BAE Systems Patente

There is described an acoustic black hole 'ABH' comprising a tapered body comprising an upstream end and a downstream end, the tapered body tapering from a first characteristic towards the upstream end to a second characteristic towards the downstream end, the tapered body comprising at least one fold in between the upstream end and the downstream end, such that the downstream end at least partly points towards the upstream end of the tapered body.

A method for verifying messages sent over a shared network, comprising generating at least one key pair comprising a private key and a public key and assigning the key pair to a first element connected to a shared media. The public key is distributed to at least a second element on the shared media. A message is transmitted from the first element to the second element. The message comprises an identifier, a data set, a message digest, and an encrypted message digest, generated by encrypting the message digest with the private key. The second element verifies the message received at the second element by decrypting the encrypted message digest using the public key corresponding to the identifier and comparing the decrypted message digest with a calculated message digest.

An optical strain sensor for use in a battery system comprising a planar optical waveguide having a planar geometry comprising a Bragg grating located in a core of the planar optical waveguide. The core extends longitudinally along a first direction of the planar optical waveguide and defines an optical propagation direction of the planar optical waveguide. A battery cell comprising the optical strain sensor. An inter-cell spacer comprising the optical strain sensor. A battery system comprising a plurality of the battery cells and/or a plurality of the inter-cell spacers.

A RADAR system (100) comprising a surface-based platform (102) and an airborne platform (112). The surface-based platform comprises a phased array (104) of antennas; a surface-based communications interface (106) configured to communicate with the airborne platform, and at least one processor (108) configured to generate, based on position information communicated via the surface-based communications interface, control signals for the phased array to transmit a beam of radio waves towards a reflectarray (114) of the airborne platform, and to process reflected radio waves received via the phased array. The airborne platform comprises the reflectarray for receiving and directing the beam transmitted by the phased array and/or reflected from an object; an airborne communications interface (116) configured to communicate with the surface-based platform, and at least one processor (118) configured to output, based on position information communicated via the airborne communications interface, control signals for directing the reflectarray.

The present invention relates to methods of producing energetic materials by flow synthesis. There is provided a method for the synthesis of 2,4,6-trinitrotoluene (TNT) using a flow reactor, the method comprising the steps of:a) providing an input flow of sulphuric acid comprising at least 50 wt% sulphuric acid;b) providing an input flow of nitric acid comprising at least 50 wt% nitric acid;c) providing an input flow of toluene;d) directing the input flow of sulphuric acid, the input flow of nitric acid and the input flow of toluene through a first flow path in a first zone of the flow reactor, the first zone having a temperature T¹, to provide a first output flow;e) directing the first output flow through a second flow path in a second zone of the flow reactor, the second zone having a temperature T², to provide a second output flow comprising TNT;wherein the temperature T² is greater than the temperature T¹.

A nuclear reactor system (100) comprising a nuclear reactor unit (200) having a reactor core (202) with a central axis (206) extending along the length of the reactor core (202). The reactor core (202) defines a radially outer perimeter (204) and extends radially outwards from the central axis (206) to the radially outer perimeter (204). There is also provided a reflector body (300) provided around the radially outer perimeter (204) of the reactor core (202), the reflector body (300) extending radially outwards from the reactor core (202) outer perimeter (204) to a reflector body wall (302). A fluid flow duct (304) is defined between by the reflector body (300) and the reflector body wall (302). A reactor pressure vessel wall (400) is provided radially outward of, and spaced apart from the reflector body wall (302), with a closed cavity (402) defined between the reactor pressure vessel wall (400) and reflector body wall (302). A shield wall (500) is provided radially outward of, and spaced apart from, the reactor pressure vessel wall (400), with a fluid reservoir (600) being defined by the reactor pressure vessel wall (400) and shield wall (500).

A propellant support unit (100) for a weapon system (200). The propellant support unit (100) extends along a propellant support unit axis (102). The propellant support unit (100) may comprise a side wall (104) extending between a first end (106) and a second end (108) along the length L of the propellant support unit (100). The side wall (104) may define a chamber (110). The chamber (110) may be closed at the first end (106) by a first end wall (112). The propellant support unit (100) may comprise an internal wall structure (114) which extends from the side wall (104) to define a plurality of sub-chambers (116). At least one of the sub-chambers (116) is configured for containing a propellant (300).

A material processing system (100) comprising a control system (200) and a material element identification marking system (300). The control system (200) is operable to receive a part request instruction (202). In dependence of the part request instruction (202), the control system (200) is operable to: determine a region (208) of a material element (206) which will form the part (204), and control the material element identification marking system (300) to perform a marking operation configured to apply an identifier (302) to the region which will form the part (204).

A safety element for an aircraft actuation system comprising an actuator, an inceptor, and a shear pin connecting the motor to the inceptor is described. The safety element comprises an absorber zone which is configured to deform in response to an excess force event in the aircraft actuation system, and is locatable between the shear pin and the actuator. The safety element reduces a force applied to an element such as the shear pin during the excess force event. Especially, where the excess force event is caused by the actuator, the shear pin is preventable from breaking.

A method 100 is provided for handling flowable materials 208, comprising the steps 102-112 of: aligning a first container 206 with a dispensing means 202; extending a nozzle 204 from the dispensing means 202 at least partially into the first container 206; depositing the flowable material 208 from the nozzle 204; retracting the nozzle 204 while the flowable material 208 is being deposited from the nozzle 204; stopping further deposition of the flowable material 208 and removing the nozzle 204 from the first container 206 when a measured amount of flowable material 208 has been deposited; and sealing the first container 206. Also described herein is a system 200 for handling flowable materials 208.

Method, apparatus and systems are described that are configured to obtain RF signals, wherein the RF signals are transmitted by each of a plurality of RF emitters, process the obtained RF signals using a trained RF emitter profiling model, and group the obtained RF signals into one or more groups, wherein the RF signals within each group are deemed to originate from the same RF emitter.

Methods, apparatus and systems are described configured to: obtain RF data at a remote node of a system, wherein the RF data is transmitted by a RF emitter; process the obtained RF data at the remote node using a trained RF emitter profiling model to perform feature extraction; determine whether the respective RF emitter is a known emitter; provide data relating to the RF emitter to a central node of the system in the event that the RF emitter is not a known emitter; and provide data relating to the RF emitter to a local database at the remote node in the event that the RF emitter is a known emitter.

A computer-implemented method is disclosed, in which a Large Language Model, LLM, is used to score or rank a plurality of test cases for use in fuzz testing an autonomous system. The method comprises: receiving a definition of interestingness and a plurality of test cases; providing the definition of interestingness and the plurality of test cases to the LLM in the form of first input text and second input text, respectively; and receiving an output from the LLM. The output is indicative of a respective score or ranking assigned to each one of the plurality of test cases by the LLM in accordance with the definition of interestingness. The autonomous system may then be fuzz tested by selecting one or more of the plurality of test cases in accordance with the assigned scores or rankings, and executing the selected test case(s) by the autonomous system.

There is provided a twin rudder arrangement (300) for a craft (250). The twin rudder arrangement (300) comprises a first rudder blade (310) and a second rudder blade (320), wherein the first rudder blade (310) and the second rudder blade (320) are configured to be provided at either side of a propeller (200) of the craft (250). At least part of the first rudder blade (310) or the second rudder blade (320) comprises a vortex generator arrangement (400), wherein the vortex generator arrangement (400) is arranged to induce vortices in fluid flow passing/interacting with the twin rudder arrangement (300). Also provided is an aircraft or watercraft comprising at least one twin rudder arrangement (300).

There is provided a twin rudder arrangement (100) for a craft (250). The twin rudder arrangement (100) comprises a first rudder blade (110) and a second rudder blade (120), wherein the first rudder blade (110) and second rudder blade (120) are configured to be provided at either side of a propeller (200) of the craft (250). The first rudder blade (110) and second rudder blade (120) are rotatable around the propeller (200) about a single common axis. Also provided is an aircraft or watercraft comprising at least one twin rudder arrangement (100).

A vehicle (100) comprising a chassis (200), a chassis suspension system (400) configured to support the chassis (200) relative to a substrate (500) and a control system (600). The control system (600) is operable to: receive a command to achieve a first objective and determine a first chassis suspension system configuration required to achieve the first objective. The first chassis suspension system configuration is defined by a relative orientation of each of the wheel arms (402) relative to the chassis (200) and a relative orientation of each drive wheel mounting member (416) relative to its respective wheel arm (402). The control system (600) is operable to operate one or more of the wheel arm actuators (430) and drive wheel mounting member actuators (440) to achieve the first chassis suspension system configuration.

A landing craft (10) comprising a hull (100). The hull (100) extends along an x-axis, a first end (102) of the hull (100) and a second end (104) of the hull (100) spaced apart from one another along the x-axis. The hull (100) extends along a y-axis, a first side (106) of the hull (100) and a second side (108) of the hull (100) spaced apart from one another along the y-axis. The hull extends along a z-axis, a base side (110) and a top side (112) of the hull (100) spaced apart from one another along the z-axis. The hull (100) further comprises a first hull wall assembly (140) spaced apart from a second hull wall assembly (150) in the direction of the y-axis by a deck assembly (142). The first hull wall assembly (140) comprises a first weapon unit (400) and/or the second hull wall assembly (150) comprises a second weapon unit (402). The or each weapon unit (400, 402) are operable to have, and to move between a hidden position in which the or each weapon unit (400, 402) is located within the respective hull wall assembly (140, 150); and a firing position in which the or each weapon unit (400, 402) is located outside of the respective hull wall assembly (140, 150).

A landing craft (10) comprising a hull (100). The hull (100) extends along an x-axis, a first end (102) of the hull (100) and a second end (104) of the hull (100) spaced apart from one another along the x-axis. The hull (100) extends along a y-axis, a first side (106) of the hull (100) and a second side (108) of the hull (100) spaced apart from one another along the y-axis. The hull extends along a z-axis, a base side (110) and a top side (112) of the hull (100) spaced apart from one another along the z-axis. The landing craft (10) further comprises a gyroscopic boat stabiliser (600) fixed to the hull (100) and configured to: sense a change in the landing craft orientation; and apply a force to the hull in response to the change in the landing craft orientation.

A landing craft (10) comprising a hull (100). The hull (100) extends along an x-axis, a first end (102) of the hull (100) and a second end (104) of the hull (100) spaced apart from one another along the x-axis. The hull (100) extends along a y-axis, a first side (106) of the hull (100) and a second side (108) of the hull (100) spaced apart from one another along the y-axis. The hull extends along a z-axis, a base side (110) and a top side (112) of the hull (100) spaced apart from one another along the z-axis. The landing craft (10) comprises a hydrofoil assembly (200) located on the base side (110) of the hull (100).

A computing device and a computer-implemented method of optimising a shape of an aquatic vessel part are provided. The method comprises obtaining (202) design data representing an initial 3D shape of an aquatic vessel part, and obtaining (204) a plurality of optimisation datasets, wherein the plurality of optimisation datasets relate to a respective plurality of performance areas of an aquatic vessel part. The method further comprises providing (206) the design data and the plurality of optimisation datasets to a shape optimisation application configured to generate output data representing an updated 3D shape of the aquatic vessel part optimised based on the plurality of optimisation datasets, and processing (208) the output data generated by the shape optimisation application.

A receiver is described having first and second phase modulators each generating a phase signal that is a phase modulated product of a carrier signal and an antenna-derived signal. The first phase modulator has a positive phase-voltage slope and the second phase modulator has a negative phase-voltage slope. ADCs convert the phase modulator outputs to first and second digital signals and a differential digital phase demodulator generates a digital output based on the first and second digital signals, wherein the digital output is a representation of the antenna-derived signal.

A fuel assembly (400) for a nuclear fission reactor system (100). The fuel assembly (400) may extend along a longitudinal axis (420). The fuel assembly (400) may comprise a pressure tube (402) and a single sleeve member (430) provided radially inward of a radially inner surface (432) of the pressure tube (402). The sleeve member (430) may define a chamber (434) which extends along a length of the sleeve member (430). The chamber (434) may comprise, in series, a first sub-chamber (436), a second sub-chamber (438) and a third sub-chamber (440). The first sub-chamber (436) may define a chamber flow inlet (442) and the third sub-chamber (440) defines chamber flow outlet (444). There may be provided a fuel compact unit (500) located in the second sub-chamber (438) within the sleeve member (430) such that a clearance gap (522) is maintained between a radially inner surface (450) of the sleeve member (430) and the fuel compact unit (500) to define a sleeve member flow passage (452).

A nuclear fission reactor system (100) provided with a nuclear reactor unit (200). The nuclear reactor unit (200) may comprise a moderator fluid tank (202) for containment of a moderator fluid (204). The moderator fluid tank (202) may comprise a moderator tank fluid flow inlet (210) and a moderator fluid tank fluid flow outlet (212). The nuclear fission reactor system (100) may comprise a moderator fluid temperature control system (220) operable to control the temperature of the moderator fluid (204) at the moderator tank fluid flow inlet (210).

There is described a computer implemented method of training a machine learning model. The method comprises obtaining source data and target data, selecting a subset of the source data based on minimising dissimilarity between the source data and the target data, and training the machine learning model using the selected subset of the source data.

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