David D Schultz

Author:

David A. Schultz

ISBN #:

0312119429

Author:

David A. Schultz

ISBN #:

0534612636

Author:

David A. Schultz

ISBN #:

0814798136

Author:

David A. Schultz

ISBN #:

0814798144

Author:

David A. Schultz

ISBN #:

0816047995

Author:

David A. Schultz

ISBN #:

0820422452

Author:

David A. Schultz

ISBN #:

0820433799

Author:

David A. Schultz

ISBN #:

0820434922

US Patent:

D494450, Aug 17, 2004

Filed:

Jul 29, 2003

Appl. No.:

29/187178

Inventors:

David P. Schultz - Arlington TX
Joseph B. Diller - Hurst TX

Assignee:

Bell Helicopter Textron, Inc. - Fort Worth TX

International Classification:

0805

US Classification:

D 8356

US Patent:

7003949, Feb 28, 2006

Filed:

May 16, 2003

Appl. No.:

10/490276

Inventors:

Carlos A. Fenny - Arlington TX, US
David P. Schultz - Arlington TX, US
Ian L. Price - Burntwood, GB
David A. Curd - Walsall, GB

Assignee:

Bell Helicopter Textron Inc. - Fort Worth TX

International Classification:

F15B 11/08
F15B 13/10

US Classification:

60468, 91437, 91447, 13759615, 13759616

Abstract:

An integrated three function valve (ITFV) that combines the functions of a bypass valve (e. g. ) into a single assembly is disclosed. The ITFV allows continued operation after any two failures. With the integrated three function valve, no combination of electrical or hydraulic component failures, regardless of expected failure rate, will prevent an actuator from continued safe operation.

US Patent:

7165950, Jan 23, 2007

Filed:

Dec 15, 2003

Appl. No.:

10/736161

Inventors:

Carlos A. Fenny - Arlington TX, US
Darrel B. Bryan - Basiglio, IT
David P. Schultz - Arlington TX, US

Assignee:

Bell Helicopter Textron Inc. - Fort Worth TX

International Classification:

F04B 1/26
F04B 49/24
F15B 21/02
F16D 31/02
F04F 1/00

US Classification:

417270, 417290, 417308, 91 38, 60468, 137130

Abstract:

A two-stage pressure relief valve for use with hydraulic systems is disclosed. The two-stage pressure relief valve has a first stage that relieves increases in hydraulic system pressure over the normal operating pressure and up to a selected threshold pressure level, and a second stage that brings the hydraulic system pressure down to a selected reduced operating pressure that is below the normal operating pressure in response to increases in the operating pressure over the threshold pressure level.

US Patent:

8562888, Oct 22, 2013

Filed:

Jul 30, 2009

Appl. No.:

12/512238

Inventors:

James A. Kelley - Benbrook TX, US
Michael B. Weaver - Fort Worth TX, US
David Schultz - Cleburne TX, US
Jason O'Rustus LeFever - Midland TX, US

Assignee:

Lockheed Martin Corporation - Bethesda MD

International Classification:

B29C 45/14

US Classification:

264263, 249 98

Abstract:

A system and method for dispensing a sealant over aircraft fasteners secured to a surface in the aircraft. The system includes a nozzle tip having a shroud configured for placement over the fasteners. Sealant is metered to the shroud via an orifice within the nozzle tip. The shroud is sized to leave a space between it and the fastener to control the amount of sealant applied to the fastener upper surface and along the interface between the fastener and aircraft surface. Pressurized fluid urges the sealant through the orifice.

US Patent:

20130209252, Aug 15, 2013

Filed:

Feb 9, 2012

Appl. No.:

13/370130

Inventors:

Corey J. Dickman - Arlington TX, US
Carlos A. Fenny - Arlington TX, US
David P. Schultz - Grand Prairie TX, US

Assignee:

BELL HELICOPTER TEXTRON INC. - FORT WORTH TX

International Classification:

F01D 7/00

US Classification:

416 1, 416114

Abstract:

The main rotor control system includes a rise/fall swashplate assembly that is coupled to three triplex actuators. The swashplate assembly is configured to provide full collective and cyclic pitch controls. Each triplex actuator includes three piston/cylinder assemblies in parallel. Selective actuation of each triplex actuator is controlled by a fly-by-wire system in conjunction with three flight control computers and three hydraulic power packs. Integrated three function valves can be associated with an individual manifold for each piston/cylinder assembly of each triplex actuator, the integrated three function valve be configured to insure safe operation of the triplex actuator during a failure of a certain piston/cylinder assembly.

US Patent:

20220402627, Dec 22, 2022

Filed:

Nov 4, 2021

Appl. No.:

17/519321

Inventors:

- Fort Worth TX, US
David Perry Schultz - Grand Prairie TX, US
Robert Reynolds - Euless TX, US
Rodney Cahoon - Argyle TX, US

Assignee:

Bell Textron Inc. - Fort Worth TX

International Classification:

B64D 47/00
G05D 23/19
F15B 1/26
F15B 15/20

Abstract:

An aircraft thermal hydraulic active-warming system includes an active thermal-warming valve interoperably coupled between a hydraulic pressure line and a hydraulic low-pressure return line and a hydraulic actuator arranged in parallel with the active thermal-warming valve between the hydraulic pressure line and the hydraulic low-pressure return line.

US Patent:

20160200430, Jul 14, 2016

Filed:

May 23, 2014

Appl. No.:

14/286197

Inventors:

- Fort Worth TX, US
Carlos A. Fenny - Arlington TX, US
David Schultz - Grand Prairie TX, US

Assignee:

BELL HELICOPTER TEXTRON INC. - Fort Worth TX

International Classification:

B64C 27/12
B64C 13/50
B64C 27/82

Abstract:

In some embodiments, an actuation system includes a an actuator assembly, a yoke, and a control rod. The actuator assembly comprises a first actuator. The first actuator is configured to extend in a first direction and retract in a second direction opposite of the first direction. The yoke is coupled to the first actuator at a first actuator end proximate to the first direction. The control rod is coupled to the yoke at a first control rod end and extends in the second direction past the actuator assembly to a second end in mechanical communication with an output device.