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公开(公告)号：US20240359820A1
公开(公告)日：2024-10-31
申请号：US18765393
申请日：2024-07-08
申请人： DENSO CORPORATION
发明人： Shinsuke KAWADU
CPC分类号： B64D45/00 , B64C27/006 , B64C27/08 , B64C39/02 , B64D2045/0085
摘要： An abnormality warning system provides an abnormality warning for multiple motor systems that drive a motor used correspondingly to each of multiple rotors included in an electric aircraft. The abnormality warning system includes an abnormality determination unit and a warning level setting unit. The abnormality determination unit determines an abnormal one of the motor systems. The warning level setting unit sets a warning level to warn abnormality, based on at least position information of the rotor in the electric aircraft or the usage of the rotor corresponding to a motor system determined to be abnormal by the abnormality determination unit.
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公开(公告)号：US20240354461A1
公开(公告)日：2024-10-24
申请号：US18442369
申请日：2024-02-15
申请人： AIRBUS HELICOPTERS
发明人： Guillaume DUMUR , Julien FRAENZEL
摘要： A method for simulating an engine failure on a rotorcraft comprising several engines for setting a rotary wing in motion. The method comprises a training mode that comprises controlling each engine with a controller in order to simulate an engine failure, this control comprising limiting the power of each engine to a respective control restriction value. The training mode comprises the following steps: i) determining, with the controller, a maximum mass at least as a function of external conditions, and an initial mass of the rotorcraft at least as a function of an unladen mass of the rotorcraft, a mass of a crew present in the rotorcraft, and an estimated mass of fuel on-board; ii) comparing, with the controller, the initial mass with the maximum mass; and iii) determining, with the controller, each control restriction value as a function of the comparison.
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公开(公告)号：US12106672B2
公开(公告)日：2024-10-01
申请号：US17457621
申请日：2021-12-03
CPC分类号： G08G5/0043 , B64C27/00 , B64C39/024 , B64G1/00 , G05D1/042 , G06T7/593 , G08G5/003 , G06T2207/10012 , G06T2207/10032
摘要： A method, apparatus, system, and computer program product for operating an aerial imaging system. A first altitude of a first aircraft is determined, by a computer system, using first images of a key point generated by the first aircraft during a flight and stereo depth triangulation. The first altitude is compared with a second altitude of a second aircraft determined by the second aircraft, by the computer system, to form a comparison. An offset between the first altitude and the second altitude is determined, by the computer system, using the comparison. At least one of the first altitude or the second altitude is adjusted based on the offset. A plurality of images of a region from the first aircraft at the first altitude and from the second aircraft at the second altitude is obtained.
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公开(公告)号：US12065262B2
公开(公告)日：2024-08-20
申请号：US17979863
申请日：2022-11-03
申请人： DENSO CORPORATION
发明人： Shinsuke Kawadu
CPC分类号： B64D45/00 , B64C27/006 , B64D2045/0085
摘要： An abnormality warning system provides an abnormality warning for multiple motor systems that drive a motor used correspondingly to each of multiple rotors included in an electric aircraft. The abnormality warning system includes an abnormality determination unit and a warning level setting unit. The abnormality determination unit determines an abnormal one of the motor systems. The warning level setting unit sets a warning level to warn abnormality, based on at least position information of the rotor in the electric aircraft or the usage of the rotor corresponding to a motor system determined to be abnormal by the abnormality determination unit.
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5.发明公开公开(公告)号：US20240239481A1
公开(公告)日：2024-07-18
申请号：US18097747
申请日：2023-01-17
申请人： BETA AIR, LLC
发明人： Herman Wiegman , Kyle Clark
IPC分类号： B64C27/00
CPC分类号： B64C27/001 , B64C29/0008
摘要： A system of vibration mitigation for a propulsor and a boom in an electric aircraft is disclosed. The system may include at least a propulsor, wherein the at least a propulsor is configured to propel an electric aircraft through a fluid medium and the at least a propulsor comprises a driving frequency from 0 to its maximum driving frequency that is generated as a function of a rotational speed of the at least a propulsor when the at least a propulsor propels the electric aircraft through the fluid medium. The system may include at least a boom, wherein the at least a boom comprises the at least a propulsor mounted on the at least a boom and a natural frequency of the at least a boom, wherein the natural frequency is a fraction of the maximum driving frequency of the at least a propulsor.
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公开(公告)号：US11999470B2
公开(公告)日：2024-06-04
申请号：US17236423
申请日：2021-04-21
发明人： Fangming Ye
IPC分类号： B64C27/32 , B64C11/00 , B64C11/10 , B64C27/00 , B64C27/08 , B64C39/02 , B64D35/00 , B64D35/02 , B64U10/10 , B64U30/20
CPC分类号： B64C27/32 , B64C11/00 , B64C11/10 , B64C27/006 , B64C27/08 , B64C39/024 , B64D35/00 , B64D35/02 , B64U10/10 , B64U30/20
摘要： A rotor assembly includes a propeller, a motor, and a connection assembly. The motor includes a stator and a rotator rotatable with respect to the stator. The connection assembly is configured to connect the propeller to the motor and includes a locking member that is arranged between the propeller and the motor. The locking member is configured to rotate with respect to the rotator and the propeller in a rotation direction identical to a rotation direction of the propeller in operation to lock the propeller to the motor.
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公开(公告)号：US20240166343A1
公开(公告)日：2024-05-23
申请号：US18514175
申请日：2023-11-20
IPC分类号： B64C27/00
CPC分类号： B64C27/001 , B64C2027/004
摘要： An anti-resonance system for a blade defining an elongated channel therein and affixed to a helicopter rotor includes a moveable mass disposed within the elongated channel of the blade so as to be able to slide along elongated channel. A moving device coupled to the moveable mass is configured to move the moveable mass within the elongated channel. A controller is configured to cause the moving device to move the moveable mass to a selected position within the elongated channel so as to avoid the additional resonance vibrations of the blade during a rotor speed change. In a method of avoiding resonance of a helicopter blade, a current rotational speed of the blade is determined. A position of the movable mass so as to avoid a resonance point at a current rotational speed is obtained. The moveable mass is moved to the position.
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公开(公告)号：US11983018B2
公开(公告)日：2024-05-14
申请号：US17603199
申请日：2021-10-12
IPC分类号： B64C11/48 , B64C11/50 , B64C27/00 , B64C27/02 , B64C27/10 , B64C27/12 , B64C27/14 , B64C27/22 , B64C27/26 , B64D31/00 , G05D1/00 , B64C27/82 , B64D27/24 , H02K1/27
CPC分类号： G05D1/0858 , B64C11/50 , B64C27/006 , B64C27/02 , B64C27/021 , B64C27/025 , B64C27/027 , B64C27/028 , B64C27/10 , B64C27/12 , B64C27/14 , B64C27/22 , B64C27/26 , B64D31/00 , B64C11/48 , B64C2027/8236 , B64D27/24 , H02K1/27
摘要： A multi-rotor aircraft includes a fuselage, a propulsion engine coupled to the fuselage that generates thrust to propel the aircraft along a first vector during forward flight, and rotors coupled to the fuselage, each rotor comprising blades, each rotor coupled to a motor, and each motor configured to supply power to and draw power from the coupled rotor. The aircraft includes a flight control system configured to control the motors coupled to the rotors in a power managed regime in which a net electrical power, consisting of a sum of the power being supplied to or drawn from each rotor by its motor, is maintained within a range determined by a feedback control system of the flight control system. The flight control system can also be leveraged to adjust rotor control inputs to modify at least one of thrust, roll, pitch, or yaw of the multi-rotor aircraft.
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公开(公告)号：US11941141B2
公开(公告)日：2024-03-26
申请号：US17952603
申请日：2022-09-26
申请人： ALETHOS, INC.
IPC分类号： G06F21/62 , B64C27/00 , B64C27/08 , B64C27/12 , B64C27/57 , B64D31/10 , B64D31/12 , B64D45/00 , G06F21/30 , G06F21/44 , G06F21/60 , H04L9/08 , H04L9/40
CPC分类号： G06F21/6218 , B64C27/006 , B64C27/08 , B64C27/12 , B64C27/57 , B64D31/10 , B64D31/12 , B64D45/00 , G06F21/30 , G06F21/445 , G06F21/602 , G06F21/604 , G06F21/6209 , G06F21/6245 , H04L9/0866 , H04L63/0407 , H04L63/10 , B64D2045/0085 , H04L63/061 , H04L63/102 , H04L2209/60 , H04L2463/061
摘要： Methods and systems are configured to store user data and control access to the user data, wherein the data is stored remotely from the user (such as external to a user's computing device) and the user's data is maintained anonymously. Content is stored in association with a user identifier and access by third parties is controlled by linked third party identifiers.
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公开(公告)号：US20240059406A1
公开(公告)日：2024-02-22
申请号：US17937608
申请日：2022-10-03
CPC分类号： B64C27/006 , B64C27/001 , B64D45/08
摘要： A system and method for detecting ground resonance and providing a warning regarding the same includes supplying, from an inertial navigation system (INS), inertial data indicative of an inertial profile of a rotorcraft, and supplying, from a sensor system, sensor data that indicates when the rotorcraft is at least partially on a landing surface. The sensor data is processed, in a processing system, to determine when the rotorcraft is at least partially on the landing surface, and when the rotorcraft is determined to be at least partially on the landing surface, the inertial data is processed, in the processing system to determine when the inertial profile of the rotorcraft indicates ground resonance may occur. Upon determining that ground resonance may occur, one or more alert signals are generated in the processing system.
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