Abstract: An internal battery heating system includes an electrical conversion device electrically coupled to an electrochemical sub-cell or battery modules to form a heating circuit. The electrical conversion device alternately raises and lowers a voltage of the heating circuit to drive current between the heating circuit and the electrochemical sub-cell or battery modules. A controller commands the electrical conversion device to cyclically charge and discharge the electrochemical sub-cell or battery modules for internally heating the battery modules. Alternatively, a battery module may be electrically coupled to electrochemical sub-cells via pairs of switches to form a heating circuit. The pairs of switches are adapted for switching the heating circuit alternately between a parallel arrangement and a series arrangement to alternate charging and discharging of the battery module which results in internal heating of the battery module.

Abstract: An internal battery heating system includes an electrical conversion device electrically coupled to an electrochemical sub-cell or battery modules to form a heating circuit. The electrical conversion device alternately raises and lowers a voltage of the heating circuit to drive current between the heating circuit and the electrochemical sub-cell or battery modules. A controller commands the electrical conversion device to cyclically charge and discharge the electrochemical sub-cell or battery modules for internally heating the battery modules. Alternatively, a battery module may be electrically coupled to electrochemical sub-cells via pairs of switches to form a heating circuit. The pairs of switches are adapted for switching the heating circuit alternately between a parallel arrangement and a series arrangement to alternate charging and discharging of the battery module which results in internal heating of the battery module.

Abstract: An expedited preflight readiness system for aircraft includes a power source having one or more battery modules for storing electrical power. An integrated controller is electrically and communicatively coupled with the power source for monitoring and controlling the power source to provide electrical power to aircraft subsystems. A mobile device is communicatively coupled with the integrated controller for communicating instructions to the integrated controller for initiating preflight readiness of the aircraft and for monitoring preflight readiness. A method for preconditioning an aircraft includes determining a state-of-charge of an APU and activating an environmental control subsystem for preconditioning the aircraft by adjusting a current temperature according to a preconditioning profile based on one or more of a target temperature, a target time, the current temperature, an outside air temperature, an amount of energy, and a state-of-charge of the APU.

Abstract: A distributed auxiliary-power-unit (APU) system for an aircraft includes one or more battery modules for storing electrical power, and a plurality of racks distributed throughout the aircraft for receiving the one or more battery modules to electrically connect with an electrical subsystem of the aircraft. A plurality of hot-swappable racks are adapted to receive the battery modules for electrically and communicatively coupling with the electrical subsystem and an integrated controller. A remote interface is communicatively coupled with the integrated controller for receiving user-input to direct electrical power from the battery modules to one or more subsystems of the aircraft. A number of battery modules installed is based on an amount of electrical power planned for a given flight of the aircraft.

Abstract: An auxiliary power unit (APU) for aircraft is provided. The APU includes one or more battery modules for storing electrical power and an integrated controller adapted to operate the one or more battery modules for electrically powering aircraft subsystems for preflight readiness. A remote interface is communicatively coupled with the integrated controller and is adapted for displaying data from the APU and for receiving user instructions for transmission to the integrated controller for governing flow of electrical current between the APU and the aircraft subsystems.

Abstract: An expedited preflight readiness system for aircraft includes a power source having one or more battery modules for storing electrical power. An integrated controller is electrically and communicatively coupled with the power source for monitoring and controlling the power source to provide electrical power to aircraft subsystems. A mobile device is communicatively coupled with the integrated controller for communicating instructions to the integrated controller for initiating preflight readiness of the aircraft and for monitoring preflight readiness. A method for preconditioning an aircraft includes determining a state-of-charge of an APU and activating an environmental control subsystem for preconditioning the aircraft by adjusting a current temperature according to a preconditioning profile based on one or more of a target temperature, a target time, the current temperature, an outside air temperature, an amount of energy, and a state-of-charge of the APU.

Abstract: An internal battery heating system includes an electrical conversion device electrically coupled to an electrochemical sub-cell or battery modules to form a heating circuit. The electrical conversion device alternately raises and lowers a voltage of the heating circuit to drive current between the heating circuit and the electrochemical sub-cell or battery modules. A controller commands the electrical conversion device to cyclically charge and discharge the electrochemical sub-cell or battery modules for internally heating the battery modules. Alternatively, a battery module may be electrically coupled to electrochemical sub-cells via pairs of switches to form a heating circuit. The pairs of switches are adapted for switching the heating circuit alternately between a parallel arrangement and a series arrangement to alternate charging and discharging of the battery module which results in internal heating of the battery module.

Abstract: An auxiliary power unit (APU) for aircraft is provided. The APU includes one or more battery modules for storing electrical power and an integrated controller adapted to operate the one or more battery modules for electrically powering aircraft subsystems for preflight readiness. A remote interface is communicatively coupled with the integrated controller and is adapted for displaying data from the APU and for receiving user instructions for transmission to the integrated controller for governing flow of electrical current between the APU and the aircraft subsystems.

Abstract: An expedited preflight readiness system for aircraft includes a power source having one or more battery modules for storing electrical power. An integrated controller is electrically and communicatively coupled with the power source for monitoring and controlling the power source to provide electrical power to aircraft subsystems. A mobile device is communicatively coupled with the integrated controller for communicating instructions to the integrated controller for initiating preflight readiness of the aircraft and for monitoring preflight readiness. A method for preconditioning an aircraft includes determining a state-of-charge of an APU and activating an environmental control subsystem for preconditioning the aircraft by adjusting a current temperature according to a preconditioning profile based on one or more of a target temperature, a target time, the current temperature, an outside air temperature, an amount of energy, and a state-of-charge of the APU.

Abstract: An expedited preflight readiness system for aircraft includes a power source having one or more battery modules for storing electrical power. An integrated controller is electrically and communicatively coupled with the power source for monitoring and controlling the power source to provide electrical power to aircraft subsystems. A mobile device is communicatively coupled with the integrated controller for communicating instructions to the integrated controller for initiating preflight readiness of the aircraft and for monitoring preflight readiness. A method for preconditioning an aircraft includes determining a state-of-charge of an APU and activating an environmental control subsystem for preconditioning the aircraft by adjusting a current temperature according to a preconditioning profile based on one or more of a target temperature, a target time, the current temperature, an outside air temperature, an amount of energy, and a state-of-charge of the APU.

Abstract: A distributed auxiliary-power-unit (APU) system for an aircraft includes one or more battery modules for storing electrical power, and a plurality of racks distributed throughout the aircraft for receiving the one or more battery modules to electrically connect with an electrical subsystem of the aircraft. A plurality of hot-swappable racks are adapted to receive the battery modules for electrically and communicatively coupling with the electrical subsystem and an integrated controller. A remote interface is communicatively coupled with the integrated controller for receiving user-input to direct electrical power from the battery modules to one or more subsystems of the aircraft. A number of battery modules installed is based on an amount of electrical power planned for a given flight of the aircraft.

Abstract: A battery heater system for a battery used in cold weather operations and methods for using the battery heater system are described. Embodiments of the battery heater system may incorporate a heater switch with an indicator, a timer circuit, a controller, a voltage meter, a temperature transducer, and a heating element. In some methods of using the device, the battery powers the heating element for a fixed cycle time based on the time to discharge the battery at a cold-soaked temperature. In other methods of using the device, the battery powers the heating element for a varying cycle time as necessary to discharge the battery to a discharge cut-off voltage value. In other methods of using the device, the heating element is operated using a duty cycle that is varied based on the battery temperature.

Abstract: A battery heater system for a battery used in cold weather operations and methods for using the battery heater system are described. Embodiments of the battery heater system may incorporate a heater switch with an indicator, a timer circuit, a controller, a voltage meter, a temperature transducer, and a heating element. In some methods of using the device, the battery powers the heating element for a fixed cycle time based on the time to discharge the battery at a cold-soaked temperature. In other methods of using the device, the battery powers the heating element for a varying cycle time as necessary to discharge the battery to a discharge cut-off voltage value. In other methods of using the device, the heating element is operated using a duty cycle that is varied based on the battery temperature.

Abstract: A battery heater system for a battery used in cold weather operations and methods for using the battery heater system are described. Embodiments of the battery heater system may incorporate a heater switch with an indicator, a timer circuit, a controller, a voltage meter, a temperature transducer, and a heating element. In some methods of using the device, the battery powers the heating element for a fixed cycle time based on the time to discharge the battery at a cold-soaked temperature. In other methods of using the device, the battery powers the heating element for a varying cycle time as necessary to discharge the battery to a discharge cut-off voltage value. In other methods of using the device, the heating element is operated using a duty cycle that is varied based on the battery temperature.

Abstract: A system for an aircraft includes a compressor for a vapor cycle cooling system (VCCS) for providing cabin air conditioning; an APU for mechanically driving the VCCS compressor; and a starter-generator-motor (SGM) apparatus operable in any of a starter mode, a generator mode, or a motor mode. The SGM apparatus includes: (i) a first coupling element for coupling the SGM apparatus to the APU such that, in the starter mode, the SGM apparatus is used in driving and starting the APU, (ii) a second coupling element for coupling the SGM apparatus to the VCCS compressor such that, in the motor mode, the SGM apparatus mechanically drives the VCCS compressor, and (iii) a set of electrical power terminals at which, in the generator mode, the SGM apparatus provides electrical output power for powering the aircraft electrical system (including the VCCS condenser fan and VCCS evaporator fans) and, in the starter mode and motor mode, the SGM apparatus receives electrical input power from an external electrical power source.

Abstract: A battery heater system for a battery used in cold weather operations and methods for using the battery heater system are described. Embodiments of the battery heater system may incorporate a heater switch with an indicator, a timer circuit, a controller, a voltage meter, a temperature transducer, and a heating element. In some methods of using the device, the battery powers the heating element for a fixed cycle time based on the time to discharge the battery at a cold-soaked temperature. In other methods of using the device, the battery powers the heating element for a varying cycle time as necessary to discharge the battery to a discharge cut-off voltage value. In other methods of using the device, the heating element is operated using a duty cycle that is varied based on the battery temperature.