A moving object includes equipment disposed in a first area and including an engine and a power generator driven by the engine, equipment disposed in a second area located forward of the first area in a traveling direction of the moving object and including an electric power device supplying electric power from the power generator to a battery, and equipment disposed in a third area located forward of the second area in the traveling direction and including the battery.

An assembly for an aircraft includes an aircraft electrical distribution bus, a battery, and a battery monitoring system. The battery includes a plurality of battery strings. The plurality of battery strings is configured as a main subset and a reserve subset. The battery monitoring system further includes a processor in communication with a non-transitory memory storing instructions, which instructions when executed by the processor, cause the processor to electrically connect the reserve subset to the aircraft electrical distribution bus by: determining the bus voltage and the battery string voltage of each battery string of the reserve subset, identifying a threshold voltage range of the reserve subset for electrically connecting the reserve subset to the aircraft electrical distribution bus, where identifying the threshold voltage range is based at least on the bus voltage, and electrically connecting at least one battery string of the reserve subset to the aircraft electrical distribution bus with the bus voltage within the identified threshold voltage range.

An assembly for an aircraft includes an aircraft electrical distribution bus, a battery, and a battery monitoring system. The battery includes a plurality of battery strings. The plurality of battery strings is configured as a main subset and a reserve subset. The battery monitoring system further includes a processor in communication with a non-transitory memory storing instructions, which instructions when executed by the processor, cause the processor to electrically connect the reserve subset to the aircraft electrical distribution bus by: determining the bus voltage and the battery string voltage of each battery string of the reserve subset, identifying a threshold voltage range of the reserve subset for electrically connecting the reserve subset to the aircraft electrical distribution bus, where identifying the threshold voltage range is based at least on the bus voltage, and electrically connecting at least one battery string of the reserve subset to the aircraft electrical distribution bus with the bus voltage within the identified threshold voltage range.

Systems and methods for an aircraft comprising: wings in tandem configuration wherein each wing having one tilting motor; an additional tilting motor located at the rear part of said aircraft; wherein all said tilting motors can tilt in the range between full horizontal and full vertical positions; at least two arrays of batteries, said arrays capable of moving forward and backward; sensing means; a computing device configured for: receiving said sensed information; controlling said motors; calculating the compensation required in case of a single motor failure and controlling the active motors accordingly; based on said sensed information and flight/movement instructions calculating continuously the optimal center of gravity location in the range possible given the movement range of said batteries arrays and controlling the movement of said batteries arrays accordingly.

Systems and methods for an aircraft comprising: wings in tandem configuration wherein each wing having one tilting motor; an additional tilting motor located at the rear part of said aircraft; wherein all said tilting motors can tilt in the range between full horizontal and full vertical positions; at least two arrays of batteries, said arrays capable of moving forward and backward; sensing means; a computing device configured for: receiving said sensed information; controlling said motors; calculating the compensation required in case of a single motor failure and controlling the active motors accordingly; based on said sensed information and flight/movement instructions calculating continuously the optimal center of gravity location in the range possible given the movement range of said batteries arrays and controlling the movement of said batteries arrays accordingly.

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.

A hybrid electric propulsion (HEP) system included in an aircraft includes a generator configured to output a first power, an energy storage system configured to output a second power, a propulsion system configured to generate thrust based on at least one of the first power and the second power, and an HEP controller in signal communication with the generator, the battery, and the HEP system. The HEP controller is configured to detect loss of the first power output from the generator, to determine an altitude of the aircraft and to actively control delivery of the second power to the propulsion system based on the altitude during the loss of the first power.

A mobile engine-generator vehicle that uses the same motor system for mobility as it does for electrical power generation. The mobile engine-generator vehicle is configured to provide electrical power to an external load via an electrical outlet mounted to the vehicle.

This disclosure relates to power sources that are structurally integrated with an airplane wing. The power sources include rechargeable batteries, such as Ni-Cd, NiMH, and/or Li-ion batteries; and/or hydrogen fuel cells. The power sources can be located on the airplane wing, inside of the wing, and/or located on the bottom of the wing, and combinations thereof. The airplane wing can be made of a metallic structural material or a composite structural material. Layers of a Li-ion battery can conformally overlay the upper metallic structural skin of a metallic wing, and the electrically-conductive metallic airplane wing itself acts as a cathode (or anode) of the battery. The airplane wing can be made of laminated sheets of carbon-fiber composites (CFCs). The power sources can be sandwiched inside of an upper and/or a lower section of the composite airplane wing. Lithium-ion batteries can be connected in series to provide a greater voltage.

A power supply system of an aircraft includes a fuel cell that generates electrical energy, a converter device including a mode switch device that supplies power to a first motor device through a first output terminal and switches a connection between an output node of the fuel cell and the first output terminal, a first battery device that supplies a voltage from a first battery to a second motor device through a second output terminal and connects the second output terminal with the first output terminal under control of the mode switch device, and a processor that controls the mode switch device to enter an emergency mode when detecting an error in the converter device or the first battery device and connects the first output terminal with the second output terminal.