Abstract: A method for final assembly of at least two aircraft includes assembling the at least two aircraft in a transverse direction on a carousel, the at least two aircraft disposed side-by-side, and rotating the carousel on a vertical rotation axis 360°.

Abstract: A method and system for estimating a path difference between two paths followed by a target signal transmitted by a spacecraft or aircraft to a first receiving antenna and a second receiving antenna of a receiving base, respectively. A useful-phase difference is measured between signals corresponding to the target signal received on the first receiving antenna and second receiving antenna. The path difference is estimated on the basis of the measurements of the useful-phase difference. A calibration signal is transmitted to the receiving base and a calibration phase difference between signals corresponding to the calibration signal received on the first receiving antenna and second receiving antenna is measured. Variations are compensated in the measurements of the calibration-phase difference relative to the measurements of the useful-phase difference.

Abstract: An aircraft landing gear arrangement is provided comprising: a first landing gear portion comprising one or more wheels, a second landing gear portion, the first landing gear portion being rotatable with respect to the second landing gear portion; and a sensor for determining a rotational position of the first landing gear portion in relation to the second landing gear portion, the sensor comprising a first magnetic field generator operable to generate a magnetic field and a first magnetic field modulator for modulating said magnetic field, the sensor being operable to sense the magnetic field as modulated by the first magnetic field modulator, the first landing gear portion comprising the first magnetic field generator or the first magnetic field modulator, the second landing gear portion comprising the other of the first magnetic field generator and the first magnetic field modulator.

Abstract: A pressurized aircraft fuselage includes a pressure bulkhead installed on a fuselage structure, which forms a barrier between an internal pressurized cabin area and an outside area. The edge of the pressure bulkhead is circumferentially attached to the fuselage structure by movable fastening means. The movable fastening means includes at least one clamping element which is arranged inside a trapezoidal shaped mounting bracket which corresponds to an inserted edge of the pressure bulkhead, in order to form a clamping connection for the pressure bulkhead towards the fuselage structure.

Abstract: A forming tool for widening an opening includes an expanding device with several expansion elements. The expansion elements are each provided with a curved forming surface extending between two peripheral end edges. The expansion elements are moveable between a first position corresponding to a contracted state where the expansion elements in connection with one another by way of separating surfaces, and a second position corresponding to a widened state where the expansion elements are displaced in radial direction from a center of the expanding device such that the separating surfaces are spaced apart from one another. In the first position the peripheral end edges are spaced further apart from the center than a central region of the forming surfaces so that the fatigue strength of mounting bores can be increased, openings in thick-walled components can expanded more reliably, and/or the formation of cracks is avoided.

Abstract: A method and apparatus for providing information about an encrypted signal transmitted by a satellite in a satellite navigation system are disclosed. A data sequence of the encrypted signal as transmitted is obtained, a signal sample is extracted from the data sequence, the signal sample including a part of the data sequence having a length less than a total length of the data sequence, and the signal sample and information about when the data included in the signal sample was transmitted by the satellite are transmitted, as the encrypted signal information, to a receiver for use in the satellite navigation system. A method and apparatus for authenticating an unencrypted signal based on the encrypted signal information are also disclosed.

Abstract: A fixed wing of an aircraft, having a main wing extending over a half-span with a wing box including spars extending along the spanwise direction of the main wing, ribs arranged one in back of the other viewed in the spanwise direction, and an outer skin. The wing box includes a wing box base section (K10) and a wing box adapter section, that forms the outer end area of the wing box, as viewed from the wing root, and is designed to secure a wing tip device. In its nominal state of construction, the dihedral angle of the wing box adapter section referring to the respective local spanwise direction continuously increases by at most 60 degrees from the outer rib of the wing box base section (K10) up to the outermost rib of the wing box adapter section.

Abstract: A method having the following steps: feeding a plastic material in the area of an inner surface of the mold, conforming the material to the inner surface of the mold, feeding a tubular film into the mold so that the material is positioned between an outer surface of the tubular film and the mold, expanding the tubular film using pressure and/or a vacuum, applying a pressure above atmospheric pressure and/or heating the mold so that the material is partly or completely melted and is adapted to conform to an inner contour of the mold and an outer contour of the expanded tubular film. The tubular film is shaped before it is fed into the mold. The invention further relates to a tubular film (1) and a method for manufacturing the same.

Abstract: The invention relates to a flight simulator vibration system, particularly to a crew seat (1), a flight control stick (20) and a panel (30) vibration system of a flight simulator with at least one plate of the crew seat (1), the flight control stick (20) and/or the panel (30) being equipped with predefined momentum weights (13, 16) and electric motors driving said respective momentum weights. Speed governors are controlling individually said electric motors (7, 8, 9, 21, 33, 34).

Abstract: An automatic landing method and device for an aircraft on a runway with strong slope. The device includes means to automatically transmit, a runway slope value to an automatic piloting system of the aircraft, and said automatic piloting system uses the slope value to automatically manage the flare phase upon landing.

Abstract: A method for mounting interior components in an aircraft includes premounting a first interior component and premounting a second interior component. At least one of the first and the second interior component is secured to a mounting device and the first and second interior components are connected to form an individual module. A plurality of individual modules secured to the mounting device are interconnected to form a large module which is secured to the mounting device. The large module is detached from the mounting device and transported to a final-mounting position in an aircraft fuselage element. The detached large module is then mounted in the aircraft fuselage element.

Abstract: An aircraft exterior door installation with a door attached to an airframe. A damper is arranged to damp motion of the door as it is opened by rotating it away from the airframe. A coupling mechanism couples the damper with the door over an opening damping range and decouples the damper from the door at the end of the opening damping range. The damper does not damp the motion of the door as it opens beyond the opening damping range. Instead of damping the door over its full range of motion, it is only damped over a limited inner range of its motion. A further advantage of decoupling the door and the damper is that the damper does not need to extend into the airflow to the same extent as the door, thus minimizing aerodynamic drag.

Abstract: A rolling bearing device, of the type including a central shaft and a hub (10) mobile in rotation relative to each other, the bearing including at least two rolling bearings (12, 13), one designated “lower” and the other designated “upper”, arranged between the central shaft (11) and the hub (10) in two positions spaced in the axial direction Z, these rolling bearings being fitted with inner (14, 16) and outer (15, 17) rings and with balls (18, 19), the rolling bearings being assembled back-to-back or face-to-face, a rigid preload being applied to these bearings along the axial direction Z, internal (22) and external (23) spacers being arranged between these rolling bearings, the inner (22) and outer (23) spacers have lengths adjusted to limit variations in rigid preload caused by temperature gradients from one point of the bearing to another to less than 30%, particularly thermal gradients in the radial direction.

Abstract: A monument is provided for an aircraft. The monument includes, but is not limited to several system components with identical, substantially identical or similar functions that can be connected by way of a single system connection arrangement to the supply in the aircraft. Distribution of the supply media, received by the aircraft, to the individual system components takes place within the monument. The system connections can thus be identical to the system connections of a single monument.

Abstract: A method for a thermal joining of two thermoplastic components includes arranging at least one reactive sheet entity in a mating zone between the two thermoplastic components. A multiply perforated metallic sheet entity configured as a bonding agent is disposed on each side of the at least one reactive sheet entity, at least in some regions of the mating zone. The at least one reactive sheet entity is activated so as thermally join the two thermoplastic components in the regions of the mating zone.

Abstract: A method capable of providing a control unit with a previously unknown capability of reasoning on this knowledge. A non-exhaustive list of particularly interesting technical applications can be derived from such a method particularly in the military and civilian fields, for example such as the identification of entities by a humanoid robot, or identification of entities for peacekeeping or first aid missions, or detection of potential obstacles during displacement of an automobile vehicle, or identification of unknown ships, or identification of potential targets for drones, aircraft, land vehicles such as extraterrestrial vehicles or warships.

Abstract: Interactive dialog device between an operator of an aircraft and a guidance system of the aircraft. The dialog device includes an interaction on a screen which represents, on the one hand, a playback element indicating the value of a guidance setpoint of the guidance system of the aircraft, and on the other hand, a control element which can be grasped and moved along a curve by an operator to modify the value of the guidance setpoint.

Abstract: A method of testing an electrical junction between a first metallic element and a second metallic element in an aircraft current return network, said network comprising a plurality of metallic elements, each of which is connected to at least two other elements, said aircraft comprising at least one element made of a composite material connected to said network. The method is remarkable in that its use does not damage the composite structure of the aircraft.

Abstract: An aircraft including a fuselage which extends along a longitudinal axis. The fuselage includes a substantially cylindrical central portion and a rear portion that may have a flattened or conventional shape. This rear portion which comprises the rear end of the fuselage includes a support surface which bears at least one horizontal stabilizer and/or vertical stabilizer. The rear portion is able to pivot in relation to the central portion around an axis such as the pitch axis, at least one stabilizer or the support surface being equipped with at least one control surface.