Abstract: The manufacture of a fibrous structure (1) for a composite material part. At least one portion (3) of the fibrous structure (1) is obtained by at least partial machining of a fibrous blank stiffened by freezing a liquid impregnating the blank.

Abstract: A system for protecting an aircraft in cruising flight against excessive load factors when a vertical gust of wind occurs is disclosed. The system has a pitch-attitude flight control system (21) which is under the control of a pilot of the aircraft, an automatic pilot (26), a switch (25) allowing the aerodynamic pitch-attitude control surfaces (22) of the aircraft to be controlled either by the flight control system (21) or by the automatic pilot (26), and a protection system (31) capable of acting on the switch (25) to disconnect the automatic pilot (26) and switch on the flight control system (21). The disconnection of the automatic pilot (26) and the switching-on of the flight control system (21) is delayed by a delay time which is at least approximately equal to a typical duration of a vertical gust of wind, and the switching-on of the flight control system (21) is not carried out unless the gust of wind persists when the delay time has elapsed.

Abstract: A method of making a connecting rod made of composite material, especially for internal-combustion engines, the composite material being formed by a reinforcement embedded in a cured material, and the connecting rod (A) comprising, along the longitudinal extension (X-X) of the connecting rod, a central shank (B) extended respectively, at its two ends, by a connecting-rod big end (C) and a connecting-rod small end (D). The connecting rod (A) is produced entirely as a single component made of composite material and the reinforcement of the composite material comprises superposed plies of crossed straight filling yarns, the filling yarns, which extend parallel to the longitudinal extension (X-X) of the connecting rod (A), constituting at least twice the volume percentage of the filling yarns which extend in each of the directions other than the longitudinal extension (X-X) of the connecting rod (A), and binding yarns which pass through the superposed plies.

Abstract: Computational rig (20) consisting of two distinct parts (2, 21), linked together in a removable manner by cooperating contactors (9, 16), said parts respectively including the central processing unit (6) and a non-volatile memory block (12A) supporting the software program of said computational rig.According to the invention, said non-volatile memory (12A) is electrically erasable and programmable and the part (21) moreover includes:a memory (22) supporting a program for loading said software program into the memory block (12A);means (23) of connection of the part (21) to a communication channel (24); anda bidirectional communication peripheral device (25), arranged between the means of connection (23) and the loading memory (22).

Abstract: The present invention relates to the interconnection of two electronic devices (2 and 3) by means of an interconnection device (1).According to the invention, the interconnection device (1) has metallized grooves (17, 18) in its edge, each in electrical connection with one of its lower contacts (15). Portions of solder (20), partially accommodated in the grooves (17, 18), fasten the interconnection device (1) on the electronic device (3) and make the electrical connections between the devices (1 and 3).

Abstract: An element (14) of a swivelling aircraft landing gear, such as an element of the swivelling, rear or tail gear of a wide-body aircraft, equipped with a swivelling, front or nose gear and a non-swivelling, underwing gear, has a swivelling truck (16) carrying a swivelling, front axle (20) and a swivelling, rear axle (22). The orientation of each of these axles is respectively ensured by two linkages (44-49), which are independent of one another and connected to a non-rotary, fixed support (30) carrying the truck (16), in such a way that the axes (Y1, Y2) of the front (20) and rear (22) axles and the axis of the truck (16) intersect at the instantaneous rotation center of the aircraft.

Abstract: A photosensitive detector (1) for detecting luminous flashes (2) is provided with a photosensitive diode (3) which is linked to a positive voltage and to ground via a resistor R1 and which is capable of transforming the luminous flashes into electrical signals and a circuit (4) that processes the electrical signals generated by the photosensitive diode (3). The circuit (4) causes electrical signals which correspond to luminous flashes (2) received by the photosensitive diode (3) and which exhibit a fast rise time to be strengthened, and the circuit (4) causes electrical signals which correspond to luminous flashes (2) received by the photosensitive diode (3) and which vary more slowly in intensity to be attenuated. The circuit (4) is linked directly to the photosensitive diode (3) and includes a differentiator circuit.

Abstract: A device for locking and unlocking a rotor to a stator, at least parallel to the rotation axis of the rotor, includes an annular rotor flange transverse to the axis, an annular stator bearing surface transverse to the axis and at least partly axially facing the annular flange, and a mobile annular bearing surface transverse to the axis and at least partially axially facing the annular flange on the opposite side of the stator annular bearing surface. The mobile annular bearing surface is formed on a thrust ring coupled radially to a stator portion and able to move axially relative thereto. An annular inflatable airbag in the stator portion axially between a stator back and the thrust ring is provided with pneumatic fluid inlet/outlet arrangements.

Abstract: A plasma torch control system includes a data storage device that stores optimum arc voltages as a function of real torch powers supplied to the torch, wherein an optimum arc voltage is a voltage for which the torch has maximum torch efficiency for a real torch power, a ramping regulator that ramps the real torch power to a power reference value and keeps a real arc voltage of the torch within an error margin of an optimum arc voltage stored in the data storage device, and a stabilizing regulator that stabilizes the real torch power around the power reference value and keeps the real arc voltage within an error margin of an optimum arc voltage stored in the data storage device.

Abstract: Weaving device for producing a woven structure which is intended for the production of a composite component, including especially a component (5) for generating different speeds of movement for at least some of the warp yarns (FC). Component (5) includes a substantially plane profiled cam (5) capable of rotating about a longitudinal axis (X--X) and arranged so that the longitudinal axis (X--X) is approximately orthogonal to the direction (D) defined by the warp yarns (FC). The profile of the cam is defined by a variable transverse length (h) perpendicular to the longitudinal axis (X--X).

Abstract: The present invention relates to a homing head mounted on a flying body, and intended to guide the flying body towards a target. According to the invention, the homing head includes a target detection system (SD1) comprising a system (SI1) for identifying luminous flashes originating from the target, and a target locating system (SL1), which includes a photosensitive detector (D1) mounted fixedly on the flying body and comprising a matrix of photosensitive sensors, and a means of focussing (6) which projects onto said matrix of the photosensitive detector (D1) the image of the scene situated fore of the flying body.

Abstract: An apparatus and method for detecting vertical gusts of wind on board an aircraft in cruising flight is disclosed. The method includes the steps of: calculating an absolute value (.vertline..alpha.-.theta..vertline.) of a difference between a pair of first differentials with respect to time (.alpha. and .theta.) of a current incidence .alpha. and a current pitch attitude .theta. of the aircraft, comparing the absolute value to an upper threshold (Ss), comparing a current Mach number (M) of the aircraft to a Mach number threshold (Mo), and generating an electrical signal that represents presence of a vertical gust of wind when the absolute value is above the upper threshold, when the current Mach number is above the Mach number threshold, and when aerodynamic flaps and slats of the aircraft are in a clean configuration.

Abstract: A magnetic bearing for active magnetic centering, on at least one centering axis perpendicular to a reference axis, a first body mobile at least on this centering axis relative to a second body includes at least one magnetized member and at least one coil wound around a ferromagnetic core substantially parallel to the reference axis and carried by the second body. Two parallel ferromagnetic plates perpendicular to the reference axis are attached to the core on respective opposite sides of the coil and have transversely oriented edges opposite the airgaps. The core is attached to the edges of the parallel plates.

Abstract: The invention relates to a water repellent composition (<<Rain Repellent>>), comprising a hydrophobic agent and a solvent compatible with the hydrophobic active agent, characterized in that the solvent comprises at least one fluorinated hydrocarbon, liquid at ambient temperature, and in that the active hydrophobic agent is a compound of organopolysiloxane type.The invention also relates to a disposable pressurized container containing the above composition and an inert gas.The invention finds application in particular in the removal of water from a surface especially the windscreen of vehicles or aircraft.

Abstract: A process for the predictive determination in the pre-critical range of the load at rupture of a structure, comprising subjecting the structure to a stress of the same type as the load and for a time according to a predetermined law, whilst recording the acoustical activity generated by the resulting damage, until a predetermined stress threshold is reached. A correlation is maintained between the registered acoustic emission and the relation ##EQU1## in which: ##EQU2## is the variation of acoustic energy generated by the damage, t is time,t.sub.r is the instant of rupture, .DELTA., .alpha., C, .lambda. and .phi. are coefficients, so as to predetermine the value of prediction of the load at rupture from the above law connecting time and load.

Abstract: Switching apparatus for automatically interconnecting a first unit with a second unit, the apparatus having a first input/output assembly connected to the first unit and a second input/output assembly connected to the second unit, and including both at least one switch card each provided with at least one switch element, and a control unit for the card for establishing or not establishing interconnections between the first and second units as a function of determined instructions issued to said control unit, the control unit also including means for enabling the physical configuration of said switching apparatus to be input, and means suitable, once said input has been performed, for automatically interconnecting the first unit with the second unit in accordance with the instructions issued to the control unit by a user.

Abstract: The present invention relates to a method and a device for guiding an aircraft (A) according to a prescribed vertical flight path (T).According to the invention:the vertical distance he between said aircraft (A) and said flight path (T) is determined;the difference ve between the actual vertical velocity (Vz) of the aircraft (A) and the vertical velocity (Vzth) which it would have on the flight path (T) is determined;a vertical acceleration variation Anz is calculated:.DELTA.nz=((k1.(he-hc))+(ve-vc)).k2k1 and k2 being characteristic coefficients, hc and vc being precontrol terms, and k1.(he-hc) being restricted; andsaid restricted variation Anz is applied to the aircraft.

Abstract: The present invention concerns a fuel injection device for ramjets for supersonic and/or hypersonic aircraft, said ramjet comprising a combustion supporting gas inlet and, downstream thereof, a combustion chamber and a nozzle adapted to channel gases leaving the combustion chamber. In accordance with the invention, the injection device includes at least one injector having a structure with a plurality of spaced walls extending generally along the longitudinal axis of the ramjet body, fuel being injected into each space formed by two adjacent walls of said plurality of walls and at the downstream end of said structure.

Abstract: A magnetic bearing for active centering about at least one centering axis of a second body mobile relative to a first body has a first portion including two parallel ferromagnetic plates, a first core carrying a first coil and permanently magnetized means magnetized perpendicularly to the ferromagnetic plates, said first mounted between said ferromagnetic plates. The bearing has a second portion separated from the ferromagnetic plates of the first portion by a pair of airgaps of variable thickness parallel to the centering axis. The permanently magnetized means are offset relative to the core in a direction substantially parallel to the pair of airgaps and the ferromagnetic plates are provided with notches facing the permanently magnetized means and oriented transversely to the pair of airgaps.

Abstract: The present invention relates to a device for controlling the thrust of an aircraft, with several engines (M1, M4), comprising calculation units (UC1, UC4) that formulate first commands for controlling the engine speeds. According to the invention, said device (1) additionally comprises means (CONT1, CONT4) of controlling the two outer engines (M1, M4), calculation means that formulate second commands for controlling the speed of the outer engines (M1, M4) making it possible to obtain a reduction in thrust, and switching means which, during normal operation of the outer engines (M1, M4) send the first commands to these engines and, when one outer engine (M1) fails, send the second commands to the opposite outer engine (M4).