Timothy Scott Nelson

US Patent:

20060282967, Dec 21, 2006

Filed:

Jun 21, 2005

Appl. No.:

11/157706

Inventors:

Brant Williams - Seattle WA, US
Timothy Nelson - Algona WA, US

International Classification:

A47L 13/12

US Classification:

015111000, 015160000

Abstract:

Aspects of the subject matter described herein relate to cleaning golf club heads. In aspects, an appliance is described for removing debris from a golf club head. The appliance may include a base that includes a first base surface and a second base surface, and a brushing assembly disposed along the first base surface of the base. In aspects, an article of footwear that includes features for removing debris may include a base defined by a first base surface and a second base surface, and a brushing assembly disposed along the first base surface of the base. Other aspects are described in the Detailed Description.

US Patent:

61586951, Dec 12, 2000

Filed:

Sep 7, 1999

Appl. No.:

9/390183

Inventors:

Kioumars Najmabadi - Bellevue WA
Monte R. Evans - Federal Way WA
Edward E. Coleman - Lake Forest Park WA
Robert J. Bleeg - Mercer Island WA
Richard S. Breuhaus - Issaquah WA
Dorr M. Anderson - Seattle WA
Timothy A. Nelson - Kirkland WA

Assignee:

The Boeing Company - Seattle WA

International Classification:

B64C 1316

US Classification:

244183

Abstract:

A method of providing speed protection to a neutrally-stable aircraft including the calculation of at least one of a stall protection signal and an overspeed protection signal. The aircraft includes a pitch control system having a command pitch signal received from pilot input to a control column. The protection signal is provided to the pitch control system to limit the commanded pitch signal during flight. The calculation of a stall protection signal includes differencing the aircraft's current airspeed with a reference speed and multiplying the difference by a scaling factor that corresponds to the force required by the pilot to move the control column. The calculation of an overspeed protection signal includes calculating a first signal based on airspeed, calculating a second signal based on Mach, selecting the large of the two signal and passing it through a limiter. The limiter is a function of roll attitude and corresponds to the force required by the pilot to move the control column. Also provided is a method of calculating a flare compensation signal to emulate ground effects encountered by an aircraft while executing a landing.

US Patent:

57226202, Mar 3, 1998

Filed:

May 15, 1995

Appl. No.:

8/441281

Inventors:

Kioumars Najmabadi - Bellevue WA
Monte R. Evans - Federal Way WA
Edward E. Coleman - Lake Forest Park WA
Robert J. Bleeg - Mercer Island WA
Richard S. Breuhaus - Issaquah WA
Dorr Marshall Anderson - Seattle WA
Timothy A. Nelson - Kirkland WA

Assignee:

The Boeing Company - Seattle WA

International Classification:

B64C 1318

US Classification:

244181

Abstract:

Disclosed is a pitch-axis stability and command augmentation system (19) in which a pilot column input (. delta. sub. C) is provided to a pitch command processor (26), the output of which is a C*U feedforward command (C*U. sub. FFC) that is supplied as an additive input to a combining unit (20). The combining unit (20) receives a second additive input of an augmented feedback command signal (AFB. sub. COM). The resulting output is filtered and generates an elevator command signal (. delta. sub. e,FILT). The command processor (26) additionally supplies a corrected column position signal (. delta. sub. C,COR) to a pitch command C*U processor (26) that converts the corrected column position signal (. delta. sub. C,COR) into a C*U pitch command (C*U. sub. PilotCmd), representative of the pilot's requested elevator pitch which is generated by movement of the control cola.

US Patent:

6325333, Dec 4, 2001

Filed:

Jul 20, 2000

Appl. No.:

9/619798

Inventors:

Kioumars Najmabadi - Bellevue WA
Monte R. Evans - Federal Way WA
Edward E. Coleman - Lake Forest Park WA
Robert J. Bleeg - Mercer Island WA
Richard S. Breuhaus - Issaquah WA
Dorr Marshall Anderson - Seattle WA
Timothy A. Nelson - Kirkland WA

Assignee:

The Boeing Company - Seattle WA

International Classification:

B64C 1318

US Classification:

244181

Abstract:

A bias correction system for use in a neutrally-stable aircraft having a control column and a pitch control system is provided. The position of the control column is generally represented by a control column position signal. The bias correction system is for removing control column bias when the control column is in a neutral position. The bias correction system includes a first combining unit for combining the control column position signal and a correction signal, and a switch. The switch includes activated and deactivated states. The switch is set to the deactivated state when the control column is physically displaced from its neutral position. The deactivated state allows the correction signal to remain at its last value, the activated state allows the correction signal to equal approximately the control column position signal. In one embodiment, the bias correction system includes a smoothing filter for receiving the control column position signal and outputting a smoothed correction signal when the switch is in the activated state. In another embodiment, the bias correction system includes a unit for limiting the correction signal to control column position signal values within a limited predefined range.