlling unit 4, an inertia measuring unit 5, a driver operating device 7 and an electronic instrument device 71; wherein, outer fringe ring wing blade formula screw 1 includes again: a flat outer edge ring wing 101, a plurality of blades 102, a hub 103, a rotating shaft 104; the power supply and control unit 4 further comprises: battery unit 41, drive unit 42, control unit 43; the flat outer edge ring wing 101 is of a flat circular ring structure, the blades 102 are uniformly distributed and connected between the flat outer edge ring wing 101 and the hub 103, the rotating shaft 104 is connected with the fixed hub 103, and the engine 21 is connected with and drives the rotating shaft 104 so as to drive the whole outer edge ring wing blade type propeller 1 to rotate;

the body 3 is uniformly distributed and connected with a plurality of outer edge ring wing blade type propellers 1 and a plurality of engines 21, and the plurality of engines 21 respectively drive the plurality of outer edge ring wing blade type propellers 1 to rotate to generate lift force and flight power; the steering engines 22 are respectively and correspondingly connected with one engine 21, and the steering engines 22 control the accelerator pulling action of the engine 21; the landing gear 31 is fixed on the fuselage 3 and used for buffering taking off and landing; the cockpit 32 is fixedly connected with the fuselage 3, and a pilot control position is arranged in the cockpit 32; the driver operating device 7 is arranged in the cab 32 for the driver to operate and drive; the inertia measurement unit 5 is fixed on the machine body 3; the electronic instrumentation 71 is fixed in the cockpit 32; the electronic instrument device 71 detects and displays the endurance mileage, the flying height, the flying airspeed, the climbing and descending rate, the flying attitude and the flying heading data as well as the operation data parameters and the control parameters of the engine 21 and the power supply and control device 4, and provides data reference for the driver to assist the driver in flying;

the steering engine 22, the driving unit 42, the control unit 43, the inertia measuring unit 5 and the driver operating device 7 are electrically connected with the battery unit 41; the battery unit 41 supplies power to the power consumption unit of the whole aircraft after charging and storing electricity, and recharges and stores energy when the electricity is insufficient; the driving unit 42 is electrically connected with each steering engine 22 through different output channels to output power to drive and control the operation and execution of the steering engines; the driving unit 42 is electrically connected to the control unit 43, and the control unit 43 participates in power output control and operation control of the driving unit 42; the inertia measurement unit 5 is electrically connected to the control unit 43, the inertia measurement unit 5 measures three-dimensional position, three-dimensional speed, three-dimensional acceleration, three-axis angle, three-dimensional angular speed, flight direction and flight height data of the aircraft and transmits the data to the control unit 43, the control unit 43 performs resolving, optimizing and error compensation on control parameters of the current aircraft attitude according to the flight motion data, adjusts and optimizes power output control on the driving unit 42, and controls the output power of each engine 21 by adjusting the moment of the accelerator pulled by each steering engine 22 so as to adjust the rotating speed of each outer edge ring wing blade type propeller 1; the driver operates the driver operating device 7 to send an operating action command and an input signal to the control unit 43; the control unit 43 controls the driving unit 42 to adjust the output power of each steering engine 22 according to the operation action instruction, so as to adjust the moment of each steering engine 22 pulling the accelerator of the engine 21, and control the output power of each engine 21, thereby adjusting the rotating speed of each outer edge ring wing blade type propeller 1, and realizing the control of the flight action of the aircraft; the control unit 43 outputs the operation parameters and the control parameters to the electronic instrument device 71, and provides data reference for the pilot to assist the pilot in piloting the flight;

the driver operates the driver control device 7 to control and adjust the operation parameters, operation and output power of the power supply and drive control unit 4, so as to control and adjust the moment of the accelerator pulled by each steering engine 22, further control and adjust the rotating speed of the plurality of engines 21 and the plurality of outer edge ring wing blade type propellers 1, and enable the aircraft to realize acceleration and deceleration flight, hovering and vertical take-off and landing; the rotation speed difference is generated among the outer edge ring wing blade type propellers 1, so that the flying rolling, the flying steering, the pitching flying and the yawing flying are realized; in the rapid flat flight process, the outer edge ring wing blade type propeller 1 utilizes the outer edge flat ring wing 101 to cut and adapt to the windward rapid laminar flow or the crosswind laminar flow, so that after the windward laminar flow or the crosswind laminar flow is cut and guided by the outer edge flat ring wing 101, the direct airflow impact of the windward laminar flow or the crosswind laminar flow on the inner side blades 102 of the ring wings is avoided, the shock wave vibration generated at the wing tips of the inner blades 102 is avoided, and the problems of large wind resistance, unstable flight or hovering wind blowing yaw caused by the reasons are avoided or alleviated.

Further, the four multi-propeller aircraft described in schemes 1 to 4 further include: a plurality of support arms 30 and/or a plurality of bladed propellers 11 and/or a plurality of guard rings 10; the supporting arms 30 are uniformly scattered and distributed on the machine body 3, and the outer edge ring wing blade type propellers 1, the blade type propellers 11, the electric motor 2, the engine 21 or the steering engine 22 are respectively and correspondingly connected with one supporting arm 30; the blade propellers 11 and the outer edge ring wing blade propellers 1 are used in a mixed mode, the mounting positions of part of the outer edge ring wing blade propellers 1 are replaced, and the two propellers jointly generate lift force and flight power; the plurality of protective rings 10 are connected to the body 3 or the supporting arms 30 and shield the periphery of the outer edge ring wing blade type propeller 1 or the blade type propeller 11 so as to prevent hurting people or buffer flight collision.

Further, the four multi-propeller aircraft described in schemes 1 to 4 further include: camera device 8 and/or pan-tilt 9 and/or electronic compass 51 and/or barometer 52 and/or satellite positioning module 50; the camera device 8 is fixed on the machine body 3, the camera device 8 is electrically connected with the power supply and the driving and controlling device 4, the power supply of the camera device 8 is controlled, the camera device 8 is powered on and shooting is controlled, and the camera device 8 is used for recording, shooting and locally storing images or videos; or, the camera device 8 is further arranged on the cloud deck 9, the cloud deck 9 is fixed on the body 3, the cloud deck 9 provides fixing, supporting and mounting positions for the camera device 8, provides stability-increasing and anti-shake functions for the camera device 8, and adjusts the horizontal and pitching shooting angles of the camera device 8, and the cloud deck 9 is electrically connected to the power supply and the driving and controlling device 4 to supply power thereto and controls the electrifying and rotating shooting actions of the cloud deck 9; or, the camera device 8 further implements wireless image transmission through the communication transceiver unit 6 and the wireless remote control device 60, and is used for implementing auxiliary flight under wireless remote control remote monitoring operation of the aircraft in a remote control flight mode; the electronic compass 51 is fixed on the fuselage 3, is electrically connected with the control unit 43 and the battery unit 41, and is used for separately measuring the flight direction data and transmitting the flight direction data to the control unit 43 so as to make reference correction on the flight direction data in the inertial measurement unit 5; the barometer 52 is also fixed to the fuselage 3, is electrically connected to the control unit 43 and the battery unit 41, and separately measures the flight height data and transmits the flight height data to the control unit 43, so that the flight height data in the inertial measurement unit 5 is corrected with reference thereto; the satellite positioning module 50 is also fixed to the body 3, is electrically connected to the control unit 43 and the battery unit 41, and provides data reference for the pilot to assist the pilot in performing navigation flight by measuring satellite positioning data; or, the control unit 43 wirelessly transmits the satellite positioning data to the wireless remote control device 60 through the communication transceiver unit 6, so that the aircraft can provide data reference for the user to assist the user in realizing wireless remote control flight and facilitating positioning and recovery after loss in the remote control flight mode.

Further, the four multi-propeller aircraft described in schemes 1 to 4 further include: a parachute 300; the safety rope of the parachute 300 is connected to the body 3; under the dangerous condition that the aircraft is parked in high altitude, the user operates to release and open the parachute 300, so that the aircraft is prevented from being crashed through parachute landing, and the safety factor is improved.

Further, the four multi-propeller aircraft described in schemes 1 to 4 further include: a fuel power generation device 40; the fuel oil power generation device 40 is fixedly arranged on the machine body 3; the fuel power generation device 40 is electrically connected to the battery unit 41 in the power supply and control unit 4; the fuel oil power generation device 40 mainly comprises a fuel oil engine and a generator, and generates power to drive the generator to generate power by burning fuel carried by the fuel oil engine and the generator to charge the battery unit 41 in an extended range mode.

Preferably, the straight cross-section of the flat outer edge ring wing 101 in the outer edge ring wing type propeller 1 in the schemes 1 to 4 is in a shape of a flat wing profile, a flat convex wing profile, a double convex wing profile, a concave-convex wing profile or a flat triangular wing profile; the surface of the flat airfoil of the flat outer edge ring wing 101 in the outer edge ring wing type propeller 1 is smooth, or the surface of the flat airfoil of the flat outer edge ring wing 101 is provided with continuous guide grooves, or continuous guide bosses, or continuous guide wingknives, or discrete guide grooves, or discrete guide bosses, or discrete guide wingknives, or discrete guide through holes, or scattering guide grooves, or scattering guide bosses, or scattering guide wingknives, or scattering guide through holes, so as to further weaken the interference impact of the high-speed impact airflow on the front side to the lift airflow of the blade 102 when the aircraft flies and the blade 102 rotates, and enhance the cutting and flow guiding effects of the outer edge flat ring wing 101 on the windward laminar flow or the cross wind laminar flow; the number of the blades 102 in the outer edge ring wing blade type propeller 1 is two, or three, or more; the number of the overlapped layers of the outer edge ring wing blade type propeller 1 is single layer, or double layer, or three layer, or multiple layer.

Preferably, in the

embodiment

1 or 3, the communication transceiver unit 6 and the wireless remote control device 60 implement wireless communication and control between them by using a WLAN communication module, a bluetooth communication module, a ZigBee communication module, or a 4G/5G communication module; the wireless remote control device 60 comprises a mobile phone, a remote control wrist strap, brain wave control glasses, remote control VR glasses, a remote control VR helmet, an image control helmet, a ground remote control station, a flight control remote controller or a flight control network platform; the landing gear 31 is a rigid landing gear, or an elastic landing gear, or a wheel type fixed landing gear, or a wheel type foldable landing gear, or a water surface buoyancy landing gear, or a skid type landing gear, or a hydraulic buffer landing gear.

Compared with the prior art, the invention has the beneficial effects that:

1. the invention provides two schemes of unmanned remote control multi-propeller aircrafts in the

schemes

1 and 3, and provides a new scheme for a flying carrier of unmanned remote control multi-rotor flying;

2. the invention provides two manned multi-propeller aircraft schemes in the schemes 2 and 4, and provides a new scheme for the manned multi-rotor flying carrier;

3. in the schemes 1-4 of the invention, the outer edge ring wing blade type propeller is adopted to generate lift force and flight power, and the outer edge flat ring wing is utilized to cut and adapt to the windward fast laminar flow or cross wind laminar flow, so that the windward or cross wind laminar flow is cut and guided by the outer edge flat ring wing, and the direct airflow impact of the windward or cross wind laminar flow on the inner side blades of the ring wing is avoided, thereby being particularly beneficial to solving the problem that the aircraft is easy to deviate from a hovering position under the action of cross wind when suspended under the condition of cross wind;

4. in the schemes 1-4 of the invention, the outer edge ring wing blade type propeller is adopted to generate lift force and flight power, and the outer edge flat ring wing is utilized to cut and adapt to the windward fast laminar flow or cross wind laminar flow, so that after the windward or cross wind laminar flow is cut and guided by the outer edge flat ring wing, the direct impact of the blades and the windward fast laminar flow when advancing is avoided, and the wind resistance can be reduced to further improve the flight speed;

5. in the schemes 1-4 of the invention, the outer edge ring wing blade type propeller is adopted to generate lift force and flight power, and the outer edge flat ring wing is utilized to cut and adapt to windward fast laminar flow or crosswind laminar flow, so that shock wave vibration generated by the wing tip of the inner ring blade is avoided, and the flight stability can be further improved;

6. after the outer edge ring wing type propeller is adopted in the schemes 1-4, the paddle is positioned in the ring of the flat outer edge ring wing, and the paddle cannot be directly extended and exposed outwards, so that fingers are not easy to hit and cut, even if the fingers touch the flat outer edge ring wing, the outer edge of the flat outer edge ring wing is not edged, so that only a friction effect is generated after the fingers or other parts of the skin of a human body are touched, and compared with the impact cutting injury of a common blade type propeller, the damage is smaller and safer;

7. after the outer edge ring wing blade type propeller is adopted in the schemes 1 to 4, the blades are positioned in the ring of the flat outer edge ring wing and cannot be directly extended and exposed outwards, so that the blades are not easy to hook obstacles such as branches and cables in the flying process, and the flying safety is improved;

8. after the outer edge ring wing blade type propeller is adopted in the schemes 1-4, the blades are positioned in the ring of the flat outer edge ring wing, the outer edge flat ring wing is utilized to shield the blades in the protecting ring, and the blades cannot be directly extended and exposed outwards, so that the safety is still realized even if a user cancels the installation of the blade protecting ring for the purpose of convenient storage;

9. in the schemes 3 and 4, the scheme that the power of the fuel engine is controlled by the steering engine to pull the accelerator is adopted, and compared with the pure electric driving scheme, the scheme that the power of the fuel engine is controlled by the steering engine to carry oil randomly has longer endurance time;

10. the parachute is adopted in the scheme of the invention, so that the user and the aircraft can be prevented from crashing through parachute landing under the dangerous condition that the aircraft is parked in high altitude, and the safety coefficient is improved;

11. the scheme of the invention adopts the fuel oil power generation device to increase the range for power generation, can solve the problem that the flying climbing of the aircraft has large power consumption and insufficient suspension capacity, and can ensure the flying and land mileage;

12. the scheme of the invention adopts the holder and the camera device to realize recording, shooting or assisting the unmanned flight of the aircraft under the wireless remote control remote monitoring operation in the flight state, particularly, the scheme mainly solves the problem of reducing the yaw of the aircraft during hovering shooting in the crosswind environment and is beneficial to improving the stability of the aircraft in hovering shooting.

Drawings

FIG. 1 is a multi-propeller aircraft embodiment 1 of the present invention;

FIG. 2 is embodiment 2 of the multi-propeller aircraft of the present invention;

FIG. 3 is embodiment 3 of the multi-propeller aircraft of the present invention;

FIG. 4 is embodiment 4 of the multi-propeller aircraft of the present invention;

FIG. 5 is a system schematic of embodiment 1 of the multi-propeller aircraft of the present invention;

FIG. 6 is a system schematic of embodiment 2 of the multi-propeller aircraft of the present invention;

FIG. 7 is a system schematic of embodiment 3 of the multi-propeller aircraft of the present invention;

FIG. 8 is a system schematic of embodiment 4 of the multi-propeller aircraft of the present invention;

figure 9 is embodiment 5 of the multi-rotor aircraft of the present invention;

figure 10 is embodiment 6 of the multi-rotor aircraft of the present invention;

figure 11 is embodiment 7 of the multi-rotor aircraft of the present invention;

figure 12 is embodiment 8 of the multi-rotor aircraft of the present invention;

figure 13 is embodiment 9 of the multi-rotor aircraft of the present invention;

FIG. 14 is a single-layer design of an outer edge ring blade propeller;

FIG. 15 is a view illustrating a shape pattern of a straight section of a flat outer edge ring blade of the outer edge ring blade type propeller;

FIG. 16 is an illustration of a flat outer edge ring wing airfoil flow guiding configuration of an outer edge ring wing blade propeller;

FIG. 17 is a side view of the outer ring blade propeller at rest with passive cutting airflow for drainage;

FIG. 18 is a side view of the outer edge ring blade propeller rotating to cut airflow against the wind to induce flow;

FIG. 19 is a top view of the outer edge ring blade propeller at rest with passive cutting airflow for flow diversion;

fig. 20 is a top view of the outer ring blade propeller rotating to direct the cutting airflow against the wind.

Description of reference numerals:

an outer edge ring wing blade type propeller 1; a motor 2; an engine 21; a steering engine 22; a body 3; a support arm 30; a landing gear 31; a cockpit 32; a power supply and drive control unit 4; a battery cell 41; a drive unit 42; a control unit 43; an inertia measurement unit 5; a communication transceiver unit 6; a wireless remote control device 60; a driver operating device 7; an electronic instrumentation device 71; an image pickup device 8; a pan-tilt head 9; a guard ring 10; a blade propeller 11; a fuel power generation device 40; a satellite positioning module 50; an electronic compass 51; a barometer 52; a flat outer rim ring wing 101; a blade 102; a hub 103; a rotating shaft 104; a flow guide groove 111; a flow guide boss 112; a guide vane 113; a flow guide through hole 114; a parachute 300.

Detailed Description

The embodiments of the present invention will be further described with reference to the accompanying drawings.

Fig. 1 shows an embodiment 1 of the multi-propeller aircraft of the present invention. As shown, scheme 1: a multi-propeller aircraft comprising: the system comprises four outer edge ring wing blade type propellers 1, four motors 2, a machine body 3, an undercarriage 31, a power supply and control unit 4, an inertia measurement unit 5, a communication transceiving unit 6 and a wireless remote control device 60; wherein, outer fringe ring wing blade formula screw 1 includes again: a flat outer edge ring wing 101, a plurality of blades 102, a hub 103, a rotating shaft 104; in addition, the support arm 30, the camera device 8, the electronic compass 51 and the barometer 52 are also included;

the flat outer edge ring wing 101 is of a flat circular ring structure, the blades 102 are uniformly distributed and connected between the flat outer edge ring wing 101 and the hub 103, the rotating shaft 104 is connected with the fixed hub 103, and the motor 2 is connected with and drives the rotating shaft 104 so as to drive the whole outer edge ring wing blade type propeller 1 to rotate;

the four outer edge ring wing blade type propellers 1 and the four motors 2 are uniformly distributed and connected on the machine body 3 through the four supporting arms 30, and the four motors 2 respectively drive the four outer edge ring wing blade type propellers 1 to rotate to generate lift force and flying power; the landing gear 31 is fixed on the fuselage 3 and used for buffering taking off and landing; the inertia measurement unit 5 and the communication transceiving unit 6 are fixed on the body 3; the communication transceiver unit 6 is connected with the wireless remote control device 60 in a matching way through wireless communication; the electronic compass 51 and the barometer 52 are also fixed to the body 3; the camera device 8 is fixed on the body 3, and the camera device 8 is used for recording, shooting and locally storing images or videos; or, the camera device 8 further implements wireless image transmission through the communication transceiver unit 6 and the wireless remote control device 60, and is used for implementing auxiliary flight under wireless remote control remote monitoring operation of the aircraft in a remote control flight mode;

the wireless remote control device 60 is connected with the communication transceiver unit 6 in a wireless communication matching way, and a user operates the wireless remote control device 60 to control and adjust the operation parameters, operation and output power of the power supply and control unit 4 through the communication transceiver unit 6, so that the rotating speeds of the four motors 2 and the four outer edge ring wing blade type propellers 1 are controlled and adjusted, and the aircraft can realize acceleration and deceleration flight, air hovering and vertical take-off and landing; the four outer edge ring wing blade type propellers 1 generate rotation speed difference mutually, so that the flying rolling, the flying steering, the pitching flying and the yawing flying are realized; in the rapid flat flight process, the outer edge ring wing blade type propeller 1 utilizes the outer edge flat ring wing 101 to cut and adapt to the windward rapid laminar flow or the crosswind laminar flow, so that after the windward laminar flow or the crosswind laminar flow is cut and guided by the outer edge flat ring wing 101, the direct airflow impact of the windward laminar flow or the crosswind laminar flow on the inner side blades 102 of the ring wings is avoided, the shock wave vibration generated at the wing tips of the inner blades 102 is avoided, and the problems of large wind resistance, unstable flight or hovering wind blowing yaw caused by the reasons are avoided or alleviated.

Fig. 2 shows an embodiment 2 of the multi-propeller aircraft of the present invention. As shown, scheme 2: a multi-propeller aircraft comprising: the system comprises four outer edge ring wing blade type propellers 1, four motors 2, a fuselage 3, an undercarriage 31, a cockpit 32, a power supply and control unit 4, an inertia measurement unit 5, a driver operating device 7 and an electronic instrument device 71; wherein, outer fringe ring wing blade formula screw 1 includes again: a flat outer edge ring wing 101, a plurality of blades 102, a hub 103, a rotating shaft 104; in addition, the supporting arm 30 and the fuel power generation device 40 are also included;

the four outer edge ring wing blade type propellers 1 and the four motors 2 are uniformly distributed and connected on the machine body 3 through the four supporting arms 30, and the four motors 2 respectively drive the four outer edge ring wing blade type propellers 1 to rotate to generate lift force and flying power; the landing gear 31 is fixed on the fuselage 3 and used for buffering taking off and landing; the cockpit 32 is fixedly connected with the fuselage 3, and a pilot control position is arranged in the cockpit 32; the driver operating device 7 is arranged in the cab 32 for the driver to operate and drive; the inertia measurement unit 5 is fixed on the machine body 3; the electronic instrumentation 71 is fixed in the cockpit 32; the electronic instrument device 71 detects and displays the endurance mileage, the flying height, the flying airspeed, the climbing and descending speed, the flying attitude and the flying heading data as well as the operation data parameters and the control parameters of the motor 2 and the power supply and control device 4, and provides data reference for the driver to assist the driver in flying; the fuel oil power generation device 40 is fixedly arranged on the machine body 3; the fuel power generation device 40 is electrically connected to the battery unit 41 in the power supply and control unit 4; the fuel oil power generation device 40 mainly comprises a fuel oil engine and a generator, and generates power to drive the generator to generate power by burning carried fuel to charge the battery unit 41 in an extended range manner; in particular, in the embodiment, because the aircraft needs to fly by people, a large amount of stored power is inevitably consumed under heavy-load working conditions, and the requirement of extended-range endurance can be well met by additionally arranging the fuel power generation device 40;

the driver operates the driver control device 7 to control and adjust the operation parameters, the operation and the output power of the power supply and control unit 4, thereby controlling and adjusting the rotating speed of the four motors 2 and the four outer edge ring wing blade type propellers 1, and enabling the aircraft to realize acceleration and deceleration flight, air hovering and vertical take-off and landing; the four outer edge ring wing blade type propellers 1 generate rotation speed difference mutually, so that the flying rolling, the flying steering, the pitching flying and the yawing flying are realized; in the rapid flat flight process, the outer edge ring wing blade type propeller 1 utilizes the outer edge flat ring wing 101 to cut and adapt to the windward rapid laminar flow or the crosswind laminar flow, so that after the windward laminar flow or the crosswind laminar flow is cut and guided by the outer edge flat ring wing 101, the direct airflow impact of the windward laminar flow or the crosswind laminar flow on the inner side blades 102 of the ring wings is avoided, the shock wave vibration generated at the wing tips of the inner blades 102 is avoided, and the problems of large wind resistance, unstable flight or hovering wind blowing yaw caused by the reasons are avoided or alleviated.

Fig. 3 shows an embodiment 3 of the multi-propeller aircraft of the present invention. As shown, scheme 3: a multi-propeller aircraft comprising: the system comprises four outer edge ring wing blade type propellers 1, four engines 21, four steering engines 22, a fuselage 3, an undercarriage 31, a power supply and control unit 4, an inertia measurement unit 5, a communication transceiving unit 6 and a wireless remote control device 60; wherein, outer fringe ring wing blade formula screw 1 includes again: a flat outer edge ring wing 101, a plurality of blades 102, a hub 103, a rotating shaft 104; in addition, the device also comprises a supporting arm 30, a camera device 8, a cloud deck 9 and a satellite positioning module 50; specifically, the satellite positioning module 50 in the figure takes the english abbreviation BDS of the beidou navigation positioning system as a symbol;

the flat outer edge ring wing 101 is of a flat circular ring structure, the blades 102 are uniformly distributed and connected between the flat outer edge ring wing 101 and the hub 103, the rotating shaft 104 is connected with the fixed hub 103, and the engine 21 is connected with and drives the rotating shaft 104 so as to drive the whole outer edge ring wing blade type propeller 1 to rotate;

the four outer edge ring wing blade type propellers 1 and the four engines 21 are uniformly distributed and connected on the machine body 3 through the four supporting arms 30, and the four engines 21 respectively drive the plurality of outer edge ring wing blade type propellers 1 to rotate to generate lift force and flying power; the four steering engines 22 are respectively and correspondingly connected with an engine 21, and the steering engines 22 control the accelerator pulling action of the engine 21; the landing gear 31 is fixed on the fuselage 3 and used for buffering taking off and landing; the inertia measurement unit 5 and the communication transceiving unit 6 are fixed on the body 3; the communication transceiver unit 6 is connected with the wireless remote control device 60 in a matching way through wireless communication; the camera device 8 is arranged on the cloud deck 9, the cloud deck 9 is fixed on the machine body 3, the cloud deck 9 provides fixing, supporting and mounting positions for the camera device 8, provides stability-increasing and anti-shaking functions for the camera device 8, and adjusts the horizontal and pitching shooting angles of the camera device 8; the camera device 8 is used for recording, shooting and locally storing images or videos; or, the camera device 8 further implements wireless image transmission through the communication transceiver unit 6 and the wireless remote control device 60, and is used for implementing auxiliary flight under wireless remote control remote monitoring operation of the aircraft in a remote control flight mode; in the figure, the satellite positioning module 50 is also fixed on the fuselage 3, and after measuring the satellite positioning data, the satellite positioning data is wirelessly transmitted to the wireless remote control device 60 through the communication transceiver unit 6, so that the aircraft provides data reference for a user to assist the user in realizing wireless remote control flight and facilitate positioning and recovery after loss in a remote control flight mode;

the wireless remote control device 60 is connected with the communication transceiving unit 6 in a matching way through wireless communication, a user operates the wireless remote control device 60 to control and adjust the operation parameters, operation and output power of the power supply and driving and controlling unit 4 through the communication transceiving unit 6, and finally the rotation speeds of the four engines 21 and the four outer edge ring wing blade type propellers 1 are controlled and adjusted by adjusting the moment of the action of pulling the accelerator by each steering engine 22, so that the aircraft can realize acceleration and deceleration flight, hovering in the air and vertical take-off and landing; the four outer edge ring wing blade type propellers 1 generate rotation speed difference mutually, so that the flying rolling, the flying steering, the pitching flying and the yawing flying are realized; in the rapid flat flight process, the outer edge ring wing blade type propeller 1 utilizes the outer edge flat ring wing 101 to cut and adapt to the windward rapid laminar flow or the crosswind laminar flow, so that after the windward laminar flow or the crosswind laminar flow is cut and guided by the outer edge flat ring wing 101, the direct airflow impact of the windward laminar flow or the crosswind laminar flow on the inner side blades 102 of the ring wings is avoided, the shock wave vibration generated at the wing tips of the inner blades 102 is avoided, and the problems of large wind resistance, unstable flight or hovering wind blowing yaw caused by the reasons are avoided or alleviated.

Fig. 4 shows an embodiment 4 of the multi-propeller aircraft of the present invention. As shown, scheme 4: a multi-propeller aircraft comprising: the system comprises four outer edge ring wing blade type propellers 1, four engines 21, four steering engines 22, a fuselage 3, an undercarriage 31, a cockpit 32, a power supply and drive control unit 4, an inertia measurement unit 5, a driver control device 7 and an electronic instrument device 71; wherein, outer fringe ring wing blade formula screw 1 includes again: a flat outer edge ring wing 101, a plurality of blades 102, a hub 103, a rotating shaft 104; furthermore, a support arm 30, a satellite positioning module 50; specifically, the satellite positioning module 50 is also denoted by BDS as a symbol in the figure;

the four outer edge ring wing blade type propellers 1 and the four engines 21 are uniformly distributed and connected on the machine body 3 through the four supporting arms 30, and the four engines 21 respectively drive the four outer edge ring wing blade type propellers 1 to rotate to generate lift force and flying power; the four steering engines 22 are respectively and correspondingly connected with an engine 21, and the steering engines 22 control the accelerator pulling action of the engine 21; the landing gear 31 is fixed on the fuselage 3 and used for buffering taking off and landing; the cockpit 32 is fixedly connected with the fuselage 3, and a pilot control position is arranged in the cockpit 32; the driver operating device 7 is arranged in the cab 32 for the driver to operate and drive; the inertia measurement unit 5 is fixed on the machine body 3; the electronic instrumentation 71 is fixed in the cockpit 32; the electronic instrument device 71 detects and displays the endurance mileage, the flying height, the flying airspeed, the climbing and descending rate, the flying attitude and the flying heading data as well as the operation data parameters and the control parameters of the engine 21 and the power supply and control device 4, and provides data reference for the driver to assist the driver in flying; in the figure, the satellite positioning module 50 is also fixed on the fuselage 3, and the satellite positioning data measured by the satellite positioning module provides data reference for the driver to assist the driver in realizing navigation flight;

Fig. 5 is a system schematic diagram of the multi-propeller aircraft embodiment 1 of the present invention. As shown, the diagram includes: the system comprises four outer edge ring wing blade type propellers 1, four motors 2, a power supply and drive control unit 4, an inertia measurement unit 5, a communication transceiving unit 6 and a wireless remote control device 60; wherein, the power supply and control unit 4 further comprises: battery unit 41, drive unit 42, control unit 43; in addition, the figure also comprises a camera device 8, an electronic compass 51 and a barometer 52;

the motor 2, the driving unit 42, the control unit 43, the inertia measuring unit 5 and the communication transceiving unit 6 are electrically connected with the battery unit 41; the battery unit 41 supplies power to the power consumption unit of the whole aircraft after charging and storing electricity, and recharges and stores energy when the electricity is insufficient; the driving unit 42 is electrically connected with each motor 2 by different output channels to drive and control the operation of the motors with output power; the driving unit 42 is electrically connected to the control unit 43, and the control unit 43 participates in power output control and operation control of the driving unit 42; the inertia measurement unit 5 is electrically connected to the control unit 43, the inertia measurement unit 5 measures three-dimensional position, three-dimensional velocity, three-dimensional acceleration, three-axis angle, three-dimensional angular velocity, flight direction and flight altitude data of the aircraft and transmits the data to the control unit 43, and the control unit 43 performs resolving, optimizing and error compensating on control parameters of the current aircraft attitude according to the flight motion data, and adjusts and optimizes the power output control of the driving unit 42; the camera device 8 is electrically connected with the power supply and the driving and controlling device 4, and the power supply of the camera device 8 and the shooting action are controlled by the camera device; the electronic compass 51 is electrically connected to the control unit 43 and the battery unit 41, and is used for separately measuring flight direction data and transmitting the flight direction data to the control unit 43, so that the flight direction data in the inertial measurement unit 5 is subjected to reference correction; the barometer 52 is electrically connected to the control unit 43 and the battery unit 41, and is used for separately measuring the flight height data and transmitting the flight height data to the control unit 43, so that the flight height data in the inertial measurement unit 5 is corrected with reference to the flight height data; the communication transceiver unit 6 receives the operation action command and the input signal from the wireless remote control device 60 and transmits the operation action command and the input signal to the control unit 43; the control unit 43 outputs the operation parameters and the control parameters to the wireless remote control device 60 through the communication transceiving unit 6, and provides data reference for the user to assist the user in realizing wireless remote control flight.

Fig. 6 is a system schematic diagram of the multi-propeller aircraft embodiment 2 of the present invention. As shown, the diagram includes: the system comprises four outer edge ring wing blade type propellers 1, four motors 2, a power supply and drive control unit 4, an inertia measurement unit 5, a driver control device 7 and an electronic instrument device 71; wherein, the power supply and control unit 4 further comprises: battery unit 41, drive unit 42, control unit 43; in addition, a fuel power generation device 40 is also included;

the electric motor 2, the driving unit 42, the control unit 43, the inertia measurement unit 5 and the driver operating device 7 are electrically connected with the battery unit 41; the battery unit 41 supplies power to the power consumption unit of the whole aircraft after charging and storing electricity, and recharges and stores energy when the electricity is insufficient; the driving unit 42 is electrically connected with each motor 2 by different output channels to drive and control the operation of the motors with output power; the driving unit 42 is electrically connected to the control unit 43, and the control unit 43 participates in power output control and operation control of the driving unit 42; the inertia measurement unit 5 is electrically connected to the control unit 43, the inertia measurement unit 5 measures three-dimensional position, three-dimensional velocity, three-dimensional acceleration, three-axis angle, three-dimensional angular velocity, flight direction and flight altitude data of the aircraft and transmits the data to the control unit 43, and the control unit 43 performs resolving, optimizing and error compensating on control parameters of the current aircraft attitude according to the flight motion data, and adjusts and optimizes the power output control of the driving unit 42; the driver operates the driver operating device 7 to send an operating action command and an input signal to the control unit 43; the control unit 43 controls the driving unit 42 to adjust the power output control of the plurality of motors 2 according to the operation action command so as to realize the control of the flight action of the aircraft; the control unit 43 outputs the operation parameters and the control parameters to the electronic instrument device 71, and provides data reference for the pilot to assist the pilot in piloting the flight; in this figure, the fuel power generation device 40 is electrically connected to the battery unit 41 and the control unit 43 in the power supply and control unit 4; the fuel oil power generation device 40 mainly comprises a fuel oil engine and a generator, generates power to drive the generator to generate power by burning carried fuel, and carries out range-extending charging for a battery unit 41 in the power supply and control unit 4; the driver can also give a start instruction to the control unit 43 through the driver operating device 7 as needed to start the fuel power generation device 40; alternatively, the driver may directly start the fuel generator 40 manually to charge the battery unit 41.

Fig. 7 is a system schematic diagram of the multi-propeller aircraft embodiment 3 of the present invention. As shown, the diagram includes: the system comprises four outer edge ring wing blade type propellers 1, four engines 21, four steering engines 22, a power supply and driving control unit 4, an inertia measurement unit 5, a communication transceiving unit 6 and a wireless remote control device 60; wherein, the power supply and control unit 4 further comprises: battery unit 41, drive unit 42, control unit 43; in addition, the figure also comprises a camera device 8, a tripod head 9 and a satellite positioning module 50;

the steering engine 22, the driving unit 42, the control unit 43, the inertia measurement unit 5 and the communication transceiving unit 6 are electrically connected with the battery unit 41; the battery unit 41 supplies power to the power consumption unit of the whole aircraft after charging and storing electricity, and recharges and stores energy when the electricity is insufficient; the driving unit 42 is electrically connected with each steering engine 22 through different output channels to output power to drive and control the operation and execution of the steering engines; the driving unit 42 is electrically connected to the control unit 43, and the control unit 43 participates in power output control and operation control of the driving unit 42; the inertia measurement unit 5 is electrically connected to the control unit 43, the inertia measurement unit 5 measures three-dimensional position, three-dimensional speed, three-dimensional acceleration, three-axis angle, three-dimensional angular speed, flight direction and flight height data of the aircraft and transmits the data to the control unit 43, the control unit 43 performs resolving, optimizing and error compensation on control parameters of the current aircraft attitude according to the flight motion data, adjusts and optimizes power output control on the driving unit 42, and controls the output power of each engine 21 by adjusting the moment of the accelerator pulled by each steering engine 22 so as to adjust the rotating speed of each outer edge ring wing blade type propeller 1; the communication transceiver unit 6 receives the operation action command and the input signal from the wireless remote control device 60 and transmits the operation action command and the input signal to the control unit 43; the control unit 43 outputs the operation parameters and the control parameters to the wireless remote control device 60 through the communication transceiving unit 6, and provides data reference for the user to assist the user in realizing wireless remote control flight; in addition, the image pickup device 8 is electrically connected to the battery unit 41 and the control unit 43 in the power supply and control device 4, the battery unit 41 supplies power to the image pickup device 8, the control unit 43 controls the power on and the shooting action of the image pickup device 8, and the image pickup device 8 is used for recording, shooting and locally storing images or videos; or, the camera device 8 further implements wireless image transmission through the communication transceiver unit 6 and the wireless remote control device 60, and is used for implementing auxiliary flight under wireless remote control remote monitoring operation of the aircraft in a remote control flight mode; the satellite positioning module 50 is electrically connected to the control unit 43 and the battery unit 41, the battery unit 41 supplies power to the satellite positioning module 50, and the control unit 43 wirelessly transmits the satellite positioning data to the wireless remote control device 60 through the communication transceiver unit 6, so that the aircraft can provide data reference for a user to assist the user in realizing wireless remote control flight and facilitating positioning and recovery after loss in a remote control flight mode.

Fig. 8 is a system schematic diagram of the multi-propeller aircraft embodiment 4 of the present invention. As shown, the diagram includes: the system comprises four outer edge ring wing blade type propellers 1, four engines 21, four steering engines 22, a power supply and driving control unit 4, an inertia measurement unit 5, a driver control device 7 and an electronic instrument device 71; wherein, the power supply and control unit 4 further comprises: battery unit 41, drive unit 42, control unit 43; in addition, a satellite positioning module 50 is included;

the steering engine 22, the driving unit 42, the control unit 43, the inertia measuring unit 5 and the driver operating device 7 are electrically connected with the battery unit 41; the battery unit 41 supplies power to the power consumption unit of the whole aircraft after charging and storing electricity, and recharges and stores energy when the electricity is insufficient; the driving unit 42 is electrically connected with each steering engine 22 through different output channels to output power to drive and control the operation and execution of the steering engines; the driving unit 42 is electrically connected to the control unit 43, and the control unit 43 participates in power output control and operation control of the driving unit 42; the inertia measurement unit 5 is electrically connected to the control unit 43, the inertia measurement unit 5 measures three-dimensional position, three-dimensional speed, three-dimensional acceleration, three-axis angle, three-dimensional angular speed, flight direction and flight height data of the aircraft and transmits the data to the control unit 43, the control unit 43 performs resolving, optimizing and error compensation on control parameters of the current aircraft attitude according to the flight motion data, adjusts and optimizes power output control on the driving unit 42, and controls the output power of each engine 21 by adjusting the moment of the accelerator pulled by each steering engine 22 so as to adjust the rotating speed of each outer edge ring wing blade type propeller 1; the driver operates the driver operating device 7 to send an operating action command and an input signal to the control unit 43; the control unit 43 controls the driving unit 42 to adjust the output power of each steering engine 22 according to the operation action instruction, so as to adjust the moment of each steering engine 22 pulling the accelerator of the engine 21, and control the output power of each engine 21, thereby adjusting the rotating speed of each outer edge ring wing blade type propeller 1, and realizing the control of the flight action of the aircraft; the control unit 43 outputs the operation parameters and the control parameters to the electronic instrument device 71, and provides data reference for the pilot to assist the pilot in piloting the flight; in the figure, the satellite positioning module 50 is electrically connected to the control unit 43 and the battery unit 41, and the battery unit 41 supplies power to the satellite positioning module 50, and the measured satellite positioning data provides data for the driver to assist the driver in performing navigation flight.

Fig. 9 shows an embodiment 5 of the multi-propeller aircraft of the present invention. As shown in the figure, the fuselage 3 of the multi-propeller aircraft in the present embodiment is uniformly distributed and connected with six outer edge ring blade propellers 1 and six motors 2 through six support arms 30, and the six outer edge ring blade propellers 1 are respectively driven by the six motors 2 to rotate to generate lift force and flight power.

Fig. 10 shows an embodiment 6 of the multi-propeller aircraft of the present invention. As shown in the figure, the multi-propeller aircraft in the embodiment adopts a scheme that the outer edge ring blade type propeller 1 and the blade type propeller 11 are mixed. The machine body 3 is uniformly connected with two outer edge ring wing blade type propellers 1 and two motors 2, two blade type propellers 11 and two motors 2 through four supporting arms 30; the four motors 2 respectively drive the two blade propellers 11 and the two blade propellers 11 to rotate so as to generate lift force and flight power. In addition, two guard rings 10 are used, which are connected to the support arms 30 and shield the periphery of the propeller blades 11 in order to prevent the blades from hurting people or to cushion flight impacts.

Fig. 11 shows an embodiment 7 of the multi-propeller aircraft of the present invention. As shown, the present embodiment employs a four-arm coaxial eight-motor eight-propeller scheme. It includes: eight outer edge ring wing blade type propellers 1, eight motors 2, a fuselage 3, an undercarriage 31, a power supply and control unit 4, an inertia measurement unit 5, a communication transceiving unit 6, a wireless remote control device 60 and four supporting arms 30;

four groups of outer edge ring wing blade type propellers 1 and motors 2 are uniformly distributed and connected on the machine body 3 through four supporting arms 30, wherein the two outer edge ring wing blade type propellers 1 and the two motors 2 form a group, and the two motors 2 are oppositely arranged, coaxially arranged, connected back to back and then fixed, and then respectively drive one outer edge ring wing blade type propeller 1 to rotate. Eight outer edge ring wing blade type propellers 1 are respectively driven by eight motors 2 to rotate to generate lift force and flight power.

Fig. 12 shows an embodiment 8 of the multi-propeller aircraft of the present invention. As shown, the present embodiment employs a four-arm coaxial eight-motor eight-propeller scheme. It includes: eight outer edge ring wing blade type propellers 1, four motors 2, a fuselage 3, an undercarriage 31, a power supply and control unit 4, an inertia measurement unit 5, a communication transceiving unit 6, a wireless remote control device 60 and four supporting arms 30;

the four groups of outer edge ring wing blade type propellers 1 and the motors 2 are uniformly distributed and connected on the machine body 3 through four supporting arms 30, wherein the two outer edge ring wing blade type propellers 1 and the motor 2 form a group, and the motor 2 coaxially drives the two outer edge ring wing blade type propellers 1 to rotate in a one-driving-two mode through a penetrating shaft. The eight outer edge ring wing blade type propellers 1 are respectively driven by four motors 2 to rotate to generate lift force and flying power.

Fig. 13 shows an embodiment 9 of the multi-propeller aircraft of the present invention. As shown, a parachute 300 is employed in the present embodiment; the safety rope of the parachute 300 is connected to the body 3; under the dangerous condition that the aircraft is parked in high altitude, the user operates to release and open the parachute 300, so that the aircraft is prevented from being crashed through parachute landing, and the safety factor is improved. Especially for a multi-propeller aircraft driven by a person, the personnel safety can be guaranteed through parachuting.

Fig. 14 is a single-layer structure of the outer edge ring blade type propeller shown in fig. 1. The figure shows a four-blade, single-layer, outer edge ring blade propeller. As shown in the figure, the flat outer edge ring wing 101 is a flat ring structure, four blades 102 are uniformly distributed and connected between the flat outer edge ring wing 101 and the hub 103, and the rotating shaft 104 is connected with the fixed hub 103; the external power mechanism drives the whole outer edge ring wing blade type propeller 1 to rotate by connecting and driving the rotating shaft 104. Similarly, the number of the blades of each layer of the outer edge ring wing blade type propeller 1 can also be two blades, three blades or multiple blades.

Fig. 15 is a drawing illustrating a shape pattern of a straight section of a flat outer edge ring blade of the outer edge ring blade type propeller. As shown in the figure, the straight cross section of the flat outer edge ring wing 101 in the outer edge ring wing type propeller 1 is in the shape of a flat wing profile, or a flat convex wing profile, or a double convex wing profile, or a concave-convex wing profile, or a flat triangular wing profile; and the surface of the flat airfoil of the flat outer edge ring wing 101 in the outer edge ring wing type propeller 1 is smooth.

Fig. 16 is an explanatory view of a flow guiding structure pattern of a flat outer edge ring wing surface of the outer edge ring wing blade type propeller. As shown in the figure, in the outer edge ring wing type propeller 1, a scattering-shaped guide groove 111, or a scattering-shaped guide boss 112, or a scattering-shaped guide wing knife 113, or a scattering-shaped guide through hole 114 is provided on the surface of the flat airfoil of the flat outer edge ring wing 101, so as to further reduce the interference impact of the high-speed impact airflow on the lift airflow of the blade 102 when the aircraft flies flatly and the blade 102 rotates, and enhance the cutting and flow guiding effect of the outer edge flat ring wing 101 on the windward laminar flow or the crosswind laminar flow.

Similarly, the surface of the flat airfoil of the flat outer edge ring wing 101 in the outer edge ring wing blade type propeller 1 may also be provided with a whole ring of concentric circle continuous flow guiding grooves 111, or a flow guiding boss 112, or a flow guiding wing knife 113; the guide groove 111, the guide boss 112, the guide vane 113 or the guide through hole 114 are arranged in a whole concentric circle and are discontinuous. The effect of the blade is to further weaken the interference impact of the high-speed impact airflow facing the aircraft during the flat flight and the rotation of the blade 102 on the lift airflow of the blade 102 and enhance the cutting and drainage effect of the outer edge flat ring wing 101 on the windward laminar flow or the crosswind laminar flow.

FIG. 17 is a side view of the passive cutting flow for drainage when the outer ring blade propeller is stationary. As shown in the figure, when the outer edge ring wing blade type propeller 1 stops rotating and is hit by high-speed airflow, the air flow can be broken or cut by the wing surface arc edge on the windward side of the flat outer edge ring wing 101, so that the air flow can pass through the upper part, the lower part and the two sides of the flat outer edge ring wing 101, and further turbulent airflow caused by the direct impact of the incoming laminar flow on the blades 102 and the hub 103 can be avoided. Of course, the high-speed laminar flow facing the wind still has little turbulence avoiding the direct impact of the blades 102 and the hub 103, which cannot be completely avoided, but the flight stability of the aircraft can be greatly improved if the strong disturbance turbulence is greatly reduced.

Compared with the prior art, when the common blade propeller is in a static state and is subjected to high-speed airflow, the blades and the hub can directly face the strong impact of high-speed laminar flow, so that the strong interference turbulent flow cannot be weakened, and finally the turbulent flow can be shared and borne only by a stable control surface system of an aircraft, so that the flight stability and the safety are extremely unfavorable.

Fig. 18 is a side view of the outer ring blade propeller rotating to cut airflow against the wind to guide the airflow. As shown in the figure, in the present figure, when the outer edge ring wing blade type propeller 1 rotates, when it hits against a high-speed airflow, it can rotate the cutting airflow by means of the airfoil arc edge of the windward side of the flat outer edge ring wing 101, so that it passes through the upper and lower parts of the flat outer edge ring wing 101, and in addition, the airfoil rotation friction airflow of the flat outer edge ring wing 101 drives the boundary layer airflow and the laminar flow to deviate from direct facing, so that a part of the airflow in the center of the windward side is influenced by the rotation friction of the flat outer edge ring wing 101, and deviates to the left side when it hits against the wind; the right side facing airflow is influenced by the rotation friction of the flat outer edge ring wing 101 and the combined action of the right side outer side normal airflow, and a part of vortex can be generated; in this case, the incoming laminar flow can also avoid directly impacting the blades 102 and the hub 103, thereby reducing the generation of turbulent air flow, and thus still contributing to the improvement of the flight stability and safety of the aircraft.

FIG. 19 is a top view of the passive cutting flow for drainage when the outer edge ring blade propeller is at rest. This figure corresponds to the top view of fig. 17. As can be seen from the figure, when the outer edge ring wing blade type propeller 1 stops rotating and is subjected to high-speed airflow, the airflow can be broken or cut by means of the arc edge of the wing surface on the windward side of the flat outer edge ring wing 101, so that the airflow passes through the upper part, the lower part and the two sides of the flat outer edge ring wing 101, but the airflow passing through the upper part and the lower part is influenced by the inclined surface of the blade fan, and does not pass straight but generates certain airflow deviation, but still can avoid the direct impact of the incident laminar flow on the blades 102 and the hub 103, and does not cause excessive turbulent airflow. Compared with the common blade type propeller, the flight stability and safety of the aircraft are greatly improved.

Fig. 20 is a top view of the outer ring blade propeller rotating to direct the cutting airflow against the wind. This figure corresponds to the top view of fig. 18. As shown in the figure, it can be embodied that the airfoil surface rotation friction airflow of the flat outer edge ring wing 101 drives the boundary layer airflow and the laminar flow to deviate from direct facing, so that a part of the airflow in the center of the windward side is influenced by the rotation friction of the flat outer edge ring wing 101 and deviates to the left side when facing the wind; the right side facing airflow is influenced by the rotation friction of the flat outer edge ring wing 101 and the combined action of the right side outer side normal airflow, and a part of vortex can be generated; in this case, the incoming laminar flow can also avoid directly impacting the blades 102 and the hub 103, thereby reducing the generation of turbulent air flow, and thus still contributing to the improvement of the flight stability and safety of the aircraft.

The above examples are only for describing the preferred embodiments of the present invention, and are not intended to limit the scope of the present invention, and various modifications and improvements of the technical solution of the present invention by those skilled in the art should be made within the protection scope defined by the claims of the present invention without departing from the spirit of the present invention.

Claims

1. A multi-propeller aircraft, comprising: the system comprises a plurality of outer edge ring wing blade type propellers (1), a plurality of motors (2), a fuselage (3), an undercarriage (31), a power supply and control unit (4), an inertia measurement unit (5), a communication transceiving unit (6) and a wireless remote control device (60); wherein the outer edge ring blade type propeller (1) comprises: the blade comprises a flat outer edge ring wing (101), a plurality of blades (102), a hub (103) and a rotating shaft (104); the power supply and control unit (4) further comprises: a battery unit (41), a drive unit (42), and a control unit (43); the flat outer edge ring wing (101) is of a flat ring structure, the blades (102) are uniformly distributed and connected between the flat outer edge ring wing (101) and the hub (103), the rotating shaft (104) is connected with the fixed hub (103), and the motor (2) is connected with and drives the rotating shaft (104) to drive the whole outer edge ring wing blade type propeller (1) to rotate;

the body (3) is uniformly connected with a plurality of outer edge ring wing blade type propellers (1) and a plurality of motors (2), and the motors (2) respectively drive the outer edge ring wing blade type propellers (1) to rotate to generate lift force and flight power; the undercarriage (31) is fixed on the fuselage (3) and is used for buffering taking off and landing; the inertia measurement unit (5) and the communication transceiving unit (6) are fixed on the machine body (3); the communication transceiver unit (6) is in matching connection with the wireless remote control device (60) through wireless communication;

the motor (2), the driving unit (42), the control unit (43), the inertia measuring unit (5) and the communication transceiving unit (6) are electrically connected with a battery unit (41); the battery unit (41) supplies power to the power consumption unit of the whole aircraft after charging and storing electricity, and recharges and stores energy when the electricity is insufficient; the driving unit (42) is electrically connected with each motor (2) by different output channels to drive and control the operation of the motors by output power; the driving unit (42) is electrically connected with the control unit (43), and the control unit (43) participates in power output control and operation control of the driving unit (42); the inertia measurement unit (5) is electrically connected with the control unit (43), the inertia measurement unit (5) measures the three-dimensional position, three-dimensional speed, three-dimensional acceleration, three-axis angle, three-dimensional angular speed, flight direction and flight height data of the aircraft and transmits the data to the control unit (43), and the control unit (43) performs calculation, optimization and error compensation on the control parameters of the current aircraft attitude according to the flight motion data, and adjusts and optimizes the power output control on the driving unit (42); the communication transceiver unit (6) receives an operation action command and an input signal sent by the wireless remote control device (60) and transmits the operation action command and the input signal to the control unit (43); the control unit (43) outputs the operation parameters and the control parameters to the wireless remote control device (60) through the communication transceiving unit (6) to provide data reference for the user to assist the user in realizing wireless remote control flight;

the wireless remote control device (60) is in matching connection with the communication transceiving unit (6) through wireless communication, and a user operates the wireless remote control device (60) to control and adjust the operating parameters, the operation and the output power of the power supply and the driving and controlling unit (4) through the communication transceiving unit (6), so that the rotating speeds of the plurality of motors (2) and the plurality of outer edge ring wing blade type propellers (1) are controlled and adjusted, and the aircraft can realize accelerated and decelerated flight, hovering in the air and vertical take-off and landing; the rotating speed difference is generated among the outer edge ring wing blade type propellers (1), so that the flying rolling, the flying steering, the pitching flying and the yawing flying are realized; in the rapid flat flight process, the outer edge ring wing blade type propeller (1) utilizes the outer edge flat ring wing (101) to cut and adapt to the windward rapid laminar flow or the crosswind laminar flow, so that the windward laminar flow or the crosswind laminar flow is cut and drained by the outer edge flat ring wing (101), the direct airflow impact of the windward laminar flow or the crosswind laminar flow on the inner side blades (102) of the ring wing is avoided, the shock wave vibration generated at the wing tips of the inner side blades (102) is avoided, and the problems of large wind resistance, unstable flight or hovering wind blowing yaw caused by the reasons are avoided or alleviated.

2. A multi-propeller aircraft, comprising: the aircraft comprises a plurality of outer edge ring wing blade type propellers (1), a plurality of motors (2), an aircraft body (3), an undercarriage (31), a cockpit (32), a power supply and control unit (4), an inertia measuring unit (5), a driver operating device (7) and an electronic instrument device (71); wherein the outer edge ring blade type propeller (1) comprises: the blade comprises a flat outer edge ring wing (101), a plurality of blades (102), a hub (103) and a rotating shaft (104); the power supply and control unit (4) further comprises: a battery unit (41), a drive unit (42), and a control unit (43); the flat outer edge ring wing (101) is of a flat ring structure, the blades (102) are uniformly distributed and connected between the flat outer edge ring wing (101) and the hub (103), the rotating shaft (104) is connected with the fixed hub (103), and the motor (2) is connected with and drives the rotating shaft (104) to drive the whole outer edge ring wing blade type propeller (1) to rotate;

the body (3) is uniformly connected with a plurality of outer edge ring wing blade type propellers (1) and a plurality of motors (2), and the motors (2) respectively drive the outer edge ring wing blade type propellers (1) to rotate to generate lift force and flight power; the undercarriage (31) is fixed on the fuselage (3) and is used for buffering taking off and landing; the cockpit (32) is fixedly connected with the fuselage (3), and a pilot operation position is arranged in the cockpit (32); the driver operating device (7) is arranged in the cab (32) for the driver to operate and drive; the inertia measurement unit (5) is fixed on the machine body (3); the electronic instrument device (71) is fixed in the cockpit (32); the electronic instrument device (71) detects and displays the endurance mileage, the flying height, the flying airspeed, the climbing and descending speed, the flying attitude and the flying course data as well as the operation data parameters and the control parameters of the motor (2) and the power supply and the driving and controlling device (4), and provides data reference for the driver to assist the driver in flying;

the motor (2), the driving unit (42), the control unit (43), the inertia measuring unit (5) and the driver operating device (7) are electrically connected with a battery unit (41); the battery unit (41) supplies power to the power consumption unit of the whole aircraft after charging and storing electricity, and recharges and stores energy when the electricity is insufficient; the driving unit (42) is electrically connected with each motor (2) by different output channels to drive and control the operation of the motors by output power; the driving unit (42) is electrically connected with the control unit (43), and the control unit (43) participates in power output control and operation control of the driving unit (42); the inertia measurement unit (5) is electrically connected with the control unit (43), the inertia measurement unit (5) measures the three-dimensional position, three-dimensional speed, three-dimensional acceleration, three-axis angle, three-dimensional angular speed, flight direction and flight height data of the aircraft and transmits the data to the control unit (43), and the control unit (43) performs calculation, optimization and error compensation on the control parameters of the current aircraft attitude according to the flight motion data, and adjusts and optimizes the power output control on the driving unit (42); the driver operates the driver operating device (7) to send out an operating action command and an input signal and transmits the operating action command and the input signal to the control unit (43); the control unit (43) controls the driving unit (42) to adjust power output control of the plurality of motors (2) according to the operation action command so as to realize control of the flight action of the aircraft; the control unit (43) outputs the operation parameters and the control parameters to the electronic instrument device (71) to provide data reference for the pilot to assist the pilot in piloting the flight;

a driver operates the driver control device (7) to control and adjust the operation parameters, operation and output power of the power supply and drive control unit (4), so that the rotating speeds of the plurality of motors (2) and the plurality of outer edge ring wing blade type propellers (1) are controlled and adjusted, and the aircraft can realize acceleration and deceleration flight, hovering in the air and vertical take-off and landing; the rotating speed difference is generated among the outer edge ring wing blade type propellers (1), so that the flying rolling, the flying steering, the pitching flying and the yawing flying are realized; in the rapid flat flight process, the outer edge ring wing blade type propeller (1) utilizes the outer edge flat ring wing (101) to cut and adapt to the windward rapid laminar flow or the crosswind laminar flow, so that the windward laminar flow or the crosswind laminar flow is cut and drained by the outer edge flat ring wing (101), the direct airflow impact of the windward laminar flow or the crosswind laminar flow on the inner side blades (102) of the ring wing is avoided, the shock wave vibration generated at the wing tips of the inner side blades (102) is avoided, and the problems of large wind resistance, unstable flight or hovering wind blowing yaw caused by the reasons are avoided or alleviated.

3. A multi-propeller aircraft, comprising: the aircraft comprises a plurality of outer edge ring wing blade type propellers (1), a plurality of engines (21), a plurality of steering engines (22), an aircraft body (3), an undercarriage (31), a power supply and control unit (4), an inertia measurement unit (5), a communication transceiving unit (6) and a wireless remote control device (60); wherein the outer edge ring blade type propeller (1) comprises: the blade comprises a flat outer edge ring wing (101), a plurality of blades (102), a hub (103) and a rotating shaft (104); the power supply and control unit (4) further comprises: a battery unit (41), a drive unit (42), and a control unit (43); the flat outer edge ring wing (101) is of a flat ring structure, the blades (102) are uniformly distributed and connected between the flat outer edge ring wing (101) and the hub (103), the rotating shaft (104) is connected with the fixed hub (103), and the rotating shaft (104) is connected and driven by the engine (21) so as to drive the whole outer edge ring wing blade type propeller (1) to rotate;

the body (3) is uniformly connected with a plurality of outer edge ring wing blade type propellers (1) and a plurality of engines (21), and the plurality of engines (21) respectively drive the plurality of outer edge ring wing blade type propellers (1) to rotate to generate lift force and flight power; the steering engines (22) are respectively and correspondingly connected with an engine (21), and the steering engines (22) control the accelerator pulling action of the engine (21); the undercarriage (31) is fixed on the fuselage (3) and is used for buffering taking off and landing; the inertia measurement unit (5) and the communication transceiving unit (6) are fixed on the machine body (3); the communication transceiver unit (6) is in matching connection with the wireless remote control device (60) through wireless communication;

the steering engine (22), the driving unit (42), the control unit (43), the inertia measuring unit (5) and the communication transceiving unit (6) are electrically connected with the battery unit (41); the battery unit (41) supplies power to the power consumption unit of the whole aircraft after charging and storing electricity, and recharges and stores energy when the electricity is insufficient; the driving unit (42) is electrically connected with each steering engine (22) through different output channels to output power to drive and control the operation and execution of the steering engines; the driving unit (42) is electrically connected with the control unit (43), and the control unit (43) participates in power output control and operation control of the driving unit (42); the inertia measurement unit (5) is electrically connected with the control unit (43), the inertia measurement unit (5) measures the three-dimensional position, three-dimensional speed, three-dimensional acceleration, three-axis angle, three-dimensional angular speed, flight direction and flight height data of the aircraft and transmits the data to the control unit (43), the control unit (43) calculates, optimizes and compensates the control parameters of the current aircraft attitude according to the flight motion data, adjusts and optimizes the power output control of the driving unit (42), and controls the output power of each engine (21) by adjusting the moment of the accelerator pulled by each steering engine (22) so as to adjust the rotating speed of each outer edge ring wing blade type propeller (1); the communication transceiver unit (6) receives an operation action command and an input signal sent by the wireless remote control device (60) and transmits the operation action command and the input signal to the control unit (43); the control unit (43) outputs the operation parameters and the control parameters to the wireless remote control device (60) through the communication transceiving unit (6) to provide data reference for the user to assist the user in realizing wireless remote control flight;

the wireless remote control device (60) is connected with the communication transceiving unit (6) in a matching way through wireless communication, a user operates the wireless remote control device (60) to control and adjust the operation parameters, operation and output power of the power supply and the driving and controlling unit (4) through the communication transceiving unit (6), and finally, the rotating speeds of the plurality of engines (21) and the plurality of outer edge ring wing blade type propellers (1) are controlled and adjusted by adjusting the moment of the action of pulling an accelerator by each steering engine (22), so that the aircraft can realize acceleration and deceleration flight, air hovering and vertical take-off and landing; the rotating speed difference is generated among the outer edge ring wing blade type propellers (1), so that the flying rolling, the flying steering, the pitching flying and the yawing flying are realized; in the rapid flat flight process, the outer edge ring wing blade type propeller (1) utilizes the outer edge flat ring wing (101) to cut and adapt to the windward rapid laminar flow or the crosswind laminar flow, so that the windward laminar flow or the crosswind laminar flow is cut and drained by the outer edge flat ring wing (101), the direct airflow impact of the windward laminar flow or the crosswind laminar flow on the inner side blades (102) of the ring wing is avoided, the shock wave vibration generated at the wing tips of the inner side blades (102) is avoided, and the problems of large wind resistance, unstable flight or hovering wind blowing yaw caused by the reasons are avoided or alleviated.

4. A multi-propeller aircraft, comprising: the aircraft comprises a plurality of outer edge ring wing blade type propellers (1), a plurality of engines (21), a plurality of steering engines (22), an aircraft body (3), an undercarriage (31), a cockpit (32), a power supply and control unit (4), an inertia measuring unit (5), a driver operating device (7) and an electronic instrument device (71); wherein the outer edge ring blade type propeller (1) comprises: the blade comprises a flat outer edge ring wing (101), a plurality of blades (102), a hub (103) and a rotating shaft (104); the power supply and control unit (4) further comprises: a battery unit (41), a drive unit (42), and a control unit (43); the flat outer edge ring wing (101) is of a flat ring structure, the blades (102) are uniformly distributed and connected between the flat outer edge ring wing (101) and the hub (103), the rotating shaft (104) is connected with the fixed hub (103), and the rotating shaft (104) is connected and driven by the engine (21) so as to drive the whole outer edge ring wing blade type propeller (1) to rotate;

the body (3) is uniformly connected with a plurality of outer edge ring wing blade type propellers (1) and a plurality of engines (21), and the plurality of engines (21) respectively drive the plurality of outer edge ring wing blade type propellers (1) to rotate to generate lift force and flight power; the steering engines (22) are respectively and correspondingly connected with an engine (21), and the steering engines (22) control the accelerator pulling action of the engine (21); the undercarriage (31) is fixed on the fuselage (3) and is used for buffering taking off and landing; the cockpit (32) is fixedly connected with the fuselage (3), and a pilot operation position is arranged in the cockpit (32); the driver operating device (7) is arranged in the cab (32) for the driver to operate and drive; the inertia measurement unit (5) is fixed on the machine body (3); the electronic instrument device (71) is fixed in the cockpit (32); the electronic instrument device (71) detects and displays the endurance mileage, the flying height, the flying airspeed, the climbing and descending speed, the flying attitude and the flying course data as well as the operation data parameters and the control parameters of the engine (21) and the power supply and the driving and controlling device (4), and provides data reference for the driver to assist the driver in flying;

the steering engine (22), the driving unit (42), the control unit (43), the inertia measuring unit (5) and the driver operating device (7) are electrically connected with the battery unit (41); the battery unit (41) supplies power to the power consumption unit of the whole aircraft after charging and storing electricity, and recharges and stores energy when the electricity is insufficient; the driving unit (42) is electrically connected with each steering engine (22) through different output channels to output power to drive and control the operation and execution of the steering engines; the driving unit (42) is electrically connected with the control unit (43), and the control unit (43) participates in power output control and operation control of the driving unit (42); the inertia measurement unit (5) is electrically connected with the control unit (43), the inertia measurement unit (5) measures the three-dimensional position, three-dimensional speed, three-dimensional acceleration, three-axis angle, three-dimensional angular speed, flight direction and flight height data of the aircraft and transmits the data to the control unit (43), the control unit (43) calculates, optimizes and compensates the control parameters of the current aircraft attitude according to the flight motion data, adjusts and optimizes the power output control of the driving unit (42), and controls the output power of each engine (21) by adjusting the moment of the accelerator pulled by each steering engine (22) so as to adjust the rotating speed of each outer edge ring wing blade type propeller (1); the driver operates the driver operating device (7) to send out an operating action command and an input signal and transmits the operating action command and the input signal to the control unit (43); the control unit (43) controls the driving unit (42) to adjust the output power of each steering engine (22) according to an operation action instruction, so as to adjust the moment of each steering engine (22) pulling the accelerator of the engine (21), control the output power of each engine (21), and adjust the rotating speed of each outer edge ring wing blade type propeller (1) to realize the control of the flight action of the aircraft;

a driver operates the driver control device (7) to control and adjust the operation parameters, operation and output power of the power supply and drive control unit (4), so that the moment of the accelerator pulled by each steering engine (22) is controlled and adjusted, the rotating speeds of the plurality of engines (21) and the plurality of outer edge ring wing blade type propellers (1) are controlled and adjusted, and the aircraft is enabled to realize acceleration and deceleration flight, hovering in the air and vertical take-off and landing; the rotating speed difference is generated among the outer edge ring wing blade type propellers (1), so that the flying rolling, the flying steering, the pitching flying and the yawing flying are realized; in the rapid flat flight process, the outer edge ring wing blade type propeller (1) utilizes the outer edge flat ring wing (101) to cut and adapt to the windward rapid laminar flow or the crosswind laminar flow, so that the windward laminar flow or the crosswind laminar flow is cut and drained by the outer edge flat ring wing (101), the direct airflow impact of the windward laminar flow or the crosswind laminar flow on the inner side blades (102) of the ring wing is avoided, the shock wave vibration generated at the wing tips of the inner side blades (102) is avoided, and the problems of large wind resistance, unstable flight or hovering wind blowing yaw caused by the reasons are avoided or alleviated.

5. The multi-propeller aircraft of any one of claims 1-4, further comprising: a plurality of supporting arms (30) and/or a plurality of bladed propellers (11) and/or a plurality of guard rings (10); the supporting arms (30) are uniformly scattered and distributed on the machine body (3), and the outer edge ring wing blade type propellers (1), or blade type propellers (11), or electric motors (2), or engines (21), or steering engines (22) are respectively and correspondingly connected to one supporting arm (30); the blade propellers (11) and the outer edge ring wing blade propellers (1) are used in a mixed mode, the mounting positions of part of the outer edge ring wing blade propellers (1) are replaced, and the two propellers jointly generate lift force and flight power; the plurality of protective rings (10) are connected to the machine body (3) or the supporting arms (30) and shield the periphery of the outer edge ring wing blade type propeller (1) or the blade type propeller (11) to prevent hurting people or buffer flight collision.

6. The multi-propeller aircraft of any one of claims 1-4, further comprising: a camera device (8) and/or a pan-tilt (9) and/or an electronic compass (51) and/or a barometer (52) and/or a satellite positioning module (50); the camera device (8) is fixed on the machine body (3), the camera device (8) is electrically connected with the power supply and the driving and controlling device (4) and is powered by the power supply and used for controlling the camera device (8) to be electrified and shoot, and the camera device (8) is used for recording, shooting and locally storing images or videos; or the camera device (8) is also arranged on the cloud deck (9), the cloud deck (9) is fixed on the machine body (3), the cloud deck (9) provides fixing, supporting and installing positions for the camera device (8), stability increasing and anti-shaking functions are provided for the camera device (8), the horizontal and pitching shooting angles of the camera device (8) are adjusted, and the cloud deck (9) is electrically connected with the power supply and the driving and controlling device (4) and is used for supplying power to the power supply and controlling the electrifying and rotating shooting actions of the cloud deck (9); or the camera device (8) also realizes wireless image transmission through the communication transceiving unit (6) and the wireless remote control device (60) and is used for realizing auxiliary flight under the wireless remote control remote monitoring operation of the aircraft in a remote control flight mode; the electronic compass (51) is fixed on the fuselage (3), is electrically connected with the control unit (43) and the battery unit (41), and is used for independently measuring the flight direction data and transmitting the flight direction data to the control unit (43) so as to make the flight direction data in the inertial measurement unit (5) perform reference correction; the barometer (52) is also fixed on the fuselage (3), is electrically connected with the control unit (43) and the battery unit (41), and is used for independently measuring the flight height data and transmitting the flight height data to the control unit (43) so as to make reference correction on the flight height data in the inertial measurement unit (5); the satellite positioning module (50) is also fixed on the fuselage (3) and is electrically connected with the control unit (43) and the battery unit (41), and the satellite positioning module measures satellite positioning data to provide data reference for a driver to assist the driver in realizing navigation flight; or the control unit (43) wirelessly transmits the satellite positioning data to the wireless remote control device (60) through the communication transceiving unit (6) for the aircraft to provide data reference for the user to assist the user in realizing wireless remote control flight and facilitating positioning and recovery after loss in the remote control flight mode.

7. The multi-propeller aircraft of any one of claims 1-4, further comprising: a parachute (300); the safety rope of the parachute (300) is connected to the machine body (3); under the dangerous condition that the aircraft is parked at high altitude, a user operates to release and open the parachute (300), so that the aircraft is prevented from being crashed through parachute landing, and the safety factor is improved.

8. A multi-propeller aircraft according to any one of claims 1 to 4, further comprising: a fuel power generation device (40); the fuel oil power generation device (40) is fixedly arranged on the machine body (3); the fuel oil power generation device (40) is electrically connected with a battery unit (41) in the power supply and control unit (4); the fuel oil power generation device (40) mainly comprises a fuel oil engine and a generator, and the fuel oil engine and the generator are driven to generate power by burning the carried fuel to charge the battery unit (41) in an extended range mode.

9. The multi-propeller aircraft as recited in any one of claims 1 to 4, wherein the straight cross section of the flat outer edge ring wing (101) of the outer edge ring wing propeller (1) is in the shape of a flat wing profile, a plano-convex wing profile, a biconvex wing profile, a concave-convex wing profile or a flat triangular wing profile; the surface of the flat airfoil of the flat outer edge ring wing (101) in the outer edge ring wing blade type propeller (1) is smooth, or the surface of the flat airfoil of the flat outer edge ring wing (101) is provided with continuous guide grooves, continuous guide bosses, continuous guide wingknives, discrete guide grooves, discrete guide bosses, discrete guide wingknives, discrete guide through holes, scattered guide grooves, scattered guide bosses, scattered guide wingknives or scattered guide through holes, so that the interference impact of the high-speed impact airflow on the blade (102) when the aircraft flies and the blade (102) rotates is further weakened, and the cutting and flow guiding effects of the outer edge flat ring wing (101) on the windward laminar flow or the crosswind laminar flow are enhanced; the number of the blades (102) in the outer edge ring wing blade type propeller (1) is two, or three, or more; the outer edge ring wing blade type propeller (1) is single-layer, double-layer, three-layer or multi-layer in the number of superposed layers.

10. A multi-propeller aircraft according to claim 1 or 3, wherein the communication transceiver unit (6) and the wireless remote control device (60) adopt a WLAN communication module, a bluetooth communication module, a ZigBee communication module or a 4G/5G communication module to realize wireless communication and control between the two; the wireless remote control device (60) comprises a mobile phone, a remote control wrist strap, brain wave control glasses, remote control VR glasses, a remote control VR helmet, an image control helmet, a ground remote control station, a flight control remote controller or a flight control network platform; the landing gear (31) adopts a rigid landing gear, an elastic landing gear, a wheel type fixed landing gear, a wheel type foldable landing gear, a water surface buoyancy landing gear, a skid type landing gear or a hydraulic buffer landing gear.