Abstract: A method of transmitting and receiving a plurality of Link 16 messages on a single subnet in a single timeslot includes a transmitting terminal packaging the Link 16 messages into an envelope enhanced throughput message (envelope LET message) and transmitting the envelope LET message to a receiving terminal, followed by the receiving terminal unpacking the Link 16 messages from the envelope LET message, restoring them to their original form, and presenting them to a host. Modification of the host is not required. The Link 16 messages can be relayed messages, and the transmitting terminal can be a relay terminal. The Link 16 messages can be concatenated within the envelope LET message, or another lossless packaging algorithm such as lossless compression can be applied. The terminals can be JTRS terminals, the Link 16 messages can be 115 kbps messages, and the envelope LET message can be a 2 Mbps LET message.

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 system for a vehicle is disclosed. The system comprises a gear box. The gear box comprises a first shaft coupled to a first motor and a second shaft coupled to the second motor and a third shift. Each shaft extends through a respective pinion. The gearbox has a first shifter for the first motor and a second shifter for the second motor. The shifters are configured to selectively engage a respective pinion to an appropriate shaft as needed. The gear box further comprises a fourth shaft extending through a first gear and a second gear and an other pinion. The first gear meshes with a first pinion. The second gear meshes with a second pinion. The other pinion meshes with a third pinion and a fourth gear. A differential is mechanically coupled to the fourth gear and a left axle shaft and a right axle shaft.

Abstract: A system for a vehicle is disclosed. The system comprises a gear box. The gear box comprises a first shaft coupled to a first motor and a second shaft coupled to the second motor and a third shift. Each shaft extends through a respective pinion. The gearbox has a first shifter for the first motor and a second shifter for the second motor. The shifters are configured to selectively engage a respective pinion to an appropriate shaft as needed. The gear box further comprises a fourth shaft extending through a first gear and a second gear and an other pinion. The first gear meshes with a first pinion. The second gear meshes with a second pinion. The other pinion meshes with a third pinion and a fourth gear. A differential is mechanically coupled to the fourth gear and a left axle shaft and a right axle shaft.

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: An imaging array and a pixel sensor are disclosed. One of the pixel sensors in the imaging array includes a photodiode having a cathode connected to an electron storage node and an anode connected to a hole storage node. An overflow path connects the electron storage node via an overflow gate that allows electrons to leak off of the electron storage node into the overflow path if the electron storage node has a potential less than a leakage potential. A floating diffusion node is connected to the electron storage node by a transfer gate and the overflow path by an overflow path gate. A hole storage node reset gate connects the hole storage node to ground. A hole storage capacitor is connected between the hole storage node and ground, and an overflow path coupling capacitor connects the hole storage node to the overflow path.

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: 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: 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: 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: 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 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 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: 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: 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: 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: 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).