Abstract: An air vehicle having a bilaterally asymmetric configuration may include a body having a longitudinal axis. The air vehicle may further include longitudinally offset engine nacelles, asymmetrically lengthened engine nacelles, and/or longitudinally offset protruding aerodynamic surfaces.

Abstract: An aircraft propulsion system is disclosed herein. The aircraft propulsion system includes a core engine having an intake, a compressor section, a combustor section, and a turbine section arranged along a centerline axis. The aircraft propulsion system also includes a nacelle surrounding the core engine. The aircraft propulsion system also includes at least one free power turbine driven to rotate by exhaust gases exiting the turbine section. The aircraft propulsion system also includes at least one rotor module driven to rotate by at least one free power turbine. The aircraft propulsion system also includes first and second pylons extending away from the nacelle and operable to mount the core engine to an aircraft. The first and second pylons are spaced from one another on opposite sides of at least one plane containing the centerline axis and mirror one another across the at least one plane.

Abstract: A propulsion engine comprises a compressor, a combustor and a turbine arranged in flow series about a turbine axis. A shaft is coupled to the turbine along the turbine axis, and first and second propulsions fans are rotationally coupled to the turbine at opposite ends of the shaft. The first and second propulsion fans rotate substantially parallel to one another, and transversely with respect to the turbine axis.

Abstract: An aircraft having propulsion units for both conventional aircraft flight in the atmosphere and for high-altitude operation as a rocket. The aircraft is divided into a payload compartment and a compartment containing rocket propulsion unit propellant or fuel, and includes a long transverse wing with a small back-sweep to favor lift in the dense layers of the atmosphere and to thus make it possible to climb to high altitudes at a subsonic speed before using the rocket propulsion units. The return flight portion is performed by gliding or controlled as for a conventional aircraft.

Abstract: A ducted ram air turbine may be used to drive a generator to provide power to an aircraft. The ducted ram air turbine may be used in a pod attached to the aircraft, where the pod is fully powered, cooled and lubricated by devices attached to the ram air turbine. A gearbox may be deployed to control the speed of the turbine for driving various pumps and the like. The speed of the turbine may be controlled by inlet and exit actuators driving inlet and exit doors.

Abstract: Aircraft fuselage section (32) subjected to impacts of external bodies, the aircraft fuselage having a curved shape with at least a vertical symmetry plane (A-A) and a central longitudinal axis and comprising a skin (35) and a plurality of frames (37) arranged perpendicularly to said longitudinal axis (33), the aircraft fuselage section also comprising at least an inner reticular structure (51, 53) mounted on a supporting structure (41, 43) comprising longitudinal beams (39) attached to the skin (35) and interconnected with said frames (37), said inner reticular structure (51, 53) being arranged for creating at least one closed cell (75) with the skin (35) for improving its resistance and its damage tolerance to said impacts. Said inner reticular structure (51, 53) can be formed by panels (61), rods (65, 65?), cables (67, 67?) or belts (69, 69?).

Abstract: An airplane, including a fuselage having an elongate shape along a longitudinal axis of the airplane, and at least one wing attached to the fuselage between front and back ends of the fuselage and a substantially cylindrical central portion and a rear scaleable portion on which a vertical tail assembly and a rear propulsion assembly are attached. Between a section for connecting the rear portion to the central portion of the fuselage and the back end: the maximum width of each fuselage section is constant or increases towards the rear up to a maximum fuselage width L; the height of each fuselage section decreases towards the rear, such that the back end of the fuselage forms a thin trailing edge substantially horizontal in the indicating line of the airplane and substantially rectilinear; a reactor for the propulsion assembly is provided in a so-called semi-buried configuration in the fuselage.

Abstract: An aircraft configuration that may reduce the level of roaring jet exhaust noise, infrared radiation, sonic boom, or combination thereof directed towards the ground from an aircraft in flight. The aircraft's nacelles are mounted to the aircraft higher than the wings, with substantially vertical stabilizers outboard of the outermost engine. Noise shifting means are provided such as, for each nacelle, primary chevrons at the core nozzle, secondary chevrons at the fan nozzle, a partial bypass mixer, a long duct full flow mixer, or a combination thereof to provide a shift in spectrum distribution of jet exhaust noise from lower to higher frequency. Variable geometry chevrons may be used with increased immersion to provide such a shift just during noise-restricted portions of an aircraft flight profile. The aircraft aerodynamic structural surfaces serve as noise shielding barriers that more effectively block or redirect the frequency shifted noise up and away from communities.

Abstract: Aircraft are provided with a pair of auxiliary power units (APUs) adjacently mounted in parallel relative to one another within the tail cone section of the aircraft's fuselage. In some embodiments, the APUs are mounted generally vertically adjacent to one another. Alternatively, the APUs may be mounted generally horizontally adjacent to one another. The aircraft fuselage may include a pair of downwardly and outwardly oriented strakes adjacent the tail cone having lower edges which establish a maximum take-off pitch angle of the fuselage and define a spatial zone therebetween. The APUs are positioned within such a spatial zone defined between the strakes so that the maximum take-off pitch angle is not required to be changed when modifying an existing single APU aircraft with dual APUs.

Abstract: A rotary-wing aircraft includes a retractable port movable between a closed position and an open position to selectively control flow of combustion gases into a bypass passage to change a power distribution between a rotor system and a secondary propulsion system.

Abstract: A nacelle configured to be coupled to an underside of a wing so as to form a clearance space therebetween includes at least a lip defining an inlet and a first cowling disposed aft of the lip. The first cowling has an outer surface with at least one concave region that is depressed relative to another region of the outer surface. In some aspects, the depressed region can be disposed on an inboard side of the wing, for example, on an upper surface of the first cowling facing a wing. The nacelle can include a second cowling disposed between the lip and the first cowling and the first cowling can translate in a longitudinal direction relative to the second cowling.

Abstract: An aircraft provided with turbojet engines of which the nacelles are partially embedded in the fuselage of the aircraft is disclosed. The aircraft includes an internal space at engine nacelles. The internal space includes a platform capable of supporting personnel and maintenance equipment, with the portions of the nacelles located inside the aircraft comprising trapdoors or devices for accessing inside the engines from the platform.

Abstract: Apparatus and methods provide for a swept-wing powered-lift aircraft. Aspects of the disclosure provide a powered-lift aircraft that utilizes the engine exhaust flow over upper surface blown flaps to increase lift during various flight operations. The powered-lift aircraft has wings with inboard portions and outboard portions. The adjacent inboard and outboard portions share a swept leading edge. The leading edge is swept to a degree that shifts the outboard portion rearward to a position in which the aircraft center of lift has little to no variance upon the activation or deactivation of a powered-lift system.

Abstract: An engine attachment pylon for an aircraft, including a rigid structure including a box formed by one or plural hollow segments. The section of at least one hollow segment is circular or elliptical in shape.

Abstract: Internal shield in the rear fuselage of an aircraft having a propulsion system formed by two engines mounted on each side of it; the rear fuselage having at least a vertical symmetry plane; the rear fuselage being made of a composite material; the internal shield being located in said vertical symmetry plane and extended in an area that covers the possible trajectories of a set of pre-defined fragments detached from one of said engines in a failure event that would impact on critical elements of the opposite engine; the internal shield having a flat shape and an energy absorption capability that allows stopping said fragments. The invention also refers to a method for determining the area of an internal shield and to an aircraft having said internal shield.

Abstract: A rear part of an aircraft including two connecting rods positioned symmetrically on either side of a median vertical plane, wherein each connecting rod has an end mounted on a support structure of the engines and another end mounted on the fuselage, wherein this part is configured to allow, by rotation of the connecting rods around their axes of rotation, an oscillating movement of limited amplitude of the assembly formed by the support structure and the engines, relative to the fuselage, through the first and second fuselage openings.

Abstract: An aft-loading aircraft with a twin T-tail assembly is provided. In one example embodiment, the aft-loading aircraft includes a fuselage portion having an aft opening with a cargo door, a first and second vertical stabilizer attached to the fuselage portion, and, a horizontal stabilizer transversely attached to the first and second vertical stabilizers.

Abstract: An amphibious large aircraft without traditional airstairs is disclosed. With its flat and oblong fuselage, said amphibious large aircraft has wing-in-ground effect in addition to generating elevating force in flight. Thus, said amphibious large aircraft has smooth takeoff and touchdown on the runway as well as on broad water area. The flight efficiency is increased by 30-40%. The fuselage has only one floor, wherein the passenger cabin is set in the front of the fuselage, and the cargo hold is mounted above the rear. The wings are extended towards two sides from upper side of the fuselage. A jet engine is mounted above the rear of the fuselage and adjacent to the tail wing. Passengers can go on and off the amphibious large aircraft directly without the need of airstairs and can escape from the aircraft directly without the need of an inflator slide during an emergency.

Abstract: An assembly for an aircraft gas turbine propulsion engine includes an engine nacelle and a thrust reverser. The engine nacelle is configured to have at least a portion of an aircraft gas turbine propulsion engine mounted therein, and includes an intake end, an exhaust end, and an outer surface that extends between the intake end and the exhaust end. At least the engine nacelle outer surface proximate the exhaust end has a semicircular section and a noncircular section. The thrust reverser includes a forward end, an aft end, and an outer surface that extends between the forward and aft ends. The thrust reverser forward end is coupled to the engine nacelle exhaust end. At least the thrust reverser outer surface proximate the forward end has an arc section and a noncircular section. The arc section subtends an angle greater than ? radians.

Abstract: An aircraft engine attachment pylon including a rigid structure forming a caisson, and a rear engine attachment including an attachment body and at least one lateral fitting arranged on either side of the caisson. Each fitting includes a first portion pierced by first assembly holes enabling it to be fixed to the caisson, and a second portion defining a fixing surface of the body. The second portion includes a housing orifice receiving a self-locking nut cooperating with a screw supported against the body and, in transversal section, an axis of the screw passes through the first holes.

Abstract: An aircraft propulsion unit includes a gas-turbine core engine 10 having at least one compressor, one combustion chamber and one turbine driving a main shaft 11. The main shaft 11 of the gas-turbine core engine 10 is operationally connected to at least two separate fans 6-9 via a mechanical drive connection, each of them being arranged beside the gas-turbine core engine 10.

Abstract: Apparatus and methods provide for a swept-wing powered-lift aircraft. Aspects of the disclosure provide a powered-lift aircraft that utilizes the engine exhaust flow over upper surface blown flaps to increase lift during various flight operations. The powered-lift aircraft has wings with inboard portions and outboard portions. The adjacent inboard and outboard portions share a swept leading edge. The leading edge is swept to a degree that shifts the outboard portion rearward to a position in which the aircraft center of lift has little to no variance upon the activation or deactivation of a powered-lift system.

Abstract: A propulsion engine comprises a compressor, a combustor and a turbine arranged in flow series about a turbine axis. A shaft is coupled to the turbine along the turbine axis, and first and second propulsions fans are rotationally coupled to the turbine at opposite ends of the shaft. The first and second propulsion fans rotate substantially parallel to one another, and transversely with respect to the turbine axis.

Abstract: An arrangement for an aircraft includes a fuselage, a wing, and a propulsor. The wing may have a wing upper surface, a rear spar and a wing trailing edge. The propulsor may include at least one rotor having a rotor diameter and a rotor axis. The propulsor may be mounted such that the rotor is located longitudinally between the rear spar and the wing trailing edge. The propulsor may also be mounted such that a lowest point of the rotor diameter is located vertically above the wing upper surface.

Abstract: An aircraft, comprising an internal combustion engine by whose drive power a propeller can be driven, wherein the internal combustion engine cooperates with an electric machine which in a first operating mode is operable as electric motor and in a second operating mode as electric generator.

Abstract: According to the invention, the engine pylon for the suspension of a turbo engine under an aircraft wing is such that the trailing edge of the rear lower part of the engine pylon is shifted toward the root of the wing.

Abstract: A mounting structure for an aircraft engine including a rigid structure and a mechanism to mount the engine on the rigid structure. The mounting mechanism includes a thrust load device including two side thrust links each including an aft end mounted on an evener bar of the device, via a mechanical connection. Each connection is formed by a lug provided on the evener bar and passing through an orifice made in the aft end, the lug being arranged so as to extend substantially laterally relative to the mounting structure.

Abstract: An aircraft having a propeller engine mounted at the rear of the aircraft, on the back thereof, such that the axis of the engine is parallel to the longitudinal axis of the aircraft. The aircraft has a cell, the rear part of which comprises a horizontal empennage and two vertical empennages, positioned one at each end of said horizontal empennage. The propeller is positioned vertically in line with the rear part of the cell, and the rear part of the cell forms a lateral and downward barrier, on each side of a plane of the propeller, that screens an acoustic intensity equal to approximately?5 dB with respect to a maximum acoustic intensity emitted by the engine.

Abstract: Systems, method, devices and apparatus are provided for reducing drag and increasing the flight efficiency characteristics of aircraft and airships including hybrid aircraft utilizing distributed boundary layer control and propulsion devices. Boundary layer control includes passive systems such as riblet films and boundary layer propulsion devices having a divided and distributed propulsion system disposed in the curved aft sections of aircraft and airships including hybrid aircraft susceptible to boundary layer drag due to degree of curvatures, speed and density of the surrounding air. Distributed propulsion devices include constructing propellers and riblets from shape memory alloys, piezoelectric materials and electroactive polymer (EAP) materials to change the shape and length of the distributed propulsion device.

Abstract: An aircraft propeller-engine layout includes at least one engine (10) arranged in a tail (2) of a fuselage (1) of an aircraft and has at least one propeller arrangement, with a shaft of the propeller (6, 7) being connected to a shaft (21) of the engine (10) via at least one transfer shaft (12).

Abstract: Sail wing aircraft which includes a wing (6) and at least one propulsion engine (8). It includes an upper beam (22) which is firmly fixed at its front end to a first frame (12) located on an air inlet (14) of the propulsion engine and which is in addition firmly fixed at its median part to a second frame (16) located to the rear of the first frame. The sail wing aircraft includes in addition a pylon (26) for attachment of the engine onto the fuselage, where the engine is fixed to the pylon (26).

Abstract: An aircraft capable of vertical take-off and landing is provided. The aircraft includes a fuselage having a forward portion and an aft portion. A lift fan extends though a duct, which extends through the fuselage. The aircraft further includes a pair of wing sets where each set of wings include first and second wings. Each set of wings has a first wing with a first wing root interconnected to the fuselage forward of a central axis of the lift fan and a second wing having a second wing root interconnected to the fuselage aft of the central axis of the lift fan. The tips of each set of wings are connected. The aircraft further includes a pusher fan.

Abstract: A full time lean air fuel mixture running spark ignited air cooled aircraft piston engine. In one embodiment, a drop-in substitution is provided for an equivalent make, model, and engine size, wherein the new, rebuilt, or reconfigured engine provides as much or more horsepower when compared to the original engine, but runs at a lean air fuel ratio condition during normal operating modes, including takeoff, climb, and cruise, thus saving significantly on fuel. In yet another embodiment, a drop-in substitution having a somewhat larger cylinder displacement volume may be provided to attain equivalent or enhanced maximum horsepower while operating at lean air fuel ratios. Enhanced engine life may be anticipated, since cylinder head temperatures (CHTs) may be reduced, compared to engines using rich air fuel ratios for climb and cruise conditions. Aircraft using such engines are also disclosed.

Abstract: An aircraft having reduced environmental impact includes at least one engine with at least one propeller carried, at the rear, on the top of the aircraft with the propeller(s) located in vertical alignment with the rear part of a noise barrier cell and the rear face of a burst zone situated forward of the central part of an empennage box.

Abstract: A system for attaching an engine to the structure of an aircraft, such as a sail wing aircraft is disclosed. The system includes an upper beam which is firmly fixed at its front end to a first frame mounted on the aircraft structure, and firmly fixed at its median part to a second frame located to the rear of the first frame. The engine is hooked beneath the upper beam. The system is orientated in relation to a longitudinal axis X, a transverse axis Y and a vertical axis Z. Two front engine attachment points are arranged symmetrically on either side of the vertical median plane of the engine. The front attachment points include a shaft which is inclined relative to the Y-direction and to the Z-direction so that they bear the forces along the longitudinal direction and forces which are inclined relative to the Z-direction and Y-direction.

Abstract: An aircraft having a lambda-box wing configuration includes, a fuselage, a propulsion system, a first pair of swept-back airfoils, connected to the top forward portion of the fuselage, a second pair of swept-forward airfoils, connected to the lower rear portion of the fuselage at a point of the said fuselage aft of the connection of the swept-back airfoils, and a third pair of substantially vertical airfoils, the tips of the swept-forward airfoils being connected to the lower side of the swept-back airfoils at an intermediate point of the span of the said swept-back airfoils, by the substantially vertical airfoils, the swept-back airfoils having a higher aspect ratio than that of the swept-forward airfoils, which makes the swept-back airfoils have a reduced induced drag without penalizing their weight.

Abstract: A communication system for supporting communications with a target market area. The system includes one or more solar-powered aircraft maintained in, or successively passing through, flight stations or flight patterns around the market area. Each of the aircraft targets limited beamwidth communication antennas on a substantial portion of the target market area. The control system is configured to fly selective flight patterns depending on the aircraft characteristics and the flight conditions. The flight patterns may emphasize high-power-generation patterns such as flying away from the sun for aircraft with wing-mounted solar cells.

Abstract: An aircraft including a longitudinal fuselage, at least two lateral wings connected symmetrically one on each side of the fuselage and at least one engine pod fixed to each lateral wing via an engine support pylon. At least one profiled bearing rod is positioned on each of the engine support pylons so as to generate a propulsive resultant force under action of an oblique air flow.

Abstract: The disclosed embodiments relates to a jet engine for an aircraft, characterized in that it bears at least one stabilizer, the stabilizer being fastened on the rigid structure of said jet engine so as to form a one-piece assembly. The jet engine can also bear one or more auxiliary devices required for the operation of the jet engine. The disclosed embodiments also relates to an aircraft provided with such a jet engine, and to a method of mounting such a jet engine on an aircraft.

Abstract: An aircraft, the propulsive units of which include engines, and which is distinguished by reduced noise emissions, includes a wing structure fixed to an upper region of the fuselage, and a vertical tail system having at least two vertical stabilizers which are generally vertically fixed to the fuselage aftwardly of the wing structure. The engines are disposed side by side in a propulsive package disposed above the fuselage, which propulsive package includes the following: air inlet openings for the propulsive package, which openings are disposed above the fuselage between a point at the leading edge and a point at the trailing edge of an aerodynamic root chord of the wing structure; and exhaust nozzle conduit outlets associated with exhaust nozzle conduits, which outlets are formed by the structure (cowling structure) of the propulsive package, and are disposed above the fuselage forwardly of an aft terminus of the fuselage and between the vertical stabilizers.

Abstract: When an aircraft is propelled by at least one jet engine fixed in a rear part of the aircraft, at least one substantially horizontal rear aerodynamic surface, the rear horizontal surface, is arranged at the rear of the aircraft and at least one jet engine is fixed under the rear horizontal surface by an attachment mast fixed by its upper part to the rear horizontal surface and maintains, by its lower part, the jet engine. The rear horizontal surface is also the horizontal tail unit of the aircraft or a horizontal surface maintained above the fuselage. The rear surfaces and the fuselage are arranged such that the engines are installed and removed using a vertical movement of the engines, which are advantageously one, two or three in number, in the rear zone of the aircraft.

Abstract: An aircraft includes a rear vertical tail unit having two tail fins forming, with the rear part of a fuselage, a channel on the back of the fuselage. A turbine engine is arranged on the back of the fuselage so that gas streams generated by the turbine engine penetrate into the channel. The main landing gear of the aircraft is arranged integrally beneath the fuselage. The wings of the aircraft have a slight sweep angle and a large fineness ratio.

Abstract: The Longitudinal Flying Wing aircraft idea provides for design of large cargo and passenger aircraft in range from low to high subsonic and transonic speed. Such aircraft would have up to twice lower fuel consumption per unit of payload, higher lift capacity, and a significantly longer range, while having a significantly lower level of noise inside passenger cabin and cockpit relative to classical concept aircraft. This idea is further providing for efficient, reliable, and simple flight controls, hence it may be successfully applied for design of all-size, long range, high-lift-capacity unmanned aircraft throughout the entire range of subsonic speeds.

Abstract: A large-capacity airplane principally includes a fuselage which has no region of constant width between the front and the rear and a wing fixed to the fuselage. As a preference, the engines are fixed at the rear under a horizontal tail held above the fuselage by vertical stabilizers and maintenance wells are formed in the fuselage in vertical alignment with each engine to allow the engines to be fitted and removed using conventional means. The width of the fuselage is determined, on the one hand, so that the airplane landing gear is fixed to the fuselage and in the up position is included within the interior volume of the fuselage and, on the other hand, so that the rear engines are above the fuselage in order to make use of the beneficial effects of this position.

Abstract: An aircraft configuration that may reduce the level of noise, infrared radiation, sonic boom, or combination thereof directed towards the ground from an aircraft in flight. In accordance with an embodiment of the present invention, an aircraft includes a tubular fuselage, two delta wings, at least one engine mounted to the aircraft and higher than the wings, and vertical stabilizers mounted on each wing outboard of the outermost engine. Each wing may include a wing strake at the leading edge of the wing and extending to the fuselage and an aft deck. The leading edge of the wing may extend forward of the intake of the engine, and the trailing edge of the aft deck may extend aft of the engine exhaust. The aft deck may include an upwardly rotatable pitch control surface at the trailing edge of the deck.

Abstract: An aircraft includes a fuselage and at least one engine provided with at least one propeller and mounted at a rear part of the fuselage, on the back thereof, with the at least one engine having an axis substantially parallel to the longitudinal axis of the fuselage, where the at least one engine is mounted on the rear part of the fuselage so that the propeller lies forward of the tails, and provided at the rear part of the fuselage, symmetrically with respect to the fuselage, are removable noise masking surfaces configured to occupy either a deployed position in which the removable noise masking surfaces project laterally with respect to the rear part of the fuselage and are positioned plumb with the propeller, or a retracted position in which the removable noise masking surfaces are incorporated into the rear part of the fuselage.

Abstract: An aircraft wing arrangement including a wing and at least one strut for attaching the aircraft engine suspended under the wing and including a front zone situated projecting towards the front with respect to a leading edge of the wing. The front zone includes a lateral projection delimiting a lateral air flow channel while being projected towards a proximal end of the wing.

Abstract: A small unmanned airplane includes; a main wing having a camber airfoil whose under surface is approximately flat, narrowing in the shape of taper to a blade tip, leading edge of which holds sweepback angle, of flying wing type which has an aerodynamic surface of tailless wing type and is low aspect ratio; movable flaps extending approximately extreme breadth in trailing edge part of both left and right sides of the main wing, having a dihedral angle at least in level flight; vertical stabilizers placed at blade tips of left and right of the main wing; and two propellers installed on the top surface of the main wing. This can materialize miniaturization and weight saving of a small unmanned airplane for individual carrying capability and for suitability for such as lift-off by hand throw.

Abstract: Thrust systems for passenger aircraft provide at least one flight engine and a taxi engine wherein all flight engines together provide, in total, a takeoff thrust arranged in a takeoff thrust direction and the taxi engine provides a taxi thrust which does not exceed 15% of the takeoff thrust and is directed substantially the same as the takeoff thrust direction. The taxi thrust is thereby sufficient to taxi the aircraft along a taxi path. In a system embodiment, the taxi thrust does not exceed 7.5% of the flight thrust. In another system embodiment, the flight engines have, in total, a flight engine weight and the taxi engine has a taxi engine weight that does not exceed 10% of the flight engine weight. In a system embodiment, the taxi engine weight does not exceed 7.0% of the flight engine weight. In another system embodiment, the taxi engine has a rated thrust and is configured so that the taxi thrust is within 40% and 100% of the rated thrust.

Abstract: An aircraft engine assembly including an engine, an engine suspension pylon, and a heat exchanger system including an outlet located between the box and the engine, aft from the aft engine suspension. Furthermore, the outlet of the heat exchanger system is provided on an outlet pipe connected to the exchanger and passing through a structural block fixed on a box, between the box and the engine.