Abstract: A decorative, nonwoven laminate and a method of forming, including a first side of a first nonwoven affixed to one or both of a) a first side of a polymeric sheet or b) a second nonwoven, wherein the first nonwoven exhibits a basis weight of 15 g/m2 to 2500 g/m2 and the second nonwoven exhibits a basis weight of 15 g/m2 to 1200 g/m2; and a colorant deposited on a second side of the first nonwoven. A topical coating may or may not be applied to improve durability of the printed surface layer. The decorative nonwoven laminate may also amount to a single layer of the first nonwoven, which then includes a layer of colorant and a topical coating over the colorant and single nonwoven layer.

Abstract: A pest animal deterrent system including a support system including a mast attached to a tripod, the mast including an arm opposite the tripod; an optical module attached to the arm; a noise generator module attached to the arm, the noise generator module in operative communication with the optical module; a speaker in operative communication with the noise generator module; a battery electrically coupled to the optical module and the noise generator module; and a solar collector electrically coupled to the battery.

Abstract: A system and method is described for labelling data for trigger identification. The system and method comprising receiving data, transforming the data, extracting content from the data, processing data content through a classification machine learning model to receive a label, and trigger a secondary system based on the label. The system and method may further include maintaining a database of labeled data.

Abstract: A system includes one or more processors configured to determine a discharge rate associated with discharging material from a hauling machine. In some examples, the system receives sensor data associated with a crushing machine configured to receive the material. Based on the sensor data, the system determines the discharge rate, to optimize the efficiency of the crushing machine. In some examples, the system determines the discharge rate based on input by an operator via a user interface. In some examples, the system determines an angular rate at which to raise a bed of the hauling machine to cause the material to be discharged at the discharge rate. Based on a determination to discharge material, the system causes the bed to be raised at the angular rate to discharge material. In some examples, the system may update the discharge rate based on additional sensor data and/or an additional operator input.

Abstract: An aircraft including a pylon attached to a gas turbine engine and a mounting system attaching the engine to the pylon. The mounting system including a first and a second frame each of three elongate members arranged in a triangle, each frame respectively arranged such that a core of the engine is positioned extending through an area defined between the three elongate members of each frame. Each frame forming at least part of a load bearing connection between the pylon and the engine. Each frame consisting of two portions, each portion corresponding to each side of the engine as attached to the pylon. The triangle formed by each frame being symmetrical about a plane separating the two portions. The engine is attached to the mounting system such that both frames are positioned axially forward of a radially extending projection of a first turbine stage in the core.

Abstract: A propeller blade retention arrangement having a propeller blade comprising in radial sequence an aerofoil portion, a shank portion and a root portion. The root portion having first cross-sectional area close to the shank portion and second cross-sectional area at the end distal to the aerofoil portion, wherein the second cross-sectional area is greater than the first cross-sectional area. At least two cheeks each having an inner surface arranged to abut the root portion, an outer surface that is threaded and edge surfaces that abut another of the at least two cheeks; wherein the at least two cheeks are arranged to surround the root portion in circumferential abutment. A collar having a threaded inner surface arranged to threadingly engage the outer surfaces of the at least two cheeks.

Abstract: An engine mount, for mounting the casing of an aircraft engine to the fuselage or wing of an aircraft, e.g. via a pylon, including first and second links having connector formations for connection to respective mounting and support formations on the engine casing and aircraft mounting structure. Each of the first and second links is typically connected by a pin between the mounting and support formations. Each link has a further connector formation arranged such that the connector formation of the first link is offset from the connector formation of the second link. The connector formations are joined by an intermediate link. The mount allows lateral forces and torque to be resolved in such a way as to substantially avoid lateral displacement of the engine away from a central plane. The intermediate link may also provide a failsafe catcher arrangement in the event that the first or second link fail.

Abstract: This invention relates to a blade assembly comprising: a hub which is rotatable about an axis; at least one blade having an aerofoil portion and a root, wherein the root is coupled to the hub using a primary retention device which prevents radial separation of the root and hub in normal use; and, a secondary retention device which comprises an annular catcher having a restriction through which the root portion cannot radially pass, the restriction being located radially outwardly and radially spaced from the root part during use.

Abstract: A mounting system is arranged in use for attaching a gas turbine engine to a pylon of an aircraft. The mounting system comprises a first frame of three elongate members arranged in a triangle. The first frame is arranged in use such that a core of the gas turbine engine is positioned extending through the area defined between the three elongate members. The first frame forms at least part of a load bearing connection between the pylon and gas turbine engine. The first frame consists of two portions, one corresponding to each side of the gas turbine engine when attached to the pylon. The triangle is symmetrical about a plane separating the two portions of the first frame.

Abstract: A support ring for a rotary assembly such as a propeller assembly includes support cups for receiving blade roots of propeller blades. The support cups are interconnected by bridging structures. Each bridging structure includes bridging walls which extend radially from a bridging web. The bridging structures thus have a channel-shaped cross-section. The bridging walls have a scalloped configuration at their radially outer edges. As a result of this configuration, the neutral axes of the bridging structures are straight, so that the support ring behaves, in structural terms, as a polygon.

Abstract: An engine mount, for mounting the casing of an aircraft engine to the fuselage or wing of an aircraft, e.g. via a pylon, including first and second links having connector formations for connection to respective mounting and support formations on the engine casing and aircraft mounting structure. Each of the first and second links is typically connected by a pin between the mounting and support formations. Each link has a further connector formation arranged such that the connector formation of the first link is offset from the connector formation of the second link. The connector formations are joined by an intermediate link. The mount allows lateral forces and torque to be resolved in such a way as to substantially avoid lateral displacement of the engine away from a central plane. The intermediate link may also provide a failsafe catcher arrangement in the event that the first or second link fail.

Abstract: A propeller blade retention arrangement having a propeller blade comprising in radial sequence an aerofoil portion, a shank portion and a root portion. The root portion having first cross-sectional area close to the shank portion and second cross-sectional area at the end distal to the aerofoil portion, wherein the second cross-sectional area is greater than the first cross-sectional area. At least two cheeks each having an inner surface arranged to abut the root portion, an outer surface that is threaded and edge surfaces that abut another of the at least two cheeks; wherein the at least two cheeks are arranged to surround the root portion in circumferential abutment. A collar having a threaded inner surface arranged to threadingly engage the outer surfaces of the at least two cheeks.

Abstract: Fiber optic connectors and components for fiber optic connectors with improved side-loading performance are disclosed along with methods for making the same. The fiber optic connector includes a ferrule and a ferrule holder where the ferrule holder may be disposed within a housing. The ferrule holder has a forward portion with a spherical feature that includes a first portion with a compound surface for cooperating with the housing, thereby allowing relative movement therebetween. Specifically, the spherical feature of the ferrule holder permits rotational translation of the ferrule holder in two degrees of freedom relative to the housing and inhibits the longitudinal translation of the ferrule holder in same two degrees of freedom relative to the housing, thereby providing improved side-loading performance.

Abstract: This invention relates to a blade assembly comprising: a hub which is rotatable about an axis; at least one blade having an aerofoil portion and a root, wherein the root is coupled to the hub using a primary retention device which prevents radial separation of the root and hub in normal use; and, a secondary retention device which comprises an annular catcher having a restriction through which the root portion cannot radially pass, the restriction being located radially outwardly and radially spaced from the root part during use.

Abstract: In a turbofan gas turbine engine, a fan shaft is rotatably mounted and radially supported by a bearing in a bearing support structure-supported from a fixed engine structure by radially frangible bolts and radially extending spokes. The radially inner ends of the radially extending spokes are mounted on a common member that engages the bearing support structure. The radially outer ends of the radially extending spokes are mounted on fixed structure of the engine located radially outwardly of the bearing support structure. The radially extending spokes are held in tension and include a super elastic material to exert a radially inward restoring force on the bearing support structure, subsequent to any radial excursion of at least part of the fan shaft relative to an engine rotational axis (X) following any fracture of the frangible bolts.

Abstract: In a turbofan gas turbine engine, a fan shaft is rotatably mounted and radially supported by a bearing in a bearing support structure supported from a fixed engine structure by radially frangible bolts and radially extending spokes. The radially inner ends of the radially extending spokes are mounted on a common member that engages the bearing support structure. The radially outer ends of the radially extending spokes are mounted on a fixed engine structure located radially outwardly of the bearing support structure. The radially extending spokes are held in tension and include a super elastic material to exert a radially inward restoring force on the bearing support structure, subsequent to any radial excursion of at least part of the fan shaft relative to an engine rotational axis (X) following any fracture of the frangible bolts.

Abstract: Composite roofing boards and methods for installing a composite roofing board are presented herein. In one embodiment, the roofing board comprises at least nine layers: two outer polymeric layers; two adhesive layers disposed between the two outer polymeric layers; two inner polymeric layers disposed between the two adhesive layers; and a substrate layer disposed between the two inner polymeric layers. A polymeric adhesive, such as an acrylate-polymer adhesive, is preformed on an outer surface of the first and/or second outer polymeric layer. A removable release liner, such as a siliconized polyester film, covers the polymeric adhesive.

Abstract: A disc arrangement for a gas turbine engine, the disc arrangement including a rotational axis, a disc, a coverplate, and a retainer to retain association between the disc and the coverplate by interference. The retainer is displaceable in a recess of the disc or the coverplate to allow release of the interference. The recess presents the retainer at an inclined angle to the rotational axis for the disc and/or the coverplate.

Abstract: In a turbofan gas turbine engine, a fan shaft is rotatably mounted and radially supported by a bearing in a bearing support structure supported from a fixed engine structure by radially frangible bolts and radially extending spokes. The radially inner ends of the radially extending spokes are mounted on a common member that engages the bearing support structure. The radially outer ends of the radially extending spokes are mounted on a fixed engine structure located radially outwardly of the bearing support structure. The radially extending spokes are held in tension and include a super elastic material to exert a radially inward restoring force on the bearing support structure, subsequent to any radial excursion of at least part of the fan shaft relative to an engine rotational axis (X) following any fracture of the frangible bolts.

Abstract: A method of forming a building wall system in the absence of building paper or housewrap that comprises providing a generally flat structural insulating sheathing. The sheathing comprises at least a first layer, a second layer and a third layer. The first and third layers comprises an alkenyl aromatic polymer foam. The second layer comprises paperboard. The insulating sheathing is fastened to the stud wall to form the building wall system such that a seal is formed that inhibits water from penetrating therethrough. The building wall system in the absence of building paper or housewrap passes the test requirements set forth in Section 1403.2 of the 2003 International Building Code.