Abstract: There is provided a vehicle for protecting an entity against directed-energy weapons, comprising: a housing; and a shield for absorbing or reflecting a laser beam, the shield, in use, extending in a plane from the housing. There is also provided a system of vehicles and a method of coordinating a plurality of vehicles to protect an entity against directed-energy weapons.

Abstract: A method of creating one or more secure tunnels within a network, a router node implementing the method and a network comprising a plurality of router nodes. The method comprises: connecting a first router node to the network, wherein the first router node comprises a plurality of bearer interfaces, each having a virtual routing and forwarding VRF module; receiving, from neighbouring nodes in the network, at least one loopback address for at least one bearer interface in the neighbouring nodes; and detecting, using the first router node, one or more routing prefixes associated with a traffic or management tunnel within the at least one received loopback address.

Abstract: The present invention relates to an improved thermal management system for a heat source, such as a high-powered electronic device. Thermal management systems work to maintain the optimal operational temperature of a device to maximise reliability, operational lifespan and/or efficiency, for example by using a fluid coolant to transfer thermal energy from the device to a heat exchanger. The present invention seeks to provide an improved thermal management system by incorporating a phase change material into a heat exchanger.

Abstract: A thermodynamic apparatus (10) comprising a compressor module (100), a turbine module (200), and a regenerative heat exchanger (300) centred on a central axis (12). The compressor module (100), turbine module (200) and regenerative heat exchanger (300) are arranged in series along the central axis (12) such that the regenerative heat exchanger (300) is provided between the compressor module (100) and the turbine module (200).

Abstract: A method to detect a hands off status of a user input device is disclosed. The method comprising filtering a sensed force, acting on the user input device, using a first lag filter to provide a first output, the lag filter comprising a first lag time constant. Filtering the sensed force using a second lag filter, substantially in parallel with the first filter, to provide a second output, the second lag filter comprising a second lag time constant greater than the first lag time constant. Comparing with a first threshold value, in a first comparison, a magnitude of a difference between the first output and the second output. Comparing with a second threshold value, in a second comparison, a magnitude of the second output. Designating the user device to have a hands off status based on the first comparison and the second comparison.

Abstract: An arrangement for influencing a liquid flow includes a first section selectively configurable to provide a vortex generator surface, the vortex generator surface comprising a series of laterally aligned projections, to induce vortices in the liquid flow.

Abstract: A cavity system is provided. The cavity system (100-600) comprises: a cavity (2) and a spoiler (104-604); and the spoiler (104-604) having a front surface and a rear surface. The spoiler (104-604) is positioned in proximity to a leading edge (14) of the cavity (2), the leading edge (14) being relative to an actual or intended flow direction (3) of a fluid over the cavity (2). The spoiler (104-604) is arranged with its longitudinal axis perpendicular or at an oblique angle to the actual or intended flow direction (3) such that the front surface faces towards the flow direction (3). A first region of the spoiler (104-604) extends further toward the leading edge than a second region of the spoiler (104-604).

Abstract: A support structure for manufacturing a pressure vessel, the support structure configured to be carried on a supporting substrate, the support structure comprising a first segment support structure nestable within, and moveable relative to, a second segment support structure, wherein the first segment support structure is configured to be raised and lowered relative to the second segment support structure to thereby raise and lower the first segment relative to the substrate, and the first segment support structure is configured to move between a nested position within the second segment support structure to a position spaced apart from the second segment support structure across a surface of the substrate.

Abstract: A mounting structure (200) comprises a first component (201) to couple the mounting structure to an aerial vehicle (203), and a second component to couple a pay load to the first component, the first component defining a body comprising a connection structure (205) configured to secure the first component to the aerial vehicle, and an interface structure (207) configured to couple with the second component.

Abstract: The present invention relates to a method of marking and identifying a target, and in particular, a method of using a Directed Energy Weapon (DEW) to heat a target without damaging it so that the target may be clearly identified by detectors and systems using thermally sensitive imaging.

Abstract: The present invention relates to an apparatus, detachably mountable to the external surface of an aircraft. More specifically, the present invention relates to a fully self-contained apparatus comprising an electrical device, such as a Directed Energy Weapon (DEW), and a corresponding thermal management system and power supply.

Abstract: According to the present disclosure there is provided a duct arrangement for influencing fluid flow, the duct arrangement comprising: a duct section arranged to receive a fluid flow therethrough, the duct section defining a first direction through the duct section from a fluid inlet end to a fluid outlet end; a rotor housed in the duct section, the rotor comprising one or more rotor blades; and a vortex generator surface housed in the duct section, the vortex generator surface arranged to induce vortices in the fluid flow through the duct section.

Abstract: An oscillation system includes 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: 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: According to the present disclosure there is provided a liquid flow influencing duct arrangement comprising: a first duct section arranged to receive a liquid flow therethrough, the first duct section defining a first direction through the first duct section from a liquid inlet end to a liquid outlet end; a second duct section defining a second direction through the second duct section from a liquid inlet end to a liquid outlet end, the second duct section comprising a vortex generator surface, wherein the vortex generator surface is arranged to induce vortices in the liquid flow through the first duct section, wherein the duct arrangement further comprises a rotor housed in one of the duct sections.

Abstract: According to the present invention there is provided a polarisation converter comprising: a first element array layer extending in a plane comprising a first array of spaced apart electrically conductive dipole elements: a second element array layer extending in a plane comprising a second array of spaced apart electrically conductive dipole elements: a dielectric layer extending in a plane separating the first element array layer and the second element array layer, each element array layer having a first and second axis parallel to the plane of the respective element array layer, the first axis and second axis being perpendicular axes, wherein: one or both of the element array layers exhibits an anisotropic spatial property. An antenna system, vehicle and method of manufacturing a polarisation converter are also provided.

Abstract: A method of training a machine learning, ML, algorithm, is described. The method is implemented, at least in part, by a computer comprising a processor and a memory. The method comprises: providing training data comprising a set of audio signals, including a first audio signal, as respective bitstreams, corresponding with respective sets of watercraft (S501); training the ML algorithm using the provided training data comprising detecting the respective sets of watercraft and classifying the detected respective sets of watercraft according to a set of classes, including a first class, based, at least in part, on a set of labels, including a first label, wherein the set of labels relates to propeller, propulsor, prime mover and/or submerged equipment associated with watercraft (S502).

Abstract: A computer-implemented method of training a machine learning, ML algorithm to control spin-stabilized steerable projectiles is described. The method comprises: obtaining training data including respective policies and corresponding trajectories of a set of spin-stabilized steerable projectiles including a first projectile, wherein each policy relates to steering a projectile of the set thereof towards a target and wherein each corresponding trajectory comprises a series of states in a state space of the projectile (S2001); and training the ML algorithm comprising determining relationships between the respective policies and corresponding trajectories of the projectiles of the set thereof based on respective results of comparing the trajectories and the targets (S2002).

Abstract: A method of manufacturing, at least in part, a composite mould tool is described. At S101, the method comprises obtaining a mould tool precursor having a first face and a reverse second face, wherein the precursor comprises a first metal. At S102, the method comprises hermetically scaling the precursor by cold spraying a layer on the second face using particles comprising a second metal, wherein the respective coefficients of thermal expansion of the first metal and the second metal are within a factor of 5. At S103, the method comprises providing a faceplate of the composite mould tool by subtractive manufacturing of the first face.