Abstract: An aircraft engine assembly including an annular structure surrounding a central casing and mechanically connected to the central casing by the intermediary of a mounting mechanism. To each of the first and second engine mounts is associated a reinforcing structure forming a shear plane, fixedly connected: in an area of the annular structure at a first anchoring point; in an area of the fan casing at a second anchoring point; and in an area of a structural arm or of the intermediate casing at a third anchoring point. The structure extends along a radial imaginary plane passing through an anchoring point of the mount on the fan casing.

Abstract: A mount yoke assembly comprises a first main hanger bracket and a first anchor bracket. The first main hanger bracket includes a first receiving portion for a first auxiliary power unit (APU) mount with first and second hanger arms. The first hanger arm includes a first hanger flange extending proximate a distal end of the first hanger arm. The first anchor bracket includes a first plurality of anchor holes and a first anchor flange. The first plurality of anchor holes are disposed substantially along a length of the first anchor bracket for securing the mount yoke assembly to a component of an APU assembly. The first anchor flange extends from the first anchor bracket for hingeably securing the first anchor bracket to the first main hanger bracket.

Abstract: Methods and apparatus are provided for an actively variable shock absorbing system for actively controlling the load response characteristics of a shock absorbing strut. In one embodiment the shock absorbing system comprises a controllable valve adapted for actively varying a load response characteristic of the shock absorbing strut. The shock absorbing system further comprises an electronic control system comprising an input for receiving a signal from a sensor, an algorithm adapted to determine an optimal position for the controllable valve in view of the sensor signal, and an output for sending a control signal to the controllable valve to place the valve in the optimal position.

Abstract: The aircraft exhaust engine nozzle system includes a fan nozzle to receive a fan flow from a fan disposed adjacent to an engine disposed above an airframe surface of the aircraft, a core nozzle disposed within the fan nozzle and receiving an engine core flow, and a pylon structure connected to the core nozzle and structurally attached with the airframe surface to secure the engine to the aircraft.

Abstract: An assembly includes a unitary nacelle structure and an integrated fan housing for a gas turbine engine assembly. The unitary nacelle structure includes an inlet region and a fan cowl region, and is configured to at least partially circumscribe the integrated fan housing. The integrated fan housing comprises an integral composite structure and includes a fan case sized and configured for encircling a fan blade assembly of an associated gas turbine engine, a fan hub, and a plurality of fan outlet guide vanes. The unitary nacelle structure cooperates with the integrated fan housing to transfer static and dynamic loads directly to a support structure, rather than through the engine core, to minimize backbone bending.

Abstract: An inner cowl structure for circumscribing at least a portion of a jet engine extending from an aircraft includes an apron configured to mount directly to the engine independent of the pylon and overly an upper portion of the jet engine, and an inner body configured to circumscribe a portion of the jet engine not circumscribed by the apron.

Abstract: The rotors of a helicopter are powered by electric motors. The electrical energy required for this purpose is produced by a motor-generator unit, which comprises one or more internal combustion engines. The motor-generator unit can be secured under the cabin floor. This yields a hybrid helicopter that can set the rotational frequency of the rotors within a large interval.

Abstract: A nacelle assembly for a high-bypass gas turbine engine includes a fan nacelle that includes a first fan nacelle section and a second fan nacelle section, the second fan nacelle section movable relative to the first fan nacelle section. A cascade array is mounted to the first fan nacelle section for movement relative thereto between a stored position and a deployed position, the stored position locates the cascade array at least partially within the first fan nacelle section.

Abstract: A bracket has an axial rear wall to be secured to a housing for a ram air fan and a base floor defined between lateral sidewalls. The base floor has a slot extending for an axial length and for a lateral width, with a ratio of the length to the width being between 1.24 and 1.29. A ran air fan, a system and a method are also disclosed.

Abstract: An engine assembly for an aircraft, including a rigid structure including a box rib extension protruding from a box of the structure, in a line of separation, towards a fuselage of the aircraft. The extension supports a first attachment in a position separating it from a second attachment in the line of separation. The first and second attachments enable the moment being exerted in a lengthways direction of the turbine engine to be transmitted jointly.

Abstract: An auxiliary power unit is composed of a gas turbine engine, a gearbox, and a gearbox driven generator. A mount bracket is mechanically attached to the gearbox. The bracket is for connecting to an aircraft strut system. The aircraft strut system connects to the aircraft structure. The mount bracket has an upper mechanical attachment point and a lower mechanical attachment point to the gearbox. The gearbox includes an oil reservoir, and the lower attachment point is beneath the oil level within the oil reservoir such that said lower attachment point will be cooled by oil in the oil reservoir.

Abstract: An aircraft control structure can be utilized for purposes of drag management, noise control, or aircraft flight maneuvering. The control structure includes a high pressure engine nozzle, such as a bypass nozzle or a core nozzle of a turbofan engine. The nozzle exhausts a high pressure fluid stream, which can be swirled using a deployable swirl vane architecture. The control structure also includes a variable geometry pylon configured to be coupled between the nozzle and the aircraft. The variable geometry pylon has a moveable pylon section that can be deployed into a deflected state to maintain or alter a swirling fluid stream (when the swirl vane architecture is deployed) for drag management purposes, or to assist in the performance of aircraft flight maneuvers.

Abstract: An intermediate casing for a gas-turbine engine has an outer ring (3), an inner ring (1) and an intermediate ring (2) mutually supported by mutually aligned outer and inner supporting struts (4, 5). A radial drive shaft (6), positioned through inner and outer supporting struts (4.1, 5.1) aligned at a 6-o? clock position, connects to an auxiliary gear drive (7). Four additional outer supporting struts (5.2, 5.3, 5.4, 5.5) are spaced apart 72°. A mounting bracket connects to the outer ring at a side facing an aircraft fuselage in areas of two of the additional outer supporting struts. The arrangement of supporting struts and type of mounting bracket attachment, saves weight, improves flow in the bypass duct and increase maintenance and installation access at the bottom side of the engine to nearly 144°.

Abstract: A shear pin connection for use in a difficult to access location has a bolt head to be positioned at an inner end of a bearing. A bushing is received between the bolt and an inner periphery of the bearing. A lock member is positioned between an inner end of the bushing and the bolt head. The lock member is radially expandable, and has a free radially outer dimension that is smaller than an inner dimension of the inner bore. The lock member is expandable to have an expanded radially outer dimension that is greater than the inner dimension of the inner bore. A nut is tightened on the outer end of the bolt. The nut causes the bushing to move relative to the bolt, and causes the lock member to expand radially. A shackle connection for a gas turbine engine and an aircraft are also disclosed.

Abstract: An aircraft propulsion system including a bypass turbojet engine surrounded by a nacelle together with a mechanism attaching the engine to a pylon of an aircraft. The nacelle includes an inner structure forming a body of revolution including a rigid framework formed by an upstream annular frame fastened to an intermediate casing of the engine, a downstream annular frame supporting the exhaust casing of the engine, and longitudinal arms connecting the frames together, the annular downstream frame being fastened to the pylon by a flexible or hinged suspension mechanism.

Abstract: This invention relates to an aft pylon fairing for the suspension system of an aircraft engine, comprising a main structure extending along a longitudinal direction of said fairing and integrating two side panels connected to each other, the fairing also comprising a heat protection deck mounted on said main structure through connection means comprising tabs designed to deform to accompany displacement of the deck relative to the main structure, if there is differential thermal expansion between these two entities.

Abstract: An assembly is designed to attach hangers from which an aircraft propulsion unit is suspended. The propulsion unit is intended to be suspended from a structural element of the aircraft. The propulsion unit includes a turbojet engine having a longitudinal axis and the attachment assembly having a clevis mount for attaching the hangers to a casing of the propulsion unit. The clevis mount is fixed to the casing by means designed to form a connection between the clevis mount and the casing at the external periphery of the casing.

Abstract: An actuating device is provided for a locking system which locks one of half-shells of a jet engine nacelle with respect to the other half-shell. The actuating device includes a fixed body in which an actuating rod is translationally and rotationally mounted with respect to the rod's longitudinal axis, and the fixed body has a track cooperating with a follower projecting from the actuating rod. In particular, the actuating rod includes a first end equipped with a handle and a second end connected to the locking system. The track has a middle part running parallel to the longitudinal axis, a first end part and a second end part formed on each side of the middle part, each of the end parts running perpendicular to the longitudinal axis.

Abstract: A pylon mounting system with vibration isolation is provided. The system generally includes a housing that defines a first fluid chamber and a second fluid chamber, a fluid disposed within the fluid chambers; a piston assembly at least partially disposed within the housing, and a tuning passage defined by the piston assembly for providing fluid communication between the fluid chambers. The piston assembly has a first arm and a second arm, and each arm has a tubeform bearing for providing pitch and roll stiffness.

Abstract: This strut (9), designed to support an aircraft turbojet engine, has, on the one hand, a connecting part (11) for connection between the casing (1) of the fan (3) or the casing of the gas generator (5) of the said turbojet engine and a wing of the said aircraft and, on the other hand, a Y-shaped box-section part (19), secured to the said connecting part (11) and designed to form the upper part of the inner fixed structure of the said nacelle.

Abstract: A fuselage mounted gas turbine engine installation the installation includes at least one propeller stage and a gas turbine core arranged in use to drive the propeller stage. The core is external to the fuselage and the rotational axes of the core and propeller stage are offset with respect to each other.

Abstract: A turboshaft engine supporting pylon covered with a porous material and a turboshaft engine/pylon assembly. The pylon supports a turboshaft engine on an aircraft, and includes an outer surface covered at least partially with a porous material to reduce amplitude of acoustic waves leaving the turboshaft engine. The assembly includes a turboshaft engine and a pylon, in which the pylon extends longitudinally from upstream to downstream and includes an upper part for securing to the aircraft, a lower part for securing to the turboshaft engine, and an absorption part extending in an exhaust stream from the turboshaft engine and including an internal absorption part extending inside the turboshaft engine and an external absorption part extending downstream of the turboshaft engine. The outer surface of the upstream end of the external absorption part of the pylon is covered with a porous material to limit noise formation downstream of the engine.

Abstract: An aircraft propulsion system (110) comprising a bypass turbojet engine surrounded by a nacelle defining a flow passage for the secondary stream flows, and connection means for connecting the engine to a wing (132) of an aircraft and comprising a pylon (134) substantially parallel to the longitudinal axis (135) of the engine together with suspension means suspending the engine from the pylon, the pylon being angularly offset from a vertical plane (150) containing the longitudinal axis of the engine and from the top of the nacelle, and being situated outside the flow path for the secondary stream.

Abstract: The invention relates to a turbojet engine nacelle (1) comprising: an outer structure including an annular lip defining an air inlet and a cowl (9) extending as a continuation of the annular lip, and an inner fixed structure (19) extending as a continuation of the air inlet and including a region equipped with at least one piece of equipment requiring maintenance or monitoring. The aforementioned outer structure can move in relation to the inner structure between an operating position in which the cowl (9) covers the region equipped with the equipment and a maintenance position in which the cowl (9) reveals said region so as to allow access to the equipment from outside.

Abstract: An aerodynamic aft fairing of an engine pylon ensuring the mounting of an engine underneath a wing of an aircraft is provided. The aerodynamic aft fairing includes an outer lateral panel and an inner lateral panel assembled together at least by a bottom panel, the bottom panel comprising, on either side of the lateral panels, an extension forming an aerothermic barrier capable of channeling hot air flows leaving the engine. The inner lateral panel and the outer lateral panel are attached to the bottom panel by a first angle bar and a second angle bar, respectively.

Abstract: One embodiment of the present invention is a unique aircraft. Another embodiment is a unique external pod for an aircraft. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aircraft and external pods for aircraft. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: A pylon for attaching a turbine engine of an aircraft having a rigid structure including protruding fittings each having a first orifice and a plurality of ties to attach the pylon onto a wing of the aircraft, the plurality of ties comprising two side front ties to take the thrust forces, the two side front being secured to the first orifices of the protruding fittings to attach the rigid structure firmly to the wing. The plurality of ties further comprises a center front tie positioned between the two side front ties, the center front tie including a ball joint to take forces in a lateral direction of the rigid structure.

Abstract: A lower hull 403 and an upper hull 402 may form a multi rotor aircraft fuselage system comprising a comprising a thermoformed thin shell monocoque fuselage 500, center console assembly 200, the center console assembly comprising a center console cover 210, an auto pilot housing cover 220 and an auto pilot housing 225. A center fuselage area 300 contains the center console assembly 200. The center fuselage area is part of a plurality of arm assemblies 400. Each arm assembly may comprise a distal end 440 and a proximal end 410, an access panel cover 420 which may expose a access panel opening 419. An access panel opening 419 may lead to an arm void area 430, with the arm void area 430 further defined by the interior sections of the thin shell fuselage 500.

Abstract: A jet engine nacelle includes an air intake section, a middle section, and an aft section. The aft section is formed from two half-shells rotatably mounted such that they can each be deployed between a working position and a maintenance position under the action of a jack and a telescopic connecting rod each respectively having a first end fastened on the jet engine and a second end fastened in the corresponding half-shell. In particular, the nacelle includes at least one damping member arranged between each telescopic connecting rod and the corresponding half-shell, and the damping member is designed so as to be in a prestressed state when the corresponding half-shell is in the working position and can reduce vibration in the half-shell.

Abstract: A device for mounting an aircraft engine, including a rigid structure, an engine attachment including a connecting plate superposed to an associated connecting plate of said rigid structure, and means for mutually tightening said plates comprising at least one wedge-effect tightening block and corresponding bearing surfaces of said plates which are conformed so that, when each tightening block is applied against said bearing surfaces along a direction parallel to the plane of the contact surface between both of these plates, this block exerts by a wedge-effect a force for tightening these plates against each other along a direction perpendicular to said plane.

Abstract: An aircraft engine pylon aft aerodynamic fairing includes upper spars, transverse stiffening ribs, lower spars and a trailing edge where the upper spars and lower spars join together. In this fairing, a profiled structure is formed according to a profile open to the outside of the fairing. In a first end portion, the profiled structure comes to be enclosed between an end portion of the lower spars and the ends of at least one transverse stiffening ribs flush with the lower spars. This structure extends between the lower spars and the upper spars over a straight central portion inclined relative to the first end portion, and comes in a second end portion flush against a portion of the upper spars, parallel to the first end.

Abstract: An aircraft propulsion assembly includes a turbojet engine, a support providing a transfer of force torque to an aircraft from a suspension assembly, and the suspension assembly interposed between the support and the turbojet engine. The suspension assembly includes a device for absorbing thrust forces, an upstream suspension fasteners mounted on a fan housing and an intermediate housing of the turbojet engine. In particular, the suspension assemble further includes a main upstream suspension fastener to absorb a moment (Mx) along an axis (X) of the turbojet engine and forces (Fy and Fz) in a plane perpendicular to the axis (X), and a pair of additional upstream suspension fasteners separate from the main upstream suspension fastener to absorb a moment (Mz) along an axis (Z) and a moment (My) along an axis (Y) and forces (Fx) along the axis (X).

Abstract: An aircraft propulsion assembly includes a support providing a transfer of a force torque to an aircraft from a suspension assembly which is interposed between the support and a turbojet engine. The suspension assembly is mounted on an intermediate housing, a main housing or a fan housing, and on the support. In particular, the suspension assembly includes following suspension fasteners: —a first suspension fastener having a device for absorbing thrust forces and forces “Fz” along an axis “Z”, —a second suspension fastener to absorb, with the first suspension fastener, a moment “Mx” around an axis “X” and forces “Fy” along an axis “Y”, —a third suspension fastener to absorb, with the first suspension fastener, a moment “My” along the axis “Y” and forces “Fx” along an axis “X”. A moment “Mz” along the axis “Z” is absorbed by one of the suspension fasteners.

Abstract: A vibration isolator includes an upper housing and a lower housing; an upper reservoir housing defining a upper fluid chamber; a lower reservoir housing defining a lower fluid chamber; a piston spindle resiliently coupled to the upper housing with an upper elastomer member, the piston spindle being resiliently coupled to the lower housing with a lower elastomer member; an elongated portion having a tuning passage; and a tuning fluid disposed there within. The vibration isolator cancels vibratory forces at an isolation frequency. The vibration isolator is utilized in a pylon system for mounting a transmission in an aircraft. The vibration isolator is located between a pylon structure and a roof structure. The isolator includes a spherical bearing assembly that is located near a waterline location of a rotational axis of a drive shaft.

Abstract: An aircraft assembly comprising a wing and an engine attachment pylon fixed to the wing by an attachment comprising a first and a second front wing system cleat connecting a rigid structure of the attachment pylon and a front longeron of the wing. The first front wing system cleat comprises a first shearing pin oriented in the transversal direction to ensure take-up of forces exerted in the longitudinal and vertical directions of the pylon, and the second front wing system cleat comprises a second shearing pin oriented in the longitudinal direction to ensure take-up of forces exerted in the transversal and vertical directions of the pylon.

Abstract: An aircraft engine attachment pylon including a box formed by an assembly of a first spar, a second spar, two lateral panels, and an aft engine attachment fitted with an aft attachment body. The engine attachment may be provided with two lateral fittings associated with the two lateral panels to which they are fixed to and project from laterally outside the box, each of the fittings forming a plane attachment interface with the attachment body through which bolts pass. Each attachment interface may be in the shape of a straight segment inclined at 45° from a vertical direction of the pylon.

Abstract: The invention proposes to protect a rear part of a floor of an aft fairing of a pylon of an aircraft bypass turbojet engine using a film of cool air formed of part of a bypass flow of the jet engine which is guided under the floor by two lateral wall portions of this fairing which have been profiled for this purpose. To do that, these two lateral wall portions delimit respective air passage spaces formed between a forward part of the floor and a jetpipe of the turbojet engine and which open laterally and towards the rear.

Abstract: Resilient aircraft engine mounts and mounting systems including the same are provided. A resilient aircraft engine mount comprises a base and a pair of opposed spiral springs in parallel forming a clevis with the base. A first spiral spring of the pair of opposed spiral springs has a first center opening extending therethrough. A second spiral spring of the pair of opposed spiral springs has a second center opening extending therethrough that is concentric with the first center opening for accepting a clevis pin. First and second spiral springs are each comprised of a rectangular cross section beam. The resilient aircraft engine mount is tunable in three translational axes to support three degrees of freedom vibration isolation. Two or more resilient aircraft engine mounts provide six degrees of freedom vibration isolation. Resilient aircraft engine mounts attach the aircraft engine to a pylon structure and help isolate vibratory forces.

Abstract: A gas turbine engine has a core engine incorporating a core engine turbine. A fan rotor is driven by a fan rotor turbine. The fan rotor turbine is in the path of gases downstream from the core engine turbine. A bypass door is moveable from a closed position at which the gases from the core engine turbine pass over the fan rotor turbine, and moveable to a bypass position at which the gases are directed away from the fan rotor turbine. An aircraft is also disclosed.

Abstract: A linking device including two hinge pins and having flexibility allowing vibrations between these two shafts to be filtered. The device includes a stack of plates connected to one another by layers of elastomer material. Plates of a first type are coupled to one of the shafts in relation to the movements parallel to the plates, while the plates of a second type are coupled to the other shaft in relation to the movements parallel to the plates, so as to allow relative movement of the shafts parallel to the plates. This linking device may be used in particular as a connecting rod, spreader beam or three-point shackle used in connecting a turbine engine to a pylon in a propulsion system of an aircraft such as an airplane.

Abstract: A boomerang link for aircraft engine mounts, including a first orifice and a second orifice both designed to connect the boomerang link to an aircraft pylon, and a third orifice designed to connect the boomerang link to an aircraft engine. The third orifice is offset relative to a plane passing simultaneously through an axis of the first orifice and through an axis of the second orifice. When the boomerang link is seen in section in any plane orthogonal to the axes, a straight line segment extending from the axis of the second orifice to an axis of the third orifice crosses a region external to the boomerang link. This conformation confers on the boomerang link a flexibility enabling it to filter transverse vibrations between an engine and an aircraft pylon.

Abstract: An engine mounting structure for aircraft including an engine mounting system including a device for transmission of the thrust efforts fitted with two lateral connecting rods and with a spreader beam mounted in connected fashion on a support element, through a principal connecting device defining a principal spreader beam hinge line positioned in a plane. The spreader beam is also mounted in connected fashion with some play on the element, using a secondary connecting device located at some distance, as seen from above, from the device, and defining a secondary spreader beam hinge line, which is also positioned in a plane. The rotation of the spreader beam is stopped by device coming into contact with the spreader beam.

Abstract: An assembly for connecting a first body to a second body includes a first element having a connection end to the first body and a first tubular portion, and a second element having a connection end to the second body and a second tubular portion extending along the longitudinal axis. The first tubular portion and the second tubular portion are interlocked by at least one complementary tubular portion nested in the first tubular portion and around the second tubular portion. A rigid piece connects the first body to the second body and is fastened to the first and second bodies. One of the first and second bodies is connected with functional play at one of the two attachment points of the rigid connecting piece, wherein the rigid connecting piece is formed of two flat rigid pieces extending on both sides of the first and second elements along the longitudinal axis.

Abstract: An engine pylon for attaching an engine to an aircraft, where the engine pylon includes a monolithic support structure having a body that includes multiple spaced bulkheads, multiple longerons connecting the bulkheads to define multiple bays and skins provided on the frame to at least partially enclose at least one of the multiple bays.

Abstract: A nacelle for a turban engine includes an air intake structure and a central structure. The central structure has a casing intended to surround a fan and an external structure. The air intake structure has at least one internal panel attached to the central structure via the casing and therewith forming a fixed structure and at least one longitudinal external panel attached removably to the fixed structure and incorporating an air intake lip. The external panel is moveable between an operating position and a maintenance position in which the external panel is separated from the external structure of the central section and the air intake lip is separated from the internal panel of the air intake structure.

Abstract: An aircraft pylon support system for mounting and supporting aircraft propulsion systems to a fuselage section of an aircraft that includes an internal, central support box disposed within and extending across the interior of an aircraft fuselage, and external support boxes extending laterally into pylons disposed at both sides of the aircraft, each of the internal and external support boxes being made of a composite material and structured as multi-spar boxes containing lateral spars and at least one central spar, wherein the central and lateral support boxes are connected together to provide a continuous interface therebetween with a full transfer of loads therebetween and between any interrupted, intermediate frame members.

Abstract: An airplane powered by exposed propeller engines has a swept wing configuration comprising a leading edge snag coincident with the exposed propeller engine mount. The portion of the leading edge disposed inboard of the exposed propeller engine is offset in an aftwise direction relative to the outboard portion of the leading edge. As a result of this construction, the point of closest approach of the blades of the exposed propeller engines is moved aft, allowing for a more compact engine installation.

Abstract: An aircraft engine attachment configured to be inserted between an engine and an EMS, the attachment including a plate assembly connected to a first fixing device including an end fitting with two arms and a pin passing through the plate assembly and the two arms, in each of which an orifice is formed including a first ring and a second ring respectively holding the pin. The first ring includes a bottom acting as a stop for a first end of the pin, and the first attachment device includes a mechanism to stop the pin in translation cooperating with a second end of the pin.

Abstract: The present invention relates, on the one hand, to a nacelle (1) for a double flow turboreactor (2) comprising a front air intake section (5), a median section (6) intended for surrounding a fan (3) of the turboreactor and a rear section (7), said rear section having an internal structure (7b) intended for serving as a housing to a rear portion of the turboreactor, characterized in that the internal structure possesses attachment means suitable for enabling the nacelle to be fastened to a pylon (12) intended to be connected to a fixed structure (13) of an aeroplane on at least one portion of said internal structure, and on the other hand, to a propellant assembly and to an aircraft provided with such a nacelle.

Abstract: Unmanned aerial device are disclosed herein which include a flight element comprising a central structural component configured to protect electronic circuitry, and structural beams, extending generally horizontally from opposing sides of the structural component, each beam being configured to contain electric wiring and a motor and to support a propeller. The device also includes a platform element, extending below the flight element, configured to support a video capturing device and a battery pack. In some implementations multiple vibration-dampening elements connect the flight element to the platform element to create a bi-deck vibration dampening system.