Honeywell International, Inc. US
Honeywell International, Inc. US
|Patent application number
|ANTENNA WITH EFFECTIVE AND ELECTROMAGNETIC BANDGAP (EBG) MEDIA AND RELATED SYSTEM AND METHOD - An apparatus includes an antenna having multiple layers. At least a first of the layers includes both an effective medium and an electromagnetic bandgap (EBG) medium. The antenna could include a ground plane and a feed line, and the first layer of the antenna can be located between the ground plane and the feed line. The antenna could also include a slot ground and a planar antenna structure, and the first layer of the antenna could be located between the slot ground and the planar antenna structure. The antenna could further include a first substrate between a feed line and a slot ground and a second substrate covering a planar antenna structure, and the first layer could include one of the first and second substrates.
|BLOWING AGENTS, FOAM PREMIXES AND FOAMS CONTAINING HALOGENATED OLEFIN BLOWING AGENT AND ADSORBENT - The invention provides polyurethane and polyisocyanurate foams and methods for the preparation thereof. More particularly, the invention relates to closed-celled, polyurethane and polyisocyanurate foams and methods for their preparation. Preferably, the foams are produced with a polyol premix composition which comprises a combination of a hydrohaloolefin blowing agent, a polyol, a catalyst and an adsorbent material.
|PROCESS FOR THE PRODUCTION OF HCFC-1233zd - A process for the manufacture of 1-chloro-3,3,3-trifluoropropene (HCFC-1233zd) at commercial scale from the reaction of HCC-240 and HF is disclosed. In one embodiment, HCC-240fa and HF are fed to a reactor operating at high pressure. Several different reactor designs useful in this process include; a stirred-tank reactor (batch and/or continuous flow); a plug flow reactor; a static mixer used as a reactor; at least one of the above reactors operating at high pressure; optionally combined with a distillation column running at a lower pressure; and combinations of the above; and/or with a distillation column. The resulting product stream consisting of 1233zd, HCl, HF, and other byproducts is partially condensed to recover HF by phase separation. The recovered HF phase is recycled to the reactor. The HCl is scrubbed from the vapor stream and recovered as an aqueous solution. The remaining organic components including the desired HCFC-1233zd are scrubbed, dried and distilled to meet commercial product specifications.
|PROCESS FOR MAKING TETRAFLUOROPROPENE - The present invention describes a process for making CF
|PROCESS FOR 1,3,3,3-TETRAFLUOROPROPENE - The present invention provides a simple three step process for the production of 1,3,3,3-tetrafluoropropene (HFO-1234ze). In the first step, carbon tetrachloride is added to vinyl fluoride to afford the compound CCl
|FLOW SENSOR ASSEMBLY WITH INTEGRAL BYPASS CHANNEL - Flow sensor assemblies having increased flow range capabilities are disclosed. In one illustrative embodiment, a flow sensor assembly includes a housing with an inlet flow port, an outlet flow port, a fluid channel extending between the inlet flow port and the outlet flow port, and a bypass channel having a pair of taps fluidly connected to the fluid channel at separate locations. A flow sensor for sensing a measure related to a flow rate of a fluid flowing through the fluid channel can positioned in the bypass channel. A pressure differential between the two taps of the bypass channel can drive a fraction of a fluid flowing through the fluid channel through the bypass channel. The flow sensor assembly may be configured to achieve, control, and/or balance a desired fraction of fluid flow through the bypass channel and past the flow sensor.
|ATOM INTERFEROMETER WITH ADAPTIVE LAUNCH DIRECTION AND/OR POSITION - Embodiments described herein provide for a method of launching atoms in an atom interferometer. The method includes determining a direction of the total effective acceleration force on the atoms, controlling a direction of launch of the atoms for measurement in the atom interferometer based on the direction of the total effective acceleration force, and obtaining measurements from the atoms.
|ON-CHIP ALKALI DISPENSER - Embodiments described herein provide for an on-chip alkali dispenser. The on-chip alkali dispenser includes a monolithic semiconductor substrate defining a trench therein, and an evaporable metal material disposed in the trench. A heating element is disposed proximate the evaporable metal material and configured to provide heat to the evaporable metal material. A getter material is disposed to sorb unwanted materials released from the evaporable metal material.
|HIGH SENSITIVITY SINGLE ANTENNA FMCW RADAR - One embodiment is directed towards a FMCW radar having a single antenna. The radar includes a transmit path having a voltage controlled oscillator controlled by a phase-locked loop, and the phase-locked loop includes a fractional-n synthesizer configured to implement a FMCW ramp waveform that ramps from a starting frequency to an ending frequency and upon reaching the ending frequency returns to the starting frequency to ramp again. The radar also includes a delay path coupled between a coupler on the transmit path and a mixer in a receive path. The delay path is configured to delay a local oscillator reference signal from the transmit path such that the propagation time of the local oscillator reference signal from the coupler to the mixer through the delay path is between the propagation time of signal reflected off the antenna and the propagation time of a leakage signal through a circulator.
|AIRCRAFT RADAR ALTIMETER STRUCTURE - Embodiments described herein are directed towards a radar altimeter for mounting onto an aircraft. The radar altimeter includes a base configured to mount to an external surface of an aircraft, the base having an inner portion and a flange disposed around the inner portion, wherein the inner portion has a generally rectangular geometry defining a long dimension and a short dimension. A chassis is mounted to the base and has a planar portion that is disposed perpendicular to a plane formed by the base. A plurality of circuit boards are mounted to the planar portion of the chassis and disposed parallel to the planar portion of the chassis. The base is configured to mount over a second aperture in the external surface of the aircraft such that the chassis and the plurality of circuit boards are placed through the aperture and are disposed inside of the aircraft.
|TURBINE STATOR AIRFOILS WITH INDIVIDUAL ORIENTATIONS - In accordance with an exemplary embodiment, a turbine stator component includes a first endwall; a second endwall; a first stator airfoil coupled between the first and second endwalls; and a second stator airfoil adjacent to the first airfoil and coupled between the first and second endwalls. The first stator airfoil has first crystallographic primary and secondary orientations. The second stator airfoil has second crystallographic primary and secondary orientations, the first crystallographic primary and secondary orientations being different from the second crystallographic primary and secondary orientations.
|COMPOSITIONS CONTAINING FLUORINE SUBSTITUTED OLEFINS AND METHODS AND SYSTEMS USING SAME - Disclosed are the use of fluorine substituted olefins, including tetra- and penta-fluoropropenes, in a variety of applications, including in methods of depositing catalyst on a solid support, methods of sterilizing articles, cleaning methods and compositions, methods of applying medicaments, fire extinguishing/suppression compositions and methods, flavor formulations, fragrance formulations and inflating agents.
|Azeotrope-Like Composition of Hexafluoropropane, Hexafluoropropene and Hydrogen Fluoride - The present invention relates to an azeotropic or azeotrope-like mixture consisting essentially of 1,1,1,2,3,3-hexafluoropropane, hexafluoropropene and hydrogen fluoride.
|ESTIMATION OF CONVENTIONAL INERTIAL SENSOR ERRORS WITH ATOMIC INERTIAL SENSOR - Embodiments described herein provide for a method for obtaining an inertial measurement. The method includes obtaining multiple contiguous high sample rate readings during a time period from a conventional inertial sensor. Non-contiguous low sample rate reading of accumulated motion are also obtained over the time period from an atomic inertial sensor. One or more observable errors are estimated for the conventional inertial sensor based on comparing the low sample rate reading to the multiple high sample rate readings. A compensated hybrid reading is determined by compensating the high sample rate readings for the one or more observable errors based on the estimating of the one or more observable errors.
|HEAT SEALABLE COATED NYLON - A heat sealable coated nylon film comprising a layer having a first and a second surface, the layer consisting essentially of nylon, and a coating on the first surface of said layer, wherein the coating is water-based and adapted for making the coated nylon film heat sealable and wherein the coating comprises a polyurethane and a polymer selected from the group consisting of polyolefin, EVA, EAA, ethylene methacrylic copolymer, and a combination thereof. A processes of forming said coated nylon film, a packaged product comprising a product and said heat sealable coated nylon film in which the product is wrapped, and a process of packaging said product.
|Turbocharger With Annular Rotary Bypass Valve for the Turbine - A turbocharger includes a turbine wheel mounted within a turbine housing and connected to a compressor wheel by a shaft. The turbine housing defines an exhaust gas inlet connected to a volute that surrounds the turbine wheel, and an axial bore through which exhaust gas that has passed through the turbine wheel is discharged from the turbine housing. The turbine housing further defines an annular bypass passage surrounding the bore and arranged to allow exhaust gas to bypass the turbine wheel. An annular bypass valve is disposed in the bypass passage. The bypass valve includes a fixed annular valve seat and a rotary annular valve member arranged coaxially with the valve seat. The valve member is disposed against the valve seat and is rotatable about the axis for selectively varying a degree of alignment between respective orifices in the valve seat and valve member.
|HIGH TENACITY HIGH MODULUS UHMWPE FIBER AND THE PROCESS OF MAKING - Processes for preparing ultra-high molecular weight polyethylene (“UHMW PE”) filaments and multi-filament yarns, and the yarns and articles produced therefrom. Each process produces UHMW PE yarns having tenacities of 45 g/denier to 60 g/denier or more at commercially viable throughput rates.
|PROCESS FOR DEHYDROHALOGENATION OF HALOGENATED ALKANES - A process for the manufacture of halogenated olefins in semi-batch mode by dehydrohalogenation of halogenated alkanes in the presence of an aqueous base such as KOH which simultaneously neutralizes the resulting hydrogen halide. During the process, aqueous base is continuously added to the haloalkane which results in better yields, lower by-product formation and safer/more controllable operation.
|HYDROGENATION CATALYST - An alpha-alumina support for a hydrogenation catalyst useful in hydrogenating fluoroolefins is provided.
|AUTOMATED TAKE OFF CONTROL SYSTEM AND METHOD - Methods and systems for operating an avionics system on-board an aircraft are provided. In one embodiment, data associated with a take off roll is received, one or more v-speeds of the aircraft associated with the take off roll are calculated, and during the take off roll, the aircraft is controlled based on the one or more calculated v-speeds.
|PROXIMITY SENSOR WITH HEALTH MONITORING - A proximity sensor includes a relatively simple health monitoring circuit. The proximity sensor includes a variable gain oscillator, a feedback circuit, and a proximity determination circuit. The variable gain oscillator has a gain that varies with the proximity of a target to a sensor coil, generates an oscillating electrical signal having a substantially constant amplitude magnitude, and generates an energy signal representative of the electrical energy needed to sustain oscillations. The feedback circuit supplies feedback to the oscillator, and the proximity determination circuit, based on the energy signal, supplies a proximity signal representative of target proximity to the sensor coil. The health monitor circuit also receives the oscillating electrical signal and supplies a health status signal representative of proximity sensor health.
|SYSTEM AND METHOD OF SPEAKER RECOGNITION
|MASS SEPARATION VIA A TURBOMOLECULAR PUMP - A mass separation method utilizing a turbomolecular pump includes providing a gas, having analytes and ambient molecules, to an inlet chamber for allowing flow of gas into the pump, pulling gas into a pump chamber via motion of at least one of a rotor and a stator, positioning the rotor and stator such that the gas flows around an outer surface of one of the rotor or stator, and then inward toward a central axis and then toward a gas outlet, and wherein one or more target molecular or atomic species that are heavier than the ambient molecules in the gas at the inlet are passed through the chamber via the rotor and stator and a partial pressure of analytes in a gas at the outlet is increased by a larger factor than the ambient molecules at the outlet, resulting in an increase in the number analytes versus ambient molecules.
|DUAL BAND IMAGER - A dual band imager includes a lens to receive short wavelength and medium or long wavelength radiation from a scene to be imaged, a beam splitter positioned to receive the radiation from the lens, a medium or long wavelength to short wavelength image converter positioned to receive long wavelength radiation reflected via the beam splitter and to transmit the image information via short wavelength radiation, and a detector to receive the short wavelength radiation containing the image information through the beam splitter or from the scene and from the image converter.
|CLOSED LOOP ATOMIC INERTIAL SENSOR - An apparatus for inertial sensing is provided. The apparatus comprises at least one atomic inertial sensor, and one or more micro-electrical-mechanical systems (MEMS) inertial sensors operatively coupled to the atomic inertial sensor. The atomic inertial sensor and the MEMS inertial sensors operatively communicate with each other in a closed feedback loop.
|HELICOPTER COLLISION-AVOIDANCE SYSTEM USING LIGHT FIXTURE MOUNTED RADAR SENSORS - A helicopter collision-avoidance system is disclosed. An exemplary system includes at least one lamp, such as a light emitting diode (LED) lamp, an incandescent lamp, a halogen lamp, an infrared lamp, or the like; a radar emitter configured to emit a radar signal; a radar detector configured to receive a radar return signal associated with reflections of the emitted radar signal that are reflected from an object; and a radio frequency (RF) system configured to wirelessly transmit radar information associated with the received radar return signal to a radar information receiver configured to receive the wirelessly transmitted radar information. The light module is located at one of a plurality of light positions on an external surface of a helicopter.
|COLLISION-AVOIDANCE SYSTEM FOR GROUND CREW USING SENSORS - A ground obstacle collision-avoidance system includes a plurality of radar sensor modules that each receive at a radar detector radar return signals corresponding to reflections of the emitted signal from a ground obstacle, and transmits radar information associated with the received radar signal reflections reflected from the ground obstacle, wherein each of the plurality of radar sensor modules are uniquely located on a surface of an aircraft that is at risk for collision with a ground obstacle if the aircraft is moving; a gateway unit that receives the radar information transmitted from the radar sensor module and transmits information associated with the received radar information; a processing system configured to determine a distance from the installation aircraft to a detected ground object detected; and a display configured to present a plan view indicating an aircraft icon and a graphical ground obstacle icon that is associated with the detected ground obstacle.
|NOVEL UHMWPE FIBER AND METHOD TO PRODUCE - Processes for preparing ultra-high molecular weight polyethylene yarns, and the yarns and articles produced therefrom. The surfaces of partially oriented yarns are subjected to a treatment that enhances the surface energy at the fiber surfaces and are coated with a protective coating immediately after the treatment to increase the shelf life of the treatment. The coated, treated yarns are then post drawn to form highly oriented yarns.
|HYBRID FIBER UNIDIRECTIONAL TAPE AND COMPOSITE LAMINATES - Ballistic resistant materials and articles formed from fiber/tape plies that incorporate multiple different fiber or tape types within a single ply. The different fiber or tape types are physically dissimilar but may be chemically different or substantially chemically similar.
|FLUOROELASTOMERS - A fluoroelastomer comprising a copolymer of fluoroolefin monomers selected from one or more of the group consisting of 2,3,3,3-tetrafluoropropene, 1,3,3,3-tetrafluoropropene and 1-chloro-3,3,3-trifluoropropene, and ethylenically unsaturated co-monomers; wherein the fluoroelastomer has a glass transition temperature (Tg) of from about −60° C. to about 53° C. A process of making the fluoroelastomer.
|METHODS FOR DISPLAYING AIRCRAFT PROCEDURE INFORMATION - Methods are provided for presenting procedure information for an airport on a display device onboard an aircraft. A method comprises displaying a map on a display device and displaying a briefing panel overlying a portion the map. The briefing panel includes a plurality of segments, wherein each segment is associated with a type of procedure information for the airport.
|AIRPORT SURFACE COLLISION-AVOIDANCE SYSTEM (ASCAS) - Systems and methods for performing airport surface collision-avoidance. A wingtip-mounted camera allows the pilot to positively ascertain that the wingtip will clear objects located in the video. An exemplary system implemented on an aircraft includes a wingtip module having a camera that generates a video stream and a communication device that transmits the generated video stream. A processor receives the video stream and generates a reticule for the video stream. A display device simultaneously presents the video stream and the reticule. The reticule includes a horizon line and is based on a focal length of a lens of the camera and height of the camera above ground. The reticule includes curved and/or straight distance lines and curved or straight travel lines. The travel line(s) correspond to at least one aircraft component or a zone of importance and are based on location of the camera and trajectory of the aircraft.
|SYSTEMS AND METHODS FOR USING RADAR-ADAPTIVE BEAM PATTERN FOR WINGTIP PROTECTION - Systems and methods for adaptively steering radar beam patterns for coverage during aircraft turns. The radar sensor system is mechanically or electrically steered to alter the radar sensor's beam pattern in order to adapt the radar sensor's field of view (FOV) to cover the area of anticipated aircraft wingtip trajectory. The anticipated trajectory is derived, for example, from the aircraft groundspeed, acceleration, heading, turn rate, tiller position, attitude, taxi clearance, etc.
|Variable-Height Attachment Point System for a Safety Harness - Systems and methods relate to a operator selectable, variable-height attachment point system for a safety harness, where the attachment point is disposed on a radial support member that can be reversibly coupled to a vertical support member, and where the attachment point height can be selected by the operator by reversing a coupled orientation of the radial support member to the vertical support member.
|COOLED TURBINE AIRFOIL STRUCTURES - In accordance with an exemplary embodiment, disclosed is an air-cooled turbine blade having an airfoil shape, including a convex suction side wall, a concave pressure side wall, the walls including an interior surface that defines an interior with the blade, a suction side flow circuit formed within the blade interior, a pressure side flow circuit formed within the blade interior; and a trailing edge pin bank positioned aft of the suction side and pressure side flow circuits. The turbine blade includes a wishbone-shaped architecture at a transition point between the suction side flow circuit and the pressure side flow circuit and the trailing edge pin bank.
|GAS TURBINE ENGINE COMPONENTS WITH LATERAL AND FORWARD SWEEP FILM COOLING HOLES - An engine component includes a body having an internal surface and an external surface, the internal surface at least partially defining an internal cooling circuit. The engine component further includes a plurality of cooling holes formed in the body and extending between the internal cooling circuit and the external surface of the body. The plurality of cooling holes includes a first cooling hole with forward diffusion and lateral diffusion.
|SMOOTHED NAVIGATION SOLUTION USING FILTERED RESETS - A navigation system includes at least one inertial sensor configured to detect motion of the system and generate inertial data; at least one aiding device configured to generate aiding device measurement data; at least one processing unit configured to generate an un-smoothed navigation solution inclusive of navigation state variable error resets based on the inertial data and the aiding device measurement data; wherein the at least one processing unit is further configured to sum the state variable error resets into a cumulative sum of the state variable error resets; wherein the at least one processing unit is further configured to high pass filter the cumulative sum of the state variable error resets; and wherein the at least one processing unit is further configured to subtract the high pass filtered cumulative sum of the state variable error resets from the un-smoothed navigation solution to generate a smoothed navigation solution.
|SYSTEMS AND METHODS FOR DIRECTING COOLING FLOW INTO THE SURGE PLENUM OF AN EXHAUST EDUCTOR COOLING SYSTEM - A method and apparatus is provided for cooling the external surface of an aircraft APU eductor assembly. A processor is configured to open a surge valve by a predetermined amount when the surge valve is closed and the temperature of the exhaust gas exceeds a predetermined temperature in order to cool the surge plenum surfaces.
|SPALL LINERS IN COMBINATION WITH BLAST MITIGATION MATERIALS FOR VEHICLES - Spall suppressing ballistic resistant vehicular armor. More particularly, a lightweight spall suppressing ballistic resistant vehicular armor system incorporating both a spall resistant liner and a blast mitigating material. The blast mitigating material is positioned contiguous to a vehicle hull to thereby space the spall resistant liner from the vehicle hull, thereby improving the performance of the liner and the overall system.
|IMPELLER BACKFACE ROTATING HEAT SHIELD - A gas turbine engine, a rotor assembly for a gas turbine engine, and a method for thermally insulating an impeller in a gas turbine engine are provided. In one embodiment, the gas turbine engine includes an impeller having a front face configured to modify a direction of air flow through the gas turbine engine. The impeller further includes backface to which a heat shield is mounted. A closed cavity is defined between the heat shield and the backface of the impeller, and is configured to insulate the backface of the impeller from a high temperature environment.
|TURBINE ENGINES WITH CERAMIC VANES AND METHODS FOR MANUFACTURING THE SAME - A vane assembly includes first and second annular metal rings configured to accept a compressed gas flow therebetween. The first and second annular rings each include a cutout portion. The assembly further includes a ceramic matrix composite vane configured as an airfoil having a blunt rounded nose and a flattened and tapered tail. A first radial end of the vane is rigidly disposed on the first annular ring and a second radial end of the vane is slidably disposed within the cutout portion of the second annular ring such that the vane is encompassed by the first and second annular rings. The vane includes a hollow through opening portion extending radially therethrough. Still further, the assembly includes a metallic elongated member disposed within and extending through the hollow portion of vane and through the cutout portion of the first annular ring.
|THERMO-OPTICAL ARRAY DEVICES AND METHODS OF PROCESSING THERMO-OPTICAL ARRAY DEVICES - Thermo-optical array devices and methods of processing thermo-optical array devices are disclosed. One method of processing thermo-optical array devices includes forming an (001) oriented titanium dioxide material on a bolometer material, and forming a vanadium dioxide material on the (001) oriented titanium dioxide material. One thermo-optical array device includes a bolometer material, a titanium dioxide material on the bolometer material, and a vanadium dioxide material on the titanium dioxide material, wherein the vanadium dioxide material has an optical transition temperature of less than 67 degrees Celsius.
|SYSTEMS AND METHODS FOR AUTOTILTING A GROUND-MAPPING RADAR - Systems and methods that utilize a terrain database to find the elevation of the ground in the area of ground-mapping illumination to optimize the tilt of a ground-mapping antenna. An exemplary system located on a host aircraft includes a memory that stores terrain elevation data and a component that provides height, position, and orientation information of the host aircraft. A processor receives the height, the position, and the orientation information; defines a desired terrain area to be mapped, based on the received information; retrieves terrain elevation data from the memory, based on the desired terrain area to be mapped; and calculates at least one tilt angle for a ground-mapping radar function based on the retrieved terrain height value and the aircraft's height, position, and orientation information. One or more actuators is commanded to move an antenna based on the calculated at least one tilt angle.
|APPARATUS AND METHOD FOR DISPLAYING A HELICOPTER TERRAIN INTERCEPT POINT DURING LANDING - A system and method displays an intercept point on a synthetic vision display that conforms to the flight path intercepting the terrain when the nose of the helicopter is pitched up during landing. A steep approach during landing may be detected by an evaluation of, for example, attitude of the helicopter, rate of descent, and airspeed.
|GAS TURBINE ENGINES WITH IMPROVED COMPRESSOR BLADES - A rotor blade for a compressor includes a pressure sidewall; a suction sidewall coupled to the pressure sidewall at a leading edge and a trailing edge; and a through hole extending between the pressure sidewall and the suction sidewall.
|Apparatus and Method for Rapid Human Detection with Pet Immunity - A method and apparatus where the apparatus performs the steps of detecting a moving object within a secured area, determining a size of the moving object, determining that the size exceeds a predetermined threshold value associated with an animal, determining an aspect ratio of the moving object, determining that the aspect ratio meets a predetermined aspect threshold value associated with an animal or crawling human, but not an upright human, retrieving an indicator from memory that establishes whether an animal is present or not present within the secured area and setting an alarm upon detecting that the moving object exceeds the predetermined size threshold, that the determined aspect ratio meets the aspect ratio of an animal or crawling human and that the indicator establishes that there is no animal present in the secured area.
|AIRCRAFT SYSTEMS AND METHODS FOR ATTITUDE RECOVERY - A vehicle system is provided. The system includes a processor configured to receive data representative of a current attitude and a desired attitude and to generate display signals associated with the current attitude and the desired attitude. The system further includes a display device configured to receive the display signals and operable to selectively render an image including roll angle alert symbology. The roll angle alert symbology includes a first curved arrow.
|System and Method to Aggregate Control of Multiple Devices - A method and apparatus wherein the method includes the steps of a downstream controller of a security system advertising a service type of the downstream controller on a sub-network, a gateway controller of the security system detecting the advertisement and authenticating the downstream controller as being part of a group that also includes the gateway controller, the gateway controller sending a connection request to the downstream controller, the gateway and downstream controllers establishing an L4 connection based upon the connection request and the gateway and downstream controller establishing a L5 session channel through the L4 connection.
|METHOD AND SYSTEM FOR DETECTING OPTICAL RING RESONATOR RESONANCE FREQUENCIES AND FREE SPECTRAL RANGE TO REDUCE THE NUMBER OF LASERS IN A RESONATOR FIBER OPTIC GYROSCOPE - A resonator fiber optic gyroscope (RFOG) is provided. The RFOG includes a gyroscope resonator having a clockwise input port and a counter-clockwise input port; a first laser configured to couple a clockwise optical beam into to the clockwise input port; a clockwise Pound-Drever-Hall modulation generator to modulate the clockwise optical beam with a resonance tracking modulation before the clockwise optical beam is coupled into the clockwise input port; bias correction electronics; FSR-detection-and-servo electronics including a switch communicatively coupled to the clockwise Pound-Drever-Hall modulation generator; a clockwise transmission detector configured to receive an optical beam output from the counter-clockwise input port and output signals to the bias correction electronics and the FSR-detection-and-servo electronics; and a second laser configured to couple a counter-clockwise optical beam into to the counter-clockwise input port, wherein the FSR of the gyroscope resonator is measured based on the Pound-Drever-Hall modulation of the clockwise optical beam.
|GAS TURBINE ENGINE OPTIMIZATION BY ELECTRIC POWER TRANSFER - A method of increasing the operational efficiency of an operating gas turbine engine includes supplying mechanical power from a first spool of the operating gas turbine engine to a first electrical machine to thereby generate electrical power using the first electrical machine and supplying mechanical power from a second spool of the operating gas turbine engine to a second electrical machine to thereby generate electrical power using the second electrical machine. The method further includes sensing one or more operational parameters of the operating gas turbine engine and, based on the one or more sensed operational parameters, ceasing to generate electrical power using the second electrical machine, and instead supplying at least a part of the electrical power generated by the first electrical machine to the second electrical machine to operate in motoring mode and to thereby generate and supply mechanical output power to the second spool of the engine.
|SYSTEMS AND METHODS FOR UNMANNED AIRCRAFT SYSTEM COLLISION AVOIDANCE - Systems and methods are operable maintain a proscribed Self Separation distance between an unmanned aircraft system (UAS) and an object. In an example system, consecutive intruder aircraft locations relative to corresponding locations of a self aircraft are determined, wherein the determining is based on current velocities of the intruder aircraft and the self aircraft, and wherein the determining is based on current flight paths of the intruder aircraft and the self aircraft. At least one evasive maneuver for the self aircraft is computed using a processing system based on the determined consecutive intruder aircraft locations relative to the corresponding locations of the self aircraft.
|Upgradable Home Awareness System - A group of unsupervised detectors or control units, in wireless communication with a user, can be upgraded for the user with the addition of hardware and/or downloadable software to provide communications and information to a supervisory station. Supervisory station services can be implemented locally or via cloud based computer services. A displaced dealer can be contacted using codes carried by the detectors or control units for installation or activation of additional services.
|VACUUM PANELS USED TO DAMPEN SHOCK WAVES IN BODY ARMOR - Ballistic resistant composite articles having improved resistance to backface deformation. The composite articles incorporate one or more vacuum panels that mitigate or eliminate shock wave energy resulting from a projectile impact to minimize transient compression of materials behind the armor.
|Access Control Systems with Variable Threat Level - A method and apparatus incorporating the method where the method includes the steps of providing an access controller that controls locking devices on entry and egress portals of a secured area, registering the controller with an external website or information source that provides information about public threats existing outside the secured area and modifying an access level for entry into the secured area in response to notice of a public threat received from the external website or information source.
|System and Method for Doppler Radar Monitoring of Restricted Areas Below Bucket Trucks, Lineworkers on Power Distribution Poles or Other Elevated Loads - A method and system (
|AIRCRAFT FLIGHT DECK DISPLAYS AND SYSTEMS AND METHODS FOR ENHANCED DISPLAY OF OBSTACLES IN A COMBINED VISION DISPLAY - Systems and methods for enhanced display of obstacles in a combined vision display are provided. The system comprises a display unit and an enhanced vision system configured to generate first signals representative of enhanced vision images. Data storage device contains obstacle data representative of obstacles. Synthetic vision system is configured to selectively retrieve obstacle data from data storage device and generate second signals representative of synthetic vision images of one or more obstacles. Processor is in operable communication with display unit and coupled to receive first and second signals and configured, in response thereto, to: overlay the synthetic vision images of the one or more obstacles over the enhanced vision images and command display unit to display the synthetic vision images of the one or more obstacles overlaid over the enhanced vision images. The overlaid synthetic vision images of the one or more obstacles may be visually highlighted.
|LOW CONDUCTIVITY THERMAL BARRIER COATING - A ceramic composition of matter includes a solvent material and a solute material. The solvent material comprises zirconia or hafnia, or a mixture thereof, which is stabilized with a stabilizing oxide. The solute material comprises a metal oxide of the formula, X
|TRAUMA REDUCTION WITHOUT BALLISTIC PERFORMANCE REDUCTION - Ballistic resistant composite articles that are resistant to both backface deformation and ballistic penetration. Multiple composites are attached to each other such that fibers in each adjacent composite are oriented at different angles. Each composite has an areal density of at least about 100 g/m
|BALLISTIC RESISTANT THERMOPLASTIC SHEET, PROCESS OF MAKING AND ITS APPLICATIONS - Woven fabrics are formed from high tenacity fibers or tapes that are loosely interwoven with adhesive coated filaments, to composite articles formed therefrom, and to a continuous process for forming the composite articles.
|SPRING ASSEMBLIES FOR USE IN GAS TURBINE ENGINES AND METHODS FOR THEIR MANUFACTURE - In accordance with an exemplary embodiment, a method for manufacturing a bypass valve of a turbine engine control system is described. The bypass valve includes a proportional valve and an integrator valve and the integrator valve includes an integrator spring assembly. The method includes forming the integrator spring assembly using an additive manufacturing technique. The integrator spring assembly comprises first and second end portions with a spring portion disposed between the first and second end portions. The first and second end portions and the spring portion are formed as an integral unit without welding or brazing using the additive manufacturing technique. The method further includes assembling the integrator spring assembly, the integrator valve, and the proportional valve into a complete bypass valve assembly.
|AVIONIC TOUCHSCREEN CONTROL SYSTEMS AND PROGRAM PRODUCTS HAVING "NO LOOK" CONTROL SELECTION FEATURE - A system and method for selecting one of a plurality of buttons on a touchscreen, each button being associated with a separate function, comprises capturing a movable mask at a predetermined position on the touchscreen by touching the mask, and navigating on the touchscreen with the mask in search of the button. Feedback is generated when the mask is positioned over the button to identify the function, after which the button may be selected to activate the function.
|AIRCRAFT ENVIRONMENTAL CONTROL SYSTEM INLET FLOW CONTROL - A system and method for controlling bleed air flow into an air cycle machine that includes a bleed air inlet and a conditioned air outlet is provided. The system and method include discharging bleed air from an operating gas turbine engine, sensing exhaust gas temperature (EGT) of the gas turbine engine, sensing conditioned air temperature at the conditioned air outlet, and controlling bleed air flow into the air cycle machine based on the sensed EGT and on the sensed conditioned air temperature.
|METHODS AND SYSTEMS FOR DISPLAYING PROCEDURE INFORMATION ON AN AIRCRAFT DISPLAY - A method for displaying a flight path navigational procedure includes, but is not limited to, detecting with a position detecting system a current location of the aircraft, obtaining from an electronic storage device a plurality of flight path navigation procedures available for a geographic location, determining with a flight path analysis system a preferred flight path that will be taken by the aircraft, and displaying on a display unit a moving map corresponding with the current location of the aircraft and further displaying a depiction of the plurality of flight path navigation procedures on the moving map. The preferred flight path is displayed with a visual cue that visually differentiates the preferred flight path from the other flight paths of the plurality of flight path navigation procedures.
|ISOLATORS INCLUDING DAMPER ASSEMBLIES HAVING VARIABLE ANNULI AND SPACECRAFT ISOLATION SYSTEMS EMPLOYING THE SAME - Embodiments of an isolator are provided, as are embodiments of a spacecraft isolation system employing a number of three parameter isolators. In one embodiment, the isolator includes a damper assembly and a thermal compensator external to the damper assembly. The damper assembly includes, in turn, a damper housing and a first hydraulic chamber, which is located within the damper housing and which is configured to contain a damping fluid. The thermal compensator includes a thermal compensator chamber, which is fluidly coupled to the first hydraulic chamber and which is configured to exchange damping fluid therewith during operation of the isolator. A thermal compensator bellows bounds an inner circumference of the thermal compensator chamber such that the bellows is externally pressurized when the first hydraulic chamber and the thermal compensator chamber are filled with the damping fluid.
|Ultrasonic Transducers in Aspirating Smoke Detectors for Transport Time Measurement - A method and apparatus of determining gas transport time from an input port to first and second ultrasonic detectors in a flow conduit for an aspirated smoke detector includes first measuring transit time of ambient air between the detectors. Then a different gas is injected into the conduit and the time of injection is stored. The transit time is measured at least intermittently between the two ultrasonic detectors until a change therein is detected. A time of detected change is subtracted from the time of injection to establish a transport time for the aspirated smoke detector.
|TURBINE NOZZLES AND METHODS OF MANUFACTURING THE SAME - A turbine nozzle assembly includes an inner circumferential support platform, an outer circumferential support platform, and a plurality of airfoil vanes disposed between the inner circumferential support platform and the outer circumferential support platform. The turbine nozzle assembly further includes a plurality of impingement plates disposed along a radially outer surface of the outer circumferential support platform or a radially inner surface of the inner circumferential support platform, and a plurality of gap-maintaining features disposed between the plurality of outer or inner circumferential support platforms and the plurality of impingement plates. Each gap-maintaining feature of the plurality of gap-maintaining features is provided at a height such that a cooling air flow space is maintained between the plurality of outer or inner circumferential support platforms and the plurality of impingement plates.
|PLASMA ACTUATED CASCADE FLOW VECTORING - A system for directing airflow, a gas turbine engine, and a method for directing airflow exiting a cascade of internal airfoils are provided. An exemplary system for directing airflow includes a cascade of internal structures spanning an airflow path. Each of the internal structures includes a rounded trailing edge. The system further includes at least one plasma generating device positioned on the rounded trailing edge of each internal structure. Also, the system includes a controller configured to selectively energize and de-energize each plasma generating device to selectively alter a direction of local airflow around each internal structure to produce a combined airflow exiting the cascade in a desired direction.
|COMBUSTORS WITH COMPLEX SHAPED EFFUSION HOLES - A combustor is provided for a turbine engine. The combustor includes a first liner having a first side and a second side and a second liner having a first side and a second side. The second side of the second liner forms a combustion chamber with the second side of the first liner, and the combustion chamber is configured to receive an air-fuel mixture for combustion therein. The first liner defines a plurality of effusion cooling holes configured to form a film of cooling air on the second side of the first liner. The plurality of effusion cooling holes including a first effusion cooling hole extending from the first side to the second side with a non-linear line of sight.
|GAS TURBINE ENGINE ACTUATION SYSTEMS INCLUDING HIGH TEMPERATURE ACTUATORS AND METHODS FOR THE MANUFACTURE THEREOF - Embodiments of a gas turbine engine actuation system are provided, as are embodiments of a high temperature actuator and methods for the manufacture thereof. In one embodiment, the gas turbine engine actuation system includes an actuated gas turbine engine component and a high temperature actuator, which has a rotor mechanically linked to the actuated gas turbine engine component and a stator surrounding at least a portion of the rotor. The stator includes, in turn, a coil support structure having a plurality of spokes extending radially therefrom. A plurality of pre-formed electromagnetic coils is circumferentially distributed about the coil support structure. Each of the plurality of pre-formed electromagnetic coils is inserted over at least one of the plurality of spokes in a radial direction. The stator further includes an inorganic dielectric material in which each of the plurality of pre-formed electromagnetic coils is at least partially embedded.
|IMPINGEMENT-COOLED TURBINE ROTOR - An integral turbine includes a forward hub section and an aft hub section. The forward hub section and the aft hub section are metallurgically coupled to one another along an annular interface that resides within a plane generally orthogonal to a rotational axis of the axially-split turbine. The turbine further includes an airfoil blade ring metallurgically coupled to a radial outer surface of the coupled forward and aft hub sections and an impingement cavity formed within an interior portion of the coupled forward and aft hub sections. The impingement cavity includes an interior surface that is positioned proximate to the radial outer surface of the coupled forward and aft hub sections. Further, an impingement cooling air flow impinges against the interior surface of the impingement cavity to provide convective and conductive cooling to the radial outer surface of the coupled forward and aft hub sections.
|LOOKDOWN ENABLE/DISABLE FOR DETECTORS - An intrusion detector comprises a housing including a cover and baseplate mounting a circuit board. The cover and baseplate are removably mountable to a base. A motion sensor and bracket are mounted to the circuit board. The cover has a lower lookdown window. A lookdown enable/disable actuator extends from a rear side of the circuit board and is accessible through the baseplate. The actuator is operable to move a door pivotally mounted to the bracket between an on position to enable a lookdown function and an off position to disable the lookdown function. The detector is normally mounted on a wall by securing the base to the wall. The cover and baseplate can be removed from the base. A screwdriver can be used to turn the actuator. The cover and baseplate can then be remounted to the base.
|TURBINE BLADE AIRFOILS INCLUDING FILM COOLING SYSTEMS, AND METHODS FOR FORMING AN IMPROVED FILM COOLED AIRFOIL OF A TURBINE BLADE - Turbine blade airfoils, film cooling systems thereof, and methods for forming improved film cooled components are provided. The turbine blade airfoil has an external wall surface and comprises leading and trailing edges, pressure and suction sidewalls both extending between the leading and the trailing edges, an internal cavity, one or more isolation trenches in the external wall surface, a plurality of film cooling holes arranged in cooling rows, and a plurality of span-wise surface connectors interconnecting the outlets of the film cooling holes in the same cooling row to form a plurality of rows of interconnected film cooling holes. Each film cooling hole has an inlet connected to the internal cavity and an outlet opening onto the external wall surface. The span-wise surface connectors in at least one selected row of interconnected film cooling holes are disposed in the one or more isolation trenches.
|COKE TREATMENT PROCESS AND SYSTEM TO MINIMIZE NOX EMISSIONS AND MINIMIZE CATALYST VOLUME - A method and a process to treat coke generated from a process application. The method includes the steps of recovering a mixture of coke particles and water or steam removed from at least one process application vessel. The mixture is directed to a cyclonic separator utilizing centrifugal force and gravity. Water is separated from the mixture in the cyclonic separator. Coke particles are separated from the mixture in the cyclonic separator and are directed to a thermal oxidizer. Coke particles are oxidized and gasified in the thermal oxidizer to produce gas and reduced particulate matter. The gas and reduced particulate matter are thereafter directed to a burner in the process application vessel.
|GAS TURBINE ENGINES WITH TURBINE AIRFOIL COOLING - An airfoil for a gas turbine engine is provided. The airfoil includes a body with a leading edge, a trailing edge, a first side wall extending between the leading edge and the trailing edge, and a second side wall extending between the leading edge and the trailing edge. The body defines an interior cavity. The airfoil includes an interior wall disposed within the interior cavity of the body and extending between the first wall and the second wall to define a supply chamber and a leading edge chamber. The interior wall defines a cooling hole with a base portion and a locally extended portion to direct cooling air from the supply chamber to the leading edge chamber such that the cooling air impinges upon the leading edge.
Patent applications by Honeywell International, Inc. US