Abstract: The invention comprises of a UAV designed to limit visually contrast and audibility in flight for covert surveillance operations, a method of configuring the UAVs structure to further reduce its visual signature to take account for the atmospheric and terrestrial environment it will operate in and a method of conducting a covert surveillance operation to actively minimise the UAVs visual & auditory signature from the viewpoint of an individual under surveillance. Both passive and active illumination are used to reduce the visual signature of the UAV. The UAV is actively camouflaged using lighting techniques that utilises the limitations of the human visual system and the optical effects of light interacting with the terrain, atmosphere and aircraft. The visual camouflage is directional. The audible signature of the UAV is reduced through the design of the propulsion system and the mode in which the UAV is operated.

Abstract: An oscillation system comprises an oscillation circuitry configured to cause at least one motor of a first set of motors to provide an oscillation of a user-input device in at least one axis of the user-input device. The oscillation may be triggered in response to an input from at least one sensor, the user-input device for operating an aircraft control system of an aircraft. The oscillation circuitry is configured to operate independently from a resistive force circuitry. The resistive force circuitry is to provide a resistive force to the user-input device, using the at least one motor of the first set of motors.

Abstract: Disclosed is an antenna comprising a substantially elliptical element arranged substantially perpendicular to, and spaced apart from, a substantially elliptical ground plane, wherein the substantially elliptical element has a major axis which is substantially perpendicular to the ground plane, and a minor axis which is substantially parallel to the ground plane.

Abstract: The invention relates to Polymerisable Binders, and Insensitive Munition (IM) energetic materials particularly to non-phthalate IM propellant compositions which are printed by a UV curing additive layer manufacture process. invention there is provided an additive layer deposable energetic composition suitable for use as a propellant comprising the following components in the following relative proportions: component A; from 60% to 95% by weight of a highly energetic filler comprising at least one nitramine compound; and component B: from 5% to 20% by weight of a binder, wherein the binder contains component D a UV curable binder in the range of from 3% to 12% by total weight of the formulation, at least one UV photoinitiator, component C: from 1% to 15% of a plasticiser, the percentages by weight of components A, B, D and C, together with minor additives, if any, adding to 100%.

Abstract: The invention relates to a cast explosive composition. There is provided a precure castable explosive composition comprising an explosive material, a polymerisable binder, said cross linking reagent comprising at least two reactive groups each of which is protected by a labile blocking group.

Abstract: A turbine module (100) for a heat engine (104) wherein the turbine module (100) defines a working fluid flow duct (60) between a turbine module inlet (110) and a turbine module outlet (114) configured to expand a working fluid as the working fluid passes along the working fluid flow duct (60). The turbine module comprises a first heat exchanger (37) and a turbine rotor stage (24) each provided in the working fluid flow duct (60). The first heat exchanger (37) is provided in flow series between the turbine module inlet (110) and the turbine rotor stage (24); and the turbine stage (24) is provided in flow series between the first heat exchanger (37) and the turbine module outlet (114). The first heat exchanger (37) defined by a wall (126) having an external surface (182) which is located in the working fluid flow duct (60).

Abstract: An apparatus for use with a cable, wherein the apparatus comprises a conduit and a stopper, wherein the stopper is formed in one or more parts from a plastic; the stopper comprises an internal hole which is configured to accommodate a cable and the stopper has an outer surface of which at least a part conforms to the geometry of one end of the conduit; the geometry of the one end of the conduit is flared and accommodates the shape of the stopper; and the conduit is configured to accommodate the cable.

Abstract: A workbench system comprising: a workbench; a multi-axis robot; a visible light projector; and a controller; wherein the workbench and the robot are located in a common workspace; the controller is configured to: determine a movement operation for the robot; and, using the determined movement operation, control the visible light projector to project a visible light indication onto at least one of a surface of the workbench and a surface of the workspace; the visible light indication indicates a limited area of the workbench and/or workspace, the limited area corresponding to a limited volume of space; and the movement operation is such that, if the robot performs the movement operation, the robot moves entirely within only the limited volume of space.

Abstract: A payload mechanism for a vehicle is provided.

Abstract: Aircraft control systems to enable shared input controls. A single inceptor may provide outputs to control both land-based aircraft controls and air-based aircraft controls to reduce the number of inceptors required. In an example a side-stick provides control of both pitch and aircraft nose-wheel steering. Active inceptor technology may be utilised to provide feedback to the operator on the control system state.

Abstract: There is provided an integrity monitor for a display system, the display system comprising an image source and a display. The integrity monitor comprises a controller configured to analyse sensed characteristics at one or more predetermined positions in an image area of the display system and to relate the sensed characteristics to predetermined characteristics of a stimulus, when injected into the system, thereby to determine the presence of a fault in the system. The sensed characteristics may be sensed optically or non-optically. The stimulus may be optical or non-optical.

Abstract: A radio frequency circuit for processing a radio frequency signal. The circuit comprises a variable frequency oscillator system and a radio frequency signal processing circuit arranged to process a radio frequency signal using the output of the variable frequency oscillator system. A digitiser is arranged to receive the output of the radio frequency signal processing circuit and generate a digitised signal. A phase noise capture circuit is arranged to capture the phase noise in the output of the variable frequency oscillator system. The radio frequency circuit is arranged to compensate for the effect of the phase noise in the output of the variable frequency oscillator system on the output of the radio frequency signal processing circuit, by digitally processing the digitised signal generated by the digitiser using the output of the phase noise capture circuit.

Abstract: The present invention provides a sabot (8) comprising a first material structure (12, 14) and a second material structure, wherein the first material structure is a lattice and wherein the second material structure is a solid. A munition (100) and a method of manufacturing a sabot are also provided.

Abstract: An aircraft (101) is provided with a single centrally located inceptor (110) for controlling pitch and roll of the aircraft. The inceptor (110) is provided with a double grip (11, 112) so that it may be comfortably operated by either a pilot or a co-pilot. A central location for the inceptor ensures that its motion and position is visible to both pilot and co-pilot. Not only is this a benefit from a safety point of view but also during pilot training. Alternatively, two inceptors (411, 412) are provided in the centre console (406) adjacent to one another for operation respectively by the pilot and co-pilot and may be mechanically linked. Optionally, the aircraft may be provided with outboard throttle quadrants (117, 118) for operation respectively by the co-pilot and pilot. The outboard throttle quadrants may be mechanically linked together.

Abstract: Disclosed is an anti-vibration apparatus comprising a bush, said bush comprising a substantially rigid, elongate core, covered in a vibration dampening material having at least one end cap washer, configured in that the bush engages with the end cap washer to cover the end of the elongate core, characterised in that the vibration dampening material further comprises a plurality of recessed portions on its surface.

Abstract: A diffuser for use in a head up display formed of an array of microlenses. The microlenses comprises both concave and convex microlenses to reduce surface discontinuities between adjacent lenses.

Abstract: The invention relates to a cast explosive composition. There is provided a precure castable explosive composition comprising an explosive material, a polymerisable binder, said cross linking reagent comprising at least two reactive groups each of which is protected by a labile blocking group.

Abstract: A coating material (10) for coating an article is described. The coating material (10) comprises a surface (100) having an optical interference coating (110) thereon. The coating material (10) improves protection of the article from incident electromagnetic radiation having a predetermined wavelength. The coating material (10) may retroreflect at least some of the incident electromagnetic radiation, for example towards a source (e.g. a laser) thereof. An article having a coating provided by such a coating material and methods of providing such coating materials are also described.

Abstract: The present invention provides a structure at least partially transparent to radio frequency signals, the structure being formed of a tessellated polyhedral material comprising a plurality of polyhedral cells. The present invention also provides a method of manufacturing the same.

Abstract: Apparatus (100) for use in space, the apparatus (100) comprising: a feedstock storage module (108) for storing a feedstock; a heating module (110) coupled to the feedstock storage module (108) and configured to heat the feedstock; an extrusion nozzle (112) coupled to the heating module (110) and configured to extrude heated feedstock from the apparatus (110); and one or more thrusters (118) configured to provide a propulsive force to the apparatus (100).