Abstract: An aircraft fuel tank assembly includes a tank for holding fuel, a canister and a fuel pump assembly. The fuel pump assembly includes: an electric motor, a pump and an electronics unit. The electronics unit and canister are arranged so that, in use, a dry bay is defined between the electronics unit and the canister.

Abstract: The present invention relates to a stringer for an aircraft wing and a method of forming such a stringer in which the stringer is formed form a single piece of material and has differential strength along its length.

Abstract: A landing gear support assembly comprises a first support member, for example a gear rib, extending from the rear spar of an aircraft, and a pintle support assembly for holding a pintle on which a landing gear assembly may be supported. The pintle support assembly is distinct from the rear spar, and is arranged such that the longitudinal axis of a pintle is offset from the support member in a direction along the length of the rear spar. This arrangement may allow a stowed landing gear assembly to be wholly contained within the aircraft wing. The landing gear support assembly may contain additional structure, for example a composite false spar, for distributing loads to various regions of the rear spar. The additional structure may also form a torsion box which reduces the stress and shear force transmitted to the rear spar.

Abstract: The load on an aircraft component is measured. In one embodiment, the system is a contactless, all-weather displacement measuring system including a processing unit and a plurality of pairs of controllable microwave emitters and microwave detectors. When the aircraft component is subjected to a load, relative movement of the emitter and detector is caused. The detector generates signals which convey information concerning the relative positions of the emitter and the detector of the pair, the signals being received and processed by a signal processor of the processing unit. The processing unit may, for example with the use of triangulation techniques, provide an output signal representative of the load sustained by the aircraft component. The system may be used to control braking in dependence on the output signal so as to maximise braking efficiency without overloading the landing gear leg.

Abstract: A method of designing a composite panel, the panel comprising a plurality of zones, each zone comprising a plurality of plies of composite material, each ply in each zone having a respective orientation angle, and some of the plies running continuously between adjacent zones. A design is provided comprising a set of design variables including a thickness for each of the zones, and a ply percentage for each orientation angle for each of the zones, each ply percentage identifying a percentage of plies within a zone having a particular orientation angle.

Abstract: A joint comprising: a first component having a face and a bore defined by a bore wall; a second component; a fastener joining the first component to the second component, the fastener comprising a head and a shaft protruding from the head; and a polysulphide gasket comprising a ring which is compressed between the head of the fastener and the face of the first component; and a collar between the shaft of the fastener and the bore wall. The gasket comprises a ring of sealing material surrounding a hole for receiving a fastener, the sealing material comprising an at least partially cured polysulphide sealant. The gasket has a region of increased thickness positioned towards the inner periphery of the ring which flows to form the collar.

Abstract: An aerofoil structure comprises first and second opposed skin components which are joined together and spaced apart by a pair of opposed spar components. The skin components have respective outer and inner surface profiles. The skin and spar components define a space envelope and a rib is arranged within the space envelope. The rib comprises a rib body and a series of rib feet. The rib feet comprise a leg and a rib foot plate. The rib foot plate is dimensioned, positioned and angled so as to conform to the inner surface profile of the skin component against which it is intended to be arranged.

Abstract: A composite material elongate structural member, such as a spar or stringer, for use in an aerospace structure, comprises a web having an angled portion, for example in the form of a chamfer, curved surface or the like, which joins a foot of the member to the rest of the web. A first surface on the foot is shaped to abut a structure to be stiffened. The foot also has a second surface opposite the first surface. The web has a third surface and a fourth surface at the same layer in the composite material as the first and third surfaces, respectively. On/in the interposed portion there is a fifth surface which joins the first and third surfaces. The geometry of the member may vary along its length (L) so that with increasing distance, the first surface is displaced towards the second surface as the width of the fifth surface decreases.

Abstract: A multi layer composite L-shaped stringer for use in an aerospace structure comprises a foot and a web extending from an edge of the foot. A first surface on the foot is shaped to abut a structure to be stiffened. The foot also has a second surface opposite the first surface. The web has a third surface and a fourth surface at the same layer in the composite material as the first and third surfaces, respectively. The geometry of the stringer may vary along its length (L) so that as the first surface is displaced towards the second surface, the fourth surface is displaced towards the third surface. The developed width (DW) from the distal edge of the foot to the distal edge of the web of the stringer may be substantially constant for all cross-sections along a length of the stringer.

Abstract: A composite material elongate structural member, such as a spar, for use in an aerospace structure, comprises a web disposed between upper and lower flanges. The web may include a clockwise twist about an axis parallel to the length L at a first portion towards the wing-root-end of the spar and a counter-twist in the anticlockwise direction at a second portion towards the wing-tip-end of the spar. The geometry of the spar may vary non-linearly along its length (L) so that the developed width of the spar as measured from a distal edge of the upper flange via the web to a distal edge of the lower flange varies linearly with increasing distance along the length (L). The risk of causing, during fabrication of the spar, undesirable creasing, stressing or stretching of composite material layers in a region in which the geometry of the member varies non-linearly may be reduced by means of such an arrangement.

Abstract: An aircraft structure, for example a wing (20), includes a structural skeleton having structural elements (for example, spars (60) and ribs (70)) enclosed within a skin (200). A fastener (110a,b) is fastened to the skeleton and wholly within the skin (200). The fastener (110a,b) fastens to the structure (20) a bracket (120) for carrying stores (80). The fastener (110a,b) includes a body (300) defining an internal bore (230). The body (300) includes an internal threaded region (330), within the internal bore (230), for fastening the bracket (120) to the aircraft structure (20).

Abstract: A pin bearing arrangement for use on an aircraft landing gear includes a pin and a load sensor arrangement, which may include strain gauges for measuring shear loads and accelerometers for measuring loads sustained by the pin. The pin includes a self-contained data logging device for logging data concerning loads sustained by the pin. Thus, inside the pin, there may be provided a processing unit, a memory store, and a battery-based power source. During normal operation of the aircraft fatigue loads may be monitored, the processing unit receiving input signals from the means for measuring loads and storing load data in the memory. The stored load data may periodically be extracted from the memory during maintenance of the aircraft.

Abstract: A winglet comprising a root connected to a distal end of a wing; an upwardly angled section; a tip; and a transition between the upwardly angled section and the tip at which an outboard cant angle of the winglet decreases relative to a reference plane of the wing. In one embodiment the winglet is continuously curved and includes a point of inflection at which the span-wise curvature of the winglet changes sign. In another embodiment the upwardly angled section is planar. The winglet generates a tip vortex when in flight. The tip vortex is displaced outboard from the winglet due to the decrease in outboard cant angle at the transition.

Abstract: The invention relates to an aircraft toilet facility, particularly an aircraft toilet facility on a single passenger-deck aircraft. The invention provides a first toilet unit (105) situated at least partially in the space (113) below the floor (103) of a passenger deck of the aircraft, and a second toilet unit (108) situated at least partially in the space (114) above the ceiling (104) of the passenger deck. The first toilet unit (105) is proximate the second toilet unit (108), and both the first toilet unit and second toilet unit are accessible from the passenger deck.

Abstract: Two aluminium alloy work-pieces are welded together. Firstly, a portion (2) of each work-piece (1) is prepared, the preparation including the performance of a surface treatment, such as friction stir welding, that results in a region (A) extending from the exterior surface into the work-piece having a grain structure that is finer than the grain structure of the work-piece outside (region C) that region. Then the work-pieces are welded together by means of a fusion welding process, such as electron beam welding, that joins the respective prepared portions (2) of the two work-pieces (1). The preparation of the work-pieces is so performed that said region (A) extends into the work-piece to a depth that exceeds the depth of material (region D) that is caused to melt during the fusion welding process.

Abstract: A valve system both controls fuel flow by means of a valve and senses the condition of the valve. The valve is actuated by an actuator via a rotatable shaft. Light is transmitted by a laser diode, via a polarising filter (which is mounted to rotate with the shaft), down the shaft, and is reflected by a mirror which directs the light back up the shaft via the filter to a receiver, which is able to detect different directions of polarisation of the light received. The polarisation of the light received by the receiver indicates whether the valve is open or shut. If no light is received a fault is deemed present. Thus, the condition of the valve is checked directly by means of an apparatus remote from the valve and the fuel.

Abstract: An electrical connector for providing electrical communication between a fixed structure (13) of an aircraft and a movable component (19) mechanically connected to the fixed structure, wherein the electrical connector is arranged to he mechanically connected to the fixed structure at a rust end of the connector and is arranged to be mechanically connected to the movable component at a second end of the connector, the electrical connector comprising a first telescopic element (17), at least a portion of which is electrically conductive and which is arranged to provide a first current path between the fixed structure and the movable component.

Abstract: A friction stir welding tool is used in welding structures. The tool comprises a shoulder and a probe extending from the shoulder. The probe has at least three sections equiangularly arranged around the longitudinal axis of the probe, each section comprising at least three contiguously arranged flats arranged about the axis of the probe. The flats are so arranged that the normal axes of the flats converge in a direction towards the axis of the probe thereby resulting in the sections each having a generally convex shape. The probe also includes a threaded portion disposed between each pair of adjacent generally convexly shaped unthreaded sections.

Abstract: An apparatus is disclosed for monitoring the load on at least one part of an aircraft landing gear during landing of the aircraft. The apparatus comprises a housing containing a sensor which senses a parameter indicative of the load in the part of the landing gear, a processor which receives signals from the sensor and processes the signals to produce data representative of the parameter measured by the sensor, a battery which provides electrical power to the processor, a memory for storing measurement data from the processor, and a wireless transmitter which is controlled by the processor. The wireless transmitter is arranged to transmit at least some of the measurement data from the processor to a remote device located outside of the housing.

Abstract: In an aircraft having an aircraft landing gear, the aircraft landing gear includes an arm, a leg and a bogie at the lower end of the leg. The bogie is moveable in a direction along the length of the leg and pivotable between a trimmed deployed position and a stowable position. The arm is mounted on the landing gear and is rotatable between a first position in which the bogie is positioned in the trimmed deployed position, and a second position in which the bogie is positioned in the stowable position. Movement of the arm can be effected by a positioning rotary actuator, which is not located in the primary or secondary load paths.