Abstract: The invention seeks to improve the integrity in respect of tolerance to damage following the spread of cracks in failure-mitigating structures of the failsafe type. To do this, the invention proposes to form a composite hybrid structure within the failure-mitigating structure. A failure-mitigating mainframe, particularly of an aircraft fuselage, equipped with a structural element made of composite according to the invention, has profiled longitudinal structural components assembled back to back by fasteners. First sides are longitudinally aligned and bonded to the fuselage skin, and the other sides are longitudinally aligned some distance away from the first sides. Fasteners couple the composite structural element to the external face of the sides of the metal components that are longitudinally aligned some distance away from the first sides.

Abstract: A composite structural member with fiber reinforcement comprising a plurality of layers oriented relative to a longitudinal direction of said member in directions including 0°, 90° and +/??, the relative proportion of layers in one of these orientations being variable along a transverse direction of said member so as to spatially adjust the rigidity of the member according to a defined distribution of mechanical stresses along this transverse axis. The rigidity of the member is adapted locally to the stress system so as to dissipate the force flux over the entire volume of said member.

Abstract: In order to generate an efficient aerodynamic braking force, whatever the speed of a vehicle such as an airplane flying in the air, the method includes a step for the production of energy by the vehicle, a step of storage of the energy produced and a step of utilization of such energy to drive a propeller which generates a force opposing the forward motion of the vehicle. Energy is produced by using the displacement of the vehicle with respect to air using a propeller driving a generator, or using the displacement with respect to the ground, using wheels driving a generator, or using generators driven by motors of the vehicle. The energy can be stored in the pneumatic, electric or kinetic form and the generation and driving means are selected according to the technology used for the storage means.

Abstract: An aircraft air-conditioning system includes an air-conditioning unit that is connected by a main fresh-air line to a mixer in order to supply the mixer with fresh air at a desired low temperature. A fresh-air branch line that is connected upstream of the mixer to the main fresh-air line has a flow cross section that is smaller than a flow cross section of the main fresh-air line. In a region of connection of the main fresh-air line to the fresh-air branch line the main fresh-air line and the fresh-air branch line are so formed that a main fresh air flow flowing through the main fresh-air line is deflected, while a fresh air branch flow flowing through the fresh-air branch line experiences substantially no deflection.

Abstract: Fluid conduit segments are provided that include, but are not limited to integrated heating systems for protection against freezing. To this effect PTC-fabric heating elements are provided that are integrated in the fluid conduit segments and that in the negative temperature range include, but are not limited to a PTC-temperature-dependent resistance. The heating system thus provides a higher output in the negative temperature range and a lower output in the positive temperature range, i.e., the heating limits itself until temperature equalization has been reached.

Abstract: A device for clamping in a slot an electronic card including contacts insertable into connectors, guided by the slot between a first position of the electronic card, the extraction position, where the contacts are not inserted into the connectors, and a second position, the insertion position, where said contacts are fully inserted into the connectors; the device includes clamping means, means of controlling the clamping means, tightening means comprising a first eccentric having a pivoting connection with the electronic card able to control the clamping means, and the tightening means in a second eccentric working with means forming a bearing surface to produce an instantaneous center of rotation of the tightening means on the bearing surface when the electronic card is in the insertion position and the tightening means are operated around the pivot axis for inserting the electronic card.

Abstract: A device (1) for the installation of a conducting component (2) on a structure (3) made from composite material, the inside of this structure (3) comprising a substance which can be ignited, which comprises an installation element (4) onto which the conducting component (2) is positioned, a conducting insert element (5), by means of which the installation element (4) is joined to the composite material structure (3) by its internal part, a conducting layer (6) arranged on the external part of the installation element (4) and a conducting fixing element (7) which joins the structure (3) and the installation element (4) to the insert element (5) and the conducting layer (6) so that the device (1) defines a low impedance current path through the conducting layer (6) and the insert element (5) through which the energy is dissipated from an atmospheric discharge to the component (2) or to the structure (3), the interior face of the structure (3) remaining isolated.

Abstract: The disclosed embodiments concern a curved structural part composed of a composite material with reinforced, continuous fibers whose cross section includes at least two wings, with said fibers extending from one wing to the other, with said structural part having a variation in the width of its section parallel to the local radius of curvature. The structural element that results from assembling the parts in the disclosed embodiments therefore has local widening of the section at the connections between the parts constituting a structural element, such as an aircraft fuselage frame, and widening at the connection with the floor profiles, if such a profile is used to make an aircraft fuselage structure. The disclosed embodiments also concern a process for manufacturing such a part, as well as a device for advantageously implementing such a process.

Abstract: The invention provides a method for producing a component (37) for aerospace, with the following method steps: supplying a lay-up arrangement (1) to be laid by means of a tape-laying machine (25), with a glass-fiber lay-up (8), which is preimpregnated with a resin matrix (10), and/or supplying a structural arrangement (12) to be laid by means of a tape-laying machine (25), with a structure (16) which is made of metal and is preimpregnated with a resin matrix (18), laying the lay-up and/or structural arrangement (1; 12) on a laminating apparatus (23) by means of a tape-laying machine (25), and curing the lay-up and/or structural arrangement (1; 12) and therefore forming the component (37).

Abstract: A cooling system for an aircraft includes an air inlet through which air from the environment of the aircraft enters a ram air channel, and an air outlet through which air emerges from the ram air channel. A heat exchanger is arranged in the ram air channel. A ventilation device is in fluid communication with the ram air channel. Also connected to the ram air channel is a distribution line to cool at least one heat-loaded component of the aircraft, in particular a cabin air conditioning system, and/or to ventilate an installation space of the at least one heat-loaded component.

Abstract: A method and a device for accessing the documentation of an aircraft according to alarms generated therein, where the documentation includes at least one document that is modifiable independently of the manufacturer of the aircraft. After having received at least one indication relating to at least one alarm generated by the avionics of the aircraft, at least one datum relating to the at least one alarm, including a link to at least one element of the documentation, is extracted and displayed.

Abstract: A device for repairing defects in an internal layer of a structure, for example, an aircraft. The device includes a cylindrical body which rotates around its axial direction, a movement conversion device housed in the cylindrical body and assembled such that it is able to move in the axial direction, a configuration device able to cause the displacement of the conversion device by an axial traveling motion, and a cutting element coupled to the cylindrical body and to the conversion device such that the cutting element is able to be made to rotate by the cylindrical body and to be made to move with a radial displacement by the conversion device between a folded position and a deployed position through an opening defined in the cylindrical body in order to machine the internal layer with a cut which depends on the axial displacement of the conversion device.

Abstract: A telescopic strut for electrically connecting a fixed structure of an aircraft to a movable structure mounted to the fixed structure, wherein the strut is adapted to be mechanically connected to the fixed structure by its one end and to be mechanically connected to the movable structure by its opposite end, the strut comprising a plurality of telescopic elements and containing a helically coiled electrical cable, wherein the cable is adapted to move between retracted and extended positions with the telescoping of the strut. Also, a method of operating an aircraft having a movable structure mounted to a fixed structure, and one or more of the telescopic struts mechanically and electrically connected between the fixed and movable structures.

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: Fuel cell systems aboard means of transport can be used for generating energy and for producing water. In order to reduce the overall weight of the system, the fuel cell is controlled or regulated in dependence on a current fill level or a limit level of the water tank, as well as a predicted future water consumption. In this way, it may be possible to minimize the water quantity to be stored in the water tank.

Abstract: Such a fuselage includes cross-members adapted for the formation of a floor, at least one of said cross-members including an upper part, a lower part, linkage for the lower part to the upper part, and at least one opening for the passage of systems which is delimited between the lower part and the upper part. The upper part of the cross-member is fastened to the fuselage and is dimensioned so as to bear the stresses to which said cross-member may be subjected when the aircraft remains on the ground. The lower part is fastened to the upper part so as to reinforce it such that when assembled, the upper part and the lower part are adapted to bear the stresses to which the cross-member may be subjected in flight conditions of the aircraft.

Abstract: Method and device for aiding the piloting of an airplane during a landing phase for ensuring, during rollout on a landing runway, that in the nominal case the airplane will stop level with a selected exit, while guaranteeing that in the case of a fault the airplane will stop before the end of the runway.

Abstract: A flow body is disclosed, particularly for aircraft. The flow body includes an outer side impinged on in a predetermined manner by a fluid in a direction of impinging flow, the flow body having on its outer side at least one flow control device including micro-perforations arranged in at least one segment of the outer side, at least one connecting passage communicated with the micro-perforations via at least one suction chamber so fluid flowing through the micro-perforations flows via the suction chamber into the connecting passage, at least one suction device having a first inlet communicated with the connecting passage, a second inlet communicated with at least one ram fluid feed line, wherein the ram fluid feed line is in a region of the flow body opposite to the direction of impinging flow of the flow body, and an outlet device for discharging the fluid.

Abstract: A method for managing data in a collaborative service-oriented workshop, which is adapted to treat objects associated with data representative of real or process data, is provided to share data and resources in an architecture of a workspace. The architecture is adapted to design complex objects and manipulate information technology objects that represent data, which may be representative of a real object or a process based on metadata representing characteristic data. The metadata includes a generic part that is common to all data, a specific part that is inherent to the type of data, and links to other objects. The links make it possible to establish, at a later time, the traceability of the data, or in other words the traceability between the different data produced or used during execution of processes.

Abstract: A pressure fuselage of an aircraft or a spacecraft includes at least two fuselage sections disposed longitudinally along the fuselage; at least one pressure calotte disposed in the fuselage so as to form a pressurized area; and an arcuate frame profile having a Y-shaped cross-section with a long profile leg connected to at least one of the at least two fuselage sections and a short profile leg extending at an acute angle from the long profile leg toward an inside of the at least two fuselage sections and attached to the at least one pressure calotte.