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公开(公告)号：US11480460B2
公开(公告)日：2022-10-25
申请号：US16508696
申请日：2019-07-11
申请人： AIRBUS HELICOPTERS
发明人： Herve Morel , Jonathan Rodriguez
摘要： A method of analyzing a vibratory signal derived from rotation of at least one moving part belonging to a rotary mechanism forming all or part of a drive train for transmitting drive torque, the rotary mechanism being fitted to an aircraft and the method comprising at least one first measurement step including measuring vibration in at least one direction and generating a vibratory signal representative of the operation of the rotary mechanism as a function of time, the first measurement step being performed by means of at least one vibration sensor; and at least one second measurement step including measuring an angular position of the moving part, the moving part having at least one degree of freedom to move in rotation about a respective axis of rotation Z. Such an analysis method makes it possible to determine at least one usable range for the vibratory signal.
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72.发明授权公开(公告)号：US11465733B2
公开(公告)日：2022-10-11
申请号：US17113424
申请日：2020-12-07
发明人： Christian Reichensperger , Uwe Kiesewetter , Petr Schejbal , Lukasz Paluszek , Klaus Kicker , Martin Blacha
摘要： A multirotor aircraft with an airframe that extends in a longitudinal direction, and with at least one thrust producing unit for producing thrust in a predetermined thrust direction, wherein the at least one thrust producing unit comprises a shrouding that is associated with at least one rotor assembly comprising at least one electrical engine, wherein the shrouding defines a cylindrical air duct that is axially delimited by an air inlet region and an air outlet region, wherein a cantilever is mounted at a leading edge region of the cylindrical air duct to the shrouding such that the cantilever is arranged inside of the cylindrical air duct and oriented at least essentially in parallel to the longitudinal direction, wherein the shrouding comprises a forward beam which connects the cantilever to the airframe, the forward beam being arranged outside of the cylindrical air duct and comprising a forward flange that is rigidly attached to the airframe, wherein the at least one electrical engine is mounted to the cantilever, and wherein the cylindrical air duct is provided in opened perimeter configuration, the shrouding being at least partly cut-off in the opened perimeter configuration at a trailing edge region of the cylindrical air duct over a predetermined opening angle.
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公开(公告)号：US20220309786A1
公开(公告)日：2022-09-29
申请号：US17696967
申请日：2022-03-17
申请人： AIRBUS HELICOPTERS
IPC分类号： G06V20/20 , G06V10/778 , G06V10/776 , G06V20/10 , G06V10/20 , G06V10/82
摘要： A method for training an artificial intelligence intended to identify a predetermined object in the environment of an aircraft in flight. The method comprises steps of identifying at least one predetermined object in representations representing at least one predetermined object and its environment, establishing a training set and a validation set, the training set and the validation set comprising a plurality of representations from the representations representing at least one predetermined object, training the artificial intelligence with the training set and validating the artificial intelligence with the validation set. The artificial intelligence may then be used, in a method for assisting the landing of the aircraft, to identify a helipad where the landing operation may be performed. The artificial intelligence may also be used, in a method for avoiding a cable, to identify cables situated on or close to the trajectory of the aircraft.
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公开(公告)号：US20220306308A1
公开(公告)日：2022-09-29
申请号：US17695933
申请日：2022-03-16
申请人： AIRBUS HELICOPTERS
发明人： Stephane CERQUEIRA
摘要： A method for controlling an aircraft with a rotary wing provided with a power plant comprising a plurality of engines, the aircraft comprising a human-machine interface controlling a control member capable of acting on a longitudinal acceleration of the aircraft. During the economy operating mode during which one of the engines does not supply power, the method comprises measuring a forward speed of the aircraft, and adjusting an authority of the human-machine interface over the longitudinal acceleration with a flight control computer as a function of the forward speed.
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公开(公告)号：US11454517B2
公开(公告)日：2022-09-27
申请号：US17228080
申请日：2021-04-12
申请人： AIRBUS HELICOPTERS
发明人： Jean Paul Petillon
摘要： A system and to a method of analyzing and monitoring interfering movements of an inertial unit of an aircraft during a stage of statically aligning the inertial unit. During the static alignment stage, measurements of the velocity of the aircraft relative to the ground are acquired, and states of a mirror process having a model that is close to the model of the process of aligning the inertial unit are estimated. The states of the mirror process are estimated from observations constituted by the measurements of velocity relative to the ground. Finally, the estimates of the states are compared with respective validation thresholds in order to validate or not validate said alignment of the inertial unit.
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76.发明授权公开(公告)号：US11433992B2
公开(公告)日：2022-09-06
申请号：US16037198
申请日：2018-07-17
申请人： AIRBUS HELICOPTERS
摘要： A rotorcraft having an airframe, the airframe carrying at least one rotor that contributes to providing the rotorcraft with lift and/or propulsion, the rotorcraft having at least one undercarriage. The at least one undercarriage comprises at least one inclined wheel undercarriage, the inclined wheel undercarriage having an undercarriage leg carrying at least one axle, the at least one axle carrying at least one wheel, the at least one wheel not being in contact with any other wheel, the at least one wheel presenting positive or negative camber when the at least one wheel touches the ground and independently of forces exerted by said airframe on the inclined wheel undercarriage.
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公开(公告)号：US11421464B2
公开(公告)日：2022-08-23
申请号：US16874863
申请日：2020-05-15
发明人： Johannes Markmiller , Daniel Stegmair , Dirk Trott
IPC分类号： G08B13/08 , E05F15/60 , B64C1/14 , B64D25/14 , E05B47/00 , E05B17/10 , F16H1/10 , F16H1/16 , F16H1/28 , F16H1/32 , F16H49/00
摘要： An aircraft door, and, more particularly, to an electromechanical door system for operating an aircraft door that closes an opening in the outer hull of an aircraft, as well as to a method of operating an electromechanical door system of an aircraft door that closes an opening in the outer hull of an aircraft. The electromechanical door system may be adapted for operating in a normal opening mode, an emergency opening mode, and a closing mode. If desired, the electromechanical door system may include a lifting and lowering lever, a lifting and lowering electric motor, and a gearbox that transmits a force from the lifting and lowering electric motor to the lifting and lowering lever.
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公开(公告)号：US20220186792A1
公开(公告)日：2022-06-16
申请号：US17530575
申请日：2021-11-19
申请人： AIRBUS HELICOPTERS
发明人： Sebastien ROBERT , Adrien ESCOFFIER
IPC分类号： F16D41/067
摘要： A free-wheel comprising a driving part and a driven part that are able to rotate about an axis of rotation, the free-wheel comprising a cage carrying at least one rolling element arranged in a connection space, the free-wheel having at least one lubrication device conveying a lubricating fluid into the connection space. The free-wheel comprises at least one variable-opening barrier arranged radially between the driving part and the driven part and longitudinally against the connection space, the opening being indexed on a relative position of the cage and of the driving part.
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公开(公告)号：US20220154762A1
公开(公告)日：2022-05-19
申请号：US17445321
申请日：2021-08-18
发明人： Rupert PFALLER , Moritz BUESING
摘要： A drive shaft made from composite materials that comprises a hollow body and a flange that is integrally formed with the hollow body. The hollow body is adapted to rotating around an associated rotation axis and is made of a first composite material. The flange is made of a second composite material and arranged at an axial end of the hollow body. The flange comprises at least two separate plates that branch out from the hollow body at the axial end. The flange further comprises a mounting section that is configured to be mounted to an external component and comprises a plurality of holes that is adapted to accommodate coupling means.
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公开(公告)号：US20220137645A1
公开(公告)日：2022-05-05
申请号：US17504079
申请日：2021-10-18
申请人： AIRBUS HELICOPTERS
发明人： Alexandre VICQ , Frederic PEREZ
摘要： An architecture for monitoring at least one aircraft. The architecture comprises an avionics system configured to generate avionics data during use of the aircraft; a mobile electronic device including an analysis unit configured to convert at least one maintenance operation into operational data; and an alerter configured to display at least one item of monitoring information; and a cloud computing infrastructure. The analysis unit and the alerter are configured to implement a local operating mode and an operating mode connected to the cloud computing infrastructure.
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