公开(公告)号：WO2012021202A3

公开(公告)日：2012-07-05

申请号：PCT/US2011038043

申请日：2011-05-26

Applicant: LORD CORP ,  JOLLY MARK ,  MILLER LANE ,  BADRE-ALAM ASKARI

Inventor： JOLLY MARK ,  MILLER LANE ,  BADRE-ALAM ASKARI

IPC: B64C27/80

CPC classification number: B64C27/001 ,  B64C27/008 ,  B64C2027/004

Abstract: Rotary wing aircraft electronic control system including a tachometer (552) and a plurality of nonrotating body vibration control sensors (554) outputting at least first nonrotating body vibration sensor data correlating to vibrations. The system includes a plurality of nonrotating body force generators (530) to input a vibration control force into said nonrotating aerostructure body. The system includes a data communications network link (150) linking together the nonrotating body force generators the tachometer sensor, the vibration control sensors, and an actuating force generator rotor track balance electronic controller (411), the actuating force generator rotor track balance electronic controller including at least a first computer processor with the actuating force generator rotor track controller controlling the nonrotating body force generators to input vibration control forces into the nonrotating aerostructure body and computing a rotor track solution for aircraft rotor blades.

Abstract translation: 旋转翼飞行器电子控制系统包括转速计（552）和多个非旋转体振动控制传感器（554），其输出与振动相关的至少第一非旋转振动传感器数据。 该系统包括多个非旋转体力发生器（530），用于将振动控制力输入到所述非旋转航空结构体中。 该系统包括将非旋转体力发生器，转速计传感器，振动控制传感器和致动力发生器转子轨道平衡电子控制器（411）连接在一起的数据通信网络链路（150），致动力发生器转子轨道平衡电子控制器 包括至少具有致动力发生器转子轨道控制器的第一计算机处理器，其控制非旋转体力发生器以将振动控制力输入到非旋转航空结构体中并计算用于飞行器转子叶片的转子轨道解决方案。

公开(公告)号：WO9730813A9

公开(公告)日：2000-04-27

申请号：PCT/AU9600763

申请日：1996-11-28

Applicant: AIMBRIDGE PTY LTD ,  WILLMOT ERIC PAUL

Inventor： WILLMOT ERIC PAUL

IPC: B23B31/36 ,  B23B31/28 ,  B63H5/10 ,  B64C11/32 ,  B64C27/54 ,  B64D31/12 ,  F01L1/352 ,  F03D7/02 ,  F03D7/04 ,  F03D11/02 ,  F16D3/10 ,  F16H35/00 ,  F16H35/18 ,  F16H37/06 ,  B23B31/26 ,  B23B31/42 ,  B63H3/02 ,  B64C11/34 ,  B64C11/36 ,  B64C27/605 ,  B64C27/78 ,  B64C27/80 ,  F01L1/34

CPC classification number: F16D3/10 ,  B23B31/28 ,  B63H5/10 ,  B64C11/32 ,  B64D31/12 ,  F01L1/352 ,  F03D7/0224 ,  F03D15/00 ,  F05B2260/4031 ,  F05B2260/40311 ,  F16H35/008 ,  Y02E10/722 ,  Y02E10/723 ,  Y10T74/19084 ,  Y10T74/19093 ,  Y10T74/1956

Abstract: The phase control mechanism includes first gears (3, 4) coupled to the output shafts which are to be phase controlled. A transfer gear (5) is provided for rotation or operation independent of the input and is coupled to the first gears (3, 4) to allow rotary motion to be transferred between the first gear members and a phase adjuster (10) causes the first gears (3, 4) to advance on regress relative to one another to change the phase relationship between the outputs.

Abstract translation: 相位控制机构包括联接到待相位控制的输出轴的第一齿轮（3,4）。 传动齿轮（5）被提供用于独立于输入的旋转或操作，并且联接到第一齿轮（3,4）以允许旋转运动在第一齿轮构件之间传递并且相位调节器（10）使得第一 齿轮（3,4）相对于彼此退回以改变输出之间的相位关系。

公开(公告)号：WO2021129180A1

公开(公告)日：2021-07-01

申请号：PCT/CN2020/126690

申请日：2020-11-05

Applicant: 苏州韬讯航空科技有限公司

Inventor： 葛讯 ,  沈元 ,  郭述臻 ,  李良伟 ,  刘卫东

IPC: B64C27/10 ,  B64C27/80 ,  B64C27/605

Abstract: 一种共轴直升机，包括机身（1）、上旋翼作动器（2）、下旋翼作动器（3）、上旋翼传动轴（4）、下旋翼传动轴（5）、上旋翼系统（6）、下旋翼系统（7）、伺服机构（8），还包括周期变距机构（9）以及差异变距机构（10）；伺服机构（8）设置有四个，其中三个伺服机构通过连杆直接驱动周期变距机构（9）；四个伺服机构中的另一个通过连杆和杠杆驱动差异变距机构（10）。该共轴直升机实现共轴飞行器多种飞行动作的同步进行，并支持在旋翼变速或定速模式下的半差动、全差动等多种飞行控制方式。还涉及一种共轴直升机的控制方法。

公开(公告)号：WO2015156879A3

公开(公告)日：2016-04-07

申请号：PCT/US2015011906

申请日：2015-01-19

Applicant: SIKORSKY AIRCRAFT CORP

Inventor： ELLER EREZ ,  WULFF OLE

IPC: B64C27/57 ,  B64C27/78 ,  B64C27/80 ,  G01L5/00

CPC classification number: G05D1/0816 ,  B64C27/32 ,  B64C27/57 ,  G05D1/0858

Abstract: Embodiments are directed to obtaining at least one measurement of blade bending associated with at least one blade of at least one rotor of an aircraft, processing, by a device comprising a processor, the at least one measurement to obtain moment data, obtaining data from an inertial measurement unit (IMU), and processing, by the device, the moment data and the data from the IMU to generate a command configured to stabilize the aircraft.

Abstract translation: 实施例旨在获得与飞机的至少一个转子的至少一个叶片相关联的叶片弯曲的至少一个测量，由包括处理器的装置处理，所述至少一个测量以获得力矩数据，从 惯性测量单元（IMU），以及由设备处理来自IMU的力矩数据和数据以产生用于使飞机稳定的命令。

公开(公告)号：WO2012021202A2

公开(公告)日：2012-02-16

申请号：PCT/US2011/038043

申请日：2011-05-26

Applicant: LORD CORPORATION ,  JOLLY, Mark ,  MILLER, Lane ,  BADRE-ALAM, Askari

Inventor： JOLLY, Mark ,  MILLER, Lane ,  BADRE-ALAM, Askari

IPC: B64C27/80

CPC classification number: B64C27/001 ,  B64C27/008 ,  B64C2027/004

Abstract: Rotary wing aircraft electronic control system including a tachometer and a plurality of nonrotating body vibration control sensors outputting at least first nonrotating body vibration sensor data correlating to vibrations. The system includes a plurality of nonrotating body force generators to input a vibration control force into said nonrotating aerostructure body. The system includes a data communications network link linking together the nonrotating body force generators the tachometer sensor, the vibration control sensors, and an actuating force generator rotor track balance electronic controller, the actuating force generator rotor track balance electronic controller including at least a first computer processor with the actuating force generator rotor track controller controlling the nonrotating body force generators to input vibration control forces into the nonrotating aerostructure body and computing a rotor track solution for aircraft rotor blades.

Abstract translation: 旋转翼飞行器电子控制系统包括转速计和多个非旋转体振动控制传感器，其输出与振动相关的至少第一非旋转体振动传感器数据。 该系统包括多个非旋转体力发生器，用于将振动控制力输入到所述非旋转航空结构体中。 该系统包括将非旋转体力发生器，转速计传感器，振动控制传感器和致动力发生器转子轨道平衡电子控制器连接在一起的数据通信网络链路，致动力发生器转子轨道平衡电子控制器至少包括第一计算机 处理器，其具有致动力发生器转子轨道控制器，其控制非旋转体力发生器以将振动控制力输入到非旋转航空结构体中并计算用于飞行器转子叶片的转子轨道解决方案。

公开(公告)号：WO2023091389A1

公开(公告)日：2023-05-25

申请号：PCT/US2022/049902

申请日：2022-11-15

Applicant: BOARD OF REGENTS, THE UNIVERSITY OF TEXAS SYSTEM

Inventor： SIROHI, Jayant ,  CAMERON, Christopher ,  JAIN, Palash

IPC: B64C27/78 ,  B64C11/02 ,  B64C11/06 ,  B64C11/30 ,  B64C27/39 ,  B64C27/54 ,  B64C27/605 ,  B64C27/80

Abstract: Various implementations include a rotor control device including a shaft extending along a rotational axis, a hub, first and second pitch control components, and a swashplate. The hub has a hub axis and is hingedly coupled to the shaft such that the hub axis is perpendicular to the rotational axis and stationary relative to the shaft. The hub is hingable about the hub axis relative to the rotational axis. The first pitch control component is coupled to the hub. The swashplate has the second pitch control component hingedly engaging the first pitch control component. The swashplate is movable along a swashplate plane transverse to the rotational axis. The shaft is rotatable about the rotational axis relative to the swashplate. Movement of the swashplate along the swashplate plane relative to the rotational axis causes the hub to periodically hinge about the hinge axis as the hub rotates about the rotational axis.

公开(公告)号：WO2017174288A1

公开(公告)日：2017-10-12

申请号：PCT/EP2017/055544

申请日：2017-03-09

Applicant: SAGITA SA

Inventor： ANTOINE, Hubert

IPC: B64C27/605 ,  B64C27/10 ,  B64C27/80 ,  B64C27/18

Abstract: Dispositif de commande du pas collectif et du pas cyclique des pales de rotor de giravion, du type à entraînement direct par turbine et à rotors coaxiaux contrarotatifs (REDT), ledit dispositif comprenant des moyens pour assurer que le troisième plateau (C) est toujours parallèle au deuxième plateau (B), c'est-à-dire que le troisième plateau (C) reçoit la même translation et la même inclinaison que le deuxième plateau (B) par les commandes respectives de pas collectif et de pas cyclique.

Abstract translation:

用于控制旋翼机转子叶片的集体俯仰和周期性俯仰的装置， 通过涡轮直接驱动并且> 同轴反向转动的转子（REDT），所述设备包括装置，以确保所述第三＆egrave;托盘I（C）总是平行＆egrave;所述第二及egrave;托盘箱（B），即＆agrave; -dire第三＆egrave;我 平台（C）通过集体俯仰和循环俯仰的相应命令接收与第二平台（B）相同的平移和倾斜。

公开(公告)号：WO2016060816A1

公开(公告)日：2016-04-21

申请号：PCT/US2015/051914

申请日：2015-09-24

Applicant: SIKORSKY AIRCRAFT CORPORATION

Inventor： FEGELY, Cody ,  ELLER, Erez ,  WITTMER, Kenneth S. ,  GREENFIELD, Aaron L. ,  KNAG, John

IPC: B64C27/80

CPC classification number: B64C27/80 ,  B64C27/10 ,  G05D1/0808 ,  G05D1/0858

Abstract: A method for controlling a differential rotor roll moment for a coaxial helicopter with rigid rotors, the method including receiving, with a processor, a signal indicative of a displacement command from a controller; receiving, with the processor via a sensor, one or more signals indicative of a longitudinal velocity, an angular velocity of one or more rotors and an air density ratio for the helicopter; determining, with the processor, a ganged collective mixing command in response to the receiving of the displacement command; determining, with the processor, a rotor advance ratio as a function of the longitudinal velocity and the angular velocity; and determining, with the processor, a corrective differential lateral cyclic command for the rigid rotors that controls the differential rotor roll moment to a desired value.

Abstract translation: 一种用于控制具有刚性转子的同轴直升机的差动转子转矩的方法，所述方法包括：用处理器接收指示来自控制器的位移指令的信号; 通过传感器与处理器接收一个或多个指示纵向速度，一个或多个转子的角速度和直升机的空气密度比的信号; 响应于所述位移命令的接收，与所述处理器确定联合的混合命令; 用处理器确定作为纵向速度和角速度的函数的转子提前比; 以及用所述处理器确定所述刚性转子的校正差分横向循环命令，所述刚性转子将所述差速转子卷轴力矩控制到期望值。

公开(公告)号：WO2022261720A1

公开(公告)日：2022-12-22

申请号：PCT/AU2022/050608

申请日：2022-06-17

Applicant: HYPER Q AEROSPACE HOLDINGS PTY LTD

Inventor： BATTEN, Peter James

IPC: B64C27/10 ,  B64C27/605 ,  B64C27/72 ,  B64C27/80

Abstract: A swashplate assembly for controlling rotor blades of a rotorcraft, comprising a rotating assembly, wherein the rotating assembly is arranged to rotate with the rotor blades about an axis and is coupled to the rotor blades; a base assembly, wherein the base assembly includes a first portion and a second portion, and the rotating assembly is guided by the base assembly to set blade angles of the rotor blades as the rotating assembly rotates with the rotor blades, wherein the second portion is arranged to induce a change in blade angle of the rotor blades.

公开(公告)号：WO2020180373A2

公开(公告)日：2020-09-10

申请号：PCT/US2019/065301

申请日：2019-12-09

Applicant: JOBY AERO, INC.

Inventor： ENGLISH, Blake ,  BEVIRT, JoeBen

IPC: B64C27/80

Abstract: The unified command system and/or method includes an input mechanism, a flight processor that receives input from the input mechanism and translates the input into control output, and effectors that are actuated according to the control output. The system can optionally include: one or more sensors, a vehicle navigation system which determines a vehicle state and/or flight regime based on data from the one or more sensors, and a vehicle guidance system which determines a flightpath for the aircraft.