Abstract: The present invention relates to a method of manufacture of a group of transverse internal stiffening ribs (46) for an aerodynamic fairing of an engine mounting device, including: production, for each rib (46), of a given rib preform (46a) by superplastic forming; and in respect of at least one of the ribs (46) of the group having a smaller size than that of the preform (46a), division of the latter into four preform parts (56a-56d) each incorporating one of the four corners of the quadrilateral formed by the preform, followed by the joining of the four parts to one another so as to obtain the rib.

Abstract: A trailing-edge flap system is described. The trailing-edge flap system includes a trailing-edge flap and a movement device. The movement device includes at least a translatory mover for the translation of the trailing-edge flap and at least a rotational mover for the rotation of the trailing-edge flap.

Abstract: Apparatuses, systems, and methods described herein provide for a refueling boom having vertical control surfaces extending primarily downward below the horizontal control surfaces out of the auxiliary power unit (APU) exhaust and airframe-induced turbulent flow fields, while reducing the torque moments applied to the boom beam and increasing control authority. According to one aspect of the disclosure provided herein, a refueling boom includes a boom beam, at least one horizontal control surface, and a pair of vertical control surfaces. The vertical control surfaces are positioned on opposing ends of the horizontal control surfaces and each include an upper portion and a longer lower portion projecting downward below the horizontal control surface. Aspects further improve the aerodynamic characteristics of the boom beam, reducing the drag associated with the refueling boom.

Abstract: An aircraft cockpit that includes an information display device with a screen having a display surface and a rear surface opposite the display surface, and a cable harness connected to the screen. The rear surface includes a mechanism for retaining the cable harness substantially wound against the rear surface. The information display device is mobile within the cockpit.

Abstract: An adjustment mechanism of a device for coupling a flap to a wing of an aerofoil and for adjusting the flap. The adjustment mechanism includes: a first lever, hinged to the wing via a first rotational joint to form a first axis of rotation; a second lever; a third lever, hingedly coupled to the second lever via a second rotational joint to form a second axis of rotation and hingedly coupled to the flap via a fourth rotational joint; and a push-pull rod, which is connected via a first ball joint to the second lever and via a second ball joint to the flap. The first lever and the second lever are hingedly coupled to one another via a middle joint to form a third axis of rotation. The first, second and third axes of rotation in each position of the flap run through a common pole.

Abstract: A first part, a second part, and a seal ring are fastened together to form a pressure structure configured for a spacecraft structure of a spacecraft, wherein the first part and the second part are each formed from a single workpiece.

Abstract: The present invention relates to a method of manufacture of a stiffening transverse internal rib (46) for an aerodynamic fairing of an engine mounting device, including: the production of a rib preform by superplastic forming having an outline of a broadly quadrilateral shape, and a central opening (52) traversing this preform; the division of the preform into two parallel straight-line segments (56, 60), which are diagonally opposed, causing the separation into two half-parts (46a?, 46a?) of the rib preform; and fishplating of the two rib preform half-parts (46a?, 46a?) by bolting.

Abstract: Fiber-based debris interceptors are used to intercept and/or contain space debris. The debris interceptors may be made up of fibers that are formed in space from a material supply on a space vehicle. The fibers for the debris interceptors may be formed by extrusion, with a heat source, such as a mirror to focus sunlight, used to heat the material of the material supply that is carried on the space vehicle. The debris interceptor may be separated from the space vehicle, and used to remove debris from an orbit, or otherwise prevent debris entering an orbit from damaging a satellite or other spacecraft that travels in that orbit. The debris interceptor may be deployed prior to later launch of a valuable spacecraft, in order to “cleanse” the intended orbit of debris. Debris objects may pass through the debris interceptor, but in so doing may lose energy so as to de-orbit.

Abstract: A device for opening and locking a tail unit is provided. The tail unit includes a body and at least one fin, pivotable relative to the body along a first axis, that has a projection that forms an element. The device comprises a control ring, slidable relative to the body along a second axis, that includes a component, forming an element, that bears against the projection to deploy the fin, the second axis being non-parallel and non-secant to the first axis. A means for shaping one of the elements during translation along the second axis of the control ring towards the projection of the fin is provided on the other element. The body includes a bearing surface to support the fin during shaping, in which the support of the fin on the bearing surface corresponds to the deployed position of the fin.

Abstract: The present document describes a yaw control system for a helicopter having a controllable aft rudder. The system comprises a fan for blowing low pressure air impinging upon the controllable aft rudder. During flight, the main rotor assembly drives the fan and the air flow impinging upon the controllable aft rudder creates a side force which enables yaw control.

Abstract: A device for delimiting a crew rest area in an aircraft passenger cabin includes a curtain which is adapted to separate at least one seat disposed in the aircraft passenger cabin from a region of the aircraft passenger cabin surrounding the seat. In addition, the device includes a fastening device for fastening the curtain in the aircraft passenger cabin. At least a first part of the fastening device is fixed to a grip rail intended for installation in the aircraft passenger cabin or formed integral with the grip rail intended for installation in the aircraft passenger cabin.

Abstract: An aircraft has a fuselage of elongated form along a longitudinal axis X corresponding essentially to the longitudinal axis of the aircraft. In a first forward section, the fuselage includes a cockpit in front of a cockpit bulkhead and a front landing gear associated with a landing gear compartment located behind the cockpit bulkhead. The front landing gear and the landing gear compartment are at least partially beneath a floorboard of a compartment of a lower space of the fuselage and in a bulge that increases a volume available for installation of the landing gear.

Abstract: A spacecraft magnetic shield apparatus is disclosed. One embodiment has an armature attached at one end of a spacecraft and an electromagnet attached to the other end. A computer determines the position of the armature and electromagnet in relation to the spacecraft, and a power source powers the electromagnet. In operation, the positioning of the electromagnet is generally in line with incoming charged particles or ion radiation and powering of the electromagnet creates a magnetic field that deflects a percentage of the incoming charged particles or ion radiation from directly impacting the spacecraft.

Abstract: The invention relates to a residence and sleeping module in an aircraft, for accommodating at least one member of an aircraft crew, wherein the module comprises a first partial module for docking a second partial module to it. In this arrangement, the first partial module or the second partial module comprises a connecting element, and the first partial module is designed to be arranged at a vertical height of an aircraft, which vertical height differs from that of the second partial module. In this arrangement, the connecting element is designed such that the second partial module can be docked to the first partial module by means of the connecting element.

Abstract: A method and apparatus for managing a flight control surface system. A leading edge device is moved on a leading edge from an undeployed position to a deployed position. The leading edge device has an outer surface, an inner surface, and a deformable fairing attached to the leading edge device such that the deformable fairing covers at least a portion of the inner surface. The deformable fairing changes from a deformed shape to an original shape when the leading edge device is moved to the deployed position. The leading edge device is then moved from the deployed position to the undeployed position, wherein the deformable fairing changes from the original shape to the deformed shape.

Abstract: A landing gear for an aircraft. The landing gear may have a wheel/truck assembly, an oleo strut/support frame for supporting the wheel/truck assembly, and a retraction assembly attached to the oleo strut/support frame, the retraction assembly for moving the landing gear between a deployed position and a retracted position. The retraction assembly may have a pivoting trunnion brace attached to the oleo strut/support frame and to a fuselage of the aircraft for positioning the wheel/truck assembly, the oleo strut/support frame and the retraction assembly at least substantially fully within the fuselage of the aircraft in the retracted position.

Abstract: An aircraft deicing system including at least one motor operative to drive at least one eccentric mass in rotational motion and at least one displacer coupled to at least one location on at least one aircraft surface and coupled to the at least one eccentric mass such that forces produced by the rotational motion of the eccentric mass are applied to the at least one displacer, causing the at least one displacer to displace the at least one aircraft surface in a plurality of directions at each of the at least one location, thereby causing disengagement of ice from the at least one aircraft surface.

Abstract: A joint construction for an aeronautical structure made from composite material having an internal structural element and an adjoining skin element which define the aeronautical structure, which includes a coupling element disposed between and contiguous with the internal structural element and the adjoining skin element, wherein the coupling element has opposing adjoining diagonally configured end portions which form a wedge shaped diagonal joint therebetween which terminates at the internal structural element at one end and the skin element at the other end, and a plurality of rivets extending from the internal structured element to the adjoining skin, across the coupling element and across the diagonal joint.

Abstract: An aircraft noise reduction apparatus includes an aircraft landing gear assembly and a noise reduction fairing 12. The landing gear assembly includes a landing gear 10 arranged to be moveable between a stowed position and a fully deployed position. The noise reduction fairing 12 may include a wrap-around fairing which, when the landing gear 10 is in its fully deployed position, wraps around the landing gear 10 and extends along the majority of the length of a landing gear leg 11. A landing gear bay door assembly 16, 17 including at least one door may also be provided. The fairing 12 may have a recess 24 for accommodating one of landing gear bay doors when the door 16 is in its fully open position.

Abstract: Concepts and technologies described herein provide for the creation of an actuating fluid flow utilizing a multi-stage actuator. According to one aspect of the disclosure provided herein, a fluid actuation system includes at least two stages, each stage having a plenum and one or two diaphragms acting on the plenum to create an actuating fluid flow. The diaphragms of each stage may be substantially aligned along an axis. The actuating flow is aggregated between stages and expelled into a fluid flow to be controlled. According to various aspects, the diaphragms may include piezoelectric discs.