Calvin P Ito

US Patent:

6938679, Sep 6, 2005

Filed:

Sep 15, 1998

Appl. No.:

09/153118

Inventors:

Calvin H. Ito - West Hills CA, US
Nigel C. Rowe - Fountain Valley CA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

F28D015/00

US Classification:

16510421, 165 41

Abstract:

A heat transport apparatus comprises an evaporator saddle having a pair of bores for housing two evaporators. The apparatus also comprises a condenser saddle having a pair of bores defining two condensers. One embodiment comprises a first loop heat pipe having a first condenser in fluid communication with a first evaporator, and a second loop heat pipe having a second condenser in fluid communication with a second evaporator. The two loop heat pipes share a single evaporator saddle and a single condenser saddle. A continuous conductance heat pipe may be placed in contact with either the evaporator saddle or the condenser saddle.

US Patent:

57327653, Mar 31, 1998

Filed:

Dec 22, 1995

Appl. No.:

8/577439

Inventors:

Bruce L. Drolen - Pasadena CA
David B. Esposto - Redondo Beach CA
Ariel Gatti - San Gabriel CA
Calvin H. Ito - West Hills CA

Assignee:

Hughes Electronics

International Classification:

B64G 150

US Classification:

165 41

Abstract:

A spacecraft having a spacecraft body and a heat radiator attached to the spacecraft body. The heat radiator is in thermal contact with the spacecraft body and the heat radiator moves from an initial position to a deployed position where heat is emitted therefrom. The predetermined deployed position is located at an angular position. theta. as measured relative to the initial position, wherein. theta. ranges from approximately 135. degree. to less than 180. degree.

US Patent:

57354898, Apr 7, 1998

Filed:

Dec 22, 1995

Appl. No.:

8/577434

Inventors:

Bruce L. Drolen - Pasadena CA
David B. Esposto - Redondo Beach CA
George L. Fleischman - Cerritos CA
Calvin H. Ito - West Hills CA

Assignee:

Hughes Electronics - Los Angeles CA

International Classification:

B64G 150

US Classification:

244163

Abstract:

The present invention relates to an apparatus for transferring heat in a spacecraft. The apparatus includes a flexible heat pipe having a first section, a second section, and a flexible section. A first member of a spacecraft is coupled to the first section of the flexible heat pipe, and a second member of the spacecraft is coupled to the second section of the flexible heat pipe. The first member of the spacecraft is in a rigidly fixed relationship to the second member of the spacecraft. A method of using a heat transport system for transferring heat in a spacecraft is also provided. The method includes providing a flexible heat pipe having a first section, a second section, and a flexible section, coupling the first section of the flexible heat pipe to a first member of a spacecraft, and coupling the second section of the flexible heat pipe to a second member of the spacecraft rigidly fixed with respect to the first member.

US Patent:

57879699, Aug 4, 1998

Filed:

Dec 22, 1995

Appl. No.:

8/577435

Inventors:

Bruce L. Drolen - Pasadena CA
David B. Esposto - Redondo Beach CA
George L. Fleischman - Cerritos CA
Calvin H. Ito - West Hills CA

Assignee:

Hughes Electronics Corporation - El Segundo CA

International Classification:

F28D 1502
B64G 150
F28F 500

US Classification:

165 41

Abstract:

A closed-loop heat pipe transport design for a deployment application having a flexible section which connects to a payload structure and a deployable structure. The flexible section is a coil which is offset from the axis of rotation of the deployable structure. Upon rotation of the deployable structure around a predetermined axis, the flexible coil decompresses and sweeps in an arcuate fashion with a portion of said flexible coil aligning with the axis. When the deployable structure has completed its rotation and is fully deployed, the flexible coil will rest in substantially the same plane as it did before sweeping.