Abstract: An assembly of parts, at least one of which is made of composite material, includes at least one fastener including a body and also two stops, between which the parts held by the fastener are disposed, holes formed in the parts held by the fastener, the body of the fastener being accommodated in the holes, the holes having a diameter adapted to that of the body of the fastener so as to allow transmission of forces by the parts and the fastener hammering together. The stops of the fastener exert a compressive force C that makes it possible to obtain transmission of forces by adhesion between the parts held by the fastener.

Abstract: Enriching and balancing the acoustic spectrum radiated by a propeller by introducing a differential pitch angle on certain blades of the propeller. Modifying the acoustic spectrum makes it possible to render the propeller noise more pleasant to the human ear.

Abstract: A load introduction element for a movable surface of an aircraft comprises a load introduction body that is connectable with the surface. A fitting connected with the load introduction body with a first section and a second section. The first section comprises a first bearing means, the second section comprises a second bearing means, and the first or second section comprises a third bearing means. The fitting is pivotally connected with the load introduction body by way of the first bearing means. An adjustment unit connects the second bearing means with the load introduction body in a variable position and is positioned on a side of the load introduction body that is opposite the fitting. In this manner adjustment of a reference position of a surface takes place without the need for an access flap. By loosening the adjustment unit the movable surface is pivotable without moving a flap drive.

Abstract: A surface element, e.g. a wing, of an aircraft includes a leading edge, a high lift device arrangement positioned along the leading edge and at least one add-on body positioned in a leading edge region, wherein the high lift device arrangement is interrupted in the region of at least one add-on body for preventing collision with the add-on body and wherein the surface element includes an arrangement of openings in a region covering the add-on body, which openings are connected to an air conveying device for conveying air through the openings. Thereby an additional flap for harmonizing the flow above a pylon or other add-on body can be eliminated.

Abstract: A manhole assembly in the lower skin (37) of an aircraft wing made of a composite material for giving access to an installation placed inside said aircraft wing such as a fuel tank, comprising an inner cover (31) and an outer cover (33) joined by first fastener means (35); the lower skin (37) being configured with a rebated edge (45) around the manhole so that the outer cover (33) can be mounted over the lower skin (37) maintaining the aerodynamic continuity in the aircraft wing surface; the inner cover (31) being mounted over the lower skin (37) by its inner surface with a sealing profile (41) between them and being joined to the lower skin (37) by second fastener means (47).

Abstract: A method, apparatus and software is disclosed for using parameters of acoustic emissions emitted from an structure, such as aircraft landing gear, for detecting yield in the structure.

Abstract: According to an exemplary embodiment of the invention, pre-assembly and integration of part of an aircraft cabin takes place outside the aircraft structure by means of an assembly device. After pre-assembly, the part of the aircraft cabin is slid into the open section of the aircraft structure where it is installed.

Abstract: An energy absorber for aircraft, which includes one or more energy absorber elements and a housing, whereby the energy absorber elements can absorb crash impulses by plastic deformation within the housing. Thus, the load on the primary structure and the respective inboard devices is limited, which can lead to an increased, passive safety of the passengers and a weight reduction.

Abstract: The present invention provides a method for the production of a fiber-reinforced plastics material profiled part. The method comprises the supplying of a tubular fiber braid in which a polymer matrix is arranged by being distributed therein. A longitudinal portion of the fiber braid is enclosed in a molding press. The molding press is heated to cure the polymer matrix in the longitudinal portion. After the press is opened, the fiber braid is drawn through the open press in order to position a further longitudinal portion of the fiber braid in the molding press. The further longitudinal portion is enclosed in the press. Another aspect of the invention is the provision of a device for the production of a fiber-reinforced plastics material profiled part.

Abstract: An area-expandable monument is provided for a cabin of a vehicle that includes, but is not limited to two housing parts that are displaceable relative to each other and can be fastened. A gap between the housing parts in an expanded state can be covered by a covering element. In the monument, a first sanitary fixture could be arranged whose position adapts to the spatial state of the monument. Optionally, there is also a pivotable second sanitary fixture that can be activated with the monument in its pushed-out state.

Abstract: A die tool for forming a C-section component having radiused shoulders, the includes a cylindrical inner die and an outer die having a cylindrical central portion connected to opposing end flanges by respective radiused concave portions. A portion of the inner die is arranged to be disposed between the end flanges of the outer die and spaced apart therefrom to define a cavity corresponding to the desired cross-section of the C-section component to be formed. The radiused convex and concave portions have a radius of curvature that varies about the circumference of the respective inner and outer dies. The inner and outer dies are rotatable such that the radius of curvature of the radiused convex and concave portions where the inner and outer dies are adjacent to one another varies as the inner and outer dies are rotated.

Abstract: The invention relates to an aircraft control system containing several aircraft control computers (14, 16, 18, 20) for said aircraft, said system having at least one server (10) which: contains at least one aeronautical data base (12); is connected to at least one subassembly of said control computers through data transmission links (26a, 26b, 26c, 26d); is able to supply information from said at least one aeronautical data base to the computers of said control computer subassembly, said at least one server being able to supply information from said at least one aeronautical data base to a computer of said control computer subassembly, in a period of time less than a predetermined duration, upon request from said computer, when said information is not available in a local data base of said computer.

Abstract: A method of lifting an aircraft at a lifting location including the steps of securing a fitting to the aircraft when the aircraft is at the lifting location, the fitting including an attachment member configured to be secured to the item and a lifting member which is pivotally coupled to the attachment member. The lifting member has a socket for engaging a crane hook. Engaging the fitting with the crane hook and transmitting lifting load from the crane hook to the aircraft via the fitting. The crane hook has an attachment link having a first pivot point attached to the hook forward of its center of gravity, and a second pivot point configured to be lifted by a crane.

Abstract: A computer-aided method suitable for assisting in the design of an aircraft by providing relevant dimensioning values corresponding to an aircraft component in transonic conditions inside a predefined parameter space by means of a reconstruction of the CFD computations for an initial group of points in the parameter space using a POD reduced-order model, comprising the following steps: a) Decomposing for each flow variable the complete flow field into a smooth field and a shock wave field in each of said computations; b) Obtaining the POD modes associated with the smooth field and the shock wave field considering all said computations; c) Obtaining the POD coefficients using a genetic algorithm (GA) that minimizes a fitness function; d) Calculating said dimensioning values for whatever combination of values of said parameters using the reduced-order model. The invention also refers to a system able to perform the method.

Abstract: This invention relates to an aft pylon fairing (30) for a suspension system of an aircraft engine, comprising two side panels (44) assembled to each other by inner cross stiffening ribs (46) spaced at intervals from each other along a longitudinal direction (X) of the fairing, and also comprising a heat protection deck (32) designed to delimit an engine core flow (36). According to the invention, it also comprises two longitudinal connecting walls (58) offsetting the deck (32) from the ribs (46), each of these two longitudinal walls (58) being provided with a first side end (62) fixed to one or the other of the two side ends (60, 60) of the deck (32), and a second side end (64) rigidly fixed to the ribs (46).

Abstract: The invention relates to an aircraft opening window comprising at least one pane (2) equipped with a movable frame (3), the assembly comprising the said movable frame (3) and the said at least one pane (2) being movable relative to a fixed frame (1), an element (4) for maneuvering the said movable assembly, a device for locking/unlocking and opening/closing the said movable assembly actuated by the said maneuvering element (4) and means for guiding and supporting the said movable assembly.

Abstract: The present invention provides a door frame construction in particular for an aircraft or spacecraft, including a former; a fibre metal laminate which is connected to the former; and an outer skin which is connected to the fibre metal laminate.

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, wherein the edge of the pressure bulkhead is circumferentially attached to the fuselage structure by fastening means, wherein the fastening means include a pair of ring-shaped attachment frames made of an open or hollow profile, which are disposed at each side of the pressure bulkhead respectively, in order to form a clamping connection for the pressure bulkhead towards the fuselage structure.

Abstract: The present invention provides a method, device and apparatus for determining a quantity of fuel within a fuel tank having a drain valve penetrating a lower boundary of the fuel tank. The method includes inserting a pressure measurement probe having a pressure sensor into the drain valve to permit contact between the pressure sensor and fuel within the tank, and measuring a pressure of the fuel with the pressure sensor. The measured pressure is used to determine the quantity of fuel within the tank, e.g. by consulting look-up tables comprising data indicating the relationship between measured pressure and fuel quantity, or by using one or more conversion equations.

Abstract: Awing box of an aircraft with a stiffened shell structure, consisting of fiber reinforced material includes a skin for absorbing shear loads, and several stringers arranged on the inner side of the wing box for absorbing axial loads, in which at least 60% of the mass of the stiffened shell structure is concentrated in the stringers, wherein the stringers provide at least 80% of the axial stiffness of the stiffened shell structure. In the specific case of wing structure, this embodiment allows the use of unbalanced laminates for the skin to induce higher nose-down twist of the wing box without any loss in bending stiffness and so envisaging higher weight saving capability.