An example hybrid aircraft propulsion system includes a plurality of power units configured to output electrical energy onto one or more electrical busses; one or more propulsors; and one or more electrical machines, each respective electrical machine configured to drive a respective propulsor of the one or more propulsors using electrical energy received from at least one of the one or more electrical busses.

A propulsion system for an aircraft includes at least one gas turbine engine, an electric auxiliary fan driving motor configured to selectively receive electric power input from one or more electric power sources, and at least one auxiliary propulsion fan configured to selectively receive a motive force from either or both of the at least one gas turbine engine and the electric auxiliary fan driving motor. The propulsion system also includes a controller configured to establish a plurality of takeoff thrust settings of the at least one gas turbine engine and the electric auxiliary fan driving motor such that a minimum total aircraft thrust required for takeoff of the aircraft is produced.

The present disclosure is directed to a fan section positioned on a tail section of an aircraft, in which the fan section defines a circumferential direction, a radial direction, and an axial direction. The fan section includes a fan and a nacelle. The fan includes a plurality of fan blades and a fan shaft, in which the plurality of fan blades are rotatable with the shaft. The nacelle includes a wall at least partially enclosing the fan. The wall includes a first portion and a second portion. The first portion translates relative to the second portion between a first, closed position in which the wall of the nacelle circumferentially encloses the fan and a second, open position in which at least a portion of the fan is unenclosed by the wall of the nacelle.

The thrust force generation device is provided with: a turbo fan engine unit that includes a generator for generating power using a rotation force of a drive shaft, and that drives a fan placed on the drive shaft using gas produced by combusting fuel; a motor driven fan unit that includes a motor driven by power supplied from the generator, that is placed in parallel with the turbo fan engine unit, and that drives a fan by using the motor; and a conducting unit that connects the generator to the motor, and supplies the power generated by the generator to the motor. The turbo fan engine unit and the motor driven fan unit are integrated with each other, and the conducting unit is placed between the turbo fan engine unit and the motor driven fan unit.

A method of operating a hybrid electric power plant in cold climates comprises absorbing heat generated by an internal combustion engine, and using at least part of the heat absorbed from the internal combustion engine to warm a battery pack operatively connected to an electric motor.

A vertical take-off and landing aerial vehicle (VTOL) includes a plurality of rotors for producing lift. For each respective rotor the VTOL has an auxiliary power source (APS) and a transformation gear set (TGS) both being associated with the respective rotor, and the VTOL further includes at least one main power source (MPS). Each TGS is configured to form an outgoing power towards its respective rotor from input powers received into the TGS from the MPS and from the APS associated with the respective rotor.

In the method for propelling an aircraft, to obtain electric energy, a fuel is combusted, and an electric machine is used, wherein the fuel is used to cool at least one part of the electric machine and contains natural gas. The propulsion system is configured to propel an aircraft, in particular according to the above-mentioned method. The propulsion system has an electric machine configured to obtain electric energy by combusting a fuel. The propulsion system further includes a natural gas tank configured to supply the fuel formed with natural gas, and a cooling device configured to cool at least one part of the electric machine. The aircraft has such a propulsion system.

Systems and methods are disclosed for providing flexible, scalable, and controllable electrical power to an aircraft. In some embodiments, a modular power unit comprises a container containing a power generation unit, a control system, a conditioning system, and an environmental control system. The power generation unit produces a generated power. The control system provides control signals to the power generation unit and controls at least one parameter of the generated power. The conditioning system receives and conditions the generated power and provides an output power to the power bus of the aircraft. The environmental control system provides a temperature regulating fluid to the power generation unit.

A hybrid electric jet powered aircraft including a fuselage member, a power unit, a set of wing members, and an emergency safety unit. The fuselage member includes a cabin having a plurality of enclosed seating elements for transporting a plurality of passengers and a cockpit having a plurality of seating elements for one or more operators of the aircraft. The power unit includes at least one electric powered motor and at least one jet fueled powered engine. The set of wing members for lifting the fuselage member. The set includes two pairs of wing members, wherein each pair of wing members is attached at its proximate end to the fuselage member on opposite sides of the fuselage member from one another. Each wing member has a tilting ducted fan attached to its distal end. Each ducted fan is tilted in a first position for horizontal forward flight and each ducted fan is tilted in a second position for vertical flight. The emergency safety unit for ejecting a parachute canopy when an emergency situation occurs in the aircraft.

An assembly for an aircraft having a propeller, including an engine assembly having an engine shaft configured for driving engagement with the propeller. The engine assembly includes first and second heat exchangers configured for circulation of at least one of a liquid coolant and a lubricant therethrough. A wheel well is configured for receiving a retracted landing gear. A first cooling duct receives the first heat exchanger and has a first outlet downstream of the first heat exchanger, and a second cooling duct receives the second heat exchanger and has a second outlet downstream of the second heat exchanger. The outlets are in direct fluid communication with an environment of the aircraft, and laterally spaced from each other. The wheel well is located between the outlets. A method of cooling an engine assembly is also discussed.