Abstract: A propulsion engine comprising at least a first propulsion unit including a first fan encased by a geared ring and a gas turbine engine driving a first shaft connected to the first fan, at least a second propulsion unit including a second fan encased by a geared ring connected to a second shaft operatively coupled to an electric machine and at least an electric storage device connected to the electric machine. The geared rings are configured to transmit torque between the fans so that they can rotate in conjunction (directly or through an intermediate gear) when they are driven by at least one of said first and second shafts. The propulsion engine is arranged for controlling the torque to be supplied to the assembly of the first and second fans by the gas turbine engine and/or by the electric machine acting as a motor or as a generator.

Abstract: A multi-fan engine including a gas turbine engine, a casing and fans encased by geared rings, which connect with the geared rings of an adjacent fan(s) such that the rotation of one fan rotates the other fans. Intermediate gears may prove the connection between adjacent geared rings, wherein the intermediate gears are retracted by linear actuators to disengage the intermediate gears from the geared rings and thereby disengage the fans from each other. The multi-fan engine may be mounted flush to the fuselage of an aircraft invention to capture into the fans boundary layer airflow moving over the skin of the fuselage.

Abstract: A double-deck airplane that facilitates passenger embarking/disembarking and cargo loading/unloading operations in order to maximize the number of flight missions carried out in a given time. The floors of its upper and lower decks are planar surfaces extending continuously inside the fuselage in at least the inner space of the fuselage intended for the payload; the lower deck is located at a height from the ground that allows carrying out passenger embarking/disembarking via equipment incorporated in the airplane without any external airport ground equipment; passenger and/or cargo compartments are distributed on the upper and/or lower decks; and the lifting structure is disposed in the airplane in a manner that none of its components crosses the upper and lower decks.

Abstract: The invention provides an aircraft with a trimmable horizontal stabilizer (13) that not requires a cut-out in resistant areas of the rear fuselage and that occupies less space that in conventional horizontal stabilizers. The rear fuselage (5) comprises at least a first section (9) having a resistant fuselage and a second section (11), aft of the first section, having a non-resistant fuselage (i.e. a fairing). The load-bearing structure (30) of the horizontal stabilizer and the trimming actuator (50) are disposed inside said second section (11). The pivot element (41) is mounted on its forward side and coupled to the first section (9) of the rear fuselage. The connection fitting (21) is mounted on its rearward side and the trimming actuator (50) is disposed so that it exerts a force in the direction of the Z-axis of the aircraft on the connection fitting (21) during a trimming operation.

Abstract: A propulsion engine comprising at least a first propulsion unit including a first fan encased by a geared ring and a gas turbine engine driving a first shaft connected to the first fan, at least a second propulsion unit including a second fan encased by a geared ring connected to a second shaft operatively coupled to an electric machine and at least an electric storage device connected to the electric machine. The geared rings are configured to transmit torque between the fans so that they can rotate in conjunction (directly or through an intermediate gear) when they are driven by at least one of said first and second shafts. The propulsion engine is arranged for controlling the torque to be supplied to the assembly of the first and second fans by the gas turbine engine and/or by the electric machine acting as a motor or as a generator.

Abstract: A multi-fan engine including a gas turbine engine, a casing and fans encased by geared rings, which connect with the geared rings of an adjacent fan(s) such that the rotation of one fan rotates the other fans. Intermediate gears may prove the connection between adjacent geared rings, wherein the intermediate gears are retracted by linear actuators to disengage the intermediate gears from the geared rings and thereby disengage the fans from each other. The multi-fan engine may be mounted flush to the fuselage of an aircraft invention to capture into the fans boundary layer airflow moving over the skin of the fuselage.

Abstract: An aircraft for transporting passengers and cargo able to efficiently handle ground operations for loading/unloading cargo and embarking/disembarking passengers at the same time. The lifting structure of the aircraft is formed by a back-swept wing and a fore-plane, the back-swept wing including winglets having a length L allowing them to act as vertical stabilizers. The propulsion system is mounted aft of the center of gravity of the aircraft and the tailcone of the fuselage is configured to act as a rear access door and as a pressure barrier.

Abstract: The invention provides an aircraft with a trimmable horizontal stabilizer (13) that not requires a cut-out in resistant areas of the rear fuselage and that occupies less space that in conventional horizontal stabilizers. The rear fuselage (5) comprises at least a first section (9) having a resistant fuselage and a second section (11), aft of the first section, having a non-resistant fuselage (i.e. a fairing). The load-bearing structure (30) of the horizontal stabilizer and the trimming actuator (50) are disposed inside said second section (11). The pivot element (41) is mounted on its forward side and coupled to the first section (9) of the rear fuselage. The connection fitting (21) is mounted on its rearward side and the trimming actuator (50) is disposed so that it exerts a force in the direction of the Z-axis of the aircraft on the connection fitting (21) during a trimming operation.

Abstract: The invention provides a double-deck airplane that facilitates passenger embarking/disembarking and cargo loading/unloading operations in order to maximize the number of flight missions carried out in a given time. Among other the airplane has the following features: the floors of the upper and lower decks (41, 43) are planar surfaces extending continuously inside the fuselage in at least the inner space of the fuselage intended for the payload; the lower deck (43) is located at a height from the ground that allows carrying out passenger embarking/disembarking autonomously without any specific airport ground equipment; passenger and/or cargo compartments (64, 63) are distributed throughout the upper and/or lower decks (41, 43); the lifting structure is disposed in the airplane in a manner that none of its components crosses the upper and lower decks (41, 43).

Abstract: The invention relates to a process for manufacturing stiffened structures (1) in composite materials formed by an outer skin (2) and a plurality of stiffeners (3) the cross-section of which has a closed shape delimiting an inner opening (6), comprising the following steps: a) providing a shaping jig (34); b) providing auxiliary male jigs (36) with inner cavities (32) reinforced (33) along their length, coated by membranes (37) suitable for curing; c) providing stiffeners (3); d) arranging the stiffeners (3) in the jig (34) and in their inner openings (6) the auxiliary male jigs (36); e) laminating the outer skin (2); f) curing the stiffened structure (1) with high temperature and pressure; g) removing the auxiliary male jigs (36) after reducing their section (41); h) separating the cured stiffened structure (1) from the jig (34), the design of the inner cavities (32) including their reinforcement (33) and the capacity to maintain or reduce their section by the application of overpressure or underpressure resp

Abstract: Arrangement for mounting a propulsive system on an aircraft airframe 12 by means of an external strut 4 which connects the engine 1 with the airframe 12, said strut 4 comprising a plurality of spars 8 intruding into the airframe 12 and means 7, 9, 11 for attaching said spars 8 to the internal airframe structure 10, the cited means 7, 9, 11 being dampers, shock absorbers or active actuators with characteristics chosen so that the said means 7, 9, 11 are particularly suited for the efficient reduction of attachment and internal dynamic loads arising mainly but not only from hard landing events and aircraft flight manoeuvres, and for damping sustained vibrations of the propulsive system-airframe 12 assembly, the said arrangement allowing the easy removal of the strut 4 from the rest of the said airframe 12 and the interchangeability of the said strut 4 between different aircrafts, being also the cited arrangement tolerant to damage or complete failure of at least one of the said spars 8.