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: 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: 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: 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: 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: 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: 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: 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.

Abstract: A process and apparatus for forming a structure comprising: a) forming a pack from a skin sheet and a core sheet, b) placing the pack in a mould and heating the pack; c) injecting a first gas between the core and skin sheets to urge the skin sheet against the mould; d) injecting a second gas on the side of the core sheet remote from the skin sheet to urge the core sheet against the skin sheet; e) maintaining gas pressure of the second gas thereby diffusion bonding the sheets; and f) injecting a third gas between the skin sheet and the mould, to force the skin sheet against the core sheet.

Abstract: A guided projectile including a precision guidance munition assembly utilizes angular rate sensors to sample a first angular velocity of the precision guidance munition assembly from the first angular rate sensor at a first time, sample a second angular velocity of the precision guidance munition assembly from the second angular rate sensor at the first time, generate a coning command based, at least in part, on the first angular velocity and the second angular velocity, and apply the coning command to the canard assembly. The range may be decreased or increased based on the coning commands.

Abstract: An assembly comprising a horizontal GPS patch antenna element and a vertical IFF antenna element provides simultaneous high performance IFF communication and GPS reception with minimal IFF to GPS interference. The IFF element can be a monopole element. A second monopole co-linear with the IFF element can provide simultaneous UHF communication. In embodiments, the assembly is a blade that can replace an existing IFF blade on an aircraft or other asset. Separate IFF and GPS connectors can be provided, or a single connecter can be shared using an integral diplexer. Embodiments include a GPS preamplifier integral with the blade. In other embodiments, the IFF element is an annular slot transponder that is centered on the GPS patch element. Some of these embodiments are fully conformal to an underlying surface. System embodiments include bandpass filters and/or GPS blanking to further protect the GPS receiver from IFF transmissions.

Abstract: There is disclosed a filter for a vehicle window comprising a layer of filter material, the layer of filter material being for substantially preventing the transmission of radiation at a first predetermined visible wavelength band, the first predetermined visible wavelength band covering the wavelength of a predetermined laser threat, whilst substantially allowing visible wavelengths outside of the band to be transmitted, such that the filter can offer a visible light transmission of at least 70%, and a radiation detector, such that radiation at the first predetermined wavelength band can be detected.

Abstract: An air vehicle comprising a main body and a pair of opposing wing members extending substantially laterally from the main body, at least a first propulsion device associated with a first of said wing members and a second propulsion device associated with a second of said wing members, each said propulsion device being arranged and configured to generate linear thrust relative to said main body, in use, the air vehicle further comprising a control module for generating a control signal configured to change a mode of flying of said air vehicle, in use, between a fixed wing mode and a rotary wing mode, wherein, in said fixed wing mode of flying, the direction of thrust generated by the first propulsion device relative to the main body is the same as the direction of thrust generated by the second propulsion device, and in said second mode of flying, the direction of thrust generated by the first propulsion device relative to the main body is opposite to that generated by the second propulsion device.

Abstract: A workstation comprising a chassis having a base frame (10) and a monitor frame assembly (11), said base frame (10) defining a work area (20) at its proximal end for accommodating a user therein, in use, wherein a desk unit (24) is mounted laterally across said work area and provides a work surface for use by a user accommodated in said work area (20), in use, said monitor frame assembly (11) comprising an outer frame, extending laterally across said base frame (10) and upwardly from its distal end, and an inner frame (32) mounted within said outer frame and configured to receive thereon a plurality of monitor brackets (45), wherein said desk unit (24) is longitudinally adjustable relative to said base frame (10) so as to selectively adjust its distance from the monitor frame assembly (11), and said inner frame (32) is vertically adjustable within, and relative to, said outer frame so as to selectively adjust its height relative to said base frame; and further wherein respective locking means are provided to

Abstract: A pixel sensor, an imaging array that includes such pixel sensors, and a method for operating an imaging array are disclosed. The pixel sensor includes a transfer gate that connects a photodiode to a floating diffusion node in response to a transfer signal, a reset circuit, and a controller. The reset circuit is adapted to apply either a first potential or a second potential to the floating diffusion node, the second potential being less than the first potential. The controller is configured to cause the reset circuit to apply the first potential to the floating diffusion node while the transfer gate is conducting just prior to a start of an accumulation phase, and then apply the second potential to the floating diffusion node after the transfer gate is rendered non-conducting, the second potential is less than the first potential.

Abstract: An air vehicle (10) comprising a main body (12) and a pair of opposing wing members (14a, 14b) extending substantially laterally from the main body (12) having a principal axis orthogonal to the longitudinal axis (20) of said wing members, at least a first propulsion device (16a) associated with a first of said wing members arranged and configured to generate a linear thrust relative to the main body in a first direction, and a second propulsion device (16b) associated with a second of said wing members arranged and configured to generate linear thrust relative to said main body in a second, substantially opposite, direction such that said wing members and said main body are caused to rotate about said principal axis, in use, the air vehicle further comprising an imaging system (100) configured to cover a substantially 360° imaging area about said principal axis and comprising at least one electro-optic sensor (102) mounted on a support member (104) and having a field of view (102a) covering a portion of said

Abstract: A spectrum sharing system includes an advanced beacon (e.g. a low latency RF link) as part of an information sharing subsystem. The advanced beacon signal carries radar spectrum transmission schedule in an obfuscated way such as not to reveal the geolocation of the radar. The information sharing subsystem directs nodes, such as cell phones, to share spectrum based on spectrum sharing instructions contained in the advanced beacon. The spectrum sharing system permits out-of-band sharing of spectrum white space, as well as sharing of in-band spectrum gray space.