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公开(公告)号：US12084173B2
公开(公告)日：2024-09-10
申请号：US17968505
申请日：2022-10-18
发明人： Steven R. Schafer
CPC分类号： B64C27/30 , B64C29/0025 , B64C29/0033
摘要： One embodiment is a rotor assembly for an aircraft, the rotor assembly comprising a plurality of rotor blades, wherein at least one of the rotor blades comprises a rotor alignment drag assembly comprising a drag structure on a surface of the at least one of the rotor blades, wherein the drag structure is moveable between a first position in which the drag structure is stowed within the at least one of the rotor blades, and a second position in which the drag structure is extended from the surface of the at least one of the rotor blades; and an actuation mechanism for moving the drag structure from the first position to the second position when a speed of the rotor assembly falls below a first threshold speed.
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公开(公告)号：US20240246666A1
公开(公告)日：2024-07-25
申请号：US18444624
申请日：2024-02-16
申请人： Joby Aero, Inc.
发明人： JoeBen Bevirt , Alex Stoll
CPC分类号： B64C27/30 , B64C11/10 , B64C29/0008 , B64C29/0033 , B64D27/24
摘要： An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle may have deployment mechanisms which deploy electric motor driven propellers from a forward facing to a vertical orientation. The aerial vehicle may have rear mounted rotors adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle may be powered with electric motors.
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公开(公告)号：US11975827B2
公开(公告)日：2024-05-07
申请号：US18034742
申请日：2021-11-02
申请人： GADFIN LTD.
发明人： Robert Roach , Eyal Regev
IPC分类号： B64C27/30
CPC分类号： B64C27/30
摘要： A rotor lock mechanism is disclosed. The mechanism includes a pair of arms at a chosen offset angle # with respect to a long axis of a pair of rotor blades; an arm engagement device configured to restrain rotary motion of the arms; and a rotor drive shaft to which the pair of arms and the pair of rotor blades are attached. A method of use is also disclosed.
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公开(公告)号：US20230137714A1
公开(公告)日：2023-05-04
申请号：US17898488
申请日：2022-08-30
申请人： Joby Aero, Inc.
发明人： JoeBen Bevirt , Alex Stoll
IPC分类号： B64C29/00 , B64C7/02 , B64D27/24 , B64C27/30 , B64C27/28 , B64C11/28 , B64C27/08 , B64C39/06
摘要： An aerial vehicle adapted for vertical takeoff and landing using pivoting thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to takeoff with thrust units providing vertical thrust and then transitioning to a horizontal flight path. An aerial vehicle with pivoting thrust units with propellers, wherein some or all of the propellers are able to be stowed and fully nested during forward flight.
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公开(公告)号：US11608173B2
公开(公告)日：2023-03-21
申请号：US17479137
申请日：2021-09-20
IPC分类号： B64C39/08 , B64C29/00 , B64C3/56 , B64C11/46 , B64C17/00 , B64C29/02 , B64C39/02 , B64D27/24 , B64D27/26 , B64C27/30 , B64C1/06 , G05D1/00 , G05D1/10 , B64U30/10 , B64U30/20 , B64U101/60
摘要： A package delivery system uses unmanned aircraft operable to transition between thrust-borne lift in a VTOL configuration and wing-borne lift in a forward flight configuration. Each of the aircraft includes an airframe having at least one wing with a distributed thrust array coupled to the airframe. The distributed thrust array includes a plurality of propulsion assemblies configured to provide vertical thrust in the VTOL configuration and a plurality of propulsion assemblies configured to provide forward thrust in the forward flight configuration. A package delivery module is coupled to the airframe. A control system is operably associated with the distributed thrust array and the package delivery module. The control system is configured to individually control each of the propulsion assemblies and control package release operations of the package delivery module. The system includes a ground station configured to remotely communicate with the control systems of the aircraft during package delivery missions.
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公开(公告)号：US20230079637A1
公开(公告)日：2023-03-16
申请号：US17474794
申请日：2021-09-14
申请人： BETA AIR, LLC
发明人： Herman Wiegman
摘要： A system for stowable propulsion in an electric aircraft that includes at least a propulsor mounted on at least a structural feature that includes at least a rotor and at least a motor mechanically coupled to the at least a rotor, where the motor is configured to cause the rotor to rotate as a function of an activation datum, at least a sensor communicatively coupled to the at least a propulsor configured to detect a position datum as a function of the configuration, generate a clearance datum as a function of the position datum, transmit the clearance datum to a flight controller, and a flight controller communicatively coupled to the at least a propulsor and the at least a sensor configured to receive the clearance datum from the at least a sensor and generate the activation datum as a function of the clearance datum.
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公开(公告)号：US20220388669A1
公开(公告)日：2022-12-08
申请号：US17373275
申请日：2021-07-12
摘要： An aircraft safety lifesaving system, disclosing an aircraft body, wherein an openable safety cabin is provided at the top of the aircraft body, a deceleration device is provided in the safety cabin, and the deceleration device is capable of being ejected from the safety cabin to enable the aircraft body to decelerate and land; a damping and buffering mechanism provided at the bottom of the aircraft body, the damping and buffering mechanism is telescopically provided in the vertical direction, and the damping and buffering mechanism is capable of extending to the position below the aircraft wheel body. A safety cabin is provided at the top of the aircraft body, and a deceleration device in the safety cabin is ejected in an emergency to assist the aircraft body to decelerate; the damping and buffering mechanism extends below the wheel body, and the damping and buffering mechanism contacts with the ground first.
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公开(公告)号：US11254425B2
公开(公告)日：2022-02-22
申请号：US16595169
申请日：2019-10-07
IPC分类号： B64C27/30 , B64C27/54 , B64C27/467 , B64C27/10
摘要： Rotor assemblies for aircraft are described that include a plurality of blades that are disposed vertically on a common axis along different horizontal planes. When the rotor assemblies are free-wheeling, the blades form a vertically stacked configuration, and when the rotor assembly is driven in rotation to generate lift, the blades bloom out from the vertically stacked configuration. At least one of the blades in the rotor assembly has a blade geometry that is different with respect to other blades such that when the blades are vertically stacked and free-wheeling, the collective shape of the blades is aerodynamic in shape, based on the different blade geometry, that reduces aerodynamic drag on the rotor assembly.
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公开(公告)号：US20210300537A1
公开(公告)日：2021-09-30
申请号：US16833630
申请日：2020-03-29
摘要： An aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a forward flight orientation. The aircraft has a blended wing body and includes an engine, a trinary lift fan system, a forced air bypass system and an exhaust system. The engine has a turboshaft mode and a turbofan mode. The lift fan system includes a plurality of ducted fans in a tandem lateral and forward orientation. In the VTOL orientation of the aircraft, the engine is in the turboshaft mode coupled to the lift fan system such that the engine provides rotational energy to the ducted fans generating the thrust-borne lift. In the forward flight orientation of the aircraft, the engine is in the turbofan mode coupled to the forced air bypass system such that bypass air combines with engine exhaust in the exhaust system to provide forward thrust generating the wing-borne lift.
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公开(公告)号：US11066156B2
公开(公告)日：2021-07-20
申请号：US16174228
申请日：2018-10-29
申请人： Wing Aviation LLC
发明人： Parsa Dormiani , James Ryan Burgess
摘要： An aerial vehicle includes one or more propeller units operable to provide thrust for takeoff or hover flight and one or more propulsion units operable to provide thrust for forward flight. At least one propeller unit includes a shaft coupled to a motor, and a first propeller blade and a second propeller blade that are both connected to the shaft. The second propeller blade is located substantially opposite the first propeller blade, and the second propeller blade has a surface area substantially perpendicular to an axis of rotation that is greater than a corresponding surface area of the first propeller blade. While the aerial vehicle is in forward flight in a first direction and the motor is turned off, the first propeller blade and the second propeller blade are each configured to orient in a second direction that is substantially parallel to the first direction, such that the first propeller blade is oriented substantially upwind of the second propeller blade.
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