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: A generic online, probabilistic, approximate computational inference model for learning-based data processing is presented. The model includes detection, feature production and classification steps. It employs Bayesian Probabilistic Models (BPMs) to characterize complex real-world behaviors under uncertainty. The BPM learning is incremental. Online learning enables BPM adaptation to new data. The available data drives BPM complexity (e.g., number of states) accommodating spatial and temporal ambiguities, occlusions, environmental clutter, and large inter-domain data variability. Generic Sequential Bayesian Inference (GSBI) efficiently operates over BPMs to process streaming or forensic data. Deep Belief Networks (DBNs) learn feature representations from data. Examples include model applications for streaming imagery (e.g., video) and automatic target recognition (ATR).

Abstract: The system and method for an additively manufactured radome for a cavity backed notch comprising at least one lattice structure wherein the antenna works over any 4:1 bandwidth, from VHF to mmW. In some cases, the radome lattice has a density that changes with distance from the antenna. In some cases multiple antennas are used for direction finding. The radome may be additively manufactured from glass-loaded polymer or other materials having a low dielectric constant. In some cases, the radome has a dielectric contract that approaches that of air.

Abstract: Techniques, systems, architectures, and methods for providing improved feature detection of signals, especially those in relatively high interference regions, thereby allowing for earlier and longer range detection of communications and radar signals are herein provided. The techniques utilize a general framework of total variation denoising, where signals are assumed to be sparse in a combination of their first or higher order derivatives, to increase signal-to-interference ratio, which is followed by cyclostationarity detection, which is used to estimate signal features, including the period of the signals of interest and their modulation type.

Abstract: An aircraft wing (6) is provided. The aircraft wing (6) comprises at least one structure (62), (64), 66 comprising: a foam core (626), (666); first and second carbon fibre composite layers (624a), (622a), (662a), (664a) respectively attached to top and bottom sides of the foam core to sandwich the foam core; and third and fourth carbon fibre composite layers (624b), (622b), (662b), (664b) respectively disposed adjacent to the first and second carbon fibre composite layers, wherein the total thickness of the structure is between 1 mm and 11 mm. An aircraft having the aircraft wing and a method of manufacturing a structure are also provided.

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: The system and method for hyperspectral target identification provides for sue of a sensor array such that for a 2 by 2 pixel, each pixel is set to a different wavelength by employing a band pass filter, so that one can determine whether a cluster set is of a natural object or a man-made object. Using ratios of the collected energy within the partitioned sub-bands one can make near real-time declarations about targets and in some cases, friend or foe determinations.

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: 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 method of producing a component part (202, 204) of an aircraft airframe (200), the method comprising: providing a first digital model, the first digital model being a digital model of the component part (202, 204); producing an initial physical part using the first digital model; measuring a surface of the initial physical part; creating a second digital model using the measurements of the surface of the initial physical part, the second digital model being a digital model of the initial physical part; specifying one or more fastener holes (606) in the second digital model; and drilling one or more fastener holes (606) in the initial physical part using the second digital model with the one or more fastener holes specified therein, thereby producing the component part (202, 204) of an aircraft airframe (200).

Abstract: A sensor determines the spin rate or rotation frequency of a munition body of a guided projectile relative to precision guidance munition assembly. The spin rate is used to determine launch velocity of the guided projectile early in flight before GPS is operationally active. The launch velocity is used to determine whether a corrective maneuver is needed to change the range of the guided projectile. Logic can control the canards on the canard assembly in response to the determination that a corrective maneuver is needed.

Abstract: An electromagnetic coupler including: a substrate; and a first conductor mounted to the substrate for receiving a first electromagnetic signal, the first conductor having a first multiple arcuate edge; a second conductor mounted to the substrate, the second conductor being spaced apart from the first conductor and having a second multiple arcuate edge that is opposed to the first edge for generating in the second conductor a second electromagnetic signal that is derived from the first electromagnetic signal.

Abstract: Techniques and architecture are disclosed for a system that includes a fuze at a leading end of a projectile body and a fuze setter configured to engage the fuze and to program the same prior to launch. The system, in one example, includes a plurality of electrical contact pads on an exterior surface of a fuze radome housing and a plurality of electrical contact pins on the fuze setter. The electrical contact pads are arranged in a rotationally symmetric pattern that enables an electrical interface to be formed with the electrical contact pins, regardless of the rotational orientation of the fuze. Commutation is performed to rotate signals to the electrical contact pins instead of requiring that the fuze be physically rotated to bring the electrical contact pads into alignment with the electrical contact pins.

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: A system and method to aid in guidance, navigation and control of a guided projectile including a precision guidance munition assembly is provided. The system and method obtain raw position data during flight of the guided projectile, the raw position data including a plurality of position data points from the guiding sensor for determining positions of the guided projectile, establish a window including a portion of the plurality of position data points, smooth the portion of the plurality of position data points in the window, and determine a reduced noise position estimate of the guided projectile, based, at least in part, on the smoothed portion of the plurality of position data points in the window. The system and method may determine a velocity estimate of the guided projectile and predict an impact point of the guided projectile relative to a target.

Abstract: A method of producing a shim (1500) for use in an aircraft, the method comprising: providing an aircraft airframe (200); measuring a surface of the airframe (200); creating a digital model of the airframe (200) using those measurements; providing an aircraft skin (1506); measuring a surface of the aircraft skin (1506); creating a digital model of the aircraft skin (1506) using those measurements; digitally assembling the digital model of the airframe (200) with the digital model of the aircraft skin (1506); using the digitally assembled models, creating a digital model of a shim (1500), the digital model of the shim (1500) substantially filling a gap between the digitally assembled digital models of the airframe (200) and the skin (1506); and producing a physical shim (1500) using the digital model of the shim(1500).

Abstract: A guided projectile including a precision guidance munition assembly utilizes at least one maneuver envelope to optimally control movement of at least one canard to steer the guided projectile during flight. The maneuver envelopes optimize movements of the at least one canard that effectuate movement in either the range direction or the cross-range direction, or both. The maneuver envelope enables optimal timing such that maneuvering in one direction does not come at the expense of maneuver authority in the other direction.

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: A guided projectile including a precision guidance munition assembly utilizes at least one maneuver envelope to optimally control movement of at least one canard to steer the guided projectile during flight. The maneuver envelopes optimize movements of the at least one canard that effectuate movement in either the range direction or the cross-range direction, or both. The maneuver envelope enables optimal timing such that maneuvering in one direction does not come at the expense of maneuver authority in the other direction.