GOODRICH CORPORATION Patent applications |
Patent application number | Title | Published |
20160137851 | Anti-Corrosion and/or Passivation Compositions for Metal Containing Subtrates and Methods for Making, Enhancing, and Applying the Same - A corrosion inhibition composition is disclosed comprising a cerium, a tungstate, a molybdate and silicate compounds. A corrosion inhibition composition is provided comprising a zinc oxide, a zinc hydroxide benzoate, a sodium benzoate, a molybdate and a silicate compound. A corrosion inhibition composition is provided comprising a zinc oxide, a zinc phosphate, a calcium silicate, an aluminum phosphate, a zinc calcium strontium aluminum orthophosphate silicate hydrate, a molybdate, and silicate compounds. | 05-19-2016 |
20160129994 | LANDING GEAR WITH STRUCTURAL LOAD PATH DIVERTER BRACKET - A landing gear support arrangement may comprise a cylinder, a pin pivotally coupled to the cylinder, a head attached to the pin having a portion extending radially from the pin, and a bracket coupled to the portion of the head configured to axially support the pin. | 05-12-2016 |
20160126811 | Brushless Motor with Modular Position Sensor - A brushless DC motor is provided. The brushless DC motor comprises a motor housing around an axis, a stator assembly inside the motor housing, a carrier plate fixed relative to the stator assembly, and a Hall effect sensor assembly removably coupled to the carrier plate. A method of making a brushless DC motor is also provided comprising fixing a carrier plate relative to a stator assembly of a brushless DC motor assembly, and fixing a first Hall effect sensor array to the carrier plate. | 05-05-2016 |
20160123445 | BALL SCREW ASSEMBLY FOR AIRCRAFT BRAKE - A mechanical linear actuator in an aircraft brake may include a ball nut, a ball screw, and an actuator drive unit housing. The ball screw may rotate to drive the ball nut axially. The ball screw and the actuator drive unit housing may form a series of annular raceways. The ball screw may have a first window corresponding to a first raceway and a second window corresponding to a second raceway. Balls may be inserted into the first raceway through the first window and into the second raceway through the second window. | 05-05-2016 |
20160122930 | SYSTEM AND METHOD TO FABRICATE HELICAL FABRIC - A substantially continuous sewn helical fabric circular loom bed plate turntable system is described herein. The circular loom bed plate turntable may comprise a positive lay down delivery station, a rotating table comprising a plurality of pass-through grooves, a robotic sewing head comprising a needle configured to pass through a first subset of the plurality of pass-through grooves, and a fabric packaging station. The circular loom bed may comprise a positive lay down delivery station, a first semi-circular conveying system, a sewing zone comprising a robotic sewing head, a second semi-circular conveying system, and a fabric packaging station. | 05-05-2016 |
20160122922 | SYSTEM AND METHOD FOR PREPARING TEXTILES WITH VOLUMIZED TOWS FOR FACILITATING DENSIFICATION - A transport of carbon fiber bundles, in as fabricated carbon fiber tow form, with in-line manipulation of the fiber bundles (spreading or spreading and volumization with manipulators) during fiber bundle transport is described herein. A method including positively transporting and placing a fiber bundle via a moveable fiber bundle delivery mechanism interposed between a fiber bundle supply and a fiber bundle delivery location, manipulating at least one of a fiber volume and an areal weight of the fiber bundle via an air jet device coupled between the fiber bundle delivery location and the fiber bundle supply, and controlling delivery of the fiber bundle tension from the fiber supply through an electronic unwinder is also described. | 05-05-2016 |
20160122921 | SYSTEM AND METHOD FOR MANUFACTURING NET SHAPE PREFORM FROM TEXTILE STRIPS - A preform manufacturing apparatus comprising a supply of fiber strip, a moveable positive fiber strip delivery mechanism coupled between a desired lay down location and the supply of fiber strip to positively deliver and orient the supply of fiber strip to the desired lay down location, and an optional electronic unwinder coupled to the supply of fiber strip when more delicate textile strips are used to fabricate the net shape preform is described herein. The electronic unwinder is configured to interact with the moveable positive fiber strip delivery mechanism. | 05-05-2016 |
20160122009 | AIRCRAFT BRAKE PUCK ASSEMBLY - An electro-mechanical actuator in an aircraft brake may include a ball nut piston, and endcap coupled to the ball nut piston, a retaining ring coupled to the endcap, and a puck secured within the endcap. The puck may be permanently retained within the retaining ring. The retaining ring may be a split ring which is installed around a base of the puck. The puck may be inserted within a single-piece retaining ring, and the retaining ring may be bent over a base of the puck. | 05-05-2016 |
20160115325 | Anti-Corrosion and/or Passivation Compositions for Metal Containing Subtrates and Methods for Making, Enhancing, and Applying the Same - A corrosion inhibition composition is disclosed comprising a cerium, a tungstate, a molybdate and silicate compounds. A corrosion inhibition composition is provided comprising a zinc oxide, a zinc hydroxide benzoate, a sodium benzoate, a molybdate and a silicate compound. A corrosion inhibition composition is provided comprising a zinc oxide, a zinc phosphate, a calcium silicate, an aluminum phosphate, a zinc calcium strontium aluminum orthophosphate silicate hydrate, a molybdate, and silicate compounds. | 04-28-2016 |
20160109114 | INDUCTIVE HEATING ENERGY RECOVERY SYSTEM - An energy recovery system is provided. The energy recovery system may comprise an inductive heating coil configured to have a cooling fluid flow through the inductive heating coil and a heat exchanger fluidly coupled to the inductive heating coil and configured to produce a steam source. The steam source drives a pump. | 04-21-2016 |
20160101857 | SLIDE BUSHING SUPPORTED AIRCRAFT CARGO LOADING SYSTEMS AND METHODS - A cargo management system is provided comprising a slide bushing supported cargo shuttle, an actuator coupled to a bushing slide plate; an aft shuttle drive belt coupled to the slide bushing supported cargo shuttle; and a forward shuttle drive belt coupled to the slide bushing supported cargo shuttle. Also disclosed is a slide bushing supported cargo shuttle comprising a housing, a bushing slide plate extendable from the housing via an actuator and a top surface of the bushing supported cargo shuttle and a power drive unit coupled to the top surface. | 04-14-2016 |
20160059956 | DIFFERENTIAL EMERGENCY/PARK ELECTRIC BRAKE SYSTEM - A system, apparatus and method provide emergency differential braking for effecting braked steering of an aircraft. A brake input device is provided that not only allows for emergency and parking brake functions, but also enables differential braking. The brake input device (e.g., a parking and/or emergency brake lever, pedal, handle, etc.) can be used in a brake system including a brake system control unit (BSCU), one or more electro-mechanical actuator controllers (EMACs) and a brake assembly including one or more electrical actuators. Each EMAC is electrically coupled to one or more of the actuators so as to provide electrical power for driving the actuators. Each EMAC is also communicatively coupled to the BSCU so as to receive braking data therefrom. In an emergency, the input device sends braking signals directly to the brake actuators. | 03-03-2016 |
20160052622 | LANDING GEAR ELECTRICAL SWIVEL - An electrical swivel system may have a movable swivel member adapted to connect to a landing gear and a fixed swivel member adapted to connect to an airframe. Each may have an interface apparatus whereby electrical signals may be conducted between components of the movable swivel member and the fixed swivel member. In this manner, electrical signals may be conveyed across a mechanically movable joint. | 02-25-2016 |
20160052502 | AIRCRAFT BRAKE SYSTEM TESTING METHODS - Methods for testing the operation of an aircraft braking system utilize the steps of applying a predetermined electrical energy level to an electromechanical actuator attached to a brake assembly, followed by discontinuing electrical energy to the electromechanical actuator. In some test methods, an actuation level of the electromechanical actuator is determined and used to evaluate braking performance. In other tests, a voltage generated by an electric motor in an actuator is measured and used to evaluate braking performance. | 02-25-2016 |
20160041058 | SYSTEM AND METHOD TO ADJUST A FORCE ZERO REFERENCE - A system and method of adjusting a zero reference may comprise retracting ram of an actuator coupled to a load cell from a first position to a second position. The system and method may comprise reporting a measurement by a load cell, in response to the actuator being in a second position. The system and method may comprise calculating a force being measured by t the load cell. The system and method may comprise creating a zero reference offset value based on the calculation, in response to the force calculation resulting in a non-zero force calculation. The system and method may comprise adjusting a zero reference value of the load cell by the zero reference offset value. | 02-11-2016 |
20160039396 | INDEPENDENT BRAKE CONTROL OF A COMMON AIRCRAFT GEAR - A brake control system for a landing gear of an aircraft is provided. The system includes a first control channel for providing brake control signals to one or more brakes on the landing gear, and a second control channel for providing brake control signals to another one or more brakes on the landing gear. At least one of the first control channel and the second control channel is configured to act as an executive in monitoring braking efforts applied by the one or more brakes as compared to braking efforts applied by the another one or more brake, and to cause the braking efforts of at least one of the one or more brakes or the another one or more brakes to be modified in an effort to equalize the braking efforts. | 02-11-2016 |
20160027576 | SYSTEM AND METHOD FOR INCREASING COUPLING OF AN AXLE ROTARY TRANSFORMER - Described herein is a system and method to enable a wireless power transmission link system. The wireless power transmission link system may comprise an axle and an optional telemetry unit interior to the axle. The wireless power transmission link system may comprise a first cup located interior to the telemetry unit and/or the axle. The first cup may comprise a first channel for housing a first wound coil. The wireless power transmission link system may comprise a second cup separated by an air gap from the first cup. The second cup may comprise a second channel for housing a second wound coil. The first wound coil and the second wound coil may form a portion of an inductively coupled, resonant, air-core transformer. The first cup and/or the second cup may comprise ferromagnetic material properties. | 01-28-2016 |
20150358522 | Stabilization Of Gyro Drift Compensation For Image Capture Device - An image capture system comprises an image capture device driven by a motor to a desired angle. A gyro senses a rate and a system senses an angle of the image capture device relative to a surface. A control removes a gyro bias error estimated by the system in real time for correcting a position of the image capture device. | 12-10-2015 |
20150354644 | INTERNAL PARK BRAKE SYSTEM, APPARATUS, AND METHOD - A park brake system for an electric motor actuator is provided. The system may comprise a micro-motor, and one or more gears. The system may be configured to exert a radial force on a shaft of the electric motor actuator to lock the actuator. Moreover, in various embodiments, the system may be bi-stable. | 12-10-2015 |
20150345993 | SENSOR WIRE COUNT REDUCTION SYSTEM - A sensor wire count reduction system having various features is disclosed. Signals from multiple sensors may be combined together to reduce the number of wires implemented to convey the signals to a remote location. Multiple binary sensor outputs may be represented on a single wire as a multi-level signal, and may be decoded at a remote location. | 12-03-2015 |
20150345576 | BELT PARK BRAKE AND METHODS - Park brake systems comprising a motor shaft coupled to a brake drum, wherein the brake drum comprises a first groove and a second groove, wherein the brake drum is mounted to the motor shaft so as to rotate with the motor shaft, a first belt at least partially disposed in the first groove and about a first pivot linkage, a second belt at least partially disposed in the second groove and about a second pivot linkage, a first actuator piston coupled to an actuator and the first pivot linkage, a second actuator piston coupled to the actuator and the second pivot linkage, and a pivot base coupled to the first pivot linkage and the second pivot linkage are disclosed. Methods are also disclosed. | 12-03-2015 |
20150344131 | TWO-STAGE SECONDARY PISTON FOR LANDING GEAR - A shock strut is disclosed. The shock strut may have multiple pistons and multiple chambers. In this manner, the shock strut may compress different lengths for different applied forces at different points during its stroke. | 12-03-2015 |
20150344130 | VOICE COIL LINEAR ACTIVATED PARK BRAKE - A park brake systems and methods are disclosed. According to various embodiments, park brake systems comprising a tapered motor shaft having a first diameter and a second diameter, the second diameter being greater than the first diameter, a voice coil disposed at least partially around a circumference of a bobbin, a first one-way clutch housed at least partially within the bobbin, the first one-way clutch disposed coaxial to the tapered motor shaft, and an annular magnet disposed coaxial to the tapered motor shaft and proximal to the first one-way clutch, wherein, in response to a first voltage applied to the voice coil, the first one-way clutch translates axially in a first direction with respect to the tapered motor shaft and engages with the second diameter are disclosed. | 12-03-2015 |
20150344129 | AUTOBRAKING SYSTEM WITH COURSE TRAJECTORY ADJUSTMENT - Methods and systems are provided for improved autobraking systems for aircraft. Such systems and methods include a pedal balance controller configured to receive one of a yaw angle, a yaw speed, and a wheel speed, and an autobrake pedal executive module configured to send an autobrake left pedal command and an autobrake right pedal command to a pedal executive module, wherein the pedal executive module is configured to execute a pedal command. These systems and methods may assist a pilot in maintaining a desired course during autobraking. | 12-03-2015 |
20150344017 | AIRCRAFT BRAKE SYSTEM TESTING METHODS - Methods for testing the operation of an aircraft braking system utilize the steps of applying a predetermined electrical energy level to an electromechanical actuator attached to a brake assembly, followed by discontinuing electrical energy to the electromechanical actuator. In some test methods, an actuation level of the electromechanical actuator is determined and used to evaluate braking performance. In other tests, a voltage generated by an electric motor in an actuator is measured and used to evaluate braking performance. | 12-03-2015 |
20150343885 | BONDING STRUCTURE WITH CTE GRADIENT FOR MOUNTING AN OPTICAL ELEMENT IN A FRAME - An athermalized window assembly intended for mounting in or on the exterior of a vehicle and associated method, the assembly comprising a window arranged with one or more mounting members in an opening in a plate. The coefficient of thermal expansion of the mounting members is between a coefficient of thermal expansion associated with the window and a coefficient of thermal expansion associated with the plate. The mounting members may comprise a plurality of skirts that form a coefficient of thermal expansion gradient between the window and the plate. | 12-03-2015 |
20150337468 | SYSTEM AND METHOD FOR TRANSPORT OF FIBERS TO/FROM A CIRCULAR NEEDLE-PUNCHING LOOM - A circular needle loom comprises a bed plate for receiving a transport layer. Engagement members may be disposed proximate to the bed plate, such that the engagement members interface with a positional structure of the transport layer that is used to position and rotate the transport layer around the bed plate. The engagement members may be configured to rotate the transport layer around the bed plate until a predetermined number of fibers and/or layers are deposited on the transport layer and/or bed plate in order to create a needled preform. | 11-26-2015 |
20150330136 | WINDOW ASSEMBLIES - A flexure ring for a window assembly includes a continuous annular portion and a segmented portion. The continuous annular portion defines a ring axis. The segmented portion defines a plurality of circumferential segments. The continuous annular portion is connected to each circumferential segment by a respective neck. Each neck extends from the continuous annular portion to a respective one of the circumferential segments. The continuous annular portion, the segmented portion and the necks are configured to circumscribe a window pane. | 11-19-2015 |
20150325866 | GAS SEPARATION FROM FUEL CELL COOLING WATER - A fuel cell has an anode and a cathode separated by a membrane. A source of fuel is provided for passing a fuel across the anode. A source of oxygen containing gas is provided for passing oxygen across a cathode. A cooling water circuit is associated with an accumulator and for supplying cooling water to cool the cathode, and to return the cooling water from the cathode back to the accumulator. A system removes entrained gases from the water returned to the accumulator and returns the removed gases to the cathode. A vehicle with such a fuel cell is also disclosed. | 11-12-2015 |
20150325008 | SYSTEMS AND METHODS FOR ENHANCING DISPLAYED IMAGES - A method of enhancing an image includes displaying an image, receiving eye-tracking information associated with the displayed image, and identifying a region of interest in the displayed image using the eye tracking information. The method further includes enhancing the region of interest and displaying the enhanced region of interest adjacent to or superimposed upon an unenhanced region of the displayed image. | 11-12-2015 |
20150316929 | Runway Traction Estimation and Reporting System - A runway traction estimation and reporting method and computer readable medium is provided. Upon detection of a landing event, a runway traction estimation and reporting method provides for various measurements and calculations to estimate the traction of the runway and create a traction map of the runway. A computer readable medium may contain instructions for a runway traction estimation and reporting processor directing the processor to perform various measurements and calculations to estimate the traction of the runway. The processor may communicate with a ground station or with other aircraft to produce collaborative results. | 11-05-2015 |
20150316206 | COMPOSITE TUBE ASSEMBLIES AND METHODS - Composite tubes comprising a compression sleeve coupled to an inner surface of a composite tube, a carbon extrusion member disposed within the composite tube, and an end fitting comprising a locking feature, wherein the end fitting is coupled to an inner surface of the compression sleeve and the locking feature is configured to engage the carbon extrusion member are disclosed. Methods comprising coupling a compression sleeve to an inner surface of a distal end of a composite tube, placing a carbon extrusion member inside the compression sleeve and the composite tube, and disposing an end fitting on the distal end of the composite tube, wherein the end fitting comprises a locking feature configured to interact with the carbon extrusion member are also disclosed. | 11-05-2015 |
20150309223 | MASKED PIXEL ARRAYS - An optical sensor includes an array of pixels configured to convert photons into electrons for forming an image or to measure spectral content without forming an image. A filter assembly is operatively associated with the array of pixels for passing predetermined bandwidths of photons to the array of pixels. A mask is operatively associated with the array of pixels and the filter assembly. The mask includes a plurality of apertures each for limiting photons passing through the filter assembly to a respective pixel in the array of pixels. | 10-29-2015 |
20150308758 | SYSTEMS AND METHODS FOR HEAT SHIELD ASSEMBLIES - Systems and methods disclosed herein may be useful for aircraft heat shield assemblies. In this regard, a heat shield assembly is provided comprising a heat shield having an aperture, the aperture comprising an end portion and an insertion portion, the insertion portion having a width larger than the end portion, a spacer comprising an upper portion, an undermount flange and a gap between the upper portion and the undermount flange, wherein a surface of the gap is engaged with the heat shield, and wherein the undermount flange has a width less than the insertion portion of the aperture and greater than the width of the end portion. | 10-29-2015 |
20150308712 | HIGH CAPACITY WATER HEATER - One embodiment includes a high capacity water heater assembly. The assembly includes a vessel with an inlet and an outlet, with water delivered to the vessel through the inlet. Also included is a heating element attached to the vessel for heating the water delivered to the vessel, an active mixing valve in fluid connection with the outlet of the vessel, and a water temperature sensor attached to the vessel to communicate data used for powering on and off the heating element. | 10-29-2015 |
20150308526 | TORQUE BAR AND METHODS FOR MAKING - A torque bar manufactured by an additive manufacturing process is provided. The torque bar may include a torque bar body made of more than one metallic material. The torque bar may also include a geometry that comprises one or more voids and one or more webs, as well as a varied geometry in the direction of a longitudinal axis. Torque bars of the present disclosure can exhibit improved characteristics, such as improved vibration damping, tuned stiffness, and tuned bending resistance in order to enhance dynamic stability. | 10-29-2015 |
20150307284 | BALL TRANSFER UNIT SUPPORT SYSTEMS - Systems and methods are disclosed herein for ball transfer unit supports. A ball transfer unit support may include a top ring, an upper portion adjacent to the top ring, a lower portion, and a shoulder located between the upper portion and the lower portion. The shoulder may be configured to support a ball transfer unit. The top ring may be in the shape of a truncated circle, and the top ring may snap into an aperture in a top skin of a ball panel. The top ring may include a retaining lip which snaps below the top skin. The truncated circle shape of the top ring may provide anti-rotation between the ball transfer unit support and the ball panel. The ball transfer unit support may transfer load on the ball transfer unit to a bottom skin of the ball panel. | 10-29-2015 |
20150298798 | BOGIE BEAM ARTICULATION MECHANISM - A bogie articulation mechanism is provided comprising, for example, a first torque link and a second torque link coupled for rotation about a pivot joint, the first torque link coupled to a bogie beam, a pitch trimmer having a first terminus and a second terminus, the first terminus coupled to the pivot joint, a bell crank having a pivot point, a first coupling point and a second coupling point, first coupling point couple to the second terminus of the pitch trimmer, and a reaction link coupled to the second coupling point of the bell crank. | 10-22-2015 |
20150293874 | DATA TRANSFER INTERFACE - A data transfer interface includes a circuit card assembly (CCA) including a mounting surface, a data transfer port mounted to the mounting surface of CCA, and a support that is through-hole mounted to the CCA and is engaged to the data transfer port to reinforce the data transfer port from against detaching from the CCA. | 10-15-2015 |
20150292911 | STATE SENSOR SYSTEMS AND METHODS - Sensor systems comprising a magnetic circuit comprising a coil, a magnet, at least one of a ferromagnetic armature plate and a conductive armature plate, wherein the at least one of the ferromagnetic armature plate and the conductive armature plate is configured to move axially in response to at least one of the magnet and the coil, and a controller configured to apply a known first voltage across the coil and monitor a current through the coil are provided. Methods are also provided. | 10-15-2015 |
20150289424 | Grid Topography For Patterned Semiconductor Coating That Minimizes Optical Scatter And Obscuration - A surveillance device includes an electronic component and a protective surface outwardly of the electronic component. A generally transparent substrate is formed from a first material. Spaced portions of an electrically conductive coating are formed within channels in the substrate. The electrically conductive material is a semiconductor material. A method is also disclosed. | 10-08-2015 |
20150285346 | ACTUATOR SYSTEM AND METHOD - Systems and methods disclosed herein may be useful for use in a ballscrew assembly. In this regard, a ballscrew assembly is provided comprising a ballscrew having a ballscrew stop, a ballnut having a ballnut stop, wherein contact between the ballnut stop and the ballscrew stop impede rotation of the ballscrew relative to the ballnut. The ballnut stop may comprise an axial mating surface and the ballscrew stop may comprise an axial mating surface. Additionally, the ballnut may comprise threads axially spaced a first distance apart and the ballnut stop comprises a surface having length equal to the first distance. | 10-08-2015 |
20150284957 | STRUTS AND METHODS UTILIZING A COMPRESSION COLLAR - Composite tube assemblies comprising a composite tube comprising a distal end having a first conical section and a second conical section, wherein a distal end of the first conical section is in contact with a proximal end of the second conical section having the same outer diameter as the distal end of the first conical section, wherein a proximal end of the first conical section and a distal end of the second conical section have a smaller outer diameter than the distal end of the first conical section, a locking ring disposed around the first conical section, an end fitting disposed around the second conical section, wherein the end fitting is coupled to the locking ring, and a retaining ring circumferentially disposed around the locking ring are disclosed. | 10-08-2015 |
20150284108 | NOSE WHEEL TIRE PRESSURE SENSING SYSTEM AND APPARATUS - Landing gear tire pressure sensing systems, methods and apparatuses are provided. In various embodiments, a tire pressure sensing system may be mounting to a landing gear. The system may comprise a rotating portion and a stationary portion. The rotating portion and stationary portion may be in electronic communication. The stationary portion may be configured to communicate an indication of tire pressure to a control unit. | 10-08-2015 |
20150277135 | MULTIPLE COLLIMATOR UNIT - A collimator unit includes an on-axis collimator tube fixedly attached to at least two off-axis collimator tubes. The off-axis collimator tubes are angled relative to the on-axis collimator tube. Each collimator tube can include a lens, a light source, and a target placed at the lens' focal point. The collimator tubes can be positioned within a housing such that the on-axis collimator tube is coaxial and centered with respect to the housing. | 10-01-2015 |
20150274984 | Anti-Corrosion and/or Passivation Compositions for Metal Containing Subtrates and Methods for Making, Enhancing, and Applying the Same - A corrosion inhibition composition is disclosed comprising a cerium, a silicate compound, and a molybdate compound. Moreover, a corrosion inhibition composition is disclosed comprising a cerium, a silicate compound, a tungstate and a molybdate compound. | 10-01-2015 |
20150274283 | Shrinking System for Landing Gear - Landing gear actuator systems and methods are disclosed. A landing gear actuator system may have an actuator body, an operating apparatus, a gas pressure adjustment apparatus, and a hydraulic fluid adjustment apparatus. The gas pressure adjustment apparatus may adjust at least one gas pressure in response to the operating apparatus. The hydraulic fluid adjustment apparatus may adjust at least one hydraulic fluid volume in response to the operating apparatus. The gas pressure and the hydraulic fluid volume may adjusted inversely. An isolation valve may be installed between the gas pressure adjustment apparatus and a strut gas chamber of a landing gear. In this manner, a landing gear strut may be shrunk without inducing high pressure in the strut, and stowed for flight, and a landing gear strut may be unshrunk and isolated by the valve to protect the actuator from high pressure and reaction forces during landing. | 10-01-2015 |
20150273811 | METHOD TO TRANSPORT AND LAY DOWN DRY FIBER BUNDLES - A positive transport of carbon fiber bundles, in ribbon form, with in-line manipulation of the fiber bundles (spreading or spreading and volumization with manipulators) during fiber bundle transport to points of fiber bundle deliveries into the circular loom bed plate turntable is described herein. The automated placements of these deliveries of the fiber bundle/tow at selected orientations in the area correspond to the feeding zone of an improved circular loom bed plate turntable. | 10-01-2015 |
20150270672 | Landing Gear Electrical Swivel - An electrical swivel system may have a movable swivel member adapted to connect to a landing gear and a fixed swivel member adapted to connect to an airframe. Each may have an interface apparatus whereby electrical signals may be conducted between components of the movable swivel member and the fixed swivel member. In this manner, electrical signals may be conveyed across a mechanically movable joint. | 09-24-2015 |
20150267893 | SYSTEMS AND METHODS FOR ANTI-COLLISION LIGHTS - Systems and methods are disclosed herein for anti-collision lights. An anti-collision light (“ACL”) may include a light source, a primary reflector, and a secondary reflector. The primary reflector may have a concave side facing the light source and the secondary reflector. The secondary reflector may include a reflective cone and a reflective base. The ACL may be configured to efficiently distribute light from the light source according to Federal Aviation Administration ACL requirements. | 09-24-2015 |
20150267812 | PISTON HOUSING SYSTEM AND APPARATUS - A piston housing manufactured by an additive manufacturing process is provided. The piston housing may comprise a plurality of chambers. The chambers may be in fluid communication with one another via non-linear fluid passageways. The non-linear fluid passageways may be defined in structural members configured to stiffen the piston housing. | 09-24-2015 |
20150267732 | COLD SPRAY NODES, STUDS, STUD ASSEMBLIES, AND METHODS OF MANUFACTURE - Studs, nodes, and study assembly systems formed by various methods are disclosed. Various disclosed methods include cold spraying a powder onto a substrate to form a node on the substrate and drilling a hole only into the node. Various disclosed methods include cold spraying a powder onto a substrate to form a node and machining the node to form a stud. | 09-24-2015 |
20150267329 | SYSTEMS AND METHODS FOR CALCULATED TOW FIBER ANGLE - An optimized fiber tow orientation, to achieve substantially uniform fiber tow volume across the web, e.g., from inner diameter (ID) to the outer diameter (OD) of a disc shaped preform, without substantially varying the angles of the plurality of fiber tows radially or circumferentially is described herein. Utilizing the systems and processes described herein, a net shape preform may be created. A substantially continuous fiber tow may be used to form the preform. The fiber tow angle of each fiber tow may vary, from more radial, such as at the ID, to more tangential, such as at the OD, as the radius increases, such that there is substantially uniform thickness and substantially uniform areal weight from ID to OD of the preform or layer. | 09-24-2015 |
20150251855 | COMPLIANT TIRE - A powered drive unit system of an aircraft is disclosed herein. The system may include a support structure, a plurality of motor driven tires configured to present a horizontal motive force on an object, and an axle of a tire. The axle of the tire may be retained by the support structure. The object may move relative to the static support structure. The location of an axle of the tire may be rigidly fixed in position relative to the support structure housing the axle. Normal force on the object by the tire may be created through tire compliance. The axle of the tire may be retained by the support structure. The axis of rotation of the axle may be in a substantially static three dimensional plane relative to the support structure. | 09-10-2015 |
20150243113 | SYSTEMS AND METHODS FOR BUILT IN TEST EQUIPMENT FOR A BRAKE CONTROL SYSTEM - A method is disclosed that comprises severing an I/O channel between an EMAC and an aircraft component; sending a test signal to the brake system controller; receiving, from the brake system controller, a feedback signal to the test signal; and determining an appropriateness of the feedback signal. | 08-27-2015 |
20150231936 | TIRE PRESSURE INDICATOR - System and methods for indicating a tire pressure condition are disclosed. Some systems and methods include receiving, by a control unit comprising a processor and a tangible, non-transitory memory, a tire pressure data, determining, by the control unit, a relationship of the tire pressure data to a predetermined tire pressure, and causing, by the control unit, an output device to display a value in accordance with the relationship, wherein the output device is externally located on an aircraft. | 08-20-2015 |
20150226551 | PASSIVE ALTIMETER - A passive altimeter includes an imaging device, a groundspeed system, an image processing device operatively connected to receive an indication of groundspeed from the groundspeed system and to receive at least a first image from the imaging device taken at a first position and a second image from the imaging device taken at a second position spaced apart from the first position. The image processing device is configured to compare the first image and the second image to determine an altitude above ground using the indication of groundspeed from the groundspeed system. | 08-13-2015 |
20150224974 | BRAKE COOLING ESTIMATION METHODS AND SYSTEMS - Systems and methods for estimating the cooling time of a brake assembly are disclosed. Various systems and methods may include receiving a temperature of a brake assembly, determining a peak brake assembly temperature, determining a temperature decay coefficient (“α”) of the brake assembly, calculating an estimated total time to cool the brake assembly to a predetermined temperature based on the peak brake assembly temperature and an ambient temperature data, and adjusting the estimated total time to cool the brake assembly to the predetermined temperature based on an amount of time elapsed after the receiving the temperature of the brake assembly. | 08-13-2015 |
20150217747 | SYSTEM AND METHOD OF DETERMINING ACCUMULATOR STATUS - A method of detecting an accumulator failure is provided. The method may comprise measuring a first pressure on a gas-side of an accumulator, measuring a second pressure on a fluid-side of the accumulator, finding a difference between the first pressure and the second pressure, and comparing the difference to a predetermined threshold. A system for detecting an accumulator failure is also provided. The system may comprise a non-transitory memory communicating with a processor, the non-transitory memory having instructions stored thereon that, in response to execution by the processor, cause the processor to perform operations. The operations may include receiving a first pressure measurement, receiving a second pressure measurement, determining a difference between the first pressure measurement and the second pressure measurement, and detecting the accumulator failure based on the difference. | 08-06-2015 |
20150215529 | RANDOM IMAGING - An image processing system comprises a filter associated with a sensor array, which is operable to capture an image. The filter is provided to separate a plurality of distinct qualities of light from the scene to be captured. The filter has filter portions associated with the plurality of distinct qualities of light which are spatially pseudo-randomly ordered relative to each other. The image processing system also comprises an image reconstruction algorithm specifically designed to operate with the filter. | 07-30-2015 |
20150203192 | SYSTEM AND METHOD FOR SPRING ASSISTED LANDING GEAR OPERATION - A landing gear actuation system comprising a motive force system, such as an actuator and/or a piston to move the landing gear from a first position to a second position is disclosed herein. The landing gear actuation system may also comprise a spring system configured to counterbalance the weight of the landing gear and/or assist the motive force system in moving the landing gear from a first position to a second position. The landing gear actuation system may further comprise a camming mechanism to distribute the direction and/or location of the force applied to the landing gear. | 07-23-2015 |
20150156463 | Long-Range Image Reconstruction Using Measured Atmospheric Characterization - A method corrects a captured image and includes the steps of determining an effect of atmosphere and a distance from an image capture device which is spaced relatively far from an area of interest. The method utilizes a transmission and reception device to identify the effect on a transmitted and reflected signal due to the atmosphere and distance. An image of the area of interest is captured. The image is corrected based upon the effect of the distance and atmosphere on the transmitted and reflected signal. An apparatus programmed to perform the method is also disclosed. An apparatus for capturing an image from a distance is also disclosed. | 06-04-2015 |
20150151851 | Rescue Hoist Digital Video Recording System - Embodiments of the disclosure include a rescue hoist digital video recording system for an aircraft includes one or more sensors disposed on the aircraft, a hoist configured to raise and lower a rescue crew/equipment from the aircraft, and one or more cameras disposed on the aircraft. The rescue hoist digital video recording system also includes a controller configured to receive information from the one or more sensors and the hoist, wherein the controller operates the one or more cameras based on the received information. | 06-04-2015 |
20150142388 | AIRCRAFT TIRE AND RUNWAY INTERFACE FRICTION MAP CONSOLIDATION - In various embodiments, a method associating received coefficient of friction data to runway friction estimation map elements. Also, the method may include aggregating the received determined coefficient of friction data into a friction estimation map. | 05-21-2015 |
20150142217 | BRAKE CONTROL INITIATION USING TIRE RUNWAY FRICTION MAP DATA - In various embodiments, a method for utilizing a determined coefficient of friction along a portion of a runway is disclosed. The method may include receiving, by a brake control unit, friction estimation map data for a specific runway. The method may include setting, by the brake control unit, a condition of the braking control algorithm based on the received friction estimation map data. The method may include initiating, by the brake control unit, a brake control system to slow a wheel of an aircraft based on the braking control algorithm. | 05-21-2015 |
20150134197 | TIRE INFLATE/DEFLATE INDICATION METHOD AND SYSTEM - Systems and methods for indicating conditions for the appropriate inflation and/or deflation of tires are disclosed. Some systems and methods include measuring a variable affecting the internal gas temperature of a tire, calculating by the processor an estimated internal gas temperature of a tire, and determining whether a tire is appropriate to inflate and/or deflate. | 05-14-2015 |
20150132573 | SYSTEMS AND METHODS FOR CONTROLLING CARBON TOW WIDTH - A technique allowing a portion of carbon fiber tow to maintain a rectangular cross sectional shape or to maintain an imparted desired shape, such as a wider shape with a rectangular cross-sectional profile, through a textile loom is disclosed herein. | 05-14-2015 |
20150129381 | CAM-OPERATED BI-DIRECTIONAL SHOCK ABSORBER DAMPER - The present disclosure relates to cam operated shock absorber damper systems for use with landing gear. The cam operated shock absorber damper systems may comprise a cylinder and a piston mounted to slide telescopically in the cylinder and a snubber ring comprising rebounding orifices and compression orifices. | 05-14-2015 |
20150129369 | KEYED BRAKE DISK ASSEMBLY - Friction disks, such as rotors and stators, including floating cores are disclosed. The friction disks may include a carrier plate and a wear liner coupled to each side of the core. The floating core may be located between the wear liners. The floating core may include a key which is located within a key notch in the carrier plate. The key may prevent the floating core from rotating relative to the carrier plate. | 05-14-2015 |
20150129368 | SYSTEM AND METHOD FOR MAXIMUM BRAKING - Systems and methods for reducing the speed of an aircraft are disclosed herein. An electronic brake control system may include a first braked wheel of a landing gear system, a brake pedal electronically coupled to the first braked wheel, and a first actuator. The first actuator may be configured to deliver a scalable clamping force on the first braked wheel via a brake stack. The first actuator may be configured to deliver an emergency maximum clamping force on the first braked wheel in response to the electronic brake control unit being in an emergency condition braking mode and a signal being received proportional to the brake pedal displacement. The emergency maximum clamping force results in the first actuator being driven in an overdriven state. | 05-14-2015 |
20150128691 | Tire Pressure Observation After Detecting Abnormal Pressure Condition - A tire pressure observation method and computer readable medium is provided. Upon detection of an abnormal pressure condition, a tire pressure observation method provides for various maintenance actions. A computer readable medium may contain instructions for a tire pressure observation controller directing the controller to present messages at different stages of the maintenance actions to assist maintenance staff in properly performing the maintenance actions, for example, observing the tire pressure. | 05-14-2015 |
20150128689 | BRAKE MANUFACTURER IDENTIFICATION SYSTEM AND METHOD - Systems and methods for identification of brake suppliers and vehicle models based on electrical resistance of the brake control unit are disclosed herein. Based on calculated values, both the brake supplier and model of vehicle can be determined. | 05-14-2015 |
20150127233 | ELECTROMECHANICAL ACTUATOR STRAIN GAUGE TEMPERATURE COMPENSATION DEVICE - The EMA may comprise an EMA housing, a strain gauge coupled to the EMA housing, the strain gauge comprising a Wheatstone bridge, the Wheatstone bridge comprising a first group of resistors coupled in parallel with a second group of resistors, a controller coupled to the strain gauge, a variable resistance resistor coupled to the Wheatstone bridge, the variable resistance resistor configured to derive a temperature of the EMA housing based upon a temperature of the variable resistance resistor and configured to provide feedback to the controller, the controller adjusting a force applied by the EMA based upon the temperature of the EMA housing. | 05-07-2015 |
20150127195 | SYSTEM AND METHOD FOR INDEPENDENT BRAKING SYSTEM ENABLEMENT - Described herein is a system and method to enable braking system operation independent of conventional aircraft signals, such as those tied to the hibernation commands. Stated another way, the present disclosure relates to the enablement of a braking system in response to an initiation signal. In this way, the crew has the ability to force the braking system out of a hibernation mode into an “emergency type” braking mode if desired. The concepts described herein may be applicable to an electric braking system and to a hydraulic braking system. | 05-07-2015 |
20150122593 | HYBRID BRAKING SYSTEM AND APPARATUS - The present disclosure relates to hybrid brake systems, The hybrid brake systems may comprise one or more electromechanical actuators and one or more hydraulic adjusters, The hybrid brake system may further comprise a housing configured to store and/or conduct fluid. The hybrid brake system may also further comprise a fluid reservoir. The hybrid brake system may be redundant, | 05-07-2015 |
20150122061 | ELECTROMECHANICAL ACTUATOR DISTAL POSITION STOPPING ASSEMBLY - An electromechanical actuator (EMA) is disclosed. The EMA may comprise an EMA housing having a distal stop that extends radially inward towards a longitudinal axis of the EMA housing, a hail nut extending axially within the EMA housing, and/or a ball screw extending axially within the ball nut, The ball nut may translate axially in a distal direction in response to a rotation by the ball screw, and/or the ball nut may be halted in the axially distal translation in response to contact with the distal stop. The distal stop may be coupled to the EMA. housing. The distal stop may comprise a continuous annular structure. The EMA may further comprise a seal located radially inward of a portion of the distal stop, which may be in contact with said portion and the ball nut and adapted to prevent debris from entering the EMA. | 05-07-2015 |
20150115779 | LOAD CELL ON EMA HOUSING WITH TRIM RESISTORS - A instrumented housing for an electric motor actuator is provided. The instrumented housing may have a ribbon gage coupled to a housing of an electrical motor actuator. The ribbon gage may have one or more strain gages. The strain gages may measure the tension on the housing when the electric motor actuator exerts a load. A cover may extend over at least a portion of the housing and ribbon gage. | 04-30-2015 |
20150115778 | INTEGRAL ACTUATOR DESIGN - An integrated actuator drive unit (ADU) assembly for an electric motor actuator is disclosed. The integrated ADU assembly may comprise at least one of an integrally formed ring gear, an integrally formed thrust bearing and integrally formed load cell. The integrated ADU assembly may comprise a portion of an electromechanical actuator. The electromechanical actuator may be utilized for aircraft braking systems. | 04-30-2015 |
20150114945 | ELECTRICAL INTERCONNECTS FOR ICE PROTECTION SYSTEMS - A rotary blade includes a blade tip assembly with a first bus bar segment and a main blade assembly with second bus bar segment. The first bus bar segment is connected to the blade tip assembly and the second bus bar segment is connected to the main blade assembly. The blade tip assembly is connected to the main blade assembly such that the first and second bus bar segments are longitudinally offset from one another. A low-profile interconnect spans the first and second bus bar segments for resistively generating less heat than the bus bar segments for a predetermined current flow. | 04-30-2015 |
20150114150 | ELECTROMECHANICAL ACTUATOR PROXIMAL POSITION STOPPING ASSEMBLY - An electromechanical actuator (EMA) is disclosed. The EMA may comprise an EMA housing, a ball nut extending axially within the EMA housing, a ball screw extending axially within the ball nut, and/or an actuator drive unit (ADU) housing extending axially within the ball screw, the ADU housing having a proximal stop that extends radially outward of the ADU housing. The ball nut may be configured to translate axially in a proximal direction in response to a rotation by the ball screw, and the ball nut may be configured to be halted in the axially proximal translation in response to contact with the proximal stop. The proximal stop may be coupled to the ADU housing. The proximal stop may comprise a continuous annular structure. | 04-30-2015 |
20150109476 | ROW BY ROW ADJUSTABLE FOCAL PLANE ARRAY FOR HYPERSPECTRAL IMAGERS - An imaging device and method of imaging an object is disclosed. The device includes a two-dimensional focal plane including a plurality of rows of pixels. The pixel is configured to measure an intensity of light directed onto the pixel using a gain parameter. A gain adjuster adjusts the gain parameter for a selected row of pixels of the focal plane array independently of a gain parameter of another row of pixels. | 04-23-2015 |
20150102163 | SHRINK STRUT LANDING GEAR SYSTEM, METHOD, AND APPARATUS - The landing gear systems, methods and apparatuses disclosed herein may comprise a shrink pump and a shrink valve that are capable of shrinking a landing gear by up to 40% of its available stroke, or more depending on the air spring configuration. The shrink pump may be configured to pump fluid (e.g., a hydraulic fluid) between an oil chamber, where hydraulic fluid is likely present and a shrink chamber to shrink the landing gear. Moreover, the shrink pump and shrink valve may be part of a strut shrink system. | 04-16-2015 |
20150101480 | SHRINK STRUT LANDING GEAR SYSTEM, METHOD, AND APPARATUS - The landing gear systems, methods and apparatuses disclosed herein may comprise a shrink pump and an unshrink valve that are capable of shrinking a landing gear shock strut up to about 40% of its available stroke. The shrink pump may be configured to pump fluid (e.g., a hydraulic fluid) between an oil chamber, where hydraulic fluid is likely present and a shrink chamber to shrink the landing gear. Moreover, the shrink pump and unshrink valve may be part of a strut shrink system. | 04-16-2015 |
20150100716 | SYSTEMS AND METHODS OF USING AN SPI CONTROLLER - A system for managing internal-computer system communications including a processor, an SPI controller, an interconnector, and an SPI cluster containing multiple SPI interfaces, with the SPI interfaces being connected to one or more devices in the computer system or environment. The SPI cluster includes SPI interfaces that can convert communications to/from a plurality of device's formats to serialized digital formats suitable for ingest and actuation for the SPI controllers. The interconnector may use a differentially, optically, galvanometrically, inductively coupled driven wire and to enable communications between the SPI cluster constituents and the SPI controller. The SPI controller manages communications to the SPI interfaces that act as coordinated intermediates for device control and communications, thus insulating the computer system's processor from the increased workload of managing all internal system communications. | 04-09-2015 |
20150097080 | ROCKING BOGIE MECHANISM - A rocking bogie mechanism may include an upper link, a lower link, a central link, a forward link, an articulation actuator, a trimmer, and a bell crank. The upper link may be coupled to a cylinder at a first joint. The lower link and trimmer may be coupled to the piston at second joint. The upper link, lower link, and central link may be coupled at a third joint. The articulation actuator may be coupled to the upper link at a fourth joint. The trimmer and bell crank may be coupled at a fifth joint. The central link and bell crank may be coupled at a sixth joint. The articulation actuator and bell crank may be coupled at a seventh joint. The central link and forward link may be coupled at an eighth joint. The forward link may be coupled to a bogie beam at a ninth joint. | 04-09-2015 |
20150075662 | DRAIN MASTS - A drain mast includes a first fairing body defining a first fairing wall and a first drain portion. A second fairing body defines a second fairing wall and a second drain portion. The first and second fairing bodies are joined together as a fairing with the first and second fairing walls as opposed exterior fairing walls, and with the first and second drain portions joined to form a drain passage through the fairing from a drain passage inlet to a drain passage outlet. | 03-19-2015 |
20150075309 | ECCENTRIC TOOL - An adjustment tool is disclosed herein. For example, an adjustment tool is provided comprising an input gear having gear teeth and an output gear having gear teeth, wherein the input gear and the output gear are in meshed engagement, an input shaft centrally coupled to the input gear, wherein the input gear is configured to rotate about the input shaft, and a housing supporting the input shaft for rotation and supporting a fastener, wherein a tooth of the output gear protrudes from the housing. | 03-19-2015 |
20150061375 | ENERGY HARVESTING SYSTEM FOR AN AIRCRAFT - An energy harvesting system for an aircraft includes an energy storage device, and an energy harvesting member electrically connected to the energy storage device and mechanically linked to the aircraft. The energy harvesting member is configured and disposed to generate an electrical energy output in response to one of a change in altitude of, or turbulence on, the aircraft. | 03-05-2015 |
20150056415 | METHOD FOR MANUFACTURING ULTRA LOW EXPANSION GLASS MIRROR SUBSTRATES - A method of manufacturing a mirror substrate that includes the steps of providing a polishable substrate surface layer formed from ultra low expansion (ULE) glass, depositing successive layers of powdered ULE glass onto the polishable substrate surface layer, and selectively lasing each successive layer of powdered ULE glass to produce successive fused layers of ULE glass joined to one another to form a mirror substrate having an optimized three-dimensional topology. A mirror substrate manufactured according to the prescribed method is also disclosed. | 02-26-2015 |
20150053664 | DIRECT WRITING BUS BARS FOR SCREEN PRINTED RESIN-BASED CONDUCTIVE INKS - A method for providing an electrical connection for conductive ink includes direct writing a bus bar onto areas of a desired electrical connection of the conductive ink. The conductive ink is screen printed onto a dielectric film to create a conductive circuit. An aircraft heated floor panel includes at least one floor panel of an aircraft. The one floor panel includes a conductive circuit having a conductive ink including a bus bar directly written onto areas of a desired electrical connection of the conductive ink. The conductive ink is screen printed onto a dielectric film to create a conductive circuit. | 02-26-2015 |
20150053662 | HEATING ELEMENTS FOR AIRCRAFT HEATED FLOOR PANELS - A method of forming a heating element includes depositing a conductive ink of silver particles in an epoxy resin on a dielectric film to create a conductive circuit, and heat curing the conductive circuit to achieve a resistivity of the heating element less than 1.68×10 | 02-26-2015 |
20150051003 | FLEXIBLE COUPLINGS FOR POWER TRANSMISSION DEVICES - A flexible coupling assembly includes a power transmitting body to carry a torsional load between opposed rotating members and a quill shaft for carrying an axial load extending through the cavity of the torsional body. The power transmitting body defines an axis, a longitudinally extending cavity, and a first and second flanged portions for coupling opposed rotating members. The quill shaft extends through the cavity of the power transmitting body, spanning the power transmitting body, and fixed to the first and second flanged portions for carrying the axial load across the power transmitting body. | 02-19-2015 |
20150041585 | BOGIE BEAM ANGLE SENSOR - A bogie beam sensor may include a bracket and a target arm pivotably coupled to the bracket. The bracket may be coupled to a bogie beam. A sensor may be coupled to the bracket, and a target may be coupled to the target arm. A drive link may be coupled to the target arm and a piston. In response to the bogie beam pivoting with respect to the piston, the drive link may cause the target arm to rotate with respect to the bogie beam. The sensor may detect movement of the target on the target arm, and an angular position of the bogie beam may be determined based on the position of the target. | 02-12-2015 |
20150041268 | AIRCRAFT SHOCK STRUT AND REBOUND DAMPING RING - A shock strut for an aircraft landing gear is disclosed. The shock strut may include a piston with a piston inner surface and a piston outer surface. A telescoping component may be coaxially aligned and slidably engagable with the piston. At least one of the piston and the telescoping component may be a titanium material. A groove defined by an upper lip and a lower lip may be coupled to at least one of the piston or the telescoping component. A piston ring may be in direct contact with the titanium material. The piston ring may be non-metallic and provide sliding engagement with the titanium material to seal a radial space between the piston and the telescoping component. The piston ring may be at least partially held within the groove, and the groove may limit axial movement of the piston ring. | 02-12-2015 |
20150040789 | ENHANCED LINEAR SHAPED CHARGE INCLUDING SPINAL CHARGE ELEMENT - An enhanced linear shaped charge (X-Jet) includes a sheath and a spinal charge element. The sheath extends along an axis between a first end and a second end to define a sheath length. The sheath has a first hollowed chevron-shaped cross-section that defines a main charge cavity, an upper apex, and a lower apex. The spinal charge element is disposed within the main charge cavity and abuts the upper apex. The spinal charge element further includes a spinal casing that extends along the sheath length to define a spinal length. The spinal casing has a hollowed cross-section defining a spinal charge cavity. | 02-12-2015 |
20150035271 | HYDRAULIC HOSE GUIDE - The disclosed hose guide may prevent a hose from bending within a specified distance of a hose fitting, and therefore prevent weakening of the hose at the hose fitting interface. The hose guide may include a hose fitting stage, a straight hose stage, and a bell stage. The hose fitting stage may secure the hose guide around the hose fitting. The straight hose stage may prevent the hose from bending. The bell stage may allow the hose to bend at a radius greater than a minimum bend radius for the hose. | 02-05-2015 |
20150034762 | ROUTINGS FOR ARTICULATED LANDING GEAR - An articulated landing gear may include electrical lines and/or hydraulic lines located within the articulated landing gear. The articulated landing gear may have a hollow structural post and a hollow trailing arm coupled by a pivot joint. The electrical lines and/or hydraulic lines may be routed through an interior of the hollow structural post and through an interior of the hollow trailing arm. A bulkhead within the hollow structural post or the hollow trailing arms may include guide holes. The electrical lines and/or hydraulic lines may be supported by the bulkhead by passing through the guide holes. The electrical lines and/or hydraulic lines may be flexible around the pivot joint. | 02-05-2015 |
20150034705 | PRESSURE WELDING USING PROPYLENE - A process and method for welding using an oxygen and propylene gas mixture is disclosed herein. Landing gear components may be welded together using this oxygen and propylene gas fuel source. For instance, an axle beam and/or a post of an aircraft may be welded using oxygen and propylene gas fuel source. | 02-05-2015 |
20150033974 | HEATED INFLATION SYSTEM - A heated inflation system for an inflatable device on an aircraft is provided. The heated inflation system includes an inflation cylinder configured to hold a gas mixture under pressure, a heating element configured to selectively heat the gas mixture, and a temperature sensor configured to sense a temperature of the gas mixture. The heated inflation system also includes a control module coupled to the heating element and the temperature sensor. The control module is configured to regulate heat applied by the heating element to the gas mixture based on a sensed temperature from the temperature sensor. | 02-05-2015 |
20150028661 | INTEGRAL CLAMP HUBCAP FOR WHEEL SYSTEM AND APPARATUS - A clamp-hubcap assembly is provided. The assembly may include a clamp, a hubcap, and a retaining device. The retaining device may be any suitable structure capable of coupling the clamp and the hubcap together. | 01-29-2015 |
20150012153 | BRAKE CONTROL SYSTEM COMPRISING TIRE/RUNWAY FRICTION PROPERTY ESTIMATION MAPPING - Systems and methods for a tire/runway friction property estimation method based on measured wheel speed, calculated acceleration, wheel reference and tire normal force estimation are disclosed. Based on the resulting estimations, a map and/or function of position for the friction properties may be formed and transmitted to external systems after an aircraft stop is completed. | 01-08-2015 |
20150008800 | INTEGRAL HOUSING LOAD CELL SYSTEM AND APPARATUS - A strain gage system for an electric motor actuator is provided. The strain gage system may be coupled to or integrally formed in a housing of the electric motor actuator. In various embodiments, the strain gauge system may comprise one or more principle strain gages. In various embodiments, the strain gage system may comprise one or more transverse strain gages. | 01-08-2015 |
20140339148 | SILVER-COATED NANOFIBERS FABRICS FOR PATHOGEN REMOVAL FILTRATION - The invention provides a novel method of preparing a filter media by thermally bonding silver-coated nanofiber fabrics to a dirt-retaining membrane, a chemical-retaining membrane, a pathogen-retaining membrane, or a combination thereof. The invention also relates to the use of silver-coated nanofiber fabric layer as a component of a microorganism-killing membrane in filter media for a liquid or air filtration system. The filter media of the invention offers efficient disinfection effects, maintaining a low pressure drop and a high flow rate when in use. Further, the filter media is adhesive-layer free and contains at least one thermal binding layer made of spunbonded nonwoven polymeric fabrics. The invention also features a water-purification cartridge and a portable water system thereof. | 11-20-2014 |
20140332459 | BIOCIDE-LOADED ELECTROSPUN NANOFIBERS SUPPORTED BY ADHESIVE-FREE THIN FABRIC FOR PATHOGEN REMOVAL FILTRATION - The invention provides a novel type of filter media that offers efficient disinfection effects, while achieving a low water pressure drop and a high water flow rate when in use. Specifically, the filter media of the invention comprises a microorganism-killing membrane containing electro spun nanofiber fabrics loaded with biocidal nano-particles. The filter media of the invention is adhesive-layer free and contains at least one thermal binding layer that are made of spunbonded nonwoven polymeric fabrics. The invention also provides a water-purification cartridge and a portable water system thereof. | 11-13-2014 |
20140326712 | PULSED ELECTROTHERMAL ICE PROTECTION SYSTEMS WITH COATED HEATING SUBSTRATES - An aircraft ice protection system includes a heating substrate with a coating in intimate thermal contact with the heating substrate. The thermal effusivities of the heating substrate and the coating are different from one another for interference of thermal waves reflected from the coating with thermal waves generated in the heating substrate. A pulse generator can be operatively connected to the heating substrate to convert pulsed electrical power from the pulse generator into thermal energy for ice removal or prevention. | 11-06-2014 |
20140292060 | SYSTEM AND METHOD FOR A WHEEL LOCK RING ASSEMBLY - Systems and methods disclosed herein may be useful for use in a wheel assembly. In this regard, a wheel assembly is provided comprising a wheel base having a side rim disposed about a circumference of the wheel base, and a lock ring disposed within a cavity between the wheel base and the side rim. An air seal may be disposed between the wheel base and the inside surface of the side rim. Lock ring has two non-contiguous surface contacts with the wheel base and two non-contiguous surface contacts with the side rim each enabling various torque paths of lock ring. | 10-02-2014 |
20140290409 | BALLSCREW ASSEMBLY HAVING A LOW FRICTION SLEEVE - A ballscrew assembly may include a ballnut configured to combat the negative effects of thermal expansion of dissimilar materials used within the ballscrew assembly. Moreover, the ballscrew assembly described herein may have a decreased coefficient of friction as compared with a steel on steel housing and ballnut configuration. A ballscrew assembly may comprise a ballnut made from a first material, a ballnut housing made from a second material, and a sleeve made from a third material. The sleeve may be positioned between the exterior of the ballnut and an interior of the ballnut housing to reduce friction between the exterior surface of the ballnut and an interior surface of the ballnut housing. | 10-02-2014 |
20140264209 | HOIST AND WINCH CABLE ANGLE SENSOR - An assembly includes a hoist or a winch, a cable, and a fleet angle sensor. The fleet angle sensor includes a frame disposed around an opening. A first photodetector with multiple light-receiving zones is mounted on the frame. A first light source is mounted on the frame opposite the first photodetector. The first light source directs a first light beam across the opening to the multiple light-receiving zones of the first photodetector. The cable extends through the opening and into the first light beam, and the multiple light-receiving zones produce signals that vary based upon a fleet angle of the cable extending through the opening. | 09-18-2014 |
20140251739 | SYSTEMS AND METHODS FOR ALTERNATING MATERIAL BRAKE DISK STACK - Systems and methods are disclosed for dissimilar aircraft brake systems for use in, for example, an aircraft. In this regard, a system is provided comprising a carbon/carbon (“C/C”) rotor disk adjacent to a ceramic matrix composite (“CMC”) stator disk. In various embodiments, a system is provided comprising a CMC rotor disk adjacent to a C/C stator disk. | 09-11-2014 |
20140239120 | MAIN LANDING GEAR BIAS AXLE STEERING - A bias steered landing gear system comprises a bogie beam, a first landing gear axle pivotally mounted to the bogie beam, and a steering actuator assembly. The first landing gear axle is pivotable through an axle steering range which includes a maximum inboard steering angle and a maximum outboard steering angle. The steering actuator assembly is operable to apply a steering force to steer the first landing gear axle through the axle steering range between the maximum inboard steering angle and the maximum outboard steering angle. The maximum inboard steering angle is substantially larger than the maximum outboard steering angle. | 08-28-2014 |
20140239119 | MAIN LANDING GEAR COMPACT AXLE STEERING - A landing gear system comprises a bogie beam, a landing gear axle pivotally mounted to the bogie beam, a steering rack, a linear actuator assembly, and a steering control link. The steering rack is secured transversely to the bogie beam and is longitudinally spaced apart from the landing gear axle. The linear actuator assembly is operable to laterally translate the steering rack. The steering control link is longitudinally extendable and has an actuator end secured to the steering rack, and an axle end of the steering control link engaged with the landing gear axle. The steering control link and the landing gear axle are pivotable relative to the bogie beam about a common axis. | 08-28-2014 |
20140191083 | ICE PROTECTION SYSTEM - An ice protection system ( | 07-10-2014 |
20140187370 | LANDING GEAR WHEEL DRIVE SYSTEM - A landing gear wheel drive system includes a landing gear strut, a wheel, a drive loop carrier assembly, a drive loop, and a displacement system. The wheel is rotatably attached to the landing gear strut and includes a ring gear mounted to the wheel. The drive loop carrier assembly includes a plurality of toothed pulleys. The drive loop extends around the toothed pulleys to form a continuous loop. The displacement system is connected to the drive loop carrier assembly to selectively engage with the ring gear. | 07-03-2014 |
20140182759 | DUAL LOCK RING WHEEL ASSEMBLY - A wheel assembly includes a wheel base and a side rim disposed about the wheel base. A recess is formed on an inside surface of the side rim. A cavity is disposed between the wheel base and the side rim. An air seal is disposed between the wheel base and the side rim. A locking mechanism secures the side rim in position around the wheel base. The locking mechanism is configured to prevent the air seal from disengaging with the inside surface and allowing air to exit the wheel assembly between the wheel base and the side rim when the locking mechanism is properly installed. The locking mechanism is also configured to permit the air seal to disengage the inside surface and allow air to exit the wheel assembly between the wheel base and the side rim when the locking mechanism is not properly installed. | 07-03-2014 |
20140174863 | BRAKE DISK ASSEMBLY - An annular-shaped disk half of a split friction disk assembly for a disk brake system. The disk half includes a friction surface and a non-friction surface. The friction surface is at an axial end of the disk half. The non-friction surface is at an axial end of the disk half on a side opposite of the friction surface. The non-friction surface includes a contact surface and a non-contact surface. The non-contact surface is recessed from the contact surface. | 06-26-2014 |
20140163815 | SYSTEM AND METHOD FOR DETERMINING AN ADAPTIVE TURNAROUND THRESHOLD - A method includes measuring a brake temperature of an aircraft brake using a sensor; determining a brake heat sink mass of the aircraft brake using a wear measuring device; and calculating a turnaround threshold based upon the measured brake temperature and the determined brake heat sink mass. | 06-12-2014 |
20140158474 | COMBINED THRUST BEARING/LOAD CELL FOR BRAKE ACTUATORS - A ring-shaped thrust bearing extending in an axial direction having an inner surface includes a first axial groove in the inner surface having a first flat wall and a second flat wall; and a first principal strain sensor positioned on the first flat wall of the first axial groove to measure compression in the axial direction. | 06-12-2014 |
20140157906 | CIRCULAR LOAD CELL STRAIN SENSOR CONFIGURATION - A load cell extending in an axial direction having an outer surface includes a groove in the outer surface having a first flat wall, and a second flat wall; and a principal strain sensor positioned on the first flat wall to measure tension and compression in the axial direction. | 06-12-2014 |
20140148038 | LOW IMPEDANCE EQUIPMENT INTERFACE - An assembly mounted to a surface, the assembly includes a component; and a plurality of fingers connected to the component and in contact with the surface to provide a low impedance path between the component and the surface. | 05-29-2014 |
20140138490 | DEICER ZONES WITH HEATER-ENHANCED BORDERS - An ice protection system comprises deicing zones wherein each zone includes an envelope with an electrothermal heater layer Adjacent envelopes have edge regions flanking shared interzone borders. These edge regions can be configured to provide a higher heating power than the rest of the envelope so as to enhance deicing at the borders. | 05-22-2014 |
20140134355 | TREATED GRAPHENE NANOPLATELETS FOR INFLATABLE STRUCTURE BARRIER LAYERS - An air-impermeable fabric is disclosed. The air-impermeable fabric has a fabric substrate, which may also be referred to as a base fabric. Disposed over the fabric substrate is a barrier layer comprising a polymer binder and at least 20 weight percent graphene nanoplatelets, based on the total weight of the barrier layer. A barrier underlayer, which may or may not also include graphene nanoplatelets, is disposed between the fabric substrate and the barrier layer. A barrier overlayer, which may or may not also include graphene nanoplatelets, is disposed on the opposite side of the barrier layer from the barrier underlayer | 05-15-2014 |
20140134354 | BARRIER LAYER FOR INFLATABLE STRUCTURES - An air-impermeable fabric is disclosed. The air-impermeable fabric has a fabric substrate, which may also be referred to as a base fabric. Disposed over the fabric substrate is a barrier layer comprising a polymer binder and at least 20 weight percent graphene nanoplatelets, based on the total weight of the barrier layer. A barrier underlayer, which may or may not also include graphene nanoplatelets, is disposed between the fabric substrate and the barrier layer. A barrier overlayer, which may or may not also include graphene nanoplatelets, is disposed on the opposite side of the barrier layer from the barrier underlayer | 05-15-2014 |
20140071216 | PRINTED HEATING ELEMENT - A heating element is provided with a conductive path pattern which can be printed in a mask-free manner (e.g., drop-on-demand) with existing printing technology. The printing step can be performed, for example, with a thermal inkjet printer, a piezoelectric inkjet printer, an aerosol jet printer, or an ultrasound printer. The ink solution can be formulated so that it establishes an electrically conductive path which is free of polymer binders. | 03-13-2014 |
20140042273 | WARPED-FLOOR TOLERANT AIRCRAFT SEAT - A track-mounted aircraft seat has seat track locking pins that are capable of moving independently to remain engaged with the seat track assembly in a warped-floor condition. The seat track locking pins are actuated by means of a pair of torque tubes that rotate independently about a common pilot shaft. A control link, which is operated by the user, acts on a pair of bell cranks each of which acts on one of the torque tubes. The control link is attached to the bell cranks by means of a spherical joint. Because the torque tubes rotate independently and because the spherical joint allows the bell cranks also to move independently, in the event of a warped-floor condition, rotation of one torque tube caused by the skewed seat track will not cause the other torque tube to release its track locking pin. | 02-13-2014 |
20140034783 | AIRCRAFT ELECTRICAL MAT WITH SOLDERLESS LEAD LINE CONNECTIONS - An electrical mat (20) is adapted for coupling to lead lines (30). The electrical mat (20) comprises a plurality of layers (41-48), a heater element (50), and a window (60) aligned with a connection face on a heater bus (52). A fastener part (71) extends through each window (60) so as to allow mechanical attachment of a terminal (32) and establish an electrical connection between the lead line (30) and a heater bus (52). | 02-06-2014 |
20140020873 | SYSTEMS AND METHODS FOR HEAT SHIELD ASSEMBLIES - Systems and methods disclosed herein may be useful for aircraft heat shield assemblies. In this regard, a heat shield assembly is provided comprising a heat shield having an aperture, the aperture comprising an end portion and an insertion portion, the insertion portion having a width larger than the end portion, a spacer comprising an upper portion, an undermount flange and a gap between the upper portion and the undermount flange, wherein a surface of the gap is engaged with the heat shield, and wherein the undermount flange has a width less than the insertion portion of the aperture and greater than the width of the end portion. | 01-23-2014 |
20140018978 | SYSTEMS AND METHODS FOR DRAGGING BRAKE DETECTION - Systems and methods are disclosed for detection of dragging brakes for use in, for example, an aircraft. A method is provided comprising calculating, by a brake controller, a slip ratio based upon an aircraft speed and a speed of an aircraft wheel, determining, by the brake controller, that the slip ratio is above a threshold value, and sending, by the brake controller and in response to the slip ratio being above the threshold value, a dragging brake signal to an aircraft component. | 01-16-2014 |
20130342828 | AIRCRAFT SHOCK STRUT HAVING A FLUID LEVEL MONITOR - A system for monitoring a liquid level in an aircraft shock strut includes a cylinder having an internal chamber sealed by a piston telescopically movable within the cylinder. The chamber contains a gas and a liquid, and a sensor assembly is provided for monitoring a condition of a level of the liquid in the chamber. The sensor assembly includes at least one probe within the chamber, and a fitting assembly allows one or more leads from the probe to pass through the wall of the strut while maintaining pressure in the chamber. The fitting assembly includes a plug molded to the one or more leads extending from the probe. The fitting assembly also includes a retainer for holding the plug in sealed relationship with a through passage in the strut. | 12-26-2013 |
20130336205 | SYSTEM AND METHOD FOR SYNCHRONIZING WIRELESS DEVICES WITHOUT SENDING TIMESTAMP DATA - A sensor network includes a plurality of sensors and a base station for sending a series of data acquisition requests to the sensors. Each data acquisition request has an index. Each sensor has a synchronization calculation module and an internal clock. The sensors are adapted and configured to receive the series of data acquisition requests and record a timestamp of receipt for each data acquisition request. The sensors also store a predefined time interval related to the plurality of data acquisition requests so that the sensor can calculate a time to start collecting data based upon the series of data acquisition requests, the timestamps, the indices, and the predefined time interval. In an alternative embodiment, the base station only sends a general request for data acquisition and a synchronization sensor module receives the general request and, in turn, sends the series of data acquisition requests to the sensors. | 12-19-2013 |
20130334367 | SEQUENTIAL LATCH FOR PALLETIZED CARGO - An aircraft cargo handling system has a pair of load restraining rail assemblies, each of which has a shaft assembly running substantially parallel to the longitudinal axis of the aircraft. The shaft assembly has a plurality of lock pawls, each of which comprises a body having a cylindrical pallet-engaging surface. The pallet engaging surfaces of the lock pawls have increasing included angles at stations moving toward the front of the aircraft (or vice versa). This enables the pallets to be locked in place sequentially by rotating the shaft assembly an predetermined angular rotation each time a pallet is loaded. Unloading of the aircraft is carried out in the reverse order, by rotating the shaft assembly in the opposite direction in steps to unlock each pallet individually as the aircraft is unloaded. | 12-19-2013 |
20130311005 | SYSTEMS AND METHODS FOR REFLECTED INERTIA PARKING BRAKE - Systems and methods are disclosed for parking brake systems for use in, for example, an aircraft. In this regard, a system is provided comprising a parking brake system for an aircraft comprising an electric motor coupled to a high gear ratio transmission, a first clutch for engaging the electric motor to a propulsion transmission, and a second clutch for engaging propulsion transmission to an aircraft wheel. The high gear ratio transmission has a gear ratio sufficient to maintain the aircraft wheel in a stationary position. | 11-21-2013 |
20130292992 | SYSTEMS AND METHODS FOR AIRCRAFT BRAKING AND TAXIING - Systems and methods are disclosed for aircraft braking and taxiing systems for use in, for example, an aircraft. In this regard, system comprising an electric motor coupled to a first transmission, a first clutch for selectively engaging the first transmission to a propulsion transmission and a brake damping system, wherein, in response to engagement with the propulsion transmission, the electric motor drives an aircraft wheel, wherein, in response to engagement with the actuator ram, the electric, motor drives the brake clamping system to apply force to an aircraft brake disk stack. | 11-07-2013 |
20130284856 | AIRCRAFT ICE PROTECTION OPTIMIZATION BASED ON ICE-DETECTION INPUT - An aircraft ice protection system ( | 10-31-2013 |
20130270253 | DEICER ZONES WITH SHEDDING-ENHANCED BORDERS - An ice protection system comprises deicing zones each including an envelope defining an ice-protection area. Adjacent envelopes have spanwise edge regions flanking shared interzone borders. The edge regions are provided with nonlinear contours having features which project-and-recess in a direction generally parallel to the airstream direction. | 10-17-2013 |
20130239376 | SYSTEM AND METHOD FOR TEXTILE POSITIONING - In various embodiments, the present disclosure relates generally to a method for needling a spiral textile to create a needled preform, the method comprising receiving the spiral textile on a bed plate of a circular needle loom, engaging a positional structure of the spiral textile, rotating the spiral textile around the circular needle loom, depositing a predetermined number of layers of the spiral textile on the bed plate, and needling the spiral textile to create the needled preform. Moreover, the present disclosure also provides, in various embodiments, a method for creating a circular needled preform from a spiral textile, comprising attaching sacrificial fibers to at least one of the weft tow and the plurality of warp tows proximate at least one of the inside diameter and the outside diameter, and engaging the sacrificial fibers with an engagement mechanism on a circular needle loom. | 09-19-2013 |
20130231024 | SYSTEMS AND METHODS FOR REDUCED CRIMP CARBON FIBER HELICAL FABRIC - Systems and methods for weaving helical carbon fabrics with minimum fiber crimp are provided herein. In various embodiments, small denier natural or synthetic yarns are used in the warp direction to interlace the carbon fiber wefts with minimum deformation. Specific weave designs are used in combination with the small denier yarn to maintain the primary carbon fiber weft and warp un-crimped. | 09-05-2013 |
20130205893 | LIQUID LEVEL SENSING SYSTEM - A linear liquid level sensing system ( | 08-15-2013 |
20130199878 | SYSTEMS AND METHODS FOR AN IMPROVED TORQUE TUBE - Systems and methods disclosed herein may be useful for improved torque tubes. In this regard, an apparatus is provided comprising a torque tube having an axis, a proximal terminus and a distal back leg, a first spline circumferentially disposed on the torque tube, a second spline circumferentially disposed on the torque tube, the first spline extending from a first location proximal to the distal back leg to a first terminal point, and the second spline extending from a second location proximal to the distal hack leg to a second terminal point, the second terminal point being distal to the first terminal point. | 08-08-2013 |
20130186224 | BALLSCREW ASSEMBLY - A ballscrew assembly may comprise a ballscrew having an axially distributed ballscrew groove about an interior circumference of the ballscrew, an extended top plate having an axially distributed extended top plate groove disposed on an outer circumference of the extended top plate, and an axially distributed thrust bearing. Further, a ballnut assembly may comprise a ballnut having an axially distributed ballnut groove about an interior circumference of the ballnut, an extended top plate having an axially distributed extended top plate groove disposed on an outer circumference of the extended top plate, and an axially distributed thrust bearing. Further still, a ballnut assembly may comprise a ballnut having an axially distributed ballnut groove about an outer circumference of the ballnut, an extended top plate having an axially distributed extended top plate groove disposed on an interior circumference of the extended top plate and an axially distributed thrust bearing. | 07-25-2013 |
20130145833 | SYSTEMS AND METHODS FOR BUILT IN TEST EQUIPMENT FOR A BRAKE CONTROL SYSTEM - A method is disclosed that comprises severing an I/O channel between a brake system controller and an aircraft component; sending a test signal to the brake system controller; receiving, from the brake system controller, a feedback signal to the test signal; and determining an appropriateness of the feedback signal. A system is disclosed that comprises a brake system controller wrapped in a BITE region, wherein the BITE region comprises a testing module, a safety interlock region having an I/O channel between the brake system controller and another system, and a testing module capable of sending a test signal to the brake system controller. | 06-13-2013 |
20130144559 | SYSTEMS AND METHODS FOR LANDING IDENTIFICATION - Systems and methods disclosed herein may be useful for use in landing identification. In this regard, a method is provided comprising receiving pulse information over a first time period, wherein the pulse information is indicative of an angular distance traveled by a first wheel, comparing the pulse information to a threshold value, and determining a likelihood of a landing event based upon the comparison. In various embodiments, a system is provided comprising a monstable multivibrator in electrical communication with a metal-oxide-semiconductor field-effect transistor (MOSFET), a resistor-capacitor network in electrical communication with the MOSFET, and a comparator that receives a voltage from the resistor-capacitor network and a reference voltage. | 06-06-2013 |
20130139590 | SYSTEMS AND METHODS FOR LANDING IDENTIFICATION - Systems and methods disclosed herein may be useful for use in landing identification. In this regard, a method is provided comprising receiving pulse information over a first time period, wherein the pulse information is indicative of an angular distance traveled by a first wheel, comparing the pulse information to a threshold value, and determining a likelihood of a landing event based upon the comparison. In various embodiments, a system is provided comprising a monstable multivibrator in electrical communication with a metal-oxide-semiconductor field-effect transistor (MOSFET), a resistor-capacitor network in electrical communication with the MOSFET, and a comparator that receives a voltage from the resistor-capacitor network and a reference voltage. | 06-06-2013 |
20130129440 | MOVEABLE TIEDOWN - A system for securing objects in an aircraft can comprise a structure in an aircraft having a plurality of receiving holes and a tie down. The tie down can comprise a housing and a fitting. The housing can have at least one engagement pin for selective positioning wherever the receiving holes are located. The fitting can be capable of receiving and securing a restraint to the housing and configured to rotate about the engagement pin to facilitate securing objects in an aircraft. | 05-23-2013 |
20130121782 | SELF-LOCKING, OVERRIDEABLE AND ATTENUATING CARGO GUIDE AND RESTRAINT - An aircraft cargo restraint has a base configured for attachment to a cargo deck. A housing is rotatably mounted to the base about a first axis and is movable between an erect position and a stowed position. A head is movably disposed in the housing, and is movable between an extended position and a contracted position in directions that are substantially parallel to the first axis. The restraint includes a lock configured to releasably secure the housing in the erect position when the head is in the contracted position, and to permit movement of the head from the erect position to the stowed position when the head is in the extended position. | 05-16-2013 |
20130076900 | Wide field of view monocentric lens system for infrared aerial reconnaissance camera systems - A wide field of view monocentric lens system for an infrared aerial reconnaissance camera includes front and rear lens shell elements and a core lens element, with the number of front and rear shell lens elements depending on the IR band of interest (LWIR, MWIR or SWIR). Infrared radiation entering the monocentric lens passes sequentially through the front shell lens element(s), the core lens element, and the rear shell lens element(s) and is focused onto a curved focal surface. The front shell lens element(s) and the rear shell lens element(s) are made of material having a relatively higher refractive index or a relatively higher optical dispersion, or both, in the band of interest, as compared to the core lens element. | 03-28-2013 |
20130068053 | ACTUATOR SYSTEM AND METHOD - Systems and methods disclosed herein may be useful for use in a ballscrew assembly. In this regard, a ballscrew assembly is provided comprising a ballscrew having a ballscrew stop, a ballnut having a ballnut stop, wherein contact between the ballnut stop and the ballscrew stop impede rotation of the ballscrew relative to the ballnut. The ballnut stop may comprise an axial mating surface and the ballscrew stop may comprise an axial mating surface. Additionally, the ballnut may comprise threads axially spaced a first distance apart and the ballnut stop comprises a surface having length equal to the first distance. | 03-21-2013 |
20130065696 | FLEXIBLE DIAPHRAGM COUPLING FOR AXIAL FORCE LOADING - A flexible diaphragm coupling is disclosed which includes a radially inner hub portion, a radially outer rim portion, and a flexible diaphragm portion extending between the radially outer rim portion and the radially inner hub portion. The flexible diaphragm portion includes a radially inner diaphragm section having a maximum axial thickness adjacent the radially inner hub portion and a radially outwardly tapering axial thickness extending to a point of minimum axial thickness of the diaphragm portion, and a radially outer diaphragm section having a maximum axial thickness adjacent the radially outer rim portion and a radially inwardly tapering axial thickness extending to the point of minimum axial thickness of the diaphragm portion. By design, the point of minimum axial thickness of the diaphragm portion is closer to the radially outer rim portion than to the radially inner hub portion. | 03-14-2013 |
20130062935 | SYSTEMS AND METHODS FOR EMERGENCY BRAKING SYSTEM - Systems and methods disclosed herein may be useful emergency braking systems for use in, for example, an aircraft. A system is disclosed that allows emergency braking without the need for a manually operated emergency brake. For example, a system is provided comprising a potentiometer in mechanical communication with a brake pedal, a first electronic switch in electrical communication with the potentiometer, a second electronic switch indicating a displacement of the brake pedal, wherein a brake control valve opens in response to the first electronic switch, and wherein a shutoff valve opens in response to the second electronic switch. | 03-14-2013 |
20130060441 | SYSTEMS AND METHODS FOR IMPROVED AIRCRAFT BRAKING - Systems and methods disclosed herein may be useful for braking systems for use in, for example, an aircraft. A method is disclosed comprising determining, at a brake controller, an aircraft reference speed for an aircraft having a first wheel and a second wheel, identifying, at the brake controller, a state comprising the first wheel having a different rotational velocity than the second wheel, wherein the difference in rotational velocity sums to about zero, calculating, at the brake controller, a compensation factor for at least one of the first wheel and the second wheel, and adjusting, at the brake controller, a locked wheel trigger velocity in accordance with the compensation factor. | 03-07-2013 |
20130060438 | SYSTEMS AND METHODS FOR MANUAL BRAKING SYSTEM - Systems and methods disclosed herein may be useful for manual braking systems for use in, for example, an aircraft. A system is disclosed that allows for manual braking. For example, a system is provided comprising a brake handle, a potentiometer in mechanical communication with the brake handle, a mapping module in electrical communication with the potentiometer, wherein the mapping module receives an output voltage from the potentiometer, wherein the mapping module produces a braking command output. | 03-07-2013 |
20130060404 | SYSTEMS AND METHODS FOR BRAKING SYSTEM TESTING - Systems and methods disclosed herein may be useful for testing braking systems for use in, for example, an aircraft. A system is disclosed that allows for built in testing. For example, a method if provided comprising sending, from a brake controller, a test command set to at least one of an electromechanical actuator (EMAC) and a brake servo valve (BSV) in response to a landing gear retraction, receiving, at the brake controller, feedback from the at least one of the EMAC and the BSV in response to the test command set, and comparing, at the brake controller, the feedback with a predetermined signature. | 03-07-2013 |
20130009003 | TORQUE LINK WITH SHIMMY DAMPER - A torque link includes a spring-damper system structurally incorporated into the design and functionality of the torque link. The spring portion may take the form of a structurally rigid beam while the damping portion may take the form of a damping mechanism or assembly. The damping mechanism is configured to damp out deformations in the beam and also configured to bottom out and become a structural tension/compression member when the load through the torque link exceeds a threshold load. The method damping may take a number of forms, such as, but not limited to, solid media damping, fluid damping with or without an orifice, a hydraulic or magnetic circuit, coulomb damping, etc. | 01-10-2013 |
20120325594 | SYSTEMS AND METHODS FOR BRAKE WHIRL MITIGATION - Systems and methods for whirl mitigation in an aircraft braking system are provided. For example, an apparatus is provided comprising a brake disk stack including a torque tube having a first axial end and a second axial end, a back leg near a first axial end of the torque tube, and a circumferentially disposed spline extending from the back leg towards the second axial end of the torque tube. | 12-27-2012 |
20120315407 | HIGH-STRENGTH LIGHTWEIGHT FABRIC FOR INFLATABLE STRUCTURES - A high-strength, lightweight inflatable structure is formed of at least one flexible fabric member that, in an inflated condition, forms a self-supporting structure. The flexible fabric member is formed from a bare fabric having an areal weight of less than 4.5 oz/yd | 12-13-2012 |
20120313423 | SYSTEM AND METHOD FOR A WHEEL LOCK RING ASSEMBLY - Systems and methods disclosed herein may be useful for use in a lock ring assembly. In this regard, a lock ring assembly is provided comprising a wheel base having a side rim disposed about a circumference of the wheel base, an ID lock ring and an OD lock ring disposed within a gap between the wheel base and the side rim. The ID lock ring has two surface contacts with the wheel base and one surface contact with the side rim. The OD lock ring has two surface contacts with the side rim and one surface contact with the wheel base. In various embodiments, the ID lock ring and the OD lock ring are in contact. | 12-13-2012 |
20120313307 | POLYMER COMPOSITES POSSESSING IMPROVED VIBRATION DAMPING - Fiber-reinforced polymer composites possessing improved damping ability are provided. In one aspect, the fibers provide the composite with a relatively high dynamic modulus over a broad range of frequencies for a given temperature. In another aspect, the polymer may comprise a viscoelastic polymer possessing a relatively high loss factor for a given frequency and temperature. The polymer may be further tailored to control the center frequency at which the maximum loss factor of the polymer is achieved. The composite so formed exhibits a relatively small reduction in loss factor with significant increase in dynamic modulus over a broad range of frequencies for a given temperature. As a result, a structure damped by the composite exhibits a relatively high, constant loss factor as compared to conventional damping materials. Thus, embodiments of the disclosed composites dissipate significantly more energy during each vibration cycle than conventional damping materials. | 12-13-2012 |
20120291705 | METHODS AND APPARATUS FOR CONTROLLED CHEMICAL VAPOR DEPOSITION - A gas injector system is provided that allows for improved distribution and directional control of the vapor material in a CVD or CVI process. Gas injector systems may be used without experiencing significant clogging of gas injector tube apertures over multiple. CVD procedures. Further, a gas injector system provided includes a dual aperture release system and/or allow vapor material to flow both substantially horizontally and substantially vertically. | 11-22-2012 |
20120286095 | DRAINMAST - A drainmast ( | 11-15-2012 |
20120280084 | ICE PROTECTION SYSTEM - An ice protection system ( | 11-08-2012 |
20120241557 | HEAT SHIELD INSTALLATION FOR AIRCRAFT WHEEL TO IMPROVE CONVECTIVE COOLING OF AIRCRAFT BRAKE - Improved chin rings are disclosed, wherein a chin ring may comprise a substantially circular chin ring having an outer surface and a slot, a first radially spaced aperture in the chin ring on a first side of the slot, a second radially spaced aperture in the chin ring on a second side of the slot, a first louver disposed at least partially over the first radially spaced aperture, the first louver disposed at a first angle relative to the outer surface and a second louver disposed at least partially over the second radially spaced aperture. | 09-27-2012 |
20120226457 | NON-CONTACT SENSOR SYSTEM AND METHOD FOR DISPLACEMENT DETERMINATION - A non-contact sensor system is provided that comprises a first sensor element and a rotary member disposed proximate the first sensor element without physically contacting the first sensor element. The rotary member may he configured to be rotated about an axis Y by a shaft configured to pass through the rotary member along the axis Y at a value X. The non-contact sensor system further comprises a second sensor element disposed on the rotary member proximate the first sensor element without physically contacting the first sensor element, and the first sensor element and the second sensor element may be operatively coupled to facilitate sensing the value X. | 09-06-2012 |
20120222475 | NON-CONTACT SENSOR SYSTEM AND METHOD FOR DISPLACEMENT DETERMINATION - A non-contact sensor system is provided that comprises a first sensor element and a rotary member disposed proximate the first sensor element without physically contacting the first sensor element. The rotary member may be configured to he rotated about an axis Y by a shaft configured to pass through the rotary member along the axis Y at a value X. The non-con act sensor system further comprises a second sensor element disposed on the rotary member proximate the first sensor element without physically contacting the first sensor element, and the first sensor element and the second sensor element may be operatively coupled to facilitate sensing the value X. | 09-06-2012 |
20120187239 | Steering collar locking mechanism for retractable aircraft nose landing gear - A retractable nose landing gear assembly for an aircraft is disclosed, which includes an elongated strut cylinder defining a longitudinal axis, an elongated strut piston mounted for reciprocal movement relative to the strut cylinder between a shrunk condition when the landing gear is retracted into a wheel well of an aircraft and a fully extended condition when the landing gear is deployed from the wheel well for landing the aircraft, and wherein the strut piston is mounted for rotation about the axis of the strut cylinder for steering the aircraft while taxiing on the ground, and a locking mechanism operatively associated with the strut cylinder for preventing rotation of the strut piston about the axis of the strut cylinder when the landing gear is in a shrunk condition retracted within the wheel well of the aircraft during flight. | 07-26-2012 |
20120180588 | BALLSCREW ASSEMBLY - Improved ballscrew assemblies are disclosed herein. For example, a ballscrew assembly may comprise a ballscrew having an axially distributed ballscrew groove about a circumference of the ballscrew, an extended top plate having an axially distributed extended top plate groove, and an axially distributed thrust bearing disposed in a space bounded by the axially distributed ballscrew groove and the axially distributed extended top plate groove. | 07-19-2012 |
20120179324 | BRAKE WEAR MEASUREMENT APPARATUS AND METHOD - A brake wear measurement apparatus for use on a brake assembly equipped with a wear pin having a plunger slidably mounted in the plunger sleeve having a first end and second end and wherein when the brake wear measurement apparatus is placed over the wear pin, the wear pin contacts the plunger first end, and moves the plunger within the plunger sleeve to a retracted position corresponding to a retraction distance delta, and wherein the retraction distance delta corresponds to a wear pin exposed height indicating an amount of brake wear. A locking mechanism for locking the plunger in the retracted position may be provided. A brake wear correlation program whereby the input of a brake part number, a plunger retraction distance delta, and a number of performed landings will result in an output of an estimated number of remaining landings may also be provided. | 07-12-2012 |
20120153911 | SYSTEMS AND METHODS FOR SWITCHED MODE POWER AMPLIFICATION - Systems and methods for switched mode power amplification are disclosed herein. A circuit is provided comprising an amplifier network, a DC translation stage for receiving input voltage from the amplifier network and for providing an output voltage to a voltage boost circuit, and a feedback network for providing feedback from the voltage boost circuit to the amplifier network. | 06-21-2012 |
20120145490 | SYSTEM AND METHOD FOR PROVIDING INDICATION OF BRAKING FOR ELECTRIC BRAKES - A system for electrical braking of a vehicle comprises a power bus coupled to a first driver associated with a first electromechanical actuator (EMA). The power bus is also coupled to a second driver associated with a second EMA, and the first EMA and the second EMA are associated with a wheel of the vehicle. The power bus provides braking power to the first EMA via the first driver and to the second EMA via the second driver. A normal braking command interface provides a first braking signal to the first driver and a second braking signal to the second driver. An emergency/park brake interface bypasses the normal braking command interface and sends a first emergency/park braking signal to the first driver and a second emergency/park braking signal to the second driver. A sensor measures a current at a single location of the power bus that is proportional to a braking force exerted on the wheel. | 06-14-2012 |
20120134612 | BEARING ENCLOSURE WITH INTEGRATED WEAR DETECTION - An electro-mechanical fuse integrated into the enclosure of a bearing assembly of a generator or like component. Under normal operation, the electro-mechanical fuse provides continuity through a bearing sensing circuit. However, ball cage damage causes the fuse to open and, in turn, the bearing sensing circuit indicates bearing wear. Thus, damage to other generator components is greatly reduced because the generator is removed for maintenance in a timely manner. | 05-31-2012 |
20120111999 | VERTICALLY RETRACTING SIDE ARTICULATING LANDING GEAR FOR AIRCRAFT - A side articulating main landing gear assembly for an aircraft is disclosed which includes a wheel axle fitting oriented in a horizontal plane when the landing gear assembly is in an extended condition deployed from a landing gear bay of the aircraft, a shock absorber adapted to stroke between an extended state and a compressed state upon landing the aircraft, a first linkage for maintaining a tire supported on the wheel axle fitting in a substantially vertical plane as the shock absorber strokes between the extended state and the compressed state, and a second linkage for maintaining the wheel axle fitting in the horizontal plane as the shock absorber strokes between the extended state and the compressed state. The first and second linkages are adapted and configured to minimize lateral tire scuffing during shock absorber stroking. | 05-10-2012 |
20120111432 | AIRCRAFT POTABLE WATER SYSTEM - An aircraft potable water system ( | 05-10-2012 |
20120104275 | AIRCRAFT POTABLE WATER SYSTEM - A water purification device ( | 05-03-2012 |
20120095703 | MONITORING SYSTEMS AND METHODS FOR AIRCRAFT LANDING GEAR - A system and method for monitoring loads applied to aircraft landing gear structure. The method includes the step of interrogating at least one sensor positioned proximate the landing gear structure by way of data acquisition circuitry to yield strain data. The method further includes the step of instructing the data acquisition circuitry with respect to a sampling rate and data resolution for interrogation. | 04-19-2012 |
20120095702 | SYSTEMS AND METHODS FOR DETECTING LANDING GEAR GROUND LOADS - There is provided a system for predicting loading of a landing gear including, a plurality sensors positioned proximate to the landing gear. The plurality of sensors measure strain applied to the landing gear, and each sensor yielding strain data. The system further includes a processor that receives the strain data from the plurality of sensors and predicts at least one ground load based on strain data. There is further provided a method for predicting loading of a landing gear. The method includes powering a plurality of sensors located proximate to a landing gear structure, interrogating the plurality of sensors via data acquisition circuitry to yield strain data, instructing the data acquisition circuitry as to a sampling rate and data resolution to be used for the interrogating, and, finally, processing the strain data to predict a ground load. | 04-19-2012 |
20120094021 | METHOD OF FORMING A DIFFUSION ALUMINIDE COATING ON A SURFACE OF A TURBINE COMPONENT AND A HOMOGENEOUS PASTE FOR COATING SUCH SURFACES - The subject invention is directed to diffusion aluminide coatings, and more particularly, to a homogenous paste for applying a diffusion aluminide coating to a selected surface of a turbine component and to a method of applying a diffusion aluminide coating to a selected surface of a turbine component. | 04-19-2012 |
20120065816 | SYSTEMS AND METHODS FOR DYNAMICALLY STABLE BRAKING - Systems and methods for dynamically stable braking are disclosed. A first electromechanical brake actuator controller may be placed in communication with a second electromechanical brake actuator controller, wherein each of the first electromechanical brake actuator controller and second electromechanical brake actuator controller are in communication with electromechanical brake actuators that are associated with the same wheel. The first electromechanical brake actuator controller and second electromechanical brake actuator controllers may then communicate electromechanical brake actuator status information and take corrective measures in accordance with the status information. | 03-15-2012 |
20120056035 | Shrink shock strut locking mechanism for retractable aircraft landing gear - A shrink shock strut assembly for retractable aircraft landing gear is disclosed which includes an elongated strut cylinder, an elongated strut piston coaxially mounted for reciprocal movement within the strut cylinder between a shrunk condition when the landing gear is retracted into a wheel well of an aircraft and a fully extended condition when the landing gear is deployed from the wheel well for landing the aircraft, and a blocking mechanism operatively associated with the strut cylinder and mounted for movement into a blocking position with respect to the strut piston, when the landing gear is retracted within the wheel well, to prevent axial movement of the strut piston into the fully extended condition within the wheel well. | 03-08-2012 |
20120043417 | CAPACITIVE SENSORS FOR MONITORING LOADS - A sensor for monitoring loads in a landing gear torque linkage includes a main pin having an axial interior bore defined therein. The main pin is configured and adapted to engage a torque link to a strut lug of a landing gear strut. A core pin is mounted axially within an interior bore of the main pin and is spaced radially inwardly from the interior bore for relative displacement with respect to the main pin. A capacitor is included having an inner capacitor plate mounted to the core pin. An outer capacitor plate is mounted to the main pin. Relative displacement of the core pin and the main pin due to loads acting on the torque link and strut lug results in relative displacement of the inner and outer capacitor plates. Signals can thereby be produced indicative of the loads acting on the torque link. | 02-23-2012 |
20120012701 | SENSOR FOR MEASURING LARGE MECHANICAL STRAINS WITH FINE ADJUSTMENT DEVICE - A capacitive strain sensor for sensing strain of a structure. The sensor includes a first section attached to the structure at a first location and a second section attached to the structure at a second location. The first section includes a capacitor plate electrically isolated from the structure and the second section includes two electrically isolated capacitive plates, both of the plates being electrically isolated from the structure. A flexible connector connects the first section to the second section. The capacitor plate of the first section is separated from the two capacitive plates of the second section by at least one capacitive gap. When strain is experienced by the structure, a change occurs in the capacitive gap due to relative motion between the first and second sections. | 01-19-2012 |
20120012700 | SYSTEMS AND METHODS FOR MEASURING ANGULAR MOTION - A system for monitoring landing gear position. An example rotation position sensor includes a hub mount that locks within a shaft of a joint, a first sensor attached to the hub mount, and a second sensor attached to the rotatably attached part that does not rotate. The hub mount includes a nut that has a partially tapered surface and a threaded cavity. The nut is secured within the shaft. The hub mount also includes a mounting unit that has a partially tapered surface that is in opposition to the partially tapered surface of the nut. A fastener secures the hub mount to the nut. In one example, the first sensor includes a magnetometer and the second sensor includes magnet(s). In another example, the first sensor includes inductor sensor(s) and the second sensor includes device(s) that causes a change in an inductance value of the inductor sensor(s) as the joint rotates. | 01-19-2012 |
20120012699 | SENSOR FOR MEASURING LARGE MECHANICAL STRAINS IN SHEAR OR LATERAL TRANSLATION - A capacitive strain sensor for sensing strain of a structure. The sensor includes a first section attached to the structure at a first location and a second section attached to the structure at a second location. The first section includes a capacitor plate electrically isolated from the structure and the second section includes two electrically isolated capacitive plates, both of the plates being electrically isolated from the structure. A flexible connector connects the first section to the second section. The capacitor plate of the first section is separated from the two capacitive plates of the second section by at least one capacitive gap. When strain is experienced by the structure, a change occurs in the capacitive gap due to relative motion between the first and second sections. The first section includes a core and the second section includes a ring that receives the core. | 01-19-2012 |
20120011946 | SYSTEMS AND METHODS FOR MOUNTING LANDING GEAR STRAIN SENSORS - A strain sensor device for measuring loads on aircraft landing gear. This is done by measuring strains in the lower end of the strut, by which we infer the loading in the entire landing gear structure. These strains can be very large (as high as 10,000 microstrain) and can be imposed in numerous random directions and levels. The present invention includes a removable sensor assembly. An electromechanical means is presented that can accommodate large strains, be firmly attached to the strut, and provide good accuracy and resolution. | 01-19-2012 |
20110309192 | TORQUE LINK WITH SHIMMY DAMPER - A torque link includes a spring-damper system structurally incorporated into the design and functionality of the torque link. The spring portion may take the form of a structurally rigid beam while the damping portion may take the form of a damping mechanism or assembly. The damping mechanism is configured to damp out deformations in the beam and also configured to bottom out and become a structural tension/compression member when the load through the torque link exceeds a threshold load. The method damping may take a number of forms, such as, but not limited to, solid media damping, fluid damping with or without an orifice, a hydraulic or magnetic circuit, coulomb damping, etc. | 12-22-2011 |
20110278394 | ELECTRICALLY POWERED DOWNLOCK ACTUATION SYSTEM - An electrically-powered downlock actuation system for a landing gear that does not convert rotary motor output into linear motion during the actuation process, but instead uses the rotary motor output to directly drive a locking mechanism coupled to upper and lower landing gear braces. The electrically-powered downlock actuation system may include an electric motor, a gearbox (optional), a clutch (optional) and a fixed link to replace a hydraulically powered downlock actuation system. Further, the electrically-powered downlock actuation system may be controlled with motor control electronics that cooperate with one or more sensors arranged to detect a position of an output shaft. | 11-17-2011 |
20110275266 | SYSTEM AND METHOD FOR TEXTILE POSITIONING - A circular needle loom comprises a stationary bed plate for receiving a spiral textile. Engagement members may be disposed next to the stationary bed plate, such that the engagement members interface with a positional structure of the spiral textile that is used to position and rotate the spiral textile around the stationary bed plate. A conical roller deploys the spiral textile on the stationary bed plate. The engagement members rotate the spiral textile around the stationary bed plate until a predetermined number of layers are deposited on the stationary bed plate. | 11-10-2011 |
20110273313 | Infrared Communication System For Activating Power Drive Units In An Aircraft Cargo Loading System - An air cargo loading system also includes a controller, a main control panel and a plurality of PDUs (PDUs), at least the controller and the PDUs being connected by a wired network. Each PDU has a motor, at least one driver roller element coupled to said motor, a light source, a light detector, and a processor. The light detector of each PDU is configured to receive and process an incoming coded light signal from a wireless remote control handset. The PDU's processor determines whether the received coded light signal is a valid command signal and, if so, provides a command information signal to the controller via the wired network. The controller decodes the command information signal and, in view of its knowledge of container locations, various switch settings and other status information, the controller then sends the appropriate control signals to turn on the required PDUs in response thereto. Because wireless remote handsets are used to communicate with the controller, the air cargo system may either be wholly devoid of local control panels or, have only a very small number of local control panels. | 11-10-2011 |
20110220763 | TAPERED BRAKE DISK - A brake stack comprises a stator having an annular, inner periphery section disposed substantially along a first radial plane extending normal to an axis of a wheel, and a stator side wall having a first stator contact surface, the first stator contact surface including a sloped portion which deviates away from the radial plane defined by the annular, inner periphery section. The brake stack further comprises a rotor having an annular, outer periphery section disposed substantially along a second radial plane extending normal to the axis of the wheel, and a rotor side wall having a first rotor contact surface shaped complementary to the first stator contact surface, wherein the stator and the rotor are interleaved. | 09-15-2011 |
20110215192 | LANDING GEAR STEERING SYSTEMS - A steering system for aircraft landing gear can be used, for example, for controlling one or more axles of a bogie style landing gear system, such as, but not limited to, a six-wheel bogie style landing gear system. The steering system includes a rack having a plurality of rack teeth. An actuator is operatively connected to move the rack in a linear direction. A pinion has a plurality of pinion teeth in meshing engagement with the rack teeth. The pinion includes a pinion body extending between the pinion teeth and a pinion pivot that is spaced apart from the pinion teeth. The actuator, rack, and pinion are configured and adapted so that linear motion of the rack imparted by the actuator results in rotation of the pinion about the pinion pivot for steering landing gear wheels. | 09-08-2011 |
20110214601 | System for indicating an airplane hard landing - An indicator assembly for an aircraft landing gear for providing indication of a hard landing. The indicator assembly including a actuator member movable when the pressure on a shock strut of the aircraft landing gear exceeds a desired load and stroke threshold indicative of a hard landing. A shear pin is coupled to the actuator member which is configured to shear when a desired level of force is applied to at least a portion of the shear pin. A visibly recognizable indictor is moved from a non-indicating position to an indicating position upon shearing of the shear pin. | 09-08-2011 |
20110214496 | SYSTEMS AND METHODS FOR BUILT IN TEST EQUIPMENT FOR A BRAKE CONTROL SYSTEM - A method is disclosed that comprises severing an I/O channel between a brake system controller and an aircraft component; sending a test signal to the brake system controller; receiving, from the brake system controller, a feedback signal to the test signal; and determining an appropriateness of the feedback signal. A system is disclosed that comprises a brake system controller wrapped in a BITE region, wherein the BITE region comprises a testing module, a safety interlock region having an I/O channel between the brake system controller and another system, and a testing module capable of sending a test signal to the brake system controller. | 09-08-2011 |
20110209955 | SHOCK STRUT WITH PRESSURE RELIEF - A shock strut includes a relief device that reduces the internal pressure within a sealed chamber of the shock strut when a load condition that exceeds a maximum operating load condition is encountered. The reduced pressure permits a telescopically moving piston of the shock strut to be received into a corresponding cylinder to an amount that increases the structural capability of the shock strut, especially with respect to applied side loads that generate bending and shearing stresses in the shock strut. In one embodiment, the reduced pressure permits the piston to “bottom out” relative to the cylinder, which is a condition not otherwise achievable without the relief device. This additional stroke achievable by the piston reduces or eliminates the need to reinforce and thus add weight to the shock strut because of higher load condition design requirements. | 09-01-2011 |
20110180524 | Electrothermal Heater Made From Thermally Conducting Electrically Insulating Polymer Material - Thermally conductive films, composite materials including the films, and electrothermal heaters including the films, are disclosed. The films include a polymer and a sufficient concentration of hexagonal boron nitride to provide adequate heat transfer properties, and have high thermal conductivity, peel strength, and shear strength. The films can include thermoset polymers, thermoplastic polymers, or blends thereof, and can also include electrically conductive materials, reinforcing materials such as fiberglass, carbon fiber, metal mesh, and the like, and thermally conductive fillers, such as aluminum oxide, aluminum nitride, and the like. The films can be included in composite materials. The films can be used as part of a layered structure, and used in virtually any application, for example, various locations in aircraft, where heating is desirable, including nacelle skins, airplane wings, heated floor panels, and the like. The electrothermal heaters provide a more even heat, and a more rapid heat, than current resistive heaters formed from metal foils adhered to an adhesive film. | 07-28-2011 |
20110176903 | METHOD AND APPARATUS FOR CONVERTING AIRCRAFT FROM COMMERCIAL TO MILITARY FREIGHT SERVICE - A method and apparatus for converting aircraft from civilian cargo to CRAF use includes a pallet guide attached to the cargo deck of the aircraft. The pallet guide includes a pair of L-shaped structural channel members that are arranged back-to-back and staggered longitudinally along the length of the aircraft cargo deck. The L-shaped guide members are staggered back-to-back to enable military 463 L pallets to be guided along both the port and starboard sides of the pallet guide with one row of pallets loaded transverse to the centerline and one row of pallets loaded parallel to the centerline. The pallet guide includes a third guide member comprising a substantially T-shaped body displaced laterally with respect to the L-shaped guide members. For loading and unloading standard commercial pallets, the L-shaped guide members are rotated into a retracted position below the deck height of the cargo deck. The T-shaped guide member are then be moved from a retracted position below the deck height to a deployed position to engage the edges of the commercial pallets. | 07-21-2011 |
20110155943 | FLAME SUPPRESSANT AEROSOL GENERANT - The present invention is directed to pyrotechnic aerosol fire suppression compositions that burn rapidly, but coolly. The rapid burning of the compositions of the present invention produces a voluminous flame-suppressive aerosol that is useful in suppressing and/or extinguishing both small and large fires. The compositions of the invention contain at least one oxidizer and a fuel component comprising at least one organic acid salt, which combination produces a rapid burning composition that burns at low temperatures with little or no flame and have a low heat of combustion. | 06-30-2011 |
20110153176 | SYSTEMS AND METHODS FOR ADAPTIVE DECELERATION - Systems and methods for adaptive deceleration are disclosed. A brake system controller may perform a method comprising receiving a pedal deflection signal comprising a pedal deflection level, determining a present level of deceleration, and mapping the pedal deflection level to a desired level of deceleration, wherein the desired level of deceleration is greater than the present level of deceleration. | 06-23-2011 |
20110150594 | Air Cargo Centerline Restraint System Having Restraints Mounted Over Floor Joists Outside the Wingbox Area for Lateral Support - A cargo loading system capable of retaining a pallet along a centerline of a cargo aircraft and outside the wingbox area of the aircraft includes a number of devices. Included among these are first and second centerline end restraints mounted on the centerline, at least one caster panel mounted on one side of the cargo hold and across the centerline from a side door of the aircraft, and a plurality of mechanical restraints mounted on a floor of the cargo hold on either side of the centerline and outside the wingbox area. The first and second centerline end restraints each have at least one retractable lockhead configured and dimensioned to engage an end of a pallet. The at least one caster panel includes at least one retractable guide formed at a first end thereof, and at least one retractable guide formed along a first side thereof. Lastly, the plurality of mechanical restraints are mounted with a portion of each mechanical restraint overlying a laterally extending floor joist in the cargo hold, such that a lateral load applied to a given mechanical restraint is transferred to at least one laterally extending floor joist. | 06-23-2011 |
20110148616 | SYSTEMS AND METHODS FOR COMPREHENSIVE TIRE PRESSURE MONITORING AND WHEEL SPEED DETECTION - Systems and methods facilitate the monitoring of tire pressure, the detection/determination of wheel speed, or a combination thereof. A system is provided comprising a hub cap, a target coupled to the hub cap, and at least two displacement sensors configured to measure a displacement between each displacement sensor and the target. The target has a variable thickness, and the target comprises a hollow vessel in fluid communication with a tire. | 06-23-2011 |
20110148396 | SYSTEMS AND METHODS FOR COMPREHENSIVE TIRE PRESSURE MONITORING AND WHEEL SPEED DETECTION - Systems and methods facilitate the monitoring of tire pressure, the detection/determination of wheel speed, or a combination thereof. A system is provided comprising a hub cap, a target coupled to the hub cap, and at least two displacement sensors configured to measure a displacement between each displacement sensor and the target. The target has a variable thickness, and the target comprises a hollow vessel in fluid communication with a tire. | 06-23-2011 |
20110146045 | Air Cargo Centerline Restraint System Having Restraints Mounted Over Floor Joists Outside the Wingbox Area for Lateral Support - A cargo loading system capable of retaining a pallet along a centerline of a cargo aircraft and outside the wingbox area of the aircraft includes a number of devices. Included among these are first and second centerline end restraints mounted on the centerline, at least one caster panel mounted on one side of the cargo hold and across the centerline from a side door of the aircraft, and a plurality of mechanical restraints mounted on a floor of the cargo hold on either side of the centerline and outside the wingbox area. The first and second centerline end restraints each have at least one retractable lockhead configured and dimensioned to engage an end of a pallet. The at least one caster panel includes at least one retractable guide formed at a first end thereof, and at least one retractable guide formed along a first side thereof. Lastly, the plurality of mechanical restraints are mounted with a portion of each mechanical restraint overlying a laterally extending floor joist in the cargo hold, such that a lateral load applied to a given mechanical restraint is transferred to at least one laterally extending floor joist. | 06-23-2011 |
20110126640 | MONOLITHIC MAGNETO-STRICTIVE LOAD TRANSDUCER - A load sensor is provided comprising a magnetostrictive material and a wire. The magnetostrictive material may comprise an aperture, a first face, a second face, a thickness, and a first dado. The wire is disposed at least partially in the first dado, wherein the first dado at least partially transverses at least one of the first face and the second face, wherein the wire at least partially transverses the first face and the second face. The load sensor may also comprise a magnetostrictive material comprising an aperture, a first face, a second face, a thickness, and a first channel, and a wire disposed at least partially in the first channel, wherein the first channel at least partially transverses at least one of the first face and the second face, wherein the wire at least partially transverses the first face and the second face. | 06-02-2011 |
20110104041 | METHODS AND SYSTEMS FOR HCN REMOVAL - Hydrogen cyanide removal during transformation of a carbon fiber precursor into carbon fiber is provided. The method may comprise heating a carbon fiber body precursor at a substantially atmospheric pressure to above about 1200° C. in a furnace in a first stage, expelling a stream of effluent gas outside the furnace, wherein the stream of effluent gas comprises a cyanide, thermally oxidizing the cyanide during the first stage, and heating the carbon fiber body precursor to a temperature of between about 1600° C. and about 2200° C. in a second stage. | 05-05-2011 |