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 optical waveguide for a head up display is disclosed. The optical waveguide is configured to provide pupil expansion in two dimensions and having an input end and an output end and a first axis substantially parallel to the direction of propagation of light in the waveguide and substantially parallel with a direction from the input end to the output end. The optical waveguide comprising: an input region at the input end; a beam splitter configured to expand light received from the input region; a symmetrical diffraction grating comprising complementary first and second grating portions, wherein the second grating portion is substantially symmetrical to the first grating portion along a line of symmetry that is substantially parallel to the first axis. Light received at the symmetrical diffraction grating from the beam splitter is configured to be diffracted by the symmetrical diffraction grating towards the line of symmetry by the first grating portion or the second grating portion.

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 provided an arming apparatus for a store, the apparatus comprising: a first attachment system and a second attachment system; a linking connector coupled with the first attachment system and the second attachment system; and an arming connector coupled with the linking connector and a first fuze input of the store; wherein each of the first attachment system and the second attachment system comprises: an arming unit; a first frangible connector coupled with the arming unit and the linking connector; and a second frangible connector coupled with the linking connector and the store.

Abstract: Apparatus for configuring a mission automation and decision support system for an unmanned aerial vehicle comprising a user interface and a computer-implemented module configured to: receive data representative of at least one task to be performed by the UAV, the task being defined by one or more decision points that correspond to system actions or responses that could result from respective specified mission information; for each decision point(s), request user inputs in response to questions, the questions being designed to determine an extent to which each system action or response can be automated and a respective level of mandated operator approval therefor; and allocate to each decision point a set of one or more corresponding automation levels, each automation level comprising data representative of a measure of automation to be applied at a respective decision point.

Abstract: There is provided an integrity monitor configured to monitor the integrity of a component protection device. The component protection device comprises a protective medium to protect at least one electronic component, and having associated therewith a magnetic element and a Hall Effect sensor. The at least one of the magnetic element and the Hall Effect sensor is embedded within the protective medium and the Hall Effect sensor is located, when in use, to sense a magnetic field generated by the magnetic element. The integrity monitor has an input for receiving an output of the Hall Effect sensor indicative of the sensed magnetic field and the integrity monitor is configured to identify from the received output any change to the sensed magnetic field and determine, based on the change to the sensed magnetic field, an integrity of the component protection device.

Abstract: A radiation backscatter detector assembly comprising: a source array comprising source components for irradiating a shared sample location, at least two source components of the array generating radiation in different respective source energy bands; a detector array comprising detector elements for detecting backscattered radiation detection events from different respective spatial portions of the shared sample location, the detector elements each generating a pulse output in response to each radiation detection event it detects; and an energy meter for measuring the energies of the pulse outputs by different respective detector elements.

Abstract: A control system (400) for an active inceptor (103) for a fly by wire aircraft permits a zero force null point to settle to a non-zero displacement trim position. An internal position state of a second order mass spring damper model is moved in conjunction with force-displacement characteristic coordinates. This results in no second order dynamics being superimposed on the feel of the inceptor (103) when dynamically adjusting the trim position, thereby eliminating the possibility of any unpleasant buzzing been felt by the operator of the inceptor during a trimming operation.

Abstract: The invention relates to the field of Free Space Optics (FSO), more specifically it is directed to: a method of obtaining a connection between at least two optical signal nodes, of a FSO, communication system each node comprising a transmitting device and receiving device; and transmitting via the transmitting device of a first node, a first diverged optical signal into an optical medium; receiving at the receiving device of the second node the first diverged optical signal and transmitting via the transmitting device of the second node a second diverged signal to the receiving device of the first node to establish a location of said first node establishing a connection, after which; the first node switches from the diverged optical signal to a narrower optical signal for the transmission of data via the connection.

Abstract: The present invention relates to a method of classifying behaviour patterns. The method comprises configuring a simulation environment based on an operational arena, configuring an artificial agent to carry out a chosen activity within the simulation environment, generating training data from the agent's activity, and training a detection model using the training data.

Abstract: According to the present invention, there is provided a fabrication fixture for retaining a workpiece, comprising: a first housing; a second housing; said housing comprising; an independently adjustable support; wherein the first and second housing substantially envelop said workpiece to allow the workpiece to be moved.

Abstract: The present invention relates generally to a method and system (10) for classifying vehicle behaviour, particularly abnormal behaviour of civil aircraft (12). The method may comprise receiving aircraft data from an aircraft (12) which is to be classified; and determining whether the received aircraft data comprises identification information for the aircraft (12). In response to a determination that the received aircraft data comprises identification information, the method may comprise using said identification information to classify the behaviour of the aircraft (12). In response to a determination that the received aircraft data does not comprises identification information, the method may comprise obtaining the position of the aircraft and comparing the obtained position to an expected route for the aircraft to classify the behaviour of the aircraft (12).

Abstract: A cavity system, comprising: a cavity (2) comprising a cavity opening; and an acoustically reflective structure (18, 20) located at least partially within the cavity (2), the acoustically reflective structure (18, 20) comprising one or more acoustically reflective surfaces (24, 26, 30, 32), each acoustically reflective surface (24, 26, 30, 32) being oblique to a plane of the cavity opening (27). The one or more acoustically reflective surfaces (24, 26, 30, 32) may be arranged to reflect incident acoustic waves out of the cavity opening while avoiding reflection into a region (48) at or proximate to a leading edge (14) of the cavity (2).

Abstract: This invention relates to improvements in and relating to ice pigging, and comprises a flowable slush of frozen particles for ice pigging a pipework, comprising, an aqueous liquid medium, a multiplicity of frozen particulates of said aqueous liquid medium, a freezing point depressant, selected from a hydroxide ion, said hydroxide ion present in the range of less than 10 wt %.

Abstract: There is disclosed an aircraft configured to collect air data, the aircraft comprising: a wing structure; a forebody, forward of the wing structure; an afterbody, backward of the forebody; a skin covering the wing, the forebody and the afterbody; at least one recess formed at the skin, the recess being configured to affect the pressure of air flowing at the recess; at least one ambient sensor port for measuring ambient air pressure at the skin; and at least one recess sensor port for measuring the air pressure at the recess.

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: A method to obtain total compensation force information of a user input device is disclosed. The method comprising obtaining velocity information of a portion of the user input device. Obtaining acceleration information of the portion of the user input device. Obtaining damping force information force based on the velocity information. Obtaining inertial compensation force information based on the acceleration information. Combining the damping compensation force and inertial compensation force to provide the compensation force information of the user input device.

Abstract: An assembly method comprising: providing a digital model of an aircraft airframe (200), the digital model comprising digital models of component parts (202, 204) of the airframe (200); providing the component parts (202, 204), each comprising one or more predrilled fastener holes; fixing a first component part (202a) to a support structure (1102); fixing a second component part (204a) to an end effector (1112) of a robot arm (1110); using the airframe digital model, controlling the robot arm (1110) to move the second component part (204a) relative to the first component (202a) as specified in the airframe digital model to cause one or more predrilled holes in the second component (204a) part to align with one or more predrilled holes in the first component part (202a); and attaching the second component part (204a) to the first component part (202a) using fasteners through the aligned predrilled holes.

Abstract: There is provided a sacrificial sensor configured to be coupled with a part and provide an indication of damage in the part, wherein an electrical property of the sacrificial sensor is configured to change as the sacrificial sensor is damaged to indicate damage to the part.

Abstract: A robotic system comprising: a multi-axis robot; one or more sensors located on the multi-axis robot; a damping system configured to apply a resistive force to the multi-axis robot, thereby to resist movement of the multi-axis robot; and a controller coupled to the one or more sensors and the damping system, the controller being configured to: receive sensor measurements from the one or more sensors; and control, based on the received sensor measurements, the damping system thereby to control the resistive force applied by the damping system to the multi-axis robot.