BAE Systems

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.