WO2019211875A1 - Hybrid vertical takeoff and landing (vtol) aircraft with vehicle assist - Google Patents
Hybrid vertical takeoff and landing (vtol) aircraft with vehicle assist Download PDFInfo
- Publication number
- WO2019211875A1 WO2019211875A1 PCT/IN2019/050354 IN2019050354W WO2019211875A1 WO 2019211875 A1 WO2019211875 A1 WO 2019211875A1 IN 2019050354 W IN2019050354 W IN 2019050354W WO 2019211875 A1 WO2019211875 A1 WO 2019211875A1
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- Prior art keywords
- aircraft
- flight
- rotors
- vertical take
- landing
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
- B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
- B64C29/0033—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being tiltable relative to the fuselage
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/06—Aircraft not otherwise provided for having disc- or ring-shaped wings
- B64C39/068—Aircraft not otherwise provided for having disc- or ring-shaped wings having multiple wings joined at the tips
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Launching or towing gear
- B64F1/10—Launching or towing gear using self-propelled vehicles
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/80—Energy efficient operational measures, e.g. ground operations or mission management
Definitions
- the present disclosure relates generally to a vertical take-off and landing (VTOL) aircraft using a hybrid-electric propulsion system.
- the present invention is particularly related to a hybrid VTOL aircraft with a combination of vertical rotors and tilt rotors enabling hovering and horizontal flight.
- Aircrafts having vertical or steep take-off and landing capabilities are well known in the art.
- Some of the common types of VTOL aircrafts are Helicopters (rotary wing aircraft), wing tip mounted Tilt rotor aircrafts, thrust vector VTOL airplanes, Tilt wing aircrafts, and multicopter type of aircrafts with fixed vertical lift-off rotors or ducted fans.
- Helicopters usually comprise a large rotor system which is complex involving several mechanical parts for transmission or gearbox. The same rotor blade of the helicopter needs to perform dual function of vertical flight and forward flight. To fly the helicopter the pilot needs to use collective and cyclic control which incorporates complex mechanical systems and requires heavy maintenance. These complex mechanical parts have single points of failure and hence lack redundancy and are less efficient compared to fixed wing airplanes. Further, helicopters are extremely noisy and are less fuel efficient.
- the wing tip mounted tilt rotor VTOL aircrafts combine the efficiency of fixed wing airplane and helicopter.
- the wingtip mounted turbo shaft engines are connected via a common central gearbox so that a single engine powers both rotors in case of an engine failure. This leads to a complex mechanical system design.
- the tilt mechanism of the wing tip mounted engines leads to increased complexity and maintenance.
- tilt rotor VTOL aircrafts are less energy efficient compared to their equivalent fixed wing counterparts.
- Tilt wing VTOL aircrafts have engines mounted on the wing instead of the wing tip. These aircrafts still possess greater design complexity of the wing tilting mechanism due to heavy engines and hence are less energy efficient. Additionally, these aircrafts comprise several single points of failure when compared to a fixed wing airplane.
- Multicopter types of aircrafts have multiple redundancies when compared to the above discussed aircrafts.
- US patent application, US20140151495 discloses an electrically powered vertical takeoff and landing aircraft with one or more rotors. However, the rotors are used for only hovering effect. The prior arts does not teach a combination of vertical rotors and tilt rotors.
- a hybrid vertical take-off and landing aircraft comprising an engine configured to operate on an electric mode and a mechanical mode.
- the engine includes a pair of wings attached to a body of the aircraft to form a box wing architecture that provides improved aerodynamic efficiency, where the wings comprise an anterior portion attached to a nose of the aircraft body and a posterior portion attached to a tail of the aircraft body.
- the aircraft includes a rotor system with a plurality of vertical rotors and a pair of tilting rotors.
- the plurality of vertical rotors is attached to the pair of wings to provide upward thrust.
- the pair of tilting rotors are attached to the posterior portion of the wings to provide forward thrust for horizontal flight.
- the aircraft includes a flight system computer that is coupled to the engine and adapted to control the power supplied to the plurality of vertical rotors and the pair of tilting rotors during vertical take-off and horizontal flight, the flight system computer is also configured to select operation of the engine in at least one of electric mode, mechanical mode or a combination thereof.
- FIG. 1 illustrates a perspective view of the main aircraft vehicle in vertical flight configuration, according to an embodiment of the present invention.
- FIG. 2 illustrates aperspective side view of the main aircraft vehicle in vertical flight configuration, according to an embodiment of the present invention.
- FIG. 3 illustrates aperspective top view of the aircraft in the vertical fight configuration, according to an embodiment of the present invention.
- FIG. 4 illustrates aperspective front view of the aircraft in the vertical flight configuration, according to an embodiment of the present invention.
- FIG. 5 illustrates a perspective view of the main aircraft vehicle showing the tilting rotors, according to an embodiment herein.
- FIG. 7 illustrates a perspective view of the main aircraft vehicle in the horizontal flight configuration with the landing gears retracted, according to an embodiment herein.
- FIG. 8 illustrates a perspective side view of the main aircraft vehicle in the horizontal flight configuration with the landing gear retracted, according to an embodiment herein.
- FIG. 9 illustrates a schematic diagram depicting a process of aircraft taking-off vertically from the ground and transitioning to forward flight, according to an embodiment herein.
- FIG. 10 illustrates a perspective view of a multicopter VTOF assist vehicle, according to an embodiment herein.
- FIG. 11 illustrates a perspective side view of the multicopter VTOF assist vehicle, according to an embodiment herein.
- FIG. 12 illustrates a perspective top view of the multicopter VTOL assist vehicle, according to an embodiment herein.
- FIG. 13 illustrates a perspective view of the main aircraft vehicle mounted to the multicopter VTOL assist vehicle, according to an embodiment herein.
- the various embodiments of the present invention provide an energy efficient VTOL aircraft capable of flying like helicopter as well as fixed wing airplane based on requirement.
- the propulsion for the aircraft is either all electric or hybrid/electric.
- the aircraft is safe, reliable, redundant and quiet in operation. Electric propulsion allows the aircraft to have less number of complex mechanical systems and least possible maintenance.
- Each rotor system comprises a compact high power to weight ratio electric motor and an optimized propeller either for cruise or hover depending upon the function.
- the usage of electric motors for propulsion reduces the noise significantly as compared with traditional aircraft engines and is less complex to design and manufacture.
- the aircraft also covers a fully autonomous VTOL assist vehicle capable of assisting the main aircraft vehicle in vertical take-off and hence reducing the energy consumption for the main aircraft vehicle during vertical take-off, landing and hover.
- the autonomous vehicle is configured for detaching itself from the main vehicle once the main vehicle transition to forward flight to operate like a fixed wing airplane.
- the VTOL landing aircraft comprises one or more fixed vertical rotors and wing mounted tilting rotors for forward flight with a smooth and quiet operation.
- the one or more fixed vertical rotors are mounted on the wing using a mount.
- the one or more tilting rotors are mounted onto the rear wing with a mount.
- the rotor system comprises an electric motor and an optimized propeller for the specific operation.
- the tilting rotors tilt to an angle until the aircraft/airplane achieves a certain forward speed at which the aircraft wings produce enough lift to keep the aircraft airborne during the forward flight. Once sufficient forward speed is achieved and the aircraft starts to cruise then the vertical thrust rotors switch off and the forward flight is powered by the tilting rotors which tilt horizontally.
- FIG. 1 illustrates a perspective view of the main aircraft vehicle in vertical flight configuration, according to an embodiment of the present invention.
- the aircraft is shown in the vertical flight configuration.
- the aircraft comprises the fuselage 102; the forward wing 104 and the rear wing 106, the set of fixed vertical rotors l08-a to l08-j and the set of tilting rotors 110 for forward flight.
- Fuselage l02 comprises the cockpit area 112; the nose landing gear 114; the set of main landing gears 202withthe wings 104 and 106 attached.
- the aircraft further comprises one or more batteries, avionics and flight control computers (not shown).
- the aircraft is configured for carrying a plurality of passenger’s/payload cabin in the fuselage 102.
- the wings 104 and l06 comprise one or more batteries and controllers for the electric motors.
- the set of fixed vertical rotors l08-a to l08-j are mounted onto the wings 104 and 106 using the mount 118.
- the tilting rotors 110 are mounted onto the rear wing l06using another mount 116.
- the rotor systems l08-a to l08-j and 110 comprise an electric motor and an optimized propeller (not shown) for the specific operation.
- vertical thrust for the aircraft is provided by the set of fixed rotors l08-a to l08-j either in planar or non-planar orientations.
- Forward thrust is provided by the set of tilting rotors 110 which comprises tilting actuators (not shown) to tilt the rotors from vertical position to horizontal position during forward flight.
- the non-planar orientation of the vertical set of rotors l08-a to l08-j also provide lateral and directional control adjustments during the VTOL mode.
- the set of tilting rotors 110 are also configured for assisting in the vertical take-off and landing or hover flight phases.
- the tilting rotors 110 are also operational during the vertical take-off and landing mode and hence contribute to the component of vertical thrust.
- FIG. 2 illustrates a perspective side view of the main aircraft vehicle in vertical flight configuration, according to an embodiment of the present invention.
- main aircraft such as the fuselage 102, vertical rotors 108, tilting rotors 110, main landing gear 116, secondary landing gear 202 are shown.
- the aircraft has 10 or more number of rotors for the VTOL operations. This enables higher redundancy in case of one or two motor failures.
- the motor power and thrust is sized such a way that in the event of even three VTOL motors failed and other motors will be able to safely land the airplane back
- FIG. 3 illustrates a perspective top view of the aircraft in the vertical fight configuration, according to an embodiment of the present invention.
- all the vertical rotors l08-a to l08-j are shown which extends on the pair of wings.
- the pair of wings form a box wing architecture that provides improved aerodynamic efficiency.
- the box wing architecture also provides structural rigidity and reduction in structural weight over the conventional aircraft layout.
- FIG. 5 illustrates a perspective view of the main aircraft vehicle showing the tilting rotors, according to an embodiment herein.
- FIG. 5 illustrates the tilting rotors 110 attached using a mount to the rear end.
- FIG. 6 illustrates a perspective view of the main aircraft vehicle with tilting rotors tilted horizontally for the horizontal fight configuration, according to an embodiment herein.
- FIG. 7 illustrates a perspective view of the main aircraft vehicle in the horizontal flight configuration with the landing gears retracted, according to an embodiment herein.
- the landing gears 116 in retracted position is shown.
- FIG. 8 illustrates a perspective side view of the main aircraft vehicle in the horizontal flight configuration with the landing gear retracted, according to an embodiment herein. With respect to FIG. 8, the side view of the main aircraft moving in forward flight axis is shown.
- FIG. 9 illustrates a schematic diagram depicting a process of aircraft taking -off vertically from the ground and transitioning to forward flight, according to an embodiment herein.
- the tilting set of rotors tilt to an angle until the airplane achieves a certain forward speed at which the aircraft wings produce enough lift to keep the aircraft airborne during the forward flight.
- the vertical thrust rotors 108 switch off and the forward flight is powered by the tilting rotors 110 which tilt horizontally.
- the various positions of the main aircraft in the take-off process are depicted using reference numerals 902 to 910.
- robust and redundant flight control systems are used to achieve the flight during VTOL and fixed wing mode of flights.
- three independent flight control computers (not shown) are used for redundancy and an independent backup flight control computer is used which takes over with limited protections to safely land the aircraft in case the three independent flight control computers fail.
- the onboard flight control computers also let the airplane perform VTOL to transition automatically without much pilot inputs and efforts.
- FIG. 10 illustrates a perspective view of a fully autonomous multicopter VTOL assist vehicle, according to an embodiment herein.
- the multicopter vehicle includes a fuselage 1002; a set of ducted propeller systems 1006.
- the fuselage 1002 also comprises flight control computer, batteries, onboard sensing unit and navigation systems (not shown) and the main aircraft landing gear securing points 1004.
- the ducted fan or propeller system 1006 further comprises an electric motor and controllers in a housing 1106; a set of high lift propellers 1102 and guide vanes 1104 (as shown in FIG. 11).
- FIG. 12 illustrates a perspective top view of the multicopter VTOL assist vehicle, according to an embodiment herein.
- FIG. 16A illustrates a block diagram of a flight controller system in the aircraft.
- the flight controller system comprises a battery unit 162, an invertor 164, a flight control computer 166, a generator 168, and a rotor system.
- the flight controller system provides flexibility in the number and position of electric rotors.
- the flight controller system can drive a plurality of rotor system 1 to N in a distributed configuration.
- the battery 162 is a rechargeable and replaceable battery that can easily be swapped at heliports.
- the battery 162 reduces noise during take-off and hover and enables the aircraft to operate in silent mode.
- the controller 166 can select the operation of the aircraft in electric mode, mechanical mode or a combination of both.
- a hybrid vertical take-off and landing aircraft comprising an engine configured to operate on an electric mode and a mechanical mode.
- the engine includes a pair of wings attached to a body of the aircraft to form a box wing architecture that provides improved aerodynamic efficiency, where the wings comprise an anterior portion attached to a nose of the aircraft body and a posterior portion attached to a tail of the aircraft body.
- the aircraft includes a rotor system with a plurality of vertical rotors and a pair of tilting rotors.
- the plurality of vertical rotors is attached to the pair of wings to provide upward thrust.
- the pair of tilting rotors are attached to the posterior portion of the wings to provide forward thrust for horizontal flight.
- the flight controller system is coupled to a sensor unit that monitor the parameters and performance of the aircraft and transmit feedback signals to the flight controller system.
- the feedback signals determine the action of the flight controller system in case of an autonomous mode or manual mode.
- the components of the sensor unit is shown in FIG. 16B.
- the sensor unit includes a motion sensor, control surface actuator feedback sensors, rotor system sensor and battery management sensors.
- the flight system computer is driven by flight envelope and flight control law in an autonomous mode.
- the flight envelope limits the airplane from high speed, tilt and turn.
- the Flight control law is maintained by measuring the feedback from the sensor unit to generate an output , and further applying the output to drive the aircraft
- the motion sensors include gravity sensor, linear acceleration sensor, a rotation vector sensor.
- the sensor unit may include a gyroscope.
- the motion sensors also monitor the aircraft speed and accelerations, pitch, roll, yaw & angular rates.
- the rotor system sensors provide rotation per minute (rpm, direction, angle, and power.
- the control surface actuator feedback sensors provide information about the angle of the aircraft, force, and linear travel distance.
- the battery management sensors provide information about the voltage, current, temperature, humidity, and battery charging status.
- vertical set of fixed rotors are used in the aircraft for performing hover, vertical take-off and landing.
- a set of tilting vertical rotors is used for forward flight.
- the aircraft has robust flight control architecture for a safe and reliable flight. Multiple flight control computers are used for redundancy.
- the electric propulsion brings down the operational cost of the vehicle. The cost of operation for the aircraft is approximately 6 times lesser than the fuel based aerial vehicles.
- the vertical take-off and landing allows the airplane to take-off and land from small spaces such as top of a building, helipads etc. No new infrastructure is needed for the operations. Adding the capability of fixed wing airplane makes it cruise efficiently for longer distances and flight time as compared to helicopters available in recent times.
- the maintenance cost of the aircraft is low as the numbers of parts are less when compared to other available helicopters and airplanes.
- the engine architecture is less complex.
- the aircraft is suitable for use in commercial applications such as Urban Air taxi services, Intercity charter services, personal transportation aircraft, Cargo transportation, Flying school training aircraft, Surveillance aircraft, Unmanned Aerial systems, ferry services, Air ambulance systems etc.
- This present invention facilitates people around the world to commute faster than a car from one location to another at the similar cost of a taxi bypassing all the traffic on the ground.
- the cost of operation is less since the airplane operates on electricity as compared to aircraft fuel.
Abstract
Description
Claims
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IN201841016973 | 2018-05-04 | ||
IN201841016973 | 2018-05-04 |
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Cited By (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20200407060A1 (en) * | 2019-05-29 | 2020-12-31 | Craft Aerospace Technologies, Inc. | Novel aircraft design using tandem wings and a distributed propulsion system |
GB2585864A (en) * | 2019-07-18 | 2021-01-27 | Gkn Aerospace Services Ltd | An aircraft |
US10981650B2 (en) * | 2019-02-27 | 2021-04-20 | Airbus Helicopters Deutschland GmbH | Multirotor joined-wing aircraft with VTOL capabilities |
EP3868660A1 (en) * | 2020-02-18 | 2021-08-25 | Aurora Flight Sciences Corporation, a subsidiary of The Boeing Company | Vertical take-off and landing (vtol) aircraft and related methods |
CN114180049A (en) * | 2021-10-22 | 2022-03-15 | 上海新云彩航空科技有限责任公司 | Box-shaped composite wing aircraft |
USD945947S1 (en) | 2020-02-24 | 2022-03-15 | Aurora Flight Sciences Corporation | Aircraft |
US20220212775A1 (en) * | 2021-01-04 | 2022-07-07 | Aurora Flight Sciences Corporation, a subsidiary of The Boeing Company | Aircraft and related methods |
EP4043344A1 (en) * | 2021-02-11 | 2022-08-17 | Bell Textron Inc. | Configurable electrical architectures for evtol aircraft |
US11465529B1 (en) | 2021-06-29 | 2022-10-11 | Beta Air, Llc | Methods and systems for optimizing battery recharge management for use with an electric vertical take-off and landing aircraft |
US11472546B2 (en) | 2020-02-24 | 2022-10-18 | Aurora Flight Sciences Corporation | Fixed-wing short-takeoff-and-landing aircraft and related methods |
WO2023038684A1 (en) * | 2021-09-08 | 2023-03-16 | General Atomics | Autonomous flight safety system |
US11634232B1 (en) | 2022-04-30 | 2023-04-25 | Beta Air, Llc | Hybrid propulsion systems for an electric aircraft |
US11639230B1 (en) | 2022-04-30 | 2023-05-02 | Beta Air, Llc | System for an integral hybrid electric aircraft |
FR3129920A1 (en) * | 2021-12-03 | 2023-06-09 | Safran | AIRCRAFT COMPRISING A FUSELAGE AND A FIXED WING |
US11749122B1 (en) * | 2019-12-12 | 2023-09-05 | Amazon Technologies, Inc. | Multi-device redundant flight controller |
EP4097004A4 (en) * | 2020-01-31 | 2023-12-20 | Wisk Aero LLC | Aircraft with tilting fan assemblies |
USD1009696S1 (en) | 2020-02-18 | 2024-01-02 | Aurora Flight Sciences Corporation, a subsidiary of The Boeing Company | Aircraft |
WO2024054195A1 (en) * | 2022-09-06 | 2024-03-14 | levhen Oleksandrovych KONONYKHIN | Closed-wing vertical take-off and landing aircraft |
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Cited By (23)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10981650B2 (en) * | 2019-02-27 | 2021-04-20 | Airbus Helicopters Deutschland GmbH | Multirotor joined-wing aircraft with VTOL capabilities |
US20200407060A1 (en) * | 2019-05-29 | 2020-12-31 | Craft Aerospace Technologies, Inc. | Novel aircraft design using tandem wings and a distributed propulsion system |
GB2585864A (en) * | 2019-07-18 | 2021-01-27 | Gkn Aerospace Services Ltd | An aircraft |
GB2585864B (en) * | 2019-07-18 | 2022-04-27 | Gkn Aerospace Services Ltd | An aircraft |
US11749122B1 (en) * | 2019-12-12 | 2023-09-05 | Amazon Technologies, Inc. | Multi-device redundant flight controller |
EP4097004A4 (en) * | 2020-01-31 | 2023-12-20 | Wisk Aero LLC | Aircraft with tilting fan assemblies |
EP3868660A1 (en) * | 2020-02-18 | 2021-08-25 | Aurora Flight Sciences Corporation, a subsidiary of The Boeing Company | Vertical take-off and landing (vtol) aircraft and related methods |
USD1009696S1 (en) | 2020-02-18 | 2024-01-02 | Aurora Flight Sciences Corporation, a subsidiary of The Boeing Company | Aircraft |
US11554865B2 (en) | 2020-02-18 | 2023-01-17 | Aurora Flight Sciences Corporation | Vertical take-off and landing (VTOL) aircraft and related methods |
US11472546B2 (en) | 2020-02-24 | 2022-10-18 | Aurora Flight Sciences Corporation | Fixed-wing short-takeoff-and-landing aircraft and related methods |
USD945947S1 (en) | 2020-02-24 | 2022-03-15 | Aurora Flight Sciences Corporation | Aircraft |
US20220212775A1 (en) * | 2021-01-04 | 2022-07-07 | Aurora Flight Sciences Corporation, a subsidiary of The Boeing Company | Aircraft and related methods |
US11772773B2 (en) | 2021-01-04 | 2023-10-03 | Aurora Flight Sciences Corporation, a subsidiary of The Boeing Company | Aircraft and related methods |
US11772805B2 (en) | 2021-02-11 | 2023-10-03 | Textron Innovations Inc. | Configurable electrical architectures for eVTOL aircraft |
EP4043344A1 (en) * | 2021-02-11 | 2022-08-17 | Bell Textron Inc. | Configurable electrical architectures for evtol aircraft |
US11465529B1 (en) | 2021-06-29 | 2022-10-11 | Beta Air, Llc | Methods and systems for optimizing battery recharge management for use with an electric vertical take-off and landing aircraft |
WO2023038684A1 (en) * | 2021-09-08 | 2023-03-16 | General Atomics | Autonomous flight safety system |
CN114180049A (en) * | 2021-10-22 | 2022-03-15 | 上海新云彩航空科技有限责任公司 | Box-shaped composite wing aircraft |
CN114180049B (en) * | 2021-10-22 | 2024-02-02 | 上海新云彩航空科技有限责任公司 | Box type composite wing aircraft |
FR3129920A1 (en) * | 2021-12-03 | 2023-06-09 | Safran | AIRCRAFT COMPRISING A FUSELAGE AND A FIXED WING |
US11634232B1 (en) | 2022-04-30 | 2023-04-25 | Beta Air, Llc | Hybrid propulsion systems for an electric aircraft |
US11639230B1 (en) | 2022-04-30 | 2023-05-02 | Beta Air, Llc | System for an integral hybrid electric aircraft |
WO2024054195A1 (en) * | 2022-09-06 | 2024-03-14 | levhen Oleksandrovych KONONYKHIN | Closed-wing vertical take-off and landing aircraft |
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