The present invention relates to a body (2) provided at air vehicles: at least one rotor (3) extending longitudinally out of the body (2) and rotating around an axis along which it extends: at least one blade (4) connected to the rotor (3), which, upon triggering of the rotor (3), rotates around the axis along which the rotor (3) extends, thus creating an aerodynamic lifting force required for the body (2) to take-off: a blade tip (5) which is located on the blade (4), at the end of a direction along which the blade (4) extends: and at least one plate (6) made of a piezo-electric material, which is located on the blade (4) and enables energy conversion.

A method for managing at least one aircraft configured to alternately occupy a first configuration suitable for a first flight category not requiring any auxiliary power unit and a second configuration suitable for a second flight category requiring at least one auxiliary power unit. The managing method includes adapting the configuration of the aircraft to the category of the flight to be performed. Thus, when the category of the flight to be performed by the aircraft does not require it, the auxiliary power unit can be removed, this leading to a decrease in on-board weight.

A method for managing at least one aircraft configured to alternately occupy a first configuration suitable for a first flight category not requiring any auxiliary power unit and a second configuration suitable for a second flight category requiring at least one auxiliary power unit. The managing method includes a step of removably mounting, alternately, a lightened first tail cone not including any auxiliary power unit or a second tail cone including at least one auxiliary power unit depending on the first or second category of flights to be performed by the aircraft. A method for managing at least one fleet of aircraft, an aircraft, and a managing device configured to implement the method are each also provided.

An aircraft includes a fuselage, a main entry door with an associated passenger loading zone, an auxiliary power unit (APU) in the fuselage, and an APU inlet assembly. The APU inlet assembly has an inlet duct, and inlet door, and means for redirecting sound waves coupled to or integrated with an interior side of the inlet door. The inlet duct has a first end coupled to the APU, and a second end associated with the inlet door. The inlet door moves between a closed position and an open position. The means for redirecting sound waves is positioned at a particular location on the interior side of the inlet door, and includes certain acoustic features and characteristics. The particular location and the acoustic features and characteristics cooperate to redirect sound waves generated by the APU away from the passenger loading zone when the inlet door is in the open position.

A method for converting a conventional airplane having at least one thermic reaction propulsion engine and at least one fuel tank fluidly connected through fuel pipes to an electric propulsion airplane comprises: removing the at least one thermic reaction propulsion engine from the conventional airplane; replacing the at least one thermic reaction propulsion engine used for propelling the conventional airplane with at least one electric engine; removing the at least one fuel tank from the conventional airplane; implanting at least one rechargeable battery instead of the at least one fuel tank; and electrically connecting the at least one electric engine and the at least one rechargeable battery.

The invention relates to an assembly comprising a structure (2) and a tubular element (6), which is mounted isostatically in the structure (2), said tubular element (6) comprising a first end (7) connected to said structure by at least four connecting rods 10a-10b-10c-10d, thus setting four first degrees of freedom, and a second end (8) connected to said structure (2) by an attachment means (20) that sets two second degrees of freedom, said connecting rods comprising a means for adjusting the length thereof. In particular, it relates to an exhaust suitable for an auxiliary power unit in the compartment thereof and to the mounting method for aligning them.

A method and configuration to optimize an entire traction system available on a helicopter including an auxiliary engine by allowing the engine to provide non-propulsive and/or propulsive power during flight. The auxiliary engine is coupled to participate directly in providing mechanical or electrical propulsive power and electrical non-propulsive power to the aircraft. An architecture configuration includes an on-board power supply network, two main engines, and a system for converting mechanical energy into electrical energy between a main gearbox to the propulsion members and a mechanism receiving electrical energy including the on-board network and power electronics in conjunction with starters of the main engines. An auxiliary power engine provides electrical energy to the mechanism for receiving electrical energy via the energy conversion system and a mechanism for mechanical coupling between the auxiliary engine and at least one propulsion member.

A mounting assembly for mounting a portion of an engine exhaust duct in an opening of an airframe panel aircraft, including a peripheral flange disposed on the portion of the exhaust duct, and at least one mounting member having an outer peripheral flange portion for connection to the airframe panel and having an inner peripheral flange portion with at least one compliant isolator member to receive the peripheral flange of the exhaust duct in a manner that suspends the exhaust duct in the opening away from the airframe panel and accommodates thermal expansion and contraction of the exhaust duct relative to the airframe panel. Embodiments include a method of mounting an engine exhaust duct in an opening of an outer airframe panel of an aircraft.

An aircraft tailcone comprising a tailcone fuselage, a turbomachine, for example an APU, housed inside the tailcone, a ram air intake on the tailcone fuselage for the ingestion of ram air towards the interior of the turbomachine compartment, an inlet flap operable reciprocately from an open position in which ingestion of ram air is allowed, and a closed position in which ram air ingestion is prevented. The ram air intake extends annularly along a perimeter of the tailcone fuselage, and the inlet flap is configured such in its closed position that a surface of the inlet flap is substantially flush with the tailcone fuselage.

One example of a mount for a rotorcraft comprises a structural support member, a bracket, and an elastomer. The bracket is configured to attach to a component of the rotorcraft. The component of the rotorcraft produces vibrations at a first frequency. The structural support member configured to transfer a weight of the component of a rotorcraft to an airframe of the rotorcraft. A rotor system of the aircraft vibrates the airframe of the rotorcraft at a second frequency. The elastomer is located between a structural support member and a bracket. The elastomer is configured to attenuate noise caused by the vibrations at the first frequency by isolating the vibrations at the first frequency from reaching the airframe of the rotorcraft while the airframe vibrates at the second frequency.