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公开(公告)号：US12006028B2
公开(公告)日：2024-06-11
申请号：US17619771
申请日：2020-05-26
申请人： LEONARDO S.P.A.
摘要： An anti-torque rotor includes a mast rotatable about a first axis; a plurality of blades extending along respective second axes; and a control element sliding along the first axis with respect to the mast, integrally rotatable with said mast, and connected to said blades. A control rod slides axially along first axis and is angularly fixed with respect to said first axis. A connection element is interposed between the control rod and the control element and is configured to enable the relative rotation of said control element with respect to the control rod about the first axis. A transmission unit is available in an active configuration or an inactive configuration. The transmission unit has an annular ridge axially and angularly integral with the control rod and a seat engaged by the ridge and angularly integral with the control element.
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公开(公告)号：US20240124136A1
公开(公告)日：2024-04-18
申请号：US18486339
申请日：2023-10-13
发明人： Tae Joo KIM
摘要： A rotor hub system includes a rotor rotation axis, a flap hinge connected to the rotor rotation axis and enabling flapping motion of a rotor blade, a lead-lag hinge connected to the flap hinge and enabling lead-lag motion of the rotor blade, a first hub to which one end of the rotor blade is fixed, a rotating pitch control actuator connected to the first hub and rotating the first hub to enable pitching motion of the rotor blade, and a second hub equipped with the rotating pitch control actuator and hinged to the lead-lag hinge.
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公开(公告)号：US11801936B2
公开(公告)日：2023-10-31
申请号：US17151718
申请日：2021-01-19
摘要： Embodiments are directed to a flight control system for a helicopter comprises a pilot interface configured to receive a control input, at least one electronically controlled actuator, and a computing device configured to translate the control input to an actuator command, wherein the computing device is further configured to apply yaw rate limits to the actuator command to avoid loss of tail rotor effectiveness. The yaw rate limits are associated with a vortex ring state (VRS) envelope for a tail rotor of the helicopter. The electronically controlled actuator comprises a tail rotor actuator. The control input is a pedal input.
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公开(公告)号：US20220227488A1
公开(公告)日：2022-07-21
申请号：US17151718
申请日：2021-01-19
摘要： Embodiments are directed to a flight control system for a helicopter comprises a pilot interface configured to receive a control input, at least one electronically controlled actuator, and a computing device configured to translate the control input to an actuator command, wherein the computing device is further configured to apply yaw rate limits to the actuator command to avoid loss of tail rotor effectiveness. The yaw rate limits are associated with a vortex ring state (VRS) envelope for a tail rotor of the helicopter. The electronically controlled actuator comprises a tail rotor actuator. The control input is a pedal input.
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公开(公告)号：US11325699B2
公开(公告)日：2022-05-10
申请号：US16833618
申请日：2020-03-29
IPC分类号： B64C11/00 , B64C21/04 , B64C29/00 , B64D27/16 , B64C11/48 , B64D35/06 , B64D35/02 , B64C27/22 , B64D33/04 , B64D35/04 , B64C3/10 , B64C19/00 , B64C27/26 , B64C27/30 , B64C9/20 , B64C21/08 , B64C27/78 , B64C39/10 , B64C9/18 , B64C15/02 , B64C15/14 , B64C21/00
摘要： A ducted fan assembly for generating thrust during edgewise forward flight. The ducted fan assembly includes a duct having an inlet with a leading portion and a diffuser with a trailing portion during the edgewise forward flight. A fan disposed within the duct is configured to rotate relative to the duct about a fan axis to generate an airflow through the duct from the inlet to the diffuser. An active flow control system includes a plurality of injectors including a first injector configured to inject pressurized air substantially tangential with the leading portion of the inlet and a second injector configured to inject pressurized air substantially tangential with the trailing portion of the diffuser such that when the injectors are injecting pressurized air, flow separation of the airflow at the leading portion of the inlet and the trailing portion of the diffuser is reduced.
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公开(公告)号：US11167844B2
公开(公告)日：2021-11-09
申请号：US16833628
申请日：2020-03-29
IPC分类号： B64C27/22 , B64C29/00 , B64C27/30 , B64C15/14 , B64C21/00 , B64C27/78 , B64C27/26 , B64D33/04 , B64C3/10
摘要： An aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a forward flight orientation. The aircraft has a blended wing body and includes first and second engines, a binary lift fan system, first and second forced air bypass systems and first and second exhaust systems. The engines have turboshaft and turbofan modes. The lift fan system includes ducted fans in a tandem longitudinal orientation. In the VTOL orientation of the aircraft, the engines are in the turboshaft mode coupled to the lift fan system such that the engines provide rotational energy to the ducted fans generating the thrust-borne lift. In the forward flight orientation of the aircraft, the engines are in the turbofan mode coupled to the forced air bypass systems such that the bypass air combines with the engine exhaust in the exhaust systems to provide forward thrust generating the wing-borne lift.
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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
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.
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公开(公告)号：US11021241B2
公开(公告)日：2021-06-01
申请号：US15514595
申请日：2015-09-29
IPC分类号： G06F7/70 , G06G7/00 , G06G7/76 , B64C27/10 , F16F15/02 , B64C27/00 , B64C27/14 , B64C1/00 , B64C7/00 , B64C13/18 , B64C13/50 , B64C19/00 , B64C27/12 , B64C27/32 , B64C27/33 , B64C27/473 , B64C27/48 , B64C27/51 , B64C27/52 , B64C27/54 , B64C27/78 , B64C27/80 , B64C27/82 , B64D39/00 , B64D39/06 , B64D45/02 , F16H37/02 , G05D1/00 , G05D1/02 , B64C27/16 , B64C13/04 , G05D1/08 , B64C27/57 , B64D35/06 , B64C27/467 , F02C9/28 , F16D13/52 , F16D13/72 , F16D13/74 , B64C27/08
摘要： An aircraft is provided and includes an airframe, an extending tail, a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly, a translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe, at least one sensor and at least one inertial measurement unit (IMU) to sense current flight conditions of the aircraft, an interface to execute controls of a main rotor assembly in accordance with control commands and at least one flight control computer (FCC) to issue the control commands. The at least one FCC includes a central processing unit (CPU) and a memory having logic and executable instructions stored thereon, which, when executed, cause the CPU to issue the control commands based on the current flight conditions and a result of an execution of the logic for the current flight conditions.
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公开(公告)号：US20210147073A1
公开(公告)日：2021-05-20
申请号：US16688261
申请日：2019-11-19
发明人： Tobias RIES
摘要： A rotor comprises at least two rotor blades, and each rotor blade of the at least two rotor blades rotates around a rotor axis and performs pitching around a pitch axis. The rotor axis and the pitch axis intersect in a rotor center. The rotor is characterized in that each rotor blade comprises at least one permanent magnet having a first spherical magnet surface. Each rotor blade further comprises a pitch control apparatus for controlling the pitching of the at least two rotor blades. The pitch control apparatus comprises electrically controlled magnets having a second spherical magnet surface.
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公开(公告)号：US10967692B1
公开(公告)日：2021-04-06
申请号：US16732473
申请日：2020-01-02
申请人： John Robert Andrew
发明人： John Robert Andrew
摘要： An automobile equipped with helicopter flight apparatus capable of travel on public roads or flight in any direction. The conversion from ground travel mode to flight mode and vis-versa is automatic.
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