WO2018075412A1 - Multicopter with angled rotors - Google Patents

Multicopter with angled rotors Download PDF

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Publication number
WO2018075412A1
WO2018075412A1 PCT/US2017/056817 US2017056817W WO2018075412A1 WO 2018075412 A1 WO2018075412 A1 WO 2018075412A1 US 2017056817 W US2017056817 W US 2017056817W WO 2018075412 A1 WO2018075412 A1 WO 2018075412A1
Authority
WO
WIPO (PCT)
Prior art keywords
aircraft
rotors
subset
fuselage
lift
Prior art date
Application number
PCT/US2017/056817
Other languages
French (fr)
Inventor
James Joseph TIGHE
Eric Allison
Original Assignee
Kitty Hawk Corporation
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Kitty Hawk Corporation filed Critical Kitty Hawk Corporation
Priority to EP23216810.4A priority Critical patent/EP4318167A3/en
Priority to CN202210735081.4A priority patent/CN114872890A/en
Priority to AU2017346502A priority patent/AU2017346502B2/en
Priority to EP17862880.6A priority patent/EP3529149B1/en
Priority to CN201780063710.0A priority patent/CN109843715B/en
Priority to NZ752614A priority patent/NZ752614A/en
Publication of WO2018075412A1 publication Critical patent/WO2018075412A1/en
Priority to AU2021202178A priority patent/AU2021202178B2/en
Priority to AU2023226684A priority patent/AU2023226684A1/en

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Classifications

    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
    • G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
    • G05D1/08—Control of attitude, i.e. control of roll, pitch, or yaw
    • G05D1/0808—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft
    • G05D1/0858—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft specially adapted for vertical take-off of aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/08—Helicopters with two or more rotors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
    • B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/52—Tilting of rotor bodily relative to fuselage
    • 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
    • B64C29/0025—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 fixed relative to the fuselage
    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
    • G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
    • G05D1/60—Intended control result
    • G05D1/652—Take-off
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force

Definitions

  • Multicopter aircraft typically include a plurality of horizontally oriented rotors, sometimes referred to as “lift fans,” to provide lift, stability, and control.
  • a flight control system sometimes referred to as a “flight controller” or “flight computer” may be provided to translate pilot or other operator input, and/or corrections computed by an onboard computer, e.g., based on sensor data, into forces and moments and/or to further translate such forces and moments into a set of actuator (e.g., lift rotors; propellers; control surfaces, such as ailerons; etc.) and/or associated parameters (e.g., lift fan power, speed, or torque) to provide the required forces and moments.
  • actuator e.g., lift rotors; propellers; control surfaces, such as ailerons; etc.
  • associated parameters e.g., lift fan power, speed, or torque
  • pilot or other operator inputs may indicate a desired change in the aircraft's speed, direction, and/or orientation, and/or wind or other forces may act on the aircraft, requiring the lift fans and/or other actuators to be used to maintain a desired aircraft attitude (roll/pitch/yaw), speed, and/or altitude.
  • An aircraft typically is considered to have six degrees of freedom of movement, including forces in the forward/back, side/side, and up/down directions (e.g., Fx, Fy, and Fz) and moments about the longitudinal (roll) axis, the transverse (pitch) axis, and the vertical (yaw) axis (e.g., Mx, My, and Mz).
  • degrees of freedom of movement including forces in the forward/back, side/side, and up/down directions (e.g., Fx, Fy, and Fz) and moments about the longitudinal (roll) axis, the transverse (pitch) axis, and the vertical (yaw) axis (e.g., Mx, My, and Mz).
  • Rotors may spin at a high rate and could pose a risk to an occupant of a manned multicopter and/or to equipment housed in a fuselage or other structure comprising the multicopter.
  • Figure 1 is a block diagram illustrating an embodiment of a flight control system.
  • Figure 2A is a block diagram illustrating an embodiment of a multicopter aircraft with angled rotors.
  • Figure 2B is a block diagram showing a front view of the multicopter aircraft
  • Figure 2C is a block diagram illustrating an example of angled rotors as implemented in an embodiment of a multicopter aircraft with angled rotors.
  • Figure 2D is a block diagram illustrating a top view of an embodiment of a multicopter aircraft with angled rotors.
  • Figure 2E is a block diagram illustrating an example of forces and moments capable of being generated by angled rotors in an embodiment of a multicopter aircraft with angled rotors.
  • Figure 2F is a block diagram showing a side view of the multicopter aircraft
  • Figure 2G is a block diagram showing a side view of the multicopter aircraft
  • the invention can be implemented in numerous ways, including as a process; an apparatus; a system; a composition of matter; a computer program product embodied on a computer readable storage medium; and/or a processor, such as a processor configured to execute instructions stored on and/or provided by a memory coupled to the processor.
  • these implementations, or any other form that the invention may take, may be referred to as techniques.
  • the order of the steps of disclosed processes may be altered within the scope of the invention.
  • a component such as a processor or a memory described as being configured to perform a task may be implemented as a general component that is temporarily configured to perform the task at a given time or a specific component that is manufactured to perform the task.
  • the term 'processor' refers to one or more devices, circuits, and/or processing cores configured to process data, such as computer program instructions.
  • a multicopter aircraft with angled rotors is disclosed.
  • a multicopter aircraft as disclosed herein includes a plurality of lift fans or other rotors disposed in a configuration around a fuselage and/or other centrally-located structure of the aircraft.
  • a first subset of the rotors may be disposed on a one side of the aircraft and a second subset of the rotors may be disposed on an opposite side of the aircraft.
  • each of at least a subset of the rotors is mounted at a corresponding non-zero angle off of a horizontal plane of the aircraft.
  • the angle at which each rotor is mounted is determined at least in part by a location of the rotor relative to the fuselage and/or a human or other occupied portion thereof, the angle being determined at least in part to ensure that a plane in which the rotor primarily rotates does not intersect the fuselage and/or a human or other occupied portion thereof.
  • the respective angles at which at least a subset of the rotors are mounted may be determined at least in part to provide the ability to generate lateral force components in the horizontal plane of the aircraft at rotor mount locations that are offset in the horizontal plane from a center of gravity of the aircraft , so as to provide an ability to use the rotors to control yaw of the aircraft (i.e., rotation about a vertical axis of the aircraft) by applying moments about the vertical axis.
  • FIG. 1 is a block diagram illustrating an embodiment of a flight control system.
  • flight control system 100 includes a source of flight control inputs 102 configured to provide flight control inputs 104 to a controller 106, e.g., a flight control computer.
  • source of inputs 102 may comprises one or both of pilot input, e.g., via manual flight controls, and auto-pilot or other self-piloting technologies.
  • pilot inputs 104 may be generated by a self-piloting program/computer 102.
  • source of inputs 102 may include manual input devices (sometimes referred to as "inceptors"), such as stick, throttle, rudder, collective, joystick, thumb stick, and/or other manual control/input devices configured to be manipulated by a pilot or other operator to control the flight of an aircraft.
  • inceptors such as stick, throttle, rudder, collective, joystick, thumb stick, and/or other manual control/input devices configured to be manipulated by a pilot or other operator to control the flight of an aircraft.
  • Such inceptor devices and/or associated electronics, and/or a self-piloting program, computer, or module may be configured to provide as input signals 104 one or more of a roll direction, roll rate, yaw direction, yaw rate, pitch angle, pitch rate, altitude, altitude rate and/or forward or other thrust input signal.
  • controller 106 also receives sensor data 118, e.g., wind speed, air temperature, etc., from sensors 116.
  • Flight controller 106 translates, aggregates, and/or otherwise processes and/or interprets the received flight control inputs 104 and/or sensor data 118 to generate and provide as output associated forces and/or moments 108 to be applied to the aircraft via its control assets (e.g., propellers, rotors, lift fans, aerodynamic control surfaces, etc.; sometimes referred to herein as "actuators”) to maneuver the aircraft in a manner determined based at least in part on the flight control inputs 104 and/or sensor data 118.
  • control assets e.g., propellers, rotors, lift fans, aerodynamic control surfaces, etc.; sometimes referred to herein as "actuators”
  • forces/moments 108 may include forces and/or moments along and/or about one or more axes of the aircraft, such as x, y, and z axes, corresponding to longitudinal, transverse, and vertical axes of the aircraft, respectively, in various
  • the flight control system 100 includes an online optimizer/mixer 110 configured to receive forces/moments 108.
  • Online optimizer/mixer 110 receives as input forces/moments 108 and computes dynamically (online) a set of actuators and associated commands/parameters 112 to achieve the requested forces/moments 108. In some embodiments, the optimizer minimizes total power given a desired combination of forces and moments.
  • Actuators 114 are configured to operate in response to actuator commands/parameters 112 provided by online optimizer/mixer 110.
  • sensors 116 provide sensor data 118 to online optimizer/mixer 110.
  • sensors 116 and/or sensor data 118 may include one or more of airspeed, temperature, or other environmental conditions; actuator availability, failure, and/or health information; aircraft attitude, altitude, and/or other position information; presence/absence of other aircraft, debris, or other obstacles in the vicinity of the aircraft; actuator position information; etc.
  • online optimizer/mixer 110 may be configured to take sensor data 118 into account in determining an optimal mix of actuators and associated parameters to achieve a requested set of forces and moments.
  • six or more lift fans may be provided to lift an aircraft into the air, enable the aircraft to hover, control aircraft attitude relative to the horizontal, etc.
  • failure of a lift fan may be reflected in sensor data 118, resulting in a seamless response by online optimizer/mixer 110, which provides an optimal set of actuators and parameters 112 that omits (does not rely on) the failed lift fan.
  • online optimizer/mixer 110 provides an optimal set of actuators and parameters 112 that omits (does not rely on) the failed lift fan.
  • sensor data reflecting diminished power/performance, overheating, etc. may be taken into consideration, such as by adjusting a mapping of actuator parameter to expected effect on the aircraft for affected actuators.
  • FIG. 2A is a block diagram illustrating an embodiment of a multicopter aircraft with angled rotors.
  • a flight control system such as flight control system 100 of Figure 1 may be embodied in an aircraft such as aircraft 200 of Figure 2 A.
  • aircraft 200 includes a fuselage (body) 202 and wings 204.
  • a set of three underwing booms 206 is provided under each wing.
  • Each boom 206 has two lift fans 208 mounted thereon, one forward of the wing and one aft.
  • Each lift fan 208 may be driven by an associated drive mechanism, such as a dedicated electric motor.
  • One or more batteries (not shown) and/or onboard power generators e.g., small gas turbine
  • each boom 206 is positioned at an angle relative to a vertical axis of the aircraft such that the lift fans 208 are mounted thereon at an associated angle, as described more fully in connection with Figures 2B - 2E.
  • a propeller 210 is mounted on the fuselage 202 and configured to push the aircraft through the air in the forward (e.g., x axis) direction.
  • the propeller 210 is positioned between a pair of tail booms 212 that extend aft and are joined at their aft end by a tail structure on which aerodynamic control surfaces including elevators 216 and rudder 218 are mounted.
  • each of the inboard booms 206 forms at least in part an integral part of the corresponding port/starboard side tail boom 212.
  • the tail booms 212 comprise extensions aft from the respective inboard booms 206.
  • tail booms 212 may be formed as part of or fastened (e.g., bolted) to an aft end of the corresponding inboard boom 206.
  • Additional control surfaces include ailerons 214 mounted on the trailing edge of wings 204.
  • ailerons 214 are included, e.g., to provide redundancy. In some embodiments, if a single aileron 214 is lost or fails the remaining three ailerons 214 are sufficient to control the aircraft. Likewise, in some embodiments, loss of one rudder 218 results in one remaining rudder to provide a degree of yaw control, along with the lift fans. Finally, in some embodiments four elevators 216 are provided for loss/failure tolerance.
  • an aircraft 200 as shown in Figure 2A may have the following approximate dimensions:
  • Figure 2B is a block diagram showing a front view of the multicopter aircraft
  • FIG. 200 of Figure 2A Coordinate axes in the z (vertical) and y (side) direction are indicated.
  • the front view shown in Figure 2B illustrates the respective angles off the vertical axis (z axis as labeled), sometimes referred to herein as "cant angles", at which the outboard, middle, and inboard pairs of lift fans 206 are oriented.
  • angling the lift fans may provide additional options to control the aircraft, especially at or near hover. For example, different combinations of fans may be used to exercise yaw control (e.g., rotate around z axis), to slip sideways or counteract the force of wind while in a hover (y axis), etc.
  • the respective angles at which lift fans 208 may be oriented may be determined based at least in part on safety considerations, such as to increase the likelihood that debris thrown centrifugally from a lift fan, e.g., should the lift fan break apart, would be propelled on a trajectory and/or in a plane that does not intersect a human- occupied portion of fuselage 202.
  • safety considerations such as to increase the likelihood that debris thrown centrifugally from a lift fan, e.g., should the lift fan break apart, would be propelled on a trajectory and/or in a plane that does not intersect a human- occupied portion of fuselage 202.
  • two side by side seats are provided for passengers in a forward part of fuselage 202.
  • Batteries to power the lift fans 208 and/or push propeller 210 may be located in a central/over wing part of the fuselage 202, and in some embodiments both the human-occupied and battery occupied parts of the fuselage are protected at least in part by canting the booms/lift fans as disclosed herein.
  • lift fan cant angles may be determined at least in part via a constrained optimization design process.
  • the fan cants e.g., roll and pitch fan angles
  • the fan cants may be determined by an optimization process in which an object is to minimize the amount of torque required by any individual motor for a variety of trimmed or equilibrium conditions including: angular accelerations, any individual fan failure, crosswinds, and center of gravity variations.
  • the optimization is subject to constraints of preventing the plane of the fan blade from intersecting the crew in the event of catastrophic failure of a fan.
  • Another example of a constraint that may be applied is ensuring that the fans are aligned to the local flow angle for forward flight with the fans stopped and aligned with the boom.
  • the effective forces and moments capable of being provided by each respective lift fan may be stored onboard the aircraft 200 in a memory or other data storage device associated with the onboard flight control system.
  • a matrix, table, database, or other data structure may be used.
  • effectiveness under different operating conditions may be stored. For example, effectiveness of a lift fan or control surface may be different depending on conditions such as airspeed, temperature, etc.
  • forces and moments expected to be generated by a lift fan or other actuator under given conditions may be discounted or otherwise reduced, e.g., by a factor determined based at least in part on an environmental or other variable, such as a measure of lift fan motor health.
  • the forces and moments capable of being generated by a given lift fan may reflect the angle at which each lift fan is mounted.
  • lift fans mounted at an angle relative to the horizontal plane of the aircraft would generate a horizontal force component and a vertical force component, and each force may generate a corresponding moment about one or more axes of the aircraft, depending on the location at which the fan is mounted relative to the center of gravity of the aircraft.
  • FIG. 2C is a block diagram illustrating an example of angled rotors as implemented in an embodiment of a multicopter aircraft with angled rotors.
  • the approximate angles at which the left side (as viewed from the front) rotors of the aircraft 200 as shown in Figures 2A and 2B are mounted are shown.
  • the left most (outboard) lift fan is shown to be mounted at an angle ⁇ 1 to the vertical (and, therefore, horizontal/lateral) axis of the aircraft, tilting away from fuselage 202, resulting in a plane of rotation of the lift fan, indicated by the dashed arrow extending away from the lift fan, not intersecting the fuselage 202.
  • the plane of rotation may intersect the fuselage but not a human-occupied or otherwise critical portion thereof.
  • the middle lift fan and the inboard lift fan have been angled in towards the fuselage 202, resulting in their respective planes of rotation being rotated downward by corresponding angles, such that they do not intersect the fuselage 202.
  • angling lift fans or other rotors towards or away from a fuselage or critical portion thereof, and/or other critical structures may decrease the risk that debris thrown centrifugally from the rotor would hit the fuselage or other structure.
  • Figure 2D is a block diagram illustrating a top view of an embodiment of a multicopter aircraft with angled rotors. Specifically, in Figure 2D a top view off aircraft 200 of Figure 2A is shown. Coordinate axes in the x (forward) and y (side) direction are indicated. In the example shown, the aircraft 200 includes twelve lift fans 208, six on either side of the fuselage 202. On each side of the fuselage 202, three lift fans are mounted forward of the wing 204 and three aft. The lift fans 208 are mounted in pairs on
  • FIG. 2E is a block diagram illustrating an example of forces and moments capable of being generated by angled rotors in an embodiment of a multicopter aircraft with angled rotors.
  • the fuselage 202 of the aircraft 200 of Figure 2D is shown to have a center of gravity 220.
  • the circles in Figure 2E each represent a corresponding one of the lift fans 208.
  • the moment contributed by any given one of the rear lift fans would be determined by the lift force generated by the lift fan as actuated by the flight control system, with the direction (counter-clockwise or clockwise) depending on the position of the lift fan and whether it was tilted away from or towards the fuselage 202.
  • the rear leftmost lift fan would contribute a lateral force F yl resulting in contributing a counter-clockwise moment component about the center of gravity 220.
  • the right side (as shown in Figure 2E) rear inner and middle lift fans (F y4 , F y5 ) similarly would contribute a counter-clockwise moment component.
  • the lift fans associated with lateral force components F y2 , F y3 , and F y6 would contribute clockwise moment components.
  • the forward lift fans (associated with lateral force components F y7 - F yl2 , in this example) would contribute moment components proportional to the x-axis distance x 2 at which they are mounted relative to the center of gravity 220.
  • the respective lift fans 208 may be rotated in alternating clockwise or counterclockwise rotations, e.g., to balance side forces associated with rotation direction.
  • a total of twelve lift fans 208 are included.
  • an even number of lift fans including at least four lift fans may be included and distributed evenly on each side of the fuselage. Upon loss or failure of a lift fan, a corresponding lift fan on an opposite side of the aircraft may be deactivated, to maintain balance.
  • loss of a clockwise rotating lift fan on a forward end of an innermost boom on a port side of the aircraft may result in a counterclockwise rotating lift fan in a complementary position on the opposite side, such as the aft end of the innermost boom on the opposite side, may be shut down and omitted from use (e.g., zero RPM/torque added as a constraint for that lift fan) in subsequent optimization computations to determine mixes of actuators and associated parameters to achieve desired forces and moments.
  • Figure 2F is a block diagram showing a side view of the multicopter aircraft
  • the lift fans 208 are mounted at a prescribed forward tilt relative to a horizontal plane of the aircraft 200.
  • the booms 206 are shown to be mounted substantially aligned with the horizontal plane of the aircraft 200 when in level flight.
  • the wings 204 sweep up slightly as they extend away from the fuselage 202.
  • the angle at which the lift fans 208 are tilted forward may be determined at least in part on the same considerations as the angles illustrated in Figures 2B and 2C, i.e., to ensure that debris thrown centrifugally from a lift fan if it were to break apart would not intersect at least a human-occupied or otherwise critical portion of a cockpit or cabin portion of fuselage 202.
  • the angle at which the lift fans 208 are tilted forward may be selected at least in part to minimize drag, turbulence, or other undesirable aerodynamic effects of the lift fans when the aircraft 200 is in forward flight, e.g., being propelled by push propeller 210.
  • Figure 2G is a block diagram showing a side view of the multicopter aircraft
  • Arrow 244 shows air flowing under/through the forward lift fans 208, under the wing 204, and flowing over the aft lift fans 208 in a relatively low drag manner, due at least in part to the forward tilt of the aft lift fans 208.
  • the wing 204 may not sweep upward to the same extent as shown in Figures 2F and 2G, and in some such embodiments the aft lift fans may be more within a same horizontal plane as the forward lift fans 208 and wing 204. In some such embodiments, the aft lift fans 208 may be tilted back slightly, instead of forward, to provide a continuous, relatively low drag pathway for air to flow over the forward lift fans 208, the wing 204, and the after lift fans 208, e.g., when the aircraft 200 is in forward flight mode.
  • a flight control system such as flight control system
  • 100 of Figure 1 is configured to determine a mix of actuators and corresponding actuator parameters, including of lift fans 208, to achieve required forces and moments, including by taking into consideration the moments about the z-axis that would be generated and applied to the aircraft 200 by virtue of the lift fans being mounted at angles, as disclosed herein.
  • techniques disclosed herein may be used to provide a multicopter aircraft having angled lift fans and/or rotors. Each rotor may be mounted at an angle such that debris thrown centrifugally from the lift fan, in a plane of rotation of the lift fan, would not intersect the fuselage or other critical structure of the aircraft.
  • angling rotors as disclosed herein may provide a degree of authority over (ability to control or influence) yaw of the aircraft, e.g., during hover or vertical takeoff (lift) or landing operations.

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  • Engineering & Computer Science (AREA)
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  • General Physics & Mathematics (AREA)
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  • Radar, Positioning & Navigation (AREA)
  • Automation & Control Theory (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
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Abstract

A multicopter with angled rotors is disclosed. In various embodiments, a multicopter as disclosed herein includes a fuselage and a plurality of rotors. At least some of the rotors are disposed on opposite sides of the fuselage and each is oriented at a corresponding angle to a substantially horizontal plane of the aircraft, the angle being of a magnitude such that a plane of rotation of the rotor does not intersect at least a critical portion of the fuselage.

Description

MULTICOPTER WITH ANGLED ROTORS
BACKGROUND OF THE INVENTION
[0001] Multicopter aircraft typically include a plurality of horizontally oriented rotors, sometimes referred to as "lift fans," to provide lift, stability, and control. A flight control system, sometimes referred to as a "flight controller" or "flight computer", may be provided to translate pilot or other operator input, and/or corrections computed by an onboard computer, e.g., based on sensor data, into forces and moments and/or to further translate such forces and moments into a set of actuator (e.g., lift rotors; propellers; control surfaces, such as ailerons; etc.) and/or associated parameters (e.g., lift fan power, speed, or torque) to provide the required forces and moments.
[0002] For example, pilot or other operator inputs may indicate a desired change in the aircraft's speed, direction, and/or orientation, and/or wind or other forces may act on the aircraft, requiring the lift fans and/or other actuators to be used to maintain a desired aircraft attitude (roll/pitch/yaw), speed, and/or altitude.
[0003] An aircraft typically is considered to have six degrees of freedom of movement, including forces in the forward/back, side/side, and up/down directions (e.g., Fx, Fy, and Fz) and moments about the longitudinal (roll) axis, the transverse (pitch) axis, and the vertical (yaw) axis (e.g., Mx, My, and Mz). If an aircraft has more actuators than degrees of freedom, it must be determined how the various actuators will be used to act on the aircraft in response to commands received via manual and/or automated controls. For a given set of one or more pilot commands under given circumstances, some combinations of actuators capable of acting on the aircraft to achieve the result indicated by the pilot command(s) may be more effective and/or efficient than others. For example, some may consume more or less power and/or fuel than others, provide a more smooth transition from a current state than others, etc.
[0004] Rotors may spin at a high rate and could pose a risk to an occupant of a manned multicopter and/or to equipment housed in a fuselage or other structure comprising the multicopter. BRIEF DESCRIPTION OF THE DRAWINGS
[0005] Various embodiments of the invention are disclosed in the following detailed description and the accompanying drawings.
[0006] Figure 1 is a block diagram illustrating an embodiment of a flight control system.
[0007] Figure 2A is a block diagram illustrating an embodiment of a multicopter aircraft with angled rotors.
[0008] Figure 2B is a block diagram showing a front view of the multicopter aircraft
200 of Figure 2A.
[0009] Figure 2C is a block diagram illustrating an example of angled rotors as implemented in an embodiment of a multicopter aircraft with angled rotors.
[0010] Figure 2D is a block diagram illustrating a top view of an embodiment of a multicopter aircraft with angled rotors.
[0011] Figure 2E is a block diagram illustrating an example of forces and moments capable of being generated by angled rotors in an embodiment of a multicopter aircraft with angled rotors.
[0012] Figure 2F is a block diagram showing a side view of the multicopter aircraft
200 of Figure 2A.
[0013] Figure 2G is a block diagram showing a side view of the multicopter aircraft
200 of Figure 2A.
DETAILED DESCRIPTION
[0014] The invention can be implemented in numerous ways, including as a process; an apparatus; a system; a composition of matter; a computer program product embodied on a computer readable storage medium; and/or a processor, such as a processor configured to execute instructions stored on and/or provided by a memory coupled to the processor. In this specification, these implementations, or any other form that the invention may take, may be referred to as techniques. In general, the order of the steps of disclosed processes may be altered within the scope of the invention. Unless stated otherwise, a component such as a processor or a memory described as being configured to perform a task may be implemented as a general component that is temporarily configured to perform the task at a given time or a specific component that is manufactured to perform the task. As used herein, the term 'processor' refers to one or more devices, circuits, and/or processing cores configured to process data, such as computer program instructions.
[0015] A detailed description of one or more embodiments of the invention is provided below along with accompanying figures that illustrate the principles of the invention. The invention is described in connection with such embodiments, but the invention is not limited to any embodiment. The scope of the invention is limited only by the claims and the invention encompasses numerous alternatives, modifications and equivalents. Numerous specific details are set forth in the following description in order to provide a thorough understanding of the invention. These details are provided for the purpose of example and the invention may be practiced according to the claims without some or all of these specific details. For the purpose of clarity, technical material that is known in the technical fields related to the invention has not been described in detail so that the invention is not unnecessarily obscured.
[0016] A multicopter aircraft with angled rotors is disclosed. In various
embodiments, a multicopter aircraft as disclosed herein includes a plurality of lift fans or other rotors disposed in a configuration around a fuselage and/or other centrally-located structure of the aircraft. In some embodiments, a first subset of the rotors may be disposed on a one side of the aircraft and a second subset of the rotors may be disposed on an opposite side of the aircraft. In various embodiments, each of at least a subset of the rotors is mounted at a corresponding non-zero angle off of a horizontal plane of the aircraft. In some embodiments, the angle at which each rotor is mounted is determined at least in part by a location of the rotor relative to the fuselage and/or a human or other occupied portion thereof, the angle being determined at least in part to ensure that a plane in which the rotor primarily rotates does not intersect the fuselage and/or a human or other occupied portion thereof. In various embodiments, the respective angles at which at least a subset of the rotors are mounted may be determined at least in part to provide the ability to generate lateral force components in the horizontal plane of the aircraft at rotor mount locations that are offset in the horizontal plane from a center of gravity of the aircraft , so as to provide an ability to use the rotors to control yaw of the aircraft (i.e., rotation about a vertical axis of the aircraft) by applying moments about the vertical axis.
[0017] Figure 1 is a block diagram illustrating an embodiment of a flight control system. In the example shown, flight control system 100 includes a source of flight control inputs 102 configured to provide flight control inputs 104 to a controller 106, e.g., a flight control computer. In some embodiments, source of inputs 102 may comprises one or both of pilot input, e.g., via manual flight controls, and auto-pilot or other self-piloting technologies. For example, in a self-piloting aircraft inputs 104 may be generated by a self-piloting program/computer 102. In various embodiments, source of inputs 102 may include manual input devices (sometimes referred to as "inceptors"), such as stick, throttle, rudder, collective, joystick, thumb stick, and/or other manual control/input devices configured to be manipulated by a pilot or other operator to control the flight of an aircraft. Such inceptor devices and/or associated electronics, and/or a self-piloting program, computer, or module, may be configured to provide as input signals 104 one or more of a roll direction, roll rate, yaw direction, yaw rate, pitch angle, pitch rate, altitude, altitude rate and/or forward or other thrust input signal. In the example shown, controller 106 also receives sensor data 118, e.g., wind speed, air temperature, etc., from sensors 116. Flight controller 106 translates, aggregates, and/or otherwise processes and/or interprets the received flight control inputs 104 and/or sensor data 118 to generate and provide as output associated forces and/or moments 108 to be applied to the aircraft via its control assets (e.g., propellers, rotors, lift fans, aerodynamic control surfaces, etc.; sometimes referred to herein as "actuators") to maneuver the aircraft in a manner determined based at least in part on the flight control inputs 104 and/or sensor data 118. In various embodiments, forces/moments 108 may include forces and/or moments along and/or about one or more axes of the aircraft, such as x, y, and z axes, corresponding to longitudinal, transverse, and vertical axes of the aircraft, respectively, in various
embodiments.
[0018] Referring further to Figure 1, the flight control system 100 includes an online optimizer/mixer 110 configured to receive forces/moments 108. Online optimizer/mixer 110 receives as input forces/moments 108 and computes dynamically (online) a set of actuators and associated commands/parameters 112 to achieve the requested forces/moments 108. In some embodiments, the optimizer minimizes total power given a desired combination of forces and moments. Actuators 114 are configured to operate in response to actuator commands/parameters 112 provided by online optimizer/mixer 110.
[0019] In the example shown, sensors 116 provide sensor data 118 to online optimizer/mixer 110. Examples of sensors 116 and/or sensor data 118 may include one or more of airspeed, temperature, or other environmental conditions; actuator availability, failure, and/or health information; aircraft attitude, altitude, and/or other position information; presence/absence of other aircraft, debris, or other obstacles in the vicinity of the aircraft; actuator position information; etc. In various embodiments, online optimizer/mixer 110 may be configured to take sensor data 118 into account in determining an optimal mix of actuators and associated parameters to achieve a requested set of forces and moments. For example, in some embodiments, six or more lift fans may be provided to lift an aircraft into the air, enable the aircraft to hover, control aircraft attitude relative to the horizontal, etc. In some embodiments, failure of a lift fan may be reflected in sensor data 118, resulting in a seamless response by online optimizer/mixer 110, which provides an optimal set of actuators and parameters 112 that omits (does not rely on) the failed lift fan. Likewise, in some
embodiments, sensor data reflecting diminished power/performance, overheating, etc., may be taken into consideration, such as by adjusting a mapping of actuator parameter to expected effect on the aircraft for affected actuators.
[0020] Figure 2A is a block diagram illustrating an embodiment of a multicopter aircraft with angled rotors. In various embodiments, a flight control system such as flight control system 100 of Figure 1 may be embodied in an aircraft such as aircraft 200 of Figure 2 A. In the example shown, aircraft 200 includes a fuselage (body) 202 and wings 204. A set of three underwing booms 206 is provided under each wing. Each boom 206 has two lift fans 208 mounted thereon, one forward of the wing and one aft. Each lift fan 208 may be driven by an associated drive mechanism, such as a dedicated electric motor. One or more batteries (not shown) and/or onboard power generators (e.g., small gas turbine) may be used to drive the lift fans 208 and/or charge/recharge onboard batteries.
[0021] In various embodiments, each boom 206 is positioned at an angle relative to a vertical axis of the aircraft such that the lift fans 208 are mounted thereon at an associated angle, as described more fully in connection with Figures 2B - 2E.
[0022] In the example shown in Figure 2A, a propeller 210 is mounted on the fuselage 202 and configured to push the aircraft through the air in the forward (e.g., x axis) direction. The propeller 210 is positioned between a pair of tail booms 212 that extend aft and are joined at their aft end by a tail structure on which aerodynamic control surfaces including elevators 216 and rudder 218 are mounted. In various embodiments, each of the inboard booms 206 forms at least in part an integral part of the corresponding port/starboard side tail boom 212. In some embodiments, the tail booms 212 comprise extensions aft from the respective inboard booms 206. For example, the tail booms 212 may be formed as part of or fastened (e.g., bolted) to an aft end of the corresponding inboard boom 206. Additional control surfaces include ailerons 214 mounted on the trailing edge of wings 204.
[0023] In the example shown, four ailerons 214 are included, e.g., to provide redundancy. In some embodiments, if a single aileron 214 is lost or fails the remaining three ailerons 214 are sufficient to control the aircraft. Likewise, in some embodiments, loss of one rudder 218 results in one remaining rudder to provide a degree of yaw control, along with the lift fans. Finally, in some embodiments four elevators 216 are provided for loss/failure tolerance.
[0024] In some embodiments, an aircraft 200 as shown in Figure 2A may have the following approximate dimensions:
Wingspan:
Nose to tail
Centerline to first boom
Distance between inner booms
Spacing between booms (same wing
Push propeller sweep
Lift fan sweep
• Distance between fan centers (same boom) 8.7 feet
[0025] Figure 2B is a block diagram showing a front view of the multicopter aircraft
200 of Figure 2A. Coordinate axes in the z (vertical) and y (side) direction are indicated. The front view shown in Figure 2B illustrates the respective angles off the vertical axis (z axis as labeled), sometimes referred to herein as "cant angles", at which the outboard, middle, and inboard pairs of lift fans 206 are oriented. In various embodiments, angling the lift fans, as indicated, may provide additional options to control the aircraft, especially at or near hover. For example, different combinations of fans may be used to exercise yaw control (e.g., rotate around z axis), to slip sideways or counteract the force of wind while in a hover (y axis), etc.
[0026] In various embodiments, the respective angles at which lift fans 208 may be oriented may be determined based at least in part on safety considerations, such as to increase the likelihood that debris thrown centrifugally from a lift fan, e.g., should the lift fan break apart, would be propelled on a trajectory and/or in a plane that does not intersect a human- occupied portion of fuselage 202. In some embodiments, two side by side seats are provided for passengers in a forward part of fuselage 202. Batteries to power the lift fans 208 and/or push propeller 210 may be located in a central/over wing part of the fuselage 202, and in some embodiments both the human-occupied and battery occupied parts of the fuselage are protected at least in part by canting the booms/lift fans as disclosed herein.
[0027] In some embodiments, lift fan cant angles may be determined at least in part via a constrained optimization design process. The fan cants (e.g., roll and pitch fan angles) may be determined by an optimization process in which an object is to minimize the amount of torque required by any individual motor for a variety of trimmed or equilibrium conditions including: angular accelerations, any individual fan failure, crosswinds, and center of gravity variations. In some embodiments, the optimization is subject to constraints of preventing the plane of the fan blade from intersecting the crew in the event of catastrophic failure of a fan. Another example of a constraint that may be applied is ensuring that the fans are aligned to the local flow angle for forward flight with the fans stopped and aligned with the boom.
[0028] In various embodiments, the effective forces and moments capable of being provided by each respective lift fan may be stored onboard the aircraft 200 in a memory or other data storage device associated with the onboard flight control system. In various embodiments, a matrix, table, database, or other data structure may be used.
[0029] In some embodiments, effectiveness under different operating conditions may be stored. For example, effectiveness of a lift fan or control surface may be different depending on conditions such as airspeed, temperature, etc. In some embodiments, forces and moments expected to be generated by a lift fan or other actuator under given conditions may be discounted or otherwise reduced, e.g., by a factor determined based at least in part on an environmental or other variable, such as a measure of lift fan motor health.
[0030] In an aircraft having angled lift fans as in the example shown in Figure 2B, the forces and moments capable of being generated by a given lift fan may reflect the angle at which each lift fan is mounted. For example, lift fans mounted at an angle relative to the horizontal plane of the aircraft would generate a horizontal force component and a vertical force component, and each force may generate a corresponding moment about one or more axes of the aircraft, depending on the location at which the fan is mounted relative to the center of gravity of the aircraft.
[0031] Figure 2C is a block diagram illustrating an example of angled rotors as implemented in an embodiment of a multicopter aircraft with angled rotors. In the example shown, the approximate angles at which the left side (as viewed from the front) rotors of the aircraft 200 as shown in Figures 2A and 2B are mounted are shown. In particular, the left most (outboard) lift fan is shown to be mounted at an angle Θ1 to the vertical (and, therefore, horizontal/lateral) axis of the aircraft, tilting away from fuselage 202, resulting in a plane of rotation of the lift fan, indicated by the dashed arrow extending away from the lift fan, not intersecting the fuselage 202. In some embodiments, the plane of rotation may intersect the fuselage but not a human-occupied or otherwise critical portion thereof.
[0032] Similarly, in the example shown the middle lift fan and the inboard lift fan have been angled in towards the fuselage 202, resulting in their respective planes of rotation being rotated downward by corresponding angles, such that they do not intersect the fuselage 202.
[0033] In various embodiments, angling lift fans or other rotors towards or away from a fuselage or critical portion thereof, and/or other critical structures, may decrease the risk that debris thrown centrifugally from the rotor would hit the fuselage or other structure.
[0034] Figure 2D is a block diagram illustrating a top view of an embodiment of a multicopter aircraft with angled rotors. Specifically, in Figure 2D a top view off aircraft 200 of Figure 2A is shown. Coordinate axes in the x (forward) and y (side) direction are indicated. In the example shown, the aircraft 200 includes twelve lift fans 208, six on either side of the fuselage 202. On each side of the fuselage 202, three lift fans are mounted forward of the wing 204 and three aft. The lift fans 208 are mounted in pairs on
corresponding booms 206 mounted under the wings 204. The outermost booms are tilted away from the fuselage 202 and the middle and inner booms are tilted towards the fuselage, as shown in Figures 2B and 2C. [0035] Figure 2E is a block diagram illustrating an example of forces and moments capable of being generated by angled rotors in an embodiment of a multicopter aircraft with angled rotors. In Figure 2E, the fuselage 202 of the aircraft 200 of Figure 2D is shown to have a center of gravity 220. The circles in Figure 2E each represent a corresponding one of the lift fans 208. The arrows labeled Fyl, Fy2, etc. represent the respective lateral (y-axis) components of the force generated by the angled lift fans 208 by virtue of their being mounted at angles, and shown in Figures 2A - 2D. The rear (aft) fans are shown to be mounted at an x-axis distance xi from center of gravity 220. As a result, the y-axis components of the rear lift fans, as shown, would result in corresponding moments of magnitudes proportional to the distance xl being applied to the aircraft about the vertical axis (z-axis, using the convention shown in Figures 2 A - 2E). The moment contributed by any given one of the rear lift fans would be determined by the lift force generated by the lift fan as actuated by the flight control system, with the direction (counter-clockwise or clockwise) depending on the position of the lift fan and whether it was tilted away from or towards the fuselage 202. For example, the rear leftmost lift fan would contribute a lateral force Fyl resulting in contributing a counter-clockwise moment component about the center of gravity 220. The right side (as shown in Figure 2E) rear inner and middle lift fans (Fy4, Fy5) similarly would contribute a counter-clockwise moment component. By contrast, the lift fans associated with lateral force components Fy2, Fy3, and Fy6 would contribute clockwise moment components.
[0036] Similar to the rear lift fans, the forward lift fans (associated with lateral force components Fy7 - Fyl2, in this example) would contribute moment components proportional to the x-axis distance x2 at which they are mounted relative to the center of gravity 220.
[0037] In various embodiments, the respective lift fans 208 may be rotated in alternating clockwise or counterclockwise rotations, e.g., to balance side forces associated with rotation direction. In the example shown in Figures 2A-2E, a total of twelve lift fans 208 are included. In various embodiments, an even number of lift fans including at least four lift fans may be included and distributed evenly on each side of the fuselage. Upon loss or failure of a lift fan, a corresponding lift fan on an opposite side of the aircraft may be deactivated, to maintain balance. For example, loss of a clockwise rotating lift fan on a forward end of an innermost boom on a port side of the aircraft may result in a counterclockwise rotating lift fan in a complementary position on the opposite side, such as the aft end of the innermost boom on the opposite side, may be shut down and omitted from use (e.g., zero RPM/torque added as a constraint for that lift fan) in subsequent optimization computations to determine mixes of actuators and associated parameters to achieve desired forces and moments.
[0038] Figure 2F is a block diagram showing a side view of the multicopter aircraft
200 of Figure 2A. In the example shown, the lift fans 208 are mounted at a prescribed forward tilt relative to a horizontal plane of the aircraft 200. The booms 206 are shown to be mounted substantially aligned with the horizontal plane of the aircraft 200 when in level flight. The wings 204 sweep up slightly as they extend away from the fuselage 202. In various embodiments, the angle at which the lift fans 208 are tilted forward may be determined at least in part on the same considerations as the angles illustrated in Figures 2B and 2C, i.e., to ensure that debris thrown centrifugally from a lift fan if it were to break apart would not intersect at least a human-occupied or otherwise critical portion of a cockpit or cabin portion of fuselage 202. In some embodiments, the angle at which the lift fans 208 are tilted forward may be selected at least in part to minimize drag, turbulence, or other undesirable aerodynamic effects of the lift fans when the aircraft 200 is in forward flight, e.g., being propelled by push propeller 210.
[0039] Figure 2G is a block diagram showing a side view of the multicopter aircraft
200 of Figure 2A. In the example shown, approximate airflow patterns are illustrated by arrows 242 and 244. Arrow 242 shows air flowing with minimal resistance over the forward lift fans 208 and, due in part to the forward tilt of the forward lift fans 242, continuing relatively unimpeded over wing 204, and clearing the aft lift fans 208 (or, in some
embodiments, flowing over them in a relatively low drag path, due in part to their forward tilt). Arrow 244 shows air flowing under/through the forward lift fans 208, under the wing 204, and flowing over the aft lift fans 208 in a relatively low drag manner, due at least in part to the forward tilt of the aft lift fans 208.
[0040] In some embodiments, the wing 204 may not sweep upward to the same extent as shown in Figures 2F and 2G, and in some such embodiments the aft lift fans may be more within a same horizontal plane as the forward lift fans 208 and wing 204. In some such embodiments, the aft lift fans 208 may be tilted back slightly, instead of forward, to provide a continuous, relatively low drag pathway for air to flow over the forward lift fans 208, the wing 204, and the after lift fans 208, e.g., when the aircraft 200 is in forward flight mode. [0041] In various embodiments, a flight control system, such as flight control system
100 of Figure 1, is configured to determine a mix of actuators and corresponding actuator parameters, including of lift fans 208, to achieve required forces and moments, including by taking into consideration the moments about the z-axis that would be generated and applied to the aircraft 200 by virtue of the lift fans being mounted at angles, as disclosed herein.
[0042] In various embodiments, techniques disclosed herein may be used to provide a multicopter aircraft having angled lift fans and/or rotors. Each rotor may be mounted at an angle such that debris thrown centrifugally from the lift fan, in a plane of rotation of the lift fan, would not intersect the fuselage or other critical structure of the aircraft. In various embodiments, angling rotors as disclosed herein may provide a degree of authority over (ability to control or influence) yaw of the aircraft, e.g., during hover or vertical takeoff (lift) or landing operations.
[0043] Although the foregoing embodiments have been described in some detail for purposes of clarity of understanding, the invention is not limited to the details provided. There are many alternative ways of implementing the invention. The disclosed embodiments are illustrative and not restrictive.

Claims

1. An aircraft, comprising: a fuselage; and
a plurality of rotors, at least a subset of the rotors being disposed on opposite sides of the fuselage, and wherein each rotor in the subset is oriented at a corresponding angle to a substantially horizontal plane of the aircraft, the angle being of a magnitude such that a plane of rotation of the rotor does not intersect at least a critical portion of the fuselage.
2. The aircraft of claim 1, wherein said substantially horizontal plane of the aircraft intersects the fuselage and at least a portion of said at least a subset of rotors.
3. The aircraft of claim 1, wherein each of said rotors in said subset is mounted at a point at which a plane parallel to said substantially horizontal plane of the aircraft intersects said at least a critical portion of the fuselage.
4. The aircraft of claim 1, wherein said rotors are mounted on booms each affixed to a corresponding wing of the aircraft.
5. The aircraft of claim 4, wherein each rotor in said subset is oriented at said
corresponding angle at least in part by mounting a corresponding boom at said corresponding angle.
6. The aircraft of claim 1 , wherein said at least a subset of rotors includes a first subset mounted forward of a center of gravity of the aircraft and a second subset mounted aft of the center of gravity.
7. The aircraft of claim 6, wherein each of the first subset and the second subset includes a first group of rotors angled in a first direction relative to vertical and a second group of rotors angled in a second direction relative to vertical, opposite the first direction.
8. The aircraft of claim 1 , wherein the orienting at respective angles of the rotors in said at least a subset of rotors results in a lateral force component of the respective lift forces generated and applied to the aircraft by said rotors.
9. The aircraft of claim 8, further comprising a flight control system that includes a processor configured to use said lateral force components to control yaw about a substantially vertical yaw axis of the aircraft.
10. The aircraft of claim 8, further comprising a flight control system that includes a processor configured to determine a set of actuators and associated actuator parameters to apply a requested set of forces and moments to the aircraft, the request set of forces and moments including a moment about a substantially vertical yaw axis of the aircraft, and wherein the processor is configured to take into consideration said lateral force components generated and applied to the aircraft by rotors including in said at least a subset of rotors, and the respective contributions of said lateral force components to a net moment about said substantially vertical yaw axis of the aircraft, in determining said set of actuators and associated actuator parameters.
PCT/US2017/056817 2016-10-18 2017-10-16 Multicopter with angled rotors WO2018075412A1 (en)

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EP23216810.4A EP4318167A3 (en) 2016-10-18 2017-10-16 Multicopter with angled rotors
CN202210735081.4A CN114872890A (en) 2016-10-18 2017-10-16 Multi-rotor device with rotors with angles
AU2017346502A AU2017346502B2 (en) 2016-10-18 2017-10-16 Multicopter with angled rotors
EP17862880.6A EP3529149B1 (en) 2016-10-18 2017-10-16 Multicopter with angled rotors
CN201780063710.0A CN109843715B (en) 2016-10-18 2017-10-16 Multi-rotor device with rotors with angles
NZ752614A NZ752614A (en) 2016-10-18 2017-10-16 Multicopter with angled rotors
AU2021202178A AU2021202178B2 (en) 2016-10-18 2021-04-09 Multicopter with angled rotors
AU2023226684A AU2023226684A1 (en) 2016-10-18 2023-09-06 Multicopter with angled rotors

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3584161A1 (en) * 2018-06-20 2019-12-25 Bell Helicopter Textron Inc. Tilted propellers for enhanced distributed propulsion control authority
EP3730404A1 (en) 2019-04-23 2020-10-28 LEONARDO S.p.A. Vertical take-off and landing aircraft and related control method

Families Citing this family (36)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
TWI538852B (en) * 2011-07-19 2016-06-21 季航空股份有限公司 Personal aircraft
US9694911B2 (en) * 2014-03-18 2017-07-04 Joby Aviation, Inc. Aerodynamically efficient lightweight vertical take-off and landing aircraft with pivoting rotors and stowing rotor blades
US10364036B2 (en) * 2016-10-18 2019-07-30 Kitty Hawk Corporation Multicopter with boom-mounted rotors
US10364024B2 (en) 2016-10-18 2019-07-30 Kitty Corporation Multicopter with angled rotors
EP3535185B1 (en) * 2016-11-02 2022-01-05 Joby Aero, Inc. Vtol aircraft using rotors to simulate rigid wing dynamics
US10526079B1 (en) * 2017-07-13 2020-01-07 Kitty Hawk Corporation Multicopter with wide span rotor configuration and protective fuselage
US10737797B2 (en) * 2017-07-21 2020-08-11 General Electric Company Vertical takeoff and landing aircraft
US10745099B2 (en) * 2017-08-31 2020-08-18 Wisk Aero Llc Conductor in composite
KR102669208B1 (en) * 2017-11-03 2024-05-28 조비 에어로, 인크. VTOL M-wing configuration
US11027836B2 (en) * 2018-07-13 2021-06-08 The Boeing Company Rotorcraft with canted coaxial rotors
US11440671B2 (en) * 2019-01-24 2022-09-13 Amazon Technologies, Inc. Adjustable motor fairings for aerial vehicles
US11453489B2 (en) * 2019-02-20 2022-09-27 Shanghai Autoflight Co., Ltd. Vertical takeoff and landing aerial vehicle
EP3702277B1 (en) * 2019-02-27 2021-01-27 AIRBUS HELICOPTERS DEUTSCHLAND GmbH A multirotor aircraft that is adapted for vertical take-off and landing (vtol)
US11829161B2 (en) 2019-04-26 2023-11-28 Aergility Corporation Hybrid gyrodyne aircraft
US11643199B2 (en) 2019-05-10 2023-05-09 Eve Uam, Llc Vertical take-off and landing (VTOL) aircraft
KR20220029575A (en) * 2019-05-21 2022-03-08 조비 에어로, 인크. Vertical take-off and landing aircraft using a fixed forward tilted rotor to simulate rigid wing aerodynamics
US11597505B1 (en) * 2019-05-31 2023-03-07 Sifly Aviation, Inc. Rotorcraft optimized for forward flight
CN110525643A (en) * 2019-09-18 2019-12-03 深圳飞马机器人科技有限公司 A kind of vertical take-off and landing drone and its manufacturing method
USD921565S1 (en) * 2019-10-02 2021-06-08 Kitty Hawk Corporation Fixed wing aircraft with tilt rotors
US11106221B1 (en) * 2019-11-25 2021-08-31 Kitty Hawk Corporation Multicopter with self-adjusting rotors
KR20220137029A (en) * 2020-02-10 2022-10-11 위스크 에어로 엘엘씨 Aircraft with pusher propellers
US10926654B1 (en) 2020-03-31 2021-02-23 Kitty Hawk Corporation Electric vertical take-off and landing vehicle with wind turbine
US10913547B1 (en) 2020-03-31 2021-02-09 Kitty Hawk Corporation Charging station for self-balancing multicopter
US20210362849A1 (en) * 2020-05-19 2021-11-25 Archer Aviation, Inc. Vertical take-off and landing aircraft
US20220234728A1 (en) * 2021-01-22 2022-07-28 Bell Textron Inc. Method and Apparatus for Reducing Download and Drag of VTOL Electric Vehicle
US11919631B2 (en) 2021-02-08 2024-03-05 Archer Aviation, Inc. Vertical take-off and landing aircraft with aft rotor tilting
US20220315207A1 (en) * 2021-04-05 2022-10-06 Beta Air, Llc Aircraft for neutralizing vertical flight
US11840351B2 (en) * 2021-04-05 2023-12-12 Beta Air, Llc Aircraft for self-neutralizing flight
US20220350348A1 (en) * 2021-04-29 2022-11-03 General Electric Company Aircraft with a multi-fan propulsion system for controlling flight orientation transitions
US11299287B1 (en) * 2021-06-29 2022-04-12 Beta Air, Llc Methods and systems for orienting a thrust propulsor in response to a failure event of a vertical take-off and landing aircraft
US11420756B1 (en) 2021-07-01 2022-08-23 Beta Air, Llc Systems and methods for fault detection and control in an electric aircraft
EP4134301A1 (en) 2021-08-12 2023-02-15 Zuri.com SE Vertical takeoff and landing aircraft
WO2023051929A1 (en) * 2021-09-30 2023-04-06 Emagic Aircraft Gmbh Electrically propelled aircraft
US12030631B2 (en) * 2021-12-01 2024-07-09 Sandor Mark Langer Aircraft with removable pod and wing for transporting cargo on pallets
EP4209414A1 (en) 2022-01-05 2023-07-12 Zuri.com SE Vertical takeoff and landing aircraft
US11691721B1 (en) * 2022-04-29 2023-07-04 Beta Air, Llc System for propeller parking control for an electric aircraft and a method for its use

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3089666A (en) * 1961-04-13 1963-05-14 Boeing Co Airplane having changeable thrust direction
US3181810A (en) 1961-02-27 1965-05-04 Curtiss Wright Corp Attitude control system for vtol aircraft
US3409248A (en) * 1965-10-22 1968-11-05 Harvard J. Bryan Rotary winged aircraft with drag propelling rotors and controls
US6719244B1 (en) * 2003-02-03 2004-04-13 Gary Robert Gress VTOL aircraft control using opposed tilting of its dual propellers or fans
US20110031355A1 (en) * 2009-06-04 2011-02-10 Alvarez Calderon F Alberto Aircraft with dual flight regimes
US20120012692A1 (en) * 2010-07-19 2012-01-19 Ilan Kroo Personal Aircraft
US20130020429A1 (en) * 2011-07-19 2013-01-24 Ilan Kroo Personal Aircraft
US20160236775A1 (en) * 2015-02-18 2016-08-18 Siniger LLC Vertical takeoff and landing aircraft

Family Cites Families (37)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1627856A (en) * 1925-06-24 1927-05-10 James L Macvicar Aircraft design
US2987272A (en) * 1959-04-29 1961-06-06 Curtiss Wright Corp Aircraft with a tiltable rotor system
US3149800A (en) * 1962-10-26 1964-09-22 Sintes Julio Fernandez Flying machine and apparatus thereof
US3627234A (en) * 1970-07-24 1971-12-14 Ver Flugtechnische Werke Aircraft with lift rotors
US4979698A (en) * 1988-07-07 1990-12-25 Paul Lederman Rotor system for winged aircraft
US6655631B2 (en) * 2000-07-28 2003-12-02 John Frederick Austen-Brown Personal hoverplane with four tiltmotors
US6882889B2 (en) 2002-12-02 2005-04-19 United Technologies Corporation Constrained dynamic inversion control algorithm
DE102006019300B4 (en) * 2006-04-26 2009-10-08 Reinhardt, Gaby Traute plane
US8453962B2 (en) 2007-02-16 2013-06-04 Donald Orval Shaw Modular flying vehicle
US8733690B2 (en) 2009-08-24 2014-05-27 Joby Aviation, Inc. Lightweight vertical take-off and landing aircraft and flight control paradigm using thrust differentials
US9187174B2 (en) * 2010-10-06 2015-11-17 Donald Orval Shaw Aircraft with wings and movable propellers
CN202244078U (en) * 2011-07-29 2012-05-30 深圳市大疆创新科技有限公司 Multi-rotary-wing unmanned aircraft
US9120560B1 (en) * 2011-10-13 2015-09-01 Latitude Engineering, LLC Vertical take-off and landing aircraft
US20130092799A1 (en) * 2011-10-17 2013-04-18 Yu Tian Fixed-wing and electric multi-rotor composite aircraft
US8931729B2 (en) 2011-10-31 2015-01-13 King Abdullah II Design and Development Bureau Sided performance coaxial vertical takeoff and landing (VTOL) UAV and pitch stability technique using oblique active tilting (OAT)
US20130126680A1 (en) 2011-11-17 2013-05-23 Honeywell International Inc. Unmanned air vehicle fault tolerant flight control system and method
US9475579B2 (en) 2013-08-13 2016-10-25 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Vertical take-off and landing vehicle with increased cruise efficiency
KR101554487B1 (en) * 2013-12-23 2015-09-21 이상현 Multi rotor aerial vehicle
US10124890B2 (en) * 2014-04-11 2018-11-13 Dronetechuav Corporation Modular nacelles to provide vertical takeoff and landing (VTOL) capabilities to fixed wing aerial vehicles, and associated systems and methods
EP2990332A1 (en) * 2014-08-19 2016-03-02 Tau Emerald Rotors Inc. Controlling rotary wing aircraft
US11485488B1 (en) * 2014-12-07 2022-11-01 L3Harris Latitude Llc Vertical take-off and landing aircraft with rotor thrust yaw control
DE102015001704B4 (en) * 2015-02-13 2017-04-13 Airbus Defence and Space GmbH Vertical launching aircraft
DE102015006511A1 (en) * 2015-05-26 2016-12-01 Airbus Defence and Space GmbH Vertical launching aircraft
US10183744B2 (en) * 2016-02-10 2019-01-22 Lockheed Martin Corporation Magnetic orientation detent
US20170300065A1 (en) * 2016-04-18 2017-10-19 Latitude Engineering, LLC Automatic recovery systems and methods for unmanned aircraft systems
CN105882953B (en) * 2016-05-17 2018-10-02 亿航智能设备（广州）有限公司 Aircraft
ITUA20163927A1 (en) 2016-05-30 2017-11-30 Magneti Marelli Spa TANGENTIAL ARCHITECTURAL ELECTRIC MACHINE WITH IMPROVED AIR COOLING
US9944386B1 (en) * 2017-07-13 2018-04-17 Kitty Hawk Corporation Multicopter with wide span rotor configuration and protective fuselage
US10086931B2 (en) * 2016-08-26 2018-10-02 Kitty Hawk Corporation Multicopter with wide span rotor configuration
US10364036B2 (en) * 2016-10-18 2019-07-30 Kitty Hawk Corporation Multicopter with boom-mounted rotors
US9764833B1 (en) * 2016-10-18 2017-09-19 Kitty Hawk Corporation Ventilated rotor mounting boom for personal aircraft
US10364024B2 (en) 2016-10-18 2019-07-30 Kitty Corporation Multicopter with angled rotors
US10053213B1 (en) * 2017-05-08 2018-08-21 Pinnacle Vista, LLC Multi-copter lift body aircraft with tail pusher
WO2019084487A1 (en) * 2017-10-27 2019-05-02 Elroy Air, Inc. Compound multi-copter aircraft
US11787525B2 (en) * 2019-10-15 2023-10-17 Elroy Air, Inc. Reconfigurable hybrid VTOL system
KR20220137029A (en) * 2020-02-10 2022-10-11 위스크 에어로 엘엘씨 Aircraft with pusher propellers
US20210362849A1 (en) * 2020-05-19 2021-11-25 Archer Aviation, Inc. Vertical take-off and landing aircraft

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3181810A (en) 1961-02-27 1965-05-04 Curtiss Wright Corp Attitude control system for vtol aircraft
US3089666A (en) * 1961-04-13 1963-05-14 Boeing Co Airplane having changeable thrust direction
US3409248A (en) * 1965-10-22 1968-11-05 Harvard J. Bryan Rotary winged aircraft with drag propelling rotors and controls
US6719244B1 (en) * 2003-02-03 2004-04-13 Gary Robert Gress VTOL aircraft control using opposed tilting of its dual propellers or fans
US20110031355A1 (en) * 2009-06-04 2011-02-10 Alvarez Calderon F Alberto Aircraft with dual flight regimes
US20120012692A1 (en) * 2010-07-19 2012-01-19 Ilan Kroo Personal Aircraft
US20130020429A1 (en) * 2011-07-19 2013-01-24 Ilan Kroo Personal Aircraft
US20160236775A1 (en) * 2015-02-18 2016-08-18 Siniger LLC Vertical takeoff and landing aircraft

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3584161A1 (en) * 2018-06-20 2019-12-25 Bell Helicopter Textron Inc. Tilted propellers for enhanced distributed propulsion control authority
US11136115B2 (en) 2018-06-20 2021-10-05 Textron Innovations Inc. Tilted propellers for enhanced distributed propulsion control authority
EP4163203A1 (en) * 2018-06-20 2023-04-12 Textron Innovations Inc. Tilted propellers for enhanced distributed propulsion control authority
US11649043B2 (en) 2018-06-20 2023-05-16 Textron Innovations Inc. Tilted propellers for enhanced distributed propulsion control authority
EP3730404A1 (en) 2019-04-23 2020-10-28 LEONARDO S.p.A. Vertical take-off and landing aircraft and related control method
WO2020217117A1 (en) 2019-04-23 2020-10-29 Leonardo S.P.A. Vertical take-off and landing aircraft and related control method

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