Abstract: There is disclosed a filter for a vehicle window comprising a layer of filter material, the layer of filter material being for substantially preventing the transmission of radiation at a first predetermined visible wavelength band, the first predetermined visible wavelength band covering the wavelength of a predetermined laser threat, whilst substantially allowing visible wavelengths outside of the band to be transmitted, such that the filter can offer a visible light transmission of at least 70%, and a radiation detector, such that radiation at the first predetermined wavelength band can be detected.

Abstract: A workstation comprising a chassis having a base frame (10) and a monitor frame assembly (11), said base frame (10) defining a work area (20) at its proximal end for accommodating a user therein, in use, wherein a desk unit (24) is mounted laterally across said work area and provides a work surface for use by a user accommodated in said work area (20), in use, said monitor frame assembly (11) comprising an outer frame, extending laterally across said base frame (10) and upwardly from its distal end, and an inner frame (32) mounted within said outer frame and configured to receive thereon a plurality of monitor brackets (45), wherein said desk unit (24) is longitudinally adjustable relative to said base frame (10) so as to selectively adjust its distance from the monitor frame assembly (11), and said inner frame (32) is vertically adjustable within, and relative to, said outer frame so as to selectively adjust its height relative to said base frame; and further wherein respective locking means are provided to

Abstract: An air vehicle (10) comprising a main body (12) and a pair of opposing wing members (14a, 14b) extending substantially laterally from the main body (12) having a principal axis orthogonal to the longitudinal axis (20) of said wing members, at least a first propulsion device (16a) associated with a first of said wing members arranged and configured to generate a linear thrust relative to the main body in a first direction, and a second propulsion device (16b) associated with a second of said wing members arranged and configured to generate linear thrust relative to said main body in a second, substantially opposite, direction such that said wing members and said main body are caused to rotate about said principal axis, in use, the air vehicle further comprising an imaging system (100) configured to cover a substantially 360° imaging area about said principal axis and comprising at least one electro-optic sensor (102) mounted on a support member (104) and having a field of view (102a) covering a portion of said

Abstract: There is provided an apparatus and method for disrupting radar systems. The apparatus comprises a chamber (110) for attachment to a vehicle, a radar countermeasure material (130) in the chamber, the radar countermeasure material comprising a plurality of hollow fibres, wherein the inner surface of at least some of the hollow fibres is at least partly coated with a conductive substance, and a release means (140) for dispensing the radar countermeasure material out of the chamber.

Abstract: An adaptive camouflage device that includes at least one non-emissive layer which includes a guest-host liquid crystal (GHLC).

Abstract: A laser diode array (102) comprising a plurality of laser diodes (201-210) and a channel (212) proximate to each of the laser diodes (201-210), the channel (212) configured to receive and provide a passage for a flow of a fluid coolant; wherein the laser diodes (201-210) are configured to emit electromagnetic radiation having the same centre wavelength at different respective junction temperatures. A coolant supply system (104) coupled to the laser diode array (102) may cause coolant to flow through the channel (212). A flow rate of the coolant through the channel (212) may be controlled based on temperature measurements of the coolant prior to entering, within, and/or after exiting the laser diode array (102).

Abstract: The present invention provides a vehicle comprising: a rotor and a stator; at least one planar control surface coupled to the rotor, wherein the rotor is configured to rotate relative to the stator such that, in use, the at least one planar control surface moves from a first position to a second position, and wherein in the first position the planar control surface is controllable to affect substantially only the pitch of the vehicle and in the second position the planar control surface is controllable to affect substantially both of the pitch and yaw of the vehicle, or substantially only the yaw, or in the first position the planar control surface is controllable to affect substantially only the yaw of the vehicle and in the second position the planar control surface is controllable to affect substantially both of the pitch and yaw of the vehicle, or substantially only the pitch of the vehicle. The present invention also provides a method of controlling a vehicle.

Abstract: Disclosed is a method and apparatus for physically coupling together a first aircraft and a second aircraft, for example for the purpose of performing air-to-air refueling. The first aircraft is an aircraft in flight. The second aircraft is an aircraft in flight. The method comprises: sending, from a transmitter located on the first aircraft, an electromagnetic signal; receiving, by a receiver located on the second aircraft, the signal; and controlling, by one or more processors, using the signal received by the second aircraft, at least one of the first and second aircraft such that the first and second aircraft are in a predetermined configuration in which the first and second aircraft are physically coupled together, for example attached together.

Abstract: An end effector for a robot having a threaded shaft; a motor coupled to the shaft and configured to rotate the shaft about its axis; a nut threaded onto the shaft; a feature for preventing the nut from rotating about the axis of the shaft; and an elongate member fixed at one end to the nut and extending from the nut in a direction parallel to the axis of the shaft. The end effector may further include a container for containing a fluid having an elongate body portion having an opening at one end; and a reciprocable plunger extending into an opposite end of the body portion. A second end of the elongate member may be coupled to the plunger.

Abstract: The present invention provides a pod (100) for an aircraft (1000), comprising: a housing (1); a unit (2) comprising a propulsion system, the unit comprising at least one attachment point (5) for coupling the unit to the housing (1), wherein the position of the unit relative to the housing is selected from a plurality of positions based on the centre of gravity of the aircraft, such that deflection of control surfaces required for the aircraft to maintain a constant angle of attack is minimised. The invention also provides an aircraft (1000) having the pod (100) and a method of balancing the aircraft (1000).

Abstract: An airframe (10) for an air vehicle comprising an outer skin layer (12) and a support layer (13) defining a fuselage of said air vehicle, wherein said outer skin layer (12) is magnetically coupled to said support layer (13).

Abstract: A method of producing part of an aircraft comprising: providing a frame having a first surface, a second surface, and one or more side edges between the first and second surfaces; mounting the frame to a first tool, the first tool comprising a support surface that contacts the second surface of the frame to opposing movement of the frame; while the frame is mounted to the first tool, machining the first surface to form attachment features; mounting the machined frame to a second tool which contacts with the frame at only the one or more side edges; and, while the frame is mounted to the second tool, attaching, using the attachment features, to the first and second surfaces, aircraft panels to form an outer skin.

Abstract: An apparatus and method for displaying an operational area, the apparatus comprising a headset (10) for placing over a user's eyes, the headset including a viewing device (12) configured to provide to said user, in use, a view of a real-world environment, a display generating device for depicting an operational area, said operational area being defined within said real-world environment and comprising a plurality of functional regions each defining a different one or more selectable functions or operations that can be performed in respect of said operational area, the apparatus being configured to transfer image data from said display generating device into said user's view of said real-world environment at said viewing device to generate an augmented reality environment, the apparatus further comprising a control module (26) including a control device (28) configured to be selectively communicably coupled to all of said functional regions to enable a user to selectively perform the respective one or more fun

Abstract: A display apparatus and method for displaying an operational area to an operative of a host platform, said operational area being defined within an external real-world environment relative to said host platform, the apparatus comprising a viewing device (12) configured to provide to said operative, in use, a three-dimensional view of said external real-world environment; a display generating device for creating images at the viewing device, a user input (33) configured to receive user input data (35) representative of a specified target or region in respect of which an operation is to be performed, and thereby defining an initial geometric volume for the operational area, said user input data including data representative of the location within said external real-world environment of said specified target or region and data representative of said operation to be performed in respect thereof; and a processor (32) configured to: use said user input data to generate or obtain three-dimensional image data represe

Abstract: Disclosed is a temperature measurement device (4) and method of using the same. The device (2) comprises a base portion (14), a plate (16), and a temperature sensor (22). The base portion (14) comprises a first surface and a second surface opposite to the first surface and spaced apart from the first surface. The base portion (14) is more thermally insulating than the plate (16). The plate (16) comprises a first surface and a second opposite to the first surface. The plate (16) is disposed on the first surface of the base portion (14) such that the second surface of the plate (16) is in contact with the first surface of the base portion (14). The temperature sensor (22) is coupled to the first surface of the plate (16) such that the temperature sensor (22) measures a temperature of the first surface of the plate (16).

Abstract: The present invention provides an actuating system, comprising: a rotatable member rotatable relative to a fixed member; at least one actuator coupled to the rotatable member and to the fixed member; and a planar control surface coupled to the rotatable member such that the control surface extends perpendicularly from the periphery of the rotatable member wherein, in use, when a first actuator is in a first configuration the rotatable member is rotated such that the planar control surface is arranged in a first position, and when the first actuator is in a second configuration the rotatable member is rotated such that the planar control surface rotates about the central axis of the rotatable member to be arranged in a second position. The present invention also provides a vehicle and a part for a vehicle having the actuating system, as well as a method of actuating a control surface for a vehicle.

Abstract: Producing an object (2), comprising: providing a tool (10) having a mould surface (14); applying uncured composite material (12) to the mould surface (14) to form an assembly (8); curing the assembly (8) to produce cured composite material (12?) having a surface (16?) the same shape as the mould surface (14); providing a digital model (24) of the object (2) specifying a first surface (4) and a second surface (6) of the object (2), the first surface (4) being the same shape as the mould surface (14); and, while the cured composite material (12?) is held against the mould surface (14), machining, using the digital model (24), a further surface (18?) of the cured composite material (12?) such that it has the same shape as the second surface (6) and the same position relative to the mould surface (14) as the second surface (6) relative to the first surface (4).

Abstract: According to an aspect of the invention, there is provided a laser weapon system, comprising: one or more lasers for generating electromagnetic radiation; laser optics for directing the generated electromagnetic radiation at a target; and a control system, the control system being arranged to monitor three-dimensional position of an object other than the target, and to control a mask to at least limit generated electromagnetic radiation being directed at that object or to direct generated electromagnetic radiation towards another target or a safe location.

Abstract: Disclosed is a method of producing an airframe component. The method comprises: providing an initial component having a first surface; providing an over press tool having a second surface complementary to the first surface; applying, to the first surface, an adhesive (94), one or more layers of a material; at least for some time during curing of the adhesive, positioning the over press tool such that the second surface is in contact with an outer surface of the material and the material is between the first and second surfaces, and forcing the over press tool against the first surface such that a normal force is exerted on the first surface; and, thereafter removing the over press tool from the one or more layers of material, thereby providing the airframe component.

Abstract: A liquid storage system comprising: a tank for containing a liquid, the tank enclosing a liquid storage space; and a tank liner fixedly attached to an internal surface of the tank (16). The tank liner comprises: a plurality of elements, each element having a hardness value of 2 GPa or above; and a binder material in which the plurality of elements are embedded. The elements have a higher hardness value than the binder material. A distance between a first element and the internal surface of the tank in a direction normal to the internal surface of the tank is different to a distance between a second element and the internal surface of the tank in the direction normal to the internal surface of the tank, the first element being different to the second element.