Provided is a flight device that includes multiple drive sources and that can continuously fly even when one of the drive sources stops in flight, by using the other drive source. The flight device 10 includes a first drive system 11 and a second drive system 12. The first drive system 11 includes a battery 27, rotor 151 and the like configured to be rotated by energy supplied from the battery 27, and a first control unit 20 configured to control the numbers of revolutions of the rotor 151 and the like depending on a flight condition. The second drive system includes the battery 27, rotor 181 and the like configured to be rotated by energy supplied from the battery 27, and a second control unit 21 configured to control the numbers of revolutions of the rotor 181 and the like depending on the flight condition. In the emergency flight state, when the first drive system 11 stops, the flight device 10 lands by rotating the rotor 151 and the like, and when the second drive system 12 stops, the flight device 10 lands by rotating the rotor 181 and the like.

A system for battery management on a vehicle, comprising: a first system associated with a first battery pack, and a second system associated with a second battery pack, where the first battery pack is electrically connected to the second battery pack via a high voltage bus, the first battery pack is configured to power to a first electric engine, and the second battery pack is configured to power to a second electric engine. The first system may be configured to monitor a state of the first battery pack and isolate, by blowing a first fuse, the first battery pack from the second battery pack upon detecting an electrical issue, and the second system may be configured to monitor a state of the second battery pack and isolate, by blowing a second fuse, the second battery pack from the first battery pack upon detecting an electrical issue.

A system for battery management on a vehicle, comprising: a first system associated with a first battery pack, and a second system associated with a second battery pack, where the first battery pack is electrically connected to the second battery pack via a high voltage bus, the first battery pack is configured to power to a first electric engine, and the second battery pack is configured to power to a second electric engine. The first system may be configured to monitor a state of the first battery pack and isolate, by blowing a first fuse, the first battery pack from the second battery pack upon detecting an electrical issue, and the second system may be configured to monitor a state of the second battery pack and isolate, by blowing a second fuse, the second battery pack from the first battery pack upon detecting an electrical issue.

A power distribution system for an aircraft, comprising: a plurality of electric propeller units (EPUs), a first paired battery pack unit, the first paired battery pack unit, and a second paired battery pack unit. The first paired battery pack unit may include a first battery electrically connected to a second battery via a first high voltage bus. The first battery may be configured to provide power to a first set of EPUs of the plurality of EPUs, the second battery may be configured to provide power to a second set of EPUs of the plurality of EPUs, the first battery may be configured to act as a backup battery for powering the second set of EPUs, and the first high voltage bus and the second high voltage bus may be electrically separate from one another.

A power distribution system for an aircraft, comprising: a plurality of electric propeller units (EPUs), a first paired battery pack unit, the first paired battery pack unit, and a second paired battery pack unit. The first paired battery pack unit may include a first battery electrically connected to a second battery via a first high voltage bus. The first battery may be configured to provide power to a first set of EPUs of the plurality of EPUs, the second battery may be configured to provide power to a second set of EPUs of the plurality of EPUs, the first battery may be configured to act as a backup battery for powering the second set of EPUs, and the first high voltage bus and the second high voltage bus may be electrically separate from one another.

An electric drive system (1A-1D) comprises an electric motor (10; 10A, 10B) having a rotor (100) and a plurality of lanes (101A-101D) which are electrically isolated from one another and to which electric current can be applied independently of one another in order to drive the rotor (100); a respective supply unit (11) for each of the lanes (101A-101D); and a control system (12) which is designed to simultaneously operate at least one of the lanes (101A-101D) in a motor mode in which electric current is applied to the lane (101A-101D) via the corresponding supply unit (11) in order to convert electrical energy into kinetic energy of the rotor (100) and operate at least one of the lanes (101A-101D) in a generator mode in which electric current is provided by means of the lane (101A-101D) via the corresponding supply unit (11).

An electric drive system (1A-1D) comprises an electric motor (10; 10A, 10B) having a rotor (100) and a plurality of lanes (101A-101D) which are electrically isolated from one another and to which electric current can be applied independently of one another in order to drive the rotor (100); a respective supply unit (11) for each of the lanes (101A-101D); and a control system (12) which is designed to simultaneously operate at least one of the lanes (101A-101D) in a motor mode in which electric current is applied to the lane (101A-101D) via the corresponding supply unit (11) in order to convert electrical energy into kinetic energy of the rotor (100) and operate at least one of the lanes (101A-101D) in a generator mode in which electric current is provided by means of the lane (101A-101D) via the corresponding supply unit (11).

An aircraft wing including: a wingbox; a fuel tank; a fuel cell system with a fuel cell; a fuel line configured to deliver fuel from the fuel tank to the fuel cell system; a propulsion system carried by the wingbox; and an electrical power line configured to deliver electrical power from the fuel cell system to the propulsion system. The fuel tank and the fuel cell system are located inside the wingbox, and the propulsion system is located outside the wingbox.

An aircraft wing including: a wingbox; a fuel tank; a fuel cell system with a fuel cell; a fuel line configured to deliver fuel from the fuel tank to the fuel cell system; a propulsion system carried by the wingbox; and an electrical power line configured to deliver electrical power from the fuel cell system to the propulsion system. The fuel tank and the fuel cell system are located inside the wingbox, and the propulsion system is located outside the wingbox.

An enclosure for a plurality of battery modules is provided that includes a pair of enclosure trays. Each enclosure tray extends lengthwise between a first end wall and a second end wall, and extends widthwise between a first lateral side wall and a second lateral side wall. Each enclosure tray has a base side that extends between the first and second end walls, and between the first and second lateral side walls. Each enclosure tray includes an interior compartment defined by the first and second end walls, the first and second lateral side walls, and the base side. Each enclosure tray includes a plurality of rails that extend lengthwise between the first and second end walls and the second end wall and extend height wise into the interior compartment.