Abstract: An aircraft is disclosed having a structure at least part of which is capable of generating aerodynamic lift. A body having a mass is movably mounted to a portion of the structure by an active support. The active support includes an actuator to move the body relative to the portion of the structure, and a controller for controlling movement of the actuator in response to a dynamic input. The active support provides a range of movement for the body in at least one degree of freedom. The actuator moves the body across the entire range of movement in that one degree of freedom in a time period of less than 3 seconds. The actuator moves the body sufficiently rapidly to generate an inertial force that is equal to or greater than any aerodynamic force generated by the body during that movement of the body. The active support may be used to reduce loads on the aircraft structure.

Abstract: An aircraft (2) including a wing (1), the wing (1) having a fixed wing (3) and a wing tip device (4) at the tip of the fixed wing (3), the wing tip device (4) being rotatable relative to the fixed wing (3) between flight and ground configurations, the aircraft including a rotational joint (10) with a rotation mechanism (11) that rotatably couples the wing tip device (4) to the fixed wing (3) and a locking mechanism including a locking bore (53, 54) and a locking pin (51) that is receivable in the locking bore to lock the wing tip device (4) in one of the flight or ground configurations, wherein the rotational joint includes an alignment mechanism including an alignment pin (61) and an alignment bore (62, 63) and at least one of the alignment pin and alignment bore is tapered such that engagement of the alignment pin (61) in the alignment bore acts to guide the locking bore and locking pin into alignment.

Abstract: An aircraft having a wing, including a fixed wing with a wing tip device movably mounted at the outer end thereof is disclosed. The wing tip device is movable between: a flight configuration; and a ground configuration. The wing tip device and the fixed wing are separated along an oblique primary cut plane. The wing tip device and the fixed wing meet along an interfacing cut line. The wing tip device and fixed wing comprise a wing skin with a thickness, and end faces extending across the thickness of the wing skin provide interfacing surfaces corresponding to the interfacing cut line, wherein the interfacing surfaces are angled at a first orientation towards the front of the wing and a second, opposite, orientation towards the rear of the wing.

Abstract: An airfoil structure comprising a torsion-box member with a cover and a spar web connected by at least one pivot joint to a leading-edge or trailing-edge member, wherein the pivot joint is configured to permit rotation of the leading-edge member, or trailing-edge member, relative to the torsion-box member between an installation position and an operational position.

Abstract: An aerodynamic body for use on an aircraft including at least a first perforated surface portion (25) and an ice-protection system (31). The first perforated surface portion (25) has perforations. The ice-protection system (31) includes an actuatable element (33) and the actuatable element (33) is movable or deformable between a first position and a second position. In the first position, the actuatable element (33) is thermally coupled to the first perforated surface portion (25) and configured to prevent an inflow or outflow between a boundary layer of an outer aerodynamic airflow and the aerodynamic body through at least one of the perforations. In the second position, the actuatable element (33) is distanced from the first perforated surface portion (25) and configured to allow an inflow from a boundary layer of an outer aerodynamic airflow through at least one of the perforations into the aerodynamic body.

Abstract: An apparatus and method is disclosed for determining a temperature characteristic at a first location on a wheel or a brake assembly of an aircraft landing gear. The temperature characteristic at the first location is determined using relationship information based on a first temperature at a second location of the wheel or the brake assembly of the landing gear, the relationship information representing a relationship between the temperature characteristic at the first location and the first temperature. Also disclosed is a method to determine the relationship information.

Abstract: A method of retrofitting a wing of a fixed wing aircraft is disclosed including the steps of providing an existing aircraft wing with a main fixed wing portion, and the main fixed wing portion having a tip end and an existing movable flight control surface connected adjacent the tip end. The existing movable flight control surface is then removed from the main fixed wing portion, and a wing tip device and movable flight control surface are selected as a pair to replace the existing movable flight control surface, with the selected movable flight control surface having an aerodynamic surface of different shape to the shape of the flight control surface removed from the wing. The selected wing tip device and movable flight control surface are then fitted to the main fixed wing portion.

Abstract: An aircraft structure, for example a wing, including a skin. The skin has an external surface, on an outer face of the skin. The skin has an internal surface, located opposite the external surface on an inner face of the skin. The aircraft structure includes a laminar flow control system including a compressor. The aircraft structure is so arranged that the exhaust air from the compressor is directed onto the internal surface of the skin of the aircraft structure, for example thus providing hot exhaust air which function as an ice protection system (whether by de-icing or anti-icing). A method of providing ice protection on a surface of an aircraft using exhaust air from a laminar flow control compressor is also described.

Abstract: An aircraft landing gear arrangement with an airbag attached inside a landing gear bay is disclosed. The airbag has a deflated configuration and a first inflated configuration, wherein, when the landing gear is in the extended position and when the airbag is in the first inflated configuration, the airbag closes off the landing gear bay. The airbag may substantially close off the landing gear bay. The airbag may comprise an external surface, wherein the external surface of the airbag closes off at least a significant proportion of the landing gear bay and lies substantially flush with an external surface of the aircraft body. An aircraft, methods of operating a landing gear arrangement, and methods of operating an aircraft are disclosed.

Abstract: A joint for connecting a first aircraft structure to a second aircraft structure such that relative rotation and relative translational movement of the first and second aircraft structures along a first axis is permitted, whilst relative translational movement of the first and second aircraft structures along axes orthogonal to the first axis is substantially prevented. The joint includes a bracket having an opening aligned with the first axis; a pin aligned with the first axis and extending through the opening; and a bearing mounted in the opening. The bearing has an inner bearing surface defining a bore through which the pin extends, which is configured for translational sliding contact with the pin, and a part-spherical outer bearing surface configured for rotational sliding contact with the opening.

Abstract: A winglet for attachment to a wing portion of an aircraft is disclosed having a winglet tip and a winglet root opposite from the winglet tip. The winglet has an opening for receiving therethrough a connector for connecting the winglet to a wing portion in use. The winglet has a retainer internal of the winglet for use in retaining the connector relative to the winglet. The retainer has a hole that extends along an axis that passes through the opening for receiving therethrough a portion of the connector when the connector is located through the opening. The retainer includes a body for reacting against a retention component with which the connector engages in use.

Abstract: A winglet for attachment to a wing portion of an aircraft is disclosed having a winglet tip and a winglet root opposite from the winglet tip. The winglet has an opening for receiving therethrough a connector for connecting the winglet to a wing portion in use. The winglet has a retainer internal of the winglet for use in retaining the connector relative to the winglet. The retainer has a hole that extends along an axis that passes through the opening for receiving therethrough a portion of the connector when the connector is located through the opening. The retainer includes a body for reacting against a retention component with which the connector engages in use.

Abstract: An aircraft (1002) including a wing (1001), having a fixed wing (1005) with a wing tip device (1003) moveably mounted at the outer end thereof. The wing tip device (1003) is moveable between: a flight configuration; and a ground configuration about an axis of rotation. The wing tip device (1003) and the fixed wing (1005) meet along an interfacing cut line (1035). The interfacing cut line (1035) includes a curved section (1039) cent red on the axis of rotation (1011), the radius of the curved section constantly increasing as the cut line passes around the axis (for example a spiral shape).

Abstract: Apparatus for laminar flow control for a skin panel for an aircraft including a body for receipt into a recess of the skin panel. The body defines a chamber. The body includes an outer portion defining one or more micro apertures through the outer portion, each of the one or more micro apertures being in fluid communication with the chamber. The body includes a support portion supporting the outer portion, the support portion defining at least one outlet for allowing air to be drawn from the chamber in use by a suction means in fluid communication with the outlet in use. The apparatus is arranged such that, in use, air is drawn through the one or more micro apertures into the chamber and out of the outlet, thereby to promote laminar airflow over the outer portion in use.

Abstract: A duct stringer is disclosed including a structural member with a hat-shaped cross-section. The structural member has a crown, a pair of webs and a pair of feet. A channel member with a U-shaped cross-section has a base and a pair of flanges. The flanges of the channel member are co-cured to opposed inner faces of the webs of the structural member. The structural member and the channel member together provide a duct with a closed cross-section which is adapted to transport fluid, for instance in an aircraft wing to provide a vent function in an aircraft fuel system.

Abstract: A control system has first and second processing modules for controlling retraction and extension of an aircraft landing gear assembly. The processing modules operate independently providing redundancy. Each processing module is configured to perform a first sequence of steps for retracting the landing gear assembly and a second sequence of steps for extending the landing gear assembly. A step of switching control from one processing module to the other (e.g. an avionics side changeover step) is performed (a) as part of the first sequence of steps, but only after the landing gear assembly has been retracted, or (b) as part of the second sequence of steps. By ensuring that the step of switching control is performed at such times, and not for example between initiation of the first sequence of steps and the retraction of the landing gear assembly, the landing gear assembly may be retracted sooner after such initiation.

Abstract: A brake cooling period prediction system for predicting a brake cooling period following a braking event, comprising a sensor apparatus in communication with a prediction apparatus. The sensor apparatus includes a torque sensor for measuring the torque reacted by a brake during a braking event; a wear sensor for measuring a wear state of the brake; and an environmental sensor for measuring at least one ambient condition of the environment of the brake. The prediction apparatus includes a memory storing information relating to the thermal behaviour of the brake; and a controller configured to receive a torque measurement, a wear measurement and an ambient condition measurement from the sensor apparatus; and predict a cooling period based on the received torque, wear and ambient condition measurements, and the information relating to the thermal behaviour of the brake.

Abstract: A cap is disclosed having a collar portion with three or more contact regions arranged to contact the end of a fastener around which the collar portion is provided, the collar portion having a lobed shape in cross-section such that an outwardly projecting lobe extends between each neighbouring pair of contact regions. An advantage of this lobed arrangement is that the cap can tolerate relatively large manufacturing tolerances at the fastener end. The cap may be for fitting over a nut or fastener head, with the contact regions of the cap being arranged to contact corresponding contact regions on a cylindrical collar base portion of the nut or fastener head. The diameter of this cylindrical collar portion may not be well controlled, so that the manufacturing tolerance is high. The lobed shape of the cap base ensures that the contact regions will always provide a good frictional engagement with the nut, whether the cylindrical collar is undersized, oversized, or at its nominal diameter.

Abstract: A wing assembly with at least two ribs is disclosed. Each rib defines a rib plane and has a peripheral edge. A fluid pipe extends through each rib plane and is disposed external to the peripheral edge of each rib. The fluid pipe is coupled to each rib.

Abstract: A cap for forming a sealed cavity around an end of a fastener is disclosed. The cap has a cap body with an annular base terminating at a base rim which surrounds an opening into a central cavity. The cap also has an annular skirt providing an annular pocket between the skirt and the base. An inlet hole is provided in the skirt which is in fluid communication with the annular pocket. A protuberance protrudes in the annular pocket and faces the inlet hole to promote a flow of sealant injected through the inlet hole to flow annularly around the annular pocket.