Abstract: The invention relates to a method of assembling composite material parts (10, 12). The method makes provision for: mounting (S6) the parts for assembly under stress on a stand (14), which parts have been partially polymerized; heating (S7) these parts so as to polymerize them completely, thereby enabling the stresses in the parts to be relaxed and enabling them to match the shape of the sand; cooling (S8) the parts; and assembling (S9) in conventional manner the parts as cooled in this way.

Abstract: The ventilation device according to the invention includes a fan and an inverter. The fan comprises a rotary electrical machine and a wheel for setting an air flow into motion, integral with the rotary machine to set it in rotation. The inverter is connected to the rotary machine and, in one motor power mode of the ventilation device, is suitable for forming the supply current of the rotary machine. The inverter is suitable for being connected to a power supply network. The inverter is reversible and is, in a generating mode of the ventilation device, suitable for converting the electrical energy supplied by the rotary machine when it is driven mechanically by the wheel and injecting said converted electrical energy into the power supply network.

Abstract: An aircraft includes a heat exchanger between a first fluid that flows into the narrow pipes of the exchanger and that is able to contain solid elements that can melt, and, a second fluid to be cooled. The heat exchanger includes a device for preheating the first fluid upstream from the pipes of the exchanger, a number of pipes arranged in at least one plane that intersects the direction of flow of the first fluid, whereby the spacing between two adjacent pipes is suitable for retaining the solid elements of large dimensions and for allowing them to pass only when they have melted at least partially.

Abstract: The method of communication between an airplane and the ground, the aircraft communicates by radiowaves with the ground via at least one satellite and in a frequency band extending from 5030 MHz to 5091 MHz, bounds included, using a WiMax type transmission standard. The invention also provides an on-board communications terminal for an aircraft, suitable for communicating by radiowaves with the outside of the terminal in a frequency band extending from 5030 MHz to 5091 MHz, bounds included, in application of a WiMax type transmission standard.

Abstract: An air discharging device (20) for an aircraft turbine engine, comprising at least one door (24) displaceable between an open and a closed position of a corresponding orifice (30) and comprising two valves (26, 28), which delimit between them a conduit (68) for guiding a portion (74) of the secondary flow (76) outwards in the downstream direction, and which are integral with each other and are hinged around a pivot axis (58), so that in said open position, the upstream end of said internal valve (26) protrudes from the inner side relative to the internal surface (12), the downstream end of said external valve (28) protrudes from the external side relative to the external surface (14), and said internal valve (26) is spaced away from the fixed structure (22) so that an air passage exists downstream of said internal valve (26), between the latter and said fixed structure (22).

Abstract: The device for controlling the display of a radar image on board an aircraft, in particular a weather radar image, is suitable for performing at least one predetermined test on a radar echo in order to decide on a representation corresponding to the echo in a radar image display.

Abstract: The device for controlling the display of a radar image on board an aircraft, in particular a weather radar image, is suitable for performing at least one predetermined test on a radar echo in order to decide on a representation corresponding to the echo in a radar image display.

Abstract: An aircraft floor portion includes crossmembers. Each crossmember comprises a top partial crossmember and a bottom crossmember, with at least one gap being left between the top partial crossmember and the bottom partial crossmember of each crossmember.

Abstract: The object of the invention is in particular a device for execution of applications (510) in an aircraft information-processing system (500), permitting the simultaneous execution of at least two distinct applications, the said information-processing system comprising shared calculation and storage resources. The device comprises software segregation means capable of creating at least two distinct information-processing environments (505), a partition of the said calculation and storage resources being allocated to each of the said at least two environments in such a way that the execution of one of the said at least two applications in one of the said at least two environments does not have any effect on the execution of the other of the said at least two applications executed in the other of the said at least two environments. Another object of the invention is a method for employing such a device.

Abstract: In the method of accessing an information system of an aircraft the system receives an authenticator request from a connector of the aircraft; the system determines whether the connector presents a predetermined characteristic; and in the event that the system determines that the connector does indeed present the predetermined characteristic, the system sends an authenticator to the connector. Provision is also made for: the system receives an authenticator the system determines whether the authenticator is valid; and in the event that the system determines that the authenticator is indeed valid, the system authorizes access to the system from a connector of the aircraft from which the authenticator was sent.

Abstract: The aircraft passenger seat headrest (20) includes a carrier (21) and a helmet (22) for at least partially housing the head of the passenger. The helmet is attached to the carrier and is movably mounted in relation to the carrier (21). Said helmet includes a body and at least one portion (32, 34) that is movably mounted onto the body to extend the latter.

Abstract: The invention has as its object in particular a method and a device for aiding in the diagnosis and in the decision on operation of an aircraft comprising means for detection of failures relating to the pieces of equipment thereof. After having received (400) at least one alert linked to the detection of at least one failure relating to at least one piece of equipment of the said aircraft, the said at least one alert comprising at least one indication relating to the said at least one failure, and at least one information item relating to the next mission of the said aircraft, a database comprising a minimum equipment list and operating conditions and/or limitations associated with the operation thereof is accessed.

Abstract: An aircraft including at least one engine having counter-rotating rotors, the engine or at least one of the engines having imbalances associated with at least one ellipse. The aircraft includes at least one vibration damper attached in an arrangement such that, at a given engine speed and for at least one given common direction of a large axis of the ellipse or at least one of the ellipses, a speed related to the two ends of the damper is higher than for any other arrangement of the damper.

Abstract: In the method of fastening aircraft parts together, the following steps are performed: crimping an element onto at least two parts so as to fasten them together; and screwing a screw into the element through at least one other part so as to fasten all the parts together and so as to place a head of the screw in a flush position relative to the other part.

Abstract: Equipment items installed on board vehicles and more particularly to a method for operating such an on-board equipment item, the method including an on-board micro software program that is executed during power-up of the on-board equipment item to achieve secure processing with the aid of sensitive security data. In particular, the method includes connecting a secure module including the sensitive security data necessary for secure processing to the on-board equipment item, and authenticating the secure module by the micro software, in such a way as to furnish the micro software with the sensitive security data for subsequent execution of the secure processing.

Abstract: A thrust reverser for a double-flow nacelle that has a cowling, with the thrust reverser having an internal door and an external door designed to be made within the thickness of the cowling. The reverser also has means for simultaneously displacing the doors between a first position called the rest position, in which the doors are integrated into the cowling so as to form an aerodynamic continuity with the external wall and the internal wall of the cowling, and a second active position, in which the doors are open so that the internal and external doors extend toward the inside and toward the outside of the nacelle, respectively, thus at least partially blocking the annular channel of the secondary flow, to deflect the secondary flow and to generate a thrust reversal, with the means being designed to be received in a compartment arranged inside the cowling formed by the doors in the rest position.

Abstract: A device for shutting an aircraft jettisoning circuit includes a coupling endpiece. The endpiece carries a sealing gasket and means suitable for modifying a dimension of the gasket.

Abstract: The aircraft includes: a floor; a top panel of a central wing box; at least two rails and at least two beams, the rails and the beams extending between the floor and the panel; and at least one reinforcement suitable, independently of the rails, for taking up a force acting at the level of the floor and for transmitting said force to the beams and/or to the top panel.

Abstract: The present invention relates to an on-board aeronautic system intended to be dynamically reconfigured, especially an on-board information system, and to an associated method as well as to an aircraft comprising such a system. In particular, the system comprises a plurality of heterogeneous equipment items, at least part of the said equipment items being reconfigurable, and comprises a reconfiguration management center set up to receive state messages from the said plurality of equipment items and to emit reconfiguration messages destined for the said reconfigurable equipment items as a function of at least the said received messages, the said state messages being emitted according to the same format by monitoring means encompassed in each of the said equipment items, the reconfigurable equipment items encompassing reconfiguration means capable of processing at least one of the said reconfiguration messages in order to reconfigure the said associated equipment item.

Abstract: The invention relates to a bleed air supply system and a safety device for closing a valve in at least one of the several bleed air supply lines depending on an alarm signal that indicates an opening in at least one of the several bleed air supply lines. To stop the supply of bleed air irrespective of the type of the bleed air source, the safety device comprises a filter device for generating the alarm signal depending on the ground connection signal and on an opening signal from an opening signal device that indicates any opening of the bleed air supply line that is connected to the high-pressure ground connection.