Abstract: Dimpled plates for light distribution and concentration are provided. Also provided are apparatus incorporating the plates as waveguides, and methods for using the dimpled plates for distributing or concentrating input light. The dimpled plates are designed to spatially distribute light from each of one or more near point light sources into a pixelated light projection using an array of reflective conical light deflection elements.

Abstract: The disclosed embodiments relate to a method for manufacturing an aircraft fuselage section of composite material that comprises the following operations manufacturing a one-piece section; cutting the section longitudinally; spreading apart two edges located on the two sides of the cut; reassembling the section and making a longitudinal joint with the two edges overlapping. The disclosed embodiments also relate to a section made in accordance with this method.

Abstract: An aircraft front portion includes a sealed bulkhead separating a non pressurized radome area from a pressurized area. The sealed bulkhead is delimited by two surfaces opposite to each other, one being substantially concave when seen from the radome area and the other being substantially convex when seen from the pressurized area.

Abstract: An aircraft center section includes a center part of an aircraft fuselage, a wing section, a center wing box installed at least partly in the fuselage and providing a junction between the wing section and the fuselage, and a ventral fairing partly enveloping the fuselage and the wing section, with the ventral fairing being attached directly to the wing section and to the fuselage by means of structural elements that can make the ventral fairing a working fairing.

Abstract: The invention relates to a fuselage element (1) comprising a first fuselage segment (2a) comprising a skin (3a), and junction means (4) for connecting the first segment (2a) to a second adjacent fuselage segment (2b), the first segment (2a) extending along the longitudinal axis (X) of the fuselage, wherein the fuselage element (1) includes stiffening elements (5a) extending along the axis (X). The end (5a1) of at least one stiffening element (5a) extends beyond a free edge (7) of the skin (3a) by a predetermined length (L).

Abstract: The disclosed embodiments relate essentially to a primary structure of an aircraft fuselage that has at least a first strut linked at one end to a crossbeam and at the other end to a reinforcing frame. A second strut has one end fastened to the structure below the end of the first strut, and another end linked to the first strut through an intermediate sliding linkage. A deformable member is linked to the struts so that in case of a crash, the compressive forces press against the second strut, so that the end of the second strut slides along the first strut so as to stretch the deformable member longitudinally to absorb the shock.

Abstract: A tool equipment for manufacturing a panel in a composite material, in particular for an aircraft fuselage. The tool equipment (1) comprises a mould (2) including a fixed part (4) and a plurality of removable modules (6) which are able to be mounted on this fixed part (4).

Abstract: A cigarette includes a rod comprising a wrapped tobacco column that is joined to an axially aligned filter by a band of air impermeable tipping paper. The filter end of the rod is inserted into a mouthpiece having an air impermeable outer surface that comprises a ventilation tube and a second filter, separated by a mixing chamber. The ventilation tube has an air permeable annular wall that defines a central axial passage through which the rod extends. In use, the end surface of the annular wall at the rod end of the ventilation tube, which extends radially outward around the rod, acts as a ventilation surface through which air is drawn into the mixing chamber, where it mixes with mainstream smoke from the burning tobacco rod. The air/smoke mixture is drawn through the second filter into the consumer's mouth.

Abstract: The invention relates to the field of structural panels, more specifically, but not exclusively, to the field of aircraft fuselage panels. The invention concerns a stiffened panel (10) comprising at least one stiffener (4), known as a longitudinal stiffener, extending substantially from one extremity of the panel to the other and whose trace on the surface of said panel's skin (1) follows a path having non-zero geodesic curvature between the two extremities of said stiffener. This configuration makes it possible to optimize both the panel's stiffness and its resistance to the force flow to which it is subjected in operation by minimizing its mass through an optimum definition of the orientation of the stiffeners relative to said force flow.

Abstract: An aircraft seat assembly structure (4) comprises at least one seat structure (5) that supports at least one seat, with which seat assembly structure is associated a reference frame that is defined by a longitudinal X-axis according to which the seat structure (5) comprises a front part and a rear part, by a Y-axis that is perpendicular to the X-axis, and that forms with said X-axis a horizontal XY plane when at least one seat is horizontal, and by a Z-axis that is perpendicular to the XY plane. In the front part, the seat structure (5) comprises a torsion bar (50) that is essentially parallel to the Y-axis that is equipped at a first lateral end (502) with a front lateral fastening device (500) that is designed to be made integral with lateral attachment means (26) of a shell structure (2) of an aircraft.

Abstract: A splice plate for stringers designed to connect two adjacent stringers at least three independent pieces, a connection rod being designed to be fixed by two opposite extremities to two adjacent stringers, and at least two connecting plates, each connecting plate being designed to be fixedly joined to a first extremity of one of the two stringers, and by a second extremity of a cross bar disposed between the two stringers. The disclosed embodiment also relate to a device for orbital fixation including at least one stringer splice plate splice bar.

Abstract: The invention relates to an aircraft front portion (1) including a sealed bulkhead (10) separating a non-pressurized radome area (20) from a pressurized area (30), whereof the volume of the pressurized area (30) is optimized. For this, said sealed bulkhead (10) is delimited by two surfaces (11,12) opposite to each other, one (11) being substantially concave when it is seen from said radome area (20) and the other one (12) being substantially convex when it is seen from said pressurized area (30).

Abstract: An aircraft center section includes a center part of an aircraft fuselage, a wing section, a center wing box installed at least partly in the fuselage and providing a junction between the wing section and the fuselage, and a ventral fairing partly enveloping the fuselage and the wing section, with the ventral fairing being attached directly to the wing section and to the fuselage by means of structural elements that can make the ventral fairing a working fairing.

Abstract: The disclosed embodiments concern an aircraft fuselage section made of composite material with an internal skeleton having frames that form the radial structure of the fuselage and stringers that form the longitudinal structure of said fuselage, and a skin made of composite material, surrounding the internal skeleton, with said skin having an evolving thickness along a longitudinal axis X, with an approximately constant, regular interior profile. The disclosed embodiments also concern a process for manufacturing the skin of an aircraft fuselage section made of composite material, having a draping operation for strips of fibers precoated with resin around a mold, with the number of strips of fibers varying longitudinally depending on the area of the fuselage being considered so as to create a skin with an evolving thickness.

Abstract: The disclosed embodiments relate essentially to a primary structure of an aircraft fuselage that has at least a first strut linked at one end to a crossbeam and at the other end to a reinforcing frame. A second strut has one end fastened to the structure below the end of the first strut, and another end linked to the first strut through an intermediate sliding linkage. A deformable member is linked to the struts so that in case of a crash, the compressive forces press against the second strut, so that the end of the second strut slides along the first strut so as to stretch the deformable member longitudinally to absorb the shock.

Abstract: The disclosed embodiments relate to a method for manufacturing an aircraft fuselage section of composite material that comprises the following operations manufacturing a one-piece section; cutting the section longitudinally; spreading apart two edges located on the two sides of the cut; reassembling the section and making a longitudinal joint with the two edges overlapping. The disclosed embodiments also relate to a section made in accordance with this method.

Abstract: A splice plate for stringers designed to connect two adjacent stringers at least three independent pieces, a connection rod being designed to be fixed by two opposite extremities to two adjacent stringers, and at least two connecting plates, each connecting plate being designed to be fixedly joined to a first extremity of one of the two stringers, and by a second extremity of a cross bar disposed between the two stringers. The disclosed embodiment also relate to a device for orbital fixation including at least one stringer splice plate splice bar.

Abstract: A cigarette includes a rod comprising a wrapped tobacco column that is joined to an axially aligned filter by a band of air impermeable tipping paper. The filter end of the rod is inserted into a mouthpiece having an air impermeable outer surface that comprises a ventilation tube and a second filter, separated by a mixing chamber. The ventilation tube has an air permeable annular wall that defines a central axial passage through which the rod extends. In use, the end surface of the annular wall at the rod end of the ventilation tube, which extends radially outward around the rod, acts as a ventilation surface through which air is drawn into the mixing chamber, where it mixes with mainstream smoke from the burning tobacco rod. The air/smoke mixture is drawn through the second filter into the consumer's mouth.

Abstract: The subject of the invention is a device for assembly of several elements by riveting, the device including rivets or analogs, the shank of which has an elliptical or analogous cross-section placed and riveted in holes with an elliptical or analogous cross-section corresponding to that of the shank, laid out in the elements to be assembled. The invention also includes a method for assembling panels to make a fuselage of an aircraft.