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公开(公告)号：US20210253231A1
公开(公告)日：2021-08-19
申请号：US16791311
申请日：2020-02-14
Inventor： Oliver Daniel Ensslin
IPC: B64C27/473 , B64C29/00 , B64C27/37 , B64C27/51
Abstract: Propeller assemblies, aircraft including the same, and associated methods. A propeller assembly includes a first propeller and a second propeller operatively coupled to a coupling shaft and configured to pivot with respect to one another about a propeller rotation axis. The propeller assembly additionally includes a coupling assembly operatively coupled to the first propeller and the second propeller and configured to transition between a plurality of pivotal configurations defined between and including a stowed configuration and a deployed configuration. The coupling assembly transitions from the stowed configuration toward the deployed configuration when a coupling assembly rotational velocity rises above a threshold stowed rotational velocity. In examples, an aircraft includes one or more propeller assemblies operatively coupled to a fuselage. In some examples, a method of operating a propeller assembly includes automatically transitioning a coupling assembly of the propeller assembly between a stowed configuration and a deployed configuration.
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公开(公告)号：US11060658B2
公开(公告)日：2021-07-13
申请号：US15816107
申请日：2017-11-17
Applicant: Aurora Flight Sciences Corporation
Inventor： Riley Griffin , Jeffery Saunders
Abstract: A gimbal stabilizing system for an aircraft having an airframe is disclosed. The gimbal stabilizing system may comprise a gimbal apparatus having at least one gimbal actuator to adjust a position of the gimbal apparatus about an axis, wherein the gimbal apparatus is positioned on the airframe, an angular acceleration apparatus positioned on the airframe to generate an angular acceleration signal reflecting an angular acceleration of the airframe, and a gimbal controller operatively coupled to each of said angular acceleration apparatus and said gimbal apparatus. The gimbal controller may be configured to generate a gimbal control signal to compensate for the angular acceleration of the airframe based at least in part on a feedback control loop and a feedforward control loop, the feedforward control loop having the angular acceleration signal as an input thereto. The gimbal controller may be further configured to output the gimbal control signal to said gimbal apparatus to adjust a position of the gimbal apparatus.
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公开(公告)号：US11046416B2
公开(公告)日：2021-06-29
申请号：US16054307
申请日：2018-08-03
Applicant: Aurora Flight Sciences Corporation
Inventor： William Bosworth , Andrew Heafitz
Abstract: A vehicle includes a fuselage having a longitudinal axis and a propulsion system that is coupled to the fuselage. The vehicle also includes a pair of articulated appendages that is coupled to the fuselage. Each one of the articulated appendages includes a plurality of airfoil segments and is moveable between a ground configuration, in which each one of the pair of articulated appendages supports the vehicle during takeoff or landing of the vehicle, and a flight configuration, in which each one of the pair of articulated appendages produces lift during flight of the vehicle.
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公开(公告)号：US11029157B2
公开(公告)日：2021-06-08
申请号：US15815245
申请日：2017-11-16
Applicant: Aurora Flight Sciences Corporation
Inventor： James Paduano , Terrence McKenna
IPC: G01S15/02 , G01S15/93 , G01C21/20 , G08G9/02 , G01S19/13 , G05D1/10 , G01S7/52 , G01S15/42 , G01S15/87 , G01S15/89 , G01C23/00 , G01C21/16 , G01S15/86
Abstract: An autonomous vehicle is improved with a navigational system having both cameras and echolocation sensors. The cameras and echolocation sensors may be part of an optical and echolocation system, respectively, that may work in conjunction with, for example, a global positioning system to determine a course for the autonomous vehicle to reach an objective while detecting and avoid obstacles along the course.
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45.发明授权公开(公告)号：US11024134B2
公开(公告)日：2021-06-01
申请号：US16572110
申请日：2019-09-16
Inventor： Thomas Needham
Abstract: Provided herein are systems to allow an operator to sense, for example, distance of a component from a component connector. The systems include a transmitter associated with the component connector, and a feedback device operable to contact the operator. The feedback device comprises a receiver operable to receive signals transmitted by the transmitter, and an actuator operable to provide haptic feedback to the operator in which, for example, strength, manner, or strength and manner of actuation of the actuator is determined by strength of the signals received by the receiver. Typically, the systems further allow the operator to engage the component to the component connector. Other aspects of the present disclosure provide various methods of allowing an operator to sense, for example, distance of a component from a component connector and to related computer readable media.
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Patent Agency Ranking
公开(公告)号：US10988246B2
公开(公告)日：2021-04-27
申请号：US16575051
申请日：2019-09-18
Applicant: Aurora Flight Sciences Corporation
Inventor： Martin Kearney-Fischer
IPC: B64C27/57 , B64C11/30 , B64C39/02 , G10K11/175 , G10K11/178 , B64C27/72 , B64C11/46
Abstract: Disclosed is a system, method, and aircraft for controlling acoustic radiation from an aircraft comprising a plurality of rotor systems and a noise controller configured to regulate acoustic radiation from the plurality of rotor systems. The noise controller can be configured to regulate a commanded flight setting from the flight control system and to output a regulated flight setting to the plurality of rotor systems. Based on the regulated flight setting, the plurality of rotor systems are configured to generate, individually and in aggregate, acoustic radiation having a target acoustic behavior. In certain aspects, the noise controller can change the directionality of acoustic radiation from the plurality of rotor systems, or otherwise tune the acoustic radiation to reduce detectability or annoyance.
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公开(公告)号：US10935991B2
公开(公告)日：2021-03-02
申请号：US16003709
申请日：2018-06-08
Applicant: Aurora Flight Sciences Corporation
Inventor： Jae-Woo Choi , Boris Abramov , James D. Paduano
Abstract: The present disclosure is directed to scanning radar reflector systems, methods, and apparatuses; even more particularly to a system, method, and apparatus for scanning and reflecting a radar beam transmitted by a radar transmitter onboard an aerial vehicle with radar reflectors equipped on unmanned aerial vehicles. The radar reflection system may include one or more unmanned aerial vehicles equipped with a one or more axis gimbal upon which a radar reflector is mounted. A user may position the unmanned aerial vehicle and the radar reflector to target a specific region for radar scanning.
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公开(公告)号：US20210036580A1
公开(公告)日：2021-02-04
申请号：US16524895
申请日：2019-07-29
Inventor： Daniel B. Cottrell
Abstract: Propulsors (e.g., an electric motor mechanically coupled to a rotor) are described that passively cool the electric motors via an airflow path through the electric motor and out of the rotors. One embodiment comprises a method of cooling an electric motor. The method comprises operating the electric motor of a propulsor for an aircraft to rotate a rotor of the propulsor, where the rotor has one or more air outlets, and where the electric motor has a housing that includes one or more air inlets in fluid communication with the one or more air inlets. The method further comprises generating, by rotating the rotor using the electric motor, an airflow through the electric motor from the one or more air inlets to the one or more air outlets to cool the electric motor.
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公开(公告)号：US20210016876A1
公开(公告)日：2021-01-21
申请号：US16515340
申请日：2019-07-18
Inventor： Andrew Mark Heafitz , Robert William Parks
Abstract: Rotor assemblies for aircraft are described where one or more blades of the rotor assembly includes a blade alignment device that passively orients a blade in response to an airflow around the blade alignment device when the rotor assembly is free-wheeling. One embodiment comprises a method of operating a rotor assembly for aircraft. The method comprises operating the rotor assembly in a free-wheeling state, where the rotor assembly includes a rotary hub that rotates about an axis and a plurality of blades extending radially from the rotary hub. At least one of the plurality of blades includes a blade alignment device. The method further comprises aligning the at least one of the plurality of blades in response to airflow around the blade alignment device when the rotor assembly is in the free-wheeling state.
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公开(公告)号：US20210011488A1
公开(公告)日：2021-01-14
申请号：US16510796
申请日：2019-07-12
Applicant: Aurora Flight Sciences Corporation
Inventor： Martin A. Kearney-Fischer
Abstract: Systems and methods for enabling consistent smooth takeoffs and landings of vertical and/or short-runway takeoff and landing aircraft at sites with gusty conditions. The system includes a network of wind measurement stations deployed around the perimeter of a takeoff/landing site for spatio-temporally characterizing wind fluctuations (e.g., wind gusts) that enter a volume of airspace overlying the site, data processing means for deriving information about the fluctuations from the wind measurements, communication means for transmitting disturbance information to the aircraft, and a flight control system onboard the aircraft that is configured to use the disturbance information to control the aircraft in a manner that compensates for the fluctuations. The wind measurement units may include laser Doppler anemometers, sound detection and ranging systems or other devices capable of simultaneous spatially and temporally resolved wind measurements.
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