Abstract: A turbomachine exhaust casing extending about an axis including a hub extending about the axis; an external ferrule; arms which extend between the hub and the external ferrule, attachment yokes radially projecting toward the outside of the external ferrule; pockets hollowed into the external ferrule and wherein the yokes are arranged, the pockets extending in a hollow radially projecting toward the inside of the external ferrule; a ring portion which extends radially under the pockets and forms a duct wall by delimiting with the hub a portion of a gas flow duct.

Abstract: A gas turbine including a turbine driven by a combustion gas, a gas turbine casing that includes an exhaust casing having an inner tube and an outer tube, a bearing that rotatably supports a shaft of the turbine, a bearing casing that holds the bearing, a support leg that supports the gas turbine casing, struts that connect the inner tube and the outer tube, and a first support and a second support that support the bearing casing on the inner tube. The first support is located on a side same as the support leg relative to the struts in a flow direction of the combustion gas. The struts are located between the first support and the second support. The first support is fixed to the inner tube and the bearing casing. The second support is fixed to the inner tube and is in slidable contact with the bearing casing.

Abstract: A method for unmanned delivery of an item to a desired delivery location includes receiving, at an unmanned vehicle, first data representative of an approximate geographic location of the desired delivery location, receiving, at the unmanned vehicle, second data representative of a fiducial expected to be detectable at the desired delivery location, using the first data to operate the unmanned vehicle to travel to the approximate geographic location of the desired delivery location, upon arriving at the approximate geographic location of the desired delivery location, using the second data to operate the unmanned vehicle to detect the fiducial; and upon detecting the fiducial, using the fiducial to operate the unmanned vehicle to deliver the item.

Abstract: A vibration isolation system for a gas turbine engine. The vibration isolation system includes a first fixed structure and a second fixed structure separate from the first fixed structure. The vibration isolation system further includes a connector coupling the first fixed structure to the second fixed structure. Additionally, the vibration isolation system includes an isolator, including a shape memory alloy material, associated with the connector. The isolator is arranged between the first fixed structure and the second fixed structure such that the isolator reduces vibrations transferred between the first fixed structure and the second fixed structure.

Abstract: An aircraft propulsion assembly includes: a gas generator coupled by a coupling mechanism to a thrust generator having a structural torque transmission gearbox, and a rigid cradle rigidly supporting the thrust generator in a first suspension plane and the gas generator in distinct second and third suspension planes, the cradle being for securing to a structural element of the aircraft via a vibration-filtering flexible connection.

Abstract: Disclosed is a vibration-damping support device, including a housing, and a core shaft having one end passing through the housing to connect with a vibration source. The vibration-damping support device further includes two elastic members arranged within the housing and spaced apart from each other. Each elastic member includes an inner hole, so that it can be mounted on the core shaft. Each elastic member includes an elastic rubber body, and a plurality of metal plates that are embedded in the elastic rubber body and parallel to each other. The elastic rubber body extends beyond the metal plates in a radial direction. With this vibration-damping support device, a variable stiffness can be achieved.

Abstract: A bushing is disclosed for pivotally mounting a damper in ductwork of the type generally used with heating, ventilation, and air conditioning (HVAC) systems. The bushing is a circular shaped member of silicone rubber material, which is particularly configured and dimensioned to provide an airtight fit with the ductwork to prevent loss of conditioned air at the pivot location, without compromising the rotational capability of the damper to alter the direction of the conditioned air. The bushing is dimensioned to be inserted into the ductwork and includes a peripheral groove which receives the ductwork in a manner which compresses the inner surface of the groove to provide the airtight seal. The bushing also includes a longitudinally tapered square central opening, which opening is dimensioned to engageably receive the damper pivot rod snugly to provide additional sealing at the interface between the bushing and the pivot rod.

Abstract: A suspension system for an aircraft auxiliary power unit located in a fuselage structure, the system including: struts (10), auxiliary power unit attachment brackets (51,52) for connecting the strut (10) to the auxiliary power unit (30), vibration isolators (5) for joining the struts (10) and the auxiliary power unit attachment bracket (51, 52), a cone-bolt (1) attached to the auxiliary power unit attachment brackets (51,52) and having a longitudinal threaded hollow, an inner bolt (2) partially located within the hollow of the cone-bolt (1) and threaded to it (1), an outer bolt (3) having a longitudinal through-hole and partially located within the hollow of the cone-bolt (1) and including an external thread that engages the thread of the cone-bolt (1), the inner bolt (2) extending across the hollow of said outer bolt (3).

Abstract: A temperature-compensating damping element, which is suitable for the temperature-independent reduction of vibrations, which has a fixed, non-elastic outer part and a fixed, non-elastic inner part, which is either inserted fully or partly into a mating cut-out or opening of the outer part. The outer and inner parts have contact surfaces which are connected to one another by an elastic layer which comprises an elastomer material and which is, or can be, pre-tensioned with respect to a desired frequency by a tensioning element. The elastic layer which is responsible for the vibration damping is directly connected at one or more points to an additional elastic volume. The additional elastic volume is a multiple of the volume of the elastic layer, and has the effect that the excitation frequency of the damping element changes in the case of a temperature change within a temperature range.

Abstract: A method and apparatus comprising an interface section and a vibration reduction structure associated with the interface section. The vibration reduction structure extends from a surface of the interface section. The interface section and the vibration reduction structure are configured to reduce vibrations at a number of frequencies that travel through the interface section and the vibration reduction structure.

Abstract: A structural rod has a primary rod that has an axial cavity and a secondary rod inside the axial cavity so that the secondary rod is able to move inside the axial cavity along the direction of the longitudinal axis of the rod. The primary rod has a bearing for fastening the structural rod at the first end in a rigid manner and is not fastened rigidly to the structure at the second end. Conversely, the secondary rod has a bearing for fastening the structural rod at the second end in a rigid manner and is not fastened rigidly to the structure at the first end. The primary and secondary rods are joined through one or more intermediate linkage elements made of a deformable and elastic material.

Abstract: This invention relates to an aft pylon fairing (30) for a suspension system of an aircraft engine, comprising two side panels (44) assembled to each other by inner cross stiffening ribs (46) spaced at intervals from each other along a longitudinal direction (X) of the fairing, and also comprising a heat protection deck (32) designed to delimit an engine core flow (36). According to the invention, it also comprises two longitudinal connecting walls (58) offsetting the deck (32) from the ribs (46), each of these two longitudinal walls (58) being provided with a first side end (62) fixed to one or the other of the two side ends (60, 60) of the deck (32), and a second side end (64) rigidly fixed to the ribs (46).

Abstract: A lower enclosure has a first recess. A first annular retainer is adapted for engaging a lower portion of a capacitor and the first recess. The first annular retainer has a plurality of tabs that extend radially outward from an outer diameter surface of the first annular retainer. Each of the tabs has a sloped surface or a peaked surface for compression of the first annular retainer against the capacitor. An upper enclosure has a plurality of second recesses. A second annular retainer is adapted for engaging an upper portion of the capacitor and the second recesses. The second annular retainer has a plurality of protrusions that extend upward from the second annular retainer. Each of the protrusions has a slit for receiving a wedge, such that if the protrusions engage the wedge the second annular retainer is compressed against the capacitor.

Abstract: A pylon for suspending an engine beneath an aircraft wing, capable of being attached by one end to a casing of the engine and by another end to the wing is disclosed. The pylon includes at least one articulation actuated by a actuator making it possible to change the height position of the engine on the ground and in flight.

Abstract: A rear lower aerodynamic fairing for an attachment device for an aircraft engine, including two side panels assembled together with transverse stiffening inner ribs spaced apart from each other along a longitudinal direction of the fairing, and a heat protection floor to be closely followed by a primary flow of the engine. The floor includes plural floor segments distributed along the direction and non-rigidly bound to each other, and the fairing further includes an assembling mechanism assembling the floor segments, offsetting the latter of the ribs to which are connected the assembling mechanism.

Abstract: A mount system for an auxiliary component includes two side brackets and a top bracket for rigidly attaching an auxiliary component to an engine casing. Each side bracket defines mount segments, a deformable member and two retainer members between the mount segment. The deformable member plastically deforms during a fan-blade out event, thereby absorbing a majority of the high shock load experienced on the auxiliary component. The retainer members maintain the attachment between the auxiliary component and the engine casing subsequent to the fan-blade out event.

Abstract: A propulsion system for an airplane having an integrated pylon includes a bypass turbojet and a nacelle. The nacelle has a downstream cylindrical part which is rigid and is attached at its upstream end to an intermediate case of the engine. This downstream cylindrical part also includes a longitudinal beam for attaching rods to secure the engine to the airplane.

Abstract: An engine mounting assembly for an engine, e.g. a gas turbine engine comprises a plurality of carrying arrangements. Each carrying arrangement comprises a rear load absorbing assembly. Each load absorbing assembly provides a rear mounting point for an engine carrier. Each carrying arrangement further comprises first and second stabilising members extending forwardly from the rear mounting point of the rear load absorbing assembly to first and second spaced forward mounting points for an engine carrier.

Abstract: The invention relates to a system for suspending an engine of a rotary wing aircraft. The technical field of the invention is that of manufacturing suspension devices for helicopter engines. The invention consists in a device for suspending an engine (21) to a rotary aircraft airframe (26), which device includes a deformable structure (20) interconnecting two attachment zones (13, 17) of the device.

Abstract: A vehicle suspension system is designed such that its equation of motion can be decoupled. Such a suspension system is provided with actuators, and the actuators are optimally controlled to reduce vibration of the suspension system.

Abstract: This invention relates to a mounting system (1) inserted between an aircraft engine and a rigid structure of an attachment strut, the system particularly comprising a thrust resistance device (20). The thrust resistance device (20) comprises two lateral actuators (30) each provided with a rod (34) in which a forward end (34b) is a piston located inside a chamber (38) of a central casing (22) of the engine, the chamber (38) comprising a forward compartment (40) and an aft compartment (42). Moreover, the thrust resistance device (20) comprises a device (32) including a piston (48) fixed to the forward mount (16) and located inside a chamber (50) fixed to the central casing, the chamber (50) comprising a forward compartment (52) and an aft compartment (54), the forward compartment (52) of the chamber (50) being hydraulically connected to the aft compartments (42) of the actuators (30).

Abstract: A strut (10) for hooking an engine (16) under a wing body assembly (12) of an aircraft comprises a rigid structure as well as a mechanism for hooking this structure under the wing body assembly. This mechanism comprises a front fastener (22), a rear fastener (24) and a structure (26) for absorbing thrust. To install an engine (16) of greater diameter under the wing body assembly (12) of an existing plane, the rear part (20b) of the strut (10) is given a width which increases as it progresses to the rear. Furthermore, the rear fastener (24) comprises two braces which are fixed on both sides of the rigid structure and two shackles which connect each of the braces to an additional transverse rib integrated into the wing body assembly.

Abstract: A height adjustable seat suspension having first and second bases connected by a linkage assembly with an air spring and shock disposed between the bases. The shock dampens vertical movement of the bases and the air spring increases in air volume to raise the seat height of the suspension and decreases in air volume to lower the seat height of the suspension. A threaded rod is also included as part of the shock which is threadably engaged with a collar that is rotated by a drive source. The engagement between the threaded portions of the rod and collar axially repositions the rod with respect to said collar to change the effective length of, the shock.

Abstract: An isolator (26) and assembly method therefor. The isolator (26) is particularly useful for aircraft thrust reverser doors, and the like, and includes an outer member (28), and a isolator component (29). The outer member (28) has a central axis (A--A), a generally non-planar inner peripheral surface (32), and first and second axially extending slotted entryways (48, 48'). The isolator component (29) preferably includes a component axis (B--B), an inner member (30) having an external radial peripheral surface (33), and an elastomer or metal mesh member (40) surrounding said external radial peripheral surface (33). The isolator component (29) is assembled and retained within said outer member (28) by insertion endwise through said first and second slotted entryways (48, 48'), and rotating 90.degree. such that the component axis (B--B) is substantially aligned with the central axis (A--A).

Abstract: A suspension system attaches an engine to a vehicle frame and includes resilient mounts that are relatively soft with respect to vibrational movement of the engine along horizontal and vertical axes. This soft connection reduces transmission of vibration from the engine to the vehicle frame. The suspension system also provides a pair of hydraulic restrainers mounted on opposite sides of the engine which react equally, but in opposite directions to loads. The hydraulic restrainers are relatively stiff with respect to torsion that results from engine rotation, yet is soft with respect to translational movement of the engine.

Abstract: An apparatus for mounting a momentum wheel assembly (10) to a spacecraft (54). The momentum wheel assembly (10) includes a momentum wheel which has a primary spin axis coinciding with the primary spin axis of the spacecraft and spins in a direction opposite that of the spacecraft (54). Suspension isolation struts (20) attach the momentum wheel assembly (10) to the spacecraft (54) and provide substantial vibration isolation between the spacecraft (54) and the momentum wheel assembly (10). Voice coil actuators (40) attach to an adaptor ring (14) which in turn attaches to the spacecraft (54). The voice coil actuators (40) magnetically interact with a magnetically conductive element (42) attached to the momentum wheel assembly case (12). Interaction between the voice coil actuators (40) and the magnetic element (42) provides forces which displace the momentum wheel assembly case (12) in two axes orthogonal to the primary spin axis.

Abstract: A linkage arrangement (20) joins a nacelle (12) enclosing a gas turbine engine (10) and a pylon (18) suspended from an aircraft wing. The linkage arrangement (20) counteracts the deflections of the nacelle (12) with respect to the free air stream due to the aerodynamic load. The linkage arrangement (20) includes a plurality of links (22, 24, 32, 34) that substantially duplicate the motion of a four bar linkage mechanism.

Abstract: A mounting for connecting a turbofan gas turbine engine to an aircraft structure comprises three mounting points at the vertices of a triangle on the aircraft structure and three mounting points on the fan casing of the turbofan gas turbine engine. The first mounting point on the aircraft structure is connected to all of the three mounting points on the fan casing by three links. The second mounting point on the aircraft structure is connected to the second mounting point and the third mounting point on the fan casing by two links. The third mounting point on the aircraft structure is connected to the second mounting point and the third mounting point by two links. The links provide an open spaceframe which defines the structure of a pylon. The mounting has reduced weight compared to conventional mountings and is cheaper to manufacture.

Abstract: Means for mounting an engine to an aircraft are provided which reduce the dynamic response of the airframe due to engine vibration. A mount comprises at least one strut extending between the engine and the airframe which is attached to the airframe by means of damping elements.

Abstract: A mounting device for mounting the exhaust casing of a turbojet engine on a rigid support structure connected with an aircraft, there being at least two flows, i.e., a primary flow in the exhaust casing and a secondary flow in a shroud which surrounds the casing and which is fastened to the support structure by a rigid ring. The device consists of a plurality of arms each having means to control its orientation.

Abstract: A pneumatic suspension, especially for the seat of a vehicle.The pneumatic suspension comprises a first horizontal plate (3) meant to support the load of the suspension, and a second horizontal plate (13) affixed to chassis (14) of the suspension, with one or several first pneumatic enclosures (19) wedged between the first and the second plates.The first plate (3) is connected to the second plate (13) by means of lateral arms (9 and 10) the ends of which are fitted with rods (7, 8) capable of rotating in bearings 35, 36 and 5, 6) respectively affixed to the rear of the second plate and to the front of the first plate. The front of the first plate (3) is, in addition, connected to the front of the second plate (13) by one or several silent-blocks (25). The lateral arms may comprise each two rigid parts connected by silent-blocks (26).Usable, especially, for seats of tractors, or trucks.

Abstract: A mounting for a helicopter pylon having a plurality of resilient vertical support links (24-27) between the pylon (12) and the helicopter fuselage (13). The links have a composite spring rate for a given pylon weight which establishes a resilient support for the fuselage from the pylon at the thrust required to support said fuselage in normal flight and in which oscillatory vertical force transmitted to fuselage is minimal for acceptable static deflections of the pylon.Physical stops (24e, 24n, 24p) are operable to limit deflection between the pylon (12) and the fuselage (13) at predetermined rotor thrust above and below said normal thrust.Links (24-27) are mounted at the ends of a pair of rigid beams (20, 21 and 22, 23) which are secured at the centers thereof to opposite sides of transmission portion of the pylon (12).A vertical rigid mounting pin (24b) extends downward at the end of each beam.