Electric vertical take-off and landing aircraft
By designing an electric vertical take-off and landing aircraft, using ducted coaxial dual rotors and built-in rotor lift components, combined with a simple and compact structure and flight control system, the problem of existing aircraft requiring special airports during take-off and landing is solved, low-cost, low-carbon emissions and vertical take-off and landing capabilities suitable for urban environments are achieved, and urban traffic congestion is alleviated.
Patent Information
- Application Number
- CN202510032945.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-01-09
- Publication Date
- 2025-03-14
- Estimated Expiration
- Not applicable · inactive patent
AI Technical Summary
Existing aircraft require special airports, runways and tarmacs during take-off and landing, resulting in high cost of use, large carbon emissions, and difficulty in taking off and landing in small urban spaces, which cannot effectively alleviate urban traffic congestion problems.
Design an electric vertical take-off and landing aircraft, adopting the lift components of six groups of ducted coaxial dual rotors, the rotor is built-in, independent power supply and control, and a redundant design; combining simple and compact structure and lightweight materials to reduce manufacturing difficulty and carbon emissions; using a flight control system to achieve complex flight control, supporting unmanned and manned driving.
Vertical take-off and landing is achieved without the need for special airports and runways, reducing the cost of use and carbon emissions; the structure is simple and light, reducing the difficulty of manufacturing and the safety risks of external personnel; the take-off and landing site requirements are low, suitable for use in narrow urban spaces, alleviating urban traffic congestion problems.
Smart Images
Figure CN119611751A_ABST
Abstract
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 aircraft. Background Art
[0002] Intelligent, automated, and electric vertical take-off and landing are the current trends, requiring aircraft to undergo changes.
[0003] The electric vertical take-off and landing aircraft involved in the present invention has at least the following beneficial technical effects: the electric vertical take-off and landing aircraft can take off and land vertically, does not require special airports, runways and aprons, and reduces the cost of use; it is electrically driven, which significantly reduces carbon emissions; it has a simple and compact structure and is light in weight, which reduces the difficulty of manufacturing; the rotor is built-in, which reduces the safety risk of external personnel; the take-off and landing site requirements are low, and the needs for take-off and landing in small spaces in the city can be met. Its 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 future urban air traffic (UAM, Urban Air Mobility) scenarios and is more in line with the future urban comprehensive three-dimensional transportation system. Summary of the invention
[0004] The purpose of the present invention is to provide an electric vertical take-off and landing aircraft that can take off and land vertically, does not require special airports, runways and aprons, and reduces the cost of use; is electrically driven, significantly reduces carbon emissions; has a simple and compact structure and is light in weight, reducing the difficulty of manufacturing; has built-in rotors, reducing the safety risk to external personnel; has low requirements for take-off and landing sites, and has a wide range of application scenarios.
[0005] The present invention provides the following technical solutions: An electric vertical take-off and landing aircraft comprises: a lift assembly 1, a cockpit 2, an aircraft landing support frame 3, a power battery 4, an aircraft outline light 5, and a flight control system 6.
[0006] Preferably, the lift assembly 1 includes six groups of ducted coaxial twin rotors 11, three groups of the ducted coaxial twin rotors 11 are arranged in a triangular manner at the front end of the aircraft; three groups of the ducted coaxial twin rotors 11 are arranged in a triangular manner at the rear end of the aircraft; 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; at the same time, the rotors are built-in to reduce the safety risks of external personnel.
[0007] Preferably, the main function of the cockpit 2 is to load equipment, passengers, cargo, etc., and the lift assembly 1, cockpit 2, aircraft landing support frame 3, power battery 4, aircraft outline light 5, flight control system 6 and other components are connected into a whole; the structure is simple, compact and light.
[0008] Preferably, the cockpit 2 includes a cabin cover 21, a seat 22, a control panel 23, a roll cage 24, an emergency parachute device 25, and a step pedal 26; the roll cage 24 is arranged at the rear of the seat 22; the emergency parachute device 25 is located at the rear of the cabin cover 2; the step pedal 26 is located on both sides of the cabin cover 2 for passengers to get on and off the aircraft.
[0009] Preferably, the aircraft landing support frame 3 is arranged at the four corners of the aircraft, namely, at both sides of a single set of the ducted coaxial twin rotors 11 .
[0010] Preferably, the power battery 4 is disposed at the bottom of the cabin 2; the power battery 4 is a power source that provides power for the aircraft.
[0011] Preferably, the aircraft contour lights 5 are arranged at the edge of the aircraft contour; the function of the aircraft contour lights 5 is to light up before takeoff to remind outsiders to pay attention to safety and keep a distance from the aircraft, thereby improving the safety of outsiders.
[0012] Preferably, the flight control system 6 is used to manipulate and control the aircraft; when there is no one piloting, the flight control system 6 controls take-off, landing, hovering, and flying according to the route and the aircraft's own state; when there is someone piloting, the pilot does not directly control the aircraft, but the flight control system 6 controls take-off, landing, hovering, and flying according to the pilot's intention and the aircraft's own state. Since the control requirements of electric vertical take-off and landing aircraft are complex and precise, computer-aided control systems are often used; this is conducive to unmanned driving, and relevant personnel do not need to obtain a flight license, reducing the cost of use; when there is someone piloting, the pilot informs the flight control system of the driving intention through the control panel, and the flight control system combines its own state to calculate the corresponding execution control signal to improve flight control safety. BRIEF DESCRIPTION OF THE DRAWINGS
[0013] Figure 1 It is a schematic diagram of the three-dimensional structure of the vertical take-off and landing aircraft of the present invention; Figure 2 It is a schematic diagram of the structure of the vertical take-off and landing aircraft of the present invention from a top view; Explanation of the reference numerals: 1. lift assembly; 11. ducted coaxial twin rotors; 2. cockpit; 21. canopy; 22. seat; 23. control panel; 24. roll cage; 25. emergency parachute device; 26. step pedal; 3. aircraft landing support frame; 4. power battery; 5. aircraft outline lights; 6. flight control system. DETAILED DESCRIPTION
[0014] 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
[0015] like Figure 1-Figure 2 As shown, this embodiment discloses a vertical take-off and landing aircraft, including: a lift assembly 1, a cockpit 2, an aircraft landing support frame 3, a power battery 4, an aircraft outline light 5, and a flight control system 6.
[0016] In this embodiment, the lift assembly 1 includes six groups of ducted coaxial twin rotors 11, three groups of ducted coaxial twin rotors 11 are arranged in a triangular manner at the front end of the aircraft; three groups of ducted coaxial twin rotors 11 are arranged in a triangular manner at the rear end of the aircraft; the upper and lower rotors are fixed to the crossbeam or longitudinal beam of the fuselage; 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; at the same time, the rotors are built-in to reduce the safety risks of external personnel.
[0017] In this embodiment, the main function of the cockpit 2 is to load equipment, passengers, cargo, etc., and the lift assembly 1, cockpit 2, aircraft landing support frame 3, power battery 4, aircraft outline lights 5, flight control system 6 and other components are connected into a whole.
[0018] In this embodiment, the cockpit 2 includes a cabin cover 21, a seat 22, a control panel 23, a roll cage 24, an emergency parachute device 25, and step pedals 26; the roll cage 24 is arranged behind the seat 22; the emergency parachute device 25 is located at the rear of the cabin cover 2; the step pedals 26 are located on both sides of the cabin cover 2 for passengers to get on and off the aircraft.
[0019] In this embodiment, the aircraft landing support frames 3 are arranged at the four corners of the aircraft, namely, at both sides of the single set of ducted coaxial twin rotors 11 .
[0020] In this embodiment, the power battery 4 is disposed at the bottom of the cockpit 2; the power battery 4 is a power source that provides power for the aircraft.
[0021] In this embodiment, the aircraft contour light 5 is arranged at the edge of the aircraft contour; the function of the aircraft contour light 5 is to light up before takeoff to remind outsiders to pay attention to safety and keep a distance from the aircraft, thereby improving the safety of outsiders.
[0022] In this embodiment, the flight control system 6 is used to manipulate and control the aircraft; when there is no one piloting, the flight control system 6 controls take-off, landing, hovering, and flying according to the route and the aircraft's own state; when there is someone piloting, the pilot does not directly control the aircraft, but the flight control system 6 controls take-off, landing, hovering, and flying according to the pilot's intention and the aircraft's own state. Since the control requirements of electric vertical take-off and landing aircraft are complex and precise, computer-aided control systems are often used; this is conducive to unmanned driving, and relevant personnel do not need to obtain a flight license, reducing the cost of use; when there is someone piloting, the pilot informs the flight control system of the driving intention through the control panel, and the flight control system combines its own state to calculate the corresponding execution control signal to improve flight control safety.
[0023] In this embodiment, the electric vertical take-off and landing aircraft has a simple and compact structure, is light in weight, occupies a small area, can take off and land vertically, does not require a dedicated airport, runway or apron, has low requirements for take-off and landing sites, and has a wide range of application scenarios.
[0024] In this embodiment, the rotor of the electric vertical take-off and landing aircraft is built-in to reduce the safety risk of external personnel; a redundant design is adopted to improve the take-off and landing flight safety; and a flight control system is adopted to improve flight control safety.
[0025] The words "arrange", "set", "connect" 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 aircraft, characterized in that: The electric vertical take-off and landing aircraft includes a lift assembly 1, a cockpit 2, an aircraft landing support frame 3, a power battery 4, an aircraft outline light 5, and a flight control system 6.
2. The electric vertical flight vehicle according to claim 1, characterized in that: The lift assembly 1 includes six groups of ducted coaxial twin rotors 11, three groups of the ducted coaxial twin rotors 11 are arranged in a triangular manner at the front end of the aircraft; and three groups of the ducted coaxial twin rotors 11 are arranged in a triangular manner at the rear end of the aircraft.
3. The electric vertical flight vehicle according to claim 1, characterized in that: The main function of the cockpit 2 is to load equipment, passengers, cargo, etc., and connect the lift assembly 1, cockpit 2, aircraft landing support frame 3, power battery 4, aircraft outline light 5, flight control system 6 and other components into a whole.
4. The electric vertical flight vehicle according to claim 1, characterized in that: The cockpit 2 includes a cabin cover 21, a seat 22, a control panel 23, a roll cage 24, an emergency parachute device 25, and a step pedal 26; the roll cage 24 is arranged at the rear of the seat 22; the emergency parachute device 25 is located at the rear of the cabin cover 2; the step pedal 26 is located on both sides of the cabin cover 2 for passengers to get on and off the aircraft.
5. The electric vertical flight vehicle according to claim 1, characterized in that: The aircraft landing support frame 3 is arranged at the four corners of the aircraft, namely, at both sides of a single set of the ducted coaxial twin rotors 11 .
6. The electric vertical flight vehicle according to claim 1, characterized in that: The power battery 4 is disposed at the bottom of the cockpit 2 ; the power battery 4 is a power source that provides power for the aircraft.
7. The electric vertical flight vehicle according to claim 1, characterized in that: The aircraft outline light 5 is arranged at the edge of the aircraft outline; the function of the aircraft outline light 5 is to light up before take-off to remind external personnel to pay attention to safety and keep a distance from the aircraft.
8. The electric vertical flight vehicle according to claim 1, characterized in that: The flight control system 6 is used to manipulate and control the aircraft; when there is no one piloting the aircraft, the flight control system 6 controls take-off and landing, hovering, and flying according to the route and the aircraft's own state; when there is someone piloting the aircraft, the pilot does not directly control the aircraft, but the flight control system 6 controls take-off and landing, hovering, and flying according to the pilot's intention and the aircraft's own state.