Douglas C Cameron

US Patent:

7142971, Nov 28, 2006

Filed:

Feb 19, 2003

Appl. No.:

10/369285

Inventors:

Eric D. Brown - Huntington Beach CA, US
Douglas C. Cameron - Seal Beach CA, US
Krish R. Krothapalli - Redondo Beach CA, US
Todd M. Williams - Long Beach CA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

G06F 19/00

US Classification:

701110, 701 23, 701 25, 701 26, 244183

Abstract:

The method and system for automatically controlling a path of travel of a vehicle include engaging an automatic control system when the security of the onboard controls is jeopardized. Engagement may be automatic or manual from inside the vehicle or remotely via a communication link. Any onboard capability to supersede the automatic control system may then be disabled by disconnecting the onboard controls and/or providing uninterruptible power to the automatic control system via a path that does not include the onboard accessible power control element(s). The operation of the vehicle is then controlled via the processing element of the automatic control system. The control commands may be received from a remote location and/or from predetermined control commands that are stored onboard the vehicle.

US Patent:

20070235592, Oct 11, 2007

Filed:

Dec 5, 2006

Appl. No.:

11/633910

Inventors:

Phillippe Horn - Long Beach CA, US
Douglas Cameron - Seal Beach CA, US
Tony Lytle - Huntington Beach CA, US
Eric Brown - Huntington Beach CA, US

International Classification:

B64G 1/00

US Classification:

244158100

Abstract:

A method and apparatus for separating a first spacecraft from a rotating second spacecraft within a separation corridor having a trailing boundary surface is disclosed. The method and apparatus use a non-stationkeeping trajectory that uses a greater portion of the separation corridor to reduce thrust requirements and reduce the time necessary for separation.

US Patent:

20120078446, Mar 29, 2012

Filed:

Sep 28, 2010

Appl. No.:

12/892853

Inventors:

Douglas C. Cameron - Ladera Ranch CA, US

Assignee:

THE BOEING COMPANY - Chicago IL

International Classification:

G05D 1/00

US Classification:

701 3

Abstract:

Presented is a system and method for controlling an actuator in a multirate control system using an integrated upsampler and filter, comprising an incremental command limiter for changing a command from a first control system into a limited incremental command in a second control system, a lead-lag filter for filtering the limited incremental command to attenuate high frequencies, and a feed forward path for reducing phase loss in rate output signal at low frequencies. In embodiments, a command position signal received at the sampling rate of the first control system is interpolated into incremental command position signals at the sampling rate of the second control system. Position error signals and rate error signals from the devices being controlled are used as feedback to further stability the control loops.

US Patent:

20210362840, Nov 25, 2021

Filed:

May 21, 2020

Appl. No.:

16/880499

Inventors:

- Chicago IL, US
Mary E. Beckman - West Chester PA, US
Andrew Leung - Philadelphia PA, US
Douglas C. Cameron - Ladera Ranch CA, US

International Classification:

B64C 21/04
B64D 41/00
H02P 29/024

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.

US Patent:

20200283125, Sep 10, 2020

Filed:

Apr 18, 2019

Appl. No.:

16/388356

Inventors:

- Chicago IL, US
Michael James Duffy - Lansing NY, US
Douglas C. Cameron - Ladera Ranch CA, US
Naveed Moayyed Hussain - Palos Verdes Peninsula CA, US

International Classification:

B64C 13/24
G05D 1/08
B64C 39/02
B64C 27/32

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. The ECSs are configured according to a model in which any of the ECSs is selectable as a primary ECS, and others of the ECSs are operable as secondary ECSs, the secondary ECSs configured to communicate respective rotor status information to the primary ECS, and the primary ECS configured to provide the motor commands to the secondary ECSs.

US Patent:

20200283126, Sep 10, 2020

Filed:

Apr 18, 2019

Appl. No.:

16/388374

Inventors:

- Chicago IL, US
Michael James Duffy - Lansing NY, US
Douglas C. Cameron - Ladera Ranch CA, US
Naveed Moayyed Hussain - Palos Verdes Peninsula CA, US

International Classification:

B64C 13/24
G05D 1/08
B64C 39/02
B64C 27/32

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.

US Patent:

20170324362, Nov 9, 2017

Filed:

May 6, 2016

Appl. No.:

15/148562

Inventors:

- Chicago IL, US
Douglas Conrad Cameron - Ladera Ranch CA, US

International Classification:

H02P 23/14
H02P 23/00

Abstract:

A method and apparatus for controlling regeneration for a motor. An instantaneous voltage provided by a power supply to the motor is identified using a voltage signal received from a voltage sensor. A new average voltage is computed for the motor using the instantaneous voltage, a previously computed average voltage, and a weight factor for the instantaneous voltage. A difference between the new average voltage and the instantaneous voltage is compared to a selected threshold to determine whether a regeneration condition exists. Operation of the motor is controlled such that a duty cycle of the motor does not decrease in response to a determination that the regeneration condition exists.

US Patent:

20160154384, Jun 2, 2016

Filed:

Feb 17, 2014

Appl. No.:

14/182151

Inventors:

- Chicago IL, US
Douglas C. Cameron - Ladera Ranch CA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

G05B 6/02
B64C 19/00

Abstract:

A multi-rate system for controlling an actuator may include an incremental command limiter that receives a command from a first control system and outputs a limited incremental command; a feed-forward that receives the limited incremental command from the incremental command limiter and outputs a feed forward rate command; a first differentiator that limits the limited incremental command to a maximum allowable command; an upsampler state that outputs a current state back to the differentiator; a first summer that receives the limited incremental command and the current state from the upsampler state, and outputs an incremental position command; and a second summer that combines the incremental position command and the feed forward rate command to produce a rate error output signal.