Abstract: The present invention relates to the control of weapons, particularly weapons which are controlled via a communications link, possibly at some distance from the weapon's location. The invention is to an apparatus comprising safety-critical and non-safety-critical functional parts wherein at least one of a plurality of safety-critical functional parts is only connected to at least one other of the plurality of safety-critical functional parts.

Abstract: There is disclosed a line apparatus for inhibiting an airborne target. The line apparatus comprises at least one line comprising: a flexible tubular member, having a wall and defining a bore; and a fluid adhesive housed within the flexible tubular member, wherein the flexible tubular member is configured to express the fluid adhesive through the wall.

Abstract: There is provided a user-vehicle interface, comprising: a gesture control system, arranged to sense a gesture of a user of the vehicle; the gesture control system being arranged to process the sensed gesture to control interaction with content on a display, in accordance with that sensed gesture; and the user-vehicle interface further comprises a gesture control support, arranged to physically support a body part of the user associated with a provision of the gesture.

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: A vehicle comprising: a fuel store (104) configured to store a fuel, the fuel comprising a hydrocarbon; a fuel reformer (108) coupled to the fuel store (104) and configured to: receive an input comprising the hydrocarbon; and process the received input to produce an output comprising hydrogen; and a fuel cell (112) coupled to the fuel reformer (108) and configured to: receive the hydrogen from the fuel reformer (108); and produce, using the received hydrogen, electricity for use on the vehicle.

Abstract: There is provided a user-vehicle interface, comprising: a gesture control system, arranged to sense a gesture of a user of the vehicle; the gesture control system being arranged to process the sensed gesture to control interaction with content on a display, in accordance with that sensed gesture; the vehicle comprising a physical actuator for controlling the vehicle, and the gesture control system is arranged to facilitate interaction with content on the display, when a body part of the user associated with a provision of the gesture is engaged with the actuator.

Abstract: There is provided a user-vehicle interface, comprising a gesture control system that is arranged to: sense a direction of a gesture of a user of the vehicle; and process the sensed gesture to control a location of an indicator on a display in accordance with that sensed direction, such that a location of the indicator is arranged to move in accordance with changes in the sensed direction, the indicator being used to show a current position for user interaction with content on the display, and being in a plane in which that content resides.

Abstract: There is provided an arming apparatus for a store, the apparatus comprising: a first attachment system and a second attachment system; a linking connector coupled with the first attachment system and the second attachment system; and an arming connector coupled with the linking connector and a first fuze input of the store; wherein each of the first attachment system and the second attachment system comprises: an arming unit; a first frangible connector coupled with the arming unit and the linking connector; and a second frangible connector coupled with the linking connector and the store.

Abstract: There is disclosed an aircraft for intercepting an airborne target, the aircraft comprising: a frame; a plurality of lines of a first type, each attached to the frame at a first end, and free at the other end; and a plurality of lines of a second, different, type, each attached to the frame at a first end, and free at the other end.

Abstract: There is disclosed a line apparatus for inhibiting an airborne target. The line apparatus comprises at least one line comprising: a flexible tubular member, having a wall and defining a bore; and a fluid adhesive housed within the flexible tubular member, wherein the flexible tubular member is configured to express the fluid adhesive through the wall.

Abstract: An optical waveguide for a head up display is disclosed. The optical waveguide is configured to provide pupil expansion in two dimensions and having an input end and an output end and a first axis substantially parallel to the direction of propagation of light in the waveguide and substantially parallel with a direction from the input end to the output end. The optical waveguide comprising: an input region at the input end; a beam splitter configured to expand light received from the input region; a symmetrical diffraction grating comprising complementary first and second grating portions, wherein the second grating portion is substantially symmetrical to the first grating portion along a line of symmetry that is substantially parallel to the first axis. Light received at the symmetrical diffraction grating from the beam splitter is configured to be diffracted by the symmetrical diffraction grating towards the line of symmetry by the first grating portion or the second grating portion.

Abstract: This invention relates to a parachute sea anchor system deployable from a payload tube. There is provided a parachute sea anchor system suitable for launch from a vessel comprising at least one payload tube, said payload tube, comprising a payload canister, which comprises a parachute sea anchor, wherein said parachute sea anchor comprises a buoy tethered thereto, wherein said payload canister is attached to said vessel.

Abstract: Apparatus for configuring a mission automation and decision support system for an unmanned aerial vehicle comprising a user interface and a computer-implemented module configured to: receive data representative of at least one task to be performed by the UAV, the task being defined by one or more decision points that correspond to system actions or responses that could result from respective specified mission information; for each decision point(s), request user inputs in response to questions, the questions being designed to determine an extent to which each system action or response can be automated and a respective level of mandated operator approval therefor; and allocate to each decision point a set of one or more corresponding automation levels, each automation level comprising data representative of a measure of automation to be applied at a respective decision point.

Abstract: There is provided an integrity monitor configured to monitor the integrity of a component protection device. The component protection device comprises a protective medium to protect at least one electronic component, and having associated therewith a magnetic element and a Hall Effect sensor. The at least one of the magnetic element and the Hall Effect sensor is embedded within the protective medium and the Hall Effect sensor is located, when in use, to sense a magnetic field generated by the magnetic element. The integrity monitor has an input for receiving an output of the Hall Effect sensor indicative of the sensed magnetic field and the integrity monitor is configured to identify from the received output any change to the sensed magnetic field and determine, based on the change to the sensed magnetic field, an integrity of the component protection device.

Abstract: A control system (400) for an active inceptor (103) for a fly by wire aircraft permits a zero force null point to settle to a non-zero displacement trim position. An internal position state of a second order mass spring damper model is moved in conjunction with force-displacement characteristic coordinates. This results in no second order dynamics being superimposed on the feel of the inceptor (103) when dynamically adjusting the trim position, thereby eliminating the possibility of any unpleasant buzzing been felt by the operator of the inceptor during a trimming operation.

Abstract: The invention relates to the field of Free Space Optics (FSO), more specifically it is directed to: a method of obtaining a connection between at least two optical signal nodes, of a FSO, communication system each node comprising a transmitting device and receiving device; and transmitting via the transmitting device of a first node, a first diverged optical signal into an optical medium; receiving at the receiving device of the second node the first diverged optical signal and transmitting via the transmitting device of the second node a second diverged signal to the receiving device of the first node to establish a location of said first node establishing a connection, after which; the first node switches from the diverged optical signal to a narrower optical signal for the transmission of data via the connection.

Abstract: A radiation backscatter detector assembly comprising: a source array comprising source components for irradiating a shared sample location, at least two source components of the array generating radiation in different respective source energy bands; a detector array comprising detector elements for detecting backscattered radiation detection events from different respective spatial portions of the shared sample location, the detector elements each generating a pulse output in response to each radiation detection event it detects; and an energy meter for measuring the energies of the pulse outputs by different respective detector elements.

Abstract: The present invention relates to a method of classifying behaviour patterns. The method comprises configuring a simulation environment based on an operational arena, configuring an artificial agent to carry out a chosen activity within the simulation environment, generating training data from the agent's activity, and training a detection model using the training data.

Abstract: The present invention relates generally to a method and system (10) for classifying vehicle behaviour, particularly abnormal behaviour of civil aircraft (12). The method may comprise receiving aircraft data from an aircraft (12) which is to be classified; and determining whether the received aircraft data comprises identification information for the aircraft (12). In response to a determination that the received aircraft data comprises identification information, the method may comprise using said identification information to classify the behaviour of the aircraft (12). In response to a determination that the received aircraft data does not comprises identification information, the method may comprise obtaining the position of the aircraft and comparing the obtained position to an expected route for the aircraft to classify the behaviour of the aircraft (12).

Abstract: According to the present invention, there is provided a fabrication fixture for retaining a workpiece, comprising: a first housing; a second housing; said housing comprising; an independently adjustable support; wherein the first and second housing substantially envelop said workpiece to allow the workpiece to be moved.