The Boeing Company Patent applications |
Patent application number | Title | Published |
20160141825 | AIR COOLED LASER SYSTEMS USING OSCILLATING HEAT PIPES - Provided are air cooled laser systems, such as portable air cooled laser systems, and methods of operating thereof. An air cooled laser system includes an oscillating heat pipe having one end thermally coupled to one or more laser diodes and the other end being air cooled. The oscillating heat pipe has an extremely high thermal conductivity (e.g., much higher than that of copper) which allows using ambient air for cooling. This air cooling aspect reduces the size, weight, and complexity of the system. Furthermore, the air cooling aspect reduces power consumption since no power is used for liquid circulation. To enhance air-cooling characteristics, the end of the oscillating heat pipe away from the diodes may be thermally coupled to one or more heat dissipating fins. Furthermore, the system may be equipped with a blower for controlling the flow of air around that end. | 05-19-2016 |
20160141063 | LASER COOLING VIA STIMULATED PHOTON EMISSIONS - An example laser cooling system may include a first laser to induce a transition of a plurality of electrons in a medium to an excited energy state via absorption of photons. The laser cooling system may also include a second laser to stimulate emission from the medium of emitted photons having a higher energy than an energy of the absorbed photons. | 05-19-2016 |
20160139254 | Short-Range Point Defense Radar - A multi-beam frequency-modulated continuous wave (FMCW) radar system designed for short range (<20 km) operation in a high-density threat environment against highly maneuverable threats. The multi-beam FMCW system is capable of providing continuous updates, both search and track, for an entire hemisphere against short-range targets. The multi-beam aspect is used to cover the entire field of regard, whereas the FMCW aspect is used to achieve resolution at a significantly reduced computational effort. | 05-19-2016 |
20160138958 | Optical Impedance Modulation for Fuel Quantity Measurement - Systems and methods that use an optical impedance sensor that eliminates electricity for measuring fuel quantity in fuel tanks. The optical impedance sensor comprises two optical fibers spaced apart inside a meniscus tube, one to transmit light along its length and the other to receive light along its length. The meniscus tube minimizes the sloshing of fuel level. The fuel level in the tank modulates the optical impedance between the two optical fibers, resulting in changes in the total light received by an optical detector. Depending on fuel tank height, the optical impedance sensor may comprise different embodiments in which the detection apparatus shapes the light to be unidirectional (emitted and collected only on one side of the fiber) or omnidirectional (all directions). | 05-19-2016 |
20160138913 | DETACHABLE PROTECTIVE COVERINGS AND PROTECTION METHODS - A detachable hazard detection device includes a protective covering configured to detachably couple to an article. A plurality of proximity sensors are coupled to the protective covering. Each of the plurality of proximity sensors is configured to gather proximity information. Electronics are embedded in the protective covering, and the electronics include a controller coupled to the plurality of proximity sensors. The controller is configured to determine a proximity of the article to an object based on the proximity information. The controller is further configured to initiate a notification based on the proximity. | 05-19-2016 |
20160138737 | FIREPROOF FLEXIBLE HOSES WITH POLYIMIDE INNER STRUCTURES - Provided are fireproof flexible hoses, aircraft having fire suppression systems including such fireproof flexible hoses, and methods of forming such fireproof flexible hoses. A fireproof flexible hose includes an inner structure and an outer structure at least partially enclosing and directly interfacing the inner structure. The inner structure forms an inner surface of the fireproof flexible hose and includes a polyimide at least at the inner surface. The polyimide has good fireproofing and temperature resistant characteristics and, unlike other polymers, does not need to be thermally isolated when the hose is exposed to fire. The outer structure may be made from metal and/or non-metal and may provide mechanical support to the inner structure. The outer structure may have a convoluted shape to ensure flexibility of the overall hose assembly. In some examples, a set of gaps may be present between the outer and inner structures for additional flexibility. | 05-19-2016 |
20160138156 | CARBON-BASED BARRIER COATINGS FOR HIGH-TEMPERATURE POLYMER-MATRIX COMPOSITES - A high-temperature polymeric-matrix composite (HTPMC) structure and a method for protecting an HTPMC from exposure to high temperatures in the presence of air, and prevent thermo-oxidative degradation. A thin, lightweight layer of a carbon-based barrier is applied onto a surface of the HTPMC structure. The carbon-based barrier coating is composed of graphene, amorphous carbon, or a mixture comprising a combination of graphene and amorphous carbon, and has coefficient of thermal expansion that is less than 10 times the coefficient of thermal expansion of the HTPMC structure. The carbon-based barrier may be coated with an erosion-barrier. | 05-19-2016 |
20160137300 | AIRCRAFT INTERIOR MODULE SUPPORT SYSTEM INCLUDING SHARED FITTINGS - An aircraft fuselage comprises a support structure, a first interior module having a first support arm, a second interior module having a second support arm, and a support system for suspending the first and second interior modules from the support structure. The support system includes a shared fitting for releasably attaching to the first and second support arms of the first and second interior modules. The shared fitting is configured to react a first rotational force when the first support arm is attached and the second support arm is released. The shared fitting is configured to react a second rotational force when the second support arm is attached and the first support arm is released. | 05-19-2016 |
20160137287 | Structural Arrangement and Method of Fabricating A Composite Trailing Edge Control Surface - The present disclosure is generally directed to a composite trailing edge control surface including a contiguous one-piece composite control surface skin wrapped around a plurality of stiffening cores, a plurality of hinge fittings, and a plurality of substantially parallel ribs. The contiguous one-piece composite control surface skin provides a control surface on opposing sides of the trailing edge control surface and substantially distributes bending, shear and torsion loads of the trailing edge control surface to the plurality of hinge fittings and the plurality of substantially parallel ribs. A method of manufacturing the trailing edge control surface includes positioning a contiguous one-piece composite control surface skin on a substantially flat tool. A plurality of stiffener cores having a plurality of thin covering skins are positioned on the contiguous one-piece composite control surface skin and are cured to create a laminate sandwich composite structure skin that is trimmed and has fastener apertures and hinge fitting access apertures provided there-through. | 05-19-2016 |
20160137285 | Enhancing aerodynamic performance of an aircraft wing assembly - Disclosed is a method of enhancing aerodynamic performance of an aircraft wing assembly including a fixed section and a foldable section. The foldable section is hinged to the fixed section at a hinge axis. The method includes turning a torque box extending from the foldable section to rotate the foldable section about the hinge axis from a stowed position to a deployed position. | 05-19-2016 |
20160136857 | SEAL MOLDING SYSTEM - A seal molding system may include a mold body having a mold inner geometry formed complementary to a fitting outer geometry of a fitting. The mold body may have a mold base formed complementary to a panel surface. The mold body may include an injection hole for injecting sealant into the mold cavity, and a vent hole for venting air and sealant from the mold cavity. | 05-19-2016 |
20160136754 | FRICTION STIR WELD PLUGS AND METHODS OF USING THEREOF - In one aspect of the disclosure, an article for filling an opening in an object includes a plug having a body, a first flange, and a second flange. The plug has a trailing end. The first flange is in contact with the body and extends away from the body. The second flange is in contact with the first flange and extends away from the first flange and the body. The second flange is configured to deform toward the body upon installation of the plug into the opening. This deformation of the second flange rotationally and translationally secures the plug in the opening and consolidates the plug in the opening. | 05-19-2016 |
20160134126 | Methods for Steering a Magnetic Field for Smart Wireless Power Transmission - Systems and methods for mitigating constraints associated with wireless power transmission in applications where the position and orientation of the desired magnetic field changes over time, for example, because the position and orientation of the receiver being powered changes over time or because different receivers having different positions and orientations are being powered at different times. In accordance with some embodiments, the system employs a plurality of wireless power transmitters in a defined space, each transmitter consisting of individual coils oriented orthogonally relative to each other. Using field interference amongst these individual coils as well as amongst the transmitters they form, one can actively control the wireless power field intensity and orientation at any given point in the defined space. This allows for methods to steer the power transmission towards a specific target at a specific angle. | 05-12-2016 |
20160133137 | TURBULENCE DETECTION AND MONITORING - A turbulence detection and monitoring system may include a data processing system configured to collect and analyze motion-related sensor data from a plurality of personal electronic devices onboard an aircraft in flight. The personal electronic devices may communicate with the data processing system at least in part via an onboard wireless network. | 05-12-2016 |
20160132748 | Hyperspectral Resolution Using Three-Color Camera - A method for capturing hyperspectral images using a regular color camera. In the method, the camera takes multiple images of a scene, with the camera oriented differently for each image. For a camera carried by an aircraft or spacecraft, this allows hyperspectral imaging without the cost or weight of a hyperspectral camera. | 05-12-2016 |
20160127387 | Method for Combining Multiple Signal Values in the Dendritic Cell Algorithm - Artificial Immune Systems (AIS) including the Dendritic Cell Algorithm (DCA) are an emerging method to detect malware in computer systems. A DCA module may receive an output or signal from multiple indicators concerning the state of at least a portion of the system. The DCA module is configured to combine the plurality of signals into a single signal vector. The DCA module may be configured to sort the received signals based on signal type and magnitude of each signal. The DCA module may then use a decay factor to weight the received signals so that a large number of “nominal” signals do not drown out a small number of “strong” signals indicating a malware attack. The decay factor may be exponentially increased each time it is applied so that all received signals are considered by the DCA module, but so that the “nominal” signals may have a minimal effect. | 05-05-2016 |
20160123938 | PREDICTIVE ANALYSIS OF COMPLEX DATASETS AND SYSTEMS AND METHODS INCLUDING THE SAME - Predictive analysis of complex datasets and systems and methods including the same are disclosed herein. The methods include analyzing airborne particle count data from a cleanroom environment to predict a particle count fault condition within the cleanroom environment. The methods further include generating an airborne particle count data repository that includes particle counts within the cleanroom environment, analyzing the airborne particle count data to calculate a difference between a first rate of change and a second rate of change, and predicting the particle count fault condition responsive to the difference between the first rate of change and the second rate of change being outside a predetermined threshold range difference. The systems include computer readable storage media including computer-executable instructions that, when executed, direct a data analysis system to perform the methods. The systems also include a distributed cleanroom particle count monitoring system including a plurality of detection nodes. | 05-05-2016 |
20160123369 | WITNESS ENABLED FASTENERS AND RELATED SYSTEMS AND METHODS - A fastening device may include a first member configured for forceful engagement with a second member. The first member may include a sensor configured to emit at least a first photo-luminescent signal to a detector when at least a predetermined first torque level is applied to the first member when the first and second members are engaged. | 05-05-2016 |
20160122000 | SYSTEM AND METHOD FOR OPTIMIZING HORIZONTAL TAIL LOADS - A method of controlling an elevator of an aircraft may include identifying a current stabilizer angle of incidence of a stabilizer of the aircraft. The stabilizer may include an elevator pivotably coupled to the stabilizer. The method may further include comparing the current stabilizer angle of incidence with a threshold stabilizer angle of incidence, and selecting an elevator position limit that is more restrictive if the current stabilizer angle of incidence is greater than or equal to the threshold stabilizer angle of incidence. The method may additionally include moving the elevator to a commanded elevator position that is no greater than the elevator position limit. | 05-05-2016 |
20160121996 | Spoiler for an Aircraft Bay - A method for managing an airflow of an aircraft. A spoiler is moved into the airflow passing a bay of the aircraft when the bay is open. The airflow moving relative to the bay is changed to form a desired airflow using louvers physically associated with a frame system in the spoiler. | 05-05-2016 |
20160121994 | ROLLER COVERS AND ASSEMBLIES - Roller covers for use with cylindrical rollers include an elongate flexible hollow body defining an interior space with an opening to the interior space for receiving the cylindrical roller via the opening, a first restrictive feature extending from the body and configured to restrict rotation of the body in a first rotational direction when the cylindrical roller is received in the interior space, and a second restrictive feature extending from the body and configured to restrict rotation of the body in a second and opposite rotational direction when the cylindrical roller is received in the interior space. Some embodiments further include a third restrictive feature positioned relative to the body and configured to restrict linear translation of the body relative to the cylindrical roller when the cylindrical roller is received in the interior space. | 05-05-2016 |
20160121447 | DRILL GUIDES FOR RIGHT ANGLE DRILLS - Drill guides for right angle drills include an elongate base, a fore guide, a fore mount, an aft guide, and an aft mount. The fore mount and the aft mount are configured to be operatively coupled to a right angle drill, and the fore guide and the aft guide are configured to permit selective translation of the right angle drill toward and away from the base. | 05-05-2016 |
20160116301 | GYRO RATE COMPUTATION FOR AN INTERFEROMETRIC FIBER OPTIC GYRO - A method comprises supplying an optical input to an interferometric fiber optic gyro (IFOG) at a first frequency and then a different second frequency; detecting a difference in responses of the IFOG to the optical input at the first and second frequencies; and computing a gyro rate as a function of the difference and a correction term. | 04-28-2016 |
20160115872 | ENGINE INSTALLATION USING MACHINE VISION FOR ALIGNMENT - Installation of an engine to a support structure includes temporarily attaching first and second alignment structures to the support structure and the engine. One of the alignment structures has a target pattern on its surface. The installation further includes using a machine vision system from the other of the mounting structures to indicate the relative position of the target pattern with respect to a reference. The relative position of the target pattern with respect to the reference provides information about relative position of an engine mounting element (e.g., bolt hole) with respect to a corresponding mounting element (e.g., bolt hole) in the support structure. The relative position of the target pattern with respect to the reference can be used to maneuver the engine in order to align the mounting elements. | 04-28-2016 |
20160115721 | SYSTEM AND METHOD FOR INTEGRATED MAGNETIC SLIDER ASSEMBLY FOR HANGING PARTITION - There is provided a system for an integrated magnetic slider assembly. The system has the integrated magnetic slider assembly with a slider portion, a hanger portion coupled to or integrated with the slider portion, and one or more magnets coupled to the hanger portion. The system further has a longitudinal hanging device configured for coupling to and suspending the slider portion of the integrated magnetic slider assembly. The system further has at least one hanging partition configured for coupling to the hanger portion of the integrated magnetic slider assembly, the at least one hanging partition having a plurality of pleats. All the magnets in a plurality of integrated magnetic slider assemblies are vertically aligned with respect to each other to cause a magnetic attraction between adjacent magnets in order to hold the plurality of pleats together, when the at least one hanging partition is in a retracted position. | 04-28-2016 |
20160114883 | ACTIVELY-CONTROLLED SUPERHYDROPHOBIC SURFACES - Active superhydrophobic surface structures are actively-controlled surface structures exhibiting a superhydrophobic state and an ordinary state. Active superhydrophobic surface structures comprise an outer elastomeric covering defining an exposed surface, a controlled group of MEMS (micro-electro-mechanical system) actuators at least covered by the elastomeric covering, and, a controlled region of the exposed surface corresponding to the controlled group. The controlled region has a superhydrophobic state in which the controlled region is textured. The controlled region also has an ordinary state in which the controlled region is smooth (i.e., less textured than in the superhydrophobic state). Active superhydrophobic surface structures may be part of an apparatus that includes a controller and/or one or more sensors. The controller, sensors, and the controlled region may form a feedback loop in which the active superhydrophobic surface is actively controlled. | 04-28-2016 |
20160112071 | MULTIBAND WIRELESS DATA TRANSMISSION BETWEEN AIRCRAFT AND GROUND SYSTEMS BASED ON AVAILABILITY OF THE GROUND SYSTEMS - Provided are methods and systems for multiband wireless data transmission between aircraft and ground systems. The transmission uses different wavelength ranges, each wavelength range corresponding to a different data domain and establishing a different communication channel. This wavelength differentiation provides physical separation between different data domains and, as a result, improves data security. Furthermore, a single broadband antenna is used on the exterior of the aircraft for transmitting data sets from different data domains. The single antenna configuration reduces drag and weight and improves structural integrity of the aircraft in comparison to multi-antenna configurations. Different aircraft communication modules, which are connected to different aircraft systems, handle different data domains and operate at different wavelength ranges. These modules are connected to the same antenna using a multiplexer. This connection may be controlled using gate devices and may be conditioned on verification of communication channel availability, security status, and other factors. | 04-21-2016 |
20160107864 | DEVICES AND METHODS FOR HANDLING RADIUS FILLERS - Devices and methods for handling uncured radius fillers are disclosed. The devices, i.e., radius filler transport tools, generally are configured to load a radius filler from above, to index the radius filler to a desired location (e.g., a cavity), and to downwardly unload (e.g., drop) the radius filler at the desired location. Radius filler transport tools comprise at least two trough portions, coupled together to form a trough to carry the radius filler, and a plurality of hanger assemblies configured to transversely span the trough. The radius filler transport tool may have a transport state, where the trough and the hanger assemblies are in closed states, a load state, where the trough is in the closed state and at least one hanger assembly is in an open state, and an unload state, where the trough is in an open state and the hanger assemblies are in closed states. | 04-21-2016 |
20160107432 | METHOD OF MANUFACTURING A VARIABLE-RADIUS LAMINATED RADIUS FILLER - A method of forming a radius filler may include providing an upper portion having substantially constant width composite plies, providing a base portion as a stack of variable width composite plies, and stacking the upper portion onto the base portion to form a radius filler stack. | 04-21-2016 |
20160107429 | HEATED TOOL ASSEMBLY FOR FORMING A STRUCTURAL MEMBER - A heated tool assembly for forming a structural member may include a heated tool and a pressure bladder for mounting the structural member. The tool may have an inner surface, a liner in thermal contact with the inner surface of the tool, and a heating system for heating the tool. The heating system may include a heater for heating a heated medium, a blower for blowing the heated medium, and a plurality of nozzles for directing the heated medium over the tool liner. | 04-21-2016 |
20160107413 | TAILORED COEFFICIENT OF THERMAL EXPANSION OF COMPOSITE LAMINATES USING FIBER STEERING - Provided are assemblies, each including a first structure having a uniform coefficient of thermal expansion (CTE) and a second composite structure having a variable CTE. Also provided are methods of forming such assemblies. The second structure has overlap, transition, and baseline regions. The overlap region directly interfaces the first structure and has a CTE comparable to that of the first structure. The baseline region is away from the first structure and has a different CTE. Each of these CTEs may be uniform in its respective region. The transition region may interconnect the baseline and overlap regions and may have gradual CTE change from one end to the other. The CTE variation with the second composite structure may be achieved by changing fiber angles in at least one ply extending through all three regions. For example, any of the plies may be subjected to fiber steering. | 04-21-2016 |
20160107298 | APPARATUS AND METHOD FOR THE INSTALLATION OF A THERMOFORMABLE FASTENER ASSEMBLY AT A PREDETERMINED PRELOAD TORQUE VALUE - An apparatus and its method of use enables a thermoplastically deformable fastener assembly to be deformed to hold an installation preload torque after the fastener has been torqued to a predetermined value. | 04-21-2016 |
20160107236 | METHODS OF MAKING PARTS FROM AT LEAST ONE ELEMENTAL METAL POWDER - One aspect of the disclosure relates to a method of making a part from at least one elemental metal powder. The part has a near-net shape, a part volume, and a part density. The method includes providing a sintered preform having a sintered density and separating a portion from the sintered preform. The portion has a portion volume exceeding the part volume and a portion shape different from the near-net shape of the part. The method also includes thermally cycling the portion for a thermal-cycling time period at a thermal-cycling pressure while superplastically deforming the portion to form the part having the near net shape and the part density. | 04-21-2016 |
20160107235 | SYSTEMS AND METHODS FOR FORMING NEAR NET-SHAPE METAL PARTS FROM BINDERLESS METAL POWDER - Systems and methods for forming near net-shape metal parts from binderless metal powder are disclosed. Systems include a mold die that defines a die cavity and may include one or more ultrasonic transducers operatively coupled to the mold die. Systems may be configured to introduce binderless metal powder into a die cavity and/or to compact the binderless metal powder within the die cavity. Methods include introducing binderless metal powder into a die cavity of a mold die and compacting the binderless metal powder within the die cavity to form a green part within the die cavity. The binderless metal powder may include spheroidal metal particles and angular metal particles. The methods may further include separating the green part from the mold die and sintering the green part, after separating, to form a sintered near net-shape metal part. | 04-21-2016 |
20160105929 | APPARATUS FOR CURING COMPOSITE MATERIALS AND METHOD OF USE THEREOF - An apparatus may include a curing apparatus and an electrical coupler. The curing apparatus may include one or more electrical components related to curing a composite material inside a vacuum chamber at least partially defined by a flexible wall. The electrical coupler may be connected to the curing apparatus. The coupler may include a first set of one or more electrical contacts electrically connected to the one or more electrical components of the curing apparatus inside the vacuum chamber. The coupler may be configured to hermetically extend through a hole in the flexible wall. Such extension may dispose the first set of one or more electrical contacts in a space outside of the vacuum chamber for electrical interconnection of the one or more electrical components of the curing apparatus inside the vacuum chamber with circuitry disposed in the space outside of the vacuum chamber. | 04-14-2016 |
20160104358 | METHOD AND SYSTEM TO ENABLE SELECTIVE SMOKE DETECTION SENSITIVITY - There is provided a method to enable selective smoke detection sensitivity onboard an aircraft. The method has the step of installing one or more sensitivity selectable smoke detector assemblies. The method further has the step of electrically or wirelessly coupling the one or more sensitivity selectable smoke detector assemblies installed onboard the aircraft to one or more sensitivity selector controls installed onboard the aircraft. The method further has the step of selecting an alarm setpoint sensitivity level from two or more alarm setpoint sensitivity levels for each of the one or more sensitivity selectable smoke detector assemblies, based on sensitivity level determination factors of one or more of a mission type of the aircraft, a cargo type on the aircraft, a compartment zone specific area type on the aircraft, and an occupancy state on the aircraft. | 04-14-2016 |
20160103320 | OPTICAL DESIGN OF A WIDE FIELD OF VIEW PUPIL FORMING HUD - A head up display or HUD system, including methods and apparatus, suitable for use in a flight simulator. According to the present teachings, a flight simulator HUD may be configured to produce a HUD image that appears superimposed on a simulated cockpit field of view image, and which has substantially the same relatively short focal distance from the user as the simulated image. A simulator HUD according to the present teachings does not require any holographic optical elements or an unrealistic cockpit volume, and provides an accurate simulation of conditions in a real aircraft cockpit. | 04-14-2016 |
20160103216 | USING FREQUENCY DIVERSITY TO DETECT OBJECTS - Technologies for detecting a passive object through the use of frequency diversity to find at least a resonant peak are disclosed. For example, a radar system may illuminate a suspect area with a pulsed radio wave based on a large number of frequency bands and based on parameters associated with the passive object. The reflected radio wave may be processed to generate synthetic aperture radar (SAR) maps associated with the frequency bands. The SAR maps may be analyzed and compared to determine large deviation amplitudes that may indicate a location of the passive object. | 04-14-2016 |
20160102973 | METHOD AND SYSTEM FOR DETERMINING AND VERIFYING PLY ORIENTATION OF A COMPOSITE LAMINATE - A method for determining and verifying ply orientation of composite laminates includes performing a first scan of a prepared edge of a composite laminate using an off-axis inclined light source directing light at a first acute angle to a first area on the prepared edge to produce a first scanned image; rotating an orientation of the off-axis inclined light source relative to the prepared edge, such that the off-axis inclined light source directs light at a second acute angle symmetrically opposite the first acute angle; and performing a second scan of the prepared edge using the off-axis inclined light source directing light at the second acute angle to the first area on the prepared edge to produce a second scanned image. The method includes comparing the first and second scanned images to determine a ply orientation of each ply, and verifying the ply orientation against a baseline ply orientation. | 04-14-2016 |
20160102966 | SYSTEMS AND METHODS FOR FIBER PLACEMENT INSPECTION DURING FABRICATION OF FIBER-REINFORCED COMPOSITE COMPONENTS - The disclosed systems and methods relate to inspecting uncured fiber-reinforced composite components by non-contact 3D measurements of the component using 3D digital image correlation with patterned illumination. Systems comprise a light projector configured to project a light pattern onto a form, a digital camera configured to image the light pattern, and may comprise and/or be associated with an AFP machine that is configured to lay uncured composite on the form. Methods comprise projecting a light pattern onto a form, acquiring a baseline 3D profile of the form by imaging the light pattern on the form, laying an uncured fiber piece onto the form, projecting the light pattern onto the uncured fiber piece, acquiring a test 3D profile of the fiber piece by imaging the light pattern on the uncured fiber piece, and computing a thickness difference between the test 3D profile and the baseline 3D profile. | 04-14-2016 |
20160101543 | Hybrid Laminate and Molded Composite Structures - A hybrid composite structure includes a molded thermoplastic composite component and a laminate thermoplastic composite component co-welded together. The molded component is reinforced with discontinuous fibers, and the laminate component is reinforced with continuous fibers. | 04-14-2016 |
20160096637 | Automated Non-Destructive Inspection of Surface Skins Using Transporter System - Systems and methods for automated maintenance of the top and bottom surfaces or skins of an integrally stiffened hollow structure (e.g., a horizontal stabilizer) using surface crawling vehicles. Each system uses dynamically controlled magnetic coupling to couple an external drive tractor to a pair of passive trailers disposed in the interior of the hollow structure on opposite sides of a vertical structural element. The external drive tractor is also coupled to an external maintenance tool, which the tractor pushes or pulls across the surface skin to perform a maintenance function. The systems allow maintenance operations to be performed on both surface skins without turning the hollow structure over. Each system is modular and can be transported to and easily set up in a building or factory. | 04-07-2016 |
20160096289 | Methods and Apparatus for Curing Composite Nacelle Structure - Methods and apparatus for curing curved cylinder-like workpieces (e.g., in the shape of a half or full barrel) made of composite material, such as nacelle honeycomb core composite sandwich structures. These methods enable tailored curing of composite nacelle structures, to significantly reduce capital cost and fabrication cycle time. In lieu of an autoclave or oven, a pressurized ring-shaped cure volume is defined by a partitioned enclosure that mimics the cylinder-like shape of the composite nacelle structure with only limited clearance (e.g., a partitioned enclosure comprising inner and outer concentric cylinder-like walls). A tool (e.g., a mandrel) and at least one composite nacelle structure supported thereon are placed in the cure volume for curing. Integrally heated tooling, optionally in combination with other heating methods, such as infrared heaters, is utilized to provide the temperature profile necessary for cure. | 04-07-2016 |
20160090455 | POLYMER NANOPARTICLES FOR CONTROLLING RESIN REACTION RATES - A composition may include a thermosetting resin containing a plurality of polymer nanoparticles. At least some of the polymer nanoparticles may release either a catalyst or a hardener during a resin curing process. The catalyst or hardener may alter the reaction rate of the resin. | 03-31-2016 |
20160089856 | COMPOSITE STRUCTURES HAVING REDUCED AREA RADIUS FILLERS AND METHODS OF FORMING THE SAME - A composite structure having a base charge and an outer channel charge is provided. The outer channel charge has an inner radius and an outer radius. A charge of plies adjacent to the inner radius reduces the inner radius. | 03-31-2016 |
20160089851 | NONWOVEN DECORATIVE LAMINATES AND METHODS OF MAKING THE SAME - A decorative laminate for application to a structural component is provided. The decorative laminate has a substrate layer of a nonwoven fabric material with or without a flame retardant material. The decorative laminate further has an embossable layer disposed upon the substrate layer. The embossable layer includes an embossing resin material and the flame retardant material. The decorative laminate further has a protective layer disposed upon the embossable layer. The protective layer includes a polyvinyl fluoride-based material and has a decorative material printed on a first side of the protective layer facing the embossable layer. An adhesive layer is applied to the substrate layer of the decorative laminate. The decorative laminate is applied to the structural component with the substrate layer facing a bonding surface of the structural component and with an adhesive layer applied between the decorative laminate and the bonding surface of the structural component. | 03-31-2016 |
20160089843 | IN-SITU ANNEALING OF POLYMER FIBERS - A method of manufacturing a composite article may include attaching a polymer element to a tool. The polymer element may be pre-stretched prior to attachment to the tool. The method may further include annealing the polymer element at a predetermined temperature while constraining a length of the polymer element using the tool. In addition, the method may include curing or solidifying resin associated with the polymer element. The annealing step may be performed prior to the curing or solidifying step. Alternatively, the annealing step may be performed concurrently with the curing or solidifying step. | 03-31-2016 |
20160085027 | TAPERED OPTICAL MIXING RODS - An optical transmission device includes a tapered mixing rod that includes an optically transmissive material and has a first face, a second face, and a length. A size of the first face is based on a first number of optical fibers and a size of the second face is based on a second number of optical fibers, where the size of the first face is different from the size of the second face. The length can be selected such that light entering the first face from one of the first number of optical fibers is distributed substantially uniformly across the second face and such that light entering the second face from one of the second number of optical fibers is distributed substantially uniformly across the first face. | 03-24-2016 |
20160084165 | PRE-COOLER INLET DUCTS THAT UTILIZE ACTIVE FLOW-CONTROL AND SYSTEMS AND METHODS INCLUDING THE SAME - Pre-cooler inlet ducts that utilize active flow-control and systems and methods including the same are disclosed herein. The systems include a pre-cooler inlet duct for a jet engine that is configured to receive a pre-cooler air stream and to direct the pre-cooler air stream into a heat exchanger. The pre-cooler inlet duct includes a flow-directing surface, which defines at least a portion of the pre-cooler inlet duct, and an active flow-control device. The active flow-control device is located to modify a boundary layer fluid flow within a boundary layer adjacent the flow-directing surface to resist separation of the boundary layer from the flow-directing surface when the pre-cooler air stream flows through the pre-cooler inlet duct. The methods include methods of resisting boundary layer separation in the pre-cooler inlet duct by flowing the pre-cooler air stream across the flow-directing surface and modifying the boundary layer with the active flow-control device. | 03-24-2016 |
20160083824 | Methods and Systems for Shape Memory Alloy Structures - There is provided a method of training a shape memory alloy (SMA) workpiece. The method includes applying a force couple to a shape memory alloy (SMA) workpiece to impart a generally planar transformational behavior to the SMA workpiece to obtain a trained shape memory alloy (SMA) workpiece. | 03-24-2016 |
20160083584 | NANOPARTICLES FOR IMPROVING THE DIMENSIONAL STABILITY OF RESINS - A composition may include the resin and a plurality of polymer nanoparticles included in the resin to form a resin mixture. The resin may have a resin coefficient of thermal expansion (CTE), a resin cure shrinkage, and/or a resin heat of reaction. The polymer nanoparticles may have a nanoparticle cure shrinkage less than the resin cure shrinkage, a nanoparticle CTE different than the resin CTE, and/or a nanoparticle heat of reaction less than the resin heat of reaction. | 03-24-2016 |
20160083583 | POLYMER NANOPARTICLE ADDITIONS FOR RESIN MODIFICATION - A composition may include a resin and a plurality of polymer nanoparticles included in the resin to form a resin mixture. The polymer nanoparticles may alter the properties of the resin mixture and improve the processing, manufacturability, and performance of an article manufactured with the polymer nanoparticles. | 03-24-2016 |
20160083536 | POLYMER NANOPARTICLES FOR CONTROLLING PERMEABILITY AND FIBER VOLUME FRACTION IN COMPOSITES - A fiber tow may include a plurality of reinforcing filaments each having a filament cross-sectional width. At least a portion of the polymer nanoparticles may be coupled to at least one of the reinforcing filaments and/or to other polymer nanoparticles. The polymer nanoparticles may have a particle cross-sectional width that is less than the reinforcing filament cross-sectional width. The polymer nanoparticles may provide a local filament spacing between the reinforcing filaments to reduce or avoid direct contact between reinforcing filaments, to allow for resin flow between the filaments, and/or to meet fiber volume fraction requirements. | 03-24-2016 |
20160083535 | PLACEMENT OF MODIFIER MATERIAL IN RESIN-RICH POCKETS TO MITIGATE MICROCRACKING IN A COMPOSITE STRUCTURE - A composite structure may include a resin, a fiber at least partially embedded within the resin, and one or more resin-rich pockets associated with the fiber. The composite structure may include modifiers in the one or more resin-rich pockets. The modifier may have at least one modifier characteristic that is different than a resin characteristic for altering the resin characteristics within the resin-rich pockets and thereby mitigating or preventing crack initiation or crack growth within the resin-rich pockets of the composite structure. | 03-24-2016 |
20160083112 | UAV Take-Off Method and Apparatus - A method and apparatus for launching unmanned air vehicles (UAVs) includes supporting the unmanned air vehicle on a surface vehicle, such as a dolly cart, for riding along a surface such as ground or water. A towline is connected to the surface vehicle and the towline is pulled to force the unmanned air vehicle in a forward direction at a speed sufficient for take-off. The towline may be pulled by a winch system. In some embodiments the UAV is positioned with a nose down angle on the surface vehicle. The nose down angle permits overspeed of the UAV and cart as it is pulled along the ground, as well as controlled take-off. | 03-24-2016 |
20160083072 | AIRCRAFT CABIN PRESSURE REGULATING SUBFLOOR - An aircraft cabin subfloor construction has flow paths through the subfloor that vent air pockets trapped beneath an air impermeable floor mat on the subfloor where, due to a difference in pressure in the air pockets trapped beneath the floor mat and the air in the aircraft cabin above the floor mat, the air pockets would create bubbles or buckling in the floor mat. The venting of the air pockets beneath the floor mat by the flow paths eliminates the problem of bubbling or buckling in the floor mat. | 03-24-2016 |
20160076968 | SYSTEMS AND METHODS FOR ICING FLIGHT TESTS - Systems and methods for the manufacture and use of artificial ice shapes for aircraft certification, including methods of manufacturing artificial ice shapes, artificial ice component systems for attachment to aircraft, methods of flight testing aircraft having artificial ice sections attached thereto, and artificial ice testing systems. | 03-17-2016 |
20160075125 | METHOD OF MANUFACTURING A SPIRAL LAMINATED STRUCTURAL CONE - A method of manufacturing a cone-shaped composite article may include providing unidirectional plies in a continuous arcuate shape in a flat pattern configured to wrap 360 degrees around a cone-shaped mandrel such that opposing ply ends of each unidirectional ply terminate at a ply seam. The method may further include laying up at least one inner sublaminate on the cone-shaped mandrel, the inner sublaminate containing at least four of the unidirectional plies having an inner stacking sequence with fiber angles of −45, 90, 0, +45 degrees such that the inner sublaminate has a quasi-isotropic layup at any location of the inner sublaminate. The method may additionally include laying up at least one outer sublaminate in an outer stacking sequence being a mirror image of the at least one inner stacking sequence. | 03-17-2016 |
20160075092 | PROCESS AND APPARATUS FOR HANDLING, INSTALLING, COMPACTING, SPLICING, AND/OR ASSEMBLING COMPOSITE STRINGERS - Methods of and systems for assembling stiffened composite structures are disclosed. Some methods include forming a stiffener assembly by compacting it within a trough formed in a trunnion. A single trunnion may accommodate two or more different types of stiffeners, thereby avoiding the need for multiple sets of tooling. In some methods, a plurality of stiffener segments may be spliced together, thereby avoiding the need to transport and handle an entire stiffener. A vacuum chuck may be utilized in some examples to transfer the stiffener assembly from the trunnion to a transfer tool. The same vacuum chuck may be transferred along with the stiffener assembly on the transfer tool and loaded onto an inner mold line layup mandrel, where the vacuum chuck may be used to compact the stiffener assembly to the inner mold line layup mandrel. | 03-17-2016 |
20160073048 | COORDINATING IMAGE SENSING WITH MOTION - A method may include generating one or more control signals configured to control a velocity of an image sensing system based on a rate of recording pixels frames in the image sensing system. In some embodiments, the method may alternatively or additionally include generating one or more control signals configured to control the rate of recording in the image sensing system based on the velocity of the image sensing system. In some embodiments, a portion of image pixel data for a pixel frame may be output for transmission to a remote receiver. In some embodiments, the output data may include a recently recorded image data pixel for those surface resolution cells for which there is no currently stored reference image data pixel of a previously recorded pixel frame that is the same or is different by less than a threshold amount as the recently recorded image data pixel. | 03-10-2016 |
20160069409 | TRANSLATIONAL TUNED MASS DAMPER WITH CONTINUOUSLY ADJUSTABLE DAMPING CHARACTERISTICS FOR APPLICATION TO HIGH SPEED WIND TUNNEL TESTING - A system, including methods and apparatus, of tuning a mass-damping apparatus to reduce dynamics forces on a wind tunnel model during wind tunnel testing. The mass-damping apparatus is coupled to a wind tunnel model and may comprise first and second pressure chambers containing a gas, a mass configured to move back and forth between the pressure chambers in a substantially airtight manner and thereby to alter gas pressure within each pressure chamber, at least one spring configured to exert a position-dependent force upon the mass, and a passageway configured to allow the gas to pass between the chambers. | 03-10-2016 |
20160068259 | WINGLET SYSTEM - A winglet system for an aircraft wing may include an upper winglet and a lower winglet mounted to a wing tip. The upper winglet root chord and the lower winglet root chord may each have a length of no greater than 100 percent of the wing tip chord. The lower winglet may have a static position when the wing is subject to an on-ground static loading. The lower winglet may be configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move upwardly and outwardly from the static position to an in-flight position resulting in an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under the on-ground static loading. | 03-10-2016 |
20160065300 | AIRCRAFT-NODED DATA COMMUNICATION NETWORK - Defined herein is a system for communicating data includes a first data source that transmits data through the air, and a second data source that is remote from the first data source. The second data source at least one of receives and transmits data through the air. The system further includes at least one aircraft that receives data through the air from the first and second data sources, and transmits data through the air to at least one of the first and second data sources. | 03-03-2016 |
20160061748 | SYSTEMS AND METHODS FOR DETECTING CRACK GROWTH - A system and method for detecting crack propagation in a material test specimen may include color contrasting a surface of a test specimen, acquiring a plurality of photographic images of the specimen during application of a stress load, processing the plurality of images to detect characteristics of pixels that are outside a baseline range of pixel characteristics indicative of a contrast between a crack in the test specimen and the color contrasted surface of the test specimen, and generating an output of a strain energy release rate based on changes in detected crack length over time. | 03-03-2016 |
20160061250 | BARREL NUT WITH STRESS REDUCTION FEATURES - A barrel nut with features for reducing tensile stresses under heavy load within the barrel nut has a partial-cylindrical body having a first planar end surface and a second planar end surface. A threaded bore extends through the partial-cylindrical body with a central axis substantially parallel to the first planar end surface and the second planar end surface. At least one groove is formed in each of the first planar end surface and the second planar end surface, the groove having a rounded surface extending at least a part of a distance between a curved upper surface of the partial-cylindrical body to a bottom surface thereof in a direction substantially parallel to the central axis of the threaded bore. | 03-03-2016 |
20160061115 | CORE COWL FOR A TURBOFAN ENGINE - A core cowl for a turbofan engine may include a plurality of valleys formed in an outer surface of the core cowl. Each valley may include a convex portion upstream of a concave portion, and may be configured to disrupt a shock cell exiting a fan nozzle of the turbofan engine. Associated methods for reducing turbofan engine noise are also described. | 03-03-2016 |
20160059952 | TORQUE TUBE DOOR - A torque tube door and related method steps may include a door coupled to an inboard wing flap, such that the door is movable with the flap to selectively cover and uncover a torque tube opening in an aircraft fuselage. | 03-03-2016 |
20160059450 | CHOPPED FIBER COMPOSITE SORTING AND MOLDING SYSTEMS AND METHODS - Chopped fiber composite systems and methods are disclosed. Sorting systems include a conveyor, an imager, a plurality of receptacles, a pneumatic device, and controller. Molding systems include a conveyor, an imager, a mold, a pneumatic device, and a controller. The controller directs the pneumatic device to alter the freefall of chopped fiber composite pieces based on characteristics of the chopped fiber composite pieces as they drop from the conveyor and into a receptacle or a mold. Sorting and molding methods include dropping chopped fiber composite pieces, detecting characteristics of the dropping pieces, and directing the pieces based on the detected characteristics. | 03-03-2016 |
20160059449 | SYSTEMS AND METHODS FOR CURING COMPLEX FIBER-REINFORCED COMPOSITE STRUCTURES - Systems and methods for curing complex fiber-reinforced composite structures utilize two distinct heat sources. A first heat source is utilized for heating a complex fiber-reinforced composite structure from within an internal portion of the complex fiber-reinforced composite structure. A second heat source is utilized for heating the complex fiber-reinforced composite structure from an external surface of the complex fiber-reinforced composite structure. | 03-03-2016 |
20160055930 | COMPOSITE MATERIALS WITH IMPROVED ELECTRICAL CONDUCTIVITY AND METHODS OF MANUFACTURE THEREOF - A method of manufacturing a composite material may include providing one or more layers of reinforcement material penetrated with viscous matrix material that is doped with electrically conductive particles. The method may further include applying a magnetic field to arrange the particles into one or more electrically conductive pathways, and curing the matrix material to secure the pathways in position relative to the reinforcement material. | 02-25-2016 |
20160052251 | SYSTEMS AND METHODS FOR FORMING RADIUS FILLERS FOR COMPOSITE STRUCTURES - Systems and methods for forming radius fillers for composite structures are disclosed herein. The systems include a sheet-locating structure that has a first support surface and a support surface edge. The systems further include a second support surface, a separation device, a conveyance structure, and a layup surface. The methods include locating a sheet of composite material on a first support surface and translating the sheet of composite material such that a first portion of the sheet is supported by the first support surface and a second portion of the sheet extends past the support surface edge. The methods also include supporting the second portion of the sheet with a second support surface and separating the second portion of the sheet from the first portion of the sheet to form a strip of composite material. The methods further include conveying the strip of composite material onto a layup surface. | 02-25-2016 |
20160052214 | SYSTEM AND METHOD FOR OPTIMIZING COMPOSITE LAMINATE STRUCTURES - A system and method for creating an optimized composite laminate structure containing a plurality of plies. The system has a processor and a memory, including an application interface. The application interface, when executed by the processor, is configured to operably: receive an input file having one or more of a maximum number of plies, design variables, material properties, and design constraints; determine an initial layup sequence defining parameters of a fiber orientation angle for each ply, and a total percentage of plies at a given fiber orientation angle; iteratively adjust the parameters, until an optimum set of parameters is obtained that achieves one or more predetermined margins of safety, and that achieves optimization of the composite laminate structure; and generate an output file for creating a layup, according to the parameters. The system further has a layup system for creating the optimized composite laminate structure. | 02-25-2016 |
20160048457 | DYNAMIC MEMORY ADDRESS REMAPPING IN COMPUTING SYSTEMS - A method provides security in a computing system including a processor having a logical address space and external system memory having physical address space. The method comprises hiding memory access patterns, including dynamically remapping the logical address space to the physical address space in response to data accesses to the logical address space. | 02-18-2016 |
20160047723 | COMPOSITE TEST SPECIMEN - A particular composite test specimen includes a first tab, a second tab, and a gage section between the first tab and the second tab. The first tab, the second tab, and the gage section are machined from a composite test blank. The composite test blank includes a plurality of plies arranged with first ply layers having fibers oriented in a first direction and second ply layers having fibers oriented in a second direction, where the first direction is different than the second direction. | 02-18-2016 |
20160047719 | SYSTEMS AND METHODS FOR IGNITION SOURCE TESTING WITH FLAMMABLE FOAM - Systems and methods for ignition source testing with a flammable foam are disclosed. Flammable foam systems and methods for testing use a flammable foam that includes fuel and oxidant. Flammable foam is applied to a test article and an energy discharge is applied to the test article. Methods include determining whether the flammable foam ignited in response to the energy discharge. | 02-18-2016 |
20160047532 | Electromagnetic Radiation Shielding Assembly - An electromagnetic shielding assembly may include a transparent substrate layer and a transparent active layer positioned with respect to the substrate, wherein the active layer is configured to absorb electromagnetic radiation having a first wavelength and emit electromagnetic radiation having a second wavelength, the second wavelength being different than the first wavelength, the active layer includes fluorescent molecules combined with a base material, the fluorescent molecules being configured to absorb electromagnetic radiation having the first wavelength and emit the electromagnetic radiation having the second wavelength, wherein the first wavelength is in a visible electromagnetic spectrum and the second wavelength is in a non-visible electromagnetic spectrum. | 02-18-2016 |
20160047452 | HARMONIC DRIVE APPARATUS - A harmonic drive apparatus (also known as a strain wave gear) is constructed with a circular, flexible spline disc having a generally flat configuration or a slightly conical configuration. | 02-18-2016 |
20160047412 | ENHANCED THERMALLY CONDUCTIVE PIVOT BUSHING - An aircraft pivot joint bushing has enhanced thermal conductivity due to the bushing having an inner cylindrical portion which has a first thermal dissipating capacity, and an outer cylindrical portion on the inner cylindrical portion which has a second thermal dissipating capacity, where the second thermal dissipating capacity is less than the first thermal dissipating capacity. | 02-18-2016 |
20160046361 | Bonded and Tailorable Composite Assembly - An all-composite assembly such as a composite laminate aircraft empennage has vertical and horizontal stabilizers with differing sets of interlaminar fracture toughnesses and differing stiffnesses to improve flight characteristics. Composite laminate skins are bonded to unitized and stiffened understructure to reduce weight and improve damage containment. | 02-18-2016 |
20160046084 | COMPOSITE LAYUP TOOLS FOR AIRCRAFT FUSELAGE BARRELS, METHODS OF ASSEMBLING THE LAYUP TOOLS, AND AIRCRAFT FUSELAGE BARREL SECTIONS FORMED UTILIZING THE LAYUP TOOLS - Composite layup tools for aircraft fuselage barrels, methods of assembling the layup tools, and aircraft fuselage barrels formed utilizing the layup tools are disclosed herein. A method of assembling the layup tools includes aligning an adaptor mating surface of a splice adaptor with a mandrel mating surface of a layup mandrel and initially attaching the splice adaptor to the layup mandrel at an initial attachment point. The methods further include attaching a lower lobe of the splice adaptor to a lower lobe of the layup mandrel. A method of forming a fuselage barrel assembly includes providing two fuselage barrel sections and a splice ring, aligning the two fuselage barrel sections, locating the splice ring within the two fuselage barrel sections, and attaching both fuselage barrel sections to the splice ring. The systems include a layup tool that is formed using the methods. | 02-18-2016 |
20160046041 | SYSTEM FOR FACILITATING FLUID MOVEMENT IN CLOSED MOLDS - A vacuum bagging system may include a layer assembly defining a fluid flow channel. The layer assembly may include a contact layer mounted to a composite part positionable within an outer mold line (OML) tool. The contact layer may have a contact layer width defined by opposing contact layer side edges. The layer assembly may further include an inner layer mounted to the contact layer and having inner layer side edges located between the contact layer side edges. The fluid flow channel may extend along at least a portion of the composite part to at least one part end. The vacuum bagging system may include an internal vacuum bag positionable against the inner layer. An inner mold line (IML) tool may support the internal vacuum bag. The contact layer width may be less than an IML tool width. | 02-18-2016 |
20160045949 | Method for Production of Performance Enhanced Metallic Materials - A method for production of a metallic material from a semifinished metallic billet, the semifinished metallic billet including a nanocrystalline microstructure and/or an ultrafine-grained microstructure, the method including the steps of (1) subjecting the semifinished metallic billet to a rotary incremental forming process to form an intermediate wrought metallic billet, and (2) subjecting the intermediate wrought metallic billet to a high rate forming process to form a metallic product. | 02-18-2016 |
20160042094 | SYSTEM AND METHOD FOR READING GEOMETRIC DATA FROM A COMPUTER-AIDED DESIGN (CAD) MODEL - There is provided a system for reading geometric data from a parametric model or a nonparametric model from a CAD model file. The system has a processor and an interface application, which when executed by the processor, is configured to operably receive automatically, using a first interface application, an input file that includes data representing one or more components of a three-dimensional model, and is further configured to operably determine, using the first interface application, a type of a part represented by the three-dimensional model. The first interface application has instructions, one or more algorithms, or a combination thereof, and is further configured to automatically operably identify, select, and group geometric data associated with specific geometric data of the three-dimensional model, based on a set of parametric rules. The processor writes extracted specific geometric data to a first geometry data intermediate output file. | 02-11-2016 |
20160033374 | DETERMINING AEROSOL MATERIAL COMPATIBILITY - Provided are methods for testing aerosol material compatibility of various samples to disinfectants, decontaminants, and other such materials that are used as aerosols. A test is performed in a controlled environment, such as an aerosol chamber, using a specific set of test parameters representative of actual use of tested materials, such as dispensing parameters and exposure parameters. During the test, a test surface of the sample is exposed to an aerosol mist. Other surfaces may be protected. After exposure to the aerosol mist, the sample may be allowed to sit for a period of time. The sample is later cleaned and tested to determine effects of various materials in the mist on the sample. In some embodiments, some or all operations may be repeated for the same sample or different samples. The test parameters may be varied to determine compatibility limits. | 02-04-2016 |
20160033237 | MACRO FIBER FOR COMPOSITE ARTICLES - A macro fiber for a composite article may include a plurality of inner fibers. Each one of the inner fibers may have an inner fiber final cross-sectional size of less than approximately 100 nanometers. The inner fibers may be surrounded by matrix material. | 02-04-2016 |
20160032758 | SYSTEMS, METHODS, AND APPARATUS FOR ROTARY VANE ACTUATORS - Systems, methods, and devices are disclosed for implementing hydraulic actuators. Devices may include a housing having an internal surface defining an internal cavity that may have a substantially circular cross sectional curvature. The devices may include a rotor that includes a first slot having a substantially circular curvature. The devices may include a first vane disk partially disposed within the first slot of the rotor, where the first vane disk has a substantially circular external geometry. The first vane disk may be mechanically coupled to the rotor via the first slot, and the first vane disk may be configured to form a first seal with the internal surface of the housing. The devices may include a first separator device that may be configured to form a second seal with the internal surface of the housing and a third seal with an external surface of the rotor. | 02-04-2016 |
20160032725 | Methods for Optimized Engine Balancing Based on Flight Data - Methods for balancing rotating machinery, such as gas turbine engines, to minimize vibrations. An optimal engine balance solution is obtained using a hybrid optimization technique based on vibration data from one or more vibration sensors and corresponding influence coefficients which quantify the change in vibration level at the vibration sensors due to a unit increase in unbalance level at unbalance source locations. More specifically, balance weight and angular position are determined based on multiple optimization methods which concurrently process the vibration data, the multiple optimization methods comprising local and global optimization algorithms. | 02-04-2016 |
20160031551 | LAMINAR FLOW WINGLET - An aircraft wing tip device may include a unitized, monolithic leading edge torque box that may be formed of polymer matrix fiber-reinforced material. The leading edge torque box may include a skin that may define a continuous, uninterrupted outer mold line surface extending aftwardly from a winglet leading edge by a distance of at least approximately 60 percent of a local chord length. The leading edge torque box may further include at least one internal component extending between opposing inner surfaces of the skin and being integrally formed therewith. | 02-04-2016 |
20160031550 | SUBMERGED VORTEX GENERATOR - A vortex generator may include a depression in an aerodynamic surface, and a vortex generator leading edge located in the depression. The vortex generator leading edge may include a leading edge upper surface. The leading edge upper surface may be positioned at or below a tangent line defined at a location along the aerodynamic surface upstream of the depression relative to an oncoming local flow. | 02-04-2016 |
20160028128 | BATTERY PACK INCLUDING STACKED BATTERY-BOARD ASSEMBLIES - A battery pack comprises a stack of battery-board assemblies. Each battery-board assembly includes a circuit board, an electrical connector mounted on the circuit board, and a battery cell secured to a side of the circuit board. The battery cells are sandwiched between the circuit boards and the connectors are interconnected. The circuit boards and the connectors electrically connect the battery cells together. | 01-28-2016 |
20160027336 | Methods for Evaluating Human Performance in Aviation - An aviation performance evaluation methodology that can be implemented in various ways depending on the applications of interest. Baseline standards for expected performance are stored in one or more databases. One database may contain performance parameters and another database may contain baseline standards such as expert gaze data. Real-time actual performance data is acquired using an eye tracker system comprising at least one video camera, at least one infrared light source, and a computer system which receives image data from the video camera(s). More specifically, the actual and expected performance data are input to a computer system that is programmed to analyze the actual performance based on a comparison of the actual and expected performance data. Based on the results of the comparative analysis, context-adjusted inferences can be made regarding performance, adopted strategies, gaze scan quality, alertness or distraction, situational awareness, and workload. | 01-28-2016 |
20160027275 | BLAST SENSOR AND MOBILE COMMUNICATION DEVICE - A device includes an interface adapter configured to physically couple to a corresponding interface adapter of a mobile communication device. The device includes a blast sensor configured to generate blast data based on one or more measurements and to communicate the blast data to the mobile communication device via the interface adapter. The device further includes a housing at least partially enclosing the blast sensor and at least partially enclosing the mobile communication device. | 01-28-2016 |
20160026824 | SECURITY AGAINST MEMORY REPLAY ATTACKS IN COMPUTING SYSTEMS - A method of providing security for data stored in external memory in a computing system comprises storing a reference updatable hash value for each protected window of the external memory. Each reference value is stored in internal memory of the computing system. The method further comprises continually generating a current hash value for each protected window and comparing each current hash value to its corresponding reference hash value. | 01-28-2016 |
20160026190 | Adaptable Automatic Nacelle Conversion for Tilt Rotor Aircraft - Systems and methods for displaying to a tilt rotor aircraft pilot an optimum nacelle position and/or automatically controlling movement of the nacelles for the pilot. An automatic nacelle conversion function employs an active flight director speed mode to provide a current desired speed and a final speed. When the automatic nacelle conversion function is in a passive (uncoupled) mode of operation, the pilot follows visual cues, manually achieving the commanded nacelle position by rotating a thumbwheel. When in an active (coupled) mode of operation, the automatic nacelle conversion function provides a fully automatic nacelle controller requiring no pilot input. This automatic nacelle controller provides a variable nacelle rate along with several angle versus speed schedules tailored for different guidance speed modes and a wide range of aircraft configurations. The automatic nacelle conversion function is improved though the inclusion of altitude, rate of climb, and deceleration rate commands. | 01-28-2016 |
20160025146 | TORQUE TUBES AND MANUFACTURING METHODS THEREOF - One aspect of the present disclosure relates to an apparatus comprising a first end fitting. The first end fitting comprises a tube engagement portion. The tube engagement portion comprises an outer coupling surface. The outer coupling surface comprises a first virtual cross-section. The first virtual cross-section comprises a first transverse inflection point. Each point along the first virtual cross-section has a first virtual tangent line coplanar with the first virtual cross-section. | 01-28-2016 |
20160024963 | NOISE ATTENUATING LIPSKIN ASSEMBLY AND METHODS OF ASSEMBLING THE SAME - An acoustic assembly includes a backsheet including a plurality of perforations defined therethrough and an acoustic core coupled to the backsheet. The acoustic core includes a plurality of channels defined therethrough that are configured to be in flow communication with the plurality of perforations. The acoustic assembly also includes a linear facesheet coupled to the acoustic core, wherein the linear facesheet includes a plurality of apertures configured to be in flow communication with the plurality of channels. A lipskin is coupled to the linear facesheet, wherein the lipskin includes a plurality of openings configured to be in flow communication with the plurality of apertures. | 01-28-2016 |
20160023431 | FABRIC JACKETED UNIDIRECTIONAL NOODLE - A composite, radius filler noodle for a co-cured spar or stringer used in aircraft construction has a unidirectional composite core and pluralities of pre-preg fabric strips stacked in layers surrounding the core. | 01-28-2016 |
20160023410 | MOLDED-IN INSERT AND METHOD FOR FIBER REINFORCED THERMOPLASTIC COMPOSITE STRUCTURE - A method of retaining a molded-in insert in a fiber reinforced thermoplastic composite material and forming a high strength mechanical locking mechanism is provided. The method includes fixing a molded-in insert in a mold cavity. The insert has a cylindrical body and at least one circumferential groove formed in the cylindrical body, and has a substantially concave configuration, and the groove has a groove radius of 0.025 inch or greater, and greater than or equal to a groove depth. The method includes introducing a fiber reinforced thermoplastic composite material into the mold cavity and around the molded-in insert, enclosing the mold cavity, heating and compressing the material in the mold cavity to consolidate the material around the molded-in insert and to form a consolidated fiber reinforced thermoplastic composite structure with the molded-in insert, cooling the structure, and removing the structure with the molded-in insert from the mold cavity. | 01-28-2016 |
20160016366 | FORMING PRESSES AND METHODS FOR FORMING JOGGLED, STIFFENED COMPOSITE STRUCTURES - Apparatuses and methods for forming a joggle and a longitudinal ridge in a multi-ply composite charge are disclosed. Charges may be formed in a forming press that comprises a joggled die, with a longitudinal ridge and a joggle that crosses the longitudinal ridge, and a conforming die, with a series of longitudinally-spaced die fingers. The die fingers include pairs of die members configured to move laterally between a closed position and an open position, with each die member configured to tilt longitudinally. | 01-21-2016 |
20160016355 | Adaptive Composite Structure Using Shape Memory Alloys - Systems and processes that integrate thermoplastic and shape memory alloy materials to form an adaptive composite structure capable of changing its shape. For example, the adaptive composite structure may be designed to serve as a multifunctional adaptive wing flight control surface. Other applications for such adaptive composite structures include in variable area fan nozzles, winglets, fairings, elevators, rudders, or other aircraft components having an aerodynamic surface whose shape is preferably controllable. The material systems can be integrated by means of overbraiding (interwoven) with tows of both thermoplastic and shape memory alloy materials or separate layers of each material can be consolidated (e.g., using induction heating) to make a flight control surface that does not require separate actuation. | 01-21-2016 |
20160004969 | SYSTEM AND METHOD FOR PREDICTING RUNWAY RISK LEVELS - A method includes receiving meteorological forecast data at an electronic device. The method includes predicting multiple risk levels associated with an aircraft using one or more runways of an airport during a forecast time interval based on the meteorological forecast data. The method further includes generating a graphical user interface (GUI) that includes multiple risk indicators based on the multiple risk levels. The multiple risk indicators may correspond to multiple time sub-intervals during the forecast time interval. | 01-07-2016 |
20160003280 | ASSEMBLIES INCLUDING SHAPE MEMORY ALLOY FITTINGS AND COMPOSITE STRUCTURAL MEMBERS - Provided are assemblies having composite structures interlocked with shape memory alloy structures and methods of fabricating such assemblies. Interlocking may involve inserting an interlocking protrusion of a shape memory alloy structure into an interlocking opening of a composite structure and heating at least this protrusion of the shape memory alloy structure to activate the alloy and change the shape of the protrusion. This shape change engages the protrusion in the opening such that the protrusion cannot be removed from the opening. The shape memory alloy structure may be specifically trained prior to forming an assembly using a combination of thermal cycling and deformation to achieve specific pre-activation and post-activation shapes. The pre-activation shape allows inserting the interlocking protrusion into the opening, while the post-activation shape engages the interlocking protrusion within the opening. As such, activation of the shape memory alloy interlocks the two structures. | 01-07-2016 |
20160001996 | WEB ROLL HANDLING & LOADING SYSTEM - A web roll handling and loading system and methods employ hubs positioned on opposing sides of a roll of web material wound on a hollow tubular core. Hub faces have an annular shape configured to be seated in respective ends of the hollow tubular core. The hubs are pivotably supported for pivoting between an operational position and a deflected position. The roll of web material is loaded on the hubs by lifting it from beneath the hubs to deflect the hub faces arcuately upward, then lowering the roll to allow the hub faces to pivot downward and become seated in the ends of the hollow tubular core. Alternatively, the roll is loaded into a pick-up tool by lowering the pick-up tool downward to the roll so the hubs deflect arcuately upward, then raising the tool so the hubs pivot downward and become seated in the hollow tubular core. | 01-07-2016 |
20160001891 | System and Method for Identifying a Receiving Aircraft During Airborne Fueling - A system for effecting automatic identifying of a receiving aircraft receiving fuel from a fuel delivery apparatus in a delivering aircraft during an airborne fueling operation includes: (a) a first unit coupled with the receiving aircraft; (b) a second unit coupled with the delivering aircraft; and (c) a processing unit coupled with at least one of the first unit and the second unit. The first and second units cooperate to effect communicative coupling for conveying identifying information between the receiving aircraft and the delivering aircraft. The processing unit cooperates with at least one of the first unit and the second unit for employing the identifying information to effect the identifying. | 01-07-2016 |
20160001467 | COLLAPSIBLE, COILED MANDREL - A collapsible, coiled mandrel, for use in co-curing of a hollow carbon-epoxy structure such as a stringer in aircraft construction, is made of a fiber stiffened with doping material that maintains an outer coil shape resistant to external compression forces when used as a mandrel during lay-up and curing, and is collapsible when an end of the fiber is pulled along its longitudinal axis so that it can be easily removed after curing and discarded. A method of fabricating a collapsible, coiled mandrel employs a mold with a shaped recess for forming a coil with a fiber wetted with a doping material fed in by an applicator, and rotating the applicator while backing it out to form the coil in the mold. In an alternative embodiment, a collapsible, coiled mandrel may be formed of a metal coil having a mandrel-shaped cross section and sleeved in a protective liner. | 01-07-2016 |
20150380952 | Battery Cell Charge Equalization - Battery cell charge equalization devices, systems and methods are provided. A particular method includes receiving a charging current at a battery charge equalization circuit coupled to a battery cell of a multi-cell battery. The method also includes routing at least a portion of the charging current away from the battery cell when a voltage of the battery cell satisfies a first voltage threshold. The method further includes establishing a second voltage threshold in response to the voltage of the battery cell satisfying the first voltage threshold. The second voltage threshold is lower than the first voltage threshold. The charging current is routed away from the battery cell while the voltage of the battery cell satisfies the second voltage threshold. | 12-31-2015 |
20150377662 | MEMS-Based Conformal Air Speed Sensor - Systems and methods for measuring air speed which solve the problem of icing or blockage by creating an exterior surface on an aircraft that channels air and measures the pressure difference of the pressure through the airflow and the static pressure. This exterior surface cannot be blocked easily because air is always flowing when the aircraft is in motion, any external matter that could be on the exterior surface is readily visible, and the exterior surface can be heated to prevent icing. In addition, the exterior surface is made of a flexible material that is able to conform closely to the exterior shape of the aircraft. The preferred embodiments comprise microelectromechanical system pressure sensors placed under the air channels for measuring the pressure difference in each channel and an air speed processor for transforming the pressure differences into an air speed estimate. | 12-31-2015 |
20150375843 | Elongated Structures and Related Assemblies - An elongated structure comprising a web extending along a length of the elongated structure and a flange comprising a first flange portion, the first flange portion extending away from an area of the web. The first flange portion comprises a variable width along at least a portion of the length of the elongated structure. The first flange portion of the elongated structure may comprise the variable width the length of the elongate structure. The first flange portion may comprise a constant width along at least a portion of the length of the elongated structure. The elongated structure may further comprise a second flange portion. The second flange portion may comprise a variable width along at least a portion of the length of the elongate structure. The first flange portion may comprise a first top flange portion. | 12-31-2015 |
20150375840 | STAND-OFF DELIVERY OF UNMANNED UNDERWATER VEHICLES - Embodiments described herein provide apparatus and method for stand-off deployment of UUVs utilizing self-directed projectiles that include guidance kits. One embodiment is a projectile that includes a guidance kit that directs the projectile in flight. The projectile further includes a shell and a hollow nose cone. The shell mates with the guidance kit and the nose cone couples with the shell. The nose cone includes an interior surface configured to house a UUV. The projectile further includes a controller that identifies a condition for deploying the UUV in flight, and detaches the nose cone from the shell in response to determining that the condition is satisfied. | 12-31-2015 |
20150369266 | Flow Control Actuator with an Adjustable Frequency - A fluidic oscillator includes a structure having an input port and an output port. A chamber within the structure is configured to channel a fluid from the input port to the output port. A volume of the chamber is configured to change so as to change to change a frequency at which the fluid flows out of the output port. | 12-24-2015 |
20150367619 | Composite Radius Fillers and Methods of Forming the Same - There is provided in an embodiment a composite radius filler for a composite structure. The composite radius filler has two or more radius laminates. Each radius laminate has a laminate of stacked composite plies formed in a desired radius with a desired radial orientation of the stacked composite plies substantially matching a radial orientation of adjacent stacked composite plies of a composite structure surrounding the two or more radius laminates. Each radius laminate is preferably trimmed to have at least one side align adjacent to the others to form a composite radius filler having a shape substantially corresponding to a radius filler region of the composite structure. | 12-24-2015 |
20150367586 | FORMING TOOLS AND FLEXIBLE ULTRASONIC TRANSDUCER ARRAYS - An apparatus comprises a forming tool having a forming surface, and an ultrasonic transducer array on the forming surface. | 12-24-2015 |
20150367565 | SYSTEMS AND METHODS FOR ASSEMBLING A STRUCTURALLY REINFORCED COMPOSITE STRUCTURE - Systems and methods for assembling a structurally reinforced composite structure are disclosed herein. The methods include deforming a composite tubular skin to a deformed conformation to generate clearance to permit a frame assembly to be conveyed into an internal volume that is defined by the composite tubular skin. The methods further include conveying the frame assembly into the internal volume, permitting the composite tubular skin to deform from the deformed conformation to the target conformation, and operatively attaching the frame assembly to the composite tubular skin to form the structurally reinforced composite structure. The systems include a frame support that is configured to support the frame assembly, a frame deformation assembly, a skin support that is configured to support the composite tubular skin, and a skin deformation assembly. | 12-24-2015 |
20150367516 | ROBOT ALIGNMENT SYSTEMS AND METHODS OF ALIGNING A ROBOT - Presently disclosed robotic alignment systems and methods may allow for alignment of a platform of a robot with respect to an access port of a part, such as a wing of an aircraft. A robot positioned under the wing may include a base and an upper platform coupled together by a plurality of legs. The upper platform may be moveable with respect to the base in six degrees of freedom in order to be aligned with the access port of the wing so that the robot may insert a tool through the access port without damaging the wing. Disclosed robotic alignment systems may include a calibration plate that is inserted into the access port. A number of positioning devices on the upper platform of the robot may interact with the calibration plate in order to align the upper platform with respect to the calibration plate, and thereby with respect to the access port. | 12-24-2015 |
20150367509 | Stabilization of an End of an Extended-Reach Apparatus in a Limited-Access Space - Apparatus and methods that can be used to stabilize a portion of an extended-reach tool assembly to enable the dimensional mapping, non-destructive inspection and/or simple repair of elongated and serpentine structures used in aerospace and military platforms. In some embodiments, a jointed (i.e., articulated) arm of the extended-reach tool assembly, which is mounted and manipulated at the entrance to a limited-access space (e.g., a cavity), is equipped with actuatable contact pads or bladders to stabilize the distal end of the arm to which a tool-carrying end effector is coupled. The end effector is capable of holding and orienting a probe or sensor (e.g., NDI sensor unit, laser scanner, camera, etc.) or other tool (e.g., drill, sander, vacuum, “grabber”, coating sprayer, etc.). | 12-24-2015 |
20150362920 | AIRCRAFT DEPARTURE PROFILE GENERATION COMPLIANT WITH NOISE ABATEMENT LIMITS - Systems and methods are described for dynamically generating flight departure profiles that are in compliance with aircraft emission limits. Emission limits may include noise abatement limits. Flight departure profiles may be generated on a flight by flight basis, and/or may be based on then-current conditions such as wind speed, wind direction, and ambient temperature. | 12-17-2015 |
20150362415 | Test Method and Fixture for Obtaining Material Properties Under Biaxial Loading - A test method and corresponding fixture design are provided which enable loading a circular test coupon (made, e.g., of ceramic matrix composite material) to failure under biaxial loading conditions while recording strain and temperature. Biaxial loading requires approximately equal loads to be applied in two directions concurrently. The disclosed method uses liquid coolant (e.g., liquid nitrogen) to cool a ring made of metal alloy (e.g., aluminum alloy) that is disposed radially outward from and surrounds the outer edge of the test coupon. The cooled metal alloy ring contracts and compresses the test coupon until failure occurs. | 12-17-2015 |
20150354672 | AIRCRAFT AND PLANETARY GEAR SYSTEMS - Planetary gear systems, transmissions, and apparatuses include a plurality of compound planet gears, each having three gear stages, a first non-fixed annular gear, a second non-fixed annular gear, a fixed annular gear, and a non-fixed sun gear. A rotational input to the non-fixed sun gear results in opposite rotational outputs of the first non-fixed annular gear and the second non-fixed annular gear. Compound planet gears and carriers for planetary gear systems are also disclosed. | 12-10-2015 |
20150354668 | ROTORCRAFT AND PLANETARY GEAR SYSTEMS - Planetary gear systems, transmissions, and apparatuses include at least one non-fixed annular gear, at least one non-fixed sun gear, at least one compound planet gear meshed between the at least one non-fixed annular gear and the at least one non-fixed sun gear, and at least one fixed gear meshed with the at least one compound planet gear. Rotational input to one of the at least one non-fixed annular gear and the at least one non-fixed sun gear results in an opposite rotational output of the other of the at least one non-fixed annular gear and the at least one non-fixed sun gear. | 12-10-2015 |
20150353210 | Thermal Seal with Thermally Induced Shape Change - A thermal seal may include a flexible insulation layer, and an element made of shape memory alloy attached to the insulation layer, the element being treated to bend in response to heating, whereby an increase in the temperature of the element causes the insulation layer to transform from a first configuration to a second configuration. | 12-10-2015 |
20150353199 | CARGO AIRCRAFT FOR TRANSPORTING INTERMODAL CONTAINERS IN TRANSVERSE ORIENTATION - Provided are aircraft for transporting intermodal containers and methods of operating such aircraft including methods of loading and unloading the containers. An aircraft includes a fuselage having a cargo space for receiving and supporting intermodal containers. The containers are oriented in the transverse direction in the cargo space or, more specifically, in a direction normal to the longitude direction that extends from the nose to the tail of the aircraft. The aircraft may transport standard 20-foot or 40-foot containers or lighter version of such containers that otherwise have the same form and features as the standard intermodal containers. The intermodal containers may be loaded through an opening in the bottom of the fuselage. Specifically, intermodal containers may be arranged into a row. The aircraft may be then rolled over this row of the containers and lowered onto the containers followed by engaging container corners. | 12-10-2015 |
20150353188 | SLIDABLE DIVERGENT TRAILING EDGE DEVICE - A wing includes a trailing edge, and a divergent trailing edge device slideable along an aft surface of the trailing edge between a stowed position and a fully deployed position. The trailing edge device is located entirely within the trailing edge when stowed, and it increases lift over drag of the wing when deployed. | 12-10-2015 |
20150353187 | LEADING EDGE ASSEMBLY FOR AN AIRCRAFT - A wing assembly includes a main wing and a slat movable between stowed and deployed positions. The main wing includes a panel movable to a retracted position when the slat is in the stowed position, such that the slat outer surface and a wing upper surface define a first continuous outer mold line shape. The panel may further be movable to an extended position when the slat is in the deployed position, such that an outer surface of the panel and the wing upper surface define a second continuous outer mold line shape. | 12-10-2015 |
20150352827 | Bonded Tab and Tooling Device - A method and apparatus for forming a composite part. An apparatus comprises a tooling plate, a tab co-bonded with the tooling plate, and a group of alignment features associated with the tab. The tooling plate is configured for use with a tool to form a composite part. The group of alignment features is configured to position the tooling plate with respect to the tool used to form the composite part. | 12-10-2015 |
20150350317 | COMPUTER SYSTEM SYNCHRONIZATION - A method may comprise communicating by a first computer with a second computer over a network during a first frame having a first frame duration; transmitting a first synchronization signal from the first computer to the second computer; receiving by the first computer during the first frame a second synchronization signal from the second computer; determining by the first computer a first elapsed time between a time when the first synchronization signal was transmitted by the first computer and a time when the second synchronization signal was received by the first computer; and determining by the first computer a duration for a second frame based at least in part on the first elapsed time. | 12-03-2015 |
20150348424 | Airspace Deconfliction System and Method - An aircraft deconfliction system including a registration system having an airspace database, a registered airspace, wherein registration details of the registered airspace are logged in the airspace database, and an aircraft assigned to the registered airspace, the aircraft including a flight control system, a guidance computer controlling the flight control system based on a pilot input, and an override unit in communication with the guidance computer, wherein the override unit overrides the pilot input when the aircraft breaches the registered airspace. | 12-03-2015 |
20150346724 | VARIABLY CONTROLLED GROUND VEHICLE - Method and apparatus for providing autonomous control of a vehicle. A vehicle can be manually controlled by an operator. An autonomous system can monitor the operator's control inputs and the environment of the vehicle to determine whether the control inputs result in safe operation of the vehicle. If control inputs are not safe, then the autonomous system can modify the operator's unsafe inputs into safe inputs. In various instances, the autonomous system can operate the vehicle without operator input. In the event an operator attempts to apply control inputs to the vehicle while the autonomous system is otherwise in control, the autonomous system can check to see whether the operator's inputs result in safe operation of the vehicle. If the operator's control inputs are safe, then the autonomous system can replace its autonomous commands with the operator's commands. | 12-03-2015 |
20150346333 | Positioning in Indoor Locations and Other GPS-Denied Environments - Methods for: (1) extracting Doppler/velocity measurements; (2) estimating relative clock bias errors; (3) determining range and velocity estimates with associated confidences; and (4) extracting range estimates using channel estimation are disclosed. These methods can be used separately or combined to improve positioning solutions obtained by positioning systems used in indoor locations and other GPS-denied environments. | 12-03-2015 |
20150346314 | NOISE SOURCE DECOMPOSITION SYSTEM AND METHOD USING AN ADAPTABLE APERTURE PHASED ARRAY - A system and method for determining a characteristic of a noise source. A first array of microphones is mounted on a platform moveable from a starting position to an ending position along a line parallel to a central axis of the noise source. A second array of microphones includes sound sensors mounted in a spaced apart fixed position with respect to the noise source. A processing system processes first information from the first array of microphones and second information from the second array of microphones. The processing system collects and stores the first and second information at each discrete step of the first array, spatially filters the first information, processes and calibrates the filtered first information based on the second information, and further processes the calibrated first information to obtain a characteristic at a selected location. For flyover testing, the first array is instead held in a fixed position. | 12-03-2015 |
20150346110 | Apparatus and Method for Spectroscopic Analysis of Residue - One example of the present disclosure relates to an apparatus for spectroscopic analysis of residue. The apparatus includes a surface including a hydrophobic portion and a hydrophilic portion. The hydrophobic portion surrounds the hydrophilic portion. The hydrophilic portion includes a dimension equal to or larger than a width of a first incident non-destructive electromagnetic beam. | 12-03-2015 |
20150345424 | THRUST REVERSER TORQUE BOX WITH DISCRETE MAJOR FITTINGS - A thrust reverser torque box assembly for an aircraft engine is constructed with a torque tube having a cross section configuration tailored and conducive to carrying torsion and discrete major fittings at opposite ends of the torque tube that connect the torque tube and thrust reverser actuation and reacts loading due to reverse thrust operation to the aircraft engine fan case. | 12-03-2015 |
20150345395 | TURBOFAN ENGINE WITH VARIABLE EXHAUST COOLING - Disclosed aircraft and turbofan engines have an active configuration (corresponding to flight, etc.) and an idle configuration (corresponding to ground idle). Turbofan engines comprise a core engine, a nacelle, a bypass duct therebetween, and a bypass splitter shell that extends at least partially between the nacelle and the core engine to define peripheral and interstitial bypass ducts. Bypass flow in the bypass duct splits into peripheral bypass flow and interstitial bypass flow. The relatively cool, slow interstitial bypass flow is directed into relatively hot, fast core exhaust flow from the core engine and into a mixed exhaust duct at least partially defined by the bypass splitter shell. The bypass splitter shell may be selectively positioned to increase (in the idle configuration) or to decrease (in the active configuration) the relative flow of the interstitial bypass flow, thereby cooling and/or slowing the mixed exhaust flow in the idle configuration. | 12-03-2015 |
20150344155 | Positioning Fixture and Method of Using the Fixture - A fixture for positioning an object relative to a beam, wherein the beam includes a web, is disclosed. The fixture includes a first portion including a first positioning face, a first contact face, and a first clamping face. Each of the first positioning face, the first contact face, and the first clamping face is movable in a first working direction. The fixture also includes a second portion including a second positioning face, a second contact face, and a second clamping face. Each of the second positioning face, the second contact face, and the second clamping face is movable in a second working direction opposite to the first working direction. When the fixture is installed on the beam, the first contact face and the second contact face abut each other, and the first clamping face and the second clamping face engage the web. | 12-03-2015 |
20150344154 | Modular Stanchion System - An apparatus for supporting a wing assembly at a wing assembly support height. Base sections are provided, each having a different predetermined height with respect to one another. A movable platform carries a plurality of base sections, and a plurality of wing assembly support sections rest on base sections and include wing assembly connectors, which are movable in a first plane and a second plane generally perpendicular relative to the first plane. A differential height is defined between the wing assembly support height and the combined heights of the platform and the height of wing assembly connector, relative to the bottom of the wing assembly support section. At least one of the base sections is of a predetermined height approximating the differential height and is carried on the platform. The wing assembly support section is carried on such base section. | 12-03-2015 |
20150344148 | Visual Fuel Predictor System - A method and apparatus for predicting fuel for an aircraft. Remaining amounts of fuel that will be present for types of fuel use for the aircraft at a destination are predicted. Flight times for the types of fuel use are calculated from the remaining amounts of fuel predicted for the types of fuel use for the aircraft at the destination. Graphical indicators are displayed indicating the types of fuel use and the flight times for the types of fuel use. | 12-03-2015 |
20150344146 | FLUID SEPARATION ASSEMBLY AND METHOD - A fluid separation assembly and method are provided. The assembly has a hollow fiber bundle with a plurality of hollow fiber membranes. The assembly further has a pair of tubesheets, each encapsulating respective ends of the hollow fiber bundle. The assembly further has a plurality of radial through openings formed along a circumference of one or both of the tubesheets and radially through a body portion in one or both of the tubesheets. The radial through openings include center connected radial through openings and partial radial through openings, and intersect each, or substantially each, of the hollow fiber membranes. The assembly further has a housing surrounding the hollow fiber bundle and the tubesheets. The housing has a feed inlet port, a permeate outlet port, and a non-permeate outlet port. The feed inlet port and the non-permeate outlet port are in parallel alignment with a longitudinal central axis of the housing. | 12-03-2015 |
20150344137 | External Case Heater For An Angle Of Attack Sensor - A heating apparatus for use in an AoA sensor is described herein. The heating apparatus includes a heating element bonded to a support element. The support element is configured to be attachable to and removable from the AoA sensor. The heating element may receive an electrical current, causing the temperature of the heating element to increase. The temperature increase is designed to reduce the probability that ice forms in certain locations of the AoA sensor. | 12-03-2015 |
20150344124 | MODULAR REPLACEABLE SLIP JOINT INTERCOSTAL - Systems, methods, and apparatus for a modular replaceable slip joint intercostal are disclosed. In one or more embodiments, an intercostal apparatus for a vehicle comprises a body, where the body is greater in length than in width. In at least one embodiment, the intercostal apparatus further comprises at least one slip joint opening located proximate an end of the body to slidably receive a bushing and a fastener, where the bushing rigidly attaches to a top surface of a seat track by the fastener. | 12-03-2015 |
20150343753 | METHODS FOR BONDING METAL AND THERMOPLASTIC COMPONENTS - A method for bonding components is provided. The method includes preparing a surface of a metal component, applying a film adhesive to the prepared surface, forming a thermoplastic component using injection molding such that the film adhesive is positioned between the metal component and the thermoplastic component, and curing the film adhesive. | 12-03-2015 |
20150343609 | METHOD AND APPARATUS FOR RELEASING A CABLE TIE - One example of the present disclosure relates to a tool for releasing a cable tie. The tool includes a front member having a front indexing surface and a front extension member. The tool includes a rear member movably coupled to the front member, with the rear member including a rear indexing surface and a rear extension member. When the front member and the rear member engage a head of the cable tie in a closed state, the front extension member protrudes into an opening in the head, in an insertion direction, a front extension distance that is less than the length of the head minus a distance from the rear surface to a pawl of the cable tie along the insertion direction, and spaces a contact portion of the pawl, along a transverse direction, by a distance sufficient to disengage the cable tie. | 12-03-2015 |
20150343586 | TABLE SAW GUIDE AND SAFETY GUARD - A guide and safety guard for a table saw, of the type having a table top and a powered saw blade with an exposed saw blade portion projecting above the table top and a movable guide fence positionable on the table top on a far side of the saw blade, has a support rail having opposite ends coupled to support members in a desired spaced relation to the guide fence of the table saw, a guard block mounted by a sleeve portion so as to be slidable on the support rail in axial directions thereon, and rotatable on the support rail so that it can be moved out of and into operative position, wherein the guard block has a height projecting above the table top in the operative position that is greater than the height of the exposed saw blade portion for protecting the hand of the user, and a guard extension fixed to a trailing side of the guard block for protecting the wrist and lower arm area of the user. | 12-03-2015 |
20150343487 | SYSTEMS AND METHODS FOR DISPENSING A SUBSTANCE ON A SURFACE - One example of the present disclosure relates to a system for dispensing a substance in a form of a bead on a surface in a progression direction along a path. The system includes a dispenser having, while the substance is being dispensed: a leading edge, a contact portion including two contact points with the surface, and a trailing edge that extends between the two contact points and terminates therein. The system also includes first means for moving the dispenser along a virtual travel plane, which is parallel to the path and passes through the two contact points, while maintaining the contact portion in communication with the surface as the substance is being dispensed. The system also includes second means for monitoring a leading portion of the bead and for generating a signal responsive to at least one characteristic of the leading portion, wherein the leading portion is located ahead of a portion of the leading edge in the progression direction along the path. The system further includes third means for controlling, responsive to the signal generated by the second means, at least one of a speed of the dispenser along the path or a flow rate of the substance to the dispenser to provide a substantially uniform cross-sectional shape of the bead along the path. | 12-03-2015 |
20150343483 | SYSTEM AND METHOD OF FORMING A NANOTUBE MESH STRUCTURE - A system for use in producing a nanotube mesh structure is provided. The system includes a first nanotube collection apparatus including a first substrate configured to collect a plurality of nanotubes substantially aligned in a first orientation on an attachment surface thereof, and a second nanotube collection apparatus including a second substrate configured to collect a plurality of nanotubes substantially aligned in a second orientation on an attachment surface thereof. The first and second nanotube collection apparatuses are configured to combine the pluralities of nanotubes at an interface. The system also includes a first energy source configured to direct energy towards the interface between the pluralities of nanotubes, wherein the energy is configured to join the pluralities of nanotubes to form the nanotube mesh structure. | 12-03-2015 |
20150343473 | AIRCRAFT COATING APPLICATION SYSTEM AND METHOD - A coating application system may include a pair of towers movable along a respective pair of floor tracks. A crossbeam may extend between the pair of towers. The cross beam may have opposing beam ends. A universal joint may couple each beam end to a tower to allow the crossbeam to rotate about a vertical axis and about a horizontal axis. A robotic device may be mounted to the crossbeam. The robotic device may include an end effector for performing one or more operations on an aircraft exterior surface. | 12-03-2015 |
20150342077 | Integrated Wiring System for Composite Structures - A method for manufacturing a composite part. Layers of composite material are cured to form the composite part. A primer is depicted on a surface of the composite part. A group of conductive elements is deposited on the primer to form an electronic device on the primer. | 11-26-2015 |
20150341113 | LIGHTING AND DATA COMMUNICATION SYSTEM USING A REMOTELY LOCATED LIGHTING ARRAY - A lighting system for transmitting light to a plurality of specific locations is disclosed. The lighting system includes at least one source lighting array and a plastic optical fiber (POF). The source lighting array comprises a plurality of lighting elements. The plurality of lighting elements are each configured to generate visible light. The POF cable has an end in communication with the source lighting array. The POF cable transmits visible light generated by the source lighting array to the plurality of specific locations. | 11-26-2015 |
20150339409 | MID-SURFACE EXTRACTION FOR FINITE ELEMENT ANALYSIS - An apparatus is provided for implementation of a mid-surface modeler including a receiver, selector, clusterer and mid-surface constructor. The receiver is to receive a solid model of a structural product composed of structural components, with the solid model representing the components by a collection of geometry. The selector is to select a group of geometry from the geometry in the solid model, with the group of geometry having approximately the same shape, and being perpendicular to an axis of a local coordinate system. The clusterer is to cluster geometry of the group of geometry into one or more clusters of geometry based on a relationship between the geometry, with each cluster of the cluster(s) representing a component of the component(s). And the mid-surface constructor is to construct a mid-surface model of the product, including computation of respective one or more mid-surfaces for the cluster(s). | 11-26-2015 |
20150339205 | BUILT-IN TEST FOR SATELLITE DIGITAL PAYLOAD VERIFICATION - According to an embodiment, a testing system for a satellite payload includes a built-in testing component configured at a satellite, the built-in testing component comprising a built-in testing component input and a built-in testing component output, and a payload component configured at the satellite, the payload component comprising a payload component input communicatively connected to the built-in testing component output and a payload component output communicatively connected to the built-in testing component input, wherein the built-in testing component is configured to transmit a digital test signal from the built-in testing component output to the payload component input and receive a digital output signal at the built-in testing component input from the payload component output. | 11-26-2015 |
20150338325 | UNIVERSAL GRIP SYSTEM - Provided are universal grip systems and method of using universal grip systems to test coupons. According to various examples, a universal grip system includes two grips and two guide posts for supporting the two grips and allowing the two grips to move with respect to each other. Each grip may include one or two wedges. The wedges are used to engage the coupons during testing and provide anti-buckling support and/or anti-rotation support. The wedges are slidably coupled within corresponding grips, which allows the universal grip system to engage and disengage the coupons by moving one grip with respect to another. The grips may be constructed from thermally neutral materials, such as invar 36. The grips may thermally isolated from the guide posts by, for example, a set of spacers disposed between the grips and linear bearing slidably coupled to the guide posts. | 11-26-2015 |
20150338306 | PIEZOELECTRIC SENSOR CONFIGURATION FOR DETECTING DAMAGE IN A STRUCTURE - Described herein is an apparatus for detecting damage in a structure that includes a plurality of first piezoelectric sensing elements arranged in a generally circular shape. The apparatus also includes an annular-shaped second piezoelectric sensing element positioned adjacent the plurality of first piezoelectric sensing elements. One of the plurality of first piezoelectric sensing elements or the annular-shaped second piezoelectric sensing element generates a wave through the structure and other of the plurality of first piezoelectric sensing elements or the annular-shaped second piezoelectric sensing element senses the wave after passing through the structure. | 11-26-2015 |
20150337886 | SELF-LOCKING MOLDED-IN BLIND INSERTS - Blind inserts for use with sandwich panels and methods for manufacturing the same. A blind insert can include a nut arranged in an insert. The insert can include a cavity at an end of the nut. When a screw is screwed into the nut, the screw can enter the cavity and dig into the insert. The interference between the insert and the screw can provide friction that prevents the screw from loosening in a vibrating environment. The blind insert can be made by placing a mandrel into the nut. The mandrel includes a nose that extends past the end of the nut. When the insert is molded around the nut, the mandrel prevents mold material from entering a threaded aperture of the nut and forms the cavity in the insert. The blind insert can also be made by placing a cap that defines the cavity on the end of the nut. The insert can be molded around the cap and the nut. | 11-26-2015 |
20150337885 | MODIFIED SHANK FASTENERS FOR ELECTROMAGNETIC EFFECT (EME) TECHNOLOGY - A fastener system for composite structure providing electromagnetic energy protection has a shank with a threaded portion on a first end of the shank terminating in a lead-in portion. A head is present on a second end of the shank. The shank is adapted for intimate conductive contact with an inner surface of an interference fit hole. | 11-26-2015 |
20150337447 | CO-BONDED ELECTROFORMED ABRASION STRIP - A system, method, and apparatus for a co-bonded electroformed abrasion strip are disclosed. A disclosed method for making a unitary abrasion strip for a fluid dynamic surface includes manufacturing or identifying a first metallic section having an overlap region on a first end of the first metallic section. The method further includes manufacturing or identifying an overlap region disposed on the first end of the first metallic section by preparing the first end of the first metallic section. Also, the method includes creating a second metallic section onto the overlap region on the first end of the first metallic section by performing a first electro-deposition process on the first end of the first metallic section; where the first metallic section, the overlap region, and the second metallic section together form a unitary, inseparable abrasion strip for a fluid dynamic surface. | 11-26-2015 |
20150336657 | ROTARY DRIVE ASSEMBLY FOR WING TIP - A rotary drive assembly is provided. The assembly includes a tip hinge box, a body hinge box pivotably coupled to the tip hinge box, a rotary actuator positioned within the body hinge box, and a linkage mechanism coupled between the rotary actuator and the tip hinge box, the linkage mechanism including a first linkage fixedly coupled to the rotary actuator, and a second linkage coupled between the first linkage and the tip hinge box, wherein rotation of the rotary actuator causes the tip hinge box to rotate relative to the body hinge box. | 11-26-2015 |
20150336656 | VENT STRINGER FITTING - A fitting for a vent stringer of a type having an open end and an outer edge defining the open end. The fitting may include a fitting body receivable along the open end of the vent stringer, the fitting body having a groove that generally corresponds with the outer edge of the vent stringer, the groove of the fitting body shaped to receive the outer edge of the vent stringer to create a tongue and groove joint with the outer edge; and a connection between the fitting and the stringer to prevent slidable movement of the fitting relative to the stringer. | 11-26-2015 |
20150336654 | AIRCRAFT BODY MOUNTED ENERGY ABSORBING RUB STRIP - An energy absorbing rub strip having a core material and a fairing positioned over the core material. The core material may be configured to buckle under the application of a predetermined amount of force and the fairing may be configured to be attached to a fuselage of an aircraft. The fairing may be made out of an abrasive-resistant material such as titanium or a nickel-based metal. The core material may be comprised of an aluminum honeycomb. The core material may be comprised of a dual density material. The length of the rub strip may extend beyond potential contact points on the fuselage during landing and takeoff. Upon a ground contact event, the thickness of deformed/buckled core material may be measured to determine if the ground contact event may have caused structural damage to the aircraft. | 11-26-2015 |
20150336294 | Concurrent Infusion of Dissimilar Resins - A fiber preform is infused with two differing resin systems concurrently using stacked resin delivery assemblies located along one edge of the preform. | 11-26-2015 |
20150336244 | Turnbuckle Wrench Assembly - A wrench assembly for turning a central portion of a turnbuckle. The wrench assembly includes first and second wrenches that are substantially identical. Slots in body portions of each of the wrenches define open ends that are oppositely disposed to one another when engaging the central portion of the turnbuckle. The wrenches may be detachably secured together around the central portion of the turnbuckle. At least two spokes extend outwardly from a periphery of each of the body portions of the wrenches that are utilized to impart rotational movement to the central portion of the turnbuckle. In at least one configuration, a distal end of an elongated member is used to push and pull on the spokes to impart the rotational movement. | 11-26-2015 |
20150336140 | METHODS, SYSTEMS, AND DEVICES FOR RADIO-FREQUENCY ASSISTED REMOVAL OF SEALANT - Cured sealant may be removed from a substrate if the cured sealant includes a susceptor within its volume. Removal proceeds by exposing the sealant with the susceptor to radio-frequency radiation sufficient to cause dielectric heating in the susceptor and the consequent heating in the cured sealant reduces the bond strength of the cured sealant. The reduced bond-strength sealant may be removed by physical methods, such as scraping etc., much more easily than the original (unexposed) cured sealant. Also disclosed are sealant compositions with susceptor, susceptor tools to introduce susceptor into cured sealant, and handheld radio-frequency heaters to apply radio-frequency radiation to cured sealant. | 11-26-2015 |
20150335217 | Hand-Held Pneumatic Vacuum - A portable pneumatic vacuum cleaner is disclosed that includes a venturi vacuum generator disposed downstream of a primary filter. The primary filter is disposed in filter chamber that is disposed downstream of a collection chamber. Both chambers are disposed in a canister and the collection chamber is separated from the filter chamber by a partition filter. A vacuum conduit extends through a wall of the canister and into the collection chamber and has a collection end positioned tangentially to the wall of the canister for generating cyclonic flow in the collection chamber. The filter chamber is connected to the vacuum generator by an outlet conduit. The vacuum generator also connects to a pressurized air source and an exhaust. | 11-26-2015 |
20150334113 | Vehicle Data Delivery - A system and method of delivering vehicle data. Reference data is received by a data processing system. The reference data comprises a reference identifying the vehicle data stored in a repository that is located off of a vehicle and reference authentication data identifying a source of the reference data. The data processing system uses the reference authentication data to determine whether the reference data is from an approved source for the reference data. The reference is used to retrieve the vehicle data from the repository by the data processing system when the reference data is determined to be from the approved source for the reference data. The vehicle data comprises authentication data identifying a source of the vehicle data. The data processing system uses the authentication data to determine whether the vehicle data is from an approved source for the vehicle data. | 11-19-2015 |
20150333250 | Structures with PZT Nanoparticle Ink Based Piezoelectric Sensor Assembly - A structure is provided having a substrate and a direct write deposited lead zirconate titanate (PZT) nanoparticle ink based piezoelectric sensor assembly deposited on the substrate. The PZT nanoparticle ink based piezoelectric sensor assembly has a PZT nanoparticle ink based piezoelectric sensor with a PZT nanoparticle ink deposited onto the substrate via an ink deposition direct write printing process. The PZT nanoparticle ink does not require a high temperature sintering/crystallization process once deposited. The PZT nanoparticle ink based piezoelectric sensor assembly further has a power and communication wire assembly coupled to the PZT nanoparticle ink based piezoelectric sensor. The power and communication wire assembly has a conductive ink deposited onto the substrate via the ink deposition direct write printing process. | 11-19-2015 |
20150331427 | Control Method to Damp Quadrotor Slung Payload Mode - A quadrotor or other vertical lift aerial vehicle measures an angle of a payload slung from the quadrotor relative to a body of the quadrotor. Using this measurement a signal may be generated that adjusts a flight characteristic of the quadrotor to counteract swing in the payload. A feedback function for generating the feedback signal may include proportional and derivative gain functions as well as non-linear signal processing functions. The feedback signal may be added to normal input control signals to cause acceleration in the direction of the payload angle that damp oscillation of the slung payload caused by wind or movements of the quadrotor. | 11-19-2015 |
20150331186 | Method and Apparatus for Fabricating an Optical Device Using a Treated Surface - A method and apparatus for forming an optical device on a substrate. A surface of the substrate may be treated to form a treated surface having a number of modified properties. A plurality of drops of material may be deposited onto the treated surface of the substrate to form the optical device. An adhesion between the plurality of drops and the treated surface of the substrate may be reduced by the number of modified properties of the treated surface such that the plurality of drops form an optical device having a lateral resolution below a selected threshold. | 11-19-2015 |
20150330601 | Optical Filtering System for Solar Cell Testing - A method and apparatus for simulating light. A first light from a first filterer is output to a solar cell. The first light output by the first filterer has a coarse spectrum that simulates the light in a selected environment. A second light from a second filterer is output to the solar cell while the first light is output by the first filterer. The second light output by the second filterer has a fine spectrum selected for a group of junctions in the solar cell. | 11-19-2015 |
20150330310 | METHODS AND APPARATUS TO DETERMINE AIRFLOW CONDITIONS AT AN INLET OF AN ENGINE - Methods and apparatus to determine airflow conditions at an inlet of an engine are disclosed herein. An example apparatus disclosed herein includes a sensor disposed at an inlet of an engine to measure a pressure characteristic, a temperature characteristic and a velocity characteristic of an airflow moving through the inlet and a processor to determine an air mass flow rate based on the pressure characteristic, the temperature characteristic and the velocity characteristic measured at the engine inlet. | 11-19-2015 |
20150329221 | Automated Scanning Systems for Non-Destructive Inspection of Curved Cylinder-Like Workpieces - Systems and methods for high-speed non-destructive inspection of a half- or full-barrel-shaped workpiece, such as a barrel-shaped section of an aircraft fuselage. Such workpieces can be scanned externally using a mobile (e.g., translating) arch gantry system comprising a translatable arch frame disposed outside the fuselage section, a carriage that can travel along a curved track carried by the arch frame, a radially inward-extending telescopic arm having a proximal end fixedly coupled to the carriage, and an NDI sensor unit coupled to a distal end of the telescoping arm. The stiffeners of the fuselage sections can be scanned using a mobile scanner platform disposed inside the fuselage section, which platform comprises a radially outward-extending telescopic arm rotatably coupled to a mobile (e.g., holonomic or linear motion) platform and an NDI sensor unit coupled to a distal end of the telescoping arm. The scan data is matched with position data acquired using any one of a plurality of tracking systems to enable the display of NDI features/flaws on a three-dimensional representation of the workpiece. | 11-19-2015 |
20150329208 | SEATING ARRANGEMENT AND METHOD - A seating arrangement for an aircraft may include a plurality of seats that may be convertible into a flat bed configuration. Each seat may have a seat centerline that may be oriented at a seat angle relative to a longitudinal axis of an aircraft cabin. Each seat may include a footrest that may be offset from the seat centerline of the seat. | 11-19-2015 |
20150328877 | METHOD AND APPARATUS FOR REPAIRING COMPOSITE MATERIALS - A method of bonding materials may comprise defining a bond interface between two materials in a cure zone on a surface of an object, and non-conductively heating the bond interface without directly heating the surface outside of the cure zone. Non-conductively heating the bond interface may involve applying microwave radiation to the bond interface. | 11-19-2015 |
20150328846 | COMPOSITE STRUCTURES HAVING INTEGRATED STIFFENERS WITH SMOOTH RUNOUTS AND METHOD OF MAKING THE SAME - A unitized composite structure comprises a composite member having at least one integrally formed composite stiffener. At least one end of the stiffener includes a runout forming a substantially smooth transition between the stiffener and the composite structure. | 11-19-2015 |
20150328845 | MANUFACTURE OF A RESIN INFUSED ONE-PIECE COMPOSITE TRUSS STRUCTURE - A composite truss structure may have a first facesheet, a second facesheet, and a plurality of truss elements joined with the first facesheet and the second facesheet at nodes to form a one-piece structure. The composite truss structure may be formed by a method comprising preparing a dry fabric mold by: 1) placing a first dry fabric layer on a tool, 2) placing a first layer of fabric-loaded mandrels on the first dry fabric layer, 3) placing a second layer of the fabric-loaded mandrels on the first layer of fabric-loaded mandrels, and 4) placing a second dry fabric layer over the fabric-loaded mandrels. The method may further comprise infusing the dry fabric mold with a resin, and curing the resin to provide the nonflexible composite truss structure. | 11-19-2015 |
20150328842 | METHOD AND APPARATUS FOR LAYUP TOOLING - One example of the present disclosure relates to a tool for laying up composite material to form a workpiece having a target contour. The tool includes a support structure including an elongated member having a longitudinal axis, and support plates connected to the elongated member and spaced apart from each other along the longitudinal axis. The elongated member includes a metallic material. The tool also includes a non-metallic backing structure connected to the support plates, the non-metallic backing structure comprising a working surface that includes a backing contour complementary to the target contour. | 11-19-2015 |
20150324658 | SENSOR FUSION USING DETECTOR CONFIDENCE BOOSTING - A method for detecting one or more target objects is provided including obtaining 2-dimensional imaging information and 3-dimensional point cloud information of a target zone. The method also includes determining a ground plane in the point cloud information and removing the ground plane to generate modified 3-dimensional information. Also, the method includes identifying a set of 2-dimensional candidate objects from the 2-dimensional imaging information, and identifying a set of 3-dimensional candidate objects from the modified 3-dimensional information. The method also includes determining, for each of at least some of the 2-dimensional candidate objects, a corresponding 3-dimensional candidate object from the set of 3-dimensional candidate objects. Further, the method includes modifying the 2-dimensional confidence measure for each of the at least some of the 2-dimensional candidate objects to generate fused confidence measures based on whether the 2-dimensional candidate object corresponds to a 3-dimensional candidate object. | 11-12-2015 |
20150324609 | SEMANTICALLY DETERMINING A SECURITY CLASSIFICATION OF DATA - Disclosed herein is a method for determining a security classification for data that includes generating a classification signature for data based on a semantic interpretation of the data. The classification signature is associated with a security classification for the data. The method also includes comparing the generated classification signature to a predetermined classification signature associated with the security classification. Further, the method includes verifying the generated classification signature matches the predetermined classification signature. | 11-12-2015 |
20150323922 | PATH REPEATABLE MACHINING FOR FULL SIZED DETERMINANT ASSEMBLY - Systems, methods, and apparatus are disclosed for machining a part. The methods may include generating a plurality of spatial representations associated with a plurality of positions identified by a machining pattern associated with the part. The plurality of spatial representations may include a first spatial representation identifying a first orientation of a machining tool relative to the part at a first position. The methods may include moving an end effector to the first position. The methods may include mechanically coupling, using a coupling tool, the end effector to the part at the first position. The methods may include generating a second spatial representation identifying a second orientation of the machining tool relative to the part at the first position. The methods may include adjusting the machining tool in response to determining that the second spatial representation is different than the first spatial representation. | 11-12-2015 |
20150323647 | METHODS AND APPARATUS TO DETERMINE A POSITION USING LIGHT SOURCES - Methods and apparatus to determine a position using light sources are disclosed. An example method includes processing an output of a photodetector based on anticipated codes to identify multiple light sources from which the photodetector receives light at a first position, determining locations of the identified light sources; and determining a location of the first position based on the locations of the identified light sources. | 11-12-2015 |
20150323581 | COMPACT SPACECRAFT ANTENNA FIELD APERTURE LOAD COUPLER - An apparatus, method, and system are disclosed that can be used to reduce the peak radiated flux density of a horn antenna or for testing the electronics associated with a horn antenna. A horn antenna with narrow and wide ends can have disposed within it a surrogate waveguide. The surrogate waveguide has a wide end smaller than the wide end of the horn antenna, and the wide end of surrogate waveguide extending to or beyond the wide end of the horn antenna. A mounting plate or face plate covers a portion of the wide end of the horn antenna. | 11-12-2015 |
20150323477 | BACKSCATTER INSPECTION SYSTEMS, AND RELATED METHODS - Inspection systems employing radiation filters with different attenuation characteristics to determine specimen irregularities, and related methods are disclosed. An inspection system includes a radiation emitter configured to emit a radiation beam along a radiation trajectory. Some of the radiation may be reflected by the specimen as backscatter and received by at least one radiation detector of the inspection system along the radiation trajectory. Irregularities and various materials of the specimen may produce backscatter radiation at different energies and/or scatter angles which may be identified by employing radiation filters having different attenuation characteristics. By employing these filters in communication with the radiation emitter and the radiation detector, the backscatter radiation passed through the filters may be measured and integrated at different positions of the radiation beam to produce a composite image of the specimen. In this manner, irregularities and associated materials within the specimen may be more easily identified. | 11-12-2015 |
20150323437 | APPARATUS AND METHOD TO MEASURE DUROMETER HARDNESS AT, ABOVE, AND BELOW ROOM TEMPERATURE - An apparatus and its method of use to measure indentation hardness of rubber materials at, above or below room temperature according to the standard test method ASTM D2240. | 11-12-2015 |
20150321768 | AIRCRAFT INTERIOR MONITORING - A system for monitoring an aircraft interior may include a multiplicity of sensors each placed at a selected location of a plurality of locations within the aircraft interior. Each sensor is configured to monitor a condition in an associated area of the aircraft interior. The system may also include a server onboard the aircraft. The onboard server is configured to receive data from each of the multiplicity of sensors and to control operation of each of the multiplicity of sensors. The system may also include a router onboard the aircraft. The onboard router is configured to communicate with a router off-board the aircraft and to transfer data from the onboard server to the off-board router. The off-board router is associated with a ground monitoring facility that is configured to analyze data from each of the multiplicity of sensors, check or compare the data to reference data and depending upon any levels being exceeded an appropriate alert may be generated. | 11-12-2015 |
20150321766 | Nacelle-To-Pylon Fairing - A nacelle-to-pylon fairing formed over at least a portion of an inter-region between a nacelle and a pylon of an aircraft may include a longitudinal axis, a lateral axis and a transverse axis, an upper end incorporated to the pylon at a fairing-to-pylon interface, and a lower end incorporated to the nacelle at a fairing-to-nacelle interface, wherein the fairing defines a surface between the upper end and the lower end. | 11-12-2015 |
20150321761 | CART CONTROL SYSTEMS AND METHODS FOR CONTROLLING CART CASTER DIRECTION - Cart control systems and methods of controlling cart caster direction allow for operation of carts near walls without caster jamming. Cart control systems comprise a cart with one or more swivel casters, a wall, and a guide surface proximate the wall that is configured to swivel outwardly at least one of the swivel casters to be directed toward the wall when the swivel caster traverses the guide surface in a direction substantially parallel to the wall. When the caster is directed toward the wall, the floor contact of the caster is further away from the wall than the swivel axis of the caster and generally under the cart. When reversing direction, the caster swivels outwardly, with the floor contact remaining further away from the wall and generally under the cart. Thus, the caster does not swivel into the wall and jam the cart. | 11-12-2015 |
20150321322 | METHOD AND APPARATUS FOR APPLYING TORQUE - One example of the present disclosure relates to a wrench for applying torque to an object threadably engaging a part. The wrench includes a first handle, a second handle, a drive, a planetary gear mechanism, a first pawl, and at least one second pawl. The drive includes an internal gear and an external gear. The planetary gear mechanism includes a ring gear, a sun-gear component including a sun gear, and a planetary carrier including at least one pinion gear in mesh with the ring gear and the sun gear. The first handle is coupled to the ring gear. The second handle is coupled to the planetary carrier. The first pawl is movably coupled to the first handle and is biased to contact the external gear of the drive. The second pawl is movably coupled to the sun-gear component and is biased to contact the internal gear of the drive. | 11-12-2015 |
20150319832 | System and Method for Quantifying X-Ray Backscatter System Performance - A system for quantifying x-ray backscatter system performance may include a support, a plurality of rods mounted on the support, the rods of the plurality of rods arranged in parallel to each other, having generally curved outer surfaces, and being arranged in groups of varying widths, each group of the groups having at least two of the rods of a same width, and a user interface configured to be connected to receive a backscatter signal from an x-ray backscatter detector associated with an x-ray tube, and generate a display representing photon counts of x-ray backscatter for each rod of the plurality of rods from x-rays transmitted by the x-ray tube. | 11-05-2015 |
20150319216 | TRANSFERRING FILES BETWEEN DIFFERENT OPERATING SYSTEMS - Disclosed herein is a method for transferring files between different operating systems that includes sending one or more files from a first computing device executing a first operating system to a second computing device executing a second operating system. The first operating system is incompatible with the second operating system. The method also includes processing data of the one or more files using one or more applications executing within the second operating system on the second computing device. Further, the method includes receiving results of the data processing on the first computing device executing the first operating system. | 11-05-2015 |
20150318914 | HITLESS REARRANGEMENT OF A SATELLITE-HOSTED SWITCH VIA PROPAGATED SYNCHRONIZATION - An apparatus includes an analog front end to receive an analog input including user data, and an analog-to-digital converter to convert the analog input to digital signals including the user data. A digital channelizer may process the digital signals to generate frequency slices of user data, and a digital combiner may assemble the frequency slices to form output sub-bands of user data. A digital switch may route the frequency slices from the digital channelizer to the digital combiner according to a selected map of a plurality of available maps. The apparatus also includes a map selector to communicate map select data that indicates the selected map. The digital channelizer may receive and insert the map select data into the frequency slices in-band with the user data thereof. And the digital switch may interpret the map select data inserted into and route the frequency slices according to the selected map. | 11-05-2015 |
20150317501 | SYSTEMS AND METHODS FOR USE IN AUTHENTICATING AN OBJECT - A system for use in authenticating an object is provided. The system includes a radio-frequency identification tag coupled to the object and an interrogation system. The interrogation system includes a backscatter x-ray source configured to discharge backscatter x-ray beams towards the object. The backscatter x-ray source is calibrated such that the backscatter x-ray beams cause the radio-frequency identification tag to emit a signal. The system also includes a radio-frequency detector configured to receive the signal from the radio-frequency identification tag and a computing device in communication with the radio-frequency detector. The computing device is configured to obtain first identifying information of the object from the signal and authenticate the object from the first identifying information. | 11-05-2015 |
20150317128 | INTEGRATED INFORMATION EXCHANGE MANAGEMENT AND CONTROL OF DESIGN CONFIGURATIONS - An apparatus for managing data exchange between tools for multiple products in a product line is provided. The apparatus includes an application launcher configured to create a workspace to support a plurality of applications. The apparatus also includes an application manager configured to execute as a web service and load a first data and a second data associated with a first application and a second application, respectively, into the workspace. The apparatus also includes a concurrent engineering data service configured to capture data types associated with the first data and the second data and resolve differences in the data types wherein the data types comprise at least strings, doubles, and integers. The apparatus also includes a data storage and retrieval service configured to enforce integrity of and access rules associated with the first data and the second data. | 11-05-2015 |
20150316649 | AIRCRAFT ENHANCED REFERENCE SYSTEM AND METHOD - A method including placing first and second measurement devices proximate first and second aircraft doors, respectively, and determining a first position of the second measurement device relative to a second position of the first measurement device. The method includes placing first and second pluralities of reflective devices inside the aircraft proximate the first and second doors, respectively. The method includes measuring first and second distances from the first and second measurement devices to the first and second pluralities of reflective devices, respectively, and measuring second distances from the second measurement device to the second plurality of reflective devices. Based on a determined position of the second measurement device and further based on the first distances and second distances, third distances are determined between each of the first and second pluralities of reflective devices. The third distances provide a measurement baseline for points on a fuselage and wings. | 11-05-2015 |
20150315999 | SELF-SEALING APPARATUS THAT ADJUSTS A THROAT AREA OF A NOZZLE - A flow control panel in an aircraft engine two-dimensional, convergent/divergent nozzle adjusts a throat area of the nozzle and is configured to be self-sealing, thereby requiring fewer parts and providing a more simplified construction of the throat area of the nozzle. | 11-05-2015 |
20150315972 | METHODS AND APPARATUS FOR NOISE ATTENUATION IN AN ENGINE NACELLE - An acoustic liner includes a first core that has a plurality of first core cells defined by a corresponding plurality of first core cell walls. The first core has a first core thickness. The acoustic liner also includes a second core that has a plurality of second core cells defined by a corresponding plurality of second core cell walls. The second core has a second core thickness, and the first core thickness and the second core thickness are unequal. The acoustic liner further includes a second fabric sheet coupled between the first core and the second core. Each of the plurality of second core cell walls generally is not coplanar with any of the plurality of first core cell walls. | 11-05-2015 |
20150315966 | Hypersonic Vehicle Base Drag Reduction and Improved Inlet Performance Through Venting Forebody Bleed Air to Base Area Using Open Core Ceramic Composites - A system and method of air routing for an air-breathing engine is disclosed. Air enters the front of a scramjet engine via an inlet region. The inlet region is connected to a duct, which extends to the aft region of the scramjet engine where a base area of the air-breathing engine is located. The duct walls are formed using a porous structure fluidly coupled to apertures in both the inlet region and the base area. The air that enters the inlet region is routed through the porous walls of the duct and expelled at the base area. This expulsion of air through apertures in the base area causes base pressure to increase, which reduces base drag. Additionally, pulling air through perforations in the inlet region reduces the amount of low momentum flow entering the engine, which improves engine performance. | 11-05-2015 |
20150315449 | COMPOSITE MATERIAL CONTAINING GRAPHENE - In one aspect, a composite material is disclosed herein that includes graphene platelets dispersed in a matrix. In some cases, the graphene platelets are randomly oriented within the matrix. The composite material can provide improved thermal conductivity and may be formed into heat spreaders or other thermal management devices to provide improved cooling to electronic, electrical components and semiconductor devices. | 11-05-2015 |
20150314882 | AIRCRAFT ENGINE NACELLE BULKHEADS AND METHODS OF ASSEMBLING THE SAME - An engine nacelle includes an exterior wall and an interior wall. A forward bulkhead is coupled between the interior wall and the exterior wall, wherein the forward bulkhead comprises a curvilinear body portion that extends between the interior wall and the exterior wall. The engine nacelle also includes an aft bulkhead coupled between the interior wall and the exterior wall, wherein the aft bulkhead comprises a curvilinear body portion that extends between the interior wall and the exterior wall. | 11-05-2015 |
20150314874 | OPTIMALLY CONFIGURED AIR-FLOW GALLEY CART - A galley cart has a rear wall with an inlet port and an outlet port. A first divider has a first edge, wherein a first distance is defined between the first edge and a front wall. A second divider has a second edge, wherein a second distance is defined between the second edge and the front wall. The second distance is less than the first distance for control of the flow of cooling air. | 11-05-2015 |
20150314850 | LIPSKIN FOR A NACELLE AND METHODS OF MAKING THE SAME - A lipskin for a nacelle includes a generally annular first lipskin segment that extends generally upstream from a first lipskin edge to a forward edge. The forward edge is proximate to a hilite of the nacelle. The lipskin also includes a generally annular second lipskin segment that extends generally downstream from the forward edge to a second lipskin edge. The second lipskin segment is oriented generally concentrically about the first lipskin segment. The first lipskin segment and the second lipskin segment are coupled together at the forward edge. | 11-05-2015 |
20150314584 | SYSTEM AND METHOD FOR AUTOMATED INITIAL SEPARATION OF COMPOSITE PLY BACKING - A method for initial separation of an adhered backing film from an uncured pre-impregnated composite lamina having an edge includes exposing and supporting the edge of the composite lamina, and applying an impact force to the exposed edge with an automated tool. The impact force is sufficient to cause delamination of the backing film from the composite lamina without damaging the lamina. | 11-05-2015 |
20150314577 | STRUCTURAL INTEGRATED REPAIR METHOD AND SYSTEM TOOL DEVICE FOR REPAIRING DELAMINATED COMPOSITE STRUCTURES - A system for repair of damaged holes in composite structures incorporates a repair system tool device having a sleeve sized to be closely received in a hole in a composite structure. The sleeve has a central bore for receiving parent resin and an array of orifices for radial expulsion of the parent resin into the hole. A caul plate seals the central bore and a vacuum bag covering the caul plate is sealed to the surface of the composite structure. Introduction of vacuum in the vacuum bag provides a differential pressure for infusion of resin from the orifices in the sleeve into delaminations extending from the hole. | 11-05-2015 |
20150314545 | Aircraft Foam Insulation Method and Apparatus - Methods and apparatus for manufacturing a foam insulation panel to include a panel feature conforming to a first feature of an aircraft sidewall assembly include compressing opposed first and second surfaces of a foam block, advancing a cutter transversely through the foam block to separate the foam block into an excess layer and the foam insulation panel, and translating the foam block by an offset distance determined from the aircraft sidewall assembly first feature to form the panel feature. | 11-05-2015 |
20150313356 | METHOD AND APPARATUS FOR COOLING AN AIRLINE GALLEY CART USING A SKIN HEAT EXCHANGER - A system for cooling a thermally insulated galley cart in an aircraft incorporates a skin heat exchanger configured to transfer heat to an aircraft skin. A cooling system is in communication with the skin heat exchanger and is configured to be removably coupled with a thermally insulated galley cart. | 11-05-2015 |