Abstract: A nacelle for double-flow engine with a cowling and at least one thrust reverser, the thrust reverser having an internal door and an external door arranged in the cowling, and means for simultaneously shifting these doors between a stable retracted position in which the doors are integrated in the cowling and a stable deployed position in which the internal and external doors are positioned at least partially inside and outside of the nacelle, respectively, to deflect the secondary flow and to generate a thrust reversal. The means for simultaneously shifting the doors comprise an actuator, one extremity of which is linked to one of the doors to shift this door between the extreme positions, and at least one linkage element linked to the doors to pivot by its extremities, so that the shifting of the door entails the shifting of the other door between these extreme positions.

Abstract: A propulsion system for an aircraft includes a heat exchange unit through which a hot air stream and a cooling air stream flow. The heat exchange unit includes a hot air inlet pipe situated on a rear face of the heat exchange unit, to carry the hot air stream into the heat exchange unit, and a cooling air discharge pipe situated on the rear face of the heat exchange unit to expel the cooling air stream from the heat exchange unit, the hot air inlet pipe and the cooling air discharge pipe being concentric with each other. The hot air stream flows from the rear face forward to a front of the heat exchange unit, then from the front of the heat exchange unit, to a rear of the heat exchange unit, so as to be expelled via the rear face of the heat exchange unit.

Abstract: A method to assist in the landing of an airplane in its final flight phase, following a current approach path toward a runway, includes determining at a given flight point, a landing delay margin, called MRAmax, corresponding to an estimated delay during which the braking actions must be undertaken, after the wheels touch down, to enable the airplane to stop on the runway. A device includes equipment for acquiring parameters necessary to perform the method of assisting the landing of the airplane, a computer to determine the landing delay margin MRAmax from the parameters, and a display for presenting the information to alert the crew.

Abstract: Provided is a resource management method in a communication system, and more particularly, a resource management method based on priority in a wireless communication system. The resource management method in a wireless management network includes: setting a priority factor value with regard to a link flow for which link establishment is requested; and if a capacity required by the flow for which link establishment is requested exceeds a remaining capacity of a base station, increasing the remaining capacity of the base station by sequentially reducing a minimum reserved rate (MRR) value of flows that receive a service at a lower priority than the flow for which link establishment is requested to a maximum sustained rate (MSR) value, until the remaining capacity required by the flow for which link establishment is requested is generated.

Abstract: A device for non-destructive testing of a structure likely to contain a defect, including microsensors for measuring vibratory waves emitted by the structure at different points of a surface of the structure, the aforementioned microsensors being integrated in a flexible housing capable of adhering on the surface of the structure to be tested. The disclosed embodiments are applicable to all industrial sectors where testing of the integrity of structures is important, in particular in areonautics.

Abstract: An aircraft, the propulsive units of which include engines, and which is distinguished by reduced noise emissions, includes a wing structure fixed to an upper region of the fuselage, and a vertical tail system having at least two vertical stabilizers which are generally vertically fixed to the fuselage aftwardly of the wing structure. The engines are disposed side by side in a propulsive package disposed above the fuselage, which propulsive package includes the following: air inlet openings for the propulsive package, which openings are disposed above the fuselage between a point at the leading edge and a point at the trailing edge of an aerodynamic root chord of the wing structure; and exhaust nozzle conduit outlets associated with exhaust nozzle conduits, which outlets are formed by the structure (cowling structure) of the propulsive package, and are disposed above the fuselage forwardly of an aft terminus of the fuselage and between the vertical stabilizers.

Abstract: A comminuting machine including a frame, an infeed conveyor connected to the frame, a hammer mill connected to the frame, the hammer mill including a hammer mill housing substantially surrounding the hammer mill, a containment system substantially surrounding a comminuting portion of the comminuting machine, the containment system includes at least one cage, the at least one cage including a cage frame extending to substantially block projectile travel paths through openings of the comminuting machine, the cage frame being connected to the frame, and a drive unit movably coupled to the frame for effecting movement of the at least one cage relative to the comminuting portion of the comminuting machine without disconnecting the cage frame from the frame.

Abstract: A device for supporting a suspended ceiling includes a section that is able to support the suspended ceiling and spacers disposed between the section and the walls of the building. A removable panel is mounted on a section, the panel being able to reduce a space provided between the wall and the section at least at the location of the section bearing the aforementioned panel. At least one of the spacers may simultaneously include means for fixing the spacer to the section and means for fixing the spacer directly to a wall or to a ceiling of the building, in such a way that the spacer may be secured to the wall or the ceiling and the section may not be secured to the wall or the ceiling without a spacer.

Abstract: A device for balancing power generators, including a plurality of converters each including an elementary conversion cell with a switch driven by a comparator that receives a ramp on one input thereof and, on another input, a voltage from a driving amplifier wherein the driving amplifiers receive on their negative input an image of the cell current and have their positive input connected to an adjustment loop including a common path CS_Bus, and wherein the CS_Bus path directly connects the positive inputs of the driving amplifiers to the outputs of transconductance amplifiers associated with the elementary conversion cells.

Abstract: An electrical cable (1) provided with a sheath (2) having external marking. The marking is formed from a block (3) of two patterns (4, 5), the two patterns being consecutive along a length of the cable, said block being repeated at least twice along the length of the cable starting from the free end (12) of the cable. The disclosed embodiments also relates to a method of crimping a contact (7) onto such a cable, the external marking of the cable making it possible to know the position of the cable in the barrel and thus guarantee that the crimping that takes place will be of good quality.

Abstract: A reinforcement insert includes superposed laps of fiber which are coupled to each other by a coupling fiber which passes through the laps in order to form fiber sections wherein at least certain sections thereof are rectilinear. The fiber sections and laps are immersed in a cured resin. The total density of the fibers that make up the insert ranges from 50% to 60% of the volume of the insert and the fiber sections take up 3%-10% of the volume of the insert. A method for creating a sandwich structure includes at least one such insert.

Abstract: Provided is a traffic class of an IEEE 802.16/WiBro system. The unsolicited grant service (UGS) scheduling method with regard to a subscriber station (SS) and a base station (BS) that are disposed in a network wherein an IEEE 802.16/WiBro system is realized, the method includes: when the SS requires 1 through M (where M is a positive integer) UGS flows, and the BS serves 1 through N (where N is a positive integer) frames, the BS storing grant periods and guaranteed sizes that are granted to the M UGS flows in each N frame; and the BS comparing service capacity of a frame and a sum of guaranteed sizes of each flow belonging to the N frames, and determining if an overload occurs.

Abstract: A loudspeaker system for an aircraft cabin for passengers has a support structure, which includes multiple flexible flat elements, forming the internal walls of the cabin, and fastening devices for fastening flat elements to the support structure, so that the flat elements may oscillate. At least one acoustic driver is connected to one or more flat elements, to induce a bending movement in the one or more flat elements. The particular flat element may oscillate as an acoustic diaphragm. The acoustic driver has a film-shaped piezoelectric exciter, which is bonded flatly to the flat element. The flat element bonded to an exciter has a first cover layer, a second cover layer, and a core layer between them. The core layer is subdivided in a plane parallel to the first and second cover layers by a horizontal incision in at least one predefined area.

Abstract: A foldable rest support including a frame has at least four sections articulated together about an axis to which is associated a bearing surface, two of the sections constituting the suspension arms. According to the disclosed embodiments, two other of the sections constituting the feet of the support, each foot having a truncated V shape, and the bearing surface links the sections constituting the suspension arms in order to at least partially cover at least one of the lateral faces of the foldable support.

Abstract: A steering device for a landing gear of an aircraft, including at least one actuator and at least one rack, located alongside the landing gear strut, outside and parallel to an upper tube of the landing gear. The steering device includes bevel pinions having a first conical pinion with an axis perpendicular to an axis of the landing gear strut and which meshes with a second conical pinion coaxial with a rotary annulus so that movement of the rack parallel to the strut is transferred to the annulus perpendicular to an axis of the landing gear through the bevel pinions having an axis perpendicular to the landing gear.

Abstract: A method for the determining, on board an aircraft, of an identifier of a communications center with which an aircraft crew wishes to enter into contact, includes the following operations: a) the writing, by the crew, of a radio-communications frequency to a display unit of the cockpit of the aircraft, b) the determining of surroundings of the aircraft, c) the determining of the communications centers situated in these surroundings, d) the comparing of the frequencies of these communications centers with the frequency displayed on the display unit of the cockpit, and f) when the frequency of a communications center is identical to the displayed frequency, the display on the aircraft display unit of the identifier of said communications center having a frequency identical to the displayed frequency.

Abstract: A pitch-oscillation limitation system, applied to an aircraft having main landing gear located toward the center of the aircraft and forward landing gear located under the nose of the aircraft, wherein the system includes means for automatically applying, in the event of sudden braking, time-deferred braking between the wheels of the landing gear under the wings and the wheels of the landing gear under the fuselage, so as to reduce the amplitude of the aircraft's pitching motion.

Abstract: A model 1911 semiautomatic pistol thumb safety or decocking lever adapted to be coupled to a model 1911 receiver. The thumb safety has a selector pivotally coupled about an axis of rotation to a side of the model 1911 receiver the selector having a flat surface portion offset from the axis of rotation and contacting the side. The selector has a raised surface portion offset from the axis of rotation and facing the side. The safety is adapted to be selectable from a first position to a second position. The flat surface portion covers a swept area when the safety is rotated from the first position to the second position. The swept area is covered by the raised surface portion in either the first position or the second position.

Abstract: When an aircraft is propelled by at least one jet engine fixed in a rear part of the aircraft, at least one substantially horizontal rear aerodynamic surface, the rear horizontal surface, is arranged at the rear of the aircraft and at least one jet engine is fixed under the rear horizontal surface by an attachment mast fixed by its upper part to the rear horizontal surface and maintains, by its lower part, the jet engine. The rear horizontal surface is also the horizontal tail unit of the aircraft or a horizontal surface maintained above the fuselage. The rear surfaces and the fuselage are arranged such that the engines are installed and removed using a vertical movement of the engines, which are advantageously one, two or three in number, in the rear zone of the aircraft.