Abstract: A method for manufacturing a one-piece annular metal part having a reinforcing insert of composite material. The method for manufacturing such a part (1), incorporating a reinforcing insert (11) issuing from at least one metal-coated fiber of composite material, consists in: forming a blank (E) of said part by superimposing, around a rotating cylindrical mandrel (5), layers of metal wire (7) and layers of coated fiber (10), said layers of coated composite fiber being arranged in the blank according to the positioning of said insert in the part, placing the blank (E) in a receiving tool (24), and applying a hot isostatic pressing treatment to the blank, and extracting the treated blank (E) from the receiving tool (24) and, as required, machining the treated blank to obtain said one-piece annular metal part (1) having a reinforcing insert (11).

Abstract: The invention provides a mechanical part for hinging to other mechanical parts at its ends, the mechanical part being made at least in part out of composite material from a central fiber preform and a peripheral fiber preform both of three-dimensional woven fabric, which preforms are assembled together while dry and then impregnated with resin, the peripheral preform surrounding the central preform in such a manner as to leave two empty spaces at the ends of the part and between the two preforms, which spaces are dedicated to hinging to said other parts. Metal inserts can be received in said spaces. The mechanical part can be used as a lever for a landing gear brace.

Abstract: The invention relates generally to the field of virology. More particularly, the present invention relates to methods of diagnosing, prognosis, treatment and prevention of porcine circoviral infection in mammals, in particular of porcine circovirus type 2 (PCV2). Methods of using a nucleic acid(s) and/or a protein(s), which are immunogenic in said mammal, and antibodies immunospecific for said protein(s), to treat, diagnose and/or prevent said porcine circoviral infection, are provided for by the present invention.

Abstract: The invention relates to a method of manufacturing a composite turbomachine blade, the method comprising the following steps: a) making a preform by three-dimensionally weaving yarns including tracer yarns disposed at least at the surface of the preform; b) cutting out said preform so as to leave intact a series of tracer yarns situated along a reference face of the preform; c) pre-deforming said cut-out preform; d) compacting and stiffening said pre-deformed preform; e) providing an injection mold in which said stiffened preform is placed; f) heating said injection mold; g) injecting a binder into said injection mold, the binder comprising a thermosettable resin; and h) extracting from the mold a composite molded part presenting substantially the shape and the dimensions of said blade. The invention is applicable to a making fan blade.

Abstract: A composite material casing of varying thickness, in particular for a gas turbine fan, is made by forming fiber reinforcement and densifying the reinforcement with a matrix. The fiber reinforcement is made by winding superposed layers of a fiber texture onto a mandrel, the texture being made by three-dimensional weaving with varying thickness.

Abstract: A composite part made from a sheet molding compound is disclosed as having improved characteristics over traditional sheet molding compound composite parts. The fibrous material is introduced as a veil layer adjacent a paste layer, the veil flows well during the molding process. The improved flow and surface characteristics of a composite part are attributed to the elongation of the veil during molding and to the improved filling capabilities.

Abstract: A turbomachine rotor including at least one disk having a ring constituted, for example, by a winding of metal-coated silicon carbide or alumina yarn. According to the invention, the composite ring is received in a closed annular cavity, e.g. defining by machining a groove in an enlarged portion of the disk and closing the groove by means of an annular plate after the ring has been put into place.

Abstract: In an altitude and vertical speed indicator for aircraft, an altitude indicator includes a graduated scale vertically mobile past a fixed marker and a vertical speed indicator includes a pointer rotatable about the point of intersection of a straight line segment through the fixed marker and a straight line segment through the pointer and pointing towards the mobile scale. The angle defined by the fixed marker and the pointer is representative of the vertical speed value.

Abstract: A combined altitude and height-above-ground indicator for an aircraft enables the altitude and the height of an aircraft to be displayed simultaneously. The combined indicator includes a first sensor and a second sensor which respectively sense altitude and height above ground, means for processing the information supplied by the first and second sensors, and means for displaying the sensed altitude and height-above-ground information by superimposing the altitude and height-above-ground information on the same scale against a pointer. The scale includes a transparent first part which represents a pressure-altitude display, and a second part which is a mask positioned under the first part so that it masks the background of the indicator for altitude levels which are below the measured height above ground.

Abstract: A combined altitude and height-above-ground indicator for an aircraft includes a first sensor and a second sensor which respectively sense altitude and height-above-ground, a processor for processing the information supplied by the first and second sensors, and a display for displaying the altitude and height-above-ground information, showing the two items of information against each other, on the same scale against at least one pointer.

Abstract: A power margin indicator for a rotary-wing aircraft, intended to give information on the power margin available on at least one engine and one gearbox of the aircraft. The indicator includes: (a) input unit (5) for the various control parameters of the engine and of the gearbox, (b) calculation device (6) connected to the input unit (5) which, on the basis of the parameters, formulate the power margin, expressed as a collective-pitch value, and (c) display units (4, 8, 9) showing, on a display screen (7), the power margins represented on a scale (8) which is graduated in collective-pitch equivalents, capable of moving past a pitch index (9) in a window (4) of the screen (7).

Abstract: The present invention relates to an indicator for monitoring the path of an aircraft in a horizontal plane, comprising:sensors delivering information relating to said aircraft,means for processing the information delivered by said sensors,means for displaying the signals delivered by said processing means presenting on a display screen:a symbol (11) portraying the position of the aircraft, the extensions of which designate the longitudinal (X--X) and transverse (Y--Y) axes of the aircraft,a compass rose (10) which can move in rotation about said symbol.According to the invention, said compass rose (10) presents a deformation along at least one of said longitudinal (X--X) and transverse (Y--Y) axes.

Abstract: The present invention concerns a device for indicating the position of an aircraft (H) notably a helicopter (H) with respect to a beam (F).In accordance with the invention, said indicator includes fixed first means (6) indicating the position of said aircraft (H), movable second means (7) indicating the position of the beam (F) in a predefined direction with respect to said aircraft (H), and third means (8) indicating which way to steer the aircraft (H) in the predefined direction to capture the beam (F) to said third means (8) being activated only when the aircraft (H) has crossed the beam (F) completely and is outside it.

Abstract: A horizontal speed indicator for a rotary-wing aircraft includes first and second sensors for determining, respectively, the heading and the horizontal speed of the aircraft. The indicator processes the signals delivered by the first and second sensors, and displays the processed signals on a screen, which includes a compass rose which can rotate when the aircraft alters its heading, and a scale which represents the horizontal speed of the aircraft. The scale includes cross wires and concentric circles, and is capable of moving with respect to the compass rose.

Abstract: A turbomachine rotor stage having a thin annular body comprising a metal alloy part reinforced by at least one fibrous ring which has a radial height h of at least 1.5 times its axial width l and which is embedded in the metal alloy part so that it projects radially outwardly from the inner wall thereof in order to stiffen the body and reduce the quantity of fibre material to be used.

Abstract: The process and apparatus concern hot shaping by plastic deformation of metal alloys by means of a pressing tool.The process comprises effecting extrusion of a billet which is covered by at least one external sleeve, by a pushing force applied by means of a pressing tool, through a die. A thin layer of at least one compound comprising oxygen and at least one metal is deposited on one of the facing walls of the sleeve and the billet. The billet is preheated before being put into the container for the extrusion operation. Lubrication is effected by a lubricant such as a glass. The process is applied to the extrusion of solid or hollow billets of refractory alloys and also other alloys which involve difficulties in shaping them.