Abstract: A method for detection and identification of defects in a weld seam created using a laser beam. According to this method, at least two measurement signals are acquired in real time delivered by optical sensors (C1 to C6) detecting variations in luminous intensity of the plasma formed by the laser beam (14). These signals are then combined by applying a mathematical operation. The combined signal obtained is then compared to a predetermined threshold. Depending on the result of this comparison, a determination is made of the presence or absence of a defect corresponding to the operator used.

Abstract: A device for emitting digital video images may include a picture-taking unit for producing the images and a unit for forming at least one signal in the field of vision of the picture-taking unit so that the signal appears in at least some of the images produced by the picture-taking unit. The signal is formed to vary temporally, making it possible to detect any image freeze emitted by the device.

Abstract: A shut-off system for an orifice of a duct, particularly for an orifice of an air inlet passage that allows air into the combustion chamber of a ramjet, includes a shutter for shutting off the orifice of the duct, and a controllable actuating device capable of acting on the shutter to uncover the orifice. The shutter includes a removable cap which is held on the duct and a locking device which keeps the cap on the duct by at least one locked jaw, which is unlockable. The actuating device includes at least one controllable striker which is capable of unlocking the jaw in such a way as to cause the cap to be ejected from the duct and to uncover the orifice.

Abstract: The nose gear of an aircraft comprises a main group of at least one wheel (10) in permanent contact with the ground and a secondary group of at least one wheel (12), which is normally spaced from the ground, when the aircraft is on the ground. In the case of emergency braking due to an aborted takeoff or in the case of a blowout of a tire of a wheel (10) of the main group, the wheel or wheels (12) come into contact with the ground. This avoids an oversizing of the nose gear.

Abstract: In order to manufacture a sandwich panel using the RTM technique, a stack comprising a core (10) with open cells, a film (12) of intumescent material covering each of the faces of the core (10), a dry barrier fabric (14) covering each of the films (12) and an overlay of dry fibers (16) covering each of the barrier fabrics is placed in a mold. During polymerization of the films (12), pressurization of the mold and the presence of the barrier fabrics (14) prevent penetration of the foam into the overlays (16). The resin is then injected into the mold and then polymerized, without danger of penetration into the cells of the core (10).

Abstract: To monitor the operating state of a composite structure formed from at least two different materials and subject to a uniform force or load over its entire surface, the deformation at the interface between the two materials is measured. A comparison with a reference quantity of the structure, normally produced by the force applied thereto, indicates the operating state. When the composite structure forms the wall (14) of a reservoir (10), monitoring takes place in an instrumentation box (30) joined to the reservoir. When a critical threshold is exceeded, an alarm indicator (32) is triggered on the box (30).

Abstract: In order to avoid an operator forgetting to actuate locking mechanism interposed between two elements, such as the pod cowls (12, 14) of an aircraft engine, when said elements are in the closed position, use is made of a closure fault indicator. Said indicator comprises retractable abutment members (42, 44) automatically maintaining the two elements spaced from one another in a visible manner, when said elements are moved from their open position into their closed position.

Abstract: Control system for a control surface (100) of an aircraft comprising at least one actuator (102, 104) of the control surface, connected to a hydraulic circuit and equipped with at least two power jacks (110) capable of operating in at least one activated mode and one deactivated mode. According to the invention, the system also comprises a control unit (114) capable of making a number of jacks operate in activated mode depending on the aircraft flight conditions. Application to aircraft.

Abstract: An Eyepiece-support arm assembly device on an aircraft. The device comprises flanges formed on the eyepiece-support arm and on a support attached to the aircraft, along with a retention belt (32) liable to be set to a locking status, wherein the arm is immobilised in relation to the support, a setting status, wherein the arm can be moved between a position for use and a retracted position, and a disassembly status allowing the assembly and disassembly of the eyepiece-support arm, without modifying the setting. The status is changed by operating levers (44, 46).

Abstract: Blanking-cap system for an orifice of a duct, in particular for an orifice of an air-intake duct into the combustion chamber of a ramjet. The blanking-cap system (16) includes a glass blanking cap (15) and a destruction device (17) which comprises a projectile (18) capable of destroying the blanking cap (15), and a controllable projection means (19), which is capable of projecting the said projectile (18) and which is arranged outside the conduit (7) while being oriented in such a way as to be able to project the said projectile (18) onto the said blanking cap (15).

Abstract: The present invention relates to a device for aiding the identification of subassemblies of an item of equipment (E) including a number of subassemblies and equipped with a storage unit (US) storing references. According to the invention, said device includes a memory (7) recording the references stored in the storage unit (US), an external electrical power supply means (9) for the memory (7), a means (13) of isolation both electrically and in terms of software processing, and a connection means (10) connected to the memory (7) and to which can be connected a reader (L) capable of reading and telling back the references which are recorded in the memory (7) and which relate to said subassemblies of the item of equipment (E).

Abstract: The present invention relates to a suspension device (4) for connecting an item of on-board equipment (2) to the structure (3) of a vehicle, particularly a rotary-wing aircraft, said suspension device (4) comprising first and second parts (5, 6) shaped in the form of plates and capable of being fixed to said structure (3) and to said item of equipment (2), and suspension means (7) which are arranged between said first and second parts (5, 6). According to the invention, the suspension device (4) additionally comprises a locking system (20) capable of bringing the suspension device (4) into one of two positions: a locked position in which the locking system (20) immobilizes the first and second parts (5, 6) one with respect to the other, and an unlocked position in which the locking system (20) releases said parts (5, 6) so that they can move relative to one another, and means (21) for controlling the locking system (20).

Abstract: The process, in which there is carried out localized surface metallization of pieces of composite material, of the type covered on their surface with a layer (CC) of an electrically conductive material, itself coated with an electrically insulating protective layer (P) such as paint or the like, is characterized in that in line with each zone of said painted surface dedicated to a hole to be metallized, there is carried out a scraping off down to the conductive layer (CC), with the help of a metallic edge pressed resiliently and moved over the surface of the piece, stopping of the scraping off being controlled consecutively upon reaching or exceeding a predetermined threshold of electrical conduction between the conductive layer (CC) and the metallic edge and, finally, the various holes of the piece are pierced and shaped.

Abstract: A sequential trigger system (10) for triggering a plurality of cameras (42, 42a) equipped with a burst picture taking mode is provided. The system includes a clock (12) and means (14, 16) of fixing the frequency of the clock frequency, and further includes means (20) of successively starting operation of the cameras in burst mode in response to a trigger signal, the means being controlled by the clock so as to put the cameras into operation at an operating rate faster than the rate at which the cameras take pictures in burst mode.

Abstract: An optical sighting system includes at least one optical channel with which there is associated at least one reticle. The reticle includes at least one mark which demarcates a blind spot, which is visible to an observer using the optical sighing system and which is centered approximately about a centering point that is situated substantially at a distance which is representative of a sighting angle of between 13° and 18°, with respect to a predetermined direction of observation along a first direction. This first direction is representative on the optical sighting system of the direction passing substantially by the centers of the eyes of an observer who is using the optical sighting system.

Abstract: A device for discharging hot air for a jet engine air inlet cowl, with a deicing circuit. The air inlet cowl for a jet engine, the leading edge of which is hollow and swept with a flow of deicing hot air, includes orifices for discharging the hot air flow to the outside of the leading edge, which form an arrangement such that at least two pressurized hot air jets passing through two adjacent orifices have, downstream of a calibration piece in which the orifices are made, different inclinations with respect to the calibration piece.

Abstract: This invention relates to a self-degradable optical fiber, that is to say, an optical fiber that contains, within its own structure, compounds capable of leading to its degradation. This optical fiber comprises a core, a sheath and a polymer coating, in which at least one calixarene is incorporated in the coating, the calixarene(s) imprisoning at least one compound capable of being released under defined conditions of temperature and/or humidity and/or irradiation and of bringing about degradation of the coating. The invention also relates to a method of preparing this fiber and a wire guided device comprising this fiber.

Abstract: According to the invention, the suspension pylon (3) comprises a fairing for reducing the local loss in lift and its maximum-width section (7) is located at the front of the concave and set-back rear part (4R) of the pressure face (4) of the wing structure (1). The fairing for reducing the local loss in lift (8): is housed, at least over most of its height, in the concavity of said rear part (4R) of the pressure face (4) of the wing structure (1), and comprises an underside (15) which comes close to its upper surface (13) as an aerodynamic continuation of the suction face (14) of the wing structure (1) so as to give the protruding rear part (12) of said fairing (8) the shape of a blade which tapers toward the rear and ends in an aerodynamic trailing edge (16).

Abstract: The invention relates to an emitter of infrared radiation in band III as well as to a composite allowing the emission of such infrared radiation. The emitter includes an emission source having a composite on which a thin oxide layer is deposited. The oxide has an emissivity which is less than 0.2 for wavelengths of emitted radiation of less than 6 &mgr;m and greater than 0.8 for wavelengths of between 8 and 10 &mgr;m. The invention also includes a heating device which can heat the composite so that it emits infrared radiation in band III.

Abstract: The present invention relates to a process and a device for guiding a flying craft onto a target, the device (1) comprising a detector (D) pointed at the target in such a way that a projection of the latter is situated on a field of measurement of the detector (D), a computation unit (UC) for determining guidance commands, and members (6) carrying out the guidance. According to the invention, the said device (1) furthermore comprises computation means (C3, C4) for determining commands for varying attitudes of the said flying craft making it possible to center the said projection with respect to a first direction of the measurement field, and the line of sight of the detector (D) is moveable and is controlled in such a way as to center the said projection with respect to a second direction of the measurement field, which is different from the said first direction.