Abstract: A laser diode array (102) comprising a plurality of laser diodes (201-210) and a channel (212) proximate to each of the laser diodes (201-210), the channel (212) configured to receive and provide a passage for a flow of a fluid coolant; wherein the laser diodes (201-210) are configured to emit electromagnetic radiation having the same centre wavelength at different respective junction temperatures. A coolant supply system (104) coupled to the laser diode array (102) may cause coolant to flow through the channel (212). A flow rate of the coolant through the channel (212) may be controlled based on temperature measurements of the coolant prior to entering, within, and/or after exiting the laser diode array (102).

Abstract: The present invention provides an emissions control apparatus for an entity. The emissions control apparatus comprises: storage means for storing transmission data relating to an entity; a controller configured to calculate a propagation profile for the entity based on at least the transmission data; and a display for displaying the propagation profile. The present invention also provides a method of controlling emissions.

Abstract: A method of manufacturing a part, the method involving providing an apparatus, the apparatus having a metal skin component; a metal HIP can and a hollow space between a portion of the HIP can and a portion of the skin component, the method further involving filling the HIP can with a metal powder; evacuating the HIP can; sealing the evacuated HIP can; and applying a HIP process to the apparatus in a HIP chamber so as to form the part.

Abstract: A structural damper (2) having an acoustic black hole (5), at least one sensor (7), a damper structure (4), an actuator (8) configured to apply an actuating force to the damper structure (4) and a controller (H) configured to control the actuator in dependence on a signal from the at least one sensor so as to provide structural damping of a primary structure (3).

Abstract: A system to determine a temperature corrected pressure of a medium in a pressure transducer is disclosed. The system comprises a first circuitry to obtain a first value related to a vibration frequency of the vibration of a pressure sensitive vibration member; a second circuity to obtain a second value related to a vibration amplitude of the vibration of the vibration member; and a third circuity to use the first value and the second value to determine the temperature corrected pressure of the medium based on a predetermined relationship between the vibration frequency and the vibration amplitude.

Abstract: A temperature sensor for a cold reference junction of a thermocouple is provided that may be incorporated permanently or removeably in a releasable connector having a first connector part arranged to engage releasably with a second connector part in which the thermocouple conductors terminate, so forming a cold reference junction for the thermocouple. When the two parts of the connector are engaged, the temperature sensor of the present invention is able to sense the temperature in the vicinity of a cold reference junction in the connector. The temperature sensor may be provided by embedding one or more thermistors into a flexible disk or plate-like seal able to fit around the conductors of the first connector part such that the thermistors make electrical contact with selected conductors of the first connector part and thermal contact with the cold reference junction.

Abstract: A method of producing a shim for use in an aircraft airframe (200) comprising: providing a plurality of component parts (202, 204) of the aircraft airframe (200); measuring a surface of each of the component parts (202, 204) and creating a digital models of the component part (202, 204) therefrom; digitally assembling together the digital models of the component parts (202, 204) thereby to produce a digital model (600) of at least part of the aircraft airframe (200); using that digital model (600), creating a digital model of a shim (604), the digital model of the shim (604) filling a gap between at least two digital models of component parts (202, 204) in the digital model (600) of at least part of the aircraft airframe (200); and producing a physical shim using the digital model of the shim (604).

Abstract: A mount for adjusting a mounting plane is disclosed. The mount comprises a first adjustable device, a second adjustable device and a third adjustable device. A first intersection between the first adjustable device and the second adjustable device forming a first principal axis and a second intersection between the second adjustable device and the third adjustable device forming a second principal axis substantially perpendicular to the first principal axis. The first adjustable device, second adjustable device and third adjustable device rigidly coupled together. The first adjustable device is configurable to be adjusted in a first translational degree of freedom, and substantially constrain the first adjustable device in remaining translational degrees of freedom, wherein adjustment of the first adjustable device in the first translational degree of freedom causes a rotation of the mounting plane about the second principal axis.

Abstract: There is disclosed a heat exchanger comprising at least one set of channels having a proximal end and a distal end, the set of channels comprising: a first channel defined by a first skin and a wall; and a second channel defined by a second skin and the wall, wherein the wall located between the first channel and the second channel comprises a first at least one aperture to allow fluid to pass through the wall from the first channel to the second channel.

Abstract: The present invention provides an emissions control apparatus for an entity. The emissions control apparatus comprises: storage means for storing transmission data relating to an entity; a controller configured to calculate a propagation profile for the entity based on at least the transmission data; and a display for displaying the propagation profile. The present invention also provides a method of controlling emissions.

Abstract: According to an aspect of the present invention, there is provided a watercraft comprising: a management system for use in managing functionality associated with the watercraft; an augmented reality system arranged to interact with the management system, at least a part of the augmented reality system being arranged to be wearable by a user of the watercraft to provide augmented reality image data to the user based on the interaction between the augmented reality system and the management system.

Abstract: Disclosed is an apparatus for testing a device, comprising: a switch (100) arranged to replace a circuit breaker (30) associated with an individual system in the device under test, wherein the switch (100) is operable to be controlled remotely from the device under test such that the switch (100) either activates or deactivates the individual system.

Abstract: According to a first aspect of the invention, there is provided an object for moving through a fluid, the object comprising: an outer housing, arranged to be exposed to a hydrostatic pressure exerted by the fluid; a strain gauge, arranged to obtain an indication of the hydrostatic pressure, wherein a first part of the strain gauge is arranged to be in contact with the outer housing, such that the strain gauge is arranged to obtain an indication of the hydrostatic pressure by obtaining an indication of the strain on the housing.

Abstract: There is disclosed a heat exchanger comprising at least one set of channels having a proximal end and a distal end, the set of channels comprising: a first channel defined by a first skin and a wall; and a second channel defined by a second skin and the wall, wherein the wall located between the first channel and the second channel comprises a first at least one aperture to allow fluid to pass through the wall from the first channel to the second channel.

Abstract: A device for monitoring the status of a munition fuze is disclosed. The device includes a visible marker; an indicator strip, capable of actuation, from a first state to a second state; and a power source providing power to the munition initiation system, the visible marker and/or the indicator strip. The visible marker and indicator strip are positioned to be visible to an observer when the fuze has been fitted for use on said munition and activation of the power source causes switching of the visible marker from an off state to an on state and actuation of the indicator strip from a first state to a second state, such that the power source's activation is indicated by the actuation of the indicator strip to its second state. The visible marker remains in an on state only if there is sufficient power to operate the initiation system.

Abstract: The present invention provides a vehicle (100) comprising: a body (4) having a skin; a heat source (12); and a thermal management system. The thermal management system comprises: a heat pipe (14) comprising: an evaporator end (close to 12) and a condenser end (close to heat exchanger 22a, 22b); a vapour arranged to flow from the evaporator end to the condenser end; and a working fluid arranged to flow from the condenser end to the evaporator end, wherein the heat pipe (14) is arranged such that the evaporator end is arranged in proximity to the heat source to absorb heat from the heat source; and one or more heat exchangers arranged in proximity to the condenser end and integrated with the skin. The present invention also provides a method of managing temperature in a vehicle.

Abstract: A plug assembly in which the insulator part can be moved from an unfolded state to a folded state. The insulator may be utilised in the unfolded state for assembly of a wiring loom and then folded into the folded state for insertion into a connector body.

Abstract: There is provided a method and apparatus for simulating a flight scenario during a live flight of an aircraft. The method comprises: (i) generating (60) images comprising scenes relevant to the simulated flight scenario at a simulated altitude; (ii) calculating, using live flight data received for the aircraft and with reference to a predetermined flight model (65), simulated flight data for the simulated flight scenario at the simulated altitude; and (iii) displaying, on a display system (35) of the aircraft, the calculated simulated flight data while controlling the display of said generated scene images to simulate movement of the aircraft through the displayed scene at a rate and in a direction corresponding to the displayed simulated flight data. The method and apparatus may optionally alter the response of the aircraft to control actions (70) by a pilot to simulate the response expected of the aircraft having the simulated flight characteristics.

Abstract: A method and system for positioning a vehicle in relation to each moving target of an ordered set of moving targets. Each of the moving targets moves from an initial position at a constant velocity. Embodiments can compute an estimated time for the vehicle to be positioned within a predetermined proximity of one of the moving targets; compute an estimated location of the moving target at the estimated time, based on a current position of the moving target and the constant velocity of the moving target, and compute a required velocity for the vehicle to move from its current position to reach the estimated location by the estimated time. If the required velocity is less than or equal to a maximum velocity of the vehicle, outputting the estimated time and the estimated location for use in positioning the vehicle.

Abstract: According to a first aspect of the present invention, there is provided a munition assembly, arranged to be launched from a gun, the assembly comprising: a carrier for a submunition, the carrier comprising a cavity in which the submunition is located; and a submunition, carried by the carrier in the cavity, the submunition arranged to be controllably expelled from the carrier; the submunition comprising: a submunition explosive charge; and a submunition fuze, wherein: the munition assembly is adapted to be launched, into the air, from a gun barrel, where the submunition is then arranged to be controllably expelled from the carrier and enter a body of water; and the submunition fuze is adapted to trigger the submunition explosive charge under water.