Michael J Andres

US Patent:

7466045, Dec 16, 2008

Filed:

Feb 14, 2006

Appl. No.:

11/364906

Inventors:

Michael J. Andres - Roscoe IL, US

Assignee:

Hamilton Sundstrand Corporation - Windsor Locks CT

International Classification:

H02K 9/00

US Classification:

310 52, 310 54, 310 59, 310 64

Abstract:

An in-shaft cryogenic cooler mounts entirely within the shaft of a dynamoelectric machine that has a rotor comprising a high temperature superconductor.

US Patent:

7987683, Aug 2, 2011

Filed:

Feb 20, 2006

Appl. No.:

11/358791

Inventors:

Michael J. Andres - Roscoe IL, US

Assignee:

Hamilton Sundstrand Corporation - Windsor Locks CT

International Classification:

F25D 9/00

US Classification:

62402, 62498

Abstract:

A cooling system with a compression cooling cycle for a working fluid that passes an expendable fluid through a warm side heat exchanger for the cooling system to cause the expendable fluid to vaporise and thus absorb heat from the working fluid by way of latent heat or enthalpy of vaporisation and then running the vaporised expendable through a turbine that drives a compressor for the cooling system.

US Patent:

8181725, May 22, 2012

Filed:

Sep 29, 2009

Appl. No.:

12/569881

Inventors:

Michael J. Andres - Roscoe IL, US
Shin Katsumata - Rockford IL, US

Assignee:

Hamilton Sundstrand Corporation - Windsor Locks CT

International Classification:

B60T 7/16

US Classification:

180 147, 180904, 180 11, 180 141, 180 144, 280508, 280477

Abstract:

An aircraft tug includes a tow bar which extends from a chassis, the tow bar operable to autonomously attach with an aircraft main landing gear assembly and transfer electrical power therebetween.

US Patent:

20110073706, Mar 31, 2011

Filed:

Sep 29, 2009

Appl. No.:

12/569888

Inventors:

Shin Katsumata - Rockford IL, US
Michael J. Andres - Roscoe IL, US

International Classification:

B64C 25/50

US Classification:

244 50, 414426, 180 147

Abstract:

An aircraft tug includes a tow bar which extends from a chassis, the tow bar operable to autonomously attach with an aircraft main landing gear assembly.

US Patent:

20110219786, Sep 15, 2011

Filed:

Mar 11, 2010

Appl. No.:

12/721598

Inventors:

Michael J. Andres - Roscoe IL, US
Kris H. Campbell - Poplar Grove IL, US

International Classification:

B64D 13/08
F25B 27/00
F25B 23/00
F25B 41/00

US Classification:

62 7, 622381, 62244, 62506, 62513

Abstract:

An aircraft cooling system includes a refrigerant cycle including a first heat exchanger, a second heat exchanger, and a compressor. A component of the aircraft is in thermal communication with the first heat exchanger. A heat sink fluid passes through the second heat exchanger to absorb heat from the refrigerant cycle. A hydraulic motor is mechanically connected with the compressor and powered by the heat sink fluid, which is circulated by a pump.

US Patent:

20120206880, Aug 16, 2012

Filed:

Feb 14, 2011

Appl. No.:

13/026727

Inventors:

Michael J. Andres - Roscoe IL, US
Robert Scott Downing - Rockford IL, US

Assignee:

HAMILTON SUNDSTRAND CORPORATION - Windsor Locks CT

International Classification:

H05K 7/20

US Classification:

361700

Abstract:

A cooling assembly comprises an electronic component, a thermal spreader, a cold plate, and a phase change thermal capacitor. The thermal spreader conducts heat freely between the electronic component, the phase change thermal capacitor, and the cold plate. The cold plate dissipates heat. The phase change thermal capacitor stores undissipated heat in a phase transition of a phase change material.

US Patent:

20120255711, Oct 11, 2012

Filed:

Apr 7, 2011

Appl. No.:

13/081644

Inventors:

Michael J. Andres - Roscoe IL, US

Assignee:

HAMILTON SUNDSTRAND CORPORATION - Windsor Locks CT

International Classification:

F28D 15/00
F04B 49/00

US Classification:

16510431, 417 53

Abstract:

A thermal management system for a vehicle includes a tank, a heat exchanger, a pump, and a valve located on a conduit. The heat exchanger is located downstream of the tank, the pump is located between the tank and the heat exchanger, and the valve is located downstream of the heat exchanger. The heat exchanger places the coolant in a heat exchange relationship with a heat load from the vehicle such that the coolant vaporizes. The valve regulates pressure within the heat exchanger and controls exhaustion of the vaporized coolant from the vehicle. Water, used as a coolant, can be replenished in flight by condensing a portion of the heat exchanger exhaust or condensing water as part of the environmental control system function or by condensing a portion of the engine exhaust.

US Patent:

20120322354, Dec 20, 2012

Filed:

Jun 16, 2011

Appl. No.:

13/162152

Inventors:

Michael J. Andres - Roscoe IL, US

International Classification:

B60H 1/00

US Classification:

454139

Abstract:

A system for providing heating and cooling to an aircraft has a single compressor for compressing and heating a fluid, a first zone and a second zone. The first zone has a first expansion valve without a condenser and a first heat exchanger removing heat from or adding heat to the first zone. The compressed fluid passes through the first zone and the first expansion valve. The second zone requires cooling and has a second expansion valve without a condenser and a second heat exchanger for removing heat from the zone. The compressed fluid passes through the second expansion valve after going through the first expansion valve and before passing through the second heat exchanger.