Electric vertical take-off and landing tilt rotor aircraft

Abstract

The invention relates to the field of aircrafts, and discloses an electric vertical take-off and landing tilt rotor aircraft which comprises an aircraft body 1, a front fixed wing 2, a rear fixed wing 3, a ducted coaxial double-rotor tilt assembly 4, an aircraft take-off and landing supporting frame 5, a power battery 6 and a flight control system 7. According to the electric vertical take-off and landing tilt rotor aircraft, directional thrust is provided through ducted coaxial double rotor tilting, and the aircraft can be transited to a transition mode from a hovering mode, then to a forward flying mode and then returns to the hovering mode. The aircraft can vertically take off and land, hover and fly forwards, special airports and runways are not needed, the use cost is reduced, the carbon emission is remarkably reduced, the manufacturing difficulty is reduced, the flight efficiency is high, the flight speed is high, and the flight stability is high.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to an electric vertical take-off and landing tilt-rotor aircraft. Background Art

[0002] Vertical take-off and landing aircraft usually refers to a type of aircraft that can take off and land vertically like a helicopter, has the ability to hover, and can fly horizontally in the manner of a fixed-wing aircraft. Benefiting from the advantages of convenient take-off and landing and high flight efficiency, vertical take-off and landing aircraft have important application value in the military. There are three types of vertical take-off and landing aircraft: rotor-type vertical take-off and landing aircraft, tilt-rotor vertical take-off and landing aircraft, and tail-seat vertical take-off and landing aircraft. These types of aircraft can meet the needs of take-off and landing in small spaces in cities. Their wide application will build a three-dimensional urban transportation network, effectively supplement ground transportation, and greatly alleviate the increasingly serious congestion problem in cities. It is an aircraft form that is oriented towards the future urban air traffic (UAM, Urban Air Mobility) scenario and is more in line with the future urban comprehensive three-dimensional transportation system.

[0003] However, existing tilt-rotor vertical take-off and landing aircraft have technical problems such as complex tilt-rotor structure, part of the rotor mechanism becoming dead weight during level flight, poor lift, short range, and high difficulty for users to drive. Summary of the invention

[0004] Based on the above problems, an object of the present invention is to provide an electric vertical take-off and landing tilt-rotor aircraft to solve the above problems in the prior art.

[0005] The present invention provides the following technical solutions: An electric vertical take-off and landing tilt-rotor aircraft comprises a fuselage 1, a front fixed wing 2, a rear fixed wing 3, a ducted coaxial twin-rotor tilt assembly 4, an aircraft landing support frame 5, a power battery 6, and a flight control system 7.

[0006] Preferably, an emergency parachute device 11 is provided above the fuselage 1; the main function of the fuselage 1 is to load equipment, passengers, cargo, etc., and the front fixed wing 2, the rear fixed wing 3, the ducted coaxial twin-rotor tilt assembly 4, the aircraft landing support frame 5, the power battery 6, the flight control system 7 and other components are connected into a whole.

[0007] Preferably, the front fixed wing 2 is located at the front of the fuselage 1, and the rear fixed wing 3 is located at the rear of the fuselage 1; the front fixed wing 2 has an aileron 21 on each side; the rear fixed wing 3 has an aileron 31 on each side; when the electric vertical take-off and landing tilt-rotor aircraft is flying horizontally, the fuselage 1, the front fixed wing 2, and the rear fixed wing 3 are the main components for generating lift. Effectively extending the flight range.

[0008] Preferably, the ducted coaxial twin rotor tilt assembly 4 includes six groups of ducted coaxial twin rotors 41, three groups of the ducted coaxial twin rotors 41 are built into the front fixed wing 2; three groups of the ducted coaxial twin rotors 41 are built into the rear fixed wing 3. The 12 groups of rotors are independently powered, independently controlled, and have a redundant design, which can ensure the safety of take-off and landing even if some rotor failures occur.

[0009] Preferably, the ducted coaxial twin rotor 41 comprises a duct 411, an upper rotor 412, a lower rotor 413, a tilt shaft 414, and a tilt drive device 415; the duct 411, the upper rotor 412, and the lower rotor 413 are fixed to the tilt shaft 414; the tilt shaft 414 is connected to the front fixed wing 2 or the rear fixed wing 3; the tilt shaft 414 can rotate from -15 degrees to 90 degrees; the tilt of the ducted coaxial twin rotor is achieved by rotating the tilt shaft 414; the tilt drive device can be a worm gear structure or other conventional structures. The tilt shaft and the fixed wing are connected in a conventional manner, and the structure is simple; the rotor is built-in to reduce the safety risk of external personnel and reduce the area of ​​the apron risk zone.

[0010] Preferably, when the electric vertical take-off and landing tilt-rotor aircraft is to achieve vertical take-off and landing, the duct axis of the ducted coaxial twin rotors 41 is deflected downward by 90 degrees (or similar to 90 degrees) and is at the 0 degree position; when the electric vertical take-off and landing tilt-rotor aircraft in the vertical take-off and landing state is to turn to level flight, it is only necessary to slowly deflect the duct axis of the ducted coaxial twin rotors 41 upward by 90 degrees (or similar to 90 degrees) and be at the 90 degree position; when the electric vertical take-off and landing tilt-rotor aircraft is in the level flight state, the thrust of the ducted coaxial twin rotors 41 is used to overcome the resistance encountered by the aircraft during flight; the electric vertical take-off and landing tilt-rotor aircraft can be controlled by controlling six groups of the ducted coaxial twin rotors 41, the ailerons 21, and the ailerons 31 to achieve vertical take-off and landing, hovering, pitching up and down, rolling left and right, turning left and right, maintaining state, etc. All rotors are used throughout the aircraft's takeoff and landing, hovering, and level flight. There is no situation in which part of the rotor mechanism becomes dead weight in a certain state.

[0011] Preferably, the aircraft landing support frame 5 is arranged at four corners below the bottom of the fuselage 1 .

[0012] Preferably, the power battery 6 is located at the bottom of the fuselage 1; the power battery 6 is a power source that provides power for the aircraft.

[0013] Preferably, the flight control system 7 is used to manipulate and control the aircraft; when the aircraft is unmanned, the flight control system 7 controls take-off and landing, hovering, and level flight according to the route and the aircraft's own state; when the aircraft is manned, the pilot does not directly control the aircraft, but the flight control system 7 controls take-off and landing, hovering, and level flight according to the pilot's intention and the aircraft's own state. The flight control system reduces the difficulty of driving for users. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a schematic diagram of the three-dimensional structure of the electric vertical take-off and landing tilt-rotor aircraft of the present invention; Figure 2 It is a schematic diagram of the structure of the electric vertical take-off and landing tilt-rotor aircraft of the present invention from a top view; Figure 3 It is a schematic diagram of the side structure of the electric vertical take-off and landing tilt-rotor aircraft of the present invention; Figure 4 It is a front structural schematic diagram of the electric vertical take-off and landing tilt-rotor aircraft of the present invention; Figure 5 It is a schematic diagram of the ducted coaxial twin-rotor structure of the electric vertical take-off and landing tilt-rotor aircraft of the present invention; Explanation of the reference numerals in the accompanying drawings: 1. fuselage; 11. emergency parachute device; 2. front fixed wing; 21. aileron; 3. rear fixed wing; 31. aileron; 4. ducted coaxial twin-rotor tilt assembly; 41. ducted coaxial twin-rotor; 411. duct; 412. upper rotor; 413. lower rotor; 414. tilt axis; 415. tilt drive device; 5. aircraft landing support frame; 6. power battery; 7. flight control system. DETAILED DESCRIPTION

[0015] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention. Example

[0016] like Figure 1-Figure 4 As shown, this embodiment discloses an electric vertical take-off and landing tilt-rotor aircraft, including a fuselage 1, a front fixed wing 2, a rear fixed wing 3, a ducted coaxial twin-rotor tilt assembly 4, an aircraft landing support frame 5, a power battery 6, and a flight control system 7.

[0017] In this embodiment, an emergency parachute device 11 is arranged above the fuselage 1; the main function of the fuselage 1 is to load equipment, passengers, cargo, etc., and the front fixed wing 2, the rear fixed wing 3, the ducted coaxial twin-rotor tilt assembly 4, the aircraft landing support frame 5, the power battery 6, the flight control system 7 and other components are connected into a whole.

[0018] In this embodiment, the front fixed wing 2 is located at the front of the fuselage 1, and the rear fixed wing 3 is located at the rear of the fuselage 1; the front fixed wing 2 has an aileron 21 on each side; the rear fixed wing 3 has an aileron 31 on each side; when the electric vertical take-off and landing tilt-rotor aircraft is flying horizontally, the fuselage 1, the front fixed wing 2, and the rear fixed wing 3 are the main components that generate lift, effectively extending the flight range.

[0019] In this embodiment, the ducted coaxial twin-rotor tilt assembly 4 includes six sets of ducted coaxial twin-rotors 41, three sets of ducted coaxial twin-rotors 41 are built into the front fixed wing 2; three sets of ducted coaxial twin-rotors 41 are built into the rear fixed wing 3. The 12 sets of rotors are independently powered and controlled. With this redundant design, even if some rotors fail, the take-off and landing flight safety can be ensured.

[0020] In this embodiment, the ducted coaxial twin rotor 41 includes a duct 411, an upper rotor 412, a lower rotor 413, a tilt shaft 414, and a tilt drive device 415; the duct 411, the upper rotor 412, and the lower rotor 413 are fixed to the tilt shaft 414; the tilt shaft 414 is connected to the front fixed wing 2 or the rear fixed wing 3; the tilt shaft 414 can rotate from -15 degrees to 90 degrees, and the ducted coaxial twin rotor can be tilted by rotating the tilt shaft 414; the tilt drive device can be a worm gear structure or other conventional structures. The tilt shaft and the fixed wing are connected in a conventional manner, and the structure is simple; the rotor is built-in, which reduces the safety risk of external personnel and reduces the area of ​​the apron risk zone.

[0021] In this embodiment, when the electric vertical take-off and landing tilt-rotor aircraft is to achieve vertical take-off and landing, the duct axis of the ducted coaxial twin rotors 41 is deflected downward by 90 degrees (or similar to 90 degrees) and is at a 0 degree position; when the electric vertical take-off and landing tilt-rotor aircraft in the vertical take-off and landing state is to turn to level flight, it is only necessary to slowly deflect the duct axis of the ducted coaxial twin rotors 41 upward by 90 degrees (or similar to 90 degrees) and be at a 90 degree position; when the electric vertical take-off and landing tilt-rotor aircraft is in the level flight state, the thrust of the ducted coaxial twin rotors 41 is used to overcome the resistance encountered by the aircraft during flight; the control of the electric vertical take-off and landing tilt-rotor aircraft in vertical take-off and landing, hovering, pitching up and down, rolling left and right, turning left and right, and maintaining the state can be achieved by controlling six groups of ducted coaxial twin rotors 41 and ailerons. All rotors act on the take-off and landing, hovering, and level flight of the aircraft throughout the process, and there is no part of the rotor mechanism becoming dead weight in a certain state.

[0022] In this embodiment, the aircraft landing support frame 5 is arranged at four corners below the bottom of the fuselage 1 .

[0023] In this embodiment, the power battery 6 is located at the bottom of the fuselage 1; the power battery 6 is a power source that provides power for the aircraft.

[0024] In this embodiment, the flight control system 7 is used to manipulate and control the aircraft; when there is no pilot, the flight control system 7 controls take-off and landing, hovering, and level flight according to the route and the aircraft's own state; when there is a pilot, the pilot does not directly control the aircraft, but the flight control system 7 controls take-off and landing, hovering, and level flight according to the pilot's intention and the aircraft's own state. The flight control system reduces the difficulty of driving for users.

[0025] The words "arrange", "set", "connect", "fix" and similar words used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, an indirect connection through an intermediate medium, or the internal connection of two components. Technical personnel in the field can understand their specific meanings in this application according to the specific circumstances.

Claims

1. An electric vertical take-off and landing tilt-rotor aircraft, characterized in that: It includes a fuselage 1, a front fixed wing 2, a rear fixed wing 3, a ducted coaxial twin-rotor tilt assembly 4, an aircraft landing support frame 5, a power battery 6, and a flight control system 7.

2. The electric vertical take-off and landing tilt-rotor aircraft according to claim 1, characterized in that: An emergency parachute device 11 is arranged above the fuselage 1; the main function of the fuselage 1 is to load equipment, passengers, cargo, etc., and the front fixed wing 2, the rear fixed wing 3, the ducted coaxial twin-rotor tilt assembly 4, the aircraft landing support frame 5, the power battery 6, the flight control system 7 and other components are connected into a whole.

3. The electric vertical take-off and landing tilt-rotor aircraft according to claim 1, characterized in that: The front fixed wing 2 is located at the front part of the fuselage 1, and the rear fixed wing 3 is located at the rear part of the fuselage 1; the front fixed wing 2 has an aileron 21 on each side; the rear fixed wing 3 has an aileron 31 on each side; when the electric vertical take-off and landing tilt-rotor aircraft is flying level, the fuselage 1, the front fixed wing 2, and the rear fixed wing 3 are the main components for generating lift.

4. The electric vertical take-off and landing tilt-rotor aircraft according to claim 1, characterized in that: The ducted coaxial twin-rotor tilt assembly 4 includes six groups of ducted coaxial twin-rotors 41 , three groups of the ducted coaxial twin-rotors 41 are built into the front fixed wing 2 ; and three groups of the ducted coaxial twin-rotors 41 are built into the rear fixed wing 3 .

5. The electric vertical take-off and landing tilt-rotor aircraft according to claim 4, characterized in that: The ducted coaxial twin rotor 41 includes a duct 411, an upper rotor 412, a lower rotor 413, a tilt axis 414, and a tilt drive device 415; the duct 411, the upper rotor 412, and the lower rotor 413 are fixed to the tilt axis 414; the tilt axis 414 is connected to the front fixed wing 2 or the rear fixed wing 3; the tilt axis 414 can rotate at an angle of -15 degrees to 90 degrees; the tilt of the ducted coaxial twin rotor is achieved by rotating the tilt axis 414; the tilt drive device 415 can be a worm gear structure.

6. The electric vertical take-off and landing tilt-rotor aircraft according to claim 4, characterized in that: When the electric vertical take-off and landing tilt-rotor aircraft is to achieve vertical take-off and landing, the duct axis of the ducted coaxial twin rotors 41 is deflected downward by 90 degrees (or similar to 90 degrees) and is at the 0 degree position; when the electric vertical take-off and landing tilt-rotor aircraft in the vertical take-off and landing state is to turn to level flight, it is only necessary to slowly deflect the duct axis of the ducted coaxial twin rotors 41 upward by 90 degrees (or similar to 90 degrees) and be at the 90 degree position; when the electric vertical take-off and landing tilt-rotor aircraft is in the level flight state, the thrust of the ducted coaxial twin rotors 41 is used to overcome the resistance encountered by the aircraft during flight; the electric vertical take-off and landing tilt-rotor aircraft can be controlled by controlling the six groups of the ducted coaxial twin rotors 41, the ailerons 21, and the ailerons 31 to achieve vertical take-off and landing, hovering, pitching up and down, rolling left and right, turning left and right, maintaining state, etc.

7. The electric vertical take-off and landing tilt-rotor aircraft according to claim 1, characterized in that: The aircraft landing support frame 5 is arranged at four corners below the bottom of the fuselage 1 .

8. The electric vertical take-off and landing tilt-rotor aircraft according to claim 1, characterized in that: The power battery 6 is located at the bottom of the fuselage 1; the power battery 6 is a power source that provides power for the aircraft.

9. The electric vertical take-off and landing tilt-rotor aircraft according to claim 1, characterized in that: The flight control system 7 is used to manipulate and control the aircraft; when there is no one pilot, the flight control system 7 controls take-off and landing, hovering, and level flight according to the route and the aircraft's own status; when there is someone piloting, the pilot does not directly control the aircraft, but the flight control system 7 controls take-off and landing, hovering, and level flight according to the pilot's intention and the aircraft's own status.

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