公开(公告)号：US20240359794A1

公开(公告)日：2024-10-31

申请号：US18767974

申请日：2024-07-09

申请人： Ruthvik Chandrasekaran ,  Dewey H. Hodges ,  David J. Hodges

发明人： Ruthvik Chandrasekaran ,  Dewey H. Hodges ,  David J. Hodges

IPC分类号： B64C27/00 ,  B64C27/04 ,  B64C27/68

CPC分类号： B64C27/001 ,  B64C27/68 ,  B64C2027/004 ,  B64C27/04

摘要： An anti-resonance system for a blade defining an elongated channel therein and affixed to a helicopter rotor includes a moveable mass disposed within the elongated channel of the blade so as to be able to slide along elongated channel. A moving device coupled to the moveable mass is configured to move the moveable mass within the elongated channel. A controller is configured to cause the moving device to move the moveable mass to a selected position within the elongated channel so as to avoid the resonance vibrations of the blade during a rotor speed change. In a method of avoiding resonance of a helicopter blade, a current rotational speed of the blade is determined. A position of the moveable mass so as to avoid a resonance point at a current rotational speed is obtained. The moveable mass is moved to the position.

公开(公告)号：US20240208645A1

公开(公告)日：2024-06-27

申请号：US17913784

申请日：2021-03-26

申请人： Overair, Inc.

发明人： Bernard AHYOW

IPC分类号： B64C27/72 ,  B64C27/625 ,  B64C27/68

CPC分类号： B64C27/72 ,  B64C27/625 ,  B64C27/68 ,  B64C2027/7205

摘要： A rotor blade pitch actuator has a first and second motor configured to control the rotor blade pitch. An actuator control system is configured to drive the first and second motor such that backlash is either eliminated from the system or minimized to an acceptable level.

公开(公告)号：US11905003B2

公开(公告)日：2024-02-20

申请号：US17605938

申请日：2020-04-24

申请人： Moog Inc.

发明人： John Kopp

IPC分类号： B64C27/72 ,  B64C27/68 ,  B64C27/605

CPC分类号： B64C27/68 ,  B64C27/605 ,  B64C2027/7255

摘要： A rotor blade pitch control system (15) comprising a rotor blade (19a, 19b, 19c, 19d) rotatable about both a central axis (20) and a pitch axis (24a, 24b, 24c, 24d), a pitch drive rotor (32a, 32b, 32c, 32d) rotatable about the central axis independently of rotation of the rotor blade about the central axis, a pitch follower (40a, 40b, 40c, 40d) rotatable relative to the pitch drive rotor, the pitch drive rotor and the pitch follower having an eccentric axis (33a, 33b, 33c, 33d), a linkage (50a, 50b, 50c, 50d) between the pitch follower and the rotor blade configured such that the pitch follower rotates with rotation of the rotor blade about the central axis, the pitch drive rotor, the pitch follower and the linkage configured such that the pitch drive rotor may be driven to control an angular displacement of the pitch drive rotor relative to the pitch follower about the central axis and thereby control the pitch of the rotor blade about the pitch axis.

公开(公告)号：US11738861B2

公开(公告)日：2023-08-29

申请号：US16449173

申请日：2019-06-21

申请人： Thomas Norman Hesse

发明人： Thomas Norman Hesse

IPC分类号： B64C27/68 ,  B64C9/00 ,  B64C27/72

CPC分类号： B64C27/68 ,  B64C9/00 ,  B64C27/72 ,  B64C2009/005 ,  Y02T50/30

摘要： A propelling system with variable aerodynamic controls is a system used to generate and control the flight forces of an aircraft. The system includes a stator, a rotor, a plurality of propelling units, and a control system. The stator serves as the stationary connection to the aircraft. The rotor revolves the propelling units about a central rotation axis. The control system enables the control of the propelling units. The propelling units generate the flight forces for the aircraft in the desired direction. In addition, each of the propelling units include a blade body, a shaft channel, a spar shaft, and at least one aileron assembly. The shaft channel receives the spar shaft within the blade body. The spar shaft connects the blade body to the rotor. The blade body passively corrects its angle of attack and supports the aileron assembly. The aileron assembly adjusts the pitch of the blade body.

公开(公告)号：US20230202649A1

公开(公告)日：2023-06-29

申请号：US17996398

申请日：2021-04-15

申请人： AIRBUS HELICOPTERS TECHNIK GMBH

发明人： Jan Haar ,  Uwe Arnold ,  Martin Meunier ,  Carsten Wintjen ,  Matthias Müller ,  Werner Pflüger

IPC分类号： B64C27/68

CPC分类号： B64C27/68 ,  B64C27/04

摘要： An actuator for aviation applications, in particular for adjusting rotor blades in a helicopter, may include an electromechanical drive assembly connected to an output drive via a downstream transmission, where the drive assembly is divided into sub-drives that can be operated independently, and where at least two sub-drives are spatially separated from one another in that the transmission is placed between these sub-drives. The transmission may include at least two harmonic gearings coupled to one another by at least one first coupling element, where a first harmonic gearing is located inside a non-rotating first housing, where a second harmonic gearing is located inside a rotating second housing, and where the second housing is connected to the output drive.

公开(公告)号：US11565803B2

公开(公告)日：2023-01-31

申请号：US16808851

申请日：2020-03-04

申请人： Bell Textron Inc.

发明人： William Kyle Heironimus ,  Stephen Yibum Chung

IPC分类号： B64C27/68 ,  B64C27/605 ,  B64C29/00 ,  B64D27/24 ,  B64D33/08 ,  H02K9/06 ,  B64D35/02 ,  B64D35/08 ,  H02K5/22 ,  H02K7/108 ,  H02K7/116 ,  H02K9/193

摘要： One embodiment is an electric drive system including a plurality of redundant motors, wherein power generated by the plurality of motors is used to drive a rotor system comprising a rotor shaft having a plurality of rotor blades connected thereto via a swashplate; a gear box associated with the plurality of redundant motors; a cyclic actuation system for controlling an individual pitch of the rotor blades connected to the swashplate; and at least one structural element for retaining the redundant motors, the gear box, and the cyclic actuation system together as a single integrated unit.

公开(公告)号：US11541997B2

公开(公告)日：2023-01-03

申请号：US16744897

申请日：2020-01-16

申请人： Maglev Aero Inc.

发明人： Ian Morris Randall

IPC分类号： B64C27/20 ,  H02K1/2786 ,  H02N15/00 ,  F01D5/02 ,  B64C27/10 ,  B64C27/72 ,  B64D27/24 ,  H02K1/17 ,  H02K1/2793 ,  B64C29/00 ,  B64C13/50 ,  H02K21/22 ,  B64C27/32 ,  H02K1/18 ,  H02K11/21 ,  B64C27/473 ,  H02K21/24 ,  B64C13/26 ,  B64D35/02 ,  B64D35/04 ,  H02K1/28 ,  H02K16/00 ,  B64C27/68 ,  B64C27/00 ,  B64C29/02 ,  B64C27/14 ,  B64C27/80 ,  B64C39/02 ,  B64D35/06

摘要： Systems and methods relate to a vertical takeoff and landing (VTOL) platform that can include a stator and a rotor magnetically levitated by the stator. The rotor and stator can be annular, such that the rotor rotates about a rotational axis. The stator can include magnets that provide guidance, levitation, and drive forces to drive the rotor, as well as to control operation of rotor blades of the rotor that can be independently rotated to specific pitch angles to control at least one of lift, pitch, roll, or yaw of the VTOL platform. Various controllers can be used to enable independent and redundant control of components of the VTOL platform.

公开(公告)号：US20220388672A1

公开(公告)日：2022-12-08

申请号：US17338236

申请日：2021-06-03

申请人： Bell Textron Inc.

发明人： Kip Gregory Campbell ,  Kristen Stuart ,  Steven G. Hagerott

IPC分类号： B64D31/00 ,  B64D27/24 ,  B64C27/68 ,  B64C39/02 ,  B64C27/635

摘要： A system can include a flight controller for an aircraft that includes an electric motor that drives blades with a variable pitch, where the flight controller receives a command to change a flight characteristic of the aircraft and creates a torque command and a revolutions per minute (RPM) command. The system can also include a propulsion assembly, where the propulsion assembly creates a current command based at least in part on the torque command and the RPM command, creates a blade pitch command based at least in part on the torque command and the RPM command, communicates the current command to the electric motor to change a mechanical output of the electric motor, and communicates the blade pitch command to blade actuators to control the pitch of the blades. The current command and the blade pitch command cause the blades of the aircraft to rotate at a predetermined RPM.

公开(公告)号：US20220315215A1

公开(公告)日：2022-10-06

申请号：US17220137

申请日：2021-04-01

申请人： Xingkang Li ,  Heng Ren ,  Qiang Li ,  Xingjian Li

发明人： Xingkang Li ,  Heng Ren ,  Qiang Li ,  Xingjian Li

IPC分类号： B64C37/00 ,  B64C1/06 ,  B64C27/68 ,  B64D31/00 ,  B64C9/00 ,  B64D27/10 ,  B64C5/00

摘要： A convertible aircraft system is provided that can convert to a helicopter configuration, an airplane configuration, or a gyroplane configuration before, during, or after flight. The convertible aircraft system includes a fuselage, a proximal flight assembly, a distal flight assembly, a support spar, and a tail assembly. The fuselage is the main structural body of the present invention. The proximal flight assembly and the distal flight assembly are the flight system of the present invention. The support spar provides an axis of rotation and a pole support for the proximal flight assembly and the distal flight assembly. The tail assembly provides stability during flight of the present invention. In more detail, the tail assembly may comprise at least one vertical stabilizer, at least one horizontal stabilizer, and at least one rudder in order to provide stability during flight of the present invention.

公开(公告)号：US11414174B1

公开(公告)日：2022-08-16

申请号：US16102782

申请日：2018-08-14

申请人： Matthew C. Birch ,  Zak Sowie

发明人： Matthew C. Birch ,  Zak Sowie

IPC分类号： B64C11/30 ,  B64C11/06 ,  B64C27/68

摘要： Multiple redundant harmonic drive motors on a rotor head actuate the angle of attack of rotor blades at the rotor blade roots, providing collective control that, in combination with a system for providing cyclic control on the rotor blades, eliminates the need for a swashplate, thereby advantageously reducing the weight and maintenance cost of a helicopter, increasing its reliability, and reducing its vulnerability to ballistic attack.