The Boeing Company

Virginia Tech Intellectual Properties, Inc.

Other

Theboeing Company

Kamiar J Karimi

Shengyi Liu

Eugene V Solodovnik

Francisco De Leon

Dariusz Czarkowski

Frederic Lacaux

Lijun Gao

Mark Eugene Liffring

John Anthony Trela

Dazhong Gu

Vyacheslav Khozikov

Qingquan Tang

Evelyn Marie Matheson

Duanyang Wang

Thomas F Currier

Sheau-Wei Johnny Fu

Dushan Boroyevich

Matthew Joseph Krolak

Christopher Mark Severns

Mariusz Bojarski

Steven B Helton

Kerim Colak

Kolten Carrington Miller

Trevor Milton Laib

Rolando Burgos

Jeffrey Joseph White

Andrew Johnson

Paolo Mattavelli

George Michael Roe

Jian Huang

Joseph S Breit

David S Krug

Leila Parsa

Mark William Lesyna

Sheverria Aikens

Andrew John Bayliss

Mehdy Barekatein

Fred Wang

Dorina L Hester

Suman Dwari

Yujie Song

Adam J Winstanley

Matthew J Krolak

Anil Kumar

Timothy McNally Mitchell

Aaron Jonathan Kutzmann

Jeffrey Michael Roach

Michael Thomas Fox

Mark Stephen Shander

Todd Burton Brouwer

Thomas R Hasenoehrl

Terrance L Thomas

Robert Dennis Holley

John T Paterson

Mary Eileen Beckman

Raju Shankar Mattikalli

Gerald T Francis

Bo Wen

Jerry Edward Farstad

Jon J Dhondt

Esther S Zidovetzki

Zhiyu Shen

Marko Jaksic

Camron Ravell Call

Patrick R Darmstadt

Hubert Wong

Alejandro Silva

Marvin J Whitney

Mehran Mesbahi

Daniel Zelazo

Nicholas J Silveri

Zachary R Lewis

Ed Woods

Bo Zhou

Vikram D Immanuel

Sheau-Wei (Johnny) Fu

Jeffery M Roach

Paul A Mezs

Marko D Jaksic

Mark E Liffring

Mark S Shander

Robert D Holley

Todd B Brouwer

Methods and systems for charging a battery string while protecting against overcharging. One system includes: a pair of disconnect devices; a power distribution bus which is electrically connected to a battery string via the disconnect devices; a battery charger connected to supply battery power to the power distribution bus for charging the battery string; a module monitoring unit configured to sense individual battery cell voltages during charging; a first processor configured to activate one disconnect device to open when the sensed individual battery cell voltages indicate overcharging; a plurality of sensors connected to sense a full-string voltage measured across the battery string and first and second half-string voltages measured across first and second half-strings of the battery string; and a second processor connected to receive sensor data during charging. The second processor is configured to independently activate the second disconnect device to open when the sensor data indicates continued overcharging.

Systems and methods for fail-safe battery protection independent from battery management system

An aircraft adaptive battery charging system is provided. The adaptive battery charging system comprises: a battery system; a bidirectional converter, wherein the bidirectional converter is capable of an inverter mode and a rectifier mode; an alternating current (AC) motor; a number of controllable contactors that control electrical current between the battery system, bidirectional converter, AC motor, and a power source wherein the controllable contactors can be switched between a closed position to allow electrical current flow and an open position to prevent electrical current flow; a motor controller; a battery charging system controller configured to send control signals to the battery system, motor controller, and controllable contactors in response to system command signals; and a vehicle system controller that sends system command signals to the motor controller and battery charging system controller.

Adaptive battery charging system and method

One example provides a method for generating and using electric power in a hybrid power system for an aircraft. The hybrid power system has an engine and a high-voltage DC (HVDC) bus interconnecting a generator-motor system, an AC distribution system, and a DC distribution system. The method comprises operating the engine through a plurality of different operation phases. The method further comprises selectively providing, based on thrust demands of the engine, electric power from the HVDC bus to the generator-motor system to assist the engine in providing thrust. The method further comprises selectively extracting, using the engine driving the generator-motor system with a high-pressure spool (HPS) shaft and/or a low-pressure spool (LPS) shaft of the engine, electric power from the engine. The method further comprises selectively delivering the electric power extracted from the engine to the AC distribution system and/or the DC distribution system.

Hybrid turbine and multiple-spool electric power system for aircraft

A discrete signal interlock system for activating an electric machine in an aircraft includes a first controller, a second controller, and a power source coupled via a single wiring harness bundle to a motor controller that is operatively connected to the electric machine. The motor controller includes a first circuit that is electrically coupled to a driver enabler of the motor controller, and a second circuit that is electrically coupled to a driver of the motor controller. The single wiring harness bundle encloses a first signal cable electrically coupling the first controller to the first circuit, a second signal cable electrically coupling the second controller to the second circuit, a first power cable electrically coupled to the first circuit, and a second power cable electrically coupled to the second circuit. Activation of the motor controller requires activation of the driver in concert with activation of the driver enabler.

Method and system for activating an electric machine in an aircraft

Apparatus and methods for mitigating abrupt release of energy due to a short circuit or other fault external to battery modules in a battery pack. Each battery module includes a plurality of weakened fusible links, which may connect an associated cell to a virtual cell busbar or connect dedicated busbars. After the fault has been cleared and faulted battery modules have been bypassed, the battery pack is ready for reconnection to the electrical network to provide power for the load(s). The battery management includes detection and isolation of a fault followed by execution of an algorithm for reconnection of the battery pack to the power distribution system after burnout of the fusible links. In addition, the respective activation times for reconnecting operative (not faulty) modules in a faulty battery string versus reconnecting other operative battery strings in the battery pack are coordinated.

Apparatus and methods for arc detection, fault isolation, and battery system reconfiguration

A computer-implemented method for optimally operating a hybrid-electric propulsion system by control of equipment dynamics. Prior to start of a mission, an original energy management plan is generated which is calculated to minimize estimated life-cycle operating costs for the vehicle during the mission. During an initial portion of the mission, operations of first and second power sources, a power distribution system, and a propulsion system are controlled such that a power mixture is supplied to the propulsion system from the first and second power sources in accordance with the original energy management plan. During the initial portion of the mission, a modified energy management plan is generated which is calculated to minimize estimated life-cycle operating costs for the vehicle. During a subsequent portion of the mission, operations of the first and second power sources, power distribution system, and propulsion system are controlled such that a power mixture is supplied to the propulsion system from the first and second power sources in accordance with the modified energy management plan.

Device and method for operating a hybrid-electric propulsion system by control of equipment dynamics

A hybrid power system for an aircraft. The hybrid power system comprises a high-voltage DC (HVDC) bus and a generator-motor system configured to (1) selectively receive electric power from the HVDC bus to assist in providing propulsion and (2) provide electric power to the HVDC bus during regulated power extraction. An LPS generator/motor is coupled with an LPS shaft of an engine. An HPS generator/motor is coupled with an HPS shaft of the engine. A first AC/DC converter is connected to the LPS generator/motor and the HVDC bus. A second AC/DC converter is connected to the HPS generator/motor, the first AC/DC converter, and the HVDC bus. An electric motor is connected to the HVDC bus and configured to provide propulsion and/or electric power. Further, AC and DC distribution systems are connected to the HVDC bus. A control system is configured to selectively control connections to the HVDC bus.

An electrical system for an aircraft includes an AC electric power source electrically connected to a rotary electric motor via a plurality of AC contactors. An AC/DC inverter is electrically connected to the rotary electric motor, a DC power bus is electrically connected to the AC/DC inverter, and a plurality of sensors are arranged to monitor electric currents between the AC electric power source and the rotary electric motor. A first controller is arranged to control the AC/DC inverter; and a second controller is arranged to monitor the sensors and are operatively connected to the AC contactors. The second controller is operable to monitor, via the sensors, the electric currents between the AC electric power source and the rotary electric motor, and detect a fault based upon the electric currents, and deactivate the AC contactors in response to the fault.

System and method for ground fault monitoring in an aircraft

Methods and systems for protection/disconnect of airborne high-power/energy high-voltage modular multi-string battery packs (such as battery packs for airborne electric propulsion systems). The methods and systems are based on a dissimilar/redundant distributed battery pack protection architecture and use a smart mid-point battery disconnect in conjunction with centralized battery management system. The resulting battery disconnect/protection system is configured to detect bus faults, load faults and string faults and then take appropriate action to isolate the detected fault. For example, in response to a short circuit in one battery string, the faulty battery string may be disconnected from the positive and negative busbars while the remaining battery strings continue to provide power.

Smart battery disconnect and protection architecture for airborne high-power modular multi-string battery pack

Methods and apparatus for detecting and characterizing arc faults in an aerospace electric propulsion system and then coordinating the operation of various elements of the protection system to execute a fault-clearing sequence. In a current-based method, the arc is detected and characterized based on differential readouts from current sensors. The difference between currents measured at two ends of a protection zone are compared to a difference threshold. In a power-based method, the arc is detected and characterized based on differential readouts from voltage and current sensors. The differential voltage and current readouts are used to compute the respective powers at two ends of a protection zone. The difference between the respective powers is integrated over a period of time and then the integrated difference is compared to a difference threshold. A differential protection trip mode is invoked when the difference threshold is exceeded.

Protection system for aircraft electric propulsion motor and motor controller

An electric propulsion unit comprising a housing, an AC motor, a beta rod, a propeller, a governor, an inverter, and a controller. The AC motor is disposed within the housing and includes bearings supported inside the housing, a hollow motor shaft rotatably coupled to the housing by the bearings, a stator which is supported by the housing, and a rotor which is mounted to the hollow motor shaft. The beta rod is axially translatable inside the hollow motor shaft. The propeller is mechanically coupled to the hollow motor shaft. The propeller includes propeller blades having an adjustable pitch angle which depends on an axial position of the beta rod. The governor is configured to adjust a pitch angle of the propeller blades by actuating axial translation of the beta rod. The controller is disposed inside the housing and configured to control the pitch angle of the propeller blades.

Integrated electric propulsion unit

A battery and related methods are described. The battery can include a plurality of battery cell segments. Each of the battery cell segments can include an anode segment, a cathode segment, and one or more current limiters. The one or more current limiters are configured to conditionally electrically isolate the battery cell segment based on an occurrence of a short circuit within the battery cell segment. The battery can be used to store electrical power and/or provide electrical power to a load.

Battery cell design for preventing internal short circuits from occurring and propagating

A battery and related methods are described. The battery can include a plurality of battery cell segments. Each of the battery cell segments can include: a positive temperature coefficient (PTC) material whose resistance increases with temperature, an anode segment, a cathode segment, and one or more current limiters. The one or more current limiters of a battery cell segment are configured to conditionally electrically isolate the battery cell segment based on an occurrence of a short circuit within the battery cell segment. The battery can be used to store electrical power and/or provide electrical power to a load.

Battery cell design for preventing internal short circuits from occurring and propagating using positive temperature coefficient (PTC) materials

An electric drive system including an impedance balancing noise filtering circuit is disclosed. The electric drive system includes a direct current (DC) power source configured to output DC power to an output port and an inverter configured to convert the DC power output by the DC power source into alternating current (AC) power that is provided to an input port of an AC load. The impedance balancing noise filtering circuit includes an impedance bridge electrically intermediate the output port of the DC power source and the input port of the AC load. The impedance balancing noise filtering circuit includes different sets of passive components that are positioned on both the DC-side and the AC-side of the inverter. These sets of passive components are configured to facilitate impedance balancing that reduces common-mode (CM) electromagnetic interference (EMI) emission at the output port of the DC power source.

Impedance balancing for noise filtering in electric drive systems

A system including a power modulation device and an active voltage balancing system is provided. The power modulation device includes first and second semiconductor switches in series. The active voltage balancing system includes a differential voltage logic configured to detect a voltage difference between the first and second semiconductor switches and edge capture logic configured to detect a time difference between when the first and second semiconductor switches are switched. The active voltage balancing system further includes a micro-controller configured to output first and second gate drive signals to drive the first and second semiconductor switches. The micro-controller is configured to tune the first and second gate drive signals based on the voltage difference to compensate for voltage imbalance and the time difference to compensate for drive signal asymmetry to actively balance a voltage between the first and second semiconductor switches.

Active voltage balancing for power modulation device

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Kirkland, WA, United States of America

Kamiar J Karimi