Abstract: Rotary assist apparatus for recirculating ball steering gears are disclosed. An example motor vehicle steering system includes an input shaft to couple to a steering shaft of a motor vehicle, a worm gear, a first end of the worm gear coupled to the input shaft, a second end of the worm gear fixed to a helical spur gear, a ball nut surrounding a portion of the worm gear, the ball nut including ball bearings and ball guides, an intermediate gear fixed to a first pinion, the first pinion engaged with the helical spur gear, a motor fixed to a second pinion, the second pinion engaged with the intermediate gear, the motor to rotate the worm gear to translate the ball nut, and a sector gear engaged with the ball nut, the sector gear to rotate as the ball nut translates.

Abstract: A rotor vane for an aircraft turbine engine, the vane having an axis of rotation once it has been rigidly connected to a rotor and a stacking axis. The vane includes a blade extending between an internal platform and an external platform bearing at least one projecting lip. The external platform is configured to cooperate in a form-fitting manner with the complementary side edges of adjacent vanes. The rotor vane has wear-resistant covering of a lower side edge which extends over one wall of a substantially rectilinear first ridge of the platform and over one wall of a second ridge of the platform. The second ridge extends at least partially inside the lip and is inclined relative to the first ridge in a direction substantially parallel to a transverse axis of the lip.

Abstract: A watercraft includes a deck, a hull supporting the deck, and a barrier structure. The barrier structure includes: a frame connected to at least one of the deck and the hull and at least partially surrounding a portion of the deck; and a pliable sheet wall connected to the frame. The frame includes an upper portion including a rail for grabbing by a user's hand; and a lower portion connected to the at least one of the deck and the hull. The lower portion and the upper portion are connected to one another. The pliable sheet wall is stretched across at least a portion of the frame so as to extend between the upper and lower portions of the frame. A barrier structure is also contemplated.

Abstract: A floor tile has arcuate slots formed on its upper surface and defined about a common center of curvature. A positioning cavity is formed on the upper surface and located radially outward from a common radius of curvature of the arcuate slots. An accessory comprises a base having a bottom section. An attachment member is pivotally mounted to the base and has two arcuate hooks extending under the bottom section of the base. A locating projection extends under the bottom section of the base, being located radially outward from a pivot axis of the attachment member. To mount the accessory on the floor tile, the arcuate hooks are received in the arcuate slots and the locating projection is received in the positioning cavity. Pivoting the attachment member causes locking or unlocking of the arcuate hooks in the arcuate slots for attaching or detaching the accessory on the floor tile.

Abstract: A method for refitting blade shrouds of a rotor wheel in an aircraft turbomachine is described. The rotor wheel has a disc bearing blades that each have an airfoil extending between a root and a shroud, the shroud of each blade having lateral edges comprising including shapes complementary to the lateral edges of the shrouds of the adjacent blades. The lateral edges of the shrouds are interlocked in engagement with one another such that anti-Wear coatings of these edges are in contact With one another in a desired interlocking engagement position, and at least one of the lateral edges of at least one of the shrouds being able to be disengaged from the lateral edge of an adjacent shroud in an undesired disengagement position. The method includes, when an undesired disengagement position is detected, a step of inserting a re-engagement device into the turbomachine.

Abstract: There is disclosed a method and system for identifying relevant training data points for a prediction by a machine learning algorithm (MLA). The method comprises determining indicators of influence for training data points used to train the MLA. A normalizing function is applied to the indicators of influence to determine normalized indicators of influence. Training data points having the highest and lowest normalized indicators of influence are output for display.

Abstract: A method for producing a metal bladed element of a turbine engine, in particular of an aircraft, includes steps of producing the bladed element, depositing a coating made of wear-proof material on at least one portion of the bladed element and verifying, preferably visually, the conformity of the bladed element. Verifying the conformity of the bladed element includes implementing a verification element on the bladed element. The bladed element is configured according to a conformity threshold value to conceal a non-conformity of the coating, if the non-conformity has at least one dimension less than the threshold value, and to show at least one portion of this non-conformity if the at least one dimension is greater than the threshold value.

Abstract: Rotary assist apparatus for recirculating ball steering gears are disclosed. An example motor vehicle steering system includes an input shaft to couple to a steering shaft of a motor vehicle, a worm gear, a first end of the worm gear coupled to the input shaft, a second end of the worm gear fixed to a helical spur gear, a ball nut surrounding a portion of the worm gear, the ball nut including ball bearings and ball guides, an intermediate gear fixed to a first pinion, the first pinion engaged with the helical spur gear, a motor fixed to a second pinion, the second pinion engaged with the intermediate gear, the motor to rotate the worm gear to translate the ball nut, and a sector gear engaged with the ball nut, the sector gear to rotate as the ball nut translates.

Abstract: A rotor blade for a rotor disk of a turbine of an aeronautical turbomachine includes, in a radial direction from inside to outside, a blade foot root, a support, a platform and a rotor vane, where the root is connected to the support by a neck. The neck has a curvilinear profile defining, in a section in a plane perpendicular to the radial direction, a curved shape. The neck section overlaps at least 75% of the section of the rotor vane, as a projection of the sections of the neck and of the rotor vane in a plane perpendicular to the radial direction, where the section of the rotor vane joins with the platform.

Abstract: Disclosed is method for monitoring an avionics software application, able to be executed on a platform including resources and hosting an operating system, the platform being intended to be on board an aircraft, implemented by an electronic monitoring device. The method includes: implementing at least one monitoring operation of the application from among syntactic monitoring of each call emitted by the application to the operating system; semantic monitoring of each call emitted by the application to the operating system; monitoring of a dynamic of the calls emitted by the application to the operating system; and monitoring of the use by the application of the resources of the platform; and generating an alarm signal if an abnormal behavior of the application is detected.

Abstract: There is disclosed a method and system for identifying relevant training data points for a prediction by a machine learning algorithm (MLA). The method comprises determining indicators of influence for training data points used to train the MLA. A normalizing function is applied to the indicators of influence to determine normalized indicators of influence. Training data points having the highest and lowest normalized indicators of influence are output for display.

Abstract: The invention relates to a rotor vane (10) for an aircraft turbine engine, said vane having an axis (A) of rotation once it has been rigidly connected to a rotor and a stacking axis (X). The vane comprises a blade (16) extending between an internal platform (19) and an external platform (20) bearing at least one projecting lip (31, 32), said blade having a lower surface (16a) and an upper surface (16b). The external platform comprises lower (22) and upper (21) side edges, located on the side of the lower (16a) and upper (16b) surfaces respectively and configured to cooperate in a form-fitting manner with the complementary side edges (21, 22) of adjacent vanes, each of said side edges having a wear-resistant covering (36).

Abstract: The main object of the invention is a rotor blade (18) for a rotor disk of a turbine of an aeronautical turbomachine including, in a radial direction (23) from inside to outside, a blade foot root, a support, a platform and a rotor vane (30), where the root is connected to the support by a neck (40), characterised by the fact that the neck (40) has a curvilinear profile defining, in a section in a plane perpendicular to the radial direction (23), a curved shape, and in that the said neck section (40) thus overlaps at least 75% of the section of the rotor vane (30), as a projection of the sections of the neck (40) and of the rotor vane (30) in a plane perpendicular to the radial direction (23), where the section of the rotor vane (30) joins with the platform.

Abstract: A support structure for mounting an accessory assembly to a vehicle having a mounting surface defining a base mount and at least one brace mount includes a base having a connection portion being selectively connectable to the vehicle, and a support portion. The base is connectable to the accessory assembly. The support structure further includes a brace having a mating portion for engaging the support portion, and at least one arm extending from the mating portion toward the connection portion and away from the base when the mating portion engages the support portion. The at least one arm has a proximal end connected to the mating portion, and a distal end being spaced from the connection portion and being selectively engageable to the vehicle. The support structure further includes a lock selectively locking the mating portion to the base.

Abstract: A method for producing a metal bladed element of a turbine engine, in particular of an aircraft, includes steps of producing the bladed element, depositing a coating made of wear-proof material on at least one portion of the bladed element and verifying, preferably visually, the conformity of the bladed element. Verifying the conformity of the bladed element includes implementing a verification element on the bladed element. The bladed element is configured according to a conformity threshold value to conceal a non-conformity of the coating, if the non-conformity has at least one dimension less than the threshold value, and to show at least one portion of this non-conformity if the at least one dimension is greater than the threshold value.

Abstract: A support structure for mounting an accessory assembly to a vehicle having a mounting surface defining a base mount and at least one brace mount includes a base having a connection portion being selectively connectable to the vehicle, and a support portion. The base is connectable to the accessory assembly. The support structure further includes a brace having a mating portion for engaging the support portion, and at least one arm extending from the mating portion toward the connection portion and away from the base when the mating portion engages the support portion. The at least one arm has a proximal end connected to the mating portion, and a distal end being spaced from the connection portion and being selectively engageable to the vehicle. The support structure further includes a lock selectively locking the mating portion to the base.

Abstract: Disclosed is method for monitoring an avionics software application, able to be executed on a platform including resources and hosting an operating system, the platform being intended to be on board an aircraft, implemented by an electronic monitoring device. The method includes: implementing at least one monitoring operation of the application from among syntactic monitoring of each call emitted by the application to the operating system; semantic monitoring of each call emitted by the application to the operating system; monitoring of a dynamic of the calls emitted by the application to the operating system; and monitoring of the use by the application of the resources of the platform; and generating an alarm signal if an abnormal behavior of the application is detected.

Abstract: A method of performing a seismic survey including: deploying nodal seismic sensors at positions in a survey region; activating a plurality of seismic sources; and using the nodal seismic sensors to record seismic signals generated in response to the activation of the plurality of signals.

Abstract: This milling cutter is composed of four blades (Ia, 1b, 1c, 1d) cut out, preferably by die-stamping, from sheets of soft metal, for example stainless steel. The blades have slits (13, 15) that allow them to be inserted into one another in such a way as to obtain a cutter head. The slits have different widths, which allows them to be assembled on the rotation shaft in a number greater than two. Each blade is continued by a lower part (12). These lower parts are engaged in a flat ring (7) that keeps the assembly rigid. Two of the blades each have two lateral extensions (2) that are cut out from the blade itself and are situated in the lower part (12) of the blade. These lateral extensions are designed in such a way as to permit their insertion in notches (3) of conventional bayonet-type cutter spindles, thereby avoiding the need for an intermediate tool.

Abstract: A remote-controlled audio system comprises sets of loudspeakers (14A-14D) connected to power amplifier units (22A-22D) in an audio distribution unit (10) to which several audio sources, such as a compact disc unit, a tape deck, etc., are connected. Remote units (34) are provided, one in each zone with a set of loudspeakers. The loudspeakers and the remote unit are connected to the audio distribution unit by four wires whereby audio and data signals and power are transmitted to the loudspeakers and the remote unit, respectively. Each power amplifier unit may have a pair of power amplifiers, each connected to one of the loudspeakers in the set, referenced to a first ground (1) and a second ground (2), respectively. The second ground (2) is maintained at a prescribed voltage relative to the first ground. The remote unit (34A) is connected between the “ground” terminals of the two loudspeakers of the set, i.e. those connected via the speaker cables to the first and second grounds in the audio distribution unit.