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: A vehicle comprising: a shift reactor (110) configured to: receive carbon monoxide produced by the vehicle; and process the received carbon monoxide to produce an output comprising hydrogen; and a fuel cell (112) coupled to the shift reactor (110) and configured to: receive the hydrogen from the shift reactor (110); and produce, using the received hydrogen, electricity for use on the vehicle.

Abstract: An aircraft wing system and method comprising: an aircraft wing including upper and lower surfaces, and a leading edge between the upper and lower surfaces; a fairing coupled to the leading edge; and actuation means configured to move the fairing relative to the aircraft wing between a stowed position, a first deployed position, and a second deployed position. The stowed position is when the fairing is in contact with the aircraft wing and serves as a continuation of the aircraft wing. The first deployed position is when the fairing is in contact with the aircraft wing and located below the stowed position. The second deployed position is when the fairing is spaced apart from the leading edge to create a gap between the fairing and the leading edge.

Abstract: Disclosed is an aircraft (102) comprising an aircraft avionics system (108) configured to perform one or more functions, and an interface module (110). The interface module (110) is configured to: store, for each function, respective one or more test criteria; receive, from an entity (104) remote from the aircraft avionics system (108), a function request for the aircraft avionics system (108) to perform a certain function; test the certain function against one or more of the stored test criteria corresponding to the certain function; and, responsive to determining that the certain function satisfies all of the test criteria that correspond to the certain function, outputting the function request for use by the aircraft avionics system (108).

Abstract: Disclosed is a method and apparatus for machining a workpiece (2). The method comprises specifying a path along which a cutting tool (6) is moved during machining the workpiece (2), the path comprising segments (26); defining, for each segment (26), an exit point on that segment (26); defining, for each segment (26), an exit path (38) from the exit point of that segment (26) to a point remote from the workpiece (2); performing a machining process including moving the cutting tool (6) along the tool path and machining the workpiece (2); and, during the machining process, when one or more criteria are satisfied: interrupting the machining process and, without machining the workpiece (2), moving the cutting tool (6) to the exit point of the current segment (26) and then along the exit path (38) of the current segment (26).

Abstract: An aircraft wing system and method comprising: an aircraft wing; an edge device coupled to a leading edge or trailing edge of the aircraft wing; a drive shaft rotatable about its axis; a crank arm, a first end of the crank arm being coupled to the drive shaft, and a second end of the crank arm opposite to the first end being coupled to the edge device; and a gear system (e.g. a strain wave gear system) coupled between the drive shaft and the first end of the crank arm.

Abstract: The invention relates to methods of bonding and a conductively bonded joint, provided by high loadings of conductively coated nano scale particulate fillers in a conductive adhesive in combination with a conductive intermediary structure, more particularly to a lightning strike resilient bonded joint between fibre reinforced polymer composites. A method of joining a first fibre reinforced polymer composite surface and a second fibre reinforced polymer composite surface, comprising the steps of providing a conductive intermediary structure between said first and second surfaces, filling the void between said surfaces and enveloping said intermediary structure with a conductive adhesive, curing the conductive adhesive to form a bonded first and second surface. A conductive adhesive comprising a curable binder and a high aspect ratio nanoscale carbon particulate filler present in the range of from 0.1 to 40% wt, wherein said particulate filler comprises a metal coating.

Abstract: Disclosed is a method of producing an assembly tool for assembling a first system comprising one or more components. The method comprises: for each component, determining, when the first system is attached to a second system, a position and orientation of that component relative to the second system and positions and orientations relative to the second system at which that component is to be supported; providing a frame; attaching, to the frame, a reference structure; providing a plurality of pickup devices each having a receiving element for receiving a component; and securing each pickup device to the frame such that a position and orientation relative to the reference structure of each receiving element is the same as a position and orientation at which a component is to be supported.

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 routing the electromagnetic radiation to laser apertures in the platform which direct the generated electromagnetic radiation at a target, the laser apertures having an associated field of regard; and a control system, the control system being arranged to control which combination of laser, laser optics and laser aperture is used to engage the target, based on a probability of successfully engaging that target in relation to the field of regard of the laser aperture of the combination.

Abstract: A method and apparatus are provided for detecting a fault condition in a network, making use of standard parameter data generated by a network termination device of a user of the network, the method comprising, in a training phase, the remote retrieval of selected parameters from a predetermined set of users' network termination devices in order to generate one or more representative models of expected operational status using the retrieved parameters and, in a monitoring phase, determining a measure of operational status for the set of users at some future time and comparing that with a corresponding expected model measure. Parameter retrieval takes place over substantially the same path through the network as used to supply services to a respective network termination device so that the models are generated in respect of communications over those elements of network infrastructure likely to affect operational status of the respective set of users in the event of a fault condition.

Abstract: A directed-energy weapon counter measure apparatus and method for modifying a path of a focused electromagnetic energy beam (204) emitted by a directed energy weapon system so as to deflect it from a platform (200), the apparatus comprising an electromagnetic radiation source, communicably coupled to a control system. The control system is configured to create an atmospheric element (202) operative to simulate a physical electromagnetic radiation path modifying device within an atmospheric volume located in the path of the focused electromagnetic radiation beam (204) by causing electromagnetic radiation from the source to be applied to a selected plurality of three-dimensional portions of said atmospheric volume so as to heat and/or ionise the air with in said portions, wherein said selected portions are spatially located together in a substantially unbroken, three-dimensional configuration.

Abstract: A method for coordinating a plurality of vehicles (102, 104) comprising: defining, as a command vehicle (C), a vehicle in the plurality; storing, by one or more storage devices (204) located on one or more of the vehicles (102, 104), a list of capabilities of each vehicle (102, 104); receiving, by one or more processors (202) on the command vehicle (C), a specification of a goal; based on the stored vehicle capabilities, allocating, by the one or more processors (202), to one or more of the vehicles (102, 104), one or more tasks, the one or more tasks being such that, if each of those tasks was to be performed, the goal would be accomplished; and sending, from the command vehicle (C), to each vehicle (102, 104) to which a task has been allocated, a specification of the one or more tasks allocated to that vehicle (102, 104).

Abstract: A method and apparatus for centrally managing the performance of maintenance on a fleet of vehicles, the method comprising: acquiring criteria specifying vehicle availability for a predetermined time period; acquiring vehicle data specifying multiple maintenance operations to be performed on one or more of the vehicles; determining, based on the criteria, a fleet plan including, for each vehicle, a schedule of the maintenance operations for that vehicle; determining, using the fleet plan, a maintenance plan comprising, for one or more maintenance service providers, a schedule of maintenance operations to be performed on a vehicle by the maintenance service providers; and managing the maintenance service providers to perform the maintenance operations on the vehicles in accordance with the maintenance plan.

Abstract: A cavity system, comprising: a cavity (2) comprising a cavity opening; and an acoustically reflective structure (18, 20) located at least partially within the cavity (2), the acoustically reflective structure (18, 20) comprising one or more acoustically reflective surfaces (24, 26, 30, 32), each acoustically reflective surface (24, 26, 30, 32) being oblique to a plane of the cavity opening (27). The one or more acoustically reflective surfaces (24, 26, 30, 32) may be arranged to reflect incident acoustic waves out of the cavity opening while avoiding reflection into a region (48) at or proximate to a leading edge (14) of the cavity (2).

Abstract: A method of producing an aircraft battery system, the method comprising: identifying a volume of free space on an aircraft (100); arranging a plurality of electrical power cells (112, 114) such that the plurality of cells (112, 114) are capable of fitting into the identified volume, wherein the arrangement of cells (112, 114) has a non-cuboid shape; fixing the plurality of cells (112, 114) together such that the relative positions of the electrical power cells (112, 114) are maintained; electrically connecting the plurality of cells (112, 114) together, thereby to provide a battery (102, 104); and electrically connecting a DC-to-DC converter (106, 108) to the battery (102, 104), the DC-to-DC converter (106, 108) being configured to control a voltage of the battery (102, 104) to be equal to a specified voltage or within a specified voltage range.

Abstract: An electro-optic window is provided, together with a method of manufacturing the window. The window (3) is made of a material substantially transparent to at least one of infra-red, visible and UV radiation and treated to have reduced RF/MICROWAVE transmission characteristics by the provision of a grid (1) set into at least one surface (2) thereof. The grid (1) is formed of a material selected to be either reflective or absorptive to RF/MICROWAVE radiation.

Abstract: A method and apparatus for generating, in an aircraft in flight, a feasibility display indicative of the feasibility of a weapon, the method comprising: providing a performance envelope for the weapon; determining, using the performance envelope, configuration data for configuring a generic algorithm; uploading the configuration data to the aircraft; generating feasibility data indicative of the feasibility of a weapon carried on the aircraft successfully engaging a target and/or the feasibility of a weapon carried on the target successfully engaging the aircraft; determining, on board the aircraft, using the same generic algorithm and the uploaded configuration data, one or more test criteria; performing, on board the aircraft, an assessment process including determining whether or not the feasibility data satisfies the one or more test criteria; and, based the assessment, using the feasibility data, generating the feasibility display.

Abstract: A tile assembly (22) which, in use, is fitted to a base structure to form at least part of a fluid washed surface. The tile assembly comprises a housing (42) with at least one plenum (45) being provided within the housing (42). A wall (44) of the housing (42) is provided with a plurality of flow passages (46) which extend from the plenum side of the wall (44) to an outer surface (48) of the wall. Flow passage closures (50) are provided which are operable to open and close at least some of the flow passages (46).

Abstract: A tamper-resistant lock assembly comprising a plate having a slot for receiving a key, the slot extending through the plate from an opening in a front face thereof to an exit in an opposing rear face thereof, the opening having a first profile and the exit having a second, different profile, the key comprising a shaft having a bit extending therefrom, the bit being formed of a shape memory material and being pre-configured such that its cross-sectional shape in its temporary form matches the first profile and the bit can be inserted through the slot via the opening and, upon application of a predetermined external stimulus, returns to a permanent form in which its cross-sectional shape matches the second profile and the bit can be retracted from the slot via the exit.

Abstract: A long range electromagnetic radiation sensor apparatus comprising a sensing system for receiving electromagnetic radiation signals from an object or area of interest and at least one electromagnetic radiation sensor, the apparatus further comprising an electromagnetic radiation source and a control system configured to cause electromagnetic radiation from said source to be applied to a selected plurality of three-dimensional portions of an atmospheric volume between said optical system and said object or area of interest (204) so as to heat and/or ionise the air within said portions, wherein said selected portions are spatially located together in a three-dimensional configuration so as to simulate an electromagnetic radiation path modifying device (202) for capturing said electromagnetic signals from said object or area of interest and directing and/or converging said captured signals toward said electromagnetic radiation sensor of said sensing system.