Abstract: An aircraft including a fuselage, a cockpit and a cabin, wherein the cockpit is situated below the cabin and outside the nose, such as a lancet-shaped nose, of the aircraft and may extend to a front end of the aircraft, and the viewing surfaces in the cockpit may be entirely formed of digital display screens.

Abstract: In order to limit the number of openings in an aircraft fuselage and to reduce the mass thereof, the invention makes provision for an item of aircraft fuselage equipment which is intended to be mounted in an opening of the fuselage, the item of equipment being configured to block/release an access passage which affords access to the inner side of the aircraft and which also comprises a discharge control valve for pressurization air.

Abstract: An efficient method for manufacturing a partially cured composite component intended to be joined with other component or components to form a composite structure and a manufacturing method of the composite structure. The partial curing of a composite layup is achieved using a mold comprising heat conductive elements and insulating elements and applying heat and pressure over the mold. The heat conductive elements are used to transmit or dissipate heat to/from the composite layup. The insulating elements are used to prevent the transmission or dissipation of heat to/from the composite layup.

Abstract: A method and a tool for remotely pivoting an element mounted in a structure is provided. The method includes exerting a lever effect on the element by way of a control bearing on the structure coupled to a connection engaged with the element to cause it to pivot in a pivoting plane. The method also includes applying an angular offset to this connection in a plane different from the pivoting plane, in which the lever effect is produced, in order to render the control remotely operable.

Abstract: A tool to screw/unscrew a screwing element, having a module comprising a lever extending radially from and rotatable around a drive axis, a first transmission element rotatable around the drive axis by the lever, a transmission module comprising a second transmission element cooperating with the first element, a third transmission element rotatable around a screwing/unscrewing axis parallel to, and spaced from, the drive axis, a transmission system comprising an element transmitting the second element rotation to the third element, and an adapter with a fourth transmission element cooperating with the third element, and a cavity confirming to the screwing element. The tool includes a wedge with at least one rotatable adapter mounted thereon. The wedge comprises two support surfaces on planes parallel to the drive axis and disposed opposite one another to define a groove receiving an end of the transmission module on the third element side.

Abstract: A method for testing a component part of an aircraft comprises the steps of determining at least one first test value of the component part of the aircraft and/or at least one first test value of a comparable component part of a further aircraft for at least one test parameter, inputting the first test parameter and the first test value into a pattern recognition system, which produces an inner correlation between the first test parameter and the first test value. The method further comprises the steps of defining at least one second test parameter, inputting the second test parameter into the pattern recognition system in order to determine a second test value by means of the inner correlation, checking whether the second test value falls within the predefined value range, and determining a third test value of the component part of the aircraft for the second test parameter if the second test value falls within the predefined value range.

Abstract: An aerodynamic audit system is provided for performing an audit process of an aircraft using a computing device via a network. An inspection module inspects at least a portion of the aircraft for locating and measuring any aerodynamic defects present by generating an inspection list having a predetermined inspection path. A display device displays the inspection path and accepts a measurement of any located aerodynamic defect. A fuel penalty estimation module calculates an estimated fuel penalty of the aerodynamic defect based on the measurement of the corresponding aerodynamic defect. A defect correction analysis module analyzes the aerodynamic defect based on a cost and benefit assessment. A findings collection module generates an audit report based on the inspection and analysis of the aerodynamic defect. A database stores data associated with the aerodynamic defect and the corresponding fuel penalty based on the cost and benefit assessment.

Abstract: A fitting for an aircraft bracing device including anchor points, wherein the fitting includes a face able to press against the aircraft and at least one guide hole for a connecting element able to collaborate with an anchor point, a slider able to move in a translational movement parallel to a first direction parallel to the face of the fitting and a connection between the slider and the connecting element which allows a movement in a second direction different from the first direction and parallel to the face of the fitting so as to align the connecting element with an anchor point.

Abstract: A display management system is provided for displaying a graphical representation of flight envelope information of an aircraft. Included in the display management system is a control module being coupled to the display management system and programmed to control the graphical representation including at least one flight envelope protection attribute. A signal detection module receives signals from a plurality of sensors of the aircraft, and the received signals include associated parameter values for the at least one flight envelope protection attribute. A protection selection module selects the at least one flight envelope protection attribute based on the received signals and parameter values. A display module displays the at least one flight envelope protection attribute on a display screen in relation to a flight control law state stored in a database using a display model of the aircraft from an elevational view based on the received signals and parameter values.

Abstract: Automating the forewarning of risks incurred when working on an aircraft, and a forewarning system. The system comprises an identification module configured to identify a set of risky zones in the aircraft and its environment during current work on the aircraft by a set of operatives, a location module configured to locate a position of each operative during the current work, and an alert module configured to generate an alert when an operative is situated in a risky zone.

Abstract: A bridge configured to allow access by an operative to an aircraft compartment via a manhole formed in a wall. The bridge comprises an overlapping section which includes at least one plate, a transverse runner beneath the plate or plates with at least one groove configured to receive a lower edge of the manhole, at least a first support configured to rest on one side of the wall and at least a second support configured to rest on the other side of the wall.

Abstract: A method of configuring an aircraft management system comprising the following steps, implemented by a configuration module integrated into the avionic system of the aircraft cockpit: obtaining at least one item of computation data for computing at least one configuration parameter of the management system, sending, to a computation module that is independent from the avionic system of the aircraft cockpit, a request for computing said at least one parameter on the basis of said at least one item of computation data, receiving, from said computation module, said at least one computed parameter, and configuring said management system with said at least one received computed parameter.

Abstract: A power supply device or system for aeronautics, having a hydrocarbon supply for supplying an engine with hydrocarbon fuel and a hydrogen supply having a fuel reformer for producing hydrogen from hydrocarbon fuel from said hydrocarbon supply. The hydrogen supply is connected to a hydrogen-powered fuel cell for producing electric power and to a hydrogen injecting system for injection of hydrogen into a combustion chamber of the engine. Further, the invention relates to an aircraft having an engine that can be supplied by that power supplying device or system, and to a method for operating said engine.

Abstract: The present invention relates to a panel, especially for a component having a box structure in an airplane airfoil, comprising a surface shaped body and grid-like reinforcement bars protruding from the body on one side of the body, and the body and the grid-like reinforcement bars are integral molded. Since the body and the grid-like reinforcement bars of the panel are integral molded, no additional connecting process is required, so that the disconnection phenomenon as happened between the skin and the stiffener or stringer of the prior art would not occur, and the assembly complexity can be decreased.

Abstract: A method for assisting the piloting of an aircraft on the ground comprises the steps of obtaining a panoramic view of at least one area adjacent to the aircraft, isolating an image corresponding to a part of the panoramic view and which is selected according to an orientation desired by the pilot, and displaying the image on a display device visible by the pilot. A system for the implementation of the method is also provided.

Abstract: The present invention relates to an anti-rotation device for a pivot for rotatably connecting at least two fittings, the pivot having a polygonal pivot head, comprising: an inner anti-rotation part for preventing the rotating of a pivot head, which comprises at least one leg, which abuts against respective one of the side faces of the pivot head in the mounting state; an outer anti-rotation part for preventing the rotating of the inner anti-rotation part, which comprises at least one wall, each of which abuts against the respective one of the at least one leg in the mounting state; and a fixer for fixing the inner anti-rotation part to the outer anti-rotation part.

Abstract: A method for installing an item of equipment in a cabin, includes: determining the actual position of each anchoring location provided for the equipment in a first reference system and of each fixing location of the equipment in a second reference system, positioning the second reference system relative to the first reference system, prior to the installation of the equipment in the cabin, adjusting each adjustable connection in accordance with at least one characteristic determined from the actual position determined for each anchoring location and for each fixing location, positioning the adjusted adjustable connections which connect the equipment to the cabin.

Abstract: An interaction method in an aircraft cockpit between a pilot and his environment. The cockpit includes a plurality of activation zones which each comprise an element of interest which is connected with the cockpit or the external environment thereof and which can be activated on the basis of the interaction of at least one movable member of the pilot's body with the activation zone. The method includes the steps of establishing, in a manner repeated over time, the spatial position of the movable member of the pilot's body and a comparison between such spatial position and the position of the activation zones and automatic activation of the activation zone in the environment of the pilot in order to inform the pilot about the availability of further interaction with the element of interest involved. The method improves the interaction between the pilot and his environment connected with the cockpit.

Abstract: A taxiing system for an aircraft including an undercarriage having a wheel, includes an electric motor associated with the wheel, an electric controller of the electric motor, connected to an output of an electrical power supply, and a taxiing control computer configured to determine control instructions for the electric motor and to transmit these instructions to the electric controller. The taxiing control computer is configured to receive braking of the aircraft commands during the taxiing of the aircraft and to determine control instructions for the electric motor corresponding to operation of the motor in generator mode when it receives a braking command. The electric controller is connected to an energy absorber making it possible to absorb the electric energy produced by the electric motor when the latter is operating in generator mode.

Abstract: The invention concerns an aircraft cockpit comprising at least one instrument panel (4) and a seat (2) for a pilot characterized in that the instrument panel forms a single unit and is carried by a hinged support (6) enabling the pilot to adjust the position of the instrument panel (4) relative to the pilot seat (2). Preferably, the instrument panel forms a single unit and is curved, for example along the arc of a circle, around the pilot seat.