Abstract: A method of repairing damage to a composite material having a composite substrate and at least one layer of shielding material includes: a) removing damage to the at least one layer of shielding material by creating a hole in the at least one layer of shielding material; b) applying a patch of shielding material in the region of the hole via a resin, wherein a ratio of a resin weight to a weight of the patch of shielding material lies in a range between about 0.45-0.55; and c) curing the resin, wherein an absorptive, consumable material is positioned in contact with the resin during at least a portion of the curing.

Abstract: A repair for a structural element made from a composite material includes a bracket defining a first surface and a second surface. The first surface is adapted for facing the structural element. A chamfer is located on a first end of the bracket. An angle is defined between a plane of the chamfer and a plane of the first surface, the first surface of the bracket being adapted to be disposed adjacent to a side of the structural element. The repair also includes a sealant material between the bracket and the structural element, where the sealant material occupies a space established between the chamfer and the structural element.

Abstract: A repair for a structural element made from a composite material includes a bracket defining a first surface and a second surface. The first surface is adapted for facing the structural element. A chamfer is located on a first end of the bracket. An angle is defined between a plane of the chamfer and a plane of the first surface, the first surface of the bracket being adapted to be disposed adjacent to a side of the structural element. The repair also includes a sealant material between the bracket and the structural element, where the sealant material occupies a space established between the chamfer and the structural element.

Abstract: Components having fibre-reinforced composite structures are disclosed. The component comprises a plurality of structural fibres embedded in a cured matrix material and a plurality of nanostructures such as carbon nanotubes extending from one or more of the structural fibres. In some embodiments a density of the nanostructures is at least 107 nanostructures per cm2 of surface area of the one or more structural fibres. In some embodiments, the nanostructures extend from an outer fibre proximal to an outer surface of the component but not from an inner fibre distal from the outer surface. In some embodiments the one or more structural fibres from which the nanostructures extend are free of a sizing agent.

Abstract: A control rod for incorporation into a composite assembly with at least a first composite preform, a second composite preform, and a cured resin includes a shaft defining an axis, wherein the shaft is disposable within an aperture in the composite assembly, and a plurality of threads disposed on at least a portion of the shaft. The shaft is made from, among other materials, a thermoplastic material. The threads define a thread pitch that encompasses more than one individual fiber layer forming at least one of the first composite layer and the second composite layer.

Abstract: A method for inserting an insert into a hole in a composite material made from a plurality of carbon fiber layers suspended in a resin material includes lowering a temperature of the insert to a reduced temperature at which a coefficient of thermal expansion of a material of the insert causes the insert to contract to a first perimeter, inserting the insert at the reduced temperature into the hole, and permitting the temperature of the insert to increase from the reduced temperature to an operational temperature. At the operational temperature, the insert expands to a second perimeter so that the insert is retained within the composite material due to an interference between the insert and the composite material. The interference transfers a structural load from the insert to the composite material and results in damage to the composite material if the insert is dislodged at the operational temperature.

Abstract: A dual load path assembly includes an outer pin, which has an axial through bore and at least one end that includes a threaded section. The threaded section includes at least one slot orientated from the end and extends axially along at least part of the threaded section. The assembly also includes an inner pin, which is receivable in the through bore of the outer fastener. A female fastener comprising at least one notch is receivable on the threaded end of the outer pin. A locking plate comprises a through hole via which it is receivable on the shank of the inner pin and at least one projection. The locking plate is arranged such that the projection is receivable in both the notch and the slot. A locking member engages with the end of the inner pin and abuts a face of the locking plate thereby sandwiching the locking plate between the locking member and the female fastener.

Abstract: A positional adjustment apparatus for an attractor includes a positioning plate disposable at least adjacent to a surface of a mold, at least one drive operatively connected to the positioning plate to move the positioning plate and alter at least one of a first height, a first angle of tilt, a first lateral position, and a rotational position of the positioning plate with respect to the surface of the mold, at least one positioner disposed in an opening through the positing plate, the positioner hanging from and being moveable independently of the positioning plate, at least one attractor connected to the at least one positioner, and a joint disposed between the positioner and the positioning plate, the joint permitting the at least one positioner to change at least one of a second height, a second angle of tilt, and a second lateral position with respect to the positioning plate.

Abstract: Precursors and methods for manufacturing perforated composite parts are disclosed. An exemplary precursor (19) comprises structural fibers (24,28) embedded in a cured matrix material (24,26) and interposed between two removable plies (20). The precursor may also comprise a sacrificial fiber (28) extending through the removable plies (20), the matrix material (24,26) and between the structural fibers (24,28). An exemplary method comprises removing the removable plies (20) from the precursor (19) and removing the sacrificial fiber (28) from the precursor after removing the removable plies to form a through hole in the precursor (19) at a location of the sacrificial fiber (28).

Abstract: A fabric handling apparatus includes a layup table, a mold disposed adjacent to the layup table, and a fabric handling array suspended above the layup table and the mold. The fabric handling array is adapted to transfer at least one fabric shape from the layup table to the mold. The fabric handling array includes a plurality of attractors in an attractor array. An orientation of the fabric handling array is alterable with respect to at least one of the layup table and the mold so that the at least one fabric shape is positionable on the mold in a predetermined orientation.

Abstract: An anti-icing system is provided within a chamber having an exterior wall of which an outer surface may be subject to ice formation. The anti-icing system comprises a nozzle arranged to inject hot gas within the chamber. A gas-mixing device defines a channel for receiving hot gas from the nozzle. The gas-mixing device includes a swirl-inducing feature for causing gas from the chamber to be drawn into the channel with a swirling effect when hot gas from the nozzle is injected into the channel.

Abstract: An electrical protector with a central axis includes a cap defining a top and a downwardly extending cap wall, and insert defining a ring and an upwardly extending insert wall, at least three protrusions extending inwardly from an interior surface of the insert wall toward the central axis, and a sealant disposed at least within the cap. The cap wall engages the insert wall, thereby establishing a connection between the cap and the insert. The protrusions are adapted to engage a structure, thereby securing the electrical protector onto the structure.

Abstract: A nacelle for an engine has outer and inner cowl doors that are independently rotatable about offset hinge lines. A connection device is provided for selectively connecting the outer and inner cowl doors so as to cause them to open simultaneously. The inner cowl door is arranged to rotate by a greater angle than the outer cowl door so as to improve access to the engine for maintenance purposes.

Abstract: An aircraft comprises a turbine engine suspended from a wing by means of a pylon. Compressed hot air is bled off from the turbine engine. A bleed air duct in the wing conveys the compressed hot air towards a fuselage. In order to prevent overheating of aircraft parts that are relatively close to the bleed air duct, the following solution is proposed. The pylon comprises an opening with a covering structure projecting into a bypass exhaust flow from the turbine engine. The covering structure leaves a slit facing away from the bypass exhaust flow. An airflow path extends from openings in the wing to the slit left by the covering structure.

Abstract: An aircraft comprises a turbine engine suspended from a wing by means of a pylon. Compressed hot air is bled off from the turbine engine. A bleed air duct in the wing conveys the compressed hot air towards a fuselage. In order to prevent overheating of aircraft parts that are relatively close to the bleed air duct, the following solution is proposed. The pylon comprises an opening with a covering structure projecting into a bypass exhaust flow from the turbine engine. The covering structure leaves a slit facing away from the bypass exhaust flow. An airflow path extends from openings in the wing to the slit left by the covering structure.

Abstract: To determine two positional co-ordinates, of a point (D) within a space, a beam (10) a radiation is caused to illuminate a part of the space and is deflected cylindrically over the space, the beam being modulated in phase with the cyclical movement such that the radiation incident upon the point (D) includes enough information to identify the point. Embodiments with rotational (r, ?) and Cartesian (x, y) co-ordinate axes are disclosed.

Abstract: A method and apparatus for forming a fiber reinforced composite structure comprising at least two components, a hard base tool presenting a first tool face, a second tooling element presenting a second tool face to locate the second component against the first component. Components are of a dry fibrous form and are to be injected with a liquid resin. A flexible bagging blanket forms with the tools a sealed enclosure into which the resin is injected to form the structure by resin transfer infusion. To maintain the relative dispositions of the components without the need for elaborate mandrel plates, control rods are inserted at least partially through the two components to act as fasteners and to maintain the relative disposition of the components during resin injection. After injection the assembly is cured and the control rods may remain in situ or be removed from the structure.

Abstract: In the formation of a fiber reinforced composite material component produced by a resin transfer infusion process such as to have an electrically conductive surface layer for lightning strike protection wherein the component is to be drilled and countersunk to receive an electrically conductive fastener, a localized part of the electrically conductive mesh is deformed so as to be relocated in the countersunk recess thus to ensure electrical contact with the fastener when inserted and to eliminate any gap between the mesh and the fastener, thus determining the electrical conductive integrity of the mesh to avoid arcing in the event of lightning strike attachment.

Abstract: A draining device for draining a fluid from an aircraft engine support strut includes a suction arrangement having an inlet and extending along a longitudinal main axis to form a plenum chamber and a drain tube fluidly connected to the aircraft engine support strut and extending along the longitudinal main axis, the drain tube ending by an outlet, the outlet of the drain tube terminating within the plenum chamber of the suction arrangement. An air flow entering the inlet of the suction arrangement causes a low-pressure region to be created within the plenum chamber, substantially downstream the outlet of the drain tube.

Abstract: A nacelle for an engine has outer and inner cowl doors that are independently rotatable about offset hinge lines. A connection device is provided for selectively connecting the outer and inner cowl doors so as to cause them to open simultaneously. The inner cowl door is arranged to rotate by a greater angle than the outer cowl door so as to improve access to the engine for maintenance purposes.