公开(公告)号：US11117653B2

公开(公告)日：2021-09-14

申请号：US15983752

申请日：2018-05-18

申请人： Textron Innovations Inc.

发明人： Charles Eric Covington ,  Bradley Don Linton ,  Thomas Earl Johnson, Jr. ,  Luke Dafydd Gillett ,  Robert Earl Worsham, II ,  Jillian Samantha Alfred

IPC分类号： B64C27/56 ,  G05G5/03 ,  B64C27/68 ,  B64C27/57

摘要： An rotorcraft including a pilot control, a pilot control position sensor connected to the pilot control and operable to generate a position signal indicating a position of the pilot control, a flight control computer (FCC) in signal communication with the pilot control position sensor and operable to provide a tactile cue in the pilot control in response to the position signal indicating the position of the pilot control exceeds a threshold associated with an operating limit, and further operable to determine a tactile cueing value for the tactile cue according to a relationship between the position of the pilot control and the threshold, and generate a cue control signal according to the tactile cueing value, and a tactile cue element connected to the pilot control and in signal communication with the FCC and operable to control action of the pilot control in response to the cue control signal.

公开(公告)号：US20210253232A1

公开(公告)日：2021-08-19

申请号：US17252502

申请日：2019-06-14

申请人： The Texas A&M University System

发明人： Moble Benedict ,  David Coleman ,  Atanu Halder ,  Bochan Lee ,  Andrew Riha ,  Farid Saemi ,  Carl Runco ,  Vishaal Subramanian ,  Eric Greenwood ,  Vinod Lakshminarayan

IPC分类号： B64C27/68 ,  B64C27/605 ,  B64D27/24 ,  B64D17/80 ,  B64C27/467 ,  B60L50/60 ,  B60L15/20 ,  B64D31/00

摘要： A hover-capable aircraft includes a body including a tubular strut, a first rotor assembly rotatably coupled to the body and positioned about the strut, wherein the first rotor assembly includes a first plurality of circumferentially-spaced blades, a first actuation assembly including a first plurality of electronically controlled actuators coupled to a first swashplate and configured to control the movement of the first swashplate relative to the body, and a control system coupled to the body and configured to control the first plurality of actuators, wherein the control system includes a cable extending through a passage formed in the tubular strut and in signal communication with the first plurality of actuators.

公开(公告)号：US20210232159A1

公开(公告)日：2021-07-29

申请号：US17158436

申请日：2021-01-26

申请人： Textron Innovations Inc.

发明人： Mark Berkley ,  David Fuessel ,  Steven Welch ,  David Meek

IPC分类号： G05D1/08 ,  B64D47/00 ,  H02J3/14 ,  B64C13/50 ,  B64C27/68 ,  G06F1/26

摘要： A rotorcraft includes an avionics control unit (ACU) and multiple power distribution units (PDUs) electrically connected to an electrical bus, wherein each PDU of the multiple PDUs is electrically connected to a respective multiple electrical loads, and wherein each PDU of the multiple PDUs is configured to receive commands from the ACU to couple or decouple one or more of its respectively connected multiple electrical loads from the electrical bus. The ACU is configured to send commands to the multiple PDUs to couple or decouple a first set of electrical loads and to couple or decouple a second set of electrical loads from the electrical bus, wherein the coupling or decoupling of the first set and the coupling or decoupling the second set is based on a first priority of the first set and a second priority of the second set, respectively.

公开(公告)号：US10676182B2

公开(公告)日：2020-06-09

申请号：US15655665

申请日：2017-07-20

申请人： Sikorsky Aircraft Corporation

发明人： Timothy F. Lauder

IPC分类号： B64C27/10 ,  B64C27/35 ,  B64C27/52 ,  B64C27/59 ,  B64D27/24 ,  B64C27/68 ,  B64C27/12

摘要： An electric propulsion system includes a static mast fixed to the airframe and a secondary mast positioned in overlapping arrangement with the static mast. The secondary mast defines an axis of rotation. An elastomeric bearing is arranged at an interface between the static mast and the secondary mast. An actuator assembly includes at least one actuator connected to the secondary mast. The actuator assembly is operable to pivot the secondary mast relative to the axis of rotation.

公开(公告)号：US10507910B2

公开(公告)日：2019-12-17

申请号：US15441427

申请日：2017-02-24

申请人： The Boeing Company

发明人： Donald Guzman

IPC分类号： B64C27/59 ,  B64C13/28 ,  B64C27/56 ,  B64C27/68 ,  B64C27/82 ,  F16H21/02

摘要： Dual-input mechanical bypass linkage apparatus and methods are disclosed. An example dual-input mechanical bypass linkage apparatus includes a primary link and a secondary link spaced apart from the primary link. The dual-input mechanical bypass linkage apparatus further includes a first extension link extending between the primary link and the secondary link. The first extension link is coupled to the primary link, to the secondary link and to a first input link. The first input link is coupled to a first actuator. The primary link is coupled to a second input link. The second input link is coupled to a second actuator. The dual-input mechanical bypass linkage apparatus further includes a second extension link spaced apart from the first extension link and extending between the primary link and the secondary link. The second extension link is coupled to the primary link, to the secondary link and to an output link.

公开(公告)号：US10351230B2

公开(公告)日：2019-07-16

申请号：US15329118

申请日：2015-07-17

申请人： SIKORSKY AIRCRAFT CORPORATION

发明人： Igor Cherepinsky ,  Joseph T. Driscoll

IPC分类号： G05D1/06 ,  B64C27/57 ,  B64C13/50 ,  B64C27/06 ,  B64C27/68

摘要： According to one aspect, a method of initial rotor state compensation for a rotorcraft includes determining a vehicle attitude of the rotorcraft prior to takeoff of the rotorcraft. A rotor state compensation is computed based on the vehicle attitude. A plurality of rotor servos is commanded to an initial rotor state based on a nominal rotor neutral position value in combination with the rotor state compensation to establish a predetermined takeoff trajectory of the rotorcraft.

公开(公告)号：US20180346110A1

公开(公告)日：2018-12-06

申请号：US16109170

申请日：2018-08-22

申请人： Merlin Technology Inc.

发明人： John E. Mercer ,  Marc Feifel ,  Mark Marvin ,  Nicholas Albion

IPC分类号： B64C27/68 ,  F16F15/121 ,  B64C13/18 ,  B64C27/58 ,  B64C27/57 ,  B64C13/04 ,  B64C27/59 ,  B64C13/30

CPC分类号： B64C27/58 ,  B64C13/0421 ,  B64C13/18 ,  B64C13/343 ,  B64C27/57 ,  F16F15/121 ,  Y02T50/44

摘要： An autopilot actuator includes first and second motors each including a rotatable motor output shaft such that either one or both of the motors can drive an actuator output shaft. An autopilot main unit enclosure is removably mounted to the helicopter proximate to a cyclic control and commonly houses autopilot actuators as well as main autopilot electronics. A cyclic vibration isolator is removably supported by an actuator shaft for co-rotation and coupled to the cyclic control to attenuate a cyclic vibration frequency at the actuator shaft while output rotations of the actuator shaft below a resonant frequency are coupled to the cyclic control. A force limited link includes first and second ends and a variable length between. The force limited link having a relaxed length when less than an unseating force is applied and the variable length changes when an applied force exceeds the unseating force to permit pilot override.

公开(公告)号：US10012273B2

公开(公告)日：2018-07-03

申请号：US15107763

申请日：2015-02-02

申请人： SOCIÉTÉ 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

IPC分类号： F16D37/00 ,  F16D37/02 ,  F16D27/14 ,  B64D31/14 ,  B64D35/04 ,  B64C27/08 ,  B64C13/28 ,  B64C27/12 ,  B64C27/56 ,  B64C27/64 ,  B64C27/68 ,  B64C27/78 ,  B64D35/02 ,  B64C27/605 ,  F16H25/20

CPC分类号： F16D37/008 ,  B64C13/341 ,  B64C27/605 ,  B64C27/64 ,  B64D31/14 ,  F16D37/02 ,  F16D2037/007 ,  F16H25/20 ,  F16H2025/2059 ,  Y02T50/44 ,  Y10T74/18704

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.

公开(公告)号：US09656746B2

公开(公告)日：2017-05-23

申请号：US14609905

申请日：2015-01-30

申请人： Bell Helicopter Textron Inc.

发明人： Geoffrey C Latham ,  Carlos A Fenny ,  Jean-Sébastien Plante ,  Brady Atkins ,  Guifré Julio ,  Marc Denninger ,  Charles Eric Covington ,  Paul Wilson

IPC分类号： B64C27/68 ,  B64C27/56 ,  B64D43/00

CPC分类号： B64C27/68 ,  B64C27/56 ,  B64D43/00

摘要： According to one embodiment, a trim actuator for a pilot input device includes a driven member and a driving member configured to receive mechanical energy from a power source. A magnetorheological (MR) fluid is disposed between the driving member and the driven member and configured to transmit a variable amount of mechanical energy from the driving member to the driven member. An output member configured to be coupled between the driven member and the pilot input device. A magnetic circuit configured to deliver a magnetic field towards the MR fluid. The magnetic circuit is configured to control movement of the pilot input device by varying the strength of the magnetic field delivered towards the first MR fluid.

公开(公告)号：US20170129599A1

公开(公告)日：2017-05-11

申请号：US15415469

申请日：2017-01-25

申请人： Merlin Technology Inc.

发明人： John E. Mercer ,  Marc Feifel ,  Mark Marvin ,  Nicolas Albion

IPC分类号： B64C27/68 ,  B64C27/57 ,  B64C13/30 ,  B64C13/18

CPC分类号： B64C27/68 ,  B64C13/04 ,  B64C13/18 ,  B64C13/30 ,  B64C27/57 ,  B64C27/58 ,  B64C27/59 ,  F16F15/121 ,  Y02T50/44

摘要： An autopilot actuator includes first and second motors each including a rotatable motor output shaft such that either one or both of the motors can drive an actuator output shaft. An autopilot main unit enclosure is removably mounted to the helicopter proximate to a cyclic control and commonly houses autopilot actuators as well as main autopilot electronics. A cyclic vibration isolator is removably supported by an actuator shaft for co-rotation and coupled to the cyclic control to attenuate a cyclic vibration frequency at the actuator shaft while output rotations of the actuator shaft below a resonant frequency are coupled to the cyclic control. A force limited link includes first and second ends and a variable length between. The force limited link having a relaxed length when less than an unseating force is applied and the variable length changes when an applied force exceeds the unseating force to permit pilot override.