A propulsion system for an aircraft, comprising at least one rotor and a nacelle fairing extending around the at least one rotor with respect to an axis of rotation of the rotor, the nacelle fairing comprising: an upstream section forming an inlet section of the nacelle fairing; a downstream section wherein a downstream end forms an outlet section of the nacelle fairing; and an intermediate section connecting the upstream and downstream sections, wherein the downstream section comprises a radially inner wall and a radially outer wall made of a deformable shape memory material, and further comprising at least one actuator mechanism with at least one cylinder configured to cooperate with one or more components, projections, etc., embedded in an inner surface of the radially outer wall so as to vary an outer diameter of the outlet section between a minimum diameter and a maximum diameter.

A hybrid powerplant is provided for an aircraft. This aircraft hybrid powerplant includes a housing, an electric machine, a heat engine and a geartrain. The housing includes a containment zone located within the housing. The electric machine is arranged within the containment zone. The heat engine is arranged partially or completely within the housing and outside of the containment zone. The geartrain is arranged partially or completely within the housing and partially or completely outside of the containment zone. The electric machine, the heat engine and the geartrain are operatively interconnected.

A hybrid powerplant is provided for an aircraft. This aircraft hybrid powerplant includes a housing, an electric machine, a heat engine and a geartrain. The housing includes a containment zone located within the housing. The electric machine is arranged within the containment zone. The heat engine is arranged partially or completely within the housing and outside of the containment zone. The geartrain is arranged partially or completely within the housing and partially or completely outside of the containment zone. The electric machine, the heat engine and the geartrain are operatively interconnected.

An aircraft propulsion system includes at least first and second electrical generators, each being configured to provide electrical power to a respective first and second AC electrical network. The system further comprises at least first and second AC electrical motors directly electrically coupled to a respective AC network and coupled to a respective propulsor, and a DC electrical network electrically coupled to the first and second AC networks via respective first and second AC to DC converters, and to a further electrical motor, the further electrical motor being coupled to a propulsor.

An aircraft propulsion system includes at least first and second electrical generators, each being configured to provide electrical power to a respective first and second AC electrical network. The system further comprises at least first and second AC electrical motors directly electrically coupled to a respective AC network and coupled to a respective propulsor, and a DC electrical network electrically coupled to the first and second AC networks via respective first and second AC to DC converters, and to a further electrical motor, the further electrical motor being coupled to a propulsor.

A hybrid interchangeable battery evaluation tool (HIBET) is provided. HIBET determines an amount of electrical energy and an amount of jet fuel necessary for a hybrid electric aircraft to complete a flight based on a range of the flight, a payload of the hybrid electric aircraft, an indication of a battery mass limitation of the hybrid electric aircraft, and an optimization of an energy split between the electrical energy and the jet fuel. HIBET causes an indication of the amount of electrical energy to be displayed in a graphical user interface and/or to be otherwise outputted.

A hybrid propulsion chain for an aircraft, the hybrid propulsion chain comprising a plurality of propulsion rotors connected to an electrical distribution module by a plurality of electrical connections, the electrical distribution module being connected, on the one hand, to a non-propulsion turbine engine via an electrical generation system and, on the other hand, to an electric battery, each propulsion rotor comprising a stator member and at least one rotor shaft which is configured to be rotated with respect to the stator member when the stator member is electrically powered, the hybrid propulsion chain comprising an auxiliary mechanical drive system mechanically connected to the non-propulsion turbine engine, the auxiliary mechanical drive system comprising a plurality of mechanical connections for mechanically rotating at least one rotor shaft of each propulsion rotor.

The invention relates to an electric architecture for a twin-engined, hybrid thermal/electric propulsion aircraft and, for each turboshaft engine, the architecture comprises: —a high-voltage DC propulsive electric distribution network (32), —a non-propulsive electric distribution network (56) which is connected to loads of the aircraft, and—an electric distribution network (76) which is connected to loads of an electrified control system of the turboshaft engine, and wherein power supply sources are shared for these different networks.

A propulsion system comprising a nacelle with an air channel along a longitudinal direction, an electric motor whose output drives a propeller, and a fuel cell, comprising a core outside the air channel, open channels, each of which has an inlet and an outlet opening in the air channel, and, for each open channel, a fuel chamber, an electrolyte between the open channel and the fuel chamber, a cathode, and an anode, each open channel having an inlet surface area which is less than the surface area of an intermediate area between the inlet and the outlet, the surface area of the outlet being smaller than the surface area of the intermediate area. Such a system makes it possible to have the fuel cell close to the electric motor, thereby reducing the lengths of the electrical conductors between them, and consequently improving the operation of the fuel cell.

The disclosure provides a penetrating high wing structure of civil aircraft with blended-wing-body, wherein the structure comprises a left wing, a right wing and a high wing penetrating central wing. The left wing and the right wing are symmetrically arranged and connected to two sides of the high wing penetrating central wing through fasteners respectively, and the high wing penetrating central wing is arranged on the top of the main body. The left wing and the right wing both comprise wing ribs and wing spars that are arranged in a crisscross way. The disclosure proposes a penetrating high wing structure, wherein the wing and the body are designed as a whole so that the wings will not damage the continuity of the internal space of the body, which improves the load transfer efficiency of the structure and reduces the fasteners used for connection, thus reducing the weight of the body.