Abstract: Embodiments relate generally to an ultraviolet lamp (100) for use with a photoionization detector comprising a sealed tube (102) configured to contain at least one gas; a coating (120) applied to the inner surface (110) of the sealed tube (102); and a crystal window (112) attached to the sealed tube (102), configured to allow transmittance of ultraviolet (UV) light generated within the sealed tube (102).

Abstract: Methods and systems for a flight display system are provided. The method includes: commanding a vertical situation display (VSD) and a lateral navigation display (ND) to render, concurrently, a viewing segment of a flight plan. The method includes receiving a user input selecting a section of the viewing segment, the user input being received on only one of the VSD and the ND. The method continues by commanding, concurrently, the VSD and the ND to visually distinguish the section, and to demark the section on the VSD with starting points and ending points. The method identifies a flight parameter, and for the flight parameter, includes (a) determining which display, among the VSD and the ND, is appropriate for the rendering of flight parameter information; (b) generating flight parameter information based on (a); and (c) overlaying the flight parameter information on the appropriate display.

Abstract: A vehicle communication system includes an on-board vehicle communication module and a remote communication module. The on-board vehicle communication module includes a light source that is configured to be modulated in order to transmit data, an on-board controller that controls the light source and an on-board memory that is operably coupled to the on-board controller such that the on-board controller can obtain data from the on-board memory for transmission by the light source. The remote communication module includes a light receiver that is sensitive to the modulated light provided by the light source forming part of the on-board vehicle communication module. In some cases, the vehicle communication system enables bidirectional communication between the vehicle communication module and the remote communication module.

Abstract: Systems and methods are provided for forming a composite optical element having a transparent lens carrier and a lens attached to the transparent lens carrier. The lens is formed from liquid silicone rubber. The Young's modulus of the material of the lens carrier is higher than that of liquid silicone rubber. The lens carrier includes a plurality of surface features configured to interface with the transparent lens.

Abstract: An optomechanical device comprising a circuit configured to generate an optical signal using a tuning signal and modulate the optical signal at a frequency corresponding to one quarter of a Full Width at Half Maximum (FWHM) of an optical resonance of the proof mass assembly to generate a partially modulated optical signal. The circuit being further configured to filter the partially modulated optical signal to remove a central carrier from the partially modulated optical signal to generate a filtered optical signal, modulate the filtered optical signal to generate a modulated optical signal driven to the mechanical resonance of the proof mass assembly, and generate the tuning signal using a difference between a DC intensity level of a first optical frequency component in the modulated optical signal and a DC intensity level of a second optical frequency component in the modulated optical signal.

Abstract: Dimensionally stable open woven fabrics formed from a plurality of high tenacity warp elongate bodies interwoven and bonded with a plurality of transversely disposed, high tenacity weft elongate bodies, composite articles formed therefrom, and to a continuous process for forming the composite articles.

Abstract: Viscoelastic, lightweight composite armor that is resistant to backface deformation, and to a method for evaluating the effectiveness of composite armor in resisting backface deformation. The index of retraction of a composite is determined by evaluating the degree of composite retraction at the site of impact of projectile after movement of the projectile is stopped. The degree of retraction indicates the ability of the composite to resist backface deformation.

Abstract: Sensing systems and methods for sensing a stationary individual. A sensing system may use a first sensor to determine whether a detected thermal signature is associated with a human presence within a space. When the detected thermal signature is not associated with a human presence, the sensing system may repeat the determining whether a detected thermal signature is associated with a human presence. When the detected thermal signature is associated with a human presence, the sensing system may determine whether motion has been detected using a second sensor. In some cases, the first sensor may be a thermal sensor that can detect a human whether the moving or not, and the second sensor may be a motion sensor that only detects motion.

Abstract: In some examples, a programmable device may load configuration data into a configuration storage to configure programmable logic of the programmable device. The programmable device may include a key generation logic that may read at least a portion of the configuration data from the configuration storage. The key generation logic may generate a cryptographic key based at least in part on the at least a portion of the configuration data read from the configuration storage.

Abstract: Methods are disclosed for fabricating heat exchangers and Heat Exchanger (HX) tubes, as are heat exchangers fabricated in accordance with such methods. In embodiments, the method includes the steps or processes of obtaining a Non-Equilibrium Alloy (NEA) feedstock powder comprised of an alloy matrix throughout which at least one minority constituent is dispersed. The first minority constituent precipitates from the alloy matrix when the NEA feedstock powder is exposed to temperatures exceeding a critical temperature threshold (TCRITICAL) for a predetermined time period. A cold spray process is carried-out to at least partially form the HX tubes from the NEA feedstock powder; and the HX tubes are subsequently installed in the heat exchanger. The HX tubes are exposed to a maximum temperature (TSPRAY_MAX) during the cold spray process, which is maintained below TCRITICAL to substantially preserve the non-equilibrium state of the NEA feedstock powder through cold spray deposition.

Abstract: A protective coating system includes a substrate that has an exterior surface exhibiting a degree of valley/hill surface irregularity including a plurality of hills and a plurality of valleys and a first coating layer formed directly on to the exterior surface of the substrate and that conforms to the exterior surface of the substrate such that the first coating layer has a non-uniform coating thickness over the substrate. The protective coating system further includes a second coating layer formed directly on to the exterior surface of the first coating layer. The second coating layer includes a plurality of pores within the second coating layer. Still further, the protective coating system includes a third coating layer formed within at least some of the plurality of pores within the second coating layer.

Abstract: A gas turbine engine includes a shroud with an abradable section and a non-abradable section that cooperatively define a shroud surface. The gas turbine engine also includes a rotor that is supported for rotation within the shroud to generate an aft axial fluid flow. The rotor includes a blade with a blade tip that is crowned and that opposes the abradable section and the non-abradable section of the shroud surface. A crown area of the blade tip opposes the abradable section. A casing treatment feature is provided in the non-abradable section of the shroud to oppose the blade tip of the rotor.

Abstract: A method for providing cost data for a flight is provided. The method (i) obtains cost target data for the flight, under anticipated conditions; (ii) obtains real-time aircraft performance parameters affecting the actual cost of the flight, using continuous monitoring during the flight, including at least aircraft speed modes, aircraft flight level changes, tactical interventions, weather impact, and descent timing deviations; (iii) determines an actual cost of the flight, based on the real-time aircraft performance parameters affecting the actual cost; (iv) identifies flight plan change options associated with a potential cost savings over the actual cost, wherein the flight plan change options comprise potential modifications to the flight plan to complete the flight; (v) presents the flight plan change options; and (vi) adapts operation of one or more avionics systems onboard the aircraft, based on one of the flight plan change options.

Abstract: A ground weather center may transmit information requests that carry at least one meteorological specific triggering command. An airborne system may translate the triggering command into detectable meteorological conditions and may arm the trigger(s) for specific weather sensors accordingly and downlink information upon the airborne system detects the triggering conditions. By using such a triggering command, the airborne system may be able transmit the same amount of valuable information with less bandwidth by reducing the number of redundant downlinked packets.

Abstract: Methods, devices, and systems for aircraft taxi routing are described herein. One device includes instructions stored thereon which, when executed by a processor, cause the processor to receive a record of a plurality of historical routes taken by a plurality of aircraft through taxiways of an airport, receive an indication of a plurality of conditions particular to the airport, receive an indication of a starting point of a proposed route in the airport and an endpoint of the airport, wherein the starting point and the endpoint are associated with a proposed taxiing of an aircraft, determine a route between the starting point and the endpoint based on the plurality of historical routes and the plurality of conditions, and provide the determined route to an air traffic controller.

Abstract: Methods, devices, and systems for aircraft taxiway routing are described herein. One device includes a memory, and a processor to execute executable instructions stored in the memory to receive routing data associated with an airfield of an airport, determine a group of taxiway routes associated with the airfield of the airport using the routing data where each respective taxiway route includes a number of taxiway segments, receive a routing plan request, generate a routing plan for an aircraft at the airfield using the group of taxiway routes in response to receiving the routing plan request, and a user interface to display the routing plan in a single integrated display.

Abstract: Flight planning systems and methods are provided, which augment supersonic flight planning via the integration of sonic boom forecast data. In embodiments, the flight planning system includes a display device, a pilot input interface, and a controller architecture coupled to the display device and to the pilot input interface. During system operation, the controller architecture receives flight plan criteria entered via the pilot input interface. The controller architecture then endeavors to generate or construct a boom-regulated flight plan, which includes at least one supersonic flight plan segment, in accordance with the flight plan criteria. If unable to construct a boom-regulated flight plan, the controller architecture generates a visual notification on the display device. The visual notification can include, for example, a warning that an excessive sonic boom or overpressure event may occur during execution of the flight plan by an aircraft, absent modifications to the flight plan.

Abstract: Systems and methods for suppressing bias in a non-degenerate vibratory structure are provided. In certain embodiments, a vibratory structure includes a first proof mass; a second proof mass, wherein the first proof mass and the second proof mass are driven into motion along a first axis, wherein the first proof mass and the second proof mass move in anti-phase along a second axis, wherein the motion of the first proof mass and the second proof mass along the second axis is such that the centers of mass of the first proof mass and the second proof mass move collinearly along a same axis.

Abstract: Disclosed are processes for the dechlorination of haloethanes comprising reacting in the gaseous phase a haloethane and reducing agent such as an alkene, an alkane, hydrogen or combinations of two or more of these, in the presence of a silicon-based catalyst.

Abstract: Methods and systems are provided for displaying non-compliance with expected performance values for flight parameters of an aircraft. The method comprises collecting flight parameter data from the aircraft during aircraft operations and generating a graphical display of a flight path of the aircraft. The flight parameter data is compared with the expected performance values for the flight parameters of the aircraft and points of noncompliance by the aircraft are identified along its flight path. A graphical display icon is superimposed on each point of noncompliance on a graphical display of the flight path of the aircraft. The graphical display icon is a unique iconographic representation of the flight parameter. The flight path and the display icons are displayed on a graphical display device for review after completion of aircraft operations.