公开(公告)号：US11952110B1

公开(公告)日：2024-04-09

申请号：US17893540

申请日：2022-08-23

申请人： SiFly Aviation, Inc.

发明人： Brian L. Hinman

IPC分类号： B64C27/68

CPC分类号： B64C27/68

摘要： An improved electrically powered rotorcraft is of the type having a rotor including a rotor hub and a pair of rotor blades mounted to the rotor hub on opposite sides thereof, the rotor being rotatably mounted on a primary drive shaft, and a rotary electric motor coupled to the drive shaft. In this rotorcraft, the improvement includes a common pitch-angle shaft coupled to each of the blades; a limited-angle electric motor, mechanically coupled to the common pitch-angle shaft, and configured to cause rotation of the common pitch angle shaft and therefore adjustment of pitch of the pair of rotor blades; and a controller system in communication with the limited-angle electric motor, configured to provide cyclic control of pitch of the pair of rotor blades.

公开(公告)号：US11787539B2

公开(公告)日：2023-10-17

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 ,  B64D27/10 ,  B64C1/06 ,  B64C27/68 ,  B64C9/00 ,  B64C5/00 ,  B64D31/00

CPC分类号： B64C37/00 ,  B64C1/065 ,  B64C5/00 ,  B64C9/00 ,  B64C27/68 ,  B64D27/10 ,  B64D31/00 ,  B64C2009/005

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：US11745864B2

公开(公告)日：2023-09-05

申请号：US17053323

申请日：2019-05-03

申请人： AIRBUS HELICOPTERS TECHNIK GMBH

发明人： Steffen Hahn ,  Andre Hausberg ,  Werner Pflüger ,  Daniel Fürst

IPC分类号： B64C27/00 ,  B64C27/68 ,  B64C27/72 ,  H02P7/06

CPC分类号： B64C27/68 ,  B64C27/72 ,  H02P7/06 ,  B64C2027/7205

摘要： A system for controlling an electromechanical actuator for setting a collective offset for a helicopter on a blade-specific basis, wherein the system comprises at least one actuator, the length and position of which can be adjusted electromechanically within a mechanically limited range, a power electronics that is configured to adjust the actuator by means of a servomotor in two directions, specifically toward a positive collective offset or toward a negative collective offset, and a first microelectronics system that is configured to control the power electronics such that positive and negative collective offsets can be set. The system also includes a second microelectronics system, which is configured to override the actuation of the first microelectronics system in order to act on the adjustment of the actuator, and by a first control line, which is configured to activate or deactivate the second microelectronics system through an external electrical signal.

公开(公告)号：US20230174228A1

公开(公告)日：2023-06-08

申请号：US17959600

申请日：2022-10-04

申请人： Microtecnica S.r.l.

发明人： Domenico TAFUNI ,  Simone ALLEVI

IPC分类号： B64C27/64 ,  B64C13/42 ,  B64C27/68

CPC分类号： B64C27/64 ,  B64C13/42 ,  B64C27/68

摘要： A Stability and Control Augmentation System (“SCAS”) module includes a SCAS actuator. The SCAS actuator has a substantially cylindrical hydraulic chamber having a first and second regions. A piston is arranged for linear motion in first and second directions along an axis of the hydraulic chamber. The SCAS module also includes a valve system for controlling a flow of a hydraulic fluid into the hydraulic chamber. The valve system has: at least one supply line arranged to provide a first fluid flow path to the first region of the hydraulic chamber and/or a second fluid flow path to the second region of the hydraulic chamber, and a moveable valve member arranged to have a position between a first and second positions.

公开(公告)号：US10077102B1

公开(公告)日：2018-09-18

申请号：US13536475

申请日：2012-06-28

申请人： Matthew C. Birch ,  Zak Sowle

发明人： Matthew C. Birch ,  Zak Sowle

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

CPC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.

公开(公告)号：US09758244B2

公开(公告)日：2017-09-12

申请号：US15015689

申请日：2016-02-04

申请人： Merlin Technology, Inc.

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

IPC分类号： B64C27/57 ,  B64C27/64 ,  B64C27/68 ,  G05D1/08 ,  B64C27/56 ,  G05D1/10 ,  B64C13/18 ,  B64C13/42 ,  B64C27/59 ,  G05D1/00

CPC分类号： B64C27/57 ,  B64C13/18 ,  B64C13/42 ,  B64C27/56 ,  B64C27/59 ,  B64C27/64 ,  B64C27/68 ,  G05D1/0077 ,  G05D1/0816 ,  G05D1/0858 ,  G05D1/102 ,  Y02T50/44

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.

公开(公告)号：US09534644B2

公开(公告)日：2017-01-03

申请号：US14482646

申请日：2014-09-10

申请人： Bell Helicopter Textron Inc.

发明人： Pasquale Spina ,  Carlos A Fenny ,  Jean-Sebastian Plante ,  Marc Denninger

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

CPC分类号： F16D37/008 ,  B64C13/28 ,  B64C27/08 ,  B64C27/12 ,  B64C27/56 ,  B64C27/605 ,  B64C27/64 ,  B64C27/68 ,  B64C27/78 ,  B64D31/14 ,  B64D35/02 ,  B64D35/04 ,  F16D27/14 ,  F16D37/02 ,  F16D2037/001 ,  F16D2037/007 ,  F16H25/20 ,  F16H2025/2059 ,  Y02T50/44 ,  Y10T74/18704

摘要： In some embodiments, an actuation system includes a plurality of threaded member portions, a plurality of roller nuts, a driving member configured to receive mechanical energy from a power source, a plurality of driven members, and a magnetorheological (MR) fluid disposed between the plurality of driven members and at least one braking surface. An output member may be coupled between the rotor system and either the plurality of threaded member portions or the plurality of roller nuts and configured to translate linearly in response to the threaded member portions advancing or receding within the roller nuts.

摘要翻译： 在一些实施例中，致动系统包括多个螺纹构件部分，多个滚子螺母，构造成从动力源接收机械能的驱动构件，多个从动构件以及设置在所述驱动构件之间的磁流变（MR）流体 多个从动构件和至少一个制动表面。 输出构件可以联接在转子系统和多个螺纹构件部分或多个滚子螺母之间并且被构造成响应于螺纹构件部分在滚子螺母内前进或后退而线性平移。

公开(公告)号：US09150308B2

公开(公告)日：2015-10-06

申请号：US13763590

申请日：2013-02-08

申请人： Merlin Technology, Inc.

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

IPC分类号： H02K7/14 ,  B64C27/68 ,  B64C27/59 ,  B64C13/04 ,  B64C13/30 ,  B64C27/57 ,  B64C27/58

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.

摘要翻译： 自动驾驶执行器包括第一和第二电动机，每个电动机包括可旋转的电动机输出轴，使得电动机中的一个或两个可以驱动致动器输出轴。 自动驾驶仪主机壳体可拆卸地安装在靠近循环控制的直升机上，并且通常容纳自动驾驶执行器以及主要的自动驾驶仪电子装置。 循环式隔振器由致动器轴可拆卸地支撑，用于共同旋转并且耦合到循环控制器，以在致动器轴处衰减循环振动频率，同时致动器轴的低于谐振频率的转速耦合到循环控制。 力限制连杆包括第一和第二端以及两者之间的可变长度。 当施加小于放开力的力时，力限制连杆具有松弛的长度，并且当施加的力超过转动力以允许引导超驰时，可变长度改变。

公开(公告)号：US20150217866A1

公开(公告)日：2015-08-06

申请号：US14482583

申请日：2014-09-10

申请人： Bell Helicopter Textron Inc.

发明人： Pasquale Spina ,  Carlos A. Fenny ,  Jean-Sebastian Plante

IPC分类号： B64C27/78 ,  B64D35/02 ,  F16D37/02 ,  B64C27/12

CPC分类号： F16D37/008 ,  B64C13/28 ,  B64C27/08 ,  B64C27/12 ,  B64C27/56 ,  B64C27/605 ,  B64C27/64 ,  B64C27/68 ,  B64C27/78 ,  B64D31/14 ,  B64D35/02 ,  B64D35/04 ,  F16D27/14 ,  F16D37/02 ,  F16D2037/001 ,  F16D2037/007 ,  F16H25/20 ,  F16H2025/2059 ,  Y02T50/44 ,  Y10T74/18704

摘要： In some embodiments, a rotorcraft flight control actuator includes a driving member configured to receive mechanical energy from a power source, a driven member, a magnetorheological (MR) fluid 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 a flight control device of a rotor system, and a magnetic circuit configured to deliver a magnetic field towards the MR fluid, the magnetic circuit configured to vary the strength of the magnetic field in response to inputs.

摘要翻译： 在一些实施例中，旋翼航空器飞行控制致动器包括驱动构件，其构造成从动力源，从动构件，设置在驱动构件和从动构件之间的磁流变（MR）流体接收机械能，并且构造成传递可变量 从驱动构件到从动构件的机械能，构造成联接在从动构件和转子系统的飞行控制装置之间的输出构件，以及被配置为向MR流体输送磁场的磁路，磁路 被配置为响应于输入而改变磁场的强度。

公开(公告)号：US08845290B1

公开(公告)日：2014-09-30

申请号：US12976687

申请日：2010-12-22

申请人： Richard H. Lugg

发明人： Richard H. Lugg

IPC分类号： B64C27/78

CPC分类号： B64C27/68 ,  B64C2027/7216 ,  Y02T50/34

摘要： A rotorcraft having an operational range and a plurality of rotor blades, each rotor blade capable of assuming an angular pitch, utilizes a control apparatus a mechanism for independently controlling an angular pitch value of each of the plurality of rotor blades wherein a collective sum of the angular pitch values of the plurality of rotor blades is not constant over the operational range of the rotorcraft.

摘要翻译： 具有操作范围的旋翼航空器和多个转子叶片，每个转子叶片能够呈现角度间距，利用控制装置，用于独立地控制多个转子叶片中的每一个的角度间距值的机构，其中， 多个转子叶片的角度间距值在旋翼航空器的操作范围内不是恒定的。