William V Bryant

US Patent:

7979938, Jul 19, 2011

Filed:

Dec 9, 2004

Appl. No.:

10/582837

Inventors:

Ronald C. Lilley - Federal Way WA, US
Scott E. Hall - Issaquah WA, US
John W. Pace - Bothell WA, US
William E. Bryant - North Bend WA, US
Joseph W. Grez - North Bend WA, US

Assignee:

Koninklijke Philips Electronics N.V. - Eindhoven

International Classification:

A61C 17/32
A61C 17/22
A61C 17/34
H02P 7/00

US Classification:

15 221, 310 10

Abstract:

The drive system drives a brushhead at a driving frequency. The drive system includes a frequency modulation system which changes. the driving frequency about a center frequency in such a manner, with selected frequency deviation and modulation frequency, which interacts with the resonance of the brushhead to produce a change of amplitude in the movement of the brushhead within a range of 5-30%.

US Patent:

56695829, Sep 23, 1997

Filed:

May 12, 1995

Appl. No.:

8/440339

Inventors:

William F. Bryant - Bellevue WA
Arun A. Nadkarni - Kirkland WA
Paul Salo - Seattle WA

Assignee:

The Boeing Company - Seattle WA

International Classification:

B64C 1316

US Classification:

244 76C

Abstract:

A method and apparatus for reducing the unwanted sideways motion of an airplane by reducing the lateral side loads and upsets caused by atmospheric turbulence and gusts is disclosed. A rudder modification command that causes the rudder command of the airplane to be changed in a manner that relieves the net force across the vertical stabilizer of the airplane caused by atmospheric turbulence and gusts is produced. More specifically, the pressure differential across opposite sides of the vertical stabilizer is measured and used to produce a rudder deflection value that is roll rate and yaw rate compensated. The compensated deflection value is high-pass filtered with a corner frequency that is twenty-five percent (25%) of the Dutch roll frequency of the airplane. The result is a first rudder deflection value that is subtractively combined with a second rudder deflection value. The second rudder deflection value is derived by gain adjusting and low-pass filtering the inertial sideslip angle rate value produced by the airplane's yaw damper.

US Patent:

54644429, Nov 7, 1995

Filed:

Jul 12, 1993

Appl. No.:

8/090608

Inventors:

Edward W. Burt - Bellevue WA
William E. Bryant - Everett WA
David M. Crist - Seattle WA

Assignee:

Model & Instrument Development Corporation - Seattle WA

International Classification:

A61F 260

US Classification:

623 27

Abstract:

A prosthetic support pylon is disclosed that is comprised of a tubular inner member being deformable along its longitudinal axis and comprised of a material having a composite stiffness value of between about 30,000 pounds. multidot. inch. sup. 2 and about 200,000 pounds. multidot. inch. sup. 2 and a tubular outer member over the tubular inner portion. The tubular outer member is comprised of a dampening material which slows the release of the energy produced by the tubular inner member upon return from deformation along its longitudinal axis. The material of the tubular inner member is comprised of a support matrix and of stiffening fibers which are most preferably selected from a group consisting of carbon, graphite, fiberglass, ultra high molecular weight polyethylene and aramid. The support matrix of the tubular inner member is most preferably selected from the group consisting of epoxy, vinyl ester and polyester. The tubular outer member is comprised of a thermoplastic material most preferably selected from a group consisting of polyamide, acetal, aromatic polyester, and polysulfone.