Abstract: A head tracking system HTS configured to determine a head position and/or a head orientation of a user includes one or more optical sensors producing optical measurements; and one or more inertial sensors producing inertial measurements; a processor configured, when the optical sensors fail to provide optical measurements to determine the head location and the head orientation of a user, to operate in a coasting mode using the inertial measurements from the one or more inertial sensors to determine the head location and the head orientation of a user.

Abstract: A jet aircraft with an airflow modifying device in an engine duct thereof comprising: a flow inlet; a flow outlet; and a flow passage extending from the flow inlet to the flow outlet; wherein the device is arranged to receive an incident air flow; and wherein the device is configured to at least partially modulate the air flow in the flow passage to improve flow ordering of the incident airflow, the airflow modifying device further comprising: at least one pitot sensor integral with the device located at the flow inlet; and a pressure line comprising a first end and a second end, the first end connected to the pitot sensor and the second end configured to be connected to a transducer; wherein the pressure line is completely enclosed within the device.

Abstract: A flow body unit (600) for a fluid flow rig (10) for simulating fluid flow patterns; the flow body unit (600) comprising: a flow body support frame (700); a core member (800) extending from the flow body support frame (700) along a flow body unit longitudinal axis (630); the core member (800) having a leading edge end (822) and a trailing edge end (824), the core member (800) mounted to the flow body support frame (700) at its trailing edge end (824) such that it extends away from the flow body support frame (700) to terminate at a free end (834) defined by the leading edge end (822).

Abstract: A suspension strut assembly (10) comprising a strut cylinder (100) that is hollow and defines a chamber (110) and has a first free end (12). A strut cylinder piston (200) is located in, and operable to move along, the strut cylinder chamber (110) to define a first strut cylinder sub-chamber region (112) on one side of the strut cylinder piston (200) and a second strut cylinder sub-chamber region (114) on the other side of the strut cylinder piston (200). A suspension rod (300) extends from the strut cylinder piston (200) inside the second strut cylinder sub-chamber region (114), through an aperture (116) in the strut cylinder (100), to a second free end (14) outside of the strut cylinder chamber (110). The first strut cylinder sub-chamber region (112) is configured to be in fluid communication with a first working fluid circuit (1000) via a first flow port (120).

Abstract: A computer-implemented method of determining utilisation of resources in a system having autonomous capability. The method comprises receiving (304) a plurality of input data from a respective plurality of components of the system, and receiving (302) rule set data comprising a plurality of rules. Each of the plurality of rules is configured to determine an integrity value for the input data. The method further comprises processing (306) the plurality of input data and the rule set data to generate an integrity value for each of the plurality of input data, and using (308) the integrity values to determine utilisation of resources of the system.

Abstract: A self-propelled gun system defining a recoil mitigation system comprises a chassis; a gun barrel and a chassis suspension system comprising a first wheel arm extending away from the chassis to a first wheel, the first wheel being rotatably mounted on the first wheel arm, the first wheel configured for engagement with a support surface. The first wheel arm and first wheel are configured to support the chassis a distance (Dz) apart from the support surface. The recoil mitigation system is operable such that a maximum recoil damping distance (Dz_max) of the chassis from the support surface in the z-axis for a gun firing condition is controlled to be set according to a predetermined relationship by pivoting the first wheel arm relative to the z-axis.

Abstract: A display system (100) for displaying on a least two different types of display a view of an environment in a real world situation, the system comprising: a first display (200) of a first type; a second display (202) of a second type which is different from the first type; a control system (100, 108) for controlling how information is to be displayed between the first display (200) and the second display (202) and configured to: determine (500) there is available symbology relating to the real world situation; determine (502) a positionally correct location the symbology would occupy if visible; determine (504) that at least one of the first display (200) and the second display (202) are displaying a view that corresponds with the positionally correct location of where the symbology, or portions of the symbology, would occupy if visible; cause (512) the symbology, or portions of the symbology, to be displayed, in the positionally correct location in the at least one of the first display (200) and the second d

Abstract: A jet engine exhaust assembly 20 is disclosed. The exhaust assembly comprises a double-walled exhaust duct 22 comprising an inner wall defining the inner profile of the duct and an outer wall spaced apart from the outer surface of said inner wall to define a cooling space 21 therebetween. The double-walled exhaust duct 20 is a structural load bearing component.

Abstract: A system for delivering an image to a user via a waveguide display system and for determining integrity of an image, the system comprising a waveguide assembly including: an in coupling element configured to receive a collimated image from a imaging system and an out coupling element configured to direct the collimated image toward an eye of a user, wherein the waveguide is configured to direct at least a first portion of the collimated image from the in coupling element to the out coupling element to be directed to the user; wherein prior to the collimated image being directed towards the eye a second portion of the collimated image is configured to be directed towards an integrity monitoring module which determines at least one discrepancy between the collimated image and the image to thereby correct the first portion of the collimated image.

Abstract: A swash plate for a hybrid air vehicle able to transition between rotary-wing and fixed-wing flight modes is provided. The swash plate comprises: a frame arranged to be driven to travel up and down a plurality of legs extending from a fuselage of the air vehicle, the frame being mounted such that it can rotate relative to the fuselage; at least one connecting rod for coupling the frame to a wing member of the air vehicle, the at least one connecting rod being coupled at its top end to the wing member and at its bottom end to the frame, wherein a bottom end of the at least one connecting rod is arranged to slide along one side of the frame and to pivot about a transverse axis of the frame. A hybrid air vehicle having the same and a method of operating a swash plate are also provided.

Abstract: A method of simulating a RADAR system defined by a corresponding RADAR model comprising a transmit chain, a receive chain and a data processing chain, the method implemented by a computer comprising a processor and a memory, the method comprising: transmitting, by the transmit chain, a radio frequency, RF, signal into an environment including a target and optionally, clutter (2702); calculating respective reflected RF signals of the transmitted RF signal from the target and from the optional clutter (2704); receiving, by the receive chain, the respective reflected RF signals (2706); detecting, by the data processing chain, the target using the received respective reflected RF signals (2708); and determining a simulated output of the RADAR system using a result of detecting the target (2710).

Abstract: The present disclosure relates to radar decoys, methods for controlling radar decoys and UAVs having a radar decoy. The radar decoy may comprise a passive reflector arranged to reflect radar signals, and a semi-active metasurface configured to have a reflection coefficient with a time-variable complex component. The present disclosure also relates to a method of controlling a semi-active radar metasurface.

Abstract: A system and method for detecting anomalous system behaviour. The system includes a plurality of sensors and a trained autoencoder. The method of training includes: obtaining training data and test data comprising multiple data records for at least one engineering asset which corresponds to the engineering asset whose behaviour is to be classified, wherein the data records comprise a plurality of sensor readings for the engineering asset; fitting the autoencoder to the obtained training data; running the test data through the encoder of the fitted autoencoder to obtain encodings of the test data; generating a plurality of data sets from the obtained encodings, wherein the generated plurality of data sets include under-represented data sets; cloning the fitted autoencoder to create a cloned autoencoder for each of the generated plurality of data sets; and aggregating the cloned autoencoders to form an over-arching autoencoder.

Abstract: According to an aspect of the present invention there is provided an optical device made according to an augmented reality optical design, the optical device comprising a plurality of optical elements for transmitting a light from a light source for display on an eye of a user, wherein the optical device comprises: a light source generating the light; a lens assembly off-axis from the light source and configured to receive the light; a first at least partially mirrored device; a second optical device located intermediate the lens assembly and the first at least partially mirrored device, the second optical device configured to receive the light from the lens assembly and transmit the light to the first at least partially mirrored device; and a combiner receiving the light from the first at least partially mirrored device and directing the light to form a virtual image at an exit pupil at the position of the eye.

Abstract: Described herein is an active throttle quadrant assembly. The active throttle assembly comprises a lever mounted via a first pivot at a proximal end of the lever and a grip on a distal end of the lever.

Abstract: A cavity system is provided. The cavity system (100-600) comprises: a cavity (2) and a spoiler (104-604); and the spoiler (104-604) having a front surface and a rear surface. The spoiler (104-604) is positioned in proximity to a leading edge (14) of the cavity (2), the leading edge (14) being relative to an actual or intended flow direction (3) of a fluid over the cavity (2). The spoiler (104-604) is arranged with its longitudinal axis perpendicular or at an oblique angle to the actual or intended flow direction (3) such that the front surface faces towards the flow direction (3). A first region of the spoiler (104-604) extends further toward the leading edge than a second region of the spoiler (104-604).

Abstract: The present invention relates to energy efficient machine learning (ML) models, in particular to energy efficient ML model generation for energy efficient inferencing. According to an aspect of the invention, there is provided a computer implemented method of operating an ML training system for training a ML model.

Abstract: An air vehicle is provided. The air vehicle comprises: a fuselage; a wing body and a pair of opposing wing members extending substantially laterally from the wing body; a stabiliser for generating force that, in use, counteracts torque exerted on the fuselage by the rotating wing body; a rotor mast for coupling the wing body to an upper side of the fuselage, wherein in a first configuration of the air vehicle the rotor mast is locked such that the wing body does not rotate relative to the fuselage and in a second configuration of the air vehicle the rotor mast is unlocked such that the wing body rotates relative to the fuselage; and propulsion means for providing linear thrust in the first configuration and for providing rotary thrust in the second configuration. A method of controlling an air vehicle is also provided.

Abstract: In some examples, an acoustic absorbing structure comprises a surface comprising an array of apertures, each aperture defining an opening for a corresponding channel, each channel forming a non-resonant acoustic attenuation structure with an axially decreasing cross-section over at least a portion of the length of the channel.

Abstract: The present invention relates to an augmented vision system (200) for a platform operator.