An aircraft propulsion system is disclosed that includes at least one hybrid-electric powerplant for delivering power to an air mover for propelling the aircraft, wherein the at least one hybrid-electric powerplant includes a heat engine and an electric motor arranged in a parallel drive configuration or an in-line drive configuration.

A vertical take-off and landing (VTOL) aircraft is provided and includes wings, first and second nacelles supported on each of the wings, each of the first and second nacelles including a propeller drivable to generate aircraft thrust, and an asymmetrical power generation unit. The asymmetrical power generation unit includes a single engine unit disposed in only one of the first and second nacelles to generate power to drive the propellers of both the first and second nacelles.

A vertical take-off and landing (VTOL) aircraft is provided and includes wings, first and second nacelles supported on each of the wings, each of the first and second nacelles including a propeller drivable to generate aircraft thrust, and an asymmetrical power generation unit. The asymmetrical power generation unit includes a single engine unit disposed in only one of the first and second nacelles to generate power to drive the propellers of both the first and second nacelles.

Systems and methods for automated configuration of mission specific aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. A method includes receiving mission parameters including flight parameters and payload parameters; configuring an airframe based upon the mission parameters including selecting a flight control system, first and second wings and first and second pylons operable for coupling between the first and second wings, the first and second wings each having first and second inboard nacelle stations and first and second outboard nacelle stations; determining thrust requirements based upon the mission parameters; configuring a two-dimensional distributed thrust array based upon the thrust requirements including selecting inboard propulsion assemblies operable for coupling to the inboard nacelle stations of the first and second wings and selecting outboard propulsion assemblies operable for coupling to the outboard nacelle stations of the first and second wings.

Systems and methods for automated configuration of mission specific aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. A method includes receiving mission parameters including flight parameters and payload parameters; configuring an airframe based upon the mission parameters including selecting a flight control system, first and second wings and first and second pylons operable for coupling between the first and second wings, the first and second wings each having first and second inboard nacelle stations and first and second outboard nacelle stations; determining thrust requirements based upon the mission parameters; configuring a two-dimensional distributed thrust array based upon the thrust requirements including selecting inboard propulsion assemblies operable for coupling to the inboard nacelle stations of the first and second wings and selecting outboard propulsion assemblies operable for coupling to the outboard nacelle stations of the first and second wings.

There is disclosed an engine assembly, including an internal combustion engine having a housing and a coolant circuitry in heat exchange relationship with the housing. A porous surface is configured for defining a portion of an external surface of an aircraft. Apertures are defined through the porous surface. The housing of the internal combustion engine is in heat exchange relationship with the porous surface for heating the porous surface. An air conduit has an inlet fluidly connected to a boundary layer region outside the engine assembly and adjacent the porous surface via the apertures of the porous surface. The air conduit is in heat exchange relationship with the coolant circuitry. A forced air system is fluidly connected to the inlet of the air conduit and is operable to draw an airflow from the inlet and inside the air conduit. A method of operating the engine assembly is disclosed.

There is disclosed an engine assembly, including an internal combustion engine having a housing and a coolant circuitry in heat exchange relationship with the housing. A porous surface is configured for defining a portion of an external surface of an aircraft. Apertures are defined through the porous surface. The housing of the internal combustion engine is in heat exchange relationship with the porous surface for heating the porous surface. An air conduit has an inlet fluidly connected to a boundary layer region outside the engine assembly and adjacent the porous surface via the apertures of the porous surface. The air conduit is in heat exchange relationship with the coolant circuitry. A forced air system is fluidly connected to the inlet of the air conduit and is operable to draw an airflow from the inlet and inside the air conduit. A method of operating the engine assembly is disclosed.

A method for mounting an aircraft pylon connected to a wing includes: a step of pre-positioning first and second contact surfaces respectively provided on the wing and the pylon, a step of installing and tightening temporary connection elements, so as to keep the first and second contact surfaces clamped against one another, a step of installing and expanding at least one radially expandable element in at least one pair of first and second receptacles respectively provided on the wing and the pylon, a step of installing and tightening final connection elements connecting the pylon and the wing in the mounted state, a step of removing the radially expandable element(s) and the temporary connection elements, and of installing the remaining final connection elements and shear pin(s).

Systems, devices, and methods for an aircraft having a fuselage; a wing extending from both sides of the fuselage; a first pair of motors disposed at a first end of the wing; and a second pair of motors disposed at a second end of the wing; where each motor is angled to provide a component of thrust by a propeller attached thereto that for a desired aircraft movement applies a resulting torque additive to the resulting torque created by rotating the propellers.

Systems, devices, and methods for an aircraft having a fuselage; a wing extending from both sides of the fuselage; a first pair of motors disposed at a first end of the wing; and a second pair of motors disposed at a second end of the wing; where each motor is angled to provide a component of thrust by a propeller attached thereto that for a desired aircraft movement applies a resulting torque additive to the resulting torque created by rotating the propellers.