A system and a method include a resource scheduling control unit configured to receive inputs including information regarding pilots and pilot training resources, generate schedules for the pilots based on the inputs, and output the schedules to one or more user interfaces.
G09B 19/00 - Teaching not covered by other main groups of this subclass
G06Q 10/0631 - Resource planning, allocation, distributing or scheduling for enterprises or organisations
G09B 9/08 - Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer
2.
METHOD AND APPARATUS FOR CONTROLLING COMPUTING ASSETS WITHIN A ZERO-TRUST ARCHITECTURE
A method and apparatus are disclosed for controlling access of a computing device to a multi-layer network implementing a zero-trust architecture, the multi-layer network including a switch and apparatus for controlling access to a plurality of hierarchical levels of the multi-layer network. The method includes receiving, at the apparatus, an access request message from the computing device, the access request message including one or more identifiers associated with the computing device for requesting access to the multi-layer network. The method further includes determining a hierarchical penetration level among the plurality of hierarchical levels of the multi-layer network to be assigned to the computing device based on the one or more identifiers within the access request message. The method further includes assigning the hierarchical penetration level to the computing device, and granting the computing device access and control privileges to the multi-layer network, based on the assigned hierarchical penetration level.
H04L 9/32 - Arrangements for secret or secure communications; Network security protocols including means for verifying the identity or authority of a user of the system
H04W 12/086 - Access security using security domains
A monitoring system and method of monitoring cargo on a vehicle during transport. The monitoring includes determining the location of the cargo that is loaded on the vehicle and monitoring one or more environmental conditions of the vehicle where the cargo is located. The monitoring system includes a control unit that receives signals from sensors that are located where the cargo is stored. Based on the signals from the sensors, the control unit is configured to determine the location and the one or more environmental conditions.
G01D 1/18 - Measuring arrangements giving results other than momentary value of variable, of general application with arrangements for signalling that a predetermined value of an unspecified parameter has been exceeded
H04W 4/38 - Services specially adapted for particular environments, situations or purposes for collecting sensor information
G01K 1/024 - Means for indicating or recording specially adapted for thermometers for remote indication
B60H 1/00 - Heating, cooling or ventilating devices
B64D 9/00 - Equipment for handling freight; Equipment for facilitating passenger embarkation or the like
B64D 13/00 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
G01S 5/00 - Position-fixing by co-ordinating two or more direction or position-line determinations; Position-fixing by co-ordinating two or more distance determinations
4.
SYSTEM AND METHOD FOR SCANNING AND TRACKING CARGO FOR TRANSPORT
Systems and methods for monitoring cargo that is loaded onto a vehicle. One or more sensors are positioned and configured to scan the cargo unit. Signals from the sensors are transmitted through a communication network to a control unit. The control unit determines a three-dimensional shape of the cargo unit based on the signals from the sensors. The control unit can also determine other aspects about the loading and unloading process to increase the efficiency.
A pilot training evaluation system and method includes receiving a first training performance data set. The pilot training evaluation system and method also includes analyzing the first training performance data set to determine a correlation between the first training performance data set and a training data comparison set, generating a training modification recommendation for an automated training system based at least on the correlation, and communicating the training modification recommendation to the automated training system.
An engine attachment system includes a strut box. The strut box includes a longitudinal axis, a forward portion that extends along the longitudinal axis, and an aft portion that extends from the forward portion along the longitudinal axis. The engine attachment system includes a forward attachment apparatus that is coupled to the forward portion of the strut box and that is coupleable to a forward spar of the wing. The engine attachment system includes an aft attachment apparatus that is coupled to the aft portion of the strut box and that is coupleable to an aft spar of the wing. When the strut box is coupled to the wing by the forward attachment apparatus and the aft attachment apparatus, the aft portion of the strut box is positioned under the wing. The strut box is coupleable to an engine.
B64D 27/40 - Arrangements for mounting power plants in aircraft
B64C 7/00 - Structures or fairings not otherwise provided for
F02C 7/20 - Mounting or supporting of plant; Accommodating heat expansion or creep
F16M 7/00 - FRAMES, CASINGS OR BEDS OF ENGINES, MACHINES OR APPARATUS, NOT SPECIFIC TO ENGINES, MACHINES OR APPARATUS PROVIDED FOR ELSEWHERE; STANDS; SUPPORTS - Details of attaching or adjusting engine beds, frames, or supporting-legs on foundation or base; Attaching non-moving engine parts, e.g. cylinder blocks
A system and method include a first icing detector configured to detect a first icing condition in relation to one or more portions of an aircraft. The first icing detector is configured to output a first icing signal indicative of the first icing condition. A second icing detector is configured to detect a second icing condition in relation to the one or more portions of the aircraft. The second icing detector is configured to output a second icing signal indicative of the second icing condition. A control unit is in communication with the first icing detector and the second icing detector, receives the first icing signal and the second icing signal and distinguishes between the presence of supercooled liquid water and ice crystal icing in response to receiving one or both of the first icing signal or the second icing signal.
B64D 15/20 - Means for detecting icing or initiating de-icing
G01K 7/36 - Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat using magnetic elements, e.g. magnets, coils
G01N 25/02 - Investigating or analysing materials by the use of thermal means by investigating sintering
8.
NO-BACK BRAKE FOR A FLIGHT CONTROL ACTUATION SYSTEM AND METHOD
A no-back brake includes a torque tube and a brake. The brake is configured to be axially displaced in response to a force to prevent the torque tube from rotating. The brake includes a rotor that is concentric with the torque tube and that is fixed to the torque tube so that the rotor rotates with the torque tube. The brake includes a stator that is concentrically mounted on the torque tube so that the torque tube is rotatable relative to the stator. The brake includes a friction device located between the rotor and the stator. The friction device is configured to form a frictional coupling between the rotor and the stator that opposes relative rotational motion between the rotor and the stator when the brake is axially displaced. The frictional device includes a composite material.
F16D 55/36 - Brakes with a plurality of rotating discs all lying side by side
F16D 55/41 - Brakes with a plurality of rotating discs all lying side by side actuated by a fluid-pressure device arranged in or on the brake by means of an intermediate leverage
9.
METHOD AND APPARATUS FOR INSPECTING A COMPOSITE ASSEMBLY
A method of inspecting a composite assembly that includes a core coated with resin. Inspecting the composite assembly includes accessing an image of a cross section of the core, the image having a dot matrix data structure with a matrix of intensity values and identifying a subset of the intensity values that describe a distribution of the resin on the core. Next, the intensity values of the subset of the intensity values are classified to indicate either uniform or non-uniform distribution of the resin on the core. Either a first comparison determining a ratio of uniform resin or a second comparison determining a ratio of non-uniform resin is performed. Based on the first comparison or the second comparison as performed, a quality of the composite assembly is determined. Finally, an indication of the quality of the composite assembly is output.
G06V 10/764 - Arrangements for image or video recognition or understanding using pattern recognition or machine learning using classification, e.g. of video objects
10.
SYSTEM AND METHOD OF RESPONSE TO AN UNSTABLE APPROACH DURING AN APPROACH TO LANDING FOR AN AIRCRAFT
A method includes determining, at a computing system of an aircraft, a target path for an approach to landing based on flight data. The method includes determining an approach phase of approach phases of the approach to landing. The method includes determining a real-time operational region of the aircraft for each monitored condition of monitored conditions based on the real-time aircraft data, the target path, and operational regions for each monitored condition. The method includes accessing notification content for a particular monitored condition for the approach phase. The real-time operational region for the particular monitored condition for the approach phase is outside of a target region of the particular monitored condition for the approach phase. The method also includes sending one or more notification signals based on the notification content from the computing system to one or more output systems.
A system and method for determining a width of a gap in a structure is provided. The system uses an underwater spark discharge to generate a compression wave in a first vessel containing a liquid. The system further includes a second vessel in which a vacuum is pulled to hold the first vessel against the structure. The compression wave is directed to propagate from the liquid into the structure and is detected after it propagates through the structure including the gap.
12.
CO-CURED UV/VISIBLE LIGHT-RESISTANT COMPOSITE MATERIAL FOR STRUCTURAL AIRCRAFT ASSEMBLY
Co-curable and co-cured UV/visible light-resistant composite materials are disclosed with UV/visible light protection exclusively imparted to a co-curable composite material substrate assembly by a co-curable UV/visible light-resistant fiberglass layer disposed to cover the co-curable and co-cured composite material substrate.
B32B 7/02 - Physical, chemical or physicochemical properties
B29C 35/02 - Heating or curing, e.g. crosslinking or vulcanising
B32B 27/04 - Layered products essentially comprising synthetic resin as impregnant, bonding, or embedding substance
B32B 37/15 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers with at least one layer being manufactured and immediately laminated before reaching its stable state, e.g. in which a layer is extruded and laminated while in semi-molten state
B32B 38/00 - Ancillary operations in connection with laminating processes
B64C 1/12 - Construction or attachment of skin panels
C08J 5/24 - Impregnating materials with prepolymers which can be polymerised in situ, e.g. manufacture of prepregs
13.
CO-CURED UV/VISIBLE LIGHT-RESISTANT FIBREGLASS COATED COMPOSITE MATERIAL FOR AIRCRAFT FUSELAGE ASSEMBLY
Co-curable and co-cured UV/visible light-resistant fiberglass-coated UV/visible light composite structural material substrates, and aircraft fuselages comprising co- cured UV/visible light-resistant fiberglass-coated composite material substrates and methods of their manufacture are disclosed.
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
B32B 5/28 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer impregnated with or embedded in a plastic substance
B32B 17/04 - Layered products essentially comprising sheet glass, or fibres of glass, slag or the like in the form of fibres or filaments bonded with or embedded in a plastic substance
B32B 27/04 - Layered products essentially comprising synthetic resin as impregnant, bonding, or embedding substance
B32B 37/15 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers with at least one layer being manufactured and immediately laminated before reaching its stable state, e.g. in which a layer is extruded and laminated while in semi-molten state
B32B 38/00 - Ancillary operations in connection with laminating processes
B64C 1/12 - Construction or attachment of skin panels
14.
CO-CURED UV-RESISTANT FIBERGLASS COATED COMPOSITE MATERIAL FOR AIRCRAFT WING FUEL TANK ASSEMBLY
Composite material protection from UV degradation is disclosed by providing a co- cured composite material substrate co-cured with a UV/visible light-resistant fiberglass layer to form co-cured composite materials for exclusively imparting UV/visible light- resistant properties to co-cured composite material substrates for use in UV/visible light-resistant vehicle fuel tank assemblies.
B32B 27/04 - Layered products essentially comprising synthetic resin as impregnant, bonding, or embedding substance
B32B 37/15 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers with at least one layer being manufactured and immediately laminated before reaching its stable state, e.g. in which a layer is extruded and laminated while in semi-molten state
B32B 38/00 - Ancillary operations in connection with laminating processes
B60K 15/073 - Tank construction specially adapted to the vehicle
C08J 5/24 - Impregnating materials with prepolymers which can be polymerised in situ, e.g. manufacture of prepregs
15.
GROUND BASED AIRCRAFT WING AND NACELLE MOCKUP DESIGN FOR TRAINING
A ground-based wing mockup station is provided. The mockup station comprises a primary support structure removably coupled to a floor and a wing mockup coupled to the primary support structure. A secondary support structure configured to suspend the wing mockup over the floor from the primary support structure. A payload pylon mockup is coupled to the wing mockup, wherein the payload pylon mockup is configured to hold an apparatus. The primary support structure, secondary support structure, wing mockup, and payload pylon mockup are configured to support a weight at least equal to the apparatus.
A method of minimizing a cost function of a quantum computation is provided. The method comprises receiving input of an initial state of a quantum problem instance comprising a Hamiltonian with an associated cost function. The Hamiltonian is converted into a number of Pauli strings, which are used to form an operator pool. The Pauli strings in the operator pool are ranked according to how much they lower a value of the cost function with respect to the initial state. Pauli strings are iteratively added from the operator pool to a parameterized quantum circuit, in a manner to minimize circuit depth, until a variational quantum eigensolver (VQE) algorithm converges to an approximate ground state wave function generated by the parameterized quantum circuit.
An aircraft includes a wing having a longitudinal centerline axis, a leading edge, a trailing edge, thickness, and a chord, an engine having a longitudinal axis vertically aligned with the wing chord and parallel to the longitudinal centerline axis and defining a reference line, a pylon connecting the wing to the engine, and a fairing received over the pylon. The fairing defines a horizontal plane, and first and second planes perpendicular to the longitudinal axis, the second plane being aft of the first plane. The fairing defines an aerodynamic surface configured such that the first plane intersects the horizontal plane and the aerodynamic surface at a first intersection point laterally displaced from the reference line by a first distance. The second plane intersects the horizontal plane and the aerodynamic surface at a second intersection point laterally displaced from the reference line by a second distance greater than the first distance.
A system and a method include one or more control units configured to receive compiled flight data for a plurality of aircraft of a fleet from a flight data aggregator sub-system. The one or more control units are configured to automatically determine aircraft utilization for the plurality of aircraft of the fleet based on the compiled flight data for the plurality of aircraft of the fleet.
The seating systems comprise a seat module and a seat track assembly comprising a plurality of seat-receiving regions, a seat track, and an electrical distribution system. The electrical distribution system comprises a plurality of track electrical contacts disposed along the seat track in the seat-receiving regions. The seat module comprises a base coupler configured to couple with the seat track at any seat-receiving region and a seat module electrical system having a seat electrical contact. The base coupler and the seat track are configured to position the seat electrical contact in connection with the track electrical contact of any seat- receiving region to which the base coupler is coupled. The methods comprise coupling the base coupler to a seat-receiving region, which comprises forming a connection between the seat electrical contact and the respective track electrical contact of the seat-receiving region, and providing electricity to the seat module via the electrical connection.
An aircraft adaptive battery charging system is provided. The adaptive battery charging system comprises: a battery system; a bidirectional converter, wherein the bidirectional converter is capable of an inverter mode and a rectifier mode; an alternating current (AC) motor; a number of controllable contactors that control electrical current between the battery system, bidirectional converter, AC motor, and a power source wherein the controllable contactors can be switched between a closed position to allow electrical current flow and an open position to prevent electrical current flow; a motor controller; a battery charging system controller configured to send control signals to the battery system, motor controller, and controllable contactors in response to system command signals; and a vehicle system controller that sends system command signals to the motor controller and battery charging system controller.
A method and mode conversion waveguide system for converting a mode of a light is provided. The light is sent through a single mode waveguide, wherein the light has a first mode while traveling through single mode waveguide. The light is sent from the single mode waveguide into a multimode interference region having connected to the single mode waveguide. The light is reflected with a cavity within the multimode interference region in a manner that causes the light to propagate away from the single mode waveguide. The light is output from multimode interference region, wherein the light has a second mode.
A method, apparatus, computer system, and computer program product for parallelizing quantum processes for processing a problem. A computer system identifies subproblems in the problem based on a structure of the problem. The computer system identifies quantum circuits in a set of quantum computers to process the subproblems. The computer system executes jobs on the quantum circuits to solve the subproblems.
In an example, a transformable cargo container for use with ground and air transportation vehicles is disclosed. The cargo container includes a main container body defining a storage chamber. The cargo container also includes a transformable assembly coupled to the main container body and positioned at an exterior of the main container body. The transformable assembly includes one or more supplemental containers and is movable between an aircraft configuration and a ground configuration. Based on the transformable assembly being in the aircraft configuration, the transformable cargo container has a non-rectangular cross-sectional area and is configured to occupy a partially-circular cross-sectional storage area of a fuselage of an aircraft. And based on the transformable assembly being in the ground configuration, the transformable cargo container is configured to occupy a rectangular cross-sectional storage area on a ground transportation vehicle.
In an example, a transformable cargo container for use with ground and air transportation vehicles is disclosed. The cargo container includes a main container body defining a storage chamber therein and including at least one inlet. The cargo container also includes a transformable assembly coupled to the main container body and positioned at an exterior of the main container body. The transformable assembly includes one or more supplemental containers and one or more supply ducts, at least one of the supplemental container(s) being configured to house refrigeration equipment. The transformable assembly is movable between an aircraft configuration and a ground configuration. Based on the transformable assembly being in either the aircraft configuration or the ground configuration, the refrigeration equipment is configured to supply coolant into the main container body via the supply duct(s) and the inlet(s).
A method, apparatus, and system include a cooling system comprising a payload refrigeration unit, control refrigeration unit, and a signal interface. The payload refrigeration unit has a set of payload cooling components that operate to cool a payload. The control refrigeration unit has a set of control circuit cooling components in a control circuit. The signal interface connecting the payload is located in the payload refrigeration unit in the control circuit located in the control refrigeration unit.
A jam detection system for a flap of a wing of an aircraft includes a linkage coupled to the flap and a support of the wing, and a sensor configured to detect a position of at least a portion of the linkage. The sensor is further configured to compare the position of the least a portion of the linkage to a jam threshold to determine if a jam condition exists. The linkage can also be coupled to a carriage moveably coupled to the support.
A system and method for forming an aft fuselage section of an aircraft include a forward section having a stabilizer channel. The forward section includes an upper sill beam and a lower sill beam. One or more pivot fittings are securely fastened between the upper sill beam and the lower sill beam. The one or more pivot fittings are configured to pivotally couple to a horizontal stabilizer within the stabilizer channel.
A machine and process for visualizing and interacting with a virtual model for a propulsion and/or fluid system. The machine includes a modular construction that includes a display server that comprises a socket in communication with a socket in a second server that comprises a piping evaluator that includes a traversal graph that accelerates processing of inputs for an executable block diagram for the propulsion and/or fluid system displayed on a graphical user interface. The traversal graph accesses support files generated by a scan shapes tool in communication with a diagram and vector graphic application with tailored stencils.
G06F 30/18 - Network design, e.g. design based on topological or interconnect aspects of utility systems, piping, heating ventilation air conditioning [HVAC] or cabling
G06F 3/0481 - Interaction techniques based on graphical user interfaces [GUI] based on specific properties of the displayed interaction object or a metaphor-based environment, e.g. interaction with desktop elements like windows or icons, or assisted by a cursor's changing behaviour or appearance
G06F 30/20 - Design optimisation, verification or simulation
F02K 99/00 - Subject matter not provided for in other groups of this subclass
A latch system and method are configured to adjustably secure a first component to a second component. The latch system includes a mounting base. A slide plate is moveably coupled to the mounting base. The slide plate is configured to be slidably adjusted relative to the mounting base. A housing is secured to the slide plate. The housing includes an arm channel configured to receive a latch arm.
A method for forming a ceramic-based material comprises depositing a ceramic- precursor composition comprising nanoparticles haying at least one dimension less than 100 nm and an aspect ratio of 1.5 or greater, and a carrier fluid on a surface of a substrate to form an as-deposited layer of the ceramic precursor composition; and sintering the as-deposited layer of the ceramic precursor composition at a sintering temperature to form a ceramic-based material.
B33Y 70/00 - Materials specially adapted for additive manufacturing
B33Y 40/20 - Post-treatment, e.g. curing, coating or polishing
C04B 35/462 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxides based on titanium oxides or titanates based on titanates
C04B 35/48 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxides based on zirconium or hafnium oxides or zirconates or hafnates
C04B 35/495 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxides based on vanadium, niobium, tantalum, molybdenum or tungsten oxides or solid solutions thereof with other oxides, e.g. vanadates, niobates, tantalates, molybdates or tungstates
C04B 35/50 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on rare earth compounds
A vehicle including a fuselage, and a fuel tank within the fuselage. The fuel tank includes one or more sealant layers disposed over one or more internal surfaces of the fuel tank. In at least one embodiment, a release agent is disposed between the one or more internal surfaces and the one or more sealant layers.
An antimicrobial coating composition is disclosed. The antimicrobial coating composition also includes a polymer having a plurality of alkene units and a plurality of macroCTA polymer units. The composition also includes one or more reactive silanes, one or more wetting agents, and one or more solvents. A method for applying an antimicrobial coating composition is disclosed. The method for applying an antimicrobial coating composition may include contacting a polymer, one or more wetting agents, one or more solvents, and one or more reactive silanes with one another to prepare an antimicrobial coating composition, homogenizing the antimicrobial coating composition, applying the antimicrobial coating composition to a substrate, and allowing the antimicrobial coating composition to dry at ambient conditions.
Ball screw rotary actuator with ball cage. In one embodiment, a ball screw rotary actuator includes an outer cylinder, a piston, and inner shaft. Outer ball bearings travel in helical groove between the outer cylinder and position to rotate the piston as it translates due to fluid pressure. The inner shaft is situated radially inward of the piston, and straight grooves are disposed between the piston and the inner shaft. Inner ball bearings travel in the straight grooves and rotate the inner shaft as the piston rotates. The ball screw rotary actuator also includes an outer ball cage to position the outer ball bearings in a spaced configuration, an outer indexing gear to control a position of the outer ball cage, an inner ball cage to position the inner ball bearings in a spaced configuration, and an inner indexing gear to control a position of the inner ball cage.
A blind fastener includes a sleeve having a distal end portion and a proximal end portion and defining a bore. The blind fastener also includes a core bolt at least partially received in the bore of the sleeve, the core bolt defining a core bolt axis and including a body having a distal end portion and proximal end portion axially opposed from the distal end portion, wherein the body is tapered from the distal end portion of the body to the proximal end portion of the body such that the core bolt causes radial expansion of the sleeve when the body is urged relative to the sleeve through the bore along the core bolt axis.
Systems and methods provide technology for inspections including receiving image data from a sensor, the sensor operable to scan an object, where the object is a manufactured object, generating a 3D image record for the object based on the image data, comparing the 3D image record with a stored design model for the object and/or a stored baseline image record of the object, and generating findings data based on the comparing, where the findings data is indicative of a discrepancy identified between the 3D image record and the one or more of the stored design model for the object or the stored baseline image record of the object. The sensor can be mounted on a moving platform such as a robotic arm, a track mounted assembly or a drone. The technology can further include a motion or flight plan for moving the sensor relative to the object.
G01N 37/00 - INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES - Details not covered by any other group of this subclass
A method for modeling a new design for electromagnetic effects includes identifying, with a model-based system engineering tool, an area of interest in the new design where a lightning strike may occur. The new design includes structural features and electromagnetic features. The method further includes generating, with an electromagnetic effects solver tool and a structural solver tool, a design model for the area of interest in the new design, extracting design parameters from the design model, and generating a reduced order model by processing the design parameters, test results, and simulation results with a modeling tool. The reduced order model couples the structural features with the electromagnetic features. The test results are determined by tests of known designs. The simulation results are determined by simulations of known models. The method further includes storing the reduced order model in a storage medium that is readable by a statistical modeling tool.
Systems, apparatus, and methods for musculoskeletal ergonomic improvement are disclosed. An example apparatus includes a performance analyzer to predict a musculoskeletal strain event for a portion of a body of a user based on strain sensor data collected via one or more strain sensors associated with the user and transmit, in response to the prediction of the strain event, an instruction including an alert to be output by the output device. The example apparatus includes an ergonomic form recommendation generator to transmit, in response to the prediction of the strain event, an instruction including an ergonomic form measure to be output by the output device.
A61B 5/22 - Ergometry; Measuring muscular strength or the force of a muscular blow
G16H 50/20 - ICT specially adapted for medical diagnosis, medical simulation or medical data mining; ICT specially adapted for detecting, monitoring or modelling epidemics or pandemics for computer-aided diagnosis, e.g. based on medical expert systems
A61B 5/11 - Measuring movement of the entire body or parts thereof, e.g. head or hand tremor or mobility of a limb
Extended reality systems, apparatus, and methods for musculoskeletal ergonomic improvement are disclosed. An example apparatus includes an avatar generator to generate an avatar based one or more properties of a user; an avatar position analyzer to determine a first ergonomic form for a movement based on the one or more properties of the user, the avatar generator to cause an output device to display the avatar in the first ergonomic form; and a feedback generator to determine a second form associated with movement of the user based on sensor data collected via one or more sensors associated with the user; generate a graphical representation of the user in the second form; and cause the output device to display the graphical representation of the user with the avatar.
G06T 19/00 - Manipulating 3D models or images for computer graphics
G16H 20/30 - ICT specially adapted for therapies or health-improving plans, e.g. for handling prescriptions, for steering therapy or for monitoring patient compliance relating to physical therapies or activities, e.g. physiotherapy, acupressure or exercising
A system includes an aircraft including a position sensor configured to output a position signal regarding a position of the aircraft within an airspace, and a propulsion system configured to output a position confirmation signal regarding the position of the aircraft within the airspace. A method includes outputting, by a position sensor of an aircraft, a position signal regarding a position of the aircraft within an airspace; and outputting, by a propulsion system of the aircraft, a position confirmation signal regarding the position of the aircraft within the airspace.
Methods include disposing a layer of a solution or emulsion having a nanostructure on a surface. The surface further includes a SARS-CoV-2 virus disposed thereon. The nanostructure includes a compound or salt thereof. The compound includes one or more styrene units, one or more N-alkylacrylamide units, and a moiety represented by the formula:(I) where R1 is alkyl. The compound includes a moiety represented by the formula: (II) where R1 is alkyl and R2 and R3 are independently hydrogen or alkyl. The compound includes a plurality of N,N-(dialkylamino)(divalent alkyl) alkylacrylate units. One or more of the N,N-(dialkylamino)(divalent alkyl)alkylacrylate units has an unsubstituted nitrogen. One or more of the N,N-(dialkylamino)(divalent alkyl)alkylacrylate units is substituted with a C1-C16 alkyl moiety, and one or more of the N,N-(dialkylamino)(divalent alkyl) alkylacrylate units is substituted with a moiety selected from the group consisting of guanidine, polygalactose, coumarin, and combination(s) thereof.
A01N 43/16 - Biocides, pest repellants or attractants, or plant growth regulators containing heterocyclic compounds having rings with one or more oxygen or sulfur atoms as the only ring hetero atom with one hetero atom six-membered rings with oxygen as the ring hetero atom
A method of managing in-service operation of a fleet of aircraft is provided that includes generating a schedule of flights through an air transportation network that includes airports, and that includes direct flight routes or flight connections between the airports. The method includes performing a fleet assignment of the fleet of aircraft to the schedule of flights based on availability metric values for respective aircraft of the fleet of aircraft, and dispatching the fleet of aircraft serve the schedule of flights to according to the fleet assignment. In this regard, performing the fleet assignment includes, for an aircraft of the fleet of aircraft, accessing reliability metric values for parts of the aircraft. Availability scores for the aircraft are determined based on the reliability metric values from respective ones of the data sources, and the availability scores are combined to determine an availability metric value for the aircraft.
Systems and methods provide technology for wayfinding assistance for visually- impaired passengers, including short-range transmitters distributed within a passenger cabin of an aircraft, a transit vehicle or a vessel, each short-range transmitter located proximate to a respective waypoint in the passenger cabin to transmit a signal identifying the respective waypoint in the passenger cabin, and a client application to, responsive to passing within a range of one of the plurality of short-range transmitters, receive a first transmission from the short-range transmitter and emit one or more of a first audible signal or a first haptic signal, based on the first transmission, as wayfinding assistance to a user of the client device. The technology can also include a mid-range transmitter located proximate to a service area in the passenger cabin, to transmit a signal providing at least one of a status of or a location of the service area.
G01S 1/00 - Beacons or beacon systems transmitting signals having a characteristic or characteristics capable of being detected by non-directional receivers and defining directions, positions, or position lines fixed relatively to the beacon transmitters; Receivers co-operating therewith
A61F 9/08 - Devices or methods enabling eye-patients to replace direct visual perception by another kind of perception
B60Q 9/00 - Arrangement or adaptation of signal devices not provided for in one of main groups
G01S 1/02 - Beacons or beacon systems transmitting signals having a characteristic or characteristics capable of being detected by non-directional receivers and defining directions, positions, or position lines fixed relatively to the beacon transmitters; Receivers co-operating therewith using radio waves
43.
ERGONOMICS IMPROVEMENT SYSTEMS HAVING WEARABLE SENSORS AND RELATED METHODS
Ergonomics improvement systems having wearable sensors and related methods. An example ergonomics improvement system includes an encoder system to couple to a limb of a body. The encoder sensor system to generate first outputs in response to movement of the limb relative to the body to determine a position of the limb relative to the body. The system includes a load sensor to generate a second output representative of a load carried by the body and a position sensor to generate a third output representative of a position of a right foot of the body relative to a position of a left foot of the body.
Wearable ergonomics improvement systems and related methods are disclosed. An example ergonomics improvement system includes a membrane including a first frame having a plurality of first cutouts defining a first pattern. The system includes a sensor coupled to the membrane and includes a second frame having a plurality of second cutouts defining a second pattern. The first pattern is complementary to the second pattern.
An apparatus for directing fluid flow is disclosed, including a valve structure having a chamber, a main port, a first port, and a second port, each of the ports being connected to the chamber. A poppet structure in the chamber is moveable between a first position blocking the first port and a second position blocking the second port. A first compliant member connecting the poppet structure to an inner wall of the chamber, is configured to alternate application of forces to the poppet structure, in opposite directions, between the first and second positions.
F16K 11/044 - Multiple-way valves, e.g. mixing valves; Pipe fittings incorporating such valves; Arrangement of valves and flow lines specially adapted for mixing fluid with all movable sealing faces moving as one unit comprising only lift valves with movable valve members positioned between valve seats
F16K 27/08 - Guiding yokes for spindles; Means for closing housings; Dust caps, e.g. for tyre valves
F16K 31/12 - Operating means; Releasing devices actuated by fluid
46.
AMPLIFIER WITH STACKED TRANSCONDUCTING CELLS IN PARALLEL AND/OR CASCADE "CURRENT MODE" COMBINING
An amplifier with stacked transconducting cells in parallel and/or cascade "current mode" combining is disclosed herein. In one or more embodiments, a method for operation of a high-voltage signal amplifier comprises inputting, into each transconducting cell of a plurality of transconducting cells, a direct current (DC) supply current (ldc), an alternating current (AC) radio frequency (RF) input current (IRF_INI), and an RF input signal (RFIN). The method further comprises outputting, by each of the transconducting cells of the plurality of transconducting cells, the DC supply current (ldc) and an AC RF output current (IRF_OUT). In one or more embodiments, the transconducting cells are connected together in cascode for the DC supply current (ldc), are connected together in parallel (or in cascade) for the RF input signal (RF1N), and are connected together in parallel (or in cascade) for the AC RF output currents (IRF_OUT).
H03F 3/195 - High-frequency amplifiers, e.g. radio frequency amplifiers with semiconductor devices only in integrated circuits
H03F 1/22 - Modifications of amplifiers to reduce detrimental influences of internal impedances of amplifying elements by use of cascode coupling, i.e. earthed cathode or emitter stage followed by earthed grid or base stage respectively
H03F 3/213 - Power amplifiers, e.g. Class B amplifiers, Class C amplifiers with semiconductor devices only in integrated circuits
47.
CONDUCTIVE POLYMER COATING COMPOSITION AND METHOD OF MAKING THE SAME
A conductive polymer coating composition including a conductive fibrillated structure and a base polymer, wherein the conductive fibrillated structure includes a fibrillated polymer and a conductive polymer grafted on the fibrillated polymer, and wherein the conductive polymer coating composition has an electrical conductivity from about 10-5 S/cm to about 10+1 S/cm and a thermal conductivity from about 1.1 W/m K to about 3 W/m K.
Systems, apparatuses, and methods relating to heat transfer devices having nested layers of helical fluid channels. In some examples, a device for transferring heat includes a set of nested tubular walls and a plurality of helical walls intersecting each of the nested tubular walls to form one or more first channel layers nested with one or more second channel layers. Each of the first and second channel layers includes a plurality of helical fluid channels. A first intake and a first outtake are in fluid communication with one another via the plurality of helical fluid channels of each first channel layer, for flow of a first fluid through the device. A second intake and a second outtake are in fluid communication with one another via the plurality of helical fluid channels of each second channel layer, for flow of a second fluid through the device.
F28D 7/00 - Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
A work platform configured to support one or more workers in proximity to a workpiece. The work platform includes sliders that are aligned along the length of the workpiece. The sliders are laterally movable towards and away from the workpiece. The sliders are individually movable with a position of each of the sliders relative to the workpiece being a function of the rotational position of the workpiece.
A reinforced sandwich panel, including two skin panels, a foam core disposed between the two skin panels and an expandable framework disposed within the foam core.
B32B 3/08 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by added members at particular parts
B32B 5/20 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by features of a layer containing foamed or specifically porous material foamed in situ
B32B 7/12 - Interconnection of layers using interposed adhesives or interposed materials with bonding properties
51.
SYSTEMS AND METHODS FOR PREVENTING A WALKWAY PLATFORM FLIP DOOR FROM BEING RAISED WITHOUT A GUARDRAIL INSTALLED
In an example, a system for preventing a flip door from being raised without a guardrail installed is disclosed. The system includes a guardrail having a post, and the post having a post dog. The system also includes a safety latch mechanism configured to be coupled to a fixed structure. The safety latch mechanism includes a body, a socket disposed in the body and configured to receive the post, and a door latch rotatably coupled to the body and biased in a latched position that is configured to retain a flip door in a lowered position. Based on the post being inserted into the socket of the safety latch mechanism, the post dog engages with and rotates the door latch from the latched position to an unlatched position, thereby allowing the flip door to be raised from the lowered position to a raised position.
In an example, a system is described. The system includes a guardrail having a post, and the post having a post dog. The system also includes a latch eye configured to be coupled to a flip door. The system also comprises a safety latch mechanism configured to be coupled to a fixed structure and including a body, a socket configured to receive the post, and a door latch rotatably coupled to the body and biased in a latched position that is configured to engage with the latch eye and thereby retain the flip door in a lowered position. Based on the post being inserted into the socket of the safety latch mechanism, the post dog engages with and rotates the door latch from the latched position to an unlatched position, thereby allowing the flip door to be raised from the lowered position to a raised position.
A resting area system and method for an internal cabin of a vehicle includes a monument, and a bed module coupled to the monument. The bed module includes one or more beds. The bed module is moveable between a stowed position and a deployed position relative to the monument.
A system includes a fuel level sensing probe inside a fuel tank and an exciter wire bundle to connect the fuel level sensing probe to a power source outside the tank. The exciter wire bundle includes an excitation wire and a grounded guard wire. The excitation wire and the grounded guard wire each include a resistive non- metallic wire. The system also includes a return signal wire bundle to connect the fuel level sensing probe to a device configured to measure a quantity of fuel within the tank. The return signal wire bundle includes a return signal wire and a grounded guard wire. The grounded guard wire of the return signal wire bundle and the grounded guard wire of the exciter wire bundle are configured to shield the return signal wire from electromagnetic interference. The return signal wire and the grounded guard wire each include a resistive non-metallic wire.
G01F 23/22 - Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm by measuring physical variables, other than linear dimensions, pressure or weight, dependent on the level to be measured, e.g. by difference of heat transfer of steam or water
B64D 37/32 - Safety measures not otherwise provided for, e.g. preventing explosive conditions
A method for recycling an aluminum alloy scrap includes performing selective oxidation roasting and washing treatment on the aluminum alloy scrap to obtain an uncoated aluminum alloy scrap; melting the uncoated aluminum alloy scrap in a refining furnace to obtain aluminum alloy melt liquid, online-detecting components of the aluminum alloy melt liquid and adding a metallic copper, a copper alloy, a magnesium alloy or a zinc alloy to the aluminum alloy melt liquid according to the requirements of target alloy components, performing pressure-controlled and oxygen-controlled melting through regulating pressure intensity and oxygen partial pressure in the refining furnace and coupling an external-field stirring mode to obtain refining aluminum alloy melt liquid; filtering the refining aluminum alloy melt liquid, to obtain an aluminum alloy melt with the target alloy components; and casting the aluminum alloy melt.
A method for computer analysis of a quality of an as-programmed surface of a composite laminate. A first data set representing an as-programmed top surface is generated based on as-programmed ply definitions and a tool surface definition. Thereafter, a second data set representing coordinates of points of a first mesh on the as-programmed top surface is generated, which points form a first mesh. Then a third data set representing coordinates of points of a second mesh on a defined tool surface is generated. A respective angle of each mesh element of the first mesh relative to a corresponding mesh element of the second mesh is then calculated. Each angle is compared to a threshold of acceptable angle. In response to an acceptable number of angles exceeding a threshold of acceptable angle, a tow placement machine may be programmed to fabricate a composite structure using the as-programmed ply definitions.
G01B 21/30 - Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring roughness or irregularity of surfaces
57.
METHOD FOR RECOVERING PROCESSED ALUMINUM SCRAPS OF AERONAUTICAL ALUMINUM ALLOY
A method includes performing pre-treating, comprising fire-roasting or wet-washing, on the processed aluminum scraps of aeronautical aluminum alloy. The method further includes performing pressing formation on the pre-treated processed aluminum scraps of aeronautical aluminum alloy to form block-shaped aluminum scraps. The method further includes performing oxygen-controlled smelting on the block-shaped aluminum scraps in a smelting furnace to form aluminum alloy melt. The method further includes performing casting on the aluminum alloy melt to obtain an aluminum alloy product of meeting component requirements of aeronautical aluminum alloy.
A method of developing a product is provided that includes generating a digital system model (DSM) that describes the product and a manufacturing process for the product, and generating a digital twin (DTw) of an instance of a component of the manufacturing process, the DTw including a digital replica of the instance. The method includes receiving attribute data for attributes of process/process characteristics subject to sources of variation that affect product quality. The digital replica is executed with input of the attribute data, and thereby updating the DTw to replicate the instance of the component of the manufacturing process as performed. A data analysis of the manufacturing process is performed based on the DTw as updated, and the manufacturing process is modified based on the data analysis to reduce variability in one or more product characteristics. The DTws of multiple instances may be used to generate further improvement.
G05B 19/4097 - Numerical control (NC), i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form characterised by using design data to control NC machines, e.g. CAD/CAM
59.
COMPUTATION OF AIRCRAFT AIRSPEED BY INCLUSION OF STATIC AIR TEMPERATURE
A system may include a static air temperature probe attached to an aircraft, an electronic flight instrument system, and a processor. The processor may be configured to measure a static air temperature at the aircraft using the static air temperature probe. The processor may further be configured to calculate a Mach number associated with the aircraft based at least partially on the static air temperature. The processor may also be configured to calculate a true air speed of the aircraft based on the Mach number. The processor may display an indication of the true air speed using the electronic flight instrument system. The processor may also be configured to calculate the speed of sound based at least partially on the static air temperature.
G01P 5/16 - Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring differences of pressure in the fluid using Pitot tubes
B64D 43/02 - Arrangements or adaptations of instruments for indicating aircraft speed or stalling conditions
60.
NACELLE INLET STRUCTURES, ENGINE ASSEMBLIES AND VEHICLES INCLUDING THE SAME, AND RELATED METHODS
Nacelle inlet structures, engine assemblies and vehicles including the same, and related methods. A nacelle inlet structure of an engine assembly includes an inlet outer barrel and an inlet inner barrel with a tubular portion and an inlet attachment flange. The tubular portion of the inlet inner barrel extends at least partially along a direction parallel to the engine axis, while the inlet attachment flange extends from the tubular portion. The inlet attachment flange is integrally formed with at least a portion of the tubular portion of the inlet inner barrel. The inlet attachment flange is configured to be operatively coupled to an engine case of the engine assembly to operatively couple the nacelle inlet structure to the engine case. In examples, a method of manufacturing an inlet inner barrel includes forming a composite laminate with a composite manufacturing process.
A demister for a gearing system includes a main body having an inner annular rim coupled to an outer annular rim through a first wall and a second wall opposite from the first wall. The main body is configured to be rotated about a central longitudinal axis to create centrifugal forces that separate oil mist particles from air. First fluid passages extend radially between and through the inner annular rim and the outer annular rim. The first fluid passages include a fluid inlet opening in the outer annular rim and a fluid outlet opening in the inner annular rim. The fluid inlet opening is configured to accept incoming air. The fluid outlet opening is configured to discharge filtered air.
A method for repairing a composite structure using pre-cured plugs. In accordance with one method, composite material is removed from a first composite laminate to form a cavity bounded by a tapered internal surface that extends from an opening at an outer mold line surface of the first composite laminate. In addition, a second composite laminate is machined to form a plug having a tapered surface. Then the plug is placed so that the tapered surface of the plug opposes the tapered internal surface of the first composite laminate. Thereafter, the tapered surface of the plug is bonded to the tapered internal surface of the first composite laminate. Optionally, a hole is drilled in the plug for receiving a fastener.
B29C 73/10 - Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass using preformed elements using patches sealing on the surface of the article
B32B 38/10 - Removing layers, or parts of layers, mechanically or chemically
B32B 43/00 - Operations specially adapted for layered products and not otherwise provided for, e.g. repairing; Apparatus therefor
A method for managing computing resources on a vehicle with line-replaceable units (LRUs) including respective allocated system resources for tasks the LRUs are designed to perform and respective unallocated system resources that are available is provided. Implementations of the method include identifying the LRUs and applying a middleware layer across the LRUs to establish an edge computing infrastructure in which the LRUs operate as edge nodes. The middleware layer receives information from the edge nodes identifying the unallocated system resources and identifies data sources onboard the vehicle, data provided by those sources, and tasks to be performed using the data. The middleware further determines expected operational performance of the edge computing infrastructure and distributes the tasks to be performed across the edge nodes based on the expected operational performance of the edge computing infrastructure.
G06F 15/16 - Combinations of two or more digital computers each having at least an arithmetic unit, a program unit and a register, e.g. for a simultaneous processing of several programs
64.
IGNITION-SUPPRESSING DEVICES FOR SHIELDING FASTENERS, AIRCRAFT FUEL TANKS HAVING FASTENERS, SHIELDED BY IGNITION SUPPRESSING DEVICES, AND METHODS OF INSTALLING IGNITION-SUPPRESSING DEVICES IN AIRCRAFT FUEL TANKS
An ignition-suppressing device (100) for shielding fasteners (106) comprises a ribbon (102) and receptacles (104) that are spaced apart from one another along the ribbon (102).
A tie-rod with a swivel tie-rod end includes a tie-rod central rod and a first tie-rod end including a swivel joint. The first tie-rod end is connected to the tie-rod central rod by the swivel joint. The swivel joint is operable to enable rotation of the first tie-rod end with respect to the tie-rod central rod while maintaining a common longitudinal axis between the first tie-rod end and the tie-rod central rod. The tie-rod further includes a second tie-rod end connected to the tie-rod central rod.
An insulation system for an aircraft fuselage uses a plurality of stringers extending longitudinally. An insulation blanket is configured for installation on the stringers and a plurality of stringer clips are attached to and extend from an outboard side of the insulation blanket. Each stringer clip has a connecting flange engaged to a cover of the insulation blanket. A first attachment arm extends outboard from a first end of the connecting flange and terminates in a first hook resiliently engaging the stringer. A second attachment arm extends outboard from a second end of the connecting flange and terminates in a second hook resiliently engaging the stringer.
F16B 2/20 - Clips, i.e. with gripping action effected solely by the inherent resistance to deformation of the material of the fastening
F16B 5/06 - Joining sheets or plates to one another or to strips or bars parallel to them by means of clamps or clips
F16L 59/12 - Arrangements for supporting insulation from the wall or body insulated, e.g. by means of spacers between pipe and heat-insulating material; Arrangements specially adapted for supporting insulated bodies
A system may include a camera module that may include a first infrared camera, a second infrared camera, and a visible light camera. The system may further include an autonomous vehicle that may include a vertically extendable arm attached to the camera module. The system may also include a processor configured to initiate movement of the autonomous vehicle around an aircraft according to a predetermined path, initiate a scan of an exterior surface of the aircraft using the first infrared camera, the second infrared camera, the visible light camera, or a combination thereof, determine whether a portion of the exterior surface of the aircraft is damaged based on the scan, and in response to the portion of the exterior surface of the aircraft being damaged, use the first infrared camera, the second infrared camera, and the visible light camera to generate a three- dimensional model of the portion of the exterior surface of the aircraft.
A three piece failsafe clevis includes a center portion having a center top surface, a planar first outer surface and a planar second outer surface. The second outer surface is oppositely oriented to the first outer surface. A channel in the center portion is configured to receive a tension and compression member. A left lateral portion is connected adjacent the first outer surface. The left lateral portion has a planar first inner surface received against the first outer surface and a left top surface coplanar with the center top surface. A right lateral portion is connected adjacent the second outer surface. The right later portion has a planar second inner surface received against the second outer surface and a right top surface coplanar with the center top surface.
A system may include a variable frequency independent speed (VFIS) motor- generator. The system may further include a first power conditioner coupled to a set of stator windings of the VFIS motor-generator and a second power conditioner, distinct from the first power conditioner, coupled to a set of primary windings of a high- frequency transformer, where a set of secondary windings of the high-frequency transformer are coupled to a set of rotor windings of the VFIS motor-generator. A method may include providing a first power signal at the set of stator windings. The method may further include generating a second power signal at the second power conditioner for driving the set of rotor windings, where a shaft speed of the VFIS motor-generator is based on a difference between a first frequency of the first power signal and a second frequency of the second power signal.
B60L 15/00 - Methods, circuits or devices for controlling the propulsion of electrically-propelled vehicles, e.g. their traction-motor speed, to achieve a desired performance; Adaptation of control equipment on electrically-propelled vehicles for remote actuation from a stationary place, from alternative parts of the vehicle or from alternative vehicles of the same vehicle train
H02K 11/04 - Structural association of dynamo-electric machines with electric components or with devices for shielding, monitoring or protection for rectification
H02P 27/04 - Arrangements or methods for the control of AC motors characterised by the kind of supply voltage using variable-frequency supply voltage, e.g. inverter or converter supply voltage
Systems and methods provide for the evaluation of flight controls for an aerial vehicle and define a vehicle dynamics model corresponding to an aerial vehicle. One or more barrier functions are constructed based on the defined vehicle dynamics model, and candidate invariant sets are identified for the defined vehicle dynamics model using the one or more barrier functions. A plurality of flight controls of the aerial vehicle are analyzed using the identified candidate invariant sets and within the analyzed candidate invariant sets, command tracking of the aerial vehicle is confirmed with control commands, using the analyzed plurality of flight controls. Control commands falling outside of the analyzed candidate invariant sets are identified.
An assembly integrates an aft wing spar root fitting to an aircraft fuselage when joining the aircraft wing to the aircraft body. The assembly provides structural strength to the connection between the aircraft wing and the aircraft body, provides corrosion prevention and provides improved inspection capabilities and repair capabilities to the aircraft wing and aircraft body connection.
A method for repairing a composite member includes assembling a composite stack on a surface. The composite stack includes a first book nested with a second book. An adhesive is disposed between the first book and the second book. At least one of the first book and the second book includes a first pattern of slots. The method further in- cludes setting the composite stack to yield a composite repair piece. The method further includes attaching the composite repair piece to the composite member. Also disclosed is a composite repair piece. The composite repair piece includes a first book and a second book. The second book is stacked on top of the first book. An adhesive is dis- posed between the first book and the second book. At least one of the first book and the second book includes a first pattern of slots.
B29C 73/10 - Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass using preformed elements using patches sealing on the surface of the article
Embodiments for hybrid pressure deck of an aircraft. One embodiment is a pressure deck disposed over a main gear wheel well of an aircraft. The pressure deck includes longitudinal beams extending in a forward and aft direction between an aft wheel well bulkhead and a rear spar of the aircraft. The pressure deck also includes a web attached to an underside of the longitudinal beams. The web includes a flat web portion supported by transverse stiffeners extending in an inboard and outboard direction, and a curved web portion including arches configured to flex laterally from load in the inboard and outboard direction. A transition between the flat web portion and the curved web portion extends at least partially in the forward and aft direction of the aircraft.
A method for automatic generation of integrated test procedures using system test procedures includes generating a system test case for each system model of a plurality of system models. The method also includes automatically generating an integrated test harness including a group of interacting system models of the plurality of system models. An output signal from one or more of the interacting system models is an input signal to one or more other interacting system models. The method additionally includes automatically generating an integrated test case for each system model in the integrated test harness and automatically running the integrated test case using an integrated test procedure. The method further includes generating an integrated test procedure coverage report in response to running the integrated test case.
Example apparatus, systems, and methods for managing common mode pneumatic events are disclosed herein. An example system includes a common mode pneumatic event detector to detect a common mode pneumatic event at pitot tubes of an aircraft, a latch, a relay switch in communication with the latch, and a latch controller to set the latch in a first state to cause the latch to output a first latch signal, the relay switch to output a first pressure signal in response to the first latch signal, the first pressure signal based on pressure data from the pitot tubes, and set the latch in a second state to cause the latch to output a second latch signal based on the detection of the common mode pneumatic event. The relay switch is to output a second pressure signal in response to the second latch signal. The second pressure signal includes estimated pressure data.
A Non-Geostationary Orbit (NGSO) satellite system is described that utilizes backbone route tables at its satellites that define different snapshots of a time-varying backbone topology of the NGSO satellite system. Because each satellite may see a different portion of the backbone topology, the backbone route tables at different satellites may be different from each other. Also, the backbone route tables at the satellites may be active at different times as the backbone topology changes over time. Different routing groups of backbone route tables may be defined in order to represent different routing options for packets arriving at a satellite. The routing options for a routing group may emphasis various network performance and security goals for traffic assigned to the routing group.
A calibration system for aircraft control surface actuation includes an inclinometer coupleable to an aircraft control surface. The inclinometer is configured to provide measurement data of an inclination value corresponding to an angle at which the surface is deflected. The system includes an adapter with a wireless transmitter module and an interface connector connected to the inclinometer. The adapter is configured to receive and wirelessly transmit the measurement data. The system includes a wireless receiver device and a computing device connected thereto to receive the measurement data. The computing device is configured to determine if the inclination value differs by more than a predetermined amount from a directed deflection angle for the surface. The computing device is also configured to communicate an adjustment amount to a controller configured to direct deflection of the surface, based on the difference between the measured inclination value and the directed deflection angle.
Methods and systems for charging a battery string while protecting against overcharging. One system includes: a pair of disconnect devices; a power distribution bus which is electrically connected to a battery string via the disconnect devices; a battery charger connected to supply battery power to the power distribution bus for charging the battery string; a module monitoring unit configured to sense individual battery cell voltages during charging; a first processor configured to activate one disconnect device to open when the sensed individual battery cell voltages indicate overcharging; a plurality of sensors connected to sense a full-string voltage measured across the battery string and first and second half-string voltages measured across first and second half-strings of the battery string; and a second processor connected to receive sensor data during charging. The second processor is configured to independently activate the second disconnect device to open when the sensor data indicates continued overcharging.
H02H 7/18 - Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from norm for accumulators
B60L 58/18 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries of two or more battery modules
B64D 41/00 - Power installations for auxiliary purposes
A sensing instrument includes a first electrode, a second electrode that surrounds the first electrode, and a sensing module configured to sense a capacitance of a material by applying a voltage between the first electrode and the second electrode while the first electrode and the second electrode are adjacent to the material. A method of operating a sensing instrument includes applying a voltage between a first electrode and a second electrode while the first electrode and the second electrode are positioned adjacent to a material. The second electrode surrounds the first electrode. The method further includes sensing a capacitance of the material based on a response of the material to the voltage.
A host computer for virtualizing a target multicore processor includes a host CPU and a host memory storing a virtual time object and a VM, the VM including target code. The host CPU executes the plurality of threads in parallel on corresponding virtual cores, including a first thread executing on a first virtual core and a second thread executing on a second virtual core. The VM assigns a designation to the first virtual core to increment the virtual time object by a first count of a first plurality of instructions executed in the first thread over a first duration. The VM moves the designation to the second virtual core in response to detecting an event that defines an end of the first duration. The second virtual core increments the virtual time object by a second count of instructions executed in the second thread over a second duration.
An aircraft is configured to perform onboard analytics using available onboard systems. The aircraft comprises a cabin and crew network core with a middleware layer comprising an orchestrator configured to send application containers to a number of cabin and crew network smart members to perform the onboard analytics; and the number of cabin and crew network smart members each having a respective edge member daemon, each edge member daemon configured to place a respective cabin and crew network smart member in a joined state with the middleware layer and release resources of the respective cabin and crew network smart member when it leaves a joined state and enters a busy state so that the edge member daemon does not interfere with a primary function of the respective cabin and crew network smart member.
H04L 67/1008 - Server selection for load balancing based on parameters of servers, e.g. available memory or workload
H04L 67/12 - Protocols specially adapted for proprietary or special-purpose networking environments, e.g. medical networks, sensor networks, networks in vehicles or remote metering networks
82.
FLAT COMPOSITE PANEL WITH TEAR ARRESTMENT AND METHOD OF MAKING THE SAME
A pressure deck for an aircraft comprises a flat composite laminate base panel having integrated tear straps to enhance damage arrestment. The tear straps include a plurality of multi- ply, spaced apart longitudinal and lateral tear straps interspersed with the plies of the base panel.
B32B 3/08 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by added members at particular parts
B32B 7/03 - Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical propert; Layered products characterised by the interconnection of layers with respect to the orientation of features
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
B32B 5/28 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer impregnated with or embedded in a plastic substance
B32B 27/04 - Layered products essentially comprising synthetic resin as impregnant, bonding, or embedding substance
B64C 1/00 - Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
83.
RECONFIGURABLE BATTERY SYSTEM FOR EFFICIENT CHARGING AND DISCHARGING
A reconfigurable battery system is disclosed. The reconfigurable battery system comprises a reconfigurable battery cell array, a controller, and a bus switch. The battery cell array is configured to operate in a first discharge mode, a second discharge mode, or a charge mode. The battery cell array includes a plurality of battery cells arranged as at least a first column of battery cells between a second battery terminal and a first battery terminal and a switch between each battery cell within the first column of battery cells. The bus switch is in signal communication with the battery cell array at the first battery terminal and is configured to select between electrically connecting the first battery terminal to a normal voltage bus or a high-voltage bus.
H01M 50/269 - Mechanical means for varying the arrangement of batteries or cells for different uses, e.g. for changing the number of batteries or for switching between series and parallel wiring
An aircraft includes an aircraft engine, a starter motor, an engine fuel delivery system, an engine ignition system, and a controller communicatively coupled to the starter motor, engine fuel delivery system, and engine ignition system. The controller is configured to automatically initiate operation of the starter motor as needed to start the aircraft engine while the aircraft engine is not running. Optionally, the controller may be configured to execute operations in accordance with either or both of two modes of operation. In the first mode, the controller automatically initiates operation of the starter motor for an aircraft engine that is not running while the aircraft is in flight. In the second mode, the controller automatically initiates operation of the starter motor for an aircraft engine that is not running while the aircraft is on ground. These operations can be done by a single, multi-position control.
A corrosion-resistant magnesium alloy with a multi-level protective coating, and to a preparation process thereof. The magnesium alloy with a multi-level protective coating comprises a magnesium alloy substrate and a multi-level protective coating. The multi-level protective coating comprises a micro-arc oxidation layer of magnesium alloy provided on the surface of the magnesium alloy substrate, an epoxy primer layer provided on the surface of the micro-arc oxidation layer of magnesium alloy, and a polyurethane topcoat layer provided on the surface of the epoxy primer layer. The magnesium alloy with a multi-level protective coating effectively integrates the excellent adhesion of the micro-arc oxidation layer and the excellent anti-corrosion effect of the organic coating. The process for the preparation of the magnesium alloy with a multi-level protective coating is cost-effective, simple, suitable for large-area and large-scale magnesium alloy treatment, and suitable for the development for large-area scale industrialization. The magnesium alloy with a multi- level protective coating is characterized by a good adhesion and an excellent salt spray resistance, exhibits a period of neutral salt spray resistance test of greater than 1,000 hours, and can be applied in the automotive industry and the aviation industry.
Aspects of the disclosure provide fuel receptacle and boom tip position and pose estimation for aerial refueling. A video frame is received and within the video frame, aircraft keypoints for an aircraft to be refueled are determined. Based on at least the aircraft keypoints, a position and pose of a fuel receptacle on the aircraft is determined. Within the video frame, a boom tip keypoint for a boom tip of an aerial refueling boom is also determined. Based on at least the boom tip keypoint, a position and pose of the boom tip is determined. Based on at least the position and pose of the fuel receptacle and the position and pose of the boom tip, the aerial refueling boom is controlled to engage the fuel receptacle. Some examples overlay projections of an aircraft model on displayed video for a human observer.
Systems and methods inspect a fastener installed at least partially through a hole in a part, by measuring fastener concentricity, measuring fastener flushness with a surface, and/or detecting foreign object debris near the fastener. Systems include an x-ray imaging system, a first camera device, a second camera device, a first support structure, and at least one processing unit. The first camera device produces a first image of the fastener from a first vantage point, and the second camera device produces a second image of the fastener from a second vantage point, such that a 3D image of the fastener can be created from the first image and the second image. The system inspects the fastener based on the x-ray image and/or the 3D image, to determine concentricity and/or flushness of the fastener. Systems may be automated and mounted on robot arms to be positioned relative to the fasteners being inspected.
G01N 21/95 - Investigating the presence of flaws, defects or contamination characterised by the material or shape of the object to be examined
G01B 15/00 - Measuring arrangements characterised by the use of electromagnetic waves or particle radiation, e.g. by the use of microwaves, X-rays, gamma rays or electrons
G01N 21/94 - Investigating contamination, e.g. dust
G01N 23/04 - Investigating or analysing materials by the use of wave or particle radiation, e.g. X-rays or neutrons, not covered by groups , or by transmitting the radiation through the material and forming images of the material
A device including a sleeve having a first end, a second end opposite the first end, and a hole disposed through an outer diameter of the sleeve between the first end and the second end. The device includes a spool having a third end and a fourth end opposite the third end, the spool disposed at least partially inside the sleeve and configured to slide along a longitudinal axis of the sleeve. The device includes a spring having a fifth end and a sixth end opposite the fifth end, the spring disposed in a slot disposed in the spool, the spring and the slot oriented at least partially in a radial direction relative to the longitudinal axis. The device also includes a retaining bit disposed at the fifth end of the spring. The spring, in a partially compressed state, urges the retaining bit against an inner wall of the sleeve.
F16K 11/07 - Multiple-way valves, e.g. mixing valves; Pipe fittings incorporating such valves; Arrangement of valves and flow lines specially adapted for mixing fluid with all movable sealing faces moving as one unit comprising only sliding valves with linearly sliding closure members with cylindrical slides
F15C 3/02 - Circuit elements having moving parts using spool valves
F16K 3/26 - Gate valves or sliding valves, i.e. cut-off apparatus with closing members having a sliding movement along the seat for opening and closing with sealing faces shaped as surfaces of solids of revolution with cylindrical valve members with fluid passages in the valve member
F16K 3/30 - Gate valves or sliding valves, i.e. cut-off apparatus with closing members having a sliding movement along the seat for opening and closing - Details
89.
SYSTEM FOR REFINING A SIX DEGREES OF FREEDOM POSE ESTIMATE OF A TARGET OBJECT
A system for refining a six degrees of freedom pose estimate of a target object based on a one-dimensional measurement includes a camera and a range-sensing device. The range-sensing device is configured to determine an actual distance measured between the range-sensing device and an actual point of intersection. The range- sensing device projects a line-of-sight that intersects with the target object at the actual point of intersection. The system also includes one or more processors in electronic communication with the camera and the range-sensing device and a memory coupled to the processors. The memory stores data into one or more databases and program code that, when executed by the processors, causes the system to predict the six degrees of freedom pose estimate of the target object. The system also determines a revised six degrees of freedom pose estimate of the target object based on at least an absolute error.
A housing assembly for selectively receiving a part includes a platform and a pad fixed to the platform. The pad has a frictional surface for maintaining a position of the part relative to the pad when the part is disposed on the frictional surface. The housing assembly includes a door apparatus coupled to the platform. The door apparatus surrounds the pad. The door apparatus is movable to an open position in which the frictional surface of the pad is exposed outside of the door apparatus for receiving the part and a closed position in which the frictional surface of the pad is concealed inside of the door apparatus. A method of removing particles from a frictional surface of a pad before performing a manufacturing process has a door apparatus disposed in a closed position to present a chamber that encloses the pad.
B08B 17/04 - Preventing deposition of fouling or of dust by using removable coverings
B08B 15/02 - Preventing escape of dirt or fumes from the area where they are produced; Collecting or removing dirt or fumes from that area using chambers or hoods covering the area
B25H 1/00 - Work benches; Portable stands or supports for positioning portable tools or work to be operated on thereby
F16M 11/00 - Stands or trestles as supports for apparatus or articles placed thereon
COMMONWEALTH SCIENTIFIC AND INDUSTRIAL RESEARCH ORGANISATION (Australia)
THE BOEING COMPANY (USA)
Inventor
Kohl, Thomas Matthew
Kinlen, Patrick J.
Bruton, Eric Alan
Abstract
The present disclosure generally relates to coatings and compositions comprising conductive polymers. The present disclosure also relates to thermally stable coatings and compositions comprising solution processable polyaniline conducting polymers and thermal stability agents, and to processes for preparing the coatings and compositions.
C08K 3/014 - Stabilisers against oxidation, heat, light or ozone
C09D 7/48 - Stabilisers against degradation by oxygen, light or heat
C08J 3/09 - Making solutions, dispersions, lattices or gels by other methods than by solution, emulsion or suspension polymerisation techniques in organic liquids
C08J 3/20 - Compounding polymers with additives, e.g. colouring
H01B 1/12 - Conductors or conductive bodies characterised by the conductive materials; Selection of materials as conductors mainly consisting of other non-metallic substances organic substances
A combined multi-spectral and polarization (CMSP) sensor is disclosed that enhances contrast-to-noise ratio (CNR). The CMSP sensor comprises a multi-spectral and polarization (MSP) filter, a single focal plane array (FPA), and a controller. The FPA comprises a plurality of detectors and the MSP filter comprises at least a first bandpass filter having a first frequency range and a second bandpass filter having a second frequency range that is distinct from the first frequency range and a first polarization filter having a first polarization value and a second polarization filter having a second polarization value that is distinct from the first polarization value.
A system that detects malicious traffic flows in a network includes a computer system including a processor in communication with at least one memory device. The processor is programmed to store a plurality of context information about the network including a plurality of devices. The processor is also programmed to determine a network configuration of the network at a specific point in time. The processor is further programmed to generate one or more security policies for one or more devices of the plurality of devices in the network based on the network configuration and the plurality of context information. In addition, the processor is programmed to deploy the one or more security policies to the one or more devices in the network, wherein the one or more devices are configured to execute an algorithm to monitor communications on the network in view of a corresponding security policy of the one or more security policies.
A system for detecting malicious traffic flows in a network is provided. The system includes a processor. Based on packet information received for a plurality of data packets transmitted over the network the processor is programmed to calculate inter- arrival times and packet durations for the plurality of data packets. The processor is also programmed to filter the packet information to remove noise. The processor is further programmed to generate at least one histogram based on the packet information, the inter-arrival times, and the packet durations. In addition, the processor is programmed to generate a power spectral density estimate based on the packet information, the inter-arrival times, and the packet durations. Moreover, the processor is programmed to analyze the at least one histogram and the power spectral density estimate to detect one or more unexpected data flows. Furthermore, the processor is programmed to report the one or more unexpected data flows.
Renewable energy charging stations, systems, and methods are disclosed for capturing storing and delivering large amounts of renewable electrical energy from a renewable energy source to vehicles including passenger aircraft using charging circuits in communication with a demultiplexer and high-temperature superconducting cables to deliver required large electrical charges at fast charging rates safely and at low temperatures.
A satellite assembly is disclosed, including a satellite and a shroud. The satellite is stowed in a launch vehicle and the shroud includes a frame supporting a flexible thermal blanket enclosing the satellite.
A satellite apparatus is disclosed, including a housing having first and second opposing walls, and a support structure inside the housing spanning the first and second walls. The support structure is structurally connected to the housing only at the first and second walls, and an end portion of the support structure is configured for connection to a launch vehicle by a separation system.
Methods and systems for computing distance data for a structure. A scan surface that represents an inspection area of the structure is identified. A plurality of sample points on an outer surface identified from a model of the structure and a corresponding plurality of projected points on an inner surface identified from the model of the structure are generated using the scan surface, a first geometric representation of the outer surface, and a second geometric representation of the inner surface. Distance data is computed using the plurality of sample points and the corresponding plurality of projected points. The distance data identifies a distance between a point pair formed by a sample point of the plurality of sample points and a corresponding projected point of the corresponding plurality of projected points.
G01B 21/30 - Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring roughness or irregularity of surfaces
B64F 5/60 - Testing or inspecting aircraft components or systems
G01B 17/08 - Measuring arrangements characterised by the use of infrasonic, sonic, or ultrasonic vibrations for measuring roughness or irregularity of surfaces
G01B 21/20 - Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring contours or curvatures, e.g. determining profile
99.
METHODS AND BRAKE SYSTEMS TO REDUCE BRAKE WEAR DURING AIRCRAFT TAXIING
Methods for reducing brake wear during aircraft taxiing are disclosed. As one example, a method comprises determining a sequence to apply brakes of a given set of landing gear during a brake event, wherein the determining includes selecting a warmer brake of the brakes to initially apply at a start of the brake event, and selecting a cooler brake of the brakes to subsequently apply when the warmer brake is released during the brake event. The method further comprises applying the warmer brake and the cooler brake in the determined sequence during the brake event. In another example, an aircraft brake system comprises brakes and a controller that is programmed to, during taxiing, apply a warmer subset of the brakes before applying a cooler subset of the brakes during a brake event.
A trim actuator (102) for a horizontal stabilizer (210) comprises a power screw (106), a rotary actuator (104), configured to rotate the power screw (106), and a nut (108), configured to translate along the power screw (106) when the power screw (106) is rotated. Trim actuator (102) also comprises an anti-back-drive mechanism (114), configured to prevent the power screw (106) from rotating in a first rotational direction when a first force is applied to the nut (108) in a first axial direction and to prevent the power screw (106) from rotating in a second rotational direction, opposite the first rotational direction, when a second force is applied to the nut (108) in a second axial direction. Trim actuator (102) further comprises a sensor (120), configured to measure internal loading of the anti-back-drive mechanism (114) when the first force is applied to the nut (108) in the first axial direction or when the second force is applied to the nut (108) in the second axial direction.
patents
