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公开(公告)号：US11960314B1
公开(公告)日：2024-04-16
申请号：US17144423
申请日：2021-01-08
发明人： Charles Culp , Greg Kemner , Bob Hale
摘要： The control system for attachment to a collective lever in a rotorcraft which comprises a body with an extended horn portion which is generally contoured to provide for a place to rest the palm and grip the collective lever at the end in the form of an open spherical grip as opposed to the more traditional cylindrical grip used to grasp the throttle and/or collective lever directly. The control system generally includes a plurality of controls which can be manipulated by any or all of the four fingers of the hand and the thumb without need to substantially move the palm. The collective lever can also be moved without having to remove the hand from the control system or the fingers or thumb from the controls.
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公开(公告)号：US11708159B2
公开(公告)日：2023-07-25
申请号：US17546370
申请日：2021-12-09
申请人： Urbineer Inc
CPC分类号： B64C29/0033 , B60L53/53 , B64C25/10 , B64C27/56 , B64D9/00 , B64D27/24 , B64D29/02 , B60L2200/10
摘要： According to at least one exemplary embodiment, a method, system and apparatus for an aircraft may be shown and described. An exemplary embodiment may be an autonomous aircraft which can vertically takeoff and land (VTOL). The VTOL aircraft may have a modular pod which carries a removable payload. The entire VTOL aircraft may be portable. An exemplary embodiment may fit into a standard sized freight container. A propulsion system may be based on distributed electric propulsion. An exemplary embodiment may implement variable pitch propellers and collective pitch variation.
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公开(公告)号：US11673680B2
公开(公告)日：2023-06-13
申请号：US17111813
申请日：2020-12-04
申请人： AIRBUS HELICOPTERS
发明人： Paul Eglin , Remy Huot , Antoine Conroy
摘要： The present invention relates to a control method in case of engine failure of a hybrid helicopter having a power plant connected to at least one lift rotor and to at least one propeller, said lift rotor having a plurality of first blades and said at least one propeller having a plurality of second blades. The method comprises the following steps: (i) measuring a forward speed of the hybrid helicopter, (ii) on condition that said forward speed is greater than a first speed threshold and that each engine has failed, automatically implementing a first emergency piloting mode comprising a step for automatic reduction by an automatic piloting system of a pitch of said second blades toward an objective pitch making said at least one propeller produce a motive power which is transmitted to the lift rotor.
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公开(公告)号：US11572163B2
公开(公告)日：2023-02-07
申请号：US16903047
申请日：2020-06-16
申请人： AIRBUS HELICOPTERS
发明人： Kamel Abdelli
摘要： A flight control handle suitable for being operated by a pilot, the flight control handle including a stick-forming grip carrying an end box that is provided with a hollow shell provided with a top face, at least one control projecting towards an external environment of the top face. The flight control handle has a controllable member suitable for being actuated by a person, the end box including at least one electronic wall incorporating an electronic circuit, the electronic circuit including at least one sensor that co-operates with the controllable member.
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公开(公告)号：US11281236B2
公开(公告)日：2022-03-22
申请号：US16257651
申请日：2019-01-25
摘要： A yaw control system for a rotorcraft featuring a floor mounted pair of pedals configured to measure an up and down motion of a pair of pedals and utilize that up and down motion as a yaw moment control input. The pair of pedals can rock laterally, fore and aft, or vertically. The pair of pedals can be mechanically interconnected to other pairs of pedals or electrically interconnected to duplicate motion across pairs of pedals.
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公开(公告)号：US20210253262A1
公开(公告)日：2021-08-19
申请号：US17111813
申请日：2020-12-04
申请人： AIRBUS HELICOPTERS
发明人： Paul EGLIN , Remy HUOT , Antoine CONROY
摘要： The present invention relates to a control method in case of engine failure of a hybrid helicopter having a power plant connected to at least one lift rotor and to at least one propeller, said lift rotor having a plurality of first blades and said at least one propeller having a plurality of second blades. The method comprises the following steps: (i) measuring a forward speed of the hybrid helicopter, (ii) on condition that said forward speed is greater than a first speed threshold and that each engine has failed, automatically implementing a first emergency piloting mode comprising a step for automatic reduction by an automatic piloting system of a pitch of said second blades toward an objective pitch making said at least one propeller produce a motive power which is transmitted to the lift rotor.
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公开(公告)号：US10926872B2
公开(公告)日：2021-02-23
申请号：US16510897
申请日：2019-07-13
发明人： John E. Mercer , Nicholas Albion , Mark Bartel , Marc Feifel , Mark Marvin
IPC分类号： B64C27/57 , B64C27/56 , G05D1/10 , B64C13/18 , G05D1/08 , G05D1/00 , B64C27/59 , B64C27/64 , B64C27/68
摘要： A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.
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公开(公告)号：US10788085B2
公开(公告)日：2020-09-29
申请号：US15996020
申请日：2018-06-01
申请人： SOCIETE DE COMMERCIALISATION DES PRODUITS DE LA RECHERCHE APPLIQUÉE SOCPRA SCIENCES ET GÉNIE S.E.C
发明人： Jean-Sebastien Plante , Marc Denninger , Patrick Chouinard , Guifre Julio , Jean-Philippe Lucking Bigue , Nicolas Huppe , Jean-Francois Desrosiers , Raphael Pilon , Alexandre Landry-Blais
IPC分类号： F16D37/00 , F16D27/14 , B64C27/08 , B64C27/56 , B64C27/605 , B64C27/78 , B64D35/02 , B64D35/04 , F16D37/02 , B64C13/28 , B64C27/12 , B64C27/64 , B64C27/68 , B64D31/14
摘要： A magnetorheological fluid clutch apparatus comprises an input rotor adapted to be coupled to a power input, the input rotor having a first set of at least one input shear surface, and a second set of at least one output shear surface. An output rotor is rotatably mounted about the input rotor for rotating about a common axis with the input rotor, the output rotor having a first set of at least one output shear surface, and a second set of at least one output shear surface, the first sets of the input rotor and the output rotor separated by at least a first annular space and forming a first transmission set, the second sets of the input rotor and the output rotor separated by at least a second annular space and forming a second transmission set. Magnetorheological fluid is in each of the annular spaces, the MR fluid configured to generate a variable amount of torque transmission between the sets of input rotor and output rotor when subjected to a magnetic field. A pair of electromagnets are configured to deliver a magnetic field through the MR fluid, the electromagnets configured to vary the strength of the magnetic field, whereby actuation of at least one of the pair of electromagnets results in torque transmission from the at least one input rotor to the output rotor.
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公开(公告)号：US20200269974A1
公开(公告)日：2020-08-27
申请号：US16284232
申请日：2019-02-25
申请人： The Boeing Company
发明人： Todd M. Waaramaa
摘要： Systems and methods for compactly mounted cyclic flight control for a rotorcraft. One embodiment is an apparatus that includes a stick base assembly coupled with a cyclic stick and configured to rotate with respect to a mounting frame to control a pitch and a roll of the rotorcraft. A cyclic housing is pivotably coupled with the mounting frame for rotation about a pitch axis to control pitch, and coupled with a pitch actuator having a pitch force sensor to measure its resistance to rotation. The cyclic housing supports the stick base assembly for independent rotation of the stick base assembly about a roll axis to control roll, and the stick base assembly couples with a roll actuator having a roll force sensor to measure its resistance to rotation.
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公开(公告)号：US10261517B2
公开(公告)日：2019-04-16
申请号：US15484994
申请日：2017-04-11
发明人： Christopher Mike Bothwell , Sung Kyun Kim , Jillian Samantha Alfred , Robert Earl Worsham, II , Luke Dafydd Gillett , Morganne Cody Klein
摘要： A rotorcraft including a flight control computer (FCC) providing a vertical speed hold for the rotorcraft, a collective control, and a collective trim motor connected to the collective control. The collective trim motor moves the collective control according to a collective set command generated by the FCC according to a target vertical speed and when the FCC determines the collective control is in-detent. A collective position sensor is connected to the collective control. The collective position sensor generates, and sends to the FCC, a collective position signal indicating the position of the collective control. A flight control device controls a flight parameter of the rotorcraft in response to a flight control device control signal received from the FCC. The FCC generates the flight control device control signal according to the collective position signal, and sends the flight control device control signal to a flight control device.
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