Kathleen M Doherty

US Patent:

61389986, Oct 31, 2000

Filed:

May 12, 1998

Appl. No.:

9/076499

Inventors:

A. Dale Parker - Rolling Hills Estates CA
Emil M. Shtarkman - Marina Del Rey CA
Kathleen M. Doherty - Rancho Palos Verdes CA

Assignee:

TRW Inc. - Redondo Beach CA

International Classification:

F16F 500

US Classification:

26714015

Abstract:

A motion control apparatus is provided for controlling oscillations of an appendage 10 coupled to a spacecraft 12. A plurality of guidelines 20 extend between remote portions 22 of the appendage 10 and the appendage base 14. A plurality of motion control elements 28 are interposed between the appendage base 14 and the spacecraft 12 and/or along the guidelines 20 between the appendage base 14 and the remote portions 22 of the appendage 10 or both. The motion control elements 28 include visco-elastic fluid, electro-rheological fluid, magnetic-rheological fluid, or a piezo-electric stack so that a motion control property of the motion control elements 28 may be varied according to the magnitude of an electric or magnetic field source 30 coupled thereto.

US Patent:

61965286, Mar 6, 2001

Filed:

Mar 15, 2000

Appl. No.:

9/525883

Inventors:

Emil M. Shtarkman - Marina Del Rey CA
Kathleen M. Doherty - Rancho Palos Verdes CA
A. Dale Parker - Rolling Hills Estates CA

Assignee:

TRW Inc. - Redondo Beach CA

International Classification:

F16M 100

US Classification:

26714014

Abstract:

A vibration control system is provided for an appendage such as an antenna 10 coupled to a platform such as a spacecraft 12. The antenna 10 is coupled at a base 14 so as to extend from the spacecraft 12. A plurality of guidelines 20 extend between remote portions 22 of the antenna 10 and the antenna base 14. A plurality of motion control elements 36 are provided within the antenna structure for reducing oscillation settling time of the antenna 10 relative to the spacecraft 12. The motion control elements 36 include a material disposed therein having its damping response changed according to the magnitude of an electric or magnetic field applied thereto.

US Patent:

6082719, Jul 4, 2000

Filed:

May 12, 1998

Appl. No.:

9/076637

Inventors:

Emil M. Shtarkman - Marina Del Rey CA
Kathleen M. Doherty - Rancho Palos Verdes CA
A. Dale Parker - Rolling Hills Estates CA

Assignee:

TRW Inc. - Redondo Beach CA

International Classification:

F16M 100

US Classification:

26714014

Abstract:

A vibration control system is provided for an appendage such as an antenna 10 coupled to a platform such as a spacecraft 12. The antenna 10 is coupled at a base 14 so as to extend from the spacecraft 12. A plurality of guidelines 20 extend between remote portions 22 of the antenna 10 and the antenna base 14. A plurality of motion control elements 36 are provided within the antenna structure for reducing oscillation settling time of the antenna 10 relative to the spacecraft 12. The motion control elements 36 include a material disposed therein having its damping response changed according to the magnitude of an electric or magnetic field applied thereto.

US Patent:

63134012, Nov 6, 2001

Filed:

Dec 18, 1998

Appl. No.:

9/216151

Inventors:

Michael J. Triller - Hermosa Beach CA
Christopher W. Felts - Lakewood CA
Kathleen M. Doherty - Rancho Palos Verdes CA
Lisa R. Hill - Rancho Palos Verdes CA
Craig A. Lavinsky - Manhattan Beach CA

Assignee:

TRW Inc. - Redondo Beach CA

International Classification:

H01L 2328
H05K 506

US Classification:

174 522

Abstract:

A singly or doubly encapsulated actuator/sensor package in which a ceramic actuator/sensor (10) may be first encapsulated in a primary encapsulating material (12) and is encapsulated in a fiber-reinforced composite material (20, 22). A combination of the material and ply angles (. theta. ) of the fiber-reinforced composite material (20, 22) are used to control selection of a composite coefficient of thermal expansion (CTE) and the stiffness or compliance of the package with respect to a selected axis. By optimal selection of the material and the ply angle, based upon a suitable actuation strength figure of merit, a CTE of zero or a CTE matching that of an underlying structural member (24) is obtained, while simultaneously maximizing the actuation strength in a selected actuation direction. Application of the invention to precision structures permits the underlying structures to be designed with very low stiffness, because precise, thermally stable, pointing or shaping actuation forces may be obtained in a thermally stable manner.

US Patent:

61965294, Mar 6, 2001

Filed:

Mar 15, 2000

Appl. No.:

9/526152

Inventors:

Emil M. Shtarkman - Marina Del Rey CA
Kathleen M. Doherty - Rancho Palos Verdes CA
A. Dale Parker - Rolling Hills Estates CA

Assignee:

TRW Inc. - Redondo Beach CA

International Classification:

F16F 904

US Classification:

26714014

Abstract:

A vibration control system is provided for an appendage such as an antenna 10 coupled to a platform such as a spacecraft 12. The antenna 10 is coupled at a base 14 so as to extend from the spacecraft 12. A plurality of guidelines 20 extend between remote portions 22 of the antenna 10 and the antenna base 14. A plurality of motion control elements 36 are provided within the antenna structure for reducing oscillation settling time of the antenna 10 relative to the spacecraft 12. The motion control elements 36 include a material disposed therein having its damping response changed according to the magnitude of an electric or magnetic field applied thereto.