Abstract: At least one encoder processor of a simulator data processing system receives simulator data from a plurality of simulators comprising a plurality of video data, including first and second data having different frame rates, and non-audio/visual data, and outputs a respective plurality of compressed video streams. A scheduler of the at least one encoder processor uses frames of the video data to generate scheduled items, specifies a frame rate for capturing the frames, and generates encoded data based on the compressed video streams and the non-audio/visual simulator data. At least one further processor receives, decodes, and processes the encoded data. The at least one further processor executes a media player/renderer application that processes the compressed video streams and displays on the display a plurality of the decoded video data are simultaneously displayed on a display at the specified frame rate, together with information based on the non-audio/visual simulator data.

Abstract: There is provided a composition and method of deposing an initiatory composition, said composition, comprising a: (i) a nanothermite suspension of a metal(M)oxide and a metal (M?) in a solvent, wherein the average particle size of the metal(M)oxide and a metal (M?) is less than 1000 nm, provided that (M)?(M?), (ii) wherein said nanothermite suspension comprises a charging reagent comprising a reagent capable of forming a stable complex with each of the metal(M)oxide and the metal (M?), to from a metal(M)oxide complex, and a metal (M?) complex that have the same electrostatic charge, such that said metal(M)oxide complex and a metal (M?) complex repel each other in said suspension, wherein the admixture of the binder, nanothermite suspension charging reagent, has been caused to be mixed under Resonant Acoustic Mixing to provide a stable suspension of a nanothermite complex

Abstract: The scintillation detector assembly 10 comprises a first scintillation detector 11A of a set SSD of scintillation detectors 11, comprising a first scintillator 12A of a set SS of scintillators 12 and a first light sensor 13A of a set SLS of respective light sensors 13 optically coupled thereto, arranged to detect electromagnetic radiation and output a first signal; a first radiation source 14A of a set SRS of radiation sources 14, configured to emit first gamma radiation G1 of a first set SG of gamma radiation G, having a first reference energy RE1 of a set SRE of respective first reference energies RE; and a controller 15 configured to control a gain of the first scintillation detector 11A based, at least in part, on the first gamma radiation, having the first reference energy, detected by the first scintillation detector 11A.

Abstract: A method is provided for operating an image generator, arranged to generate and to output signals for displaying image elements of a predefined set of image elements, each image element being defined by respective varying deflection signals. A colour change trigger is firstly defined comprising an additional image element defined by varying deflection signals different to varying deflection signals of an image element of the predefined set. Varying deflection signals of the defined colour change trigger are generated and output thereby to indicate a respective colour for use in displaying an image element of the predefined set. An image generator is also provided, configured to implement the method. A method is also provided for generating digital colour image data from signals output by such an image generator. A display system is also provided incorporating such an image generator together with a colour change trigger detector and scan converter.

Abstract: An apparatus for a directed-energy weapon comprises an assessment system arranged to, during an assessment phase, perform an assessment of a target environment, wherein the target environment comprises a target; and a controller arranged to, during the assessment phase, control the directed energy weapon to direct energy towards the target environment so that the assessment system can perform the assessment using the directed energy.

Abstract: A compressor module (200) wherein the compressor module (200) defines a working fluid flow duct (60) between a compressor module inlet (210) and a compressor module outlet (214). The compressor module comprises: a first heat exchanger (37) and a compressor rotor stage (24) each provided in the working fluid flow duct (60). The first heat exchanger (37) is provided in flow series between the compressor module inlet (210) and the compressor rotor stage (24). The compressor stage (24) is provided in flow series between the first heat exchanger (37) and the compressor module outlet (214). The first heat exchanger (37) is defined by a wall (226) having an external surface (282) which is located in the working fluid flow duct (60). There is provided a heat sink unit (236) which defines a portion (240) of the working fluid flow duct (60) in flow series between the compressor rotor stage (24) and compressor module outlet (214).

Abstract: A signal transmitting device is provided for communicating with an aircraft in the vicinity of a landing area. The signal transmitting device configured to receive a signal from the aircraft and further configured to transmit a return signal to the aircraft automatically upon receipt of the signal. The return signal comprising information regarding the landing area. FIG.

Abstract: The present disclosure provides a payload activation device. The payload activation device comprises a camera having a fixed focal length, arranged to capture an image of an object on a platform for carrying a payload having the payload activation device, wherein, when the payload is in a first position relative to the platform, the image of the object is in a first focused state and, when the payload is in a second position relative to the platform, the image of the object is in a second focused state. The payload activation device also comprises a processor configured to determine whether the image of the object is in the first focused state or the second focused state and to cause actuation of an activation mechanism within the payload when the image of object is in the second focused state to activate the payload. The present disclosure also provides a deployable payload having the payload activation device and an aircraft for carrying the deployable payload.

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: An antenna 300 comprising a housing 310 with an internal cavity 315. The cavity 315 holds an adjustable amount of electrically conductive liquid, and a twin-conductor feedline 350 connects the antenna 300 to a receiving and/or transmitting device. The conductive liquid in the cavity 315 of the antenna housing 310 acts as a first element and receives/transmits signals from/to the first feedline conductor, whilst the second feedline conductor is attached to electrical ground 320.

Abstract: The invention relates to a power system for a vehicle, the power system for a vehicle, the power system comprising a plurality of supercapacitors, a plurality of batteries, at least one electronic load and a master controller, arranged so that at least one battery is connected with at least one supercapacitor, such that power from the at least one battery may be supplied to the at least one supercapacitor, wherein the master controller ability to switch the at least one supercapacitor to a further at least one supercapacitor and wherein at least one battery and/or at least one supercapacitor of the plurality of supercapacitors supplies power to the electronic load.

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: 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: 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: 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: 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 payload mechanism for a vehicle is provided.

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.