An apparatus for venting battery ejecta for use in an electric aircraft is presented. The apparatus includes a battery module with a plurality of electrochemical cells. The electrochemical cells of the plurality of electrochemical cells are separated by a carbon fiber barrier. Venting port of a plurality of venting ports is configured to vent an electrochemical cell of the plurality of electrochemical cells using a venting path of a plurality of venting paths, wherein the plurality of vent ports is fluidly connected to the plurality of venting paths and the plurality of venting paths are fluidly connected to at least an outlet. Venting paths direct the battery ejecta from the electrochemical cell to the outside of the electric aircraft through at least an outlet.

Thrust values for motors in an aircraft are generated where each flight controller in a plurality of flight controllers generates a thrust value for each motor in a plurality of motors using an optimization problem with a single solution. Each flight controller in the plurality of flight controllers passes one of the generated thrust values to a corresponding motor in the plurality of motors, where other generated thrust values for that flight controller terminate at that flight controller. The plurality of motors perform the passed thrust values.

To provide an electric aircraft and an aerodynamic performance control method therefor that are capable of optimizing aerodynamic performance of a wing in each flight phase or an emergency such as gust action without depending on the shape of a wing.

To provide an electric aircraft and an aerodynamic performance control method therefor that are capable of optimizing aerodynamic performance of a wing in each flight phase or an emergency such as gust action without depending on the shape of a wing.

[Solving Means] An electric aircraft 1 includes: one or two or more electric propulsion systems 20 each including a propeller or fan 21 for propulsion disposed to contribute to a lift of a main wing 11, 12, and an electric motor 22 that drives the propeller or fan 21; and a controller that adjusts the electric propulsion system 20 on the basis of a relationship between a variable relating to an operating state of the electric propulsion system 20 and an aerodynamic force generated on the main wing 11, 12 such that a total thrust by the electric propulsion systems 20 or the aerodynamic force on the main wing 11, 12 has a predetermined value or falls within a predetermined range.

To provide an electric aircraft and an aerodynamic performance control method therefor that are capable of optimizing aerodynamic performance of a wing in each flight phase or an emergency such as gust action without depending on the shape of a wing.

To provide an electric aircraft and an aerodynamic performance control method therefor that are capable of optimizing aerodynamic performance of a wing in each flight phase or an emergency such as gust action without depending on the shape of a wing.

[Solving Means] An electric aircraft 1 includes: one or two or more electric propulsion systems 20 each including a propeller or fan 21 for propulsion disposed to contribute to a lift of a main wing 11, 12, and an electric motor 22 that drives the propeller or fan 21; and a controller that adjusts the electric propulsion system 20 on the basis of a relationship between a variable relating to an operating state of the electric propulsion system 20 and an aerodynamic force generated on the main wing 11, 12 such that a total thrust by the electric propulsion systems 20 or the aerodynamic force on the main wing 11, 12 has a predetermined value or falls within a predetermined range.

A method of operating an electrically powered rotorcraft of the type having a fuselage and a set of N rotors driven by a set of electric motors and coupled to the fuselage, N?4, under a failure condition preventing ordinary operation of the rotorcraft. The method includes entering a failsafe mode of operation wherein autorotation of at least four of the rotors is enabled. The method also includes using electrical braking associated with a selected group of the rotors to control pitch, roll and yaw of the rotorcraft.

A propulsor fan array having reduced noise emission is disclosed. The propulsor fan array includes a plurality of propulsor fans that collectively generate thrust. Each of the propulsor fans include a blade fan having a plurality of blades. The plurality of blades are tensioned at tips of the plurality of blade fans such that a pitch of the blades during thrust generation is substantially the same as a pitch of the blades at rest. By tensioning the tips of the blades, an angle of the blades is maintained during operation of the propulsor fan thereby reducing noise that may result from changes in the angle of the blades.

A propulsor fan array having reduced noise emission is disclosed. The propulsor fan array includes a plurality of propulsor fans that collectively generate thrust. Each of the propulsor fans include a blade fan having a plurality of blades. The plurality of blades are tensioned at tips of the plurality of blade fans such that a pitch of the blades during thrust generation is substantially the same as a pitch of the blades at rest. By tensioning the tips of the blades, an angle of the blades is maintained during operation of the propulsor fan thereby reducing noise that may result from changes in the angle of the blades.

A cooling system includes a plurality of heat exchanger assemblies corresponding to a plurality of battery packs and a fluid conveyance assembly. Each heat exchanger assembly includes a first heat exchanger inlet-outlet and a second heat exchanger inlet-outlet configured to receive a heat transfer fluid or discharge the heat transfer fluid. The fluid conveyance assembly is coupled to the heat exchanger assemblies and configured to circulate the heat transfer fluid in parallel to the heat exchanger assemblies in a U-flow scheme with an inlet and an outlet of the heat transfer fluid arranged at the same location. The fluid conveyance assembly includes a plurality of flow restrictors configured to balance the heat transfer fluid flowing into the heat exchanger assemblies. The heat transfer fluid flows through the corresponding flow restrictor before flowing into the corresponding heat exchanger assembly of the battery pack.

An electric aircraft includes a fuselage, at least one rotor, at least one coupling structure, at least one electric motor, a battery and wirings. The at least one coupling structure couples the at least one rotor to the fuselage. The at least one electric motor is for rotating the at least one rotor. The battery is attached to the fuselage. The battery is for supplying current to the at least one electric motor. The wirings electrically couples the battery to the at least one electric motor. At least a part of the wirings includes rigid conductors. At least a part of the at least one coupling structure includes the rigid conductors. At least a part of a load on the fuselage from the at least one rotor is received with the rigid conductors.

Electric engine to provide thrust to fly an aircraft. Engine includes housing, air inlet, shaft, bladed rotor having a plurality of magnets secured on shaft, stator having plurality of coils positioned so as to interact with plurality of magnets and an exhaust nozzle. Powering coils causes interaction with magnets that results in bladed rotor rotating and pressurizing and accelerating air received via air inlet and expelling via exhaust nozzle to provide thrust. Engine may include generator having stator with coils secured to shaft via bearings and plurality of rotors with magnets secured to shaft to rotate with shaft. Magnets rotating past coils results in electric generation. Second hollow shaft may be mounted to shaft with bearings and generator may be located with hollow shaft. Second bladed rotor may be connected to, and rotate, second shaft. Engine may include ducts external to bladed rotor and fan to route air therein.