Abstract: A propulsion system for an aircraft, comprising at least one rotor and a nacelle fairing extending around the at least one rotor with respect to an axis of rotation of the rotor, the nacelle fairing comprising: an upstream section forming an inlet section of the nacelle fairing; a downstream section, a downstream end of which forms an outlet section of the nacelle fairing; and an intermediate section connecting the upstream and downstream sections, wherein the downstream section comprises a radially inner wall and a radially outer wall made of a deformable shape memory material, and wherein the downstream end forming the outlet section has a pneumatic or hydraulic annular actuator extending around the axis of rotation and configured to deform radially under a predetermined control pressure so as to vary an outer diameter of the outlet section between a minimum diameter and a maximum diameter.

Abstract: Apparatus and methods for sealing powder holes in additively manufactured parts are presented herein. Powder holes are co-printed to facilitate post processing sealing. Embodiments include co-printed caps, friction welded caps, rivets, silicone plugs, co-printed tangs, multiple micro holes, layup, and spin forming. By using one or more of the above techniques, powder holes can be sealed on additively manufactured parts.

Abstract: Systems and methods for assembling Unmanned Autonomous Vehicle (UAV) are disclosed herein. In one embodiment, a method for assembling a UAV includes connecting a wing spar with boom carriers to form an H-frame. The wing spar provides mounting locations for securing horizontal propulsion units, and the boom carriers provide mounting locations for securing vertical propulsion units. The method also includes attaching a fuselage body to the wing spar; attaching a pre-formed wing shell to the H-frame; and attaching pre-formed individual boom shells to their corresponding boom carriers. The H-frame provides structural frame for mounting the wing shell and the boom shells.

Abstract: An airfoil for a turbine engine having an engine component including an internal cooling circuit fluidly coupled to a plurality of passages within the outer wall of the engine component where cooling air moves from the internal cooling circuit to an outer surface of the engine component through the passages.

Abstract: A liquid storage tank, for example an aircraft fuel tank, having a tank wall enclosing a liquid storage space, and a tie assembly located at least partially within the liquid storage space. The tie assembly includes an elongate member, for example a wire or cable, and a plurality of attachment devices fixed to an inner surface of the tank wall. The elongate member includes a plurality of spaced part points along its length, each of the spaced apart points being fixed to a respective attachment device such that the tie assembly resists outward deformation of the tank wall.

Abstract: A method includes building an article by a layer-by-layer additive manufacturing process. While the article is being built, a solid outer wall is formed. An inner structure of the article is integrally formed with the outer wall. The inner structure includes an internal permeable structure.

Abstract: In various embodiments, an airfoil used as a turbine blade for a turbine wheel in a gas turbine engine is provided. The airfoil may comprise a root, a tip, and a body. The root may have a first area. The tip may have a second area. The body may have a chord bounded by the root and the tip. The body may also define a cooling chamber. The cooling chamber may have a first rib substantially perpendicular to the chord. The cooling chamber may also have a second rib extending partially between the root and the tip.

Abstract: An integrated composite trailing edge and its method of manufacturing. The trailing edge comprises an integrated main structure having an upper cover, lower flanges, and a set of ribs extending between the upper cover and the lower flanges, with a set of sandwich type lower panels attachable to the lower flanges of the integrated main structure. The method comprises the steps of providing a set of prepreg laminated preforms over a set of tool modules having a hollow so that each laminated configures a double C-shaped laminated preform having an upper section with a recess, two primary and secondary flanges, the upper section partly forming the upper cover, the two primary flanges partly forming the ribs and the two secondary flanges forming the lower flanges.

Abstract: A system and method that allow inspection of hollow structures made of composite material, such as an integrally stiffened wing box of an aircraft. A wing box comprises top and bottom skins connected by a plurality of spaced spars. The system employs a plurality of scanners for inspecting different portions of each spar. The system uses dynamically controlled magnetic coupling to connect an external drive tractor to computer-controlled scanners that carry respective sensors, e.g., linear ultrasonic transducer arrays. A system operator can control the various components by means of a graphical user interface comprising multiple interaction regions that represent the individual scanner motion paths and are associated with respective motion script files.

Abstract: A collapsible wing, methods of producing the collapsible wing, and an unmanned aircraft system that includes the collapsible wing are provided.

Abstract: Using the lowest possible amount of resources, a system is to be provided with a structural element (1), which system allows the characteristics of a vacuum to be used in the construction sector in a particularly simple manner. In particular, with a substantial freedom from thermal bridges, it is possible to also subsequently insulate a building envelope, for example, in situ at the lowest possible cost and this insulation is to be flexibly adaptable to changes of the building envelope. For this purpose, the structural element (1) comprises two cover layers (2) arranged substantially parallel to one another and a closed frame structure (4) which is formed integrally with the cover layers (2) and is arranged between said cover layers (2) such that a gastight cavity (6) is formed, said cavity (6) containing a vacuum.

Abstract: A single wing for an unmanned aircraft adapted for image acquisition, surveillance or other applications consists of a ribbed frame and a foam wherein the ribbed frame is integrated during molding for stiffness and strength. The foam has a container for holding the electric and/or electronic components. The foam constitutes the outer layer of the unmanned aircraft at impact side. The wing can be produced at low cost and low complexity in large volumes, increases the impact resistance and safety when used in civil areas, and is removable and disposable thereby enabling reuse of the electric and/or electronic components.

Abstract: An aircraft wing has hinged ribs, and a skin covering the ribs. The ribs each include plural rib sections, array from the leading edge of the wing, to the trailing edge of the wing, and a lock to hold the rib sections together in a deployed state or condition. The wings are initially in a stowed state, with the ribs and the rib sections having a curved chord, and deploy to the deployed state, in which the ribs have a straightened chord that defines an airfoil state. The wing may have foam material between the ribs to allow the wings to expand in the wingspan direction, for instance after the ribs have been placed in the deployed state.

Abstract: A wing includes a spar, and a pair of flexible skins that are attached to the spar. The spar is at the leading edge of the wing, and the skins extend toward the trailing edge of the wing. The wing deploys from a stowed condition, in which the skins are curved in the same direction around a fuselage of an aircraft, to a deployed condition, in which the skins provide the wing with an airfoil cross-sectional shape, for example with the skins curve in opposite direction. A lock is used to maintain the skins in the deployed state, with the lock for example located at the trailing edge of the wing. The lock may be a mechanical mechanism that automatically locks the wing in the deployed state, preventing the wing from returning to the stowed state.

Abstract: A streamlined profile reducing the speed deficit in a wake, a pylon with such a profile, a propulsion assembly including such a pylon and an aircraft including this assembly. The profile has a device for suction of air from the boundary layer formed on this profile. This suctioned air is discharged with the aid of a nozzle the outlet of which is situated close to the trailing edge of the profile. Suction of the air and discharge thereof contribute to reducing the speed deficit downstream from the profile and therefore to reducing the turbulences in this zone.

Abstract: A leading edge element, a method for manufacturing one, and an aircraft wing and stabilizer furnished with the leading edge element. The leading edge element is an elongate piece that comprises a skin plate and at least one longitudinal stiffener. The shape of the front edge of the skin plate is closed and the tail edge is open. The stiffener is fastened between the inner surfaces of the skin plate. Between the inner surface of the skin plate of the outermost longitudinal stiffener, there is a longitudinal space free of transverse stiffeners.

Abstract: In one step of a method of fabricating a composite tube, layers of uncured composite material may be laid over a surface. In another step, spaced-apart strips of at least one of uncured, partially cured, and completely cured composite material may be laid lengthwise over the laid layers of composite material. In still another step, the spaced-apart strips may be compacted against the layers of uncured composite material. In an additional step, the compacted spaced-apart strips and the layers of uncured composite material may be further consolidated and/or cured to form a composite tube.

Abstract: A three-dimensional hollow fiber component includes a first sheet having first; second, third, fourth and fifth consecutive adjacent sheet sections, the first and fifth sections being end sections, the sheet shaped so as to surround a first chamber such that the first and fifth sections overlap to form a top wall of the first chamber and are stitched to each other by at least one seam and a second sheet having first, second, third, fourth and fifth adjacent consecutive sheet section, the first and fifth sections being end sections, the sheet sections shaped so as to surround a second chamber such that the first and fifth sections overlap to form a top wall of the second chamber and are stitched to each other by at least one seam.

Abstract: A hull structure is provided, for use in particular in an aircraft or spacecraft, the hull structure including an outer skin and structural components which are connected to said skin, as well as an inner lining which forms a supporting structure together with the outer skin and the structural components.

Abstract: A structuring construction for an aircraft fuselage is provided having an outer skin as well as a plurality of formers extending at a spacing side by side crosswise to the longitudinal direction of the fuselage wherein at least a partial number of the formers include a main former portion which is channel-like in cross section and the channel edges of which are adjacent to the outer skin and wherein the channel space of the main former portion serves to accommodate at least one supply air line which may be formed, for example, by a separate pipe line.

Abstract: An aircraft structure comprising: a spar; a primary cover attached to the spar and extending on a first side of the spar; and a secondary cover positioned on a second side of the spar and partially overlapping an internal surface of the primary cover. A bracket is attached to the spar, and a spacer is provided between the secondary cover and the bracket. The spacer is sized so that the primary and secondary covers together form a substantially continuous external aerodynamic surface. The structure provides an alternative to conventional butt-strap arrangements.

Abstract: There is provided a method of manufacturing a rib for an aircraft wing, the method comprising providing a billet of material for forming the rib, machining away material from all sides of the billet to form a rib for use in an aircraft, the rib including a web that extends between first and second flanged portions, each flanged portion having a flange that facilitates fixing of the rib to another component of the aircraft, wherein the material that forms the web extends diagonally across the billet, the web having a first face on a first side and a second face on a second side opposite to the first side of the web, and the first flanged portion extends more to the first side of the web than to the second side and the second flanged portion extends more to the second side of the web than to the first side.

Abstract: A leading edge element, a method for manufacturing one, and an aircraft wing and stabilizer furnished with the leading edge element. The leading edge element is an elongate piece that comprises a skin plate and at least one longitudinal stiffener. The shape of the front edge of the skin plate is closed and the tail edge is open. The stiffener is fastened between the inner surfaces of the skin plate. Between the inner surface of the skin plate of the outermost longitudinal stiffener, there is a longitudinal space free of transverse stiffeners.

Abstract: A method of forming an internal structure within a hollow component (2), the component comprising first and second panels (4, 6) and at least one membrane (8; 10) disposed between the first and second panels (4, 6), the method comprising: selectively bonding the at least one membrane (8; 10) to the first and/or second panels (4, 6); inflating the component (2) by passing a pressurised fluid between the first and second panels (4, 6) such that the first and second panels (4, 6) are inflated into contact with a die assembly (38) and such that the membrane (8; 10) forms an internal structure between the first and second panels (4, 6); and deforming the internal structure by applying the pressurised fluid at a first pressure (P1) on one side of the membrane (8; 10) and at a second pressure (P2) on the other side of the membrane (8; 10).

Abstract: A single piece co-cured composite wing is disclosed. The wing has a flying surface and structural members. In one embodiment the structural members may be a plurality of spars. The spars may have various shapes to increase the buckling strength. The spars may be wave shaped, such as a sinusoidal shape. The flying surface and the structural members are co-cured in order to form a single piece, integral wing structure. A process for manufacturing a single piece co-cured wing is also disclosed. The process may include laying out composite sheets for the flying surface of the wing. Then, the composite material of the spars is arranged around a plurality of pressurizable forms. Finally, the composite material is cured in a clamshell frame. A single piece co-cured composite structure is also disclosed that includes an outer skin, and inner skin, a frame, and a stringer.

Abstract: There is provided a method of manufacturing a rib for an aircraft wing, the method comprising providing a billet of material for forming the rib, machining away material from all sides of the billet to form a rib for use in an aircraft, the rib including a web that extends between first and second flanged portions, each flanged portion having a flange that facilitates fixing of the rib to another component of the aircraft, wherein the material that forms the web extends diagonally across the billet, the web having a first face on a first side and a second face on a second side opposite to the first side of the web, and the first flanged portion extends more to the first side of the web than to the second side and the second flanged portion extends more to the second side of the web than to the first side.

Abstract: A method of manufacturing an aerofoil for a gas turbine engine (10). The method comprises the steps of providing first and second panels (16, 18), providing a web (30) between the first and second panels, deforming the panels and the web by applying internal pressure between the panels so as to form a series of internal cavities partitioned by the web. The method further includes the step of either cutting the web (30) across its entire width or causing the web to fail across its entire width so as to define an aerofoil having first and second panels with at least one protrusion extending from the first panel partially across the space between the first and second panels.

Abstract: A method of manufacturing an aerofoil for a gas turbine engine (10). The method comprises the steps of providing first and second panels (16, 18), providing a web (30) between the first and second panels, deforming the panels by applying internal pressure between the panels so as to form an internal cavity. The method further includes the step of providing a pattern of ribs (60) on the web so as to define a aerofoil having first and second panels with at least one rib (60) forming a protrusion extending from the first panel partially across the space between the first and second panels.

Abstract: An intercostal for an aircraft for dissipating a load from a first frame onto a second frame and/or a skin of the aircraft, the intercostal having a framework.

Abstract: A hollow aerofoil (30) comprises an aerofoil portion (40) having a leading edge (42), a trailing edge (44), a concave pressure surface wall (46) extending from the leading edge (42) to the trailing edge (44) and a convex suction surface (48) extending from the leading edge (42) to the trailing edge (44). The concave pressure surface wall (46) and the convex suction surface wall (48) are integral and define a cavity (50). A plurality of webs (52) extend across the cavity (50) between the concave pressure surface wall (46) and the convex suction surface wall (48). At least one of the webs (52A) extends substantially perpendicularly to the concave pressure surface wall (46) and the convex suction surface wall (48) and at least one of the webs (52B) extends substantially diagonally to the concave pressure surface wall (46) and the convex suction surface wall (48).

Abstract: A micro air vehicle having a bendable wing enabling the micro air vehicle to fly. The bendable wing may be bent downwards so that the wingspan may be reduced for storing the micro air vehicle. The bendable wing may be formed from one or more layers of material, and the wing may have a camber such that a concave surface of the wing faces downward. The wing may substantially resist flexing upwards and may transfer uplift forces to a central body of the micro air vehicle. In addition, the wing may be bent severely downwards by applying a force to tips of the wing. The micro air vehicle is capable of being stored in a small cylindrical tube and may be deployed from the tube by simply releasing the micro air vehicle from the tube.

Abstract: An airfoil box and associated method are provided. The airfoil box includes two or more half-shell structures. Each half-shell structure is an integral or unitary member that includes at least a portion of the outer skin of the airfoil as well as stiffener members and connection members. For example, the half-shell structures can be integrally formed of composite materials. The half-shell structures can be assembled by connecting the connection members with fasteners such as rivets to form the airfoil box.