A system is provided for an aircraft. This aircraft system includes an aircraft structure, an electrical power storage and an air system. The aircraft structure includes an internal compartment. The electrical power storage is housed within the internal compartment. The air system is configured to direct pressurized air into the internal compartment. The air system includes a plurality of air sources and a flow regulator. The flow regulator is configured to fluidly couple each of the air sources to the internal compartment.

The invention is related to a Method for producing a battery device (10), in particular for use in an electric aircraft, comprising the following steps: providing a battery housing (20) with at least one cell compartment (30) having one receiving opening (32) and surrounding compartment walls (34) for holding a battery module (40) with multiple battery cells (42), stacking multiple battery cells (42) on top of each other to create at least one battery module (40), inserting the at least one battery module (40) into the at least one cell compartment (30) through the receiving opening (32), and closing the receiving opening (32) of the at least one cell compartment (30).

The invention is related to a Method for producing a battery device (10), in particular for use in an electric aircraft, comprising the following steps: providing a battery housing (20) with at least one cell compartment (30) having one receiving opening (32) and surrounding compartment walls (34) for holding a battery module (40) with multiple battery cells (42), stacking multiple battery cells (42) on top of each other to create at least one battery module (40), inserting the at least one battery module (40) into the at least one cell compartment (30) through the receiving opening (32), and closing the receiving opening (32) of the at least one cell compartment (30).

Provided is an aircraft with a multi-power source electric propulsion system. The aircraft includes a fuselage, a power turbine accommodated in the fuselage and having a power shaft, a generator accommodated in the fuselage and connected to one end of the power shaft, a forward propeller for a forward flight and connected to another end of the power shaft, and a lift propeller for vertical take-off and landing (VTOL) and configured to receive power from the generator.

Provided is an aircraft with a multi-power source electric propulsion system. The aircraft includes a fuselage, a power turbine accommodated in the fuselage and having a power shaft, a generator accommodated in the fuselage and connected to one end of the power shaft, a forward propeller for a forward flight and connected to another end of the power shaft, and a lift propeller for vertical take-off and landing (VTOL) and configured to receive power from the generator.

The present disclosure relates to a battery cell, a battery cell fabrication method, an aviation battery, and a method for monitoring an aviation battery. The battery cell includes a housing and an electrode assembly accommodated in the housing. The battery cell further includes one or more sensor strips embedded between the electrode assembly and the housing and spirally wound around an outer peripheral surface of the electrode assembly. The battery cell, the battery cell fabrication method, the aviation battery, and the method for monitoring an aviation battery according to the present disclosure can accurately detect the state of each battery cell in an aviation battery in a real time manner, so as to enable early detection of abnormality of a single battery cell, thereby improving the state monitoring of the battery cell, and improving the safety performance of the battery cell and the battery including the battery cell

The present disclosure relates to a battery cell, a battery cell fabrication method, an aviation battery, and a method for monitoring an aviation battery. The battery cell includes a housing and an electrode assembly accommodated in the housing. The battery cell further includes one or more sensor strips embedded between the electrode assembly and the housing and spirally wound around an outer peripheral surface of the electrode assembly. The battery cell, the battery cell fabrication method, the aviation battery, and the method for monitoring an aviation battery according to the present disclosure can accurately detect the state of each battery cell in an aviation battery in a real time manner, so as to enable early detection of abnormality of a single battery cell, thereby improving the state monitoring of the battery cell, and improving the safety performance of the battery cell and the battery including the battery cell

An aircraft power battery, an aircraft, and an aircraft power battery integrated power supply method are provided. One battery box is accommodated in each separate compartment. The battery boxes in each row or column of separate compartments being connected in series and then being connected to a battery management system (BMS) module, forming a plurality of battery paths which are then connected in parallel, before supplying power to the aircraft. The method ensures power supply reliability and achieving the integrated arrangement of the limitation and integration of battery packs and battery management system, avoiding the occurrence of high working current and overheating of wire harness caused by scattered layout of each battery pack in the cabin, and is conducive to installation and maintenance. In addition, a cooling bottom plate is equipped for the power battery to ensure heat dissipation performance.

An aircraft power battery, an aircraft, and an aircraft power battery integrated power supply method are provided. One battery box is accommodated in each separate compartment. The battery boxes in each row or column of separate compartments being connected in series and then being connected to a battery management system (BMS) module, forming a plurality of battery paths which are then connected in parallel, before supplying power to the aircraft. The method ensures power supply reliability and achieving the integrated arrangement of the limitation and integration of battery packs and battery management system, avoiding the occurrence of high working current and overheating of wire harness caused by scattered layout of each battery pack in the cabin, and is conducive to installation and maintenance. In addition, a cooling bottom plate is equipped for the power battery to ensure heat dissipation performance.

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.