Abstract: An apparatus for manufacturing composite parts produced by resin transfer molding (RTM) is configured to operate in controlled flow-rate mode or controlled pressure mode to use the RTM technique for manufacturing large-sized composite parts with a low fiber content. In both modes, control is by means of a fuzzy logic control card. In controlled flow-rate mode the resin is injected alternately by two injection cylinders (40a and 40b) controlled by motors whose speed is controlled. In controlled pressure mode the resin is injected directly from resin supply vessels (16) subjected to pressure controlled by an air regulator (30).

Abstract: A fuel injection strut for a ramjet adapted to operate at high Mach numbers includes a combustion chamber into which a flow of combustion-supporting gas is introduced. A first end of the strut includes a stem having a leading edge with a dihedral shaped wall for defining a chamber on a concave side for receiving the flow of combustion supporting gas. An injection member generates a plurality of jets impinging cooling fluid on the concave side of the wall to cool the strut. The leading edge provides two-way permeability so that at lower speeds, air permeates through the leading edge to facilitate pilot combustion in the combustion chamber, and a higher speeds, the cooling fluid permeates through the leading edge to cool the strut.

Abstract: The present invention relates to a hybrid engine capable of employing a ramjet mode and a super ramjet mode and comprising a main engine system (3, 4, 5, 8) which burns fuel and which comprises at least one air inlet (3) for an air stream (F), a combustion chamber (8) and a jetpipe (4). According to the invention, said engine (1) additionally comprises first means (10) for storing, in ramjet mode, air diverted from the air stream (F), and second means (11) for burning, in super ramjet mode, some of a fuel of the engine (1) with the air stored by the first means (10), before injecting it into the main engine system (3, 4, 5, 8).

Abstract: A solid propellant charge for a propulsion unit (1). The latter includes a casing (2) containing the solid propellant charge (3), in the form of an elongated body having a longitudinal axis (X--X), which charge (3) has, over part of its longitudinal extent, a propellant charge profile (4) of large combustion area and is subdivided, along the longitudinal axis (X--X), into at least two segments abutting one another with their respective mutually confronting faces. The propulsion unit furthermore includes a nozzle (5) and means (6) for igniting said charge. The propellant charge profile (4) of large combustion area is provided in that part of the propellant charge (3) which is intermediate along the longitudinal axis (X--X).

Abstract: A method of determining an optimal flight path of an aircraft during its cruising phase includes forming a grid in a vertical plane of the space between a first position and a second position, selecting various path portions between the first position and the second position, determining the cost of each of the path portions, determining various possible paths from the path portions, determining the cost of each of the possible paths, and selecting the lowest-cost path.

Abstract: A device for guiding an aircraft includes an image sensor mounted on the aircraft, a data transmission unit for transmitting the images provided by the image sensor, a guide station for receiving the images which includes a touch-sensitive screen for displaying the images sensed by the image sensor. The touch-sensitive screen permits touch selection of a guide point representing a specific location displayed on the screen to which the aircraft is guided. A calculating unit calculates the instructions to guide the aircraft to the area represented by the guide point. The touch sensitive screen can include a light pen for selection of the guide point.

Abstract: The invention relates to a method of steering a vehicle, as well as to said vehicle allowing the method to be implemented.The method of steering such a vehicle including a propulsion system (2) and a jettisonable nose cone (8) containing a payload is noteworthy, according to the invention, in that, during the trajectory of said vehicle, the propulsion thrust of said vehicle (1) is temporarily interrupted in order to allow said jettisonable nose cone (8) to be ejected.

Abstract: A manufacturing process of a large part of composite materials with a high fiber content (more than 58%) using the resin transfer moulding technique, wherein a fiber pellet (26) is placed in a mould (20) and strongly compressed, whilst the resin is injected at a constant reference flow rate value and while the instantaneous pressure at the mould inlet is lower than a reference pressure value. When this reference pressure value is reached, the injection flow rate is reduced to maintain the pressure at this level, and the compression of the pellet (26) is temporarily reduced. The injection flow rate is then altered to the constant reference flow rate value and the compression is increased, to start another cycle.

Abstract: A mold having a supply tube in a lower portion and in which has been placed a fibrous preform, is placed in a container. A crucible filled with magnesium blocks is placed under the mold. The magnesium is heated and the mold is preheated under vacuum until the fusion of the magnesium starts. The tube is then introduced into the magnesium and a neutral gas circulation is set up in the container, under a vacuum insufficient to trigger the evaporation of magnesium. After its complete fusion, the magnesium is transferred into the mold by a rapid pressurization of the container. The mold is then cooled and the part removed from the mold.

Abstract: The present invention relates to the production of a reinforcement for a composite component, comprising a fibrous substrate (22, 23) reinforced by a stitching thread forming stitches (27.1, 27.2; 30.1, 30.2; 33.1, 33.2 and 36.1, 36.2) passing through said substrate. According to the invention, said stitches are oblique and pass through said substrate slantwise, making an angle of inclination of at most 30.degree.. It is advantageous for said fibrous substrate to consist of plies of crossed threads (22, 23) defining mesh cells (24) through which said stitches pass.

Abstract: In an aircraft turbine, an assembly consisting of an air inlet structure, a air blower housing (22) and a connecting part (36), is fitted in such a way as to reduce noise including in the junction area between the structure and the housing. The connecting part (36) is fastened onto a rear section (20'), not provided with a honeycomb core, of the internal wall (20) of the air inlet structure. A honeycomb structure (44) is fitted inside the air blower housing (22). The space inside the rear section (20') houses a forward extension (44') of the honeycomb structure (44), or a different honeycomb structure.

Abstract: A system for aiding the clearing of mines includes an equipment assembly composed of a portable processing unit (10) having multimedia capabilities, a helmet (12) with projection by overprinting, at least one position sensor (13) integral with the helmet and a camera for taking shots (14), capable of recording the actions of the operator. The system further includes a software assembly composed of software for the management of a data base of the various existing mines, software for the creation of synthesis and animation images, software for retouching an image which allows the images to be improved, and vocal command software.

Abstract: A satellite designed to be spin-stabilized in geostationary orbit which has, coaxial with a spin rotation axis, a satellite body surrounded with a cylindrical solar generator, an apogee maneuver system disposed along the axis and two axially disposed equipments. The apogee maneuver system has opposite one of the equipments at least two thrusters oriented parallel to the axis but offset relative thereto by the same distance. Equi-angularly spaced around the other of the two equipments, the thrusters are connected to a common liquid propellant feed system.

Abstract: The present invention relates to an air inlet cowl (9) for a jet engine, especially for an aircraft. According to the invention, the diffuser (12) of hot air for de-icing, arranged in the hollow leading edge (16) of the cowl (9) is in the form of a polygonal ring and is fixed by elastic support tabs (24) each equipped with a ball joint (25) holding a straight portion (22) of the polygonal ring.

Abstract: A process and a device for verifying the consistency of the measurements made by an angle-of-attack probe (2) mounted on an aircraft. The device (1) includes:first system (3) for computing a first coefficient of lift of the aircraft from a measurement from the probe (2) and from data relating to the aircraft;second system (5) for computing a second coefficient of lift from information about the aircraft;system (6) for computing the difference between the first and second coefficients of lift and for deducting therefrom that the measurement is or is not consistent.

Abstract: The system embodying the invention involves a communications instrument comprising a sensitive surface coupled to a processor ensuring management of a plurality of display elements, the dialogue between said instrument and said processor taking place according to a sequence comprising a first operational mode in which the sensitive surface is virtually divided into a plurality of zones corresponding isomorphically with the geometrical disposition of the display elements, and a second operational mode in which a variable displayed on a visualisation element is modified subsequent to displacement of the operator's finger on the sensitive surface. This system is notably suitable in the case of management of a large number of display elements and is highly ergonomic.

Abstract: An aircraft having a reduced-load wing structure is provided with a controllable canard stabilizer (5G, 5D) at the front end of the aircraft and a controller that controls the canard stabilizer. The controller generates a turn command corresponding to an increase in the lift of the canard stabilizer when, simultaneously, the turn command applied by the pilot to the elevational control surfaces (6G, 6D) exceeds a threshold and the measurement of the vertical acceleration of the aircraft exceeds a threshold.

Abstract: A device for attaching an engine to a strut (10) of an aircraft comprises a main attachment structure and an emergency or standby attachment structure (52). The main attachment structure includes a fitting (16) fixed to the strut (10), as well as at least two swivelled rods (18, 20) connecting the fitting (16) to the engine. The standby attachment structure (52), through which no force passes when the main attachment structure is operational, connects directly, with a clearance, the strut (10) to the engine. It e.g. comprises a yoke (54) integral with the strut (10) and passing through a window formed in the fitting (16), or a rod articulated to the engine and to the strut.

Abstract: The present invention relates to a hot-air supply system for an aircraft equipped with at least one engine (2) with a fan (3) and compressors (4). According to the invention, the regulating devices (14, 15, 16) intended to regulate the flows of hot air and of cold air sent by the pipes (10 and 11) to the heat exchanger (12) are pneumatic, controlled electrically, and are controlled by a centralized management device (24).

Abstract: A process and apparatus for controlling the deposition of roving by winding or by contact on large structures, in which deposition is carried out on a mandrel (1) driven in rotation about its axis (.theta.). A deposition head (6) is adjustable in position along at least a first rectilinear axis (X) of movement parallel to the axis of rotation (.theta.) of the mandrel. The head (6) is also movable along a second axis of rectangular displacement (Y) orthogonal to the axis of the mandrel. The axis of rotation (.theta.) of the mandrel is taken as a master axis and the other axes (X, Y, .beta., .gamma., 8, 9) are made subservient to the master axis. The master axis (.theta.) is controlled by speed orders according to a pre-established program and from a pre-established trajectory table (21). The slave axes are made subservient as a function of the angular position of the master axis, from the instantaneous angular position of the master axis (.theta.