A hybrid aircraft architecture is disclosed that uses an electric motor-generator-propeller propulsion system for takeoff, landings, and low speed flying, and wave engines for cruise-condition flying and flying at high speeds. The propeller of the electric motor-generator-propeller propulsion system can be located at the nose or aft end (tail) of the aircraft. The wave engines can be located at the aft end of the fuselage, or under or integrated into the wing structures. The wave engines can be deployed in pairs and the wave engines of the pair may be cross-connected and operated in an anti-phase mode to reduce the noise and vibration that would exist if each wave engine is operated independently.

A hybrid aircraft architecture is disclosed that uses an electric motor-generator-propeller propulsion system for takeoff, landings, and low speed flying, and wave engines for cruise-condition flying and flying at high speeds. The propeller of the electric motor-generator-propeller propulsion system can be located at the nose or aft end (tail) of the aircraft. The wave engines can be located at the aft end of the fuselage, or under or integrated into the wing structures. The wave engines can be deployed in pairs and the wave engines of the pair may be cross-connected and operated in an anti-phase mode to reduce the noise and vibration that would exist if each wave engine is operated independently.

A control system for charging an aircraft, comprising: a battery pack, an input device configured to enable a user to select between different charging modes, two main contactors connecting the battery pack to an electric propulsion unit (EPU) load and an auxiliary load, a EPU load contactor connecting the battery pack to the EPU load and a controller configured to receive the selected charge mode and control the contactors, keep the two main contactors open upon receiving a user selection to charge in a first mode, close the two main contactors and keep an EPU load contactor open upon receiving a user selection to charge in a second mode, and close the two main contactors and the EPU load contactor upon receiving a user selection to charge in a third mode.

A control system for charging an aircraft, comprising: a battery pack, an input device configured to enable a user to select between different charging modes, two main contactors connecting the battery pack to an electric propulsion unit (EPU) load and an auxiliary load, a EPU load contactor connecting the battery pack to the EPU load and a controller configured to receive the selected charge mode and control the contactors, keep the two main contactors open upon receiving a user selection to charge in a first mode, close the two main contactors and keep an EPU load contactor open upon receiving a user selection to charge in a second mode, and close the two main contactors and the EPU load contactor upon receiving a user selection to charge in a third mode.

The disclosure relates to a battery driven flight vehicle. The battery-driven flight vehicle, comprising: a control unit; and a battery charged by a power supply device, wherein the control unit executes flight control in accordance with a charging speed of the battery. The disclosure also relates to a method of providing a Mobility as a Service (MaaS) in which the flight vehicle is used.

The disclosure relates to a battery driven flight vehicle. The battery-driven flight vehicle, comprising: a control unit; and a battery charged by a power supply device, wherein the control unit executes flight control in accordance with a charging speed of the battery. The disclosure also relates to a method of providing a Mobility as a Service (MaaS) in which the flight vehicle is used.

An aircraft having a hybrid power source includes horizontal drive thrusters powered by an electric motor and forming a horizontal drive unit, vertical take-off/landing rotors forming with electric motors and a corresponding stored electrical energy source a vertical drive unit comprising an electric power supply bus, power generation sources connected to the electric power supply buses and by an input of a vertical drive unit and to each horizontal drive unit via an output of each vertical drive unit. The electric power supply controller emits a power command to the power generation source according to power requirements of the vertical and/or horizontal drive units. The stored electrical energy sources supply electricity according to the difference between the power requirements of the vertical and/or horizontal drive units. The power generation source recharges the stored electrical energy sources, so that the stored electrical energy sources are passively controlled.

An aircraft having a hybrid power source includes horizontal drive thrusters powered by an electric motor and forming a horizontal drive unit, vertical take-off/landing rotors forming with electric motors and a corresponding stored electrical energy source a vertical drive unit comprising an electric power supply bus, power generation sources connected to the electric power supply buses and by an input of a vertical drive unit and to each horizontal drive unit via an output of each vertical drive unit. The electric power supply controller emits a power command to the power generation source according to power requirements of the vertical and/or horizontal drive units. The stored electrical energy sources supply electricity according to the difference between the power requirements of the vertical and/or horizontal drive units. The power generation source recharges the stored electrical energy sources, so that the stored electrical energy sources are passively controlled.

An electric motor drive system for a propulsion device. The system includes a battery stack having an earth terminal and an end terminal and an electric motor electrically connected to be powered by the battery stack. The motor is configured to be connected to drive the propulsion device, The system also includes: a power converter electrically connected between the battery stack and the electric motor; and a switch between the power converter and the battery stack. The switch is arranged to switch between a first state electrically connecting the end terminal of the battery stack to the power converter to provide a maximum battery voltage to the power converter, and a second state electrically connecting a tap point from one or more intermediate nodes, intermediate the earth terminal and the end terminal, of the battery stack, to provide a voltage less than the maximum battery voltage to the power converter.

A method of and system for operating a hybrid electric propulsion system for an aircraft in a start sequence is provided. The hybrid electric propulsion system includes a thermal engine, an electric motor, a gearbox, an electric power storage unit, and a propulsion unit having a propeller having propeller blades. The method includes: driving the propeller from a static state to a target rotational speed within a predetermined range of speeds using the electric motor; transitioning the propeller blades from a feathered mode to an unfeathered mode while the propeller is being driven at the target rotational speed solely by the electric motor; starting the thermal engine; and transitioning the driving of the propeller using the electric motor to driving the propeller using the thermal engine.