Abstract: The disclosure relates to a charge container device, said charge container device having a volume suitable to substantially fill a barrel chamber, said charge container device is formed from a substantially rigid and combustible material, wherein said charge container device comprises at least one wall to define a cavity for the retention of at least one cartridge case, said at least one cartridge case comprising an energetic material, wherein said at least one cartridge case is arranged in a stacked formation within said charge container, the charge container device further comprising a base portion and a top portion, wherein the top portion comprises an aperture to allow for expulsion of energy and the base portion comprising an ignition means.

Abstract: A holding device and method for decreasing the contact-impact event on sub-projectiles when fired from a barrel, cylinder, carrier shell or the like includes a core and at least two legs that at least partially enclose at least one sub-projectile each. When a projectile is fired from a barrel or the like the sub-projectiles load the legs of the device which are deformed and open up and release the sub-projectiles in a controlled manner without tumbling which leads them to hit and penetrate their target with the short-side. A holding device including sub-projectiles and a projectile including the holding device are also provided.

Abstract: A fastener for securing a circuit board to a housing and/or a second circuit board. The fastener includes a locking mechanism that ensures the circuit board is reliably mounted within the housing such that the circuit board is not thermally or physically damaged because of vibrational loosening or overheating.

Abstract: A tail portion for a fin-stabilized projectile includes at least two deployable fins, which are inclined. The fins are arranged in at least two sections, which are arranged adjacent to another in the axial direction.

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: Systems and methods for encoding a data signal as a pulse position modulation (PPM) signal and decoding a PPM signal to output the original data signal. The method of encoding may comprise receiving an input data signal; converting the data within the input data signal to a sequence of PPM symbol values; and generating a PPM signal comprising an alternating sequence of synchronisation pulses and data pulses. The PPM signal may be generated by generating a plurality of synchronisation pulses at a fixed pulse repetition rate; and generating a sequence of data pulses with each data pulse having a time delay from a preceding synchronisation pulse, whereby the sequence of data pulses represent the sequence of PPM symbol values.

Abstract: The invention is a self-contained, anti-collision safety system controller for high altitude, solar powered, unmanned aircraft. The controller acts as a backup to the primary safety system on the aircraft. It automatically turns on safety system equipment, such as a Mode S transponder and anti-collision lights when the aircraft descends below a pre-set pressure altitude. The pre-set altitude is chosen so that exceeds the altitude where other aircraft are operating and where collisions might occur. The controller measures the external air pressure to determine the aircrafts pressure altitude and activates/deactivates an internal switch between the power supply and the safety system equipment depending on whether the measured altitude exceeds the pre-set altitude level or not. The controller can be integrated into the exterior surface of an aircraft or internally within the airframe.

Abstract: A remote authentication device includes a memory. The memory includes a one time pad comprising a series of bits. The memory includes circuitry arranged to retrieve a plurality of the bits from the one time pad. The circuitry is arranged to form a key from the plurality of bits and to use the key in a hash to generate an authentication code. The retrieval of the bits, forming of the key, and generation of the authentication code are repeated a plurality of times using a different plurality of bits from the one time pad.

Abstract: An indicator assembly and method for detecting and indicating a Global Positioning System (GPS) signal error during testing or monitoring of a GPS enabled device. The assembly includes an azimuth-elevation servo system; a GPS receiver; and a microprocessor engaged with the GPS receiver and servo system. The microprocessor executes programming that compares an expected self-position solution of the indicator assembly with a reported-position solution of the indicator assembly provided by the GPS receiver. The microprocessor activates the servo system to move a visually-observable indicator device to a position that reflects results of the comparison between the expected and reported position solutions. An operator noting unexpected behavior in the GPS enabled device checks the position of the indicator device and determines that a GPS signal error has occurred when the indicator device is oriented at any angle other than ninety degrees relative to a surface upon which the indicator assembly rests.

Abstract: A method is provided for manufacturing RF structures such as waveguides using additive manufacturing such as 3D printing. RF structures are also provided suitable for manufacturing with said method. The RF structures include waveguides and antenna assemblies manufactured using the additive process. The structures include flanges at the ends of the waveguide and the flanges are integrally manufactured with the said manufacturing process. The structures include a participating conductive surface that is formed on the entirety of an interior of the body, where the conductive surface extends continuously between the two ends and has been subjected to a surface modification process.

Abstract: Techniques are provided for geolocation of an airborne radar emitting source. A methodology implementing the techniques according to an embodiment includes initializing a search grid with hypothesized emitter geolocations boxes of the grid. The method further includes refining geolocations based on calculated pulse repetition intervals of de-Dopplerized times of arrival (TOAs) of emitter pulses received at multiple collection platforms within a dwell period. A residue metric is employed to qualify candidate target geolocations based on differences between the measured TOAs and hypothesized TOAs associated with the refined geolocations. A candidate history tracks the geolocations of the candidates with the smallest residue over subsequent dwells, identifying such candidates that match locations in the history and updating counts of times the candidate has been matched. Candidates with lagging match counts are dropped from the history.

Abstract: A cone antenna has at least one resistor electrically coupled to the radiating structure of the cone antenna. The capacitor may be part of a resistor network that is electrically connected to the cone. One or more patches may be coupled to the resistor network which act as a capacitor. A feed card may be embedded within a ground plane to enable the exterior of an antenna assembly to be conformal with an outer surface of a platform carrying the cone antenna.

Abstract: An analog to digital converter is disclosed that is designed to receive a differential analog signal and includes a signal chopping circuit and a successive approximation register (SAR) coupled to the signal chopping circuit. The signal chopping circuit is designed to invert a polarity of the differential analog signal and includes a first switching circuit having a first transistor and a second switching circuit having a second transistor. A gate of the first transistor and a gate of the second transistor is each coupled to a same bootstrap capacitor. Coupling both switching circuits to the same bootstrap capacitor (as opposed to separate bootstrap capacitors) greatly frees up space on the die or chip.

Abstract: Techniques and architecture are disclosed for a fuze setter adapter that operationally engages an incompatible fuze and fuze setter with each other so that fuze setting may be undertaken. The fuze and fuze setter each include at least one wireless or direct connect interface for electrical power transfer and/or data communications. The fuze setter adapter provides complementary interfaces configured to couple with the interfaces of the fuze and fuze setter. A processor control in the fuze setter adapter links the fuze setter adapter interfaces. The processor control is programmed to receive data communications from the fuze setter, convert those signals to fuze-compatible signals, and transfer the fuze-compatible signals to the fuze, and vice versa. The processor control is further programmed to receive electrical power from the fuze setter, convert that electrical power to fuze-compatible power, and transfer the fuze-compatible power to the fuze.

Abstract: There is provided an integrity monitor for a display system, the display system comprising an image source and a display. The integrity monitor comprises a controller configured to analyse sensed characteristics at one or more predetermined positions in an image area of the display system and to relate the sensed characteristics to predetermined characteristics of a stimulus, when injected into the system, thereby to determine the presence of a fault in the system. The sensed characteristics may be sensed optically or non-optically. The stimulus may be optical or non-optical.

Abstract: A fuse is provided with a reversible airbrake intended for a projectile, wherein the airbrake is arranged such that errors which occur in the flight path of the projectile can be corrected by performing one or more extensions and retractions of the airbrake. The airbrake includes at least two braking surfaces symmetrically arranged each behind a respective protective device arranged on the casing surface of the fuse, wherein the brake surfaces can be extended and retracted in a rotational direction behind the at least two protective devices via a twist shaft arranged centrally in the fuse.

Abstract: An aperture feed network includes a substrate having a first surface and a parallel second surface, first and second conductive traces on the first surface of the substrate, a third conductive trace on the second surface of the substrate, a conductive via extending through a thickness of the substrate, and one or more ground plane structures on the second surface of the substrate. The substrate comprises a dielectric material. The first and second conductive traces together form a differential signal line. The third conductive trace comprises a first branch and a second branch. The conductive via contacts the first branch of the third conductive trace on the second surface of the substrate and the second conductive trace on the first surface of the substrate. The one or more ground plane structures have irregular shapes.

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

Abstract: A light sensing apparatus includes: an arrangement of light sensing pixels, one or more pixels each associated with a noise floor and able to detect a triggering level of incoming light above the noise floor from a corresponding portion of a scene; readout circuitry to process and reset the triggering pixels; and an automatic gain control (AGC) to raise the noise floor of one or more pixels. Sometimes, the light sensing apparatus is part of a seeker that includes control circuitry to dynamically control the AGC to raise the noise floor of one or more pixels by an adjustable amount that varies in relation to the distance between the seeker and an intended target. Sometimes, the control circuitry dynamically controls the AGC in response to a concurrent triggering of two or more triggering pixels. or in response to a gain schedule corresponding to guiding the seeker to the intended target.

Abstract: A hybrid frame-based and event driven pixel, the pixel comprising a frame-based capture circuit, an event-driven capture circuit, and a photodiode in electrical communication with both the frame-based and event-driven capture circuits, wherein the frame based capture circuit is a buffered direct injection circuit, and wherein the event-driven capture circuit is a dynamic vision system circuit.