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

IPC分类号： B64D31/06 ,  B64D31/14 ,  B64C27/06 ,  B64D27/02 ,  B64C27/56

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.

公开(公告)号：US20220187849A1

公开(公告)日：2022-06-16

申请号：US17540780

申请日：2021-12-02

申请人： AIRBUS HELICOPTERS

发明人： Paul EGLIN ,  Remy HUOT ,  Martin EMBACHER ,  Antoine CONROY

IPC分类号： G05D1/08 ,  B64C27/06 ,  B64C11/00 ,  B64C5/10 ,  B64C13/24 ,  B64C13/16 ,  B64C27/56 ,  B64C11/30 ,  B64C27/22

摘要： A method for controlling a hybrid helicopter having at least one lifting rotor, at least one forward-movement propeller and an empennage provided with at least one moveable empennage surface. The method includes the following steps: using a main sensor to determine a current value of a rotor parameter conditioning a current power drawn by the lifting rotor, using an estimator to determine a current setpoint of the rotor parameter, adjusting a position of the moveable empennage surface using a deflection controller as a function of the current value and of current setpoint.

公开(公告)号：US20210291975A1

公开(公告)日：2021-09-23

申请号：US17169668

申请日：2021-02-08

申请人： AIRBUS HELICOPTERS

发明人： Paul EGLIN ,  Remy HUOT

IPC分类号： B64C27/78 ,  B64C27/22 ,  B64C27/00 ,  B64C27/57

摘要： A method of providing torque protection and/or thrust protection for the or each propeller of a hybrid helicopter. The hybrid helicopter includes a control system connected to the blades of each propeller and a thrust control configured to generate an order for modifying a pitch of the blades, which order is transmitted to the control system, the propeller(s) being driven in rotation by a mechanical transmission system of the hybrid helicopter. The method includes a step of having the control system keep the pitch of the blades of a propeller within at least one control envelope relating to a thrust generated by the propeller or to a torque exerted in the mechanical transmission system. In this way, the pitch of the blades of each propeller is kept between a lower limit and an upper limit of the control envelope.

公开(公告)号：US20220380033A1

公开(公告)日：2022-12-01

申请号：US17745651

申请日：2022-05-16

申请人： AIRBUS HELICOPTERS

发明人： Paul EGLIN

IPC分类号： B64C27/26 ,  B64D35/06 ,  B64C27/59 ,  B64C11/00

摘要： An aircraft comprising two half-wings extending to either side of an airframe. The aircraft comprises at least one propeller arranged in the rear part of the airframe. The aircraft comprises a rotary wing provided with two synchronized counter-rotating rotors carried respectively by the half-wings. The aircraft comprises a power plant comprising at least one engine and a mechanical interconnection system connecting the power plant permanently to the rotors except in the event of failure and during training, and to the at least one propeller.

公开(公告)号：US20210284326A1

公开(公告)日：2021-09-16

申请号：US17198329

申请日：2021-03-11

申请人： AIRBUS HELICOPTERS

发明人： Paul EGLIN ,  Remy HUOT ,  Antoine CONROY

IPC分类号： B64C13/18 ,  B64C11/00 ,  B64C11/30 ,  B64C27/06 ,  B64C5/10 ,  B64C13/24

摘要： A method for optimizing the operation of at least one first propeller and of at least one second propeller of a hybrid helicopter. The method comprises the following step during a control phase: deflection, with an autopilot system, of at least one aerodynamic stabilizer member into a setpoint position having, with respect to a reference position, a target deflection angle that is a function of a setpoint deflection angle, the setpoint deflection angle being calculated by the autopilot system in order to compensate for a torque exerted by the lift rotor at zero sideslip.

公开(公告)号：US20210291974A1

公开(公告)日：2021-09-23

申请号：US17173300

申请日：2021-02-11

申请人： AIRBUS HELICOPTERS

发明人： Remy HUOT ,  Paul EGLIN

IPC分类号： B64C27/26 ,  B64C27/82 ,  G05D1/08

摘要： A method of protecting a margin for controlling the yaw attitude of a hybrid helicopter that includes a lift rotor as well as at least one first propeller and at least one second propeller. A thrust control is configured to generate at least a first order issued to increase a first pitch of first blades of the first propeller and a second pitch of second blades of the second propeller. After a first order has been issued, the method includes an inhibition step for having a control computer inhibit the first order when a yaw attitude control margin, with regard to an envelope delimiting a flight control domain, is and/or will be less than or equal to a threshold.

公开(公告)号：US20210284331A1

公开(公告)日：2021-09-16

申请号：US17172232

申请日：2021-02-10

申请人： AIRBUS HELICOPTERS

发明人： Paul EGLIN ,  Remy HUOT

IPC分类号： B64C27/26 ,  G05D1/08 ,  B64C27/57

摘要： A method of automatically adjusting lift in a hybrid rotorcraft, the hybrid rotorcraft including a fuselage and at least two half-wings on either side of the fuselage, the at least two half-wings including at least one left half-wing having a left fixed structure secured to the fuselage and at least one left flap mounted to move relative to the left fixed structure, and at least one right half-wing having a right fixed structure secured to the fuselage and at least one right flap mounted to move relative to the right fixed structure. The method determines at least one first deflection angle setpoint δw1 by which the at least one left flap is to be deflected relative to the left fixed structure and at least one second deflection angle setpoint δw2 by which the at least one right flap is to be deflected relative to the right fixed structure.

公开(公告)号：US20210163125A1

公开(公告)日：2021-06-03

申请号：US17099064

申请日：2020-11-16

申请人： AIRBUS HELICOPTERS

发明人： Oliver BARAIS ,  Paul EGLIN ,  Jerome GENEIX

IPC分类号： B64C27/06 ,  B64C27/82 ,  B64D27/02 ,  B64D27/24 ,  B64D35/04 ,  B64D31/00 ,  B64C5/02 ,  B64C3/32 ,  B64C11/46 ,  B64D27/04 ,  B64D27/10 ,  B64D31/04

摘要： A rotorcraft including a first power plant, at least one main rotor participating at least in providing lift for the rotorcraft in the air, and at least one tail rotor carried by a tail boom, the first power plant including at least one engine. In accordance with the invention, the rotorcraft includes: at least one pusher or puller propeller independent from the at least one main rotor, the at least one pusher or puller propeller participating at least in providing propulsion or traction for the rotorcraft; a second power plant including at least one electric motor; and at least one control member configured to generate a control setpoint or instruction for controlling the at least one electric motor.

公开(公告)号：US20210291976A1

公开(公告)日：2021-09-23

申请号：US17177255

申请日：2021-02-17

申请人： AIRBUS HELICOPTERS

发明人： Paul EGLIN ,  Remy HUOT

IPC分类号： B64C27/80 ,  B64C27/22 ,  B64C27/58

摘要： A method of controlling at least a first pitch of a first propeller and a second pitch of a second propeller of a hybrid helicopter, the hybrid helicopter having a thrust control and a yaw control that are configured to generate orders for modifying respectively a mean pitch component and a differential pitch component of the first pitch and of the second pitch, the hybrid helicopter having a collective pitch control for modifying a collective pitch component of main blades of the lift rotor. The method includes a step of: keeping with the control system the first pitch and the second pitch within a control domain that varies as a function of information relating to the collective pitch component.

公开(公告)号：US20210291970A1

公开(公告)日：2021-09-23

申请号：US17176439

申请日：2021-02-16

申请人： AIRBUS HELICOPTERS

发明人： Paul EGLIN

IPC分类号： B64C27/06 ,  B64C11/44

摘要： A method of controlling at least one first propeller of a hybrid helicopter, the hybrid helicopter having a thrust control for controlling a first pitch of the first blades of the first propeller. The thrust control includes a movable control member. The method includes the following steps: the thrust control continuously transmitting a control signal carrying a control setpoint to the control system; the control system transforming the control setpoint into a pitch setpoint; and the control system controlling the first pitch by applying the pitch setpoint.