Abstract: Various devices, assemblies, components, systems, and methods are provided relating to a shuttle stopper to facilitate alignment of a shuttle with a rail. An example shuttle stopper may include an alignment portion defining an alignment surface configured to face inwardly towards a center axis of the rail. The alignment surface may define a first distance to the center axis. The shuttle stopper may further include a safety portion defining a safety surface configured to face inwardly towards a center axis of the rail on an opposite side of the center axis from the alignment surface. The safety surface may define a second distance to the center axis. The second distance may be greater than the first distance. The shuttle stopper may be configured to rigidly attach to the rail.

Abstract: Various devices, assemblies, components, systems, and methods are provided relating to a cushion for a face mask assembly. An example cushion may include an annular sealing wall having an annular sealing surface and having an annular internal surface. The annular sealing surface may engage a face of a user. The cushion may further include an annular support wall extending circumferentially along the annular sealing wall. The annular support wall may compress into contact with the annular support wall. The cushion may further include a connector wall extending between a proximal end of the annular sealing wall and a proximal end of the annular support wall.

Abstract: The present disclosure concerns an acoustic attenuation panel for an aircraft turbojet engine nacelle and a method for manufacturing this panel. The acoustic attenuation panel includes an alveolar central core interposed between an acoustic front skin comprising perforations and a rear skin, the acoustic attenuation panel including a front structure and a rear structure. The front structure includes the acoustic front skin and a first network of alveolar walls, the rear structure including the rear skin and a second network of alveolar walls, the first and second networks of alveolar walls being complementary so as to form, in an assembled position, the alveolar central core, the front structure and the rear structure being positioned opposite to each other and so that the network of alveolar walls of a structure is spaced from the skin of the other structure facing it by a clearance d.

Abstract: An acoustic attenuation panel for a propulsion assembly includes an acoustic front skin having perforations, and a central structure formed from partitions arranged perpendicularly in order to make up cells, wherein the front skin and the central structure form the panel which is made as a single piece and is provided for directly covering a surface of an element of the propulsion assembly forming a rear skin which closes the cells of the central structure at the rear.

Abstract: A thrust reverser for a turbojet engine nacelle includes thrust reversal cascade vanes arranged about an annular flow duct having a stationary front casing, at least one movable cover moving backwards into a thrust reversal open position, and tilting flaps connected by rear pivots to the movable cover, which, in an open position, tilt and thereby at least partially close the annular flow duct. The cascade vanes move backwards with the movable cover, in that, in the closed position, the tilting flaps and the cascade vanes are arranged outside the stationary casing, and each tilting flap is connected to the stationary casing by slides which cause the tilting flaps to tilt when the movable cover moves backwards.

Abstract: The present disclosure concerns an acoustic attenuation panel for an aircraft turbojet engine nacelle and a method for manufacturing this panel. The acoustic attenuation panel includes an alveolar central core interposed between an acoustic front skin comprising perforations and a rear skin, the acoustic attenuation panel including a front structure and a rear structure. The front structure includes the acoustic front skin and a first network of alveolar walls, the rear structure including the rear skin and a second network of alveolar walls, the first and second networks of alveolar walls being complementary so as to form, in an assembled position, the alveolar central core, the front structure and the rear structure being positioned opposite to each other and so that the network of alveolar walls of a structure is spaced from the skin of the other structure facing it by a clearance d.

Abstract: A thrust reverser for a turbojet engine nacelle includes thrust reversal cascade vanes arranged about an annular flow duct having a stationary front casing, at least one movable cover moving backwards into a thrust reversal open position, and tilting flaps connected by rear pivots to the movable cover, which, in an open position, tilt and thereby at least partially close the annular flow duct. The cascade vanes move backwards with the movable cover, in that, in the closed position, the tilting flaps and the cascade vanes are arranged outside the stationary casing, and each tilting flap is connected to the stationary casing by slides which cause the tilting flaps to tilt when the movable cover moves backwards.

Abstract: An acoustic attenuation panel for a propulsion assembly includes an acoustic front skin having perforations, and a central structure formed from partitions arranged perpendicularly in order to make up cells, wherein the front skin and the central structure form the panel which is made as a single piece and is provided for directly covering a surface of an element of the propulsion assembly forming a rear skin which closes the cells of the central structure at the rear.

Abstract: The invention relates to a plant extract obtained by a single-phase extraction method, by means of a solvent and/or a mixture of solvents of plant origin, containing characterised and chemically defined constituents. Said plant extract is characterised in that it is free of polyphenol, anthocyan and/or tannin, and comprises a fraction of lipophile-type components and/or a fraction of polar-type components. The invention also relates to an extraction method which enables an inventive extract to be obtained, said method being a single-phase extraction method characterised in that it comprises the following steps: a plant material is brought into contact with a solvent and/or a mixture of solvents of plant origin, containing characterised and chemically defined constituents; the plant material is eliminated; and the solvent and/or mixture of solvents is partially or completely eliminated.

Abstract: Provided are a method, system, deployment and article of manufacture, for variable length file entry navigation. In one embodiment, a first file entry size portion of a first entry marker at a first end of a file entry is read. A position of a second entry marker at a second end of the file entry may be calculated as a function of the first file entry size portion. A determination may be made as to whether file data at the calculated position is a second entry marker, and if so whether the file data between said first and second entry markers is a valid entry by comparing the first entry size portion of the first entry marker to a second file entry size portion of the second entry marker. Other embodiments are described and claimed.

Abstract: A process for controlling pulse energy and integrated energy dose in bursts of pulses produced by an excimer laser. The energy of each pulse in each burst is measured. The rate of change of pulse energy with charging voltage is determined. A pulse energy error is determined for a previous pulse of the present burst. An integrated dose error is also determined for all previous pulses in the current burst. A charging voltage for the next pulse is determined using the pulse energy error, the integrated dose error, the rate of change of energy with charging voltage and a reference voltage. In a preferred embodiment, the rate of change of energy with voltage is determined by dithering the voltage during two pulses of each burst, once lower and once higher. The reference voltage is a voltage calculated using prior energy and voltage data. In this embodiment, the method of determining the reference voltage during a first portion of the pulse is different from the method used during a latter portion of the burst.