Abstract: A support trolley for supporting a door of an aircraft to permit working on the door comprises a frame with an upper support portion having at least two pairs of support bolts for engagement with locking bolts of the door to be supported so that the door is supported at each lateral side by a pair of support bolts. For engagement with the locking bolts the support bolts comprise recesses at their free ends.

Abstract: An aircraft has a bearing structure, the bearing structure having at least one central fuselage and two pylons each situated at a distance laterally from the fuselage. In addition, the aircraft has a wing structure, at least four hub rotors, and at least one thrust drive. Each hub rotor is fastened to the bearing structure, has a propeller having two propeller blades, and produces, through rotation of the propeller, an upward drive force acting in the vertical direction on the aircraft. The thrust drive is produces a thrust force acting in the horizontal direction on the bearing structure. The pylons each have two hub rotors, the hub rotors being configured to arrest respective propeller blades of a hub rotor in a position relative to the pylons. In the arrested position, the propeller blades of a hub rotor do not extend beyond the outer dimensions of the pylons.

Abstract: A flexbeam unit for a multi-blade rotor of a rotary wing aircraft, said flexbeam unit defining a predetermined number of torsion elements that are connectable with associated rotor blades, at least one torsion element comprising a flexbeam element having an associated longitudinal direction and comprising inner layers of a first fiber reinforced material that are embedded between outer layers of a second fiber reinforced material, said outer layers being composed of main plies comprising unidirectional fibers and said inner layers defining a cross section profile center in said associated longitudinal direction, said cross section profile center being composed of interconnected bias plies comprising fibers that are oriented transversely relative to said unidirectional fibers.

Abstract: A device for the manufacture of a fiber-reinforced thermoplastic composite module from a multiplicity of module components, which are continuously moved in the feed direction and are connected together section-by-section. The device includes a tool mold configured and arranged to be continuously traversed in the feed direction for purposes of positioning module components relative to one another. A pressure application head is configured and arranged to be traversed in the feed direction and in the counter-direction for purposes of connecting the module components. The pressure application head is configured and arranged to move at the same speed and in the same direction as the continuously moving tool mold, and then in an opposite direction, in order to connect to each section of the fiber reinforced thermoplastic composite during reciprocal movement.

Abstract: A method for implementing a simulation test comprising generating a first simulation context comprising a display of a first portion of a first virtual environment defined over 360° on a screen, the portion being projected over an angle of 180° and an avatar generated at a GPS position in the virtual environment. A generation of a second simulation context is activated comprising retrieving the position of the head and its orientation from a sensor, generating a second portion of the first virtual environment computed according to the position and orientation of the captured head, displaying the second portion on an optical unit of the helmet. The first and second portions coincide over an angle corresponding to that of the second portion for at least one position and one orientation of the predefined head.

Abstract: A device for absorbing kinetic energy for an aircraft structural element undergoing a dynamic impact. The device includes an outer enclosure made from a braided composite material configured to preserve its integrity after an impact, and a foam core contained in the outer enclosure and to at least partially fill the outer enclosure. The foam core configured to at least partially absorb the kinetic energy generated by the impact. Reinforcing elements include at least one dry composite fiber preform integrated into the foam core to dissipate, in combination with the foam core, the kinetic energy generated by the impact. A method for integrating the device for absorbing kinetic energy.

Abstract: A material for use in vacuum bagging a component. The material includes a compound sensitive to moisture, such that an exposure of the compound to moisture or wetting causes a physical and/or chemical change in the compound that is visually detectable in the cover material. A method of leak detection during vacuum bagging involves the steps of: arranging a component in a vacuum bagging assembly, such as to form a fiber-reinforced plastic component; arranging a material according to the invention in the vacuum bagging assembly such that the compound sensitive to wetting or moisture is under, or on an inner side of, a sealing film or vacuum bag of the assembly; applying a vacuum to the vacuum bagging assembly to evacuate a space containing the component and sealed by the sealing film or vacuum bag; and wetting an outer surface of the sealing film or vacuum bag.

Abstract: The subject matter disclosed herein relates to a method for assembling at least one panel and frames for producing part of an aircraft fuselage, the method including shaping the panel on support surfaces of a tool, wherein it includes holding each frame clamped against at least one sliding support surface arranged in a transverse plane, the sliding support surfaces of the various frames and the support surfaces being secured to the same tool and positioned relative to one another, and in putting in place permanent attachment elements for connecting the panel and the frames. The subject matter disclosed herein also proposes a tool for implementing the assembly method.

Abstract: A fixture for electronic devices includes a substantially planar receptacle, and a mounting framework arranged at least partially at the surrounding edges of the receptacle, the mounting framework having at least one framework component made from a shape memory material and/or an electro-active polymer, wherein the framework component exhibits a relaxed state and a triggered state in which the framework component is moved or flexed inwardly into the area of the receptacle.

Abstract: A stopper for a tank having an opening includes a body which is provided to be fixed in the opening and which has a hole, a membrane which is fixed to the body and of which a portion completely blocks the hole, a core which is fixed to the portion of the membrane which blocks the hole, and stop means which are provided to permit a movement of the core between a blocking position which corresponds to the non-broken membrane which blocks the hole, and an open position which corresponds to the broken membrane which is spaced apart from the hole, and to keep the core fixedly joined to the body in an open position. The knowledge of the characteristics of the membrane enables the force from which the stopper opens to be known.

Abstract: A winglet comprising a tubular main spar with forward and aft main spar webs joined by upper and lower main spar caps; a front spar with a front spar web, an upper front spar cap, and a lower front spar cap; an upper skin joined to the upper main spar cap and the upper front spar cap; and a lower skin joined to the lower main spar cap and the lower front spar cap. The winglet is manufactured by co-curing the upper skin to the upper main spar cap and the upper front spar cap; and co-curing the lower skin to the lower main spar cap and the lower front spar cap.

Abstract: A method for predicting temperatures tolerable by a component, a piece of equipment or a vehicle structure. This method includes the steps of determining, for each piece of equipment, component or structure of the vehicle, such as an airplane, a temperature spectrum depending on a plurality of extrinsic parameters measured during a full operating cycle of the airplane, by taking into account, for each piece of equipment, component or structure, possible combinations of the extrinsic parameters and setting aside unlikely combinations of the extrinsic parameters, determining, for each piece of equipment, component or structure, the probability of occurrence of the spectrum during the full airplane operating cycle, and defining a database including the temperature spectra so as to predict the lifetimes of the piece of equipment, component or structure and redefine weather and operational standards indicating extreme temperatures and their probability of occurrence obtained with the measured extrinsic parameters.

Abstract: An aluminum material for producing light-weight components includes aluminum (Al), scandium (Sc), zirconium (Zr) and ytterbium (Yb), where a weight ratio of scandium (Sc) to zirconium (Zr) to ytterbium (Yb) [Sc/Zr/Yb] is in a range from 10/5/2.5 to 10/2.5/1.25.

Abstract: A joining part with a wing comprises a through bore defining a fastening direction perpendicular to the wing. The wing comprises at least one non-through pocket configured to reduce the stress gradient in a peripheral zone of the through bore and/or at least one relief configured to reduce the stress gradient in a peripheral zone of the through bore, the non-through pocket forming a cavity in the thickness of the wing and comprising a curved side at a distance from the peripheral edge of the through bore. The joining part may be part of a lug, such as, for an aircraft fitting.

Abstract: A pipe treatment system for a supply unit is provided. The pipe treatment system comprises a fresh water inlet pipe, a tap for fresh water, a controllable tap valve, and a control device for the pipe treatment control system. The controllable tap valve is arranged between the fresh water inlet pipe and the tap for fresh water. The control device for the pipe treatment control system is connected to the controllable tap valve so as to place the controllable tap valve in a pipe treatment state when there is a pipe treatment signal at the control device, so as to provide a more reliable pipe treatment system, for example for disinfection or descaling.

Abstract: A method of generating electricity with a fuel cell includes a phase in which the cell is primed; and a phase in which the cell functions at a stable rate, during which the cell, fed with a hydrogenated gas, generates electricity and heat. In order to prime the cell, it is fed with a hydrogenated gas including at least 70 vol. % hydrogen, generated by self-sustaining combustion of at least one hydrogenated gas-generating solid pyrotechnic charge; and while it is operating at a stable rate, the cell is fed with a hydrogenated gas containing at least 85 vol. % hydrogen, generated by thermal decomposition of at least one hydrogenated gas-generating solid pyrotechnic charge; a portion of the heat produced by the operating cell being transferred to the at least one solid charge in order to start and maintain the thermal decomposition thereof.

Abstract: A method of determining a depth of a hole formed in a work piece is disclosed. The method includes determining the hole depth based upon a load signal indicative of a load on a tool forming the hole during the forming of the hole. The hole depth determined is then adjusted with an offset and component specifications are combined with the hole length to determine a component specification for use in the hole to fix components together. At least a part of the depth determination and component specification can be carried out automatically in a computer, for an array of holes.

Abstract: A system including a load factor control module for calculating a deflection order on manual actuation of a control column by a pilot of the aircraft and transmitting that deflection order to at least one elevator of the aircraft, a longitudinal attitude control module for maintaining the longitudinal attitude of the aircraft at a target attitude in the event of absence of manual actuation of the control column by the pilot during a flight, and a transition management module for determining and storing a present longitudinal attitude value of the aircraft at a recording moment and transmitting that longitudinal attitude value to the longitudinal attitude control module for the longitudinal attitude control module to use the longitudinal attitude value as the target attitude.

Abstract: A method of detection and removal of auxiliary material suitable for the manufacturing of an aircraft element includes providing an auxiliary material having at least one detection label, scanning the element with a label detector suitable to detect the detection label once the element has been manufactured, detecting the auxiliary material by means of a warning signal emitted by the label detector and removing the auxiliary material from the element. An auxiliary material suitable for the manufacturing of an aircraft element includes a detection label.

Abstract: The disclosure refers to a propeller blade for an aircraft engine that includes an airbag system contained inside the blade and comprising at least one bag and at least one gas generator, the at least one gas generator in fluid communication with at least one bag for inflating the bag, a detecting system for detecting a rupture of a part of the blade, a trigger for activating the at least one gas generator when the rupture is detected by the detecting system, and the blade skin being configured for allowing the at least one bag to pass through the blade skin for being expanded outside the blade upon the bag inflation by the gas generator.