| Rosemount Aerospace Inc. Patent applications |
| Patent application number | Title | Published |
|---|
| 20160131691 | SYSTEM AND METHOD FOR PROBE HEATER HEALTH INDICATION - A multi-function probe wire de-icing apparatus is described. The multi-function probe wire de-icing apparatus may include a multi-function probe wire, a main heater wire collocated with the multi-function probe wire, and a sacrificial wire deposed adjacent to the main heater wire. The sacrificial wire is configured to fail prior to the main heater wire failing. | 05-12-2016 |
| 20160124738 | TABLET BASED AIRBORNE DATA LOADER - A method for data loading with a tablet includes receiving one or more software updates published by a ground station and storing the software updates on the tablet. The method also includes establishing communications between the tablet and a tablet interface module of an aircraft and determining if software on the aircraft needs to be updated. Based on determining that the software on the aircraft needs to be updated, the method includes transmitting at least one of the one or more software updates to the tablet interface module for loading into the aircraft and monitoring an installation process of the software updates in the aircraft via the tablet interface module. | 05-05-2016 |
| 20160025842 | SYSTEM AND METHOD FOR MONITORING OPTICAL SUBSYSTEM PERFORMANCE IN CLOUD LIDAR SYSTEMS - A method of detecting optical subsystem failures includes emitting a pulsed light beam from a laser through a window. A reflection signal indicative of a portion of the beam reflected by the window is compared to an expected signal to monitor for degradation of an optical component. | 01-28-2016 |
| 20150323287 | MULTIMODE SHORT WAVELENGTH INFRARED AND RADIO-FREQUENCY SEEKER - A multimode seeker includes a radio-frequency antenna and a controller. The radio-frequency antenna comprises a substrate and an electrically conductive film deposited on the substrate. The substrate is transparent to short wavelength infrared radiation. The electrically conductive film is configured to transmit and receive radio-frequency radiation and is transparent to the short wavelength infrared radiation. The controller is configured to receive and interpret data from the radio-frequency antenna. | 11-12-2015 |
| 20150304741 | MICROELECTROMECHANICAL RATE SENSOR - A high signal to noise ratio circuit and signal processing scheme described herein provides signal power above a noise floor such that high performance rate gyro operation can be achieved. The technology described herein exploits the combination of very low noise rate signal front end and a carrier frequency locked to a crystal filter's passband. A fixed single frequency and a sampled alternating current amplitude for conveyance of rate information is utilized. | 10-22-2015 |
| 20150302955 | HEADER SUB-ASSEMBLIES - A dielectric header sub-assembly includes a header body with opposed first and second surfaces and a side wall. The first and second surfaces define a header axis extending therebetween. The side wall extends from the first surface to the second surface. The second surface includes a tapered portion. A dielectric header sub-assembly includes a bore. The bore extends from the first surface to the second surface. A first bore opening of the bore proximate to the first surface is greater in area than a second bore opening of the bore proximate the second surface. A method of assembling a header sub-assembly includes inserting an electrical connector into a bore of a header body, applying an active braze filler material into the bore and applying heat to braze the active braze filler material to the header body and the electrical connector. | 10-22-2015 |
| 20150285432 | DISPLAY DEVICE HOLDER - In one example, an apparatus for holding a display device includes a back plate and a plurality of engaging members disposed around a periphery of the back plate. The back plate includes a rear face and a front face opposite the rear face. The plurality of engaging members extend from the back plate in a direction from the rear face to the front face to define an outer boundary of a retention space configured to accept the display device. The plurality of engaging members includes a rotatable engaging member configured to rotate between an engagement position and a disengagement position. The engagement position is configured to secure the display device within the retention space. The disengagement position is configured to allow removal of the display device from the retention space. | 10-08-2015 |
| 20150276530 | CAPACITIVE STATIC AND DYNAMIC SENSOR - A capacitive pressure sensor may be configured to transduce both a dynamic pressure and a static pressure using a single diaphragm. A capacitive pressure sensor may comprise a dynamic excitation signal module in parallel with a static excitation signal module, a summing amplifier module in connection with both the dynamic excitation module and the static excitation module, a dynamic charge amplifier stage in a parallel with a static charge amplifier stage, and a capacitive sensor connected to an output of the summing amplifier module, as well as an input of the dynamic charge amplifier stage, and an input of the static charge amplifier stage. Further, a dynamic excitation signal may be provided by the dynamic excitation signal module as a constant DC voltage signal, and a static excitation signal may be provided by the static excitation signal module as an AC voltage signal. | 10-01-2015 |
| 20150276512 | CAPACITIVE PRESSURE SENSORS FOR HIGH TEMPERATURE APPLICATIONS - A capacitive pressure sensor includes a substrate wafer and a diaphragm wafer. The substrate wafer defines a substrate recess with a first recess. The diaphragm wafer defines a diaphragm recess with a second recess. The diaphragm wafer is bonded to the substrate wafer such that the substrate and diaphragm recesses form a height differentiated pressure chamber. | 10-01-2015 |
| 20150253111 | SEMI-ACTIVE LASER SEEKER SYNCHRONIZATION - A system for semi-active laser seeker synchronization includes a laser target designator configured to emit a laser pulse signal and a seeker configured to detect the emitted signal from the laser target designator. The laser target designator and the seeker are operatively connected to synchronize the emission of the laser pulse signal and the detection of the seeker. | 09-10-2015 |
| 20150241286 | TOTAL AIR TEMPERATURE PROBE WITH LOW FRONTAL PROJECTED AREA - Deicing performance of a total air temperature (TAT) probe may be improved by reducing the size of a frontal projected area upstream of an inertial bend of the TAT probe. In accordance with various embodiments, a TAT probe may comprise an airflow inlet having a first surface substantially parallel to an incoming airflow, a primary airflow passage through the TAT probe from the airflow inlet to a primary airflow outlet, and a total air temperature sensor assembly disposed within a sensor flow passage. In various embodiments, the sensor flow passage may be oriented perpendicular to a mounting surface of the TAT probe. Further, the first surface may be perpendicular to the sensor flow passage. In various embodiments, the airflow inlet may have a second surface that is inclined relative to the first surface to help facilitate a desirable pressure gradient and boundary bleed passage function. | 08-27-2015 |
| 20150222822 | VIDEO SIGNAL TERMINATION DETECTION CIRCUIT - A video signal termination detection system includes an input configured to connect to a video driver that produces a video signal, an output configured to connect to a video receiver that operates with a signal type, a detection circuit connected between the input and the output and configured to detect the signal type of the video receiver and to output a detection signal, and a conversion circuit configured to receive the video signal from the video driver and to convert the video signal to the signal type if the video signal is different than the signal type. | 08-06-2015 |
| 20150201529 | Integrated Pipe Heat Exchanger - A heat exchanger system may have a base, a mounting apparatus for attaching the base to a device, a gasket shelf for placing a gasket, a dissipation member for dissipating heat, and heat generator attachment sites for absorbing heat. A mounting apparatus may have finger-like extensions which flex and draw the base into contact with an underlying electronic device from which the system conducts heat. A base may also have an integrated heat pipe clamp attachment forming an aperture in the base into which a heat pipe may extend and may be clamped in thermal communication. The dissipation device may be a series of fins and troughs and a fan may direct air over the dissipation device to cool the apparatus. | 07-16-2015 |
| 20150197344 | Single Aisle Mount - A single aisle mount system is disclosed. A single aisle mount system may have a device mount, an articulating base having an articulation guide and a joiner member, and a structural support. The joiner member may retain a device mount in mechanical communication with an articulating base and the articulating base may facilitate positioning of a device mount. An electronic device may be mounted on the device mount. In this manner, a single aisle mount system may facilitate easier use and viewing of an electronic device. | 07-16-2015 |
| 20150185103 | HIGH TEMPERATURE PRESSURE SENSOR - A pressure sensor assembly includes a pressure sensor having a pressure sensing transducer connected to a plurality of electrode pins via a plurality of electrode pads disposed on the transducer, an inner casing configured to hold the pressure sensing transducer including a plurality of inner casing electrode pin channels having the electrode pins disposed therein. The pressure sensor further includes an outer casing holding the inner casing therein having a capsule header with a plurality of capsule header electrode pin channels defined therein which can include a ceramic seal disposed therein such that the capsule header electrode pin channels engage the electrode pins in an insulating sealed relationship. The outer casing further includes an isolator plate including an isolator plate fluid port defined therein and a pressure isolator disposed on the isolator plate and configured to deflect in response to a change in ambient pressure. The pressure sensor includes a pressure transmitting fluid disposed in the fluid volume. | 07-02-2015 |
| 20150160254 | INDUCTIVE ROTATIONAL SPEED SENSORS - An inductive rotational speed sensor assembly includes a first PCB with a transmitter coil configured to convert an alternating electrical input into an alternating magnetic field. A second PCB is operatively connected to the first PCB for relative rotation and includes a resonance coil configured to couple to the alternating magnetic field of the first PCB to output a modulating position signal. The first PCB includes a receiver coil configured to receive the first and the modulating position signal and to output a signal indicative of rotational speed of the second PCB relative to the first PCB. | 06-11-2015 |
| 20150159988 | CONTROL SURFACE SKEW DETECTION SYSTEMS - A sensor package for sensing rotational positional data includes a stack of separated printed circuit boards that includes a first position target printed board, a second printed circuit board having a rotary sensor and a third printed circuit board having power supply components. The sensor package is included in a skew detection system for an aircraft control system, which includes a control surface having opposed first and second ends. A first drive mechanism is operatively connected to the first end of the control surface by a first rack and pinion assembly and a second drive mechanism is operatively connected to the second end of the control surface by a second rack and pinion assembly. Each rack and pinion assembly includes a respective sensor package operatively connected to the pinion thereof. A processing component is operatively connected to both sensor packages to determine presence of skew in the control surface. | 06-11-2015 |
| 20150115762 | ROTATING TRANSFORMERS FOR ELECTRICAL MACHINES - A rotary transformer for an electrical machine includes a rotary printed circuit board and a stator printed circuit board. The rotary printed circuit board is operatively connected to the stator printed circuit board for relative rotation with respect to the stator printed circuit board. A conductor is fixed to the one of the printed circuit boards and includes a spiral coil for transferring electrical energy between the rotary printed circuit board and stator printed circuit board. | 04-30-2015 |
| 20150110154 | TEMPERATURE SENSORS - A temperature sensor includes a sensor body and a wedge extension. The sensor body extends from a sensor base to an opposed sensor tip along a longitudinal axis. The sensor body has a leading edge and opposed trailing edge. The sensor body also has an interior flow passage with an inlet for fluid communication of fluid into the interior flow passage and an outlet for exhausting fluid out from the interior flow passage. The wedge extension is on the sensor body between the sensor tip and the sensor base on the leading edge of the sensor body. | 04-23-2015 |
| 20150109001 | HARDWARE-ONLY CONTACTLESS POSITION SENSOR SYSTEM - A hardware-only contactless position sensor system is provided that includes a contactless position sensor and hardware-only sensor system electronics. The sensor includes excitation, sine, and cosine coils. The electronics are coupled to the sensor and detect a position of a target relative to the sensor. The electronics include a phase shift and summation circuit that applies a phase shift at a frequency of the excitation coil to one of a sine signal from the sine coil or a cosine signal from the cosine coil as a phase shifted signal and add the phase shifted signal with an unshifted instance of the cosine or sine signal to produce a phase shifted output. The electronics also include a phase detector circuit that detects a phase of the phase shifted output and generate an output voltage corresponding to the phase and proportional to the position of the target. | 04-23-2015 |
| 20150103864 | TOTAL AIR TEMPERATURE SENSORS - A total air temperature sensor includes a probe head, a strut, and a turbulence inducing surface. The probe head has an airflow inlet and an airflow outlet. The strut defines a leading edge and an opposed trailing edge extending along a longitudinal axis, and connects between the probe head and an opposed probe mount. The turbulence inducing surface is defined in the strut aft the leading edge. The turbulence inducing surface is configured to trip a fluid boundary layer passing over the strut to transition from laminar to turbulent for moving flow separation toward the trailing edge to reduce acoustic noise emission from the total air temperature sensor. | 04-16-2015 |
| 20150103863 | TOTAL AIR TEMPERATURE SENSORS - A total air temperature probe includes a probe body extending from a probe base to an opposed probe tip along a longitudinal axis defining a leading edge and opposed trailing edge, an interior flow passage aligned with longitudinal axis defined in probe body with an inlet defined on probe tip for fluid communication with interior flow passage, and an outlet for exhausting fluid out from interior flow passage. A sloped surface on probe tip extends from leading edge to trailing edge. A temperature sensor is mounted within interior flow passage for measuring temperature of flow through interior flow passage to determine total air temperature. Sloped surface is flush with leading edge and set in from trailing edge with respect to longitudinal axis to define a lip proximate the trailing edge. The sloped surface and lip are configured to create a high pressure region proximate inlet of interior flow passage. | 04-16-2015 |
| 20150101414 | DUPLEX PRESSURE TRANSDUCERS - A transducer baseplate includes a base, a protrusion extending from the base along a longitudinal axis, a pair of opposed transducer receptacles defined within the protrusion, and respective pressure plena. The pressure plena are separated by a plenum wall, each plenum being in fluid connection with an area external to the protrusion through a respective pressure line. The pressure lines provide a direct fluid path to their respective receptacles. | 04-16-2015 |
| 20150093244 | TOTAL AIR TEMPERATURE SENSORS - A total air temperature sensor includes an airfoil body extending from an airfoil base to an opposed airfoil tip along a longitudinal axis. The airfoil body defines a leading edge and opposed trailing edge. The airfoil body defines an interior flow passage with an inlet for fluid communication of fluid into the interior flow passage and an outlet for exhausting fluid out from the interior flow passage, and wherein the airfoil body defines a bleed passage through the airfoil body between the leading edge and the interior flow passage. A temperature probe is mounted within the interior flow passage for measuring temperature of flow through the interior flow passage to determine total air temperature. | 04-02-2015 |
| 20150070700 | APPARATUS AND METHOD FOR IN-FLIGHT DETECTION OF AIRBORNE VOLCANIC ASH - A method of optically determining the presence of volcanic ash within a cloud comprises emitting a circularly polarized illuminating beam within a cloud and analyzing backscatter light to identify the presence of volcanic ash within the cloud. The method further includes determining the degree to which the cloud has altered the polarization state of the emitted beam. The index of refraction of the backscatter light and the opacity of the backscatter light are also analyzed. | 03-12-2015 |
| 20150066251 | FLUTTER CONTROL ACTUATOR - A method and apparatus for controlling an angular parameter between a base member and a control surface of an aircraft is disclosed. An estimate is obtained of an angular rate of the control surface with respect to an inertial frame of the aircraft using a rate sensor. A residual angular rate that is a difference between a commanded angular rate and the estimate of the angular rate of the control surface is determined. The residual angular rate is used to control the angular parameter of the control surface or the angular parameter of the base member. | 03-05-2015 |
| 20150063414 | SUPERCRITICAL TOTAL AIR TEMPERATURE SENSORS - A total air temperature sensor includes a supercritical airfoil body extending from an airfoil base to an opposed airfoil tip along a longitudinal axis. The supercritical airfoil body defines an interior flow passage with an inlet for fluid communication of fluid into the interior flow passage and an outlet for exhausting fluid out from the interior flow passage. A temperature probe is mounted within the interior flow passage for measuring temperature of flow through the interior flow passage to determine total air temperature. | 03-05-2015 |
| 20140339385 | ROTATING ELECTRONIC DISPLAY MOUNT - An assembly is disclosed for mounting an electronic display device to a supporting structure within the cockpit of an aircraft which includes a circular adapter plate configured for attachment to a rear surface of an electronic display device, the adapter plate having a central alignment aperture with an axially extending annular wall that faces away from the rear surface of the display device, and a receiver plate configured for attachment to a supporting structure within the cockpit of an aircraft, the receiver plate having a recessed port for blindly receiving the annular wall of the central alignment aperture of the adapter plate. | 11-20-2014 |
| 20140327764 | INTEGRATED GIMBAL ASSEMBLY - A gimbal assembly including a gimbal housing having opposed first and second yoke portions dimensioned and configured to receive a surveillance device therebetween, the yoke portions defining a gimbal axis about which the surveillance device can rotate relative to the gimbal housing, and a drive assembly disposed within the first yoke portion of the gimbal housing for driving the surveillance device about the gimbal axis, the drive assembly having a connector adapted and configured to mate with and pass electrical signals to and from a corresponding connector on the surveillance device, wherein the second yoke portion is detachable from the gimbal housing to gain access to the surveillance device and the surveillance device is removably connected to the drive assembly. | 11-06-2014 |
| 20140312161 | DUAL-MODE SAL/IR IMAGING - Dual mode SAL/IR imaging seekers are described herein. In some embodiments, a dual-mode SAL/IR imaging seeker described herein includes a focal plane array (FPA), an objective optical assembly providing a common optical path to the FPA for incident laser radiation of a first wavelength band and incident ambient radiation of a second wavelength band non-overlapping with the first wavelength band, a first optical filter operable to selectively pass the incident laser radiation to the FPA in a transmissive mode and selectively block the incident laser radiation from the FPA in a non-transmissive mode and a second optical filter assembly operable to selectively pass the incident ambient radiation to the FPA in a transmissive mode and selectively block the incident ambient radiation from the FPA in a non-transmissive mode. | 10-23-2014 |
| 20140290354 | Air data probe sense port repair - A method of repairing an air data probe sense port includes inserting a plug into a sense port in an air data probe, mounting the plug to the air data probe, dressing the welded plug to be substantially flush with adjacent air data probe surface, and forming a new sense port in the air data probe. The method can include enlarging the sense port prior to inserting the plug therein. | 10-02-2014 |
| 20140251001 | AIR DATA PROBES - An air data probe includes a probe head and a raised portion. The probe head defines a longitudinal axis and includes a forward tip and a probe head surface. The raised portion is defined in the probe head surface aft of the forward tip. The raised portion is raised radially relative to the probe head surface. The raised portion is configured and adapted to trip a fluid boundary layer passing over the probe head to transition from laminar to turbulent for reducing boundary layer separation for consistent readings at high altitudes and/or high mach numbers. A method of manufacturing an air data probe includes forming a probe head and applying a raised portion to a surface of the probe head aft of the forward tip. Applying the raised portion to the surface of the probe head includes using brazing, additive manufacturing, adhesives and/or any other suitable technique. | 09-11-2014 |
| 20140251000 | AIR DATA PROBES - An air data probe includes a probe head defining a longitudinal axis with a forward tip, and a turbulence inducing surface defined in the probe head aft of the forward tip. The turbulence inducing surface is configured and adapted to trip a fluid boundary layer passing over the probe head to transition from laminar to turbulent to control or reduce boundary layer separation resulting in consistent readings at high altitudes. | 09-11-2014 |
| 20140180638 | METHOD TO DETECT ANGLE SENSOR PERFORMANCE DEGRADATION THROUGH DITHER MONITORING - A method for detecting angle sensor performance degradation in a flow angle measurement device in moving platform, such as aircraft and watercraft, as well as stationary platforms. Sensor dither in a flow angle measurement device is used to detect operational performance degradation of the sensor as a result of dynamic response changes caused by damaged or degraded mechanical components. | 06-26-2014 |
| 20140116154 | ICE RESISTANT PITOT TUBE - A pitot tube includes a substantially cylindrical body portion and a tip portion extending along a pitot tube axis from the body portion. The tip portion includes an inlet opening and a radially tapering outer surface extending from the body portion toward the inlet opening. Another pitot tube includes a substantially cylindrical body portion and a tip portion extending along a pitot tube axis from the body portion. The tip portion includes an inlet opening. One or more electrical coils including one or more coil wraps are located at an interior of the pitot tube. One or more bulkeads are located between a forwardmost coil wrap and a drainage feature to limit travel of particles ingested into the interior. | 05-01-2014 |
| 20140074322 | AIRCRAFT AVIONICS TABLET INTERFACE MODULE - An aircraft avionics system including an aircraft interface device configured to communicate with an aircraft avionics system and a tablet interface module configured to communicate with the aircraft interface device and with one or more tablets. The aircraft avionics system includes a plurality of sensors for an aircraft and the tablet interface module provides the one or more tablets with information received from the aircraft interface device. | 03-13-2014 |
| 20140063579 | RUGGEDIZED TWO-AXIS OPTICAL BEAM STEERING DEVICE - An optical beam steering device is disclosed which includes a compartment for containing an optical component for interacting with an optical beam, a gimbal supporting the optical component and defining a pan axis, a roll cage rotatably supporting the gimbal and defining a tilt axis, wherein the tilt axis is orthogonal to the pan axis, and a mount that houses and rotatably supports the roll cage, wherein the angular position of the roll cage with respect to the mount and the angular position of the gimbal with respect to the roll cage are both locked from one side of the mount. | 03-06-2014 |
| 20140053644 | Moisture Resistant Air Data Probes - An air data probe includes a probe head. The probe head defines a longitudinal axis with a forward tip and aft base and includes a wall tap port inlet defined in the probe head aft between the forward tip and the aft base. The wall tap port inlet opens on an angle relative to the longitudinal axis, wherein the wall tap port inlet has an elongated inlet perimeter configured to resist the formation of a meniscus, or otherwise reduce moisture induced pressure errors. | 02-27-2014 |
| 20140050247 | TOTAL AIR TEMPERATURE PROBES FOR REDUCING DEICING HEATER ERROR - A total air temperature probe includes a probe head having an airflow inlet, a main airflow outlet, a main probe head wall extending from the airflow inlet to the main airflow outlet, and a flow separation bend wall positioned between the airflow inlet and the main airflow outlet. The flow separation bend wall is opposite the main probe head wall across a primary flow passage defined through the probe head from the airflow inlet to the main airflow outlet. A flow separation trip feature is defined on an interior surface of the main probe head wall for tripping a boundary layer flow separation in flow in the primary flow passage, e.g., for reduction of deicing heater error. | 02-20-2014 |
| 20140037446 | Rotor ice protection systems and methods - A method for managing icing conditions on a rotary aircraft via one or more ice protection controllers. The method includes steps for receiving an icing condition signal from an icing rate sensor at an ice protection controller, determining, in response to the icing condition signal, a de-icing signal based at least in part a liquid water content (LWC). The method further includes steps for transmitting, via a digital communication bus disposed in at least part of a slip ring assembly, the de-icing signal to a upper distributor to cause the upper distributor to transmit power to one or more heating elements for a respective rotor blade. | 02-06-2014 |
| 20140000367 | MEMS GYROS WITH QUADRATURE REDUCING SPRINGS | 01-02-2014 |
| 20130305391 | Common Computing Apparatus Providing Distinct Non-Certified And Certified Computing Platforms - An example apparatus includes a non-certified computing platform, a certified computing platform and a user interface. The non-certified computing platform includes first hardware and configured to host non-certified software. The certified computing platform is separate and distinct from the non-certified computing platform, and it includes second hardware and configured to host certified software in a partitioned environment. The user interface is coupled to both platforms and includes a display coupled to both the first hardware and second hardware via a controllable switch. According to this example, the non-certified computing platform and certified computing platform are configured to host the non-certified software and certified software such that both are capable of operating concurrently. | 11-14-2013 |
| 20130298699 | SEPARATION MODE CAPACITORS FOR SENSORS - A capacitor for use in sensors includes opposed first and second capacitor plates, wherein the second capacitor plate is mounted to the first capacitor plate by a flexible attachment. The flexible attachment is configured and adapted so that flexure of the attachment causes a change in the spacing between the first and second capacitor plates to cause a change in the capacitance thereacross. | 11-14-2013 |
| 20130276544 | STRESS ISOLATED MEMS STRUCTURES AND METHODS OF MANUFACTURE - A MEMS pressure sensor may be manufactured to include a backing substrate having a diaphragm backing portion and a pedestal portion. A diaphragm substrate may be manufactured to include a pedestal portion and a diaphragm that is mounted to the diaphragm backing portion of the backing substrate to form a stress isolated MEMS die. The pedestal portions of the backing and diaphragm substrates form a pedestal of the stress isolated MEMS die. The pedestal is configured for isolating the diaphragm from stresses including packaging and mounting stress imparted on the stress isolated MEMS die. | 10-24-2013 |
| 20130257391 | Power-Factor Correction Using Voltage-To-Current Matching - An example apparatus includes a power-factor correction (PFC) circuit coupleable to a primary load that exhibits a change in resistance with a change in applied voltage, with the respective voltage being a primary-load voltage, and current through the primary load being a primary-load current. The PFC circuit is configured to provide an auxiliary load and control current therethrough, with the respective current being an auxiliary-load current. In this regard, the PFC circuit is configured to control the auxiliary-load current such that the sum of the primary-load current and auxiliary-load current is a substantially-constant proportion of the primary-load voltage, the respective sum being a sum current. | 10-03-2013 |
| 20130248647 | VIEW-POINT GUIDED WEAPON SYSTEM AND TARGET DESIGNATION METHOD - A passive guidance system including a viewpoint capture system (VCS) including a first processor in communication with first memory and a first SWIR imager for creating a viewpoint image database having a plurality of images, at least one of the images having a target point. A weapon guidance module is in communication with the VCS and coupled to a weapon. The weapon guidance module includes a second processor in communication with second memory and a second SWIR imager for storing the viewpoint image database and correlating in-flight images from the second SWIR imager to provide guidance commands directing the weapon to the target point. | 09-26-2013 |
| 20130247576 | APPARATUS, SYSTEM AND METHOD FOR OBSERVING COMBUSTOR FLAMES IN A GAS TURBINE ENGINE - A fuel injector for a gas turbine engine is disclosed which includes a nozzle body for issuing fuel and air into a combustor, and an on-axis optical probe located within the nozzle body for observing combustor flame radiation, wherein the optical probe includes a plurality of optical fiber bundles extending to a distal end of the probe, and a shaped lens is supported at the distal end of the probe to provide a multi-directional field of view of combustion characteristics and properties in an operating gas turbine engine combustor. | 09-26-2013 |
| 20130204469 | SYSTEM AND METHOD FOR REAL-TIME AIRCRAFT PERFORMANCE MONITORING - A computer apparatus and method to determine aircraft fuel mileage performance. The computer apparatus including a memory and a processor disposed in communication with the memory and configured to issue a plurality of instructions stored in the memory. The instructions issue signals to receive real-time aircraft data during aircraft flight and process the real-time data to determine real-time aircraft mass data. A calculation is performed to determine the real-time fuel mileage performance for the aircraft based upon determined real-time aircraft mass data. | 08-08-2013 |
| 20130181303 | DIE ATTACH STRESS ISOLATION - A microstructure device package includes a package housing configured and adapted to house a microstructure device. A bracket is housed in the package housing. The bracket includes a bracket base with a first bracket arm and a second bracket arm each extending from the bracket base. A channel is defined between the first and second bracket arms. The first bracket aim defines a first mounting surface facing inward with respect to the channel. The second bracket aim defines a second mounting surface facing outward with respect to the channel. The second mounting surface of the bracket is mounted to the package housing. A microstructure device is mounted to the first mounting surface in the channel. The bracket is configured and adapted to isolate the microstructure device from packaging stress imparted from the package housing on the second mounting surface of the bracket. | 07-18-2013 |
| 20130093030 | UNATTACHED CONTAINED SEMICONDUCTOR DEVICES - An unattached, contained semiconductor device includes a semiconductor die, for example a MEMS pressure sensor die. The semiconductor die is unattached from the interior cavity of a surrounding containment body in that the semiconductor die is free of adherence to the containment body to mitigate packaging stress and strain between the containment body and the semiconductor die. | 04-18-2013 |
| 20130081341 | COMPRESSION MOUNTED WINDOW ASSEMBLY - A compression mounted window assembly is disclosed that includes a circular window having opposed front and rear planar surfaces and an outer periphery having forward and rearward chamfered edge surfaces, a compressible gasket circumscribing the outer periphery of the window, a housing with a portal having an annular seat for accommodating the window circumscribed by the gasket, wherein the annular seat has a first chamfered abutment surface corresponding to the forward chamfered edge surface of the window, an annular bezel operatively associated with the housing for compressively retaining the window assembly within the annular seat of the portal, and structure for securing the bezel to the housing, wherein the bezel has a second chamfered abutment surface corresponding to the rearward chamfered edge surface of the window. | 04-04-2013 |
| 20130013935 | Power supply system for an electronic flight bag - A control system for providing electrical power to an electronic flight bag device on an aircraft. The control system including a power switching component coupled to a plurality of power sources and at least one electronic flight bag device. The power switching component is operative and configured to selectively apply electrical power from at least one of the plurality of power sources to the at least one electronic flight bag device based upon a condition of the aircraft. | 01-10-2013 |
| 20120274938 | APPARATUS AND METHOD FOR DETECTING AIRCRAFT ICING CONDITIONS - An apparatus for detecting icing conditions on an aircraft includes a laser system configured to direct a light signal into a cloud, a lens component configured to collect echo signals from a cloud caused by the light signal directed into the cloud, a beam splitter component configured to redirect signals received and passing through the lens component into at least first and second paths and a supercooled large droplet (SLD) detector to receive the redirected signals. The SLD includes a first signal detector component configured to perform a first color measurement on the first redirected signal, and a second signal detector component configured to perform a second color measurement on the second redirected signal. The SLD detector is configured to use the first and second color measurements to determine liquid water content and droplet diameter distribution for the cloud. | 11-01-2012 |
| 20120224058 | AIRPLANE COCKPIT VIDEO SYSTEM - A cockpit video system for an airplane includes a camera assembly positioned on the airplane, a video monitor for receiving a signal from the camera assembly, and a video processing module for electronically aligning the signal so that a pilot of the airplane is presented with an aligned image on the video monitor. Preferably, the signal is an over-sized field of view and the alignment module performs the electronic aligning by cropping and re-aligning the over-sized field of view to fit the video monitor. The camera assembly is adapted and configured to attach to the exterior of the airplane. | 09-06-2012 |
| 20120167685 | IN-PLANE CAPACITIVE MEMS ACCELEROMETER - A system for determining in-plane acceleration of an object. The system includes an in-plane accelerometer with a substrate rigidly attached to an object, and a proof mass—formed from a single piece of material—movably positioned a predetermined distance above the substrate. The proof mass includes a plurality of electrode protrusions extending downward from the proof mass to form a gap of varying height between the proof mass and the substrate. The proof mass is configured to move in a direction parallel to the upper surfaces of each of the plurality of substrate electrodes when the object is accelerating, which results in a change in the area of the gap, and a change in capacitance between the substrate and the proof mass. The in-plane accelerometer can be fabricated using the same techniques used to fabricate an out-of-plane accelerometer and is suitable for high-shock applications. | 07-05-2012 |
| 20120123704 | SYSTEM AND METHOD FOR DETECTING BLOCKED PITOT-STATIC PORTS - An avionics system and process for detecting pneumatic blockages having an air pressure measurement system including a first sensor positioned in association with the air inlet of an air probe component. The air pressure measurement system having a second sensor positioned in association with the air inlet for detecting air pressure in which the second sensor has a frequency response higher than that of the first sensor. An air data computer is coupled to each of the first and second sensors being configured and operable to calculate a first aircraft movement measurement using detected air pressure from the first sensor and is further operative to determine if the first sensor is faulty or if the air inlet is blocked in dependence upon the frequency content and amplitude of the output from the second sensor. | 05-17-2012 |
| 20120121385 | METHODS AND DEVICES FOR FORCED AIR COOLING OF ELECTRONIC FLIGHT BAGS - An electronic flight bag computer (EFB) includes a housing defining first and second compartments that are fluidly isolated from and in thermal communication with one another. The first compartment contains electronic components connected to a user interface on an exterior portion of the housing for providing interactive flight related computation functions to a user. The second compartment contains a forced convection cooling component in thermal communication with the electronic components. The forced convection cooling component directs a flow of cooling fluid into the second compartment to convey heat produced by the electronic components out of the housing, such that the cooling fluid in the second compartment remains fluidly isolated from the electronic components in the first compartment of the housing. | 05-17-2012 |
| 20120118075 | STATIC PORT APPARATUS - A static port apparatus for an aircraft having a static plate having inner and outer surfaces for fixture on the aircraft. The static plate including a first set of a plurality of port apertures and at least a second set of a plurality of port apertures. Each port aperture of the second set of port apertures is coaxially positioned with respect to each port aperture of the first set of port apertures. | 05-17-2012 |
| 20120105828 | Passive optical gaseous emissions sensor - A probe assembly for measuring the concentration of exhaust's emissions in a turbine engine. The probe assembly including a first probe member configured and operable to passively generate a beam of light wherein the wavelength of the beam of light is contingent upon the configuration of the first probe member. A second probe member positioned in the probe assembly to receive the beam of light generated by the first probe member, the second probe member configured and operable to attenuate the light passively generated from the first probe member contingent upon the gaseous species present in the exhaust emissions of the turbine engine. | 05-03-2012 |
| 20120096943 | MEMS GYROS WITH QUADRATURE REDUCING SPRINGS - Spring set configurations that include an advantageous combination of spring geometries are disclosed. Spring elements having curved and straight sections, orientation of spring element anchor points with respect to the common radius, orientation of spring element segments with respect to a specific axis, balance of the length of spring elements about the common radius, and mass balance about the common radius can be used to mitigate unwanted out of plane motion. The spring set provides planar motion while reducing undesired out of plane motion making MEMS devices substantially insensitive to the process-induced etch angle variations of the spring elements. The spring set can be used in a MEMS gyro device which maintains the desired resonant modes and consistently low quadrature error even with process variations in manufacturing causing undesirable etch angles. | 04-26-2012 |
| 20120055103 | Compression mounted window assembly - A compression mounted window assembly is disclosed that includes a circular window having opposed front and rear planar surfaces and an outer periphery having forward and rearward chamfered edge surfaces, a compressible gasket circumscribing the outer periphery of the window, a housing with a portal having an annular seat for accommodating the window circumscribed by the gasket, wherein the annular seat has a first chamfered abutment surface corresponding to the forward chamfered edge surface of the window, an annular bezel operatively associated with the housing for compressively retaining the window assembly within the annular seat of the portal, and structure for securing the bezel to the housing, wherein the bezel has a second chamfered abutment surface corresponding to the rearward chamfered edge surface of the window. | 03-08-2012 |
| 20120043978 | CAPACITIVE SENSORS FOR MONITORING LOAD BEARING ON PINS - A sensor for monitoring external loads acting on a pin assembly includes a pin having an axial interior bore defined therein and having a length defined from a first end to an opposed second end thereof. A core pin is mounted axially within the interior bore of the pin spaced radially inwardly from the interior bore for relative displacement with respect to the pin. A capacitor is provided having an inner capacitor plate mounted to the core pin, and an outer capacitor plate mounted to the pin, such that relative displacement of the core and the pin due to external loading on the pin results in relative displacement of the inner and outer capacitor plates. The capacitor is configured and adapted to be connected to an electrical circuit to produce signals indicative of external loading on the pin based on relative displacement of the inner and outer capacitor plates. | 02-23-2012 |
| 20120024073 | High temperature capacitive static/dynamic pressure sensors and methods of making the same - Disclosed are capacitive pressure probes or sensors for high temperature applications. The capacitive pressure sensors of the present invention include, inter alia, a sapphire diaphragm which is disposed within an interior sensing chamber of the probe housing and has a first electrode formed on a central portion thereof. The central portion of the diaphragm and the first electrode are adapted and configured to deflect in response to pressure variations encountered within an interior sensing chamber and by the pressure sensor. A sapphire substrate which has a second electrode formed thereon is fused to the sapphire diaphragm about its periphery to form a sapphire stack and to define a reference chamber therebetween. Prior to fusing the sapphire diaphragm to the sapphire substrate, all contact surfaces are chemically treated and prepared using plasma activation, so as to create a bonding layer and to reduce the temperature required for the fusion. | 02-02-2012 |
| 20120017675 | Systems and Methods for Liquid Level Sensing Having a Differentiating Output - A liquid level sensing system including a housing configured to hold a liquid, a first temperature sensor connected to the housing and configured to output a first signal representing a first temperature measured at the first temperature sensor, a second temperature sensor connected to the housing and configured to output a second signal representing a second temperature measured at the second temperature sensor, and a circuit configured to receive the first and second signals as input and to provide an output signal proportional to the time rate of change of the difference between the first signal and the second signal. | 01-26-2012 |
| 20110282595 | THERMAL ICING CONDITIONS DETECTOR - A sensor for detecting icing conditions in an airstream includes a flow housing mounted on an aircraft and in which one or more probes are mounted. At least one of the probes subjected to impingement of the airstream and liquid moisture droplets in such airstream. The heat removal, or cooling effect on the probe in the airstream carrying liquid droplets is determined. A temperature signal indicating the airstream temperature is combined with signals from the at least one probe for determining whether or not icing conditions are present. | 11-17-2011 |
| 20110270576 | Method to detect angle sensor performance degradation through dither monitoring - A method for detecting angle sensor performance degradation in a flow angle measurement device in moving platform, such as aircraft and watercraft, as well as stationary platforms. Sensor dither in a flow angle measurement device is used to detect operational performance degradation of the sensor as a result of dynamic response changes caused by damaged or degraded mechanical components. | 11-03-2011 |
| 20110256652 | METHOD FOR FORMING A TRANSDUCER - A method for forming a transducer including the step of providing a semiconductor-on-insulator wafer including first and second semiconductor layers separated by an electrically insulating layer, wherein the first layer is formed or provided by hydrogen ion delamination of a starting wafer. The method further includes doping the first layer to form a piezoresistive film and etching the piezoresistive film to form at least one piezoresistor. The method also includes depositing or growing a metallization layer on the semiconductor-on-insulator wafer, the metallization layer including an electrical connection portion that is located on or is electrically coupled to the piezoresistor. The method includes removing at least part of the second semiconductor layer to form a diaphragm, with the at least part of the piezoresistor being located on the diaphragm, and joining the wafer to a package by melting a high temperature braze material or a glass frit material. | 10-20-2011 |
| 20110106475 | Total Air Temperature Probe and Method for Reducing De-Icing/Anti-Icing Heater Error - A method of reducing de-icing heater error (DHE) in total air temperature (TAT) probes is provided. Using the method, a nominal DHE function is obtained for a particular type of TAT probe, with the nominal DHE function having been derived from a plurality of TAT probes of the particular type. A probe specific correction coefficient is calculated for an individual TAT probe of the particular type as a function of a measured DHE at a first airflow and a predicted DHE at the first airflow. The predicted DHE at the first airflow is determined using the nominal DHE function derived from the plurality of TAT probes of the particular type. The probe specific correction coefficient is then stored for later use, or used to determine DHE with the individual TAT probe over a range of airflows as a function of the probe specific correction coefficient. | 05-05-2011 |
| 20110106331 | IMPENDING ICING PROBE WITH THERMAL ISOLATION PEDESTAL - In an icing condition detection system, a circuit provides an output representing impending icing conditions as a function of power consumption of a single element detector. A thermal isolation pedestal includes a detector support end that supports the single element detector and an opposite strut mounting end. A thermal isolation controller controls a thermal isolation pedestal temperature to thermally isolate the single element detector from a strut mounting end. | 05-05-2011 |
| 20110068230 | DETECTING ICE PARTICLES - Systems and methods for detecting ice particle accumulation is disclosed herein. In one exemplary implementation, a method for detecting ice is described in which a parameter within an interior volume of a heated conduit is measured. The method also includes detecting the presence of an accumulation of ice particles based on the parameter measured within the interior volume of the heated conduit. | 03-24-2011 |
| 20110019188 | In-Flight Multiple Field of View Detector for Supercooled Airborne Water Droplets - An airborne multiple field-of-view water droplet sensor includes an illumination portion and a detection portion. The illumination portion includes a first optical beam emitter configured to output a light beam. The detection portion includes a kaleidoscope configured to channel a first portion of the backscattered light towards an inner reflective surface of a circle-to-line converter, a multiple field of view subsystem having at least a first detector configured to receive light reflected by the circle-to-line converter, and a single field-of-view subsystem configured to receive a second portion of the backscattered light, the second portion not having been reflected by the circle-to-line converter. The single field-of-view subsystem may include a dual channel circular polarization detector for distinguishing between liquid water droplets and ice crystals based on information in the single field-of-view. | 01-27-2011 |
| 20110018741 | Mechanical latch locking detection sensors - The invention provides a sensor for determining when a latch for securing an engine cowl on an aircraft is secured by detecting the proximity of a latch hook and a latch pin. The sensor includes a resonant circuit configured and adapted to transmit a status signal when the latch is in a secured state. The sensor also includes a means for conveying status information of the latch to a location remote from the latch based on the status signal, the conveying means being operably connected to the resonant circuit. The invention also provides a method of determining when a latch is open or secured by detecting the proximity of a latch hook and a latch pin. | 01-27-2011 |
| 20110013664 | ASPIRATED ENHANCED TOTAL AIR TEMPERATURE PROBE - A total air temperature probe includes an inlet through which airflow enters a primary airflow passage through the probe. A sensor flow passage is connected to the primary flow passage. Bleed ports extend between the primary airflow passage and a cross-port which extends laterally across the probe. An aspiration aperture in the cross-port couples the cross-port to an internal cavity of a strut of the probe. The aspiration aperture can be centered within the cross-port to provide symmetrical deicing heater error behavior of the probe during changes in angle of attack. An aspiration tube couples the internal cavity of the probe to a pressure source. | 01-20-2011 |
| 20100328877 | METHODS AND DEVICES FOR FORCED AIR COOLING OF ELECTRONIC FLIGHT BAGS - An electronic flight bag computer (EFB) includes a housing defining first and second compartments that are fluidly isolated from and in thermal communication with one another. The first compartment contains electronic components connected to a user interface on an exterior portion of the housing for providing interactive flight related computation functions to a user. The second compartment contains a forced convection cooling component in thermal communication with the electronic components. The forced convection cooling component directs a flow of cooling fluid into the second compartment to convey heat produced by the electronic components out of the housing, such that the cooling fluid in the second compartment remains fluidly isolated from the electronic components in the first compartment of the housing. | 12-30-2010 |
| 20100296162 | Membrane grating for beam steering device and method of fabricating same - A method of fabricating a membrane structure for a diffractive phased array assembly is provided. The method includes the steps of providing a wafer having a body and at least a membrane layer and a backside layer disposed on opposite faces of the body, forming a grating pattern on a surface of the membrane layer, and forming a window through the wafer to expose a back surface of the membrane, thereby allowing light to pass through the membrane. | 11-25-2010 |
| 20100206991 | DETECTING ICE PARTICLES - Systems and methods for detecting ice particle accumulation is disclosed herein. In one exemplary implementation, a method for detecting ice is described in which a parameter within an interior volume of a heated conduit is measured. The method also includes detecting the presence of an accumulation of ice particles based on the parameter measured within the interior volume of the heated conduit. | 08-19-2010 |
| 20100140373 | High temperature seal assembly for optical sensor - A seal assembly for an optical sensor employed in a high temperature environment is disclosed which includes an elongated metal guide tube having a distal end portion defining an open distal end and an inner rear wall, a sapphire window disposed within the distal end portion of the metal guide tube, the sapphire window having a rear end surface abutting the inner rear wall of the distal end portion of the metal guide tube, and a platinum mounting sleeve for securing the sapphire window to the metal guide tube, the platinum mounting sleeve having one portion joined to the metal guide tube and another portion joined to the sapphire window. | 06-10-2010 |
| 20100128455 | FARADAY CAGE FOR CAMERA - A camera includes an electrically conductive housing defined by exterior walls and an interior cavity. The exterior walls of the housing have a lens opening and a connector opening formed therein. An imaging device is disposed within the interior cavity of the housing and communicates with the lens opening. A printed wiring board (PWB) is disposed within the interior cavity of the housing separating the imaging device from the connector opening. The PWB has an electrically conductive chassis plane operatively connected to the exterior walls of the housing so that the chassis plane and the housing form at least a partial Faraday cage around the imaging device. | 05-27-2010 |
| 20100116047 | THERMAL ICING CONDITIONS DETECTOR - A sensor for detecting icing conditions in an airstream includes a flow housing mounted on an aircraft and in which one or more probes are mounted. At least one of the probes subjected to impingement of the airstream and liquid moisture droplets in such airstream. The heat removal, or cooling effect on the probe in the airstream carrying liquid droplets is determined. A temperature signal indicating the airstream temperature is combined with signals from the at least one probe for determining whether or not icing conditions are present. | 05-13-2010 |
| 20100085239 | Device and method for detecting a target using a high speed sampling device - Devices and methods for detecting a target using a logic circuit for increasing the accuracy and speed at which targets can be detected in security and surveillance applications. A commercially available field programmable gate array may be used as the logic device. In one embodiment, the Multigigabit Transfer port (MGT) of the field programmable gate array is locked to an external clock. The coupling of the MGT port to an external clock increases the rate at which the received signal is sampled, without having to use the device in the oversampling mode. By doing so, the field programmable gate array is able to sample at least eight times faster than the actual transfer rate, which increases the speed and accuracy by which a target can be detected. | 04-08-2010 |
| 20100079136 | Blade tip clearance measurement sensor and method for gas turbine engines - An electromagnetic field sensor assembly for blade tip clearance measurement in a gas turbine engine is disclosed that includes a ceramic sensor body, a multi-layered wire coil wound about a distal end portion of the sensor body for producing an electromagnetic field, a ceramic well enclosing the sensor body and the coil, and a metallic housing surrounding the well and having an open distal end. | 04-01-2010 |
| 20100071375 | Apparatus for observing combustion conditions in a gas turbine engine - A fuel injector for a gas turbine combustor is disclosed which includes a fuel nozzle for issuing fuel into the combustor for combustion, at least one photodetector responsive to flame radiation indicative of an OH chemiluminescence peak, and at least one photodiode responsive to flame radiation indicative of a CH chemiluminescence peak. | 03-25-2010 |
| 20100047491 | TRANSIENT LIQUID PHASE EUTECTIC BONDING - A structure including a first structural component, a second structural component and a bonding structure bonding the first and second structural components together, where the bonding structure contains a hypoeutectic solid solution alloy. The hypoeutectic solid solution alloy may be a gold-germanium solid solution alloy, a gold-silicon solid solution alloy or a gold-tin solid solution alloy. | 02-25-2010 |
| 20100045965 | LIDAR SYSTEM USING A PSEUDO-RANDOM PULSE SEQUENCE - A light detection and ranging system includes a transmitter transmitting a transmitted light pulse timing sequence, with pseudo-random timing and including a plurality of light pulses, toward a target. An optical receiver receives a reflected light pulse timing sequence including a plurality of light pulses from the target. An electronic control unit identifies a time delay between the transmitted light pulse timing sequence and the reflected light pulse timing sequence as a function of a correlation between the transmitted and reflected light pulse timing sequences. | 02-25-2010 |
| 20100018326 | Coriolis effect mass flow meter and gyroscope - A Coriolis effect device includes a housing defining an interior chamber having a central axis, an inlet, an outlet, a leading disc and a trailing disc. Each disc is supported for oscillatory movement within the interior chamber of the housing. The leading disc defines a leading flow path in fluid communication with the inlet and interior chamber, wherein a portion of the leading flow path extends radially with respect to the central axis. The trailing disc is axially spaced from the leading disc. The trailing disc defines a trailing flow path in fluid communication with the interior chamber and the outlet, wherein a portion of the trailing flow path extends radially with respect to the central axis. A phase difference between leading and trailing oscillating signals picked up from the disc movement can be used to determine a mass flow rate of fluid passing from the inlet to the outlet. | 01-28-2010 |
| 20090288485 | High bandwidth inertial measurement unit - An inertial measurement unit is disclosed which includes a system of gyros for sensing angular rates, a system of accelerometers for sensing angular accelerations, an integrator for deriving gyro-less angular rates from the sensed angular accelerations, and a complimentary filter for blending the sensed angular rates and the gyro-less angular rates to produce a virtual angular rate output for the inertial measurement unit. | 11-26-2009 |
| 20090177326 | Heater control architecture for an ice protection system - A heater control structure for an ice protection system is disclosed that includes a first multi-role logic block having a first scheduler to schedule the operation of an array of heaters and a first controller to control a first group of heaters within the array of heaters, wherein the first scheduler communicates with a first private data bus and the first controller communicates with a second private data bus, and wherein the first scheduler and the first controller communicate with one another over a first pair of inter-channel data busses. The structure further includes a second multi-role logic block having a second controller to control a second group of heaters within the array of heaters and a second scheduler to schedule the operation of the array of heaters, wherein the second controller communicates with the first private data bus and the second scheduler communicates with the second private data bus, and wherein the second controller and the second scheduler communicate with one another over a second pair of inter-channel data busses. | 07-09-2009 |
| 20090141349 | Apparatus for observing combustion conditions in a gas turbine engine - A fuel injector for a gas turbine combustor is disclosed which includes a feed arm having a flange for mounting the injector within the combustor and a fuel nozzle depending from the feed arm for injecting fuel into the combustor for combustion. An optical sensor array is operatively associated with the fuel nozzle for observing combustor flame characteristics. The optical sensor array includes a plurality of sapphire rods positioned to be close enough to the combustor flame to oxidize soot deposits thereon. | 06-04-2009 |
| 20090123158 | LIGHT DETECTION AND RANGING SYSTEM - A light detection and ranging system includes a mirror unit rotating around a scan axis. The mirror unit includes a receiving portion and a transmitting portion offset by an angle about the scan axis relative to a surface plane of the receiving portion. Respective centroids of the receiving and transmitting portions are positioned at a common point on the scan axis while the receiving and transmitting portions rotate around the scan axis. A transmitter transmits a light pulse toward the mirror unit. The transmitting portion is positioned to reflect the light pulse toward a target. A receiver is positioned to reflect the light pulse reflected from the target toward the receiver. The angle offset compensates for a change between a cone of illumination of the transmitting portion and a field-of-view of the receiving portion resulting from the rotation of the mirror unit. | 05-14-2009 |
| 20090109048 | Wireless surface acoustic wave-based proximity sensor, sensing system and method - The subject invention is related to wireless proximity sensor and sensing system for detecting the position of an object. The system includes a transceiver for providing wireless communication with a passive wireless surface acoustic wave (SAW) proximity sensor. The wireless proximity sensor receives a wireless signal from the transceiver, which powers the SAW device and in turn transmits a signal back to the transceiver that includes information about the position of an object. The wireless proximity sensor uses one or more SAW devices with a sensing element made of magnetostrictive material, in conjunction with one or more magnets and one or more targets that are positioned relative to an object. The movement of the target(s) in relation to the proximity sensor operatively produces a mechanical response due to the shift in the magnetic field of the sensing element. The sensing element in turn enhances the magnetic field of the SAW device to which it is attached, and this information is transmitted to the transceiver as information about the position of an object. | 04-30-2009 |
| 20090095842 | Power distribution architecture for an ice protection system - An ice protection system for a vehicle is disclosed which includes a plurality of de-ice power distribution units positioned proximate to a leading edge surface of the vehicle that is susceptible to ice accretion, at least two anti-ice power distribution units located within the vehicle, spaced from the de-ice power distribution units, and a point of power regulation located within the vehicle, spaced from the power distribution units, from which power is fed to the power distribution units through independent feeder wire bundles so as to distribute line current across the system in a manner that optimizes wire weight. | 04-16-2009 |
| 20090078846 | Force sensing clevis insert - A sensor includes a clevis insert for reception within a first bore of a clevis. The clevis insert is configured to accommodate a latch pin. A strain sensing element is operatively associated with the clevis insert for detecting mechanical strain imparted to the clevis insert when a force acts on the clevis insert through the pin. The invention also provides a method of retrofitting a cowl latch assembly. | 03-26-2009 |
| 20090049927 | Force balanced impeller flow meter for mass flow rate control - A force balanced mass flow meter is disclosed that includes a cylindrical sensor housing having an interior bore, an impeller body supported for axial rotation within the interior bore of the sensor housing, and including structure for converting fluid inertia into flow induced torque when fluid flows relative to the impeller body, a proximity sensor for measuring a rotation angle of the impeller body relative to the sensor housing, an electromagnet for generating a magnetic field about the sensor housing to prevent rotation of the impeller body, electronics for determining electrical values from the proximity sensor when fluid flows relative to the impeller body and a controller for controlling current supplied to the electromagnet in response to electrical values determined from the proximity sensor, to generate a magnetic field sufficient to prevent impeller rotation. | 02-26-2009 |
| 20090003408 | THERMAL ICING CONDITIONS DETECTOR - A sensor for detecting icing conditions in an airstream includes a flow housing mounted on an aircraft and in which one or more probes are mounted. At least one of the probes subjected to impingement of the airstream and liquid moisture droplets in such airstream. The heat removal, or cooling effect on the probe in the airstream carrying liquid droplets is determined. A temperature signal indicating the airstream temperature is combined with signals from the at least one probe for determining whether or not icing conditions are present. | 01-01-2009 |
| 20080285620 | Aspirated Enhanced Total Air Temperature Probe - A total air temperature probe includes an inlet through which airflow enters a primary airflow passage through the probe. A sensor flow passage is connected to the primary flow passage. Bleed ports extend between the primary airflow passage and a cross-port which extends laterally across the probe. An aspiration aperture in the cross-port couples the cross-port to an internal cavity of a strut of the probe. The aspiration aperture can be centered within the cross-port to provide symmetrical deicing heater error behavior of the probe during changes in angle of attack. An aspiration tube couples the internal cavity of the probe to a pressure source. | 11-20-2008 |
| 20080278715 | SCANNING LADAR WITH ADJUSTABLE OPERATIONAL PARAMETERS - A LADAR has adjustable operational parameters to accommodate surveillance of a particular site. The LADAR includes a controller, a laser source governed by the controller to generate a laser beam pulsed at a pulse repetition rate, an optical scanner, a first set of optics, a first drive assembly governed by the controller, a second drive assembly governed by the controller, a light detector, a second set of optics for guiding laser echo pulses, and a processor coupled to the light detector to accommodate surveillance of the particular site. | 11-13-2008 |
