Charles S Meis

US Patent:

7207521, Apr 24, 2007

Filed:

Dec 12, 2005

Appl. No.:

11/301179

Inventors:

Warren A. Atkey - Bothell WA, US
Alan T. Bernier - Woodinville WA, US
Michael D. Bowman - Bellevue WA, US
Thomas A. Campbell - Seattle WA, US
Jonathan M. Cruse - Everett WA, US
Charles J. Fiterman - Mukilteo WA, US
Charles S. Meis - Renton WA, US
Casey Y. K. Ng - Sammamish WA, US
Farhad Nozari - Woodinville WA, US
Edward Zielinski - Kent WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64D 41/00

US Classification:

244 58

Abstract:

Methods and systems for providing secondary power to aircraft systems. In one embodiment, an aircraft system architecture for providing power to an environmental control system includes an electric generator operably coupled to a jet engine. The jet engine can be configured to provide propulsive thrust to the aircraft, and the electric generator can be configured to receive shaft power from the jet engine. The environmental control system can be configured to provide outside air to a passenger cabin of the aircraft in the absence of bleed air from the jet engine.

US Patent:

7210653, May 1, 2007

Filed:

Oct 21, 2003

Appl. No.:

10/691440

Inventors:

Warren A. Atkey - Bothell WA, US
Alan T. Bernier - Woodinville WA, US
Michael D. Bowman - Bellevue WA, US
Thomas A. Campbell - Seattle WA, US
Jonathan M. Cruse - Everett WA, US
Charles J. Fiterman - Mukilteo WA, US
Charles S. Meis - Renton WA, US
Casey Y. K. Ng - Sammamish WA, US
Farhad Nozari - Woodinville WA, US
Edward Zielinski - Kent WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64D 41/00

US Classification:

244 58

Abstract:

Methods and systems for providing secondary power to aircraft systems. In one embodiment, an aircraft system architecture for providing power to an environmental control system includes an electric generator operably coupled to a jet engine. The jet engine can be configured to provide propulsive thrust to the aircraft, and the electric generator can be configured to receive shaft power from the jet engine. The environmental control system can be configured to provide outside air to a passenger cabin of the aircraft in the absence of bleed air from the jet engine.

US Patent:

7950606, May 31, 2011

Filed:

Mar 29, 2007

Appl. No.:

11/693532

Inventors:

Warren A. Atkey - Bothell WA, US
Alan T. Bernier - Woodinville WA, US
Michael D. Bowman - Bellevue WA, US
Thomas A. Campbell - Seattle WA, US
Jonathan M. Cruse - Everett WA, US
Charles J. Fiterman - Mukilteo WA, US
Charles S. Meis - Renton WA, US
Casey Ng - Sammamish WA, US
Farhad Nozari - Woodinville WA, US
Edward Zielinski - Kent WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64D 41/00

US Classification:

244135R

Abstract:

Methods and systems for providing secondary power to aircraft systems. In one embodiment, an aircraft system architecture for providing power to an environmental control system includes an electric generator operably coupled to a jet engine. The jet engine can be configured to provide propulsive thrust to the aircraft, and the electric generator can be configured to receive shaft power from the jet engine. The environmental control system can be configured to provide outside air to a passenger cabin of the aircraft in the absence of bleed air from the jet engine.

US Patent:

20070267540, Nov 22, 2007

Filed:

Mar 29, 2007

Appl. No.:

11/693046

Inventors:

Warren Atkey - Bothell WA, US
Alan Bernier - Woodinville WA, US
Michael Bowman - Bellevue WA, US
Thomas Campbell - Seattle WA, US
Jonathan Cruse - Everett WA, US
Charles Fiterman - Mukilteo WA, US
Charles Meis - Renton WA, US
Casey Ng - Sammamish WA, US
Farhad Nozari - Woodinville WA, US
Edward Zielinski - Kent WA, US

International Classification:

B64D 41/00

US Classification:

244058000, 060778000

Abstract:

Methods and systems for providing secondary power to aircraft systems. In one embodiment, an aircraft system architecture for providing power to an environmental control system includes an electric generator operably coupled to a jet engine. The jet engine can be configured to provide propulsive thrust to the aircraft, and the electric generator can be configured to receive shaft power from the jet engine. The environmental control system can be configured to provide outside air to a passenger cabin of the aircraft in the absence of bleed air from the jet engine.

US Patent:

20130175396, Jul 11, 2013

Filed:

Jan 5, 2012

Appl. No.:

13/344144

Inventors:

Charles Steven Meis - Renton WA, US
Cris Kevin Bosetti - Seattle WA, US

Assignee:

THE BOEING COMPANY - Chicago IL

International Classification:

B64D 15/20

US Classification:

244134 F

Abstract:

An ice detection system comprising a first group of sensors and a second group of sensors. The first group of sensors is located in a first group of locations on an aircraft. The first group of sensors in the first group of locations is configured to detect a first type of icing condition for the aircraft. The second group of sensors is located in a second group of locations on the aircraft. The second group of sensors in the second group of locations is configured to detect a second type of icing condition for the aircraft.

US Patent:

20130175397, Jul 11, 2013

Filed:

Mar 8, 2012

Appl. No.:

13/414894

Inventors:

Charles Steven Meis - Renton WA, US
Cris Kevin Bosetti - Seattle WA, US

Assignee:

THE BOEING COMPANY - Chicago IL

International Classification:

B64D 15/20

US Classification:

244134 F

Abstract:

A method and apparatus for an ice detection system. The ice detection system comprises a first sensor located on a leading edge of a vertical stabilizer on an aircraft, a second sensor located on a first side of the vertical stabilizer, and a third sensor located on a second side of the vertical stabilizer. The first sensor is configured to detect a first type of icing condition for the aircraft. The second sensor is configured to detect a second type of icing condition for the aircraft. The third sensor is configured to detect the second type of icing condition for the aircraft.

US Patent:

20130239670, Sep 19, 2013

Filed:

Mar 13, 2012

Appl. No.:

13/419033

Inventors:

Charles Steven Meis - Renton WA, US
David Charles Hass - Renton WA, US
Carl Hallstrom - Federal Way WA, US

Assignee:

THE BOEING COMPANY - Chicago IL

International Classification:

G01M 9/02

US Classification:

7311803

Abstract:

A method and apparatus for an icing simulation system. The icing simulation system comprises a wind tunnel, a nozzle system, and a controller. The nozzle system is configured to spray drops of water within the wind tunnel. The controller is configured to control a number of properties of the water in the nozzle system such that the nozzle system sprays the drops of the water with different sizes for a desired type of icing condition.

US Patent:

20130240672, Sep 19, 2013

Filed:

Mar 15, 2012

Appl. No.:

13/421360

Inventors:

Charles Steven Meis - Renton WA, US

Assignee:

THE BOEING COMPANY - Chicago IL

International Classification:

B64D 15/20

US Classification:

244134 F

Abstract:

A method and apparatus for detecting icing conditions. An icing condition detection system comprises a number of sensors and an icing condition detector. The number of sensors is located in a number of locations on an aircraft. A sensor in the number of sensors is configured to emit electromagnetic radiation into drops of water in an environment around the aircraft. The sensor in the number of sensors is configured to detect responses to the electromagnetic radiation. The sensor in the number of sensors is configured to generate data from the responses. The icing condition detector is configured to monitor for the data from the number of sensors. The icing condition detector is further configured to detect a presence of a number of types of icing conditions for the aircraft using the data from the number of sensors.