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公开(公告)号：US20200283126A1
公开(公告)日：2020-09-10
申请号：US16388374
申请日：2019-04-18
Applicant: THE BOEING COMPANY
Inventor： John Jian Dong , Michael James Duffy , Douglas C. Cameron , Naveed Moayyed Hussain
Abstract: A multi-rotor vehicle includes a plurality of electric motors and edge computing systems (ECSs). The electric motors are operatively coupled to respective rotors, and cause the respective rotors to rotate relative to the airframe. The ECSs are independent, distinct and distributed to the electric motors, each operatively coupled to a respective electric motor and thereby a respective rotor. Each ECS is configured to acquire and process sensor data for the respective rotor to determine rotor status information, and execute motor commands to control the respective electric motor and thereby the respective rotor. Each ECS is configured as an integrated flight computer and motor controller.
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公开(公告)号：US20190296761A1
公开(公告)日：2019-09-26
申请号：US15933991
申请日：2018-03-23
Applicant: THE BOEING COMPANY
Inventor： Douglas C. Cameron , Dwayne C. Merna , Manu Sharma
Abstract: Demodulation circuitry includes an input terminal configured to be coupled to an analog-to-digital converter (ADC) and configured to receive a plurality of ADC outputs. The plurality of ADC outputs are generated based on resolver outputs. The demodulation circuitry also includes a rectifier configured to rectify the plurality of ADC outputs. Rectifying the plurality of ADC outputs preserves a phase of the plurality of ADC outputs. The demodulation circuitry includes amplitude determination circuitry configured to determine, based on the rectified plurality of ADC outputs, demodulated amplitude values corresponding to the resolver outputs. The demodulation circuitry further includes angle computation circuitry configured to generate position outputs based on the demodulated amplitude values.
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公开(公告)号：US20190293429A1
公开(公告)日：2019-09-26
申请号：US15934034
申请日：2018-03-23
Applicant: THE BOEING COMPANY
Inventor： Douglas C. Cameron , Dwayne C. Merna , Manu Sharma
Abstract: An apparatus includes a coarse resolver configured to output coarse position signals indicative of a coarse position of a drive shaft of a motor. The apparatus also includes a fine resolver configured to output fine position signals indicative of a fine position of the drive shaft of the motor. The apparatus further includes a control circuit. The control circuit is configured to receive the coarse position signals from the coarse resolver and the fine position signals from the fine resolver and generate an initial position output, based on the coarse position signals, that indicates an initial position of the drive shaft. The control circuit is further configured to generate a subsequent position output, based on the fine position signals, that indicates a subsequent position of the drive shaft.
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公开(公告)号：US20190291898A1
公开(公告)日：2019-09-26
申请号：US15934066
申请日：2018-03-23
Applicant: THE BOEING COMPANY
Inventor： Douglas C. Cameron , Dwayne C. Merna
Abstract: Feedback control circuitry includes rate limiter circuitry configured to generate a rate limited position command based on a position command for a controlled component and based on a speed command for the controlled component. The feedback control circuitry also includes error adjustment circuitry configured to apply a control gain to an error signal to generate an adjusted error signal. The error signal is based on position feedback and the rate limited position command, and the position feedback indicates a position of the controlled component. The feedback control circuitry further includes an output terminal configured to output a current command generated based on the adjusted error signal.
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公开(公告)号：US20150115108A1
公开(公告)日：2015-04-30
申请号：US14064366
申请日：2013-10-28
Applicant: The Boeing Company
Inventor： Christopher Pete Benson , Leonard J. Quadracci , Douglas C. Cameron
CPC classification number: B60L11/1809 , B60L53/00 , B64C39/024 , B64C2201/042 , B64C2201/066 , B64D27/24 , B64D41/00 , Y02T50/44 , Y02T50/53 , Y02T50/54 , Y02T50/62
Abstract: A method and apparatus for controlling an electric aircraft is presented. An apparatus comprises a controller. The controller is configured to identify a state for an electric aircraft. The controller is further configured to identify a group of recharging parameters for a group of electric motors in an electric propulsion system. The electric propulsion system is configured to move the electric aircraft based on the state for the group of electric motors for the electric aircraft. The controller is still further configured to recharge a power source for the electric aircraft using the group of recharging parameters to control recharging of the power source with the group of electric motors when a recharge state is present for the electric aircraft.
Abstract translation: 提出了一种用于控制电动飞机的方法和装置。 一种装置包括控制器。 控制器被配置为识别电动飞机的状态。 控制器还被配置为识别电力推进系统中的一组电动机的一组充电参数。 电推进系统被配置为基于用于电动飞机的电动机组的状态移动电动飞机。 控制器还被配置为使用一组充电参数为电动飞机的电源充电，以在电动飞机存在充电状态时控制电动机组的电源的再充电。
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Patent Agency Ranking
公开(公告)号：US20150084561A1
公开(公告)日：2015-03-26
申请号：US14034964
申请日：2013-09-24
Applicant: The Boeing Company
Inventor： Christopher Pete Benson , Peng Zeng , Douglas C. Cameron
IPC: H02P6/04
CPC classification number: H02P6/04 , B60L15/2045 , G05B2219/50191 , H02P27/04 , H02P27/085 , H02P29/02 , H02P29/60 , Y02T10/644 , Y02T10/645 , Y02T10/646 , Y02T10/72 , Y02T10/7283
Abstract: A method and apparatus for controlling a group of electric motors. A controller is configured to identify a group of switching frequencies for a desired signature for the group of electric motors. The controller is further configured to control switching of a current supplied to the group of electric motors with the group of switching frequencies for the desired signature identified.
Abstract translation: 一种用于控制一组电动机的方法和装置。 控制器被配置为识别用于该组电动机的期望签名的一组切换频率。 所述控制器还被配置为控制提供给所述一组电动机的电流与所识别的期望签名的开关频率组的切换。
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公开(公告)号：US20150008849A1
公开(公告)日：2015-01-08
申请号：US14096614
申请日：2013-12-04
Applicant: The Boeing Company
Inventor： Christopher Pete Benson , Douglas C. Cameron
IPC: H02P6/00
CPC classification number: H02P25/03 , B60L1/00 , B60L1/003 , B60L3/003 , B60L3/0046 , B60L3/0061 , B60L7/14 , B60L7/22 , B60L11/1866 , B60L15/06 , B60L15/08 , B60L2240/421 , B60L2240/423 , B60L2240/427 , B60L2240/429 , B60L2240/527 , B60L2240/529 , B60L2240/547 , B60L2240/549 , B60L2240/80 , H02H7/0838 , H02H7/0844 , H02H7/085 , H02H7/12 , H02M1/00 , H02P6/00 , H02P6/085 , H02P6/28 , H02P9/006 , H02P9/10 , H02P23/14 , H02P25/034 , H02P27/085 , H02P29/0241 , H02P29/027 , H02P29/032 , H02P2207/05 , Y02T10/644 , Y02T10/7005 , Y02T10/7061
Abstract: A method and apparatus for controlling a motor. The motor comprises windings. A switch bridge comprising a plurality of switches is configured to couple a power source to the windings. A motor controller is configured to control the plurality of switches. An undesired condition identifier is configured to identify an undesired condition when the motor is providing power to the power source, wherein the undesired condition is defined with respect to a characteristic of the power source. An undesired condition reducer is configured to reduce the undesired condition in response to identifying the undesired condition by the undesired condition identifier.
Abstract translation: 一种用于控制电动机的方法和装置。 电机包括绕组。 包括多个开关的开关桥被配置为将电源耦合到绕组。 电动机控制器被配置为控制多个开关。 非期望条件标识符被配置为当电动机向电源提供电力时识别不期望的状况，其中相对于电源的特性定义不期望的状况。 响应于通过不需要的条件标识符识别不期望的状况，不期望的条件减少器被配置为减少不期望的状况。
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公开(公告)号：US12040730B2
公开(公告)日：2024-07-16
申请号：US16880499
申请日：2020-05-21
Applicant: The Boeing Company
Inventor： Bradley J. Rafferty , Mary E. Beckman , Andrew Leung , Douglas C. Cameron
IPC: H02P29/024 , B64C21/04 , B64C21/08 , B64D45/00
CPC classification number: H02P29/024 , B64C21/04 , B64C21/08 , B64D2045/0085 , B64D2221/00
Abstract: Example active flow control systems and methods for aircraft are described herein. An example an active flow control system includes a plenum, a plurality of nozzles fluidly coupled to the plenum, configured to eject high pressure air across a control surface, a compressor to supply pressurized air to the plenum, an electric motor to drive the compressor, and a control system to determine an amount of power input to the electric motor, determine a current speed of the electric motor, and determine a fault has occurred in the active flow control system based on the current speed of the electric motor.
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公开(公告)号：US11267574B2
公开(公告)日：2022-03-08
申请号：US14064366
申请日：2013-10-28
Applicant: The Boeing Company
Inventor： Christopher Pete Benson , Leonard J. Quadracci , Douglas C. Cameron
Abstract: A method and apparatus for controlling an electric aircraft. An apparatus comprises a motor, a power source, and a four-quadrant controller. The motor operates in four quadrants of operational space and operates in one of an accelerating state and a regenerative braking state. A total current flows through the motor. The power source is connected to the motor, and when the motor operates in the regenerative braking state, the total current flows through the power source. The power source has a maximum allowable current. The four-quadrant controller is programmed to identify a recharging parameter, brake the motor to initiate the regenerative braking state when the recharging parameter is present, recharge the power source with the total current during the regenerative braking state, and control a duty cycle of the motor such that the total current does not exceed the maximum allowable current during the regenerative braking state.
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公开(公告)号：US10913550B2
公开(公告)日：2021-02-09
申请号：US15934066
申请日：2018-03-23
Applicant: THE BOEING COMPANY
Inventor： Douglas C. Cameron , Dwayne C. Merna
IPC: H02P21/05 , B64G1/28 , G01C19/30 , B64G1/36 , B64G1/24 , G01C21/18 , B64G1/38 , G01C19/06 , H02P27/08
Abstract: Feedback control circuitry includes rate limiter circuitry configured to generate a rate limited position command based on a position command for a controlled component and based on a speed command for the controlled component. The feedback control circuitry also includes error adjustment circuitry configured to apply a control gain to an error signal to generate an adjusted error signal. The error signal is based on position feedback and the rate limited position command, and the position feedback indicates a position of the controlled component. The feedback control circuitry further includes an output terminal configured to output a current command generated based on the adjusted error signal.
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