The Boeing Company

Michael L Trent

Douglas Dean Maben

Daniel F Lewinski

Richard Kevin Johnson

Julie K Plessner

Warren Andrew Atkey

George A McEachen

Mark E Smith

Kevin Scott Callahan

Daniel J Murray

Kelly Thomas Jones

Royal E Boggs

Mohammad M Malik

Harry H Ayubi

Alan D Amort

Michael R Madden

Frederic Lacaux

John Rubrecht Lowell

Bruce Lee Drolen

James C Russell

Mehdy Barekatein

Nels A Olson

Timothy R North

Sidney D Shell

Andre G Brasseur

Thomas P Barrera

Howard E McKenzie

Mike R Madden

Charles A Fieldson

Frank P Brady

Chetan B Megchiani

Richard K Johnson

Douglas D Maben

Matthew J O'Brien

Richard P Lorenz

Jean-Philippe Belieres

David C Shangraw

Stephen E Izbicki

Cheh-Min J Su

Paul A Guilford

Al R Carlo

Craig G Robotham

Alfred R Carlo

Zachary G Brown

John J Stevens

Kelly T Jones

Kevin S Callahan

Warren A Atkey

John R Lowell

Howard E Mckenzie

Nels S Olson

George A Mceachen

Matthew J O'brien

Bruce L Drolen

Frederic P Lacaux

An aircraft includes a fuselage defining a cabin region and a crown region. The aircraft also includes a duct disposed within the fuselage. The duct is coupled to one or more drying air vents disposed in the crown region and coupled to one or more cabin vents disposed with the cabin region. The one or more drying air vents are configured to output drying air, received via the duct, into the crown region, and the one or more cabin vents are configured to output conditioned air, received via the duct, into the cabin region. The aircraft further includes one or more valves coupled to the duct and configured to, in a first valve position, route airflow within the duct to the one or more drying air vents and configured to, in a second valve position, route the airflow within the duct to the one or more cabin vents.

Aircraft moisture control

According to an embodiment, an aircraft comprises a fuselage including composite skin; an enclosure located inside the fuselage; a rechargeable battery disposed inside the enclosure; and a ventilation conduit extending from the enclosure to an opening in the composite skin, the ventilation conduit including: a first portion having a first end coupled to the enclosure and a second end spaced from the composite skin, and a second portion extending between the composite skin and the second end of the first portion, the second portion comprising an electrically non-conductive material.

Ventilation conduit for an aircraft

An aircraft comprises composite skin having an opening, and a ventilation conduit having an end portion that extends to the opening in the composite skin. The conduit is made of metal except for the end portion, which functions as an electrical insulator.

An aircraft comprises a rechargeable battery including an array of battery cells, and means for mitigating consequences of failure of the rechargeable battery due to aircraft operating cycles.

Aircraft including mitigation system for rechargeable batteries

An apparatus comprises a rechargeable battery susceptible to thermal runaway, and a metal enclosure for the battery. The enclosure is configured to mitigate battery failure consequences resulting from thermal runaway.

Enclosure for rechargeable batteries

The present invention comprises systems and methods for providing conditioned air to a selected portion of an aircraft cabin. In one embodiment, a system includes a cargo compartment air recirculation system fluidly coupled to the cargo compartment and having an air moving device to extract air from the compartment and to transport the air to an air heating device and an air cooling device fluidly coupled to the cargo compartment. Air may be supplied from an air source. Extracted air maybe discharged overboard. A temperature control system is operably coupled to the air heating device and the air cooling device, the control system being configured to maintain a predetermined air temperature within the compartment in response to a sensed compartment temperature.

Systems and methods for cargo compartment air conditioning using recirculated air

The present invention provides a temperature control system for an aircraft ventilation system that couples with existing aircraft upstream ventilation system architecture and downstream ventilation system architecture. The temperature control system includes an air duct arranged to receive a volume of ventilation air from the upstream ventilation system architecture and transfer the volume of air to the downstream ventilation system architecture. A heater is arranged to heat the ventilation air. A controller is arranged to control the heater responsive to a comparison of the actual temperature of the ventilation air to a desired range of temperatures. The controller maintains the actual ventilation air temperature within the predetermined range of temperatures such that formation of ice is minimized in the aircraft ventilation system. An exhaust shutoff valve between the air distribution system and the lavatory/galley ventilation system provides for ventilation in the event smoke is detected.

Flight crew and attendant rest environmental control system

Growing community of inventors

Everett, WA, United States of America

Michael L Trent