Abstract: A support assembly for deployment and retraction of an aero surface from an aircraft is disclosed. The assembly comprises a guide track, a primary support arm having one end coupled to a carriage mounted on the track such that the primary support arm is rotatable relative to the carriage about multiple axes, and a control arm having one end coupled to the primary support arm and a second end pivotably attachable to a fixed support forming part of the structure of the aircraft. The assembly being configured such that, when the carriage is driven along the guide track, the control arm causes the primary support arm to pivot about said multiple axes to deploy and/or retract an aero surface pivotally attached to an opposite end of the primary support member along an arcuate path.

Abstract: A power plant includes a nacelle with a bypass turbojet engine having a ducted fan with a low compression ratio. A secondary flow, drawn in and accelerated by the fan, is channeled through a secondary duct installed in the nacelle between the inner surface of the nacelle and the outer surface of the turbojet, toward a fan nozzle. The power plant has at least two moving parts on either side of a vertical plane of symmetry of the nacelle, at least one moving part being able to adopt one of a discrete number of positions, the moving part containing or releasing a portion of the secondary flow, depending on the moving part's position. A control unit controls a different displacement of each of the moving parts between their possible positions in order to create asymmetry of the moving parts relative to the vertical plane of symmetry.

Abstract: An antenna for electromagnetic compatibility testing, that includes an upper plate and a lower plate having parallel longitudinal axes, maintained at a distance from each other, and mechanically connected to each other at each of their longitudinal ends by longitudinal plates. The upper and lower plates and longitudinal plates define a space. The upper and lower plates and the longitudinal plates are mounted so as to be capable of movement relative to each other to define a space having dimensions that can be modified, wherein the distance between the lower and upper plates can be modified and/or the length of the lower and upper plates can be modified.

Abstract: The invention relates to a device for supporting a door which is pivotably received in a fuselage airframe of an aircraft, with a counter bearing arranged in the region of a doorframe and a thrust bearing located opposite in the region of the door. According to the invention, the counter bearing has a planar counter bearing surface and the thrust bearing has a mounting in which a planar thrust bearing surface which can tilt about at least one spatial axis is received, the counter bearing surface lying against the thrust bearing surface at least in some regions when the door is closed. Because of the thrust bearing surface which can be tilted in at least one spatial direction, the counter bearing always lies against the thrust bearing over the entire surface areas thereof, irrespective of any manufacturing tolerance deviations between the doorframe and the door or the bearing on the fuselage airframe, in such a way that optimal force transfer is ensured.

Abstract: A method of manufacturing two or more composite parts, the method comprising: assembling the composite parts on a mandrel by laying a series of layers of bands of composite material onto the mandrel with a placement machine,—rotating the mandrel as the bands are laid onto the mandrel; attaching two or more debulk frames (10, 11) to the mandrel between opposed edges of the composite parts after the composite parts have been assembled; wrapping the mandrel, debulk frames (10, 11) and composite parts in a debulk bag; heating the composite parts,—forming a vacuum between the mandrel and the debulk bag so that the debulk bag is sucked into voids between the debulk frames and the heated composite parts and progressively presses against the heated composite parts whereby excess material is squeezed by the debulk bag towards their opposed edges; and removing the debulk bag and the composite parts from the mandrel.

Abstract: An aircraft wing assembly comprising: a wing; a spoiler pivotally attached to the wing; and a spoiler deployment mechanism. The deployment mechanism comprises a scissor linkage mechanism comprising an upper link pivotally attached to the spoiler at an upper pivot, and a lower link pivotally attached to the wing at a lower pivot and to the upper link at a central pivot. An actuator is pivotally attached to the wing at a proximal pivot and to the scissor linkage mechanism at a distal pivot. The actuator is adjustable between expanded and contracted configurations so as to vary the distance between the proximal and distal pivots. This opens up the angle between the upper and lower links of the scissor linkage mechanism and pushes the spoiler up into the air-stream above the wing.

Abstract: The present invention relates to an aircraft load frame (1) made of a composite material, characterized in that it comprises two side elements (2, 3) and a base element (7), the side elements (2, 3) being joined at the inner part of the frame (1) by means of the base element (7) and each of the side elements (2, 3) comprising a leg (4) joining the frame (1) to the aircraft fuselage skin, a web (5) and a lower flange (6) joining the web (5) and the base element (7).

Abstract: A rib bay platform for use in an aircraft rib bay, is adjustable in length (for example it comprises two telescopically mounted sections. The platform comprises a first end configured for mounting on a stringer of the rib bay (for example by an interference fit), and a second end configured for mounting on another stringer of the rib bay (for example on feet mounted on ball-and-socket joints). A method of operating in an aircraft rib bay comprises the steps of providing a rib bay platform of adjustable length; adjusting the length of the platform; mounting the platform between the two stringers; whereby a person may then operate inside the aircraft rib bay while being supported on the platform.

Abstract: A process for determining the distribution of seats of a passenger cabin, whereby the cabin includes at least one row of seats arranged essentially one behind the other along a longitudinal axis, and the cabin includes element for arranging each seat in a position on the ground among a set of possible positions spaced longitudinally at known intervals, includes a phase for optimization of the spacing of seats according to an overall comfort function of passengers, taking into account bodily characteristics that are specific to at least some of the passengers, including the length of the front segment of the passengers' legs, and the purpose of the optimization is to maximize a comfort function taking into account in particular the space that is free for each passenger between his knees and the seat that is located in front of him. The purpose of the invention is also the related device.

Abstract: A method for optimization of the avionics platform of an aircraft, intended to implement a set of avionics functions. The association between the platform's functional architecture elements (functions, functional links) and the elements of its equipment architecture (equipment, network paths, direct physical links) are formalized by sets of constraints in the form of linear inequalities of decision variables. Certain segregation or co-location functional constraints are also envisaged. Optimization of the avionics platform is achieved through the minimization of cost functions which are linearly dependent on said decision variables. This minimization under constraints is achieved in an effective manner by the Simplex algorithm.

Abstract: An actuation system includes: two hydraulic actuators, each being coupled to a load-bearing structural component and to an elevator, and displaceable relative to the load-bearing structural component for the operation of the elevator; a first control valve device to control the first actuator; a second control valve device to control the second actuator; a control and monitoring unit that determines and transmits appropriate command signals to the control valve devices to execute appropriate control movements for the operation of the actuators; a locking device coupled to the first actuator to secure the first actuator a locked state, which is hydraulically connected with the first hydraulic system and the second hydraulic system via an hydraulic OR-circuit, where in normal operation the locking mechanism is in its unlocked state, and in the event of a failure of both hydraulic systems the locking mechanism secures the first actuator.

Abstract: Disclosed is a method of manufacturing a composite sheet. The method comprises (a) irradiating a sheet of fibers and a matrix film at an irradiation zone with a plasma at substantially atmospheric pressure, and (b) impregnating the sheet of fibers with the matrix at an adhesion zone. The processes (a) and (b) are performed simultaneously, and the matrix film is irradiated with a plasma at said irradiation zone after being unwound from a roller and prior to entering said adhesion zone.

Abstract: A method and apparatus are disclosed for testing a valve control system in an aircraft fuel supply system having a plurality of control valves, wherein the control system includes relay means for outputting control signals to each of the plurality of control valves. The method includes providing connection means for electrically connecting a test device to the control system relay means, connecting a test device to the relay means such that the test device is adapted to receive control signals output by the control system to any one of the plurality of control valves, detecting an electrical control signal output from the relay means to any one of the plurality of control valves, and identifying the particular one of the plurality of control valves to which a detected control signal is output by the relay means and identifying the nature of the control signal output to that particular control valve.

Abstract: A joint with a first component; a second component; and an electrical assembly which provides an electrical pathway between the first and second components with an electrical resistance between 100 k? and 10 M?. The electrical assembly comprises a bonding lead; and a pair of connection assemblies each connecting the bonding lead to a respective one of the components. Each connection assembly comprises: a fastener with a shaft which passes through a hole in the component and a hole in the bonding lead, the hole in the bonding lead passing between an inner face of the bonding lead which faces towards the component and an outer face of the bonding lead which faces away from the component, and a washer which is carried by the shaft of the fastener and engages the component and the inner face of the bonding lead. Each washer provides the path of least electrical resistance between the bonding lead and a respective one of the components, each said path having an electrical resistance between 50 k? and 5 M?.

Abstract: A set of equipment items for an aircraft including a video transducer and at least two head-up display devices, wherein the video transducer and/or each HUD device is/are capable of defining the image to be projected by the HUD device on the basis of the display field of the HUD device and of one or more HUD/transducer errors, each HUD/transducer error being defined as being the difference between the HUD error of the corresponding HUD support around a direction and the transducer error around this same direction, the HUD error of an HUD support around a direction being the angular difference around this direction between the line of sight of the HUD support and a measuring reference line, and the transducer error around a direction being the angular difference around this direction between the line of sight of the transducer support and a measuring reference line.

Abstract: A method and device performs onboard monitoring of a horizontal position of a taxiing aircraft, in which the monitoring of the horizontal position is based on separately determined height differences of the aircraft. A predetermined threshold value is compared with a first height difference calculated using repetitively determined first current height positions received by an onboard positioning device over a first duration. The predetermined threshold value is also compared with calculated second height differences calculated from two successively measured second current height positions determined by an altimeter over a second duration that is less than or equal to the first duration. A warning signal, signaling a problem with the reliability of the monitored horizontal position of the taxiing aircraft, is emitted in the event none of the second height differences is greater than the threshold value, and the first height difference is greater than the threshold value.

Abstract: A device for using a programmable component carrying out at least one logical function in a radiative environment includes: a mechanism for error detection in a data-storing working memory space actually serving to carry out each logical function of the device through use of data stored in at least one reference memory space storing a data copy implemented by at least one logical function; a mechanism blocking at least one output of at least one logical function of the component for which an error in the data implemented by the logical function is detected by the mechanism for detection; and a mechanism correcting each error detected in the working space.

Abstract: An a.c. signal generator is provided with a first circuit (B1) capable of generating alternations of a first a.c. signal (S1) between a first potential (V+) formed by a first voltage source and a second potential (V?). A second circuit (B2) is capable of generating alternations of a second a.c. signal (S2), phase-shifted relative to the first signal (S1), between the first potential (V+) formed by the first voltage source and the second potential (V?). Such a generator can be used, for example, in a flight control calculator of an aircraft.

Abstract: An aircraft engine attachment pylon including a rigid structure forming a caisson, and a rear engine attachment including an attachment body and at least one lateral fitting arranged on either side of the caisson. Each fitting includes a first portion pierced by first assembly holes enabling it to be fixed to the caisson, and a second portion defining a fixing surface of the body. The second portion includes a housing orifice receiving a self-locking nut cooperating with a screw supported against the body and, in transversal section, an axis of the screw passes through the first holes.

Abstract: An acoustic treatment structure related to a leading edge onto which an aerodynamic stream flows, in particular at an air intake of an aircraft nacelle, includes—from the outside to the inside—at least one acoustically resistive substructure (30), at least one alveolar substructure including strips (32) of cells, arranged in a direction that is essentially perpendicular to the direction of flow of the aerodynamic stream, and at least one reflective layer (34). Each strip (32) includes a first part that insulates the strips from one another, called a support, with a U-shaped cross-section in the longitudinal direction, whose open surface that is opposite to the bottom of the U shape is flattened against the acoustically resistive substructure (30), and at least a second part, called partitioning, making it possible to partition the space that is delimited by the support and the acoustically resistive substructure (30) into cells.