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公开(公告)号：US20240343424A1
公开(公告)日：2024-10-17
申请号：US18601114
申请日：2024-03-11
申请人： GoPro, Inc.
发明人： Joseph Anthony Enke , Benjamin Tankersley , Jean-Bernard Berteaux , Axel Murguet , Garance Bruneau
CPC分类号： B64U50/19 , G05D1/46 , G05D1/854 , B64U10/14 , B64U2201/20
摘要： An aerial vehicle, comprising: one or more motors, one or more sensors, and a flight sub-system. The one or more sensors configured to detect data. The flight sub-system includes an attitude controller module; a rate controller module; and a compensator module. The compensator module is configured to: determine a maximum RPM of the one or more motors or a maximum torque of the one or more motors; receive a torque vector from the rate controller module; determine a rotational speed of the one or more motors to generate a desired flight orientation based upon the torque vector; and consider sensor data from the one or more sensors to adjust the rotational speed of the one or more motors.
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公开(公告)号：US20240353867A1
公开(公告)日：2024-10-24
申请号：US18635198
申请日：2024-04-15
摘要： An aircraft emergency descent method includes setting a pre-set maximum collective blade pitch and a pre-set altitude as part of a failure procedure; monitoring rotor assemblies through an aircraft control system and a failure detection module; determining when a rotor assembly has failed; and activating the failure procedure. The failure procedure includes commanding a maximum torque to a motor of each rotor assembly such that the rotational velocity of functioning rotors increases; detecting the increase in rotational velocity; adjusting either motor torque or a collective blade pitch to regulate rotational velocity; monitoring altitude of the aircraft; and upon determining when the aircraft reaches the pre-set altitude, adjusting the collective blade pitch to the pre-set maximum collective blade pitch via the at least one governor such that momentum is conserved, causing a descent rate of the aircraft to decrease as the aircraft approaches a ground surface.
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公开(公告)号：US20240329662A1
公开(公告)日：2024-10-03
申请号：US18617819
申请日：2024-03-27
发明人： Bon Aizawa
IPC分类号： G05D1/85 , B64C19/02 , B64C27/72 , G05D109/25
CPC分类号： G05D1/854 , B64C19/02 , B64C27/72 , G05D2109/25
摘要： When any one of a plurality of first rotors (VTOL rotors) fails, a rotor controller (a VTOL rotor controller) executes thrust increase control for increasing the thrust generated by an adjacent first rotor that is the first rotor adjacent to the failed first rotor, without making the adjacent first rotor cause the thrust variation for vibration suppression control, and executes the vibration suppression control in a manner so that one or more second rotors (VTOL rotors) bear the burden of the thrust variation that has been borne by the adjacent first rotor.
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公开(公告)号：US20240272652A1
公开(公告)日：2024-08-15
申请号：US18630205
申请日：2024-04-09
申请人： DENSO CORPORATION
发明人： Masato FUKUSHI , Shun Sugita
IPC分类号： G05D1/85 , G05D1/652 , G05D1/654 , G05D109/25
CPC分类号： G05D1/854 , G05D1/652 , G05D1/654 , G05D2109/254
摘要： A flight control device performs flight control processing for causing a vertical takeoff and landing aircraft to fly. When a drive device abnormal occurs during vertical takeoff, the flight control device performs a takeoff processing in flight control processing. The flight control device performs an abnormal stop processing in the takeoff processing. In the abnormal stop processing, a processing for stopping the driving of the abnormal drive device is performed. The flight control device performs a correction increase processing. In the correction increase processing, the output of at least one normal drive device is increased. In the correction increase processing, for example, the output of an adjacent drive device among a plurality of normal drive devices is increased. The adjacent drive device is a normal drive device adjacent to the abnormal drive device in a circumferential direction of a yaw axis.
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