公开(公告)号：US11977394B2

公开(公告)日：2024-05-07

申请号：US17603190

申请日：2021-10-12

Applicant: Aergility Corporation

Inventor： James E. Vander Mey ,  Lawrence Winston Yonge, III

IPC: B64C27/10 ,  B64C11/50 ,  B64C27/00 ,  B64C27/02 ,  B64C27/12 ,  B64C27/14 ,  B64C27/22 ,  B64C27/26 ,  B64D31/00 ,  G05D1/00 ,  B64C11/48 ,  B64C27/82 ,  B64D27/24 ,  H02K1/27

CPC classification number: G05D1/0858 ,  B64C11/50 ,  B64C27/006 ,  B64C27/02 ,  B64C27/021 ,  B64C27/025 ,  B64C27/027 ,  B64C27/028 ,  B64C27/10 ,  B64C27/12 ,  B64C27/14 ,  B64C27/22 ,  B64C27/26 ,  B64D31/00 ,  B64C11/48 ,  B64C2027/8236 ,  B64D27/24 ,  H02K1/27

Abstract: A multi-rotor aircraft includes a fuselage, a propulsion engine coupled to the fuselage that generates thrust to propel the aircraft along a first vector during forward flight, and rotors coupled to the fuselage, each rotor comprising blades, each rotor coupled to a motor, and each motor configured to supply power to and draw power from the coupled rotor. The aircraft includes a flight control system configured to control the motors coupled to the rotors in a power managed regime in which a net electrical power, consisting of a sum of the power being supplied to or drawn from each rotor by its motor, is maintained within a range determined by a feedback control system of the flight control system. The flight control system can also be leveraged to adjust rotor control inputs to modify at least one of thrust, roll, pitch, or yaw of the multi-rotor aircraft.

公开(公告)号：US20230382546A1

公开(公告)日：2023-11-30

申请号：US17752020

申请日：2022-05-24

Applicant: BETA AIR, LLC

Inventor： Collin Freiheit ,  Nicholas Moy

IPC: B64D31/12 ,  B64D27/24 ,  B64C29/00 ,  B64C11/50

CPC classification number: B64D31/12 ,  B64D27/24 ,  B64C29/0025 ,  B64C11/50

Abstract: A system for propulsor synchronization using electronic brakes is disclosed. The system includes a controller located in an electric aircraft configured to receive a first signal from a first propulsor sensor of a plurality of propulsor sensors, the first propulsor sensor configured to measure a first motion parameter of a first propulsor of a plurality of propulsors. The controller may receive a second signal from a second propulsor sensor of the plurality of propulsor sensors, the second propulsor sensor configured to measure a second motion parameter of a second propulsor of the plurality of propulsors. The controller may synchronously decelerate the first propulsor and the second propulsor based on the first motion parameter and the second motion parameter.

公开(公告)号：US20170297699A1

公开(公告)日：2017-10-19

申请号：US15335523

申请日：2016-10-27

Applicant: Sikorsky Aircraft Corporation

Inventor： Mark R. Alber ,  Jeffrey Parkhurst

IPC: B64C29/02 ,  B64D27/24 ,  B64C11/50 ,  B64C11/30 ,  B64D27/10 ,  B64C3/16 ,  B64D27/02

CPC classification number: B64C29/02 ,  B64C3/16 ,  B64C11/30 ,  B64C11/50 ,  B64D27/10 ,  B64D27/24 ,  B64D2027/026 ,  Y02T50/64

Abstract: A tail-sitter aircraft is provided and includes a fuselage having first and second axisymmetric sides, first collectively controllable prop-rotors, which are formed to define a first pair of rotor disks and which are respectively supported at the first axisymmetric side of the fuselage, and second collectively controllable prop-rotors, which are formed to define a second pair of rotor disks and which are respectively supported at the second axisymmetric side of the fuselage.

公开(公告)号：US08740133B2

公开(公告)日：2014-06-03

申请号：US13055340

申请日：2009-07-21

Applicant: Jean-Michel Saucray ,  Philippe Chareyre

Inventor： Jean-Michel Saucray ,  Philippe Chareyre

IPC: B64C1/40

CPC classification number: B64D31/12 ,  B64C11/008 ,  B64C11/48 ,  B64C11/50 ,  B64D27/08 ,  B64D2027/026 ,  Y02T50/66

Abstract: An aircraft including at least one engine having counter-rotating rotors, the engine or at least one of the engines having imbalances associated with at least one ellipse. The aircraft includes at least one vibration damper attached in an arrangement such that, at a given engine speed and for at least one given common direction of a large axis of the ellipse or at least one of the ellipses, a speed related to the two ends of the damper is higher than for any other arrangement of the damper.

Abstract translation: 一种包括至少一个具有反转转子的发动机的发动机，所述发动机或至少一个所述发动机具有与至少一个椭圆相关联的不平衡。 飞行器包括至少一个振动阻尼器，该振动阻尼器以一种布置方式附接，使得在给定的发动机转速下，对于椭圆的大轴或至少一个椭圆的至少一个给定的共同方向，与两端相关的速度 的阻尼器比阻尼器的任何其它布置高。

公开(公告)号：US5335175A

公开(公告)日：1994-08-02

申请号：US847007

申请日：1992-05-27

Applicant: Gilbert A. Turner

Inventor： Gilbert A. Turner

IPC: B64C11/50

CPC classification number: B64C11/50

Abstract: A propeller control system comprises a phase controller (11) having a phase control gain to control a propeller phase relationship, free air turbulence detection means (7, 9) and a gain controller (8) for varying the phase control gain in response to detected free air turbulence such that in the presence of turbulence a low gain is selected and in the absence of turbulence a high gain is selected. By varying the gain in this way the sensitivity of the phase controller (11) is reduced during turbulent conditions preventing excessive phase changes by the controller (11) striving to follow a turbulent master propeller. Similarly a speed controller (14) has its gain set by a gain controller (17) according to the degree of turbulence detected.

Abstract translation: PCT No.PCT / GB91 / 01361 Sec。 371日期：1992年5月27日 102（e）日期1992年5月27日PCT 1991年8月9日PCT PCT。 出版物WO92 / 02411 日期1992年2月20日。一种螺旋桨控制系统，包括具有相位控制增益以控制螺旋桨相位关系的相位控制器（11），自由空气湍流检测装置（7,9）和增益控制器（8） 响应于检测到的自由空气湍流的相位控制增益，使得在存在湍流的情况下选择低增益，并且在没有湍流的情况下选择高增益。 通过以这种方式改变增益，相位控制器（11）的灵敏度在湍流条件下被减小，从而防止控制器（11）过度相位变化，从而追求湍流主螺旋桨。 类似地，根据检测到的湍流程度，速度控制器（14）具有由增益控制器（17）设定的增益。

公开(公告)号：US5165240A

公开(公告)日：1992-11-24

申请号：US761606

申请日：1991-09-18

Applicant: George W. Page ,  Glen T. High ,  Larry C. Prevallet ,  Joseph W. Free

Inventor： George W. Page ,  Glen T. High ,  Larry C. Prevallet ,  Joseph W. Free

IPC: B64C11/50 ,  B64D31/00 ,  G05D1/06

CPC classification number: B64D31/00 ,  B64C11/50 ,  G05D1/063

Abstract: Disclosed herein is a method of matching engine torques in a power management system having a digital engine control for each of multiple turbine engines. Input data is selected from one source such that each digital engine control utilizes the same set of input data to generate torque commands. As a result, engine torques can be matched to within one percent.

Abstract translation: 本文公开了一种在具有用于多个涡轮发动机中的每一个的数字发动机控制的电力管理系统中匹配发动机扭矩的方法。 从一个源选择输入数据，使得每个数字引擎控制利用相同的一组输入数据来产生转矩指令。 因此，发动机扭矩可以匹配在1％以内。

公开(公告)号：US4772180A

公开(公告)日：1988-09-20

申请号：US902231

申请日：1986-08-29

Applicant: Neil Walker ,  Stanley G. Day ,  Paul D. Collopy ,  George W. Bennett

Inventor： Neil Walker ,  Stanley G. Day ,  Paul D. Collopy ,  George W. Bennett

IPC: B64D31/12 ,  B64C11/30 ,  B64C11/50 ,  F02C9/58 ,  F02K3/072 ,  B64C11/48

CPC classification number: F02C9/58 ,  B64C11/306 ,  B64C11/50 ,  F02K3/072 ,  B64D2027/005 ,  Y02T50/66

Abstract: An integrated control system for coaxial counterrotating aircraft propulsors driven by a common gas turbine engine. The system establishes an engine pressure ratio by control of fuel flow and uses the established pressure ratio to set propulsor speed. Propulsor speed is set by adjustment of blade pitch.

公开(公告)号：US3206640A

公开(公告)日：1965-09-14

申请号：US7940460

申请日：1960-12-29

Applicant: WOODWARD GOVERNOR CO

Inventor： LEESON JR JAMES L

IPC: B64C11/50 ,  B64D31/12 ,  H02P5/52

CPC classification number: B64D31/12 ,  B64C11/50 ,  H02P5/56

公开(公告)号：US3177400A

公开(公告)日：1965-04-06

申请号：US1837960

申请日：1960-03-29

Applicant: GEN MOTORS CORP

Inventor： NELSON ROBERT E

IPC: B64C11/50 ,  H02P5/52 ,  H02P23/00

CPC classification number: B64C11/50 ,  H02P5/56 ,  H02P23/186

公开(公告)号：US2878427A

公开(公告)日：1959-03-17

申请号：US55559555

申请日：1955-12-27

Applicant: UNITED AIRCRAFT CORP

Inventor： BEST STANLEY G

IPC: B64C11/50 ,  H02P5/50

CPC classification number: B64C11/50 ,  H02P5/51