| GOODRICH CORPORATION Patent applications |
| Patent application number | Title | Published |
|---|
| 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 |
| 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 |
| 20110104031 | METHODS AND APPARATUS FOR RESIDUAL MATERIAL MANAGEMENT - Residual impurity reduction methods and apparatus are provided. A method comprises conducting a gaseous stream through an unlined portion of a pipe, wherein the gaseous stream comprises sodium and wherein the unlined portion of the pipe is at least about eighteen inches long, injecting a neutralizing agent into the gaseous stream at an injection point, wherein the injection point is located at a point where the sodium is in at least a partially condensed state. The gaseous stream is conducted through a heated portion of a pipe and a cooled portion of a pipe. In addition, methods and apparatus may include a trap system for use with a carbonization furnace. | 05-05-2011 |
| 20110049292 | LIGHTNING STRIKE PROTECTION - An aircraft component having an external surface includes an improved lightning strike protection surface film disposed on or proximate to the external surface. The surface film includes a preform that includes a substrate having a first areal weight density and a plurality of spaced carbon nanotubes grown on the substrate, the nanotubes having a second areal weight density. The sum of the first areal weight density and the second areal weight density is less than about 500 grams per square meter, and the preform has a surface resistance less than about 1 ohm/square. | 03-03-2011 |
| 20110002752 | AIR CARGO ROLLOUT STOP - A cargo rollout stop includes a base having a first end and a second end. A first guide head is movably mounted to the base proximate to the first end, and a second guide head is movably mounted to the base proximate to the second end. The guide heads each are movable between a raised blocking position and a lowered non-blocking position. A blocking member is movably mounted to the base, and is disposed between the guide heads. The blocking member includes a first portion engaged with the first guide head, and a second portion engaged with the second guide head, and is movable between a first position and a second position. The first and second portions prevent substantial downward movement of the guide heads when the guide heads are in their raised blocking positions and the blocking member is in its first position. The guide heads are restrained in their lowered non-blocking positions by the blocking member when the blocking member is in its second position. | 01-06-2011 |
| 20110001086 | Methods of making nanoreinforced carbon fiber and components comprising nanoreinforced carbon fiber - Methods for enhancing the strength and stiffness of fibers, including nanoreinforced fibers and fiber tows, composite materials including the nanoreinforced fibers and tows, and articles of manufacture including the composite materials, are disclosed. The methods involve adhering random or aligned nanoreinforcement materials, such as carbon nanotubes, nanofibers, graphene plates, nanowires, nanoparticles, into or onto a spread carbon tow or yarn to form modified fibers wherein nanoreinforcement is adhered or trapped within the carbon tow. The carbon nanotubes or nanofibers can be aligned. Carbon fiber tows including the modified carbon fibers can be processed or woven for impregnation with a thermoset resin or thermoplastic to form a composite structure. The performance increase of the modified fibers relative to the unmodified fibers can be greater than the weight increase caused by the modification. Increased fiber stiffness and strength can result in a significant weight saving. | 01-06-2011 |
| 20100316460 | 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. | 12-16-2010 |
| 20100286881 | BRAKE WEAR CONTROL SYSTEM - A system, apparatus and method provide a means for managing wear of brake friction material such that even friction material wear is experienced between brakes. The available friction material of each brake is monitored to determine an amount of wear. Based on the amount of wear, a braking force applied by each brake may be varied to ensure even wear between brakes. | 11-11-2010 |
| 20100286880 | AUTOBRAKE AND DECEL CONTROL BUILT-IN TEST EQUIPMENT - A system, apparatus and method provide a means for testing operation of a vehicle brake system. More particularly, a brake controller for controlling operation of the brake system includes a signal generator that can generate data indicative of wheel speed. Based on a user command, the controller uses either actual wheel speed data or simulated wheel speed data as inputs for controlling brake operation. The controller also includes logic for exercising various braking functions so as to enable maintenance personal to determine operational systems of the brake system. | 11-11-2010 |
| 20100282377 | METHODS FOR TREATING HIGH-STRENGTH, LOW-ALLOY STEEL - A method for treating high-strength, low-alloy steel includes controlling material responses, such as the crystal structure of the steel, through various processing steps. More specifically, the method includes cold treating the steel to achieve predictable increases in a minimum ultimate tensile strength or desired changes in the crystal structure of the steel. In one embodiment, cold treating the steel operates to controllably increase the minimum ultimate tensile strength of the steel within increasing a specified maximum ultimate tensile strength of the steel. Stated otherwise, cold treating the steel may reduce or narrow a minimum-to-maximum ultimate tensile strength range such that the minimum ultimate tensile strength is closer to the specified maximum ultimate tensile strength. | 11-11-2010 |
| 20100281967 | OVER-SPEED, ROUGH LOADS AND HARD LANDING DETECTION SYSTEM - A system, apparatus and method provide a means for indicating an overload condition has occurred during aircraft operation. The occurrence of an overload condition is automatically determined and an indication output thereof. Based on the indication received by the cockpit, avionics, maintenance, etc., further action may be taken to correct the effects of the overload condition on the tires and/or landing gear. | 11-11-2010 |
| 20100280725 | DISTRIBUTED PEDAL SYSTEM FOR AIRCRAFT - A braking system that can reduce wiring without sacrificing performance. The system includes a data concentrator in the form of a distributed sensor processor unit for receiving braking command signals from a plurality of sensors and, based on the command signals, generating a brake control signal to be sent to a brake system control unit via a serial connection or the like. | 11-04-2010 |
| 20100276989 | BRAKE FILL EFFECT MINIMIZATION FUNCTION - A brake fill effect minimization function for preventing or reducing brake controller windup during a brake fill condition or the like that may commonly occur in hydraulic or electromechanical brake systems, particularly during initial application of the brakes or during anti-skid conditions. The function temporarily reduces error input to the brake controller during a perceived brake fill condition (hydraulic brakes) or running clearance condition (electromechanical brakes) thereby facilitating smooth application of the brakes during initial braking and/or under anti-skid conditions. | 11-04-2010 |
| 20100276988 | 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. | 11-04-2010 |
| 20100276233 | SYSTEM TO ELIMINATE ELECTRIC ACTUATOR CONTAMINATION - A system to reduce or eliminate brake actuator contamination by providing a clean air source for the actuator such that a volume of a void in the actuator can vary without introducing moisture and/or contaminants into the actuator. A movable wall moves in response to changes in the volume of the void of the actuator to compensate for the changes without drawing moisture or contaminants into the actuator housing. By reducing or eliminating actuator contamination the service life of the actuator can be extended. | 11-04-2010 |
| 20100266770 | OXIDATION INHIBITION OF CARBON-CARBON COMPOSITES - The disclosed invention relates to a method and a composition for treating a porous carbon-carbon composite with an oxidation inhibiting composition. The oxidation inhibiting composition comprises at least one phosphate glass. In one embodiment, the method optionally further comprises pretreating the composite with a pretreating composition prior to application of the oxidation inhibiting composition. Carbon-carbon composites treated by the foregoing method are disclosed. | 10-21-2010 |
| 20100266424 | INFLATION ASPIRATOR WITH COLLAPSIBLE BARREL - An aspirator for inflating an aircraft evacuation slide, emergency raft or other inflatable device includes a flexible, collapsible aspirator barrel that is inflated during operation to form a substantially rigid tube. According to one embodiment, the inflatable support member receives a flow of high pressure air directly from the aspirator injector nozzle assembly. According to another embodiment, the collapsible aspirator barrel receives a flow of high pressure gas directly from the high pressure inflation source. Because the aspirator barrel of the present invention is collapsible, the present invention occupies significantly less space when stored than an equivalent aspirator with a rigid aspirator barrel. | 10-21-2010 |
| 20100252678 | GROUND SENSING SYSTEM - A ground sensing system for an aircraft attaches to the aircraft's landing gear to provide a ground touch indication. The ground sensing system includes a bracket, an upper arm, a lower arm, a roller and a sensor. The bracket is mounted to the landing gear while the upper arm is pivotally and biasly coupled to the bracket. The lower arm is pivotally and biasly coupled to the upper arm. The roller mounts to the lower arm and extends just slightly beneath a lowermost surface of the tire when the aircraft is airborne. The sensor is triggered once a portion of the upper arm has sufficiently entered the sensor's field of view, which occurs when the roller is urged upward by the ground during landing. | 10-07-2010 |
| 20100228430 | SYSTEM AND METHOD TO DETERMINE BRAKE PEDAL SENSOR FAILURE - Systems and methods for determining aircraft brake pedal sensor failure are provided. A brake pedal sensor and/or a brake pedal may be “failed” if brake pedal sensor readings unlikely to be generated as a result of human input are detected. The method comprises acquiring brake pedal measurements from a brake pedal sensor, determining a state of the brake pedal sensor, and providing a notification of the state. Each brake pedal measurement comprises a brake pedal deflection amount. The brake pedal sensor test algorithm may be conducted at regular intervals, in preparation for aircraft landing, at the request of a human operator, and the like. | 09-09-2010 |
| 20100225503 | SYSTEM AND METHOD FOR DETECTING A DRAGGING BRAKE - Systems and methods to determine whether a brake is dragging based on post-takeoff spindown data are provided. The method comprises measuring spindown of a wheel to obtain spindown data. The spindown data is compared with a spindown envelope, and notification is provided if the spindown data indicates a wheel is spinning down outside a spindown envelope. | 09-09-2010 |
| 20100221427 | 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 include a dual aperture release system and/or allow vapor material to flow both substantially horizontally and substantially vertically. | 09-02-2010 |
| 20100219290 | ELECTRIC-POWERED TRANSFER CYLINDER FOR LANDING GEAR SYSTEM - A shock strut for an aircraft landing gear having a retract actuator that is moveable in length to deploy or retract the landing gear, that includes a shrink strut and a transfer device. The shrink strut may be compressed in length for stowage in the fuselage. The transfer device may be in closed fluid communication with the strut shrink for transferring and receiving hydraulic fluid to and from the strut shrink. When actuated by an aircraft hydraulic or electric system independent of any motion of the retract actuator, the transfer device may drive hydraulic fluid to the strut shrink thereby compressing or shrinking the shrink strut to a partially compressed length. | 09-02-2010 |
| 20100213313 | INTEGRATED AIRCRAFT CARGO LOADING AND CARGO VIDEO MONITORING SYSTEM - An integrated cargo loading and video monitoring system for an aircraft having at least one cargo compartment is disclosed. The system includes a cargo loading processor and a plurality of power drive units within the cargo compartment, each power drive unit being coupled to the cargo loading processor. The system also includes a video processor, and at least one video camera within the cargo compartment, the camera being coupled to the video processor. A central processor in communication with the cargo loading processor and the video processor is operable to receive information from both the cargo loading processor and from the video processor. | 08-26-2010 |
| 20100209209 | 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. | 08-19-2010 |
| 20100207618 | NON-CONTACT SENSOR SYSTEM AND METHOD FOR VELOCITY DETERMINATION - A non-contact sensor system is provided that comprises a first sensor element disposed within a first member having an axis Y, and a second member configured to rotate about the axis Y at a value X. The second member is configured to interface with the first member. The non-contact sensor system further comprises a second sensor element disposed on the second member proximate the first sensor element without physically contacting the first sensor element, and the first sensor element and the second sensor element are operatively coupled to facilitate sensing the value X. The non-contact sensor system may be configured to sense velocity, acceleration, and other values. | 08-19-2010 |
| 20100207613 | 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 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. | 08-19-2010 |
| 20100207609 | NON-CONTACT SENSOR SYSTEM AND METHOD FOR SELECTION DETERMINATION - A non-contact sensor system is provided that comprises a first sensor element disposed on a stationary member, and a second sensor element disposed on a rotational member. The second sensor element is proximate the first sensor element without physically contacting the first sensor element. The rotational member is configured to facilitate selection of at least a first position and a second position, and the first sensor element and the second sensor element are operatively coupled to facilitate sensing of the selected position. | 08-19-2010 |
| 20100207608 | NON-CONTACT SENSOR SYSTEM AND METHOD FOR POSITION DETERMINATION - A non-contact sensor system is provided that comprises a first sensor element disposed on an outside surface of a chamber. The chamber comprises an inside surface configured to receive a piston, and the piston is configured to move a value X within the chamber without physically contacting the first sensor element. The non-contact sensor system further comprises a second sensor element disposed on the piston and separated from the first sensor element by a wall of the chamber. The first sensor element and the second sensor element are operatively coupled to facilitate sensing the value X. The non-contact sensor system may be configured to sense velocity, acceleration, volume, and other values. | 08-19-2010 |
| 20100206671 | BRAKE WEAR MEASUREMENT SYSTEM AND METHOD - A brake measurement system comprising a measurement mechanism for measuring brake wear operatively coupled to a moveable member of a brake assembly is provided. The system further includes a displacement sensor and a visual indicator. The displacement sensor is operatively coupled to the measurement mechanism, wherein movement of the moveable member is converted by the measurement mechanism into a displacement sensed by the displacement sensor. The visual indicator is operatively connected to the measurement mechanism, wherein the visual indicator displays the movement of the moveable member and consequently the wear of the brake stack at a point on the exterior of an aircraft brake housing for inspection. | 08-19-2010 |
| 20100194179 | THERMAL MANAGEMENT COMPOSITE HEAT SHIELD - A thermal management system and methods for use are disclosed. The thermal management system comprises a shield portion and a dissipation portion. The shield portion may comprise a hot side skin, a conduction layer, an insulation layer, and a cool side skin. The dissipation portion may comprise a fin array. Heat absorbed by the shield portion is partially or fully conducted to the dissipation portion for transfer to the ambient environment. The thermal management system may be employed as an aircraft wheel heat shield, an automotive brake heat shield, a gas turbine heat shield, an electronic heat sink, and in various other applications where heat shielding and/or heat transfer are desirable. | 08-05-2010 |
| 20100179045 | METHODS AND APPARATUS RELATING TO A COMPOSITE MATERIAL - A composite material having a fibrous structure and a coating is disclosed. More specifically, a composite material may be comprised of a fibrous structure having a surface and impregnated with a interface material, a first ceramic material, a ceramic mixture, and a third ceramic material or alloy material or combination thereof, a coating disposed on the surface of the fibrous structure, wherein the coating comprises a first ceramic coating material and a ceramic coating mixture. | 07-15-2010 |
| 20100140027 | ASYMMETRICAL BRAKE TORQUE PLATE BACK LEG - A brake comprising a brake disk stack including stators alternating with rotors that are rotatable relative to the stators about an axis of the disk stack, an annular torque plate at one axial end of the brake disk stack, and a circumferential arrangement of actuators at the other axial end of the brake disk stack for urging the brake disk stack against the torque plate thereby to effect a braking force on the rotors. A back leg ( | 06-10-2010 |
| 20100134981 | Heat sink assembly having interdigitated cooling fins - A heat sink assembly including a first heat sink sub-assembly in thermal contact with a first heat source and including spaced apart columns of spaced horizontal fins extending outwardly from the first heat source, and a second heat sink sub-assembly in thermal contact with a second heat source and including spaced apart rows of space vertical fins extending outwardly from the second heat source, wherein the spaced apart columns of spaced horizontal and the spaced apart rows of spaced vertical fins are arranged in an interdigitated manner. | 06-03-2010 |
| 20100117447 | FAULT TOLERANT AIRCRAFT BRAKING CONTROL USING ALTERNATE WHEEL SPEED INFORMATION - A method for providing anti-skid braking control for a vehicle having a plurality of wheels, each wheel including a corresponding wheel speed sensor and brake, wherein when velocity data from at least one wheel speed sensor is lost, velocity data from a wheel speed sensor coupled to a different wheel is used as the wheel speed for the wheel with the non-operational sensor. | 05-13-2010 |
| 20100110431 | APPARATUS AND METHOD FOR IN-FLIGHT DETECTION OF AIRBORNE WATER DROPLETS AND ICE CRYSTALS - A device for optically detecting and distinguishing airborne liquid water droplets and ice crystals includes an illumination portion and a detection portion. The illumination portion outputs a circularly polarized illuminating beam. The detection portion receives circularly polarized backscattered light from moisture in the cloud, in response to the illuminating beam. The circularly polarized backscattered light is passed through a circular polarizer to convert it into linearly polarized backscattered light, which is split into two components. Each of the two components is optionally subject to further linear polarization to filter out any leakage-type orthogonal polarization. The two components are then optically detected and the resulting detection signals are used to calculate one or more parameters reflective of the presence or absence of airborne ice crystals and/or water droplets. | 05-06-2010 |
| 20100106347 | 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. | 04-29-2010 |
| 20100101068 | REPAIR OF ELECTRIC AIRCRAFT BRAKE - A method for enabling removal and replacement of a failed actuator module of a brake assembly that includes multiple actuators ( | 04-29-2010 |
| 20100100225 | INTEGRATED AIRCRAFT CARGO LOADING AND MONITORING SYSTEM - A cargo loading and monitoring system for an aircraft having a plurality of separate cargo compartments includes a processor in communication with a plurality of power drive units located within a first cargo compartment. A cargo monitoring display unit is located in a second cargo compartment that is separate from the first cargo compartment, and is in communication with the processor. The cargo monitoring display unit is configured to selectively display information received from the power drive units. | 04-22-2010 |
| 20100078517 | LANDING GEAR WITH LOCKING STEERING SYSTEM - A landing gear system for an aircraft comprises a truck beam ( | 04-01-2010 |
| 20100070150 | AIRCRAFT BRAKE CONTROL ARCHITECTURE HAVING IMPROVED ANTISKID REDUNDANCY - An electromechanical braking system includes first and second electromechanical actuator controllers (EMACs) that each independently generate a complete set of drive control signals for an associated set of electromechanical actuators (EMAs). The drive control signals are generated in accordance with an antiskid algorithm to impart antiskid control to the braking of wheels associated with the EMAs. Drive signals for some of the EMAs from the set of EMAs are output by drivers of the first EMAC and drive signals for the other EMAs from the set of EMAs are output by drivers of the second EMAC. Drive control signals from one of the EMACs are used to control output the drive signals for all the EMAs from the set of EMAs, regardless of the EMAC in which the associated drivers are present. The drive control signals from the other of the EMACs are used as a backup set of drive control signals. | 03-18-2010 |
| 20100055466 | OXHIDATION INHIBITION OF CARBON-CARBON COMPOSITES - A method of inhibiting oxidation of a porous carbon-carbon composite is disclosed and comprises the steps of: (a) contacting the carbon-carbon composite with an oxidation inhibiting composition comprising phosphoric acid or an acid phosphate salt, at least one aluminum salt, and at least one additional metal salt, the oxidation inhibiting composition penetrating at least some of the pores of the carbon-carbon composite; and (b) heating the carbon-carbon composite at a temperature sufficient to form a deposit from the oxidation inhibiting composition within at least some of the penetrated pores of the carbon-carbon composite. The foregoing oxidation inhibiting composition and carbon-carbon composites treated by the foregoing method are also disclosed. | 03-04-2010 |
| 20100054889 | ATTENUATED CARGO CASTER - A caster for use in aircraft along a cargo deck comprises a housing having at least one wall, a pivot assembly, a brake assembly and at least one spring. A pivot assembly can have at least one wall, first and second ends, and a base between the first and second ends, wherein the first end of the pivot assembly can be elevated above the second end of the pivot assembly. The wall of the pivot assembly can be rotatably linked to the wall of the housing. An optional brake assembly can be on the first end of the pivot assembly. At least one spring can be on the second end of the pivot assembly. A cover on or above the at least one spring can be secured to the wall of the housing. | 03-04-2010 |
| 20100051863 | OXHIDATION INHIBITION OF CARBON-CARBON COMPOSITES - A method of inhibiting oxidation of a porous carbon-carbon composite is disclosed and comprises the steps of: (a) contacting the carbon-carbon composite with an oxidation inhibiting composition comprising phosphoric acid or an acid phosphate salt, at least one aluminum salt, and at least one additional metal salt, the oxidation inhibiting composition penetrating at least some of the pores of the carbon-carbon composite; and (b) heating the carbon-carbon composite at a temperature sufficient to form a deposit from the oxidation inhibiting composition within at least some of the penetrated pores of the carbon-carbon composite. The foregoing oxidation inhibiting composition and carbon-carbon composites treated by the foregoing method are also disclosed. | 03-04-2010 |
| 20100038475 | ICE PROTECTION SYSTEM FOR A MULTI-SEGMENT AIRCRAFT COMPONENT - An aircraft component includes a first segment having a first leading edge surface that extends to a first end of the first segment. The aircraft component also includes a second segment having a second leading edge surface that extends to a second end of the second segment. The second end is substantially adjacent to the first end of the first segment, and is connected to the first end. The first leading edge surface includes electrical resistance heating that extends to the first end of the first segment. In addition, the second leading edge surface includes electrical resistance heating that extends to the second end of the second segment. The electrical resistance heating is capable of providing ice protection heating immediately on either side of a juncture between the connected first and second ends. | 02-18-2010 |
| 20100038188 | AIRCRAFT BRAKE ACTUATION MEASUREMENT UNIT - A compact aircraft brake actuation measurement unit ( | 02-18-2010 |
| 20100037441 | METHOD AND SYSTEM FOR ENABLING Z FIBER TRANSFER IN NEEDLED PREFORM - A method for preparing a needled preform comprises transporting, cutting and needling a textile tape. The method further comprises cutting through a portion of the textile tape with a cutting device. The textile tape remains substantially contiguous after the cutting. The method further comprises needling the textile tape into a needled preform after cutting the textile tape, and the needling utilizes needles having working surfaces oriented in a direction to transfer fiber segments from a selected fiber orientation into a z-direction. In an embodiment, a system for enabling z-fiber transfer in a textile tape comprises a textile support configured to transport the textile tape, a cutting device configured to cut a portion of the textile tape, and a needling device configured to needle the textile tape into a needled preform after the cutting device cuts the textile tape. | 02-18-2010 |
| 20100025172 | SEGMENTED HEAT SHIELD ASSEMBLY - A heat shield assembly for a wheel and brake assembly ( | 02-04-2010 |
| 20100017052 | 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. | 01-21-2010 |
| 20090324356 | 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. | 12-31-2009 |
| 20090321560 | ADJUSTABLE LANDING GEAR SYSTEM - A landing gear system includes a shock strut assembly and a linkage member coupled to an aircraft. Preferably, the shock strut assembly and linkage member are oriented or angled relative to one another in a non-parallel relationship. Actuation of the linkage member moves the shock strut from a de-hiked to a hiked configuration or vice-versa. In addition, the orientation of the linkage member relative to the shock strut assembly permits it to automatically move the shock strut assembly to the de-hiked position during retraction of the landing gear system and prevents the shock strut assembly from exceeding a desired length during retraction. The linkage member may take the form of a hydraulic actuator having a lower end portion coupled to an inner cylinder of the shock strut assembly and an upper end portion coupled to the aircraft aft of where the shock strut assembly is coupled to the aircraft. | 12-31-2009 |
| 20090278401 | ELECTROMECHANICAL BRAKE SYSTEM WITH DISTRIBUTED ARCHITECTURE - A brake system of a vehicle includes a plurality of electromechanical brake actuators (EBAs) proximate the wheels of the vehicle. Each EBA includes a power device for effectuating braking of an associated wheel, and electronics to generate a drive signal for the power device. The brake system may further include at least one brake control unit (BCU) for converting a brake command signal into a control signal for each EBA. The electronics for each EBA may be configured to convert the corresponding control signal into the drive signal that is applied to the power device to cause movement of the power device and effectuate braking of the vehicle. | 11-12-2009 |
| 20090277260 | WHEEL AND BRAKE ASSEMBLY - A wheel and brake assembly ( | 11-12-2009 |
| 20090276133 | AIRCRAFT BRAKE CONTROL SYSTEM AND METHOD - A method includes receiving an input brake command that indicates a desired amount of braking for a vehicle. A brake control signal is then derived from the input brake command to facilitate applying a braking force to a wheel of the vehicle, and the braking force facilitates achieving the desired amount of braking for the vehicle. The method further comprises determining that data from a sensor associated with the wheel is unavailable, and then modifying the brake control signal in response to determining that the data is unavailable. The modification may be based on sensor data or controller output associated with a second wheel where data is available. Such modification facilitates the desired amount of braking for the vehicle. | 11-05-2009 |
| 20090274532 | CARGO RESTRAINT TIE DOWN - A tie down for securing objects in an aircraft having a roller tray can comprise a tie-fitting, a carriage, and protruding elements. A carriage can include at least one side wall with protruding elements extending from the side wall of a carriage to cooperate with a roller tray. The protruding elements removably secure the tie down to a selected location along the roller tray. A restraint extending from an object can be removably secured to a tie down. The tie down being vertically insertable and removable by hand operation and without the use if tools or mechanical fasteners. | 11-05-2009 |
| 20090230242 | AIR CARGO ROLLOUT STOP - A cargo rollout stop includes a base, and a guide head pivotally mounted to the base. The guide head is movable between a raised blocking position, and a lowered non-blocking position. A retraction pedal is pivotally mounted to the guide head, and is movable between a first position and a second position relative to the guide head. The retraction pedal permits downward rotation of the guide head from its raised blocking position to its lowered non-blocking position when the retraction pedal is in its second position, and blocks downward rotation of the guide head from its raised blocking position to its lowered non-blocking position when the retraction pedal is in its it first position. | 09-17-2009 |
| 20090217748 | 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. | 09-03-2009 |
| 20090152058 | BRAKE LINING CUP ATTACHMENT METHOD FOR REDUCED WEAR - A brake lining assembly is provided for improved useful life. A brake lining assembly may comprise a carrier disk, a brake lining cup secured to the carrier disk and filled with a brake lining material, wherein the segmented brake lining cup has a center, wherein the brake lining material is secured to the carrier disk with an attachment fastener through the lining material and the brake lining cup, and wherein the attachment fastener is offset from the center. | 06-18-2009 |
| 20090121085 | 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. | 05-14-2009 |
| 20090121084 | Infrared Communication Power Drive Unit and Method for Activating Same 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. | 05-14-2009 |
| 20090120767 | CARGO POWER DRIVE UNIT WITH UNIFORM BI-DIRECTIONAL DRIVE TRACTION - A power drive unit for propelling cargo containers and pallets in a desired direction over a plurality of cargo deck roller elements includes an elongated yoke having a pivot end and an opposite end. The pivot end is pivotally connected to a deck support structure. A drive roller is rotatably mounted to the yoke. At least one resilient member is disposed between the opposite end of the yoke and the support portion of the deck structure. A drive motor coupled to the drive roller selectively rotates the drive roller in two opposed directions. A reaction member connected to the drive motor is at least partially movably engaged with the deck support structure to permit at least some pivotal movement of the yoke, and to substantially prevent rotation of the drive motor relative to the yoke. | 05-14-2009 |
| 20090108131 | RETRACTABLE ARTICULATED LANDING GEAR - A landing gear for an aircraft, characterized by upper and lower pintle frame members ( | 04-30-2009 |
| 20090071763 | HEAT SHIELD ASSEMBLY FOR AIRCRAFT WHEEL AND BRAKE ASSEMBLY - A heat shield assembly for a wheel and brake assembly includes one or more torque bars that include a coupling device which cooperates with a portion of a heat shield (and more particularly heat shield sections) at a location axially outwardly remote from the inboard end of the heat shield so as to restrain radial outward movement of the heat shield. In another embodiment, the heat shield assembly includes heat shield carriers between which respective heat shield sections are axially inserted, and retainers are removably secured with respect to the carriers for blocking axial withdrawal of the heat shield sections from respective carriers. In another embodiment, heat shield carriers include a reversely bent edge portion defining a capture slot, and at least one aperture in the bent edge portion. A heat shield section has at one side thereof a first tab portion circumferentially inserted in the capture slot and at an opposite side thereof a second tab portion engaged in the aperture. | 03-19-2009 |
| 20090016839 | AIR CARGO ROLLOUT STOP - A cargo rollout stop includes a base having a first end and a second end. A first guide head is movably mounted to the base proximate to the first end, and a second guide head is movably mounted to the base proximate to the second end. The guide heads each are movable between a raised blocking position and a lowered non-blocking position. A blocking member is movably mounted to the base, and is disposed between the guide heads. The blocking member includes a first portion engaged with the first guide head, and a second portion engaged with the second guide head, and is movable between a first position and a second position. The first and second portions prevent substantial downward movement of the guide heads when the guide heads are in their raised blocking positions and the blocking member is in its first position. The guide heads are restrained in their lowered non-blocking positions by the blocking member when the blocking member is in its second position. | 01-15-2009 |
| 20090016838 | AIR CARGO ROLLOUT STOP - A cargo rollout stop includes a base, and a guide head pivotally mounted to the base. The guide head is movable between a raised blocking position, and a lowered non-blocking position. A retraction pedal is pivotally mounted to the guide head, and is movable between a first position and a second position relative to the guide head. The retraction pedal permits downward rotation of the guide head from its raised blocking position to its lowered non-blocking position when the retraction pedal is in its second position, and blocks downward rotation of the guide head from its raised blocking position to its lowered non-blocking position when the retraction pedal is in its it first position. | 01-15-2009 |
| 20080310944 | POWER DRIVE UNIT WITH ECCENTRIC ROLLER LIFT SYSTEM - A cargo power drive unit (PDU) includes a housing, and a shaft rotatably mounted in the housing. The shaft has a longitudinal axis, an end, and a spindle outwardly extending from the end. The spindle is radially offset from the longitudinal axis. The PDU further includes a lift roller having a center axis, and having an opening that is radially offset from the center axis. The spindle is non-rotatably received in the opening of the lift roller. When the shaft rotates in the housing and the lift roller contacts a stationary support beneath the housing, at least a portion of the housing is lifted away from the stationary support by the roller. | 12-18-2008 |
| 20080308390 | POWER DRIVE UNIT WITH ECCENTRIC ROLLER LIFT SYSTEM - A cargo power drive unit (PDU) includes a housing, and a shaft rotatably mounted in the housing. The shaft has a longitudinal axis, an end, and a spindle outwardly extending from the end. The spindle is radially offset from the longitudinal axis. The PDU further includes a lift roller having a center axis, and having an opening that is radially offset from the center axis. The spindle is non-rotatably received in the opening of the lift roller. When the shaft rotates in the housing and the lift roller contacts a stationary support beneath the housing, at least a portion of the housing is lifted away from the stationary support by the roller. | 12-18-2008 |
| 20080304931 | OVERRIDEABLE GUIDE AND VERTICAL RESTRAINT FOR AN AIR CARGO SYSTEM - A centerline restraint includes a conventional center guide/restraint and a pair of a overrideable guide/restraint at either end. Each overrideable guide/restraint is lockable into one of three rotational positions about a common axis: a retracted position, an erect position and an overridden position. The overrideable guide/restraint has a yoke-shaped body with a pair of legs rotatably mounted on an axle which, in turn, is mounted on a base of the centerline restraint. Lift handles, each operatively connected to a spring-loaded plunger are used to adjust the overrideable guide/restraint between the three positions. A head of the spring-loaded plunger abuts one or more stops formed on the legs of the overrideable guide/restraint to lock the overrideable guide/restraint in various predetermined positions. Lift handles operatively connected to the plungers, when operated, cause the overrideable guide/restraint to switch between positions. | 12-11-2008 |
| 20080251348 | HYBRID INFLATOR WITH TEMPORARY GAS GENERATOR THROTTLE - A dual stage hybrid inflation device includes a first stage gas source comprising a liquefied gas stored in a first stage pressure vessel and a second stage gas source comprising a gas generator having a gas output directed into the first stage pressure vessel. The gas generator is isolated from the first stage pressure vessel by a frangible diaphragm that ruptures when the pressure in the gas generator exceeds the pressure in the first stage pressure vessel by a predetermined amount. The gas generator is also isolated from the first stage pressure vessel by an eroding nozzle that temporarily restricts the flow of gas from the gas generator to the first stage pressure vessel after the frangible diaphragm ruptures. The eroding nozzle initially restricts the flow of gas from the gas generator to the first stage pressure vessel to prevent a sudden pressure drop in the gas generator that would cause the pyrotechnic gas generating material to self extinguish. The nozzle then erodes away to allow an unrestricted flow of combustion products from the gas generator to the first stage pressure vessel. | 10-16-2008 |
| 20080232730 | Diaphragm bearing hanger assembly - A bearing hanger assembly for coupling rotating shaft components is disclosed which includes a mounting assembly for mounting the bearing hanger assembly to a supporting structure, a bearing assembly for supporting axial rotation of coupled shaft components, and a flexible diaphragm plate supported by the mounting assembly and operatively connected to the bearing assembly so as to accommodate misalignment of the coupled shaft components relative to the supporting structure. | 09-25-2008 |
