A modular power plant for a rotorcraft comprising at least one lift rotor, the power plant comprising: at least one combustion or electric engine; a main gearbox, comprising a gearbox housing and a toothed wheel arranged in an internal space at least partially delimited by the gearbox housing, the toothed wheel having a degree of rotational freedom about a primary axis of rotation relative to the gearbox housing, the toothed wheel mechanically transmitting an engine torque generated by the at least one engine to the at least one lift rotor; and at least two mechanical connection interfaces, a first mechanical connection interface mechanically connecting the main gearbox to a first engine, and a second mechanical connection interface being left free or mechanically connecting the main gearbox to a second engine.

A method for assisting the piloting of a rotorcraft including at least two engines capable of transmitting engine torque to at least one main rotor, the assistance method comprising the following steps: periodically determining a current position of the rotorcraft; making a first periodic comparison between the current position and a decision point; identifying an engine failure; making a second periodic comparison between the current position of the rotorcraft and a touchdown point; periodically determining an emergency landing profile, the emergency landing profile being generated at least depending on a result of the second periodic comparison; and periodically generating control orders to pilot the rotorcraft according to the emergency landing profile.

A method for assisting the piloting of a rotorcraft including at least two engines capable of transmitting engine torque to at least one main rotor, the assistance method comprising the following steps: periodically determining a current position of the rotorcraft; making a first periodic comparison between the current position and a decision point; identifying an engine failure; making a second periodic comparison between the current position of the rotorcraft and a touchdown point; periodically determining an emergency landing profile, the emergency landing profile being generated at least depending on a result of the second periodic comparison; and periodically generating control orders to pilot the rotorcraft according to the emergency landing profile.

A plurality of energy storage packs (51 to 58) supply a current to a plurality of motor driver (31 to 38) that drive a plurality of motors (21 to 28) mounted on moving object (1), respectively. Sub energy storage pack (59) supplies a current to at least one of a plurality of first current paths connecting the plurality of motor driver (31 to 38) and the plurality of energy storage packs (51 to 58), or pulls a current from at least one of the plurality of first current paths. Controller (70) controls the plurality of first switches (S11 to S18) and the plurality of second switches (S21 to S28) to adjust capacities between the plurality of energy storage packs (51 to 58).

A plurality of energy storage packs (51 to 58) supply a current to a plurality of motor driver (31 to 38) that drive a plurality of motors (21 to 28) mounted on moving object (1), respectively. Sub energy storage pack (59) supplies a current to at least one of a plurality of first current paths connecting the plurality of motor driver (31 to 38) and the plurality of energy storage packs (51 to 58), or pulls a current from at least one of the plurality of first current paths. Controller (70) controls the plurality of first switches (S11 to S18) and the plurality of second switches (S21 to S28) to adjust capacities between the plurality of energy storage packs (51 to 58).

A propulsion system for an aircraft, which has a chassis, a propeller able to move in rotation about an axis of rotation, a main gear as one with the propeller, an electric generator, at least one linear electric motor having a fixed element and a slider able to move in translation, for each linear electric motor, a secondary gear meshing with the main gear and mounted to be able to move in rotation about an axis of rotation perpendicular to the axis of rotation, and a rod of which one end is articulated on the corresponding slider and of which the other end is articulated on the corresponding secondary gear at an articulation that is offset with respect to the axis of rotation of the secondary gear.

A high-speed vertical take-off and landing aircraft has a lifting structure, a first rotor with a first and second blade, a second rotor with a first and second blade, an auxiliary propulsion unit for providing forward thrust, and a control system for controlling the pitch of each of the rotor blades. The aircraft has a first, rotor-only, flight mode for hovering and low speed maneuvering. It also has a second flight mode where the rotors are held in at fixed azimuth angles and forward thrust is provided by the auxiliary propulsion unit. Three axis control is provided during the second flight mode by adjusting the attack angles of the fixed rotor blades. Between these two flight modes, there is an intermediate flight mode covering a fully controlled transition between the first two flight modes.

A high-speed vertical take-off and landing aircraft has a lifting structure, a first rotor with a first and second blade, a second rotor with a first and second blade, an auxiliary propulsion unit for providing forward thrust, and a control system for controlling the pitch of each of the rotor blades. The aircraft has a first, rotor-only, flight mode for hovering and low speed maneuvering. It also has a second flight mode where the rotors are held in at fixed azimuth angles and forward thrust is provided by the auxiliary propulsion unit. Three axis control is provided during the second flight mode by adjusting the attack angles of the fixed rotor blades. Between these two flight modes, there is an intermediate flight mode covering a fully controlled transition between the first two flight modes.

The invention relates to a device for the rapid reactivation of a helicopter turbine engine (6), characterised in that it comprises a pneumatic turbine (7) mechanically connected to said turbine engine (6) so as to be able to rotate it and ensure reactivation thereof; a pneumatic storage (9) connected to said pneumatic turbine (7) by means of a pneumatic circuit (10) for supplying pressurised gas to said pneumatic turbine (7); a controlled fast-opening pneumatic valve (11) arranged on the pneumatic circuit (10) between said storage (9) and said pneumatic turbine (7) and suitable for being on demand placed at least in an open position in which the gas can supply said pneumatic turbine (7), or in a closed position in which said pneumatic turbine (7) is no longer supplied with pressurised gas.

The invention relates to a device for the rapid reactivation of a helicopter turbine engine (6), characterised in that it comprises a pneumatic turbine (7) mechanically connected to said turbine engine (6) so as to be able to rotate it and ensure reactivation thereof; a pneumatic storage (9) connected to said pneumatic turbine (7) by means of a pneumatic circuit (10) for supplying pressurised gas to said pneumatic turbine (7); a controlled fast-opening pneumatic valve (11) arranged on the pneumatic circuit (10) between said storage (9) and said pneumatic turbine (7) and suitable for being on demand placed at least in an open position in which the gas can supply said pneumatic turbine (7), or in a closed position in which said pneumatic turbine (7) is no longer supplied with pressurised gas.