The Boeing Company

Mehdy Barekatein

Sheverria Aikens

Frederic Lacaux

Kamiar J Karimi

Eugene V Solodovnik

Mark Eugene Liffring

Evelyn Marie Matheson

Lowell W Schaffner

Glen M Brown

Frederic P Lacaux

Shengyi Liu

Kevin Scott Callahan

Daniel J Murray

Kelly Thomas Jones

Douglas Dean Maben

John Rubrecht Lowell

John Anthony Trela

Daniel F Lewinski

Bruce Lee Drolen

Richard Kevin Johnson

James C Russell

Michael L Trent

Royal E Boggs

Mark E Smith

George A McEachen

Timothy R North

Nels A Olson

Julie K Plessner

Thomas P Barrera

Bruce L Drolen

Mohammad M Malik

Matthew J O'Brien

Harry H Ayubi

Alan D Amort

Richard P Lorenz

Jean-Philippe Belieres

David C Shangraw

Michael R Madden

Craig G Robotham

Alfred R Carlo

Tony Aikens

Kevin S Callahan

Kelly T Jones

Richard K Johnson

Douglas D Maben

John R Lowell

Nels S Olson

George A Mceachen

Matthew J O'brien

Glen Brown

Systems and methods for operating a lithium-ion battery high-voltage distribution system architecture are disclosed. A battery pack includes: a plurality of lithium-ion battery cells; a disconnect mechanism operable in an operational position between a battery bus and the plurality of lithium-ion battery cells and a bypass position between the battery bus and a bus-power pass through; and a battery management system. The battery management system is configured to monitor battery pack performance; and responsive to detecting a triggering event in the battery pack performance, cause the disconnect mechanism to be in the bypass position.

Li-Ion battery high voltage distribution system architecture

System and method for allocating load power drawn from multiple batteries for powering propulsion of a vehicle. The system includes: high-energy and high-power batteries respectively designed for optimal production of DC power during high-specific-energy and high-specific-power propulsion; and battery health management systems configured to monitor state of charge and state of health of the batteries and generate battery status signals. The system further includes a propulsion load configured to produce propulsion force using power converted from power generated by at least one of the batteries and a system controller configured to allocate load power drawn from the high-energy and high-power batteries for use by the propulsion load in dependence on a propulsion phase of the vehicle and the battery status.

System and method for allocating propulsion load power drawn from high-energy and high-power batteries

A method and apparatus for providing regulated direct current power for a direct current load on an aircraft. A regulated transformer rectifier unit on an aircraft comprises a plurality of converter modules connected in parallel between an input and an output. Each converter module in the plurality of converter modules comprises a transformer rectifier unit. The plurality of converter modules are controlled by a controller to provide regulated direct current power at the output from alternating current power provided at the input from an alternating current power source on the aircraft.

Regulated transformer rectifier unit for aircraft systems

A battery module system includes at least one cell and a battery module processor. The battery module processor may be configured to receive at least one cell signal associated with the at least one cell, wherein the at least one cell signal includes at least one of a temperature signal, a voltage signal, or a current signal. The battery module processor may be also configured to determine a status of the at least one cell based on the at least one cell signal. The battery module system may be configured to removably connect to a master/module interface, and to deliver power from the at least one cell to the master/module interface. The battery module system may be also configured to communicate, from the battery module processor, the status of the at least one cell to the master/module interface.

Battery module system

A method and apparatus for providing power stably for direct current loads. A regulated transformer rectifier unit is controlled to provide regulated direct current power for the direct current loads at an output of the regulated transformer rectifier unit from alternating current power provided by an alternating current power source to an input of the regulated transformer rectifier unit. The direct current loads comprise passive direct current loads and active direct current loads comprising active switching power supplies. The direct current loads have at least one of constant power characteristics, resistive power characteristics, inductive power characteristics, and capacitive power characteristics. A source impedance at the output of the regulated transformer rectifier unit is determined based on an aggregate load impedance of the direct current loads and stability criterion.

Stable electrical power system with regulated transformer rectifier unit

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

Growing community of inventors

Kirkland, WA, United States of America

Mehdy Barekatein