Abstract: There is disclosed an aircraft for intercepting an airborne target, the aircraft comprising: a frame; a plurality of lines of a first type, each attached to the frame at a first end, and free at the other end; and a plurality of lines of a second, different, type, each attached to the frame at a first end, and free at the other end.

Abstract: Apparatus for a Directed-Energy Weapon An apparatus for a directed-energy weapon comprises: an assessment system arranged to, during an assessment phase, perform an assessment of a target environment, wherein the target environment comprises a target, and the assessment comprises determining a possible engagement efficiency of the target by the directed-energy weapon; and a controller arranged to, during an engaging phase, control the directed-energy weapon to direct energy towards the target environment conditionally upon the possible engagement efficiency.

Abstract: An airborne redirection unit (ARU), for deflecting an RF energy beam, the ARU comprising: A canopy comprising a surface for slowing the rate of descent, A beam director supported at the canopy, the ARU being configured to focus the RF energy beam.

Abstract: There is disclosed a line apparatus for inhibiting an airborne target. The line apparatus comprises at least one line comprising: a flexible tubular member, having a wall and defining a bore; and a fluid adhesive housed within the flexible tubular member, wherein the flexible tubular member is configured to express the fluid adhesive through the wall.

Abstract: There is disclosed a line apparatus for inhibiting an airborne target. The line apparatus comprises at least one line comprising: a flexible tubular member, having a wall and defining a bore; and a fluid adhesive housed within the flexible tubular member, wherein the flexible tubular member is configured to express the fluid adhesive through the wall.

Abstract: There is disclosed an aircraft for intercepting an airborne target, the aircraft comprising: a frame; a plurality of lines of a first type, each attached to the frame at a first end, and free at the other end; and a plurality of lines of a second, different, type, each attached to the frame at a first end, and free at the other end.

Abstract: An apparatus for a directed-energy weapon comprises an assessment system arranged to, during an assessment phase, perform an assessment of a target environment, wherein the target environment comprises a target; and a controller arranged to, during the assessment phase, control the directed energy weapon to direct energy towards the target environment so that the assessment system can perform the assessment using the directed energy.

Abstract: Apparatus (100) for use in space, the apparatus (100) comprising: a feedstock storage module (108) for storing a feedstock; a heating module (110) coupled to the feedstock storage module (108) and configured to heat the feedstock; an extrusion nozzle (112) coupled to the heating module (110) and configured to extrude heated feedstock from the apparatus (110); and one or more thrusters (118) configured to provide a propulsive force to the apparatus (100).

Abstract: An apparatus for a directed-energy weapon comprises an assessment system arranged to, during an assessment phase, perform an assessment of a target environment, wherein the target environment comprises a target, and the assessment comprises receiving data relating to a map of at least a portion of a target environment; and a controller arranged to, during an engaging phase, control the directed-energy weapon to direct energy towards the target environment conditionally upon the data.

Abstract: An apparatus for a directed-energy weapon comprises an assessment system arranged to, during an assessment phase, perform an assessment of a target environment, wherein the target environment comprises a target, and the assessment comprises receiving data relating to a map of at least a portion of a target environment; and a controller arranged to, during an engaging phase, control the directed-energy weapon to direct energy towards the target environment conditionally upon the data.

Abstract: An apparatus for a directed-energy weapon comprises an assessment system arranged to, during an assessment phase, perform an assessment of a target environment, wherein the target environment comprises a target; and a controller arranged to, during the assessment phase, control the directed energy weapon to direct energy towards the target environment so that the assessment system can perform the assessment using the directed energy.

Abstract: A rotary-wing air vehicle comprising a main body (12) and at least two rotor devices (16a, 16b) arranged and configured to generate propulsion and thrust, in use, to lift and propel said air vehicle, said rotor devices (16a, 16b) being arranged and configured relative to said main body (12) such that the blades thereof do not cross through a central vertical axis of said main body (12) defining the centre of mass thereof, wherein said main body (12) is provided with an aperture (100) that extends therethrough to define a channel about said central vertical axis.

Abstract: Apparatus for a Directed-Energy Weapon An apparatus for a directed-energy weapon comprises: an assessment system arranged to, during an assessment phase, perform an assessment of a target environment, wherein the target environment comprises a target, and the assessment comprises determining a possible engagement efficiency of the target by the directed-energy weapon; and a controller arranged to, during an engaging phase, control the directed-energy weapon to direct energy towards the target environment conditionally upon the possible engagement efficiency.

Abstract: A wing member (14b) for an air vehicle (10), said wing member comprising a core section (20) defining its longitudinal axis and having upper and lower surfaces, at least one of said surfaces comprising apparatus (22) selectively configurable between at least two positions, wherein in a fully extended position, at least portions of said apparatus extend outwardly from said respective surface so as to increase the effective cross-sectional area of said wing member and define an effective aerofoil in respect thereof.

Abstract: A computational ghost imaging apparatus comprising a first electromagnetic radiation source (100) and a control system configured to cause electromagnetic radiation from said first source to be applied to a selected plurality of three-dimensional portions of an atmospheric volume between a second electromagnetic radiation source (110) and object or region of interest (106) so as to heat or ionise the air within said selected portions and create an atmospheric spatial radiation modulator (108) of a specified pattern for causing said object or region of interest to be irradiated with spatially modulated electromagnetic radiation in said specified pattern, the apparatus further comprising a detector for receiving electromagnetic radiation reflected from said object or region of interest (106), and a processing module for reconstructing an image of said object or region of interest using data output by said detector.

Abstract: A method of manufacturing a graphene sheet comprising the steps of: providing a container containing liquid and a volume above the liquid; supplying carbon atoms to the volume; and allowing carbon atoms to settle on the surface of the liquid and to coalesce to form the graphene sheet.

Abstract: A counter measure apparatus and method for modifying a path of an electromagnetic detector signal (204) so as to prevent incidence thereof on 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 said electromagnetic detector signal path (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 within said portions, wherein said selected portions are spatially located together in a substantially unbroken, three-dimensional configuration.

Abstract: Disclosed is a lighter than air vehicle comprising a first envelope, a second envelope located inside the first envelope, and a tube connecting the first envelope to the second envelope. The first envelope and the second envelope are spaced apart so as to define a chamber between the first envelope and the second envelope. The chamber is filled with a lighter than air gas. A first opening of the tube is located at an external surface of the first envelope. A second opening of the tube is located at an internal surface of the second envelope, the second opening of the tube being at an opposite end of the tube to the first opening of the tube.

Abstract: The present invention provides a method suitable for use in a sense and avoid system of a vehicle having a hyperspectral imaging system, the method comprising: estimating the range to an object from the vehicle, wherein estimating the range comprises: measuring the emission spectrum of the object using the hyperspectral imaging system; identifying at least one trough and/or discontinuity in the emission spectrum by subtracting the measured emission spectrum from a perfect blackbody emission spectrum; and searching a storage means storing spectral radiances and/or wavelengths of troughs and/or discontinuities, each with an associated known atmospheric path length, for the corresponding spectral radiance and/or wavelength of the identified at least one trough and/or discontinuity in order to estimate the atmospheric path length, and consequently the range, between the object and the vehicle. The present invention also provides a sense and avoid system for performing the same method.

Abstract: Apparatus for releasing a payload from an air vehicle (14), the apparatus comprising a generally tubular holding device (10) mounted on, or formed integrally with, said air vehicle, said holding device (10) having an open end facing in a direction substantially opposite to the direction of travel (16) of said air vehicle (14), in use, the apparatus further comprising a container (18) for housing said payload and configured to be at least partially received within said holding device (10), at least one releasable retaining device (20) for releasably retaining said container (18) within said holding device (10), and an actuation device for selectively actuating said at least one releasable retaining device to release said container from said holding device, said container (18) having thereon at least one drag inducing device (22) configured to induce drag in a direction substantially opposite to that of said direction of travel (16) of said air vehicle, in use, so as to act to drag said container (18) from said