Jack Stewart Jacobs

US Patent:

6349903, Feb 26, 2002

Filed:

Feb 15, 2001

Appl. No.:

09/784771

Inventors:

John Harold Caton - Edwardsville IL
Michael James Hobey - St. Louis MO
John David Groeneveld - Maryland Heights MO
Jack Howard Jacobs - Glendale AZ
Robert Henry Wille - St. Charles MO

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64C 900

US Classification:

244213

Abstract:

A control surface ( ) for an aircraft has a reinforced elastomer surface ( ) on a surface of the aircraft and has a perimeter ( ) attached to the aircraft. An actuation mechanism ( ) moves the reinforced elastomer surface ( ) from a first position, substantially conforming to a moldline of the aircraft, to a second position, protruding from the moldline of the aircraft.

US Patent:

6354576, Mar 12, 2002

Filed:

Oct 22, 1999

Appl. No.:

09/426392

Inventors:

Jack H. Jacobs - Glendale AZ
Tristram Tupper Hyde - Phoenix AZ

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

F16F 500

US Classification:

26714014

Abstract:

A vibration isolator which may be constructed in the form of a cube for use in retrofitting a device which is subjected to unwanted vibration present in an attached member which utilizes an active vibration isolator and a passive isolator in series between the members and which may include an overload protection device in the form of a deformable member in parallel with the isolators.

US Patent:

6415674, Jul 9, 2002

Filed:

Apr 28, 2000

Appl. No.:

09/561335

Inventors:

L. Porter Davis - Phoenix AZ
Christopher J. Heiberg - Peoria AZ
Jack H. Jacobs - Glendale AZ

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

F16H 5518

US Classification:

74409, 74411

Abstract:

A gear drive having a third order damper operating with the antibacklash gear so as to lower the impact of the antibacklash gear at high torques to reduce gear wear while maintaining good contact with the antibacklash gear at lower torques to maintain high accuracy and bandwidth.

US Patent:

6508437, Jan 21, 2003

Filed:

Jan 15, 2002

Appl. No.:

10/050066

Inventors:

Toren S. Davis - Peoria AZ
Jack H. Jacobs - Glendale AZ
Steven L. Hadden - Peoria AZ

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

B64G 164

US Classification:

244158R, 244161, 292256, 292DIG 66

Abstract:

A spacecraft payload, suspended by an isolator, is locked down during launch by using a compliant member to pull on a pin, clamping the payload against the launch lock. The payload is unlocked, after launch, by heating a shape memory alloy to move the pin to overcome the compliant member, releasing the payload from launch lock. The payload may be re-locked for reentry by heating another shape memory alloy to push the pin against the other shaped memory alloy.

US Patent:

6679457, Jan 20, 2004

Filed:

Jan 13, 2003

Appl. No.:

10/341753

Inventors:

Marc E. Meffe - Glendale AZ
Jack H. Jacobs - Glendale AZ

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

H64G 128

US Classification:

244165, 244 315, 244 32, 244 79, 74 534

Abstract:

A reaction wheel system is provided that includes at least two rotors. The first rotor is the primary rotor that provides the large output torques to the vehicle. The second rotor is a vernier control rotor. The primary rotor and vernier control rotor each rotate about a common axis. The vernier control rotor has an inertial mass that is less than the inertial mass of the primary rotor, and rotates independently of the primary rotor. Because the vernier control rotor can be rotated independently from the primary rotor, it can be used to significantly improve the performance of the reaction wheel system. Specifically, the vernier control rotor is used to provide relatively small output torques. These relatively small output torques can be used to reduce the disturbances created by motor ripple, provide precise torque output control and/or reduce the disturbances created by static friction.

US Patent:

6775599, Aug 10, 2004

Filed:

Jul 10, 2002

Appl. No.:

10/192838

Inventors:

Marc E. Meffe - Glendale AZ
Jack H. Jacobs - Glendale AZ

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

G06F 1700

US Classification:

701 13, 244164, 244165

Abstract:

A plurality of sensors provide spacecraft attitude signals to reaction wheel assemblies which provide converted signals to a flight controller that controls the reaction wheel assemblies. The reaction wheel assemblies include a secondary power supply to power the sensors, and power can be regenerated from the reaction wheels. A microcomputer in the reaction wheel assemblies can control the reaction wheel assemblies in place of the flight controller.

US Patent:

6891498, May 10, 2005

Filed:

Mar 28, 2002

Appl. No.:

10/108306

Inventors:

Jack H. Jacobs - Glendale AZ, US
Marc E. Meffe - Glendale AZ, US

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

H04B007/185

US Classification:

342355, 244164

Abstract:

An inertial reference system for a spacecraft includes an attitude control assembly and a plurality of force sensors. The attitude control assembly is coupled to a spacecraft body at a plurality of attachment points and at least one of the plurality of force sensors is integrated at each of the attachment points. In one embodiment, the force sensors are piezoelectric transducers. In another embodiment, the control assembly is coupled to the spacecraft body at four attachment points. In yet another embodiment, each of the force sensors is preloaded by a bolt that attaches the attitude control assembly to the spacecraft body.

US Patent:

7057734, Jun 6, 2006

Filed:

Jul 23, 2003

Appl. No.:

10/624688

Inventors:

Jack H. Jacobs - Glendale AZ, US
Ed C. Moulton - Tarpon Springs FL, US

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

G01C 19/72
G01C 19/02
B64G 1/28

US Classification:

356460, 244165, 74 522

Abstract:

The present invention relates to a reaction wheel assembly and fiber optic gyro device. The device includes a reaction wheel assembly having a reaction wheel assembly housing, a fiber optic gyro coil integrated with the reaction wheel assembly housing, and a fiber optic gyro electronics integrated with the reaction wheel assembly housing. The fiber optic gyro coil may be wound around the reaction wheel assembly housing. The gyro coil may also be located within the reaction wheel assembly housing.