Methods of reducing calculation time for inverse kinematics for a robotic arm are presented. An analytical solver is used based on design values for a robot type to generate an analytical solution of joint parameters to achieve a desired location of a tool center point of the robot type, wherein the robotic arm has the robot type. The analytical solution of joint parameters is provided as a seed value to a numerical solver for the robotic arm of the robot type. A numerical solution is determined using the numerical solver and the seed value, the numerical solution comprising joint parameters for the robotic arm to achieve the desired location of a tool center point of the robotic arm.
Methods of controlling induction welding. An electrically conductive metal is machined into a heat sink comprising a plurality of channels extending from a first end of the heat sink to a second end of the heat sink. The plurality of channels is connected to a fluid control system comprising a number of pumps, a heater, a chiller, and a number of valves. The heat sink is positioned on top of a first composite part and clamped to a support structure underneath the first composite part. An electromagnetic field is applied to the first composite part under the heat sink to inductively weld the first composite part to a second composite part beneath the first composite part to form a thermoplastic joint. A heat control fluid is flowed through the plurality of channels to control a temperature of the first composite part during induction welding of the thermoplastic joint.
Methods of compression resin transfer infusion are presented. A dry preform with a thermoplastic veil is placed onto a lower mold die. An upper mold die is placed over the lower mold die to create an infusion and cure tool having a sealed cavity holding the dry preform, the sealed cavity defining a gap, the gap corresponding to a cavity volume equivalent to an amount of resin to infuse the dry preform. Resin is injected into the gap of the sealed cavity while the infusion and cure tool is maintained at an infusion temperature. The upper mold die is lowered to infuse the dry preform to form a resin-infused preform. The resin-infused preform is cured within the infusion and cure tool to form a cured composite part, wherein curing occurs at a curing temperature higher than the infusion temperature.
B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
4.
SYSTEMS AND METHODS FOR CONTROLLING AIRCRAFT DURING IN-FLIGHT REFUELING
A system and a method are configured for allowing a first vehicle to refuel a second vehicle. The system and the method include sensors configured to acquire scan data of the second vehicle. A control unit is in communication with the sensors. The control unit is configured to receive the scan data of the second vehicle from the sensors, associate the scan data with a three-dimensional (3D) model of the second vehicle, register the scan data with the 3D model to provide monitored data of the second vehicle, and control one or more of the first vehicle, the second vehicle, or a refueling boom of the first vehicle based on the monitored data.
A system includes a transmitting horn coupled to a first robotic arm and positionable in immediate non-contacting proximity to a transparency, and configured to emit an emitted signal comprising a focused energy beam for impingement on the transparency. The system further includes a receiving horn coupled to a second robotic arm and positionable relative to the transmitting horn in immediate proximity to the transparency, and configured to receive a received signal comprising at least a portion of the emitted signal after transmission through or reflection off of the transparency. The system also includes a processor configured to move the first robotic arm and the second robotic arm in a coordinated manner along a preprogrammed measurement path, and determine at least one transparency characteristic based on an analysis of the received signal.
Tools and methods are disclosed for automatically capturing debris generated during rivet installation using an autoloading rivet gun. In some examples, an autoloading rivet installation device includes a hand-held rivet gun and an automatic loader which uses a first actuator having a shaft oriented parallel to a longitudinal plane of the rivet gun. A second actuator is coupled to the rivet gun and has an orientation orthogonal to the first actuator, such that the second actuator is configured to transition a magnet laterally between a plurality of positions relative to the longitudinal plane to capture ferromagnetic debris. The magnet may, for example, be disposed on a load arm of the loader, and the second actuator may be configured to translate the loader's first actuator from side to side.
A fluid reservoir and associated fluid circulation system and method are disclosed. The fluid reservoir is rotatable into any one of various rotational orientations and includes a housing defining an interior chamber that is divided into a working fluid chamber and a gas chamber by a membrane. An inlet port is fluidically coupled with the working fluid chamber to provide working fluid into the working fluid chamber and an outlet port is fluidically coupled with the working fluid chamber to remove working fluid from the working fluid chamber. A bleed channel extends a length along an outer periphery of the working fluid chamber and is fluidically open to the working fluid chamber along the length of the bleed channel. A bleed port is fluidically coupled with only a portion of the bleed channel and bleeds gas out of the working fluid chamber via the bleed channel. The length of the bleed channel is such that at least a portion of the bleed channel is open to an uppermost portion of the working fluid chamber when the housing is in any one of the various rotational orientations.
A method for virtual fatigue testing includes reading a coarse-grid finite-element-model of a component from one or more libraries with a computer, and identifying static stress locations neighboring at least one of fasteners and non-fastener stress concentration regions in the component by a static analysis of a component intermediate-grid finite-element-model of the component, identifying hot spot locations in the component intermediate-grid finite-element-model by performing a fatigue screening on the component, generating details for the component intermediate-grid finite-element-model based on the hot spot locations, and predicting crack results by a deterministic durability-and-damage-tolerance analysis of the details for a component fine-grid finite-element-model of the component, calculating a crack margins for the component fine-grid finite-element-model by a probabilistic durability-and-damage-tolerance analysis of the crack results, and generating an output file that contains the final crack initiation margin and the final crack growth margin.
G06F 30/23 - Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
G06F 119/02 - Reliability analysis or reliability optimisationFailure analysis, e.g. worst case scenario performance, failure mode and effects analysis [FMEA]
A method for fatigue hot spot screening includes identifying multiple static stress locations neighboring one or more fastener locations and multiple stress concentrations in a finite-element-model of a component in response to analysis results and validated assembly-level analysis results with a computer, generating a fatigue spectrum at each static stress location, generating multiple fatigue analysis control files in response to the fatigue spectrum, reducing the validated assembly-level analysis results, generating a first output file that contains multiple non-fastener stress concentration hot spots in the finite-element-model by a first fatigue analysis at multiple non-fastener stress concentration regions in response to the fatigue analysis control files, calculating one or more local peak stresses for the one or more fastener locations, and generating a second output file that contains multiple fastener hot spots in the finite-element-model by a second fatigue analysis at the fastener locations in response to the fatigue analysis control files.
In a first example, a radome includes a shell including a ceramic matrix composite, the shell forming a first hole at a forward end of the shell and a second hole at an aft end of the shell. The radome also includes a fluid impervious coating on the shell. In a second example, a vehicle includes a main body, the radome, and an attachment assembly that couples the radome to the main body. In a third example, a method includes forming a shell comprising a ceramic matrix composite using a wet layup process, applying a fluid impervious coating onto the shell, and curing the shell and the fluid impervious coating.
Aspects herein describe performing analysis of electromagnetic effects (EME) on a structure (e.g., a wing of an aircraft) to identify routes for a link that extends along a length of the structure. With metallic links, it is easier to identify safe regions since EME is typically limited to simply simulating the voltage along the fuel line when a harmful EM event occurs, e.g., a lightning strike. However, for non-metallic links, the system can also determine the energy along the link, which depends on the electric field, the voltage potential, and the properties of the link. The potential energy can determine whether, a hazardous EM event could occur. Thus, the aspects herein can apply to both metallic and non-metallic links. After determining the potential energy, the system can output a GUI that indicates to the designer safe zones for routing the link in the structure.
G06F 30/20 - Design optimisation, verification or simulation
G06F 30/12 - Geometric CAD characterised by design entry means specially adapted for CAD, e.g. graphical user interfaces [GUI] specially adapted for CAD
G06F 30/15 - Vehicle, aircraft or watercraft design
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 119/02 - Reliability analysis or reliability optimisationFailure analysis, e.g. worst case scenario performance, failure mode and effects analysis [FMEA]
A device includes a memory configured to store a first token that indicates that a first entity has data authority of a first data object. The device also includes one or more processors configured to receive a data authority request from a second entity to transfer the data authority of the first data object to the second entity. The one or more processors are further configured to, based on a determination that a data authority transfer criterion is satisfied, generate a second token that indicates that the second entity has the data authority of the first data object. The one or more processors are further configured to generate a first reference that indicates that the second token is related and subsequent to the first token.
G06F 21/10 - Protecting distributed programs or content, e.g. vending or licensing of copyrighted material
H04L 9/32 - Arrangements for secret or secure communicationsNetwork security protocols including means for verifying the identity or authority of a user of the system
A heat exchanger system and method includes a securing frame, a heat transfer core having heat transfer panels removably secured to the securing frame, the heat transfer panels optionally including a plurality of segment modules coupled together, and one or more filter screens removably secured to the securing frame at one or both of an inlet end or an outlet end. The heat transfer core is disposed between the inlet end and the outlet end.
F28F 19/01 - Preventing the formation of deposits or corrosion, e.g. by using filters by using means for separating solid materials from heat-exchange fluids, e.g. filters
A grommet installation tool and methods using the installation tool for installing grommets. The grommet installation tool includes a hydraulic puller. An anvil is removably coupled to the hydraulic puller, the anvil including a proximal anvil end, a distal anvil end, and an anvil conduit that extends from the proximal anvil end to the distal anvil end, wherein the proximal anvil end is removably connected to the hydraulic puller. A mandrel is removably coupled to the anvil and the hydraulic puller, wherein the mandrel comprises a proximal mandrel end, and a threaded distal mandrel end. The mandrel passes through the anvil conduit and is removably connected to the hydraulic puller.
B23P 19/04 - Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformationTools or devices therefor so far as not provided for in other classes for assembling or disassembling parts
15.
INTEGRATED BACKSCATTER X-RAY ASSEMBLIES FOR DETECTING BACKSCATTER X-RAYS REFLECTED BY TARGET AREA OF ARTICLE UNDER TEST AND ASSOCIATED METHODS
Integrated backscatter X-ray assemblies for detecting backscatter X-rays reflected by a target area of an article under test are disclosed. The integrated backscatter X-ray assembly includes an enclosure, an X-ray power supply, an X-ray tube, a backscatter X-ray detector and a cooling fluid. The X-ray power supply disposed within the enclosure. The X-ray tube disposed within the enclosure and operatively coupled to the X-ray power supply. The backscatter X-ray detector is disposed within the enclosure. The cooling fluid disposed within the enclosure such that the X-ray power supply, the X-ray tube and the backscatter X-ray detector are immersed in the cooling fluid. In various examples, integrated backscatter X-ray assemblies may also include a movable base and/or a mobile platform. Methods for detecting backscatter X-rays reflected by a target area of an article under test are also disclosed.
G01N 23/20008 - Constructional details of analysers, e.g. characterised by X-ray source, detector or optical systemAccessories thereforPreparing specimens therefor
Disclosed herein is a computer-implemented method of generating a three-dimensional structure for a thermal management component. The computer-implemented method of generating a three-dimensional structure for a thermal management component comprises selecting, by a processor, at least one three-dimensional element from a plurality of three-dimensional elements. The computer-implemented method of generating a three-dimensional structure for a thermal management component also comprises determining, by the processor, a surface area necessary to dissipate heat from a first fluid according to a desired temperature difference and a desired heat transfer coefficient. The computer-implemented method of generating a three-dimensional structure for a thermal management component further comprises generating, by the processor, the three-dimensional structure for the thermal management component by intercoupling a quantity of the selected three-dimensional elements whose combined surface area equals the determined surface area.
G06F 30/28 - Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
G06F 30/12 - Geometric CAD characterised by design entry means specially adapted for CAD, e.g. graphical user interfaces [GUI] specially adapted for CAD
G06F 30/15 - Vehicle, aircraft or watercraft design
G06F 119/08 - Thermal analysis or thermal optimisation
17.
SYSTEMS AND METHODS FOR REMOVING A CAP SEAL FROM A FASTENER
A system and a method for removing a cap seal from a fastener include a seal remover including fingers outwardly extending from a base. Passages are defined between the fingers. The seal remover is configured to be coupled to a distal end of an operative portion of a tool. The tool is configured to be operated to rotate the seal remover in relation to the cap seal so that the fingers remove the cap seal from the fastener. Removed portions of the cap seal are discharged through and out of the passages.
A corrosion inhibitor coating composition includes a polymerized thiosemicarbazone, and a thiirane crosslinker, where the thiirane crosslinker is a difunctional molecule. The corrosion inhibitor coating composition can include where the thiirane crosslinker may include an aliphatic thiirane, a tri-functional thiirane, a bisphenol thiirane, or a combination thereof. The corrosion inhibitor coating composition can be metal-free and catalyst-free. An article utilizing and a method of preparing a corrosion inhibitor coating composition is also disclosed, which can include adding a thiourea to a difunctional epoxy terminated molecule in solution in the presence of a catalyst, converting the difunctional epoxy terminated molecule to a thiirane terminated difunctional molecule, and purifying the thiirane terminated difunctional molecule to produce a thiirane.
A method, computer program product, and computer system for identifying, by a computing device, a plurality of information associated with a flight simulation. A plurality of frame arrivals can be constructed based upon, at least in part, the plurality of information associated with the flight simulation. The plurality of frame arrivals can be packetized into a plurality of data packets. The plurality of data packets can be multiplexed to generate multiplexed data packets. A total amount of bandwidth needed for the flight simulation can be predicted based upon, at least in part, the multiplexed data packets.
A method, computer program product, and computer system for identifying, by a computing device, a plurality of information associated with a flight simulation. A plurality of charts for a plurality of frame arrivals can be initialized based upon, at least in part, the plurality of information associated with the flight simulation. The plurality of charts can be populated based upon, at least in part, a portion of the plurality of information associated with the flight simulation. At least a portion of the plurality of charts can be combined together. A total amount of bandwidth needed for the flight simulation can be predicted based upon, at least in part, the combining together at least the portion of the plurality of charts.
A self-sealing suction device system is provided. The system comprises a suction device, a pressure sensor in communication with the suction device, a vacuum supply in communication with the suction device, and a solenoid valve in communication with the suction device and the vacuum supply. A controller is programmed to turn on the vacuum supply responsive to the pressure sensor detecting air pressure within the suction device above a specified threshold. The controller turns off the vacuum supply responsive to the pressure sensor detecting a specified level of negative pressure within the suction device, wherein the solenoid valve maintains the negative pressure within the suction device. The controller maneuvers the solenoid valve to equilibrate the suction device with atmospheric pressure to release the object upon completion of a task.
A system and a method include a control unit configured to determine drag factors and fuel flow factors for different phases of one or more prior flights of an aircraft, and determine a fuel level for one or more upcoming flights of the aircraft based on the drag factors and the fuel flow factors for the different phases of the one or more prior flights of the aircraft.
A method for automatic product authenticity verification includes, at an authentication computing system, computer-recognizing one or more observed identifying parameters of a candidate physical product, the candidate physical product associated with a product identifier. The authentication computing system computer-identifies a block of a digital blockchain referencing the product identifier, the block including one or more recorded identifying parameters for a genuine physical product. An authenticity of the candidate physical product is computer-evaluated by automatically comparing the one or more observed identifying parameters of the candidate physical product to the one or more recorded identifying parameters for the genuine physical product.
A system and a method include a control unit configured to determine drag factors and fuel flow factors for different phases of one or more prior flights of an aircraft, and determine a fuel level for one or more upcoming flights of the aircraft based on the drag factors and the fuel flow factors for the different phases of the one or more prior flights of the aircraft.
An aircraft fueling adapter incorporating an aircraft fueling adapter flow meter is disclosed for improving accuracy of fueling protocols by providing an additional independent flow data point in mass units and/or volume units in the fueling process that can be compared against existing fuel flow readings.
An air vehicle management system comprising a controller for an air vehicle. The controller is configured to determine a prediction of an acceleration using an air vehicle model system and backscatter data. The air vehicle model system is trained to predict the acceleration using the backscatter data and is generated using backscatter light detected from emitting a laser beam in an atmosphere in a direction ahead of the air vehicle. The controller is configured to determine an adjustment to a number of flight control settings for the air vehicle that reduces a stress on the air vehicle using the prediction of the acceleration. The controller is configured to adjust the number of flight control settings using the adjustment.
A method of generating a recursively mapped infill geometry for an additively manufacturable part. The method includes receiving a base unit cell mesh including a plurality of base quadrilateral elements. In each of a plurality of iterations, the method further includes receiving a target unit cell mesh including target quadrilateral elements. In each iteration, the method further includes generating a target hexahedral unit cell mesh including target hexahedral elements by extruding the target quadrilateral elements. In each of the iterations, the method further includes generating a recursive supercell mesh by mapping each of the base quadrilateral elements onto a target hexahedral element. If the current iteration is not a final iteration, the method further includes setting the recursive supercell mesh as the base unit cell mesh used in a subsequent iteration. The method further includes outputting a recursively mapped unit cell mesh including a final recursive supercell mesh.
A system and method for measuring mutual inductance between adjacent first communication transmission line and second communication transmission line is disclosed. The system includes a mutual inductance measurement circuit that includes a coupling generator which biases the first communication transmission line with a current ramp signal; a sample and hold circuit which captures an induced voltage on the second communication transmission line using a switched capacitor storage element; a switched capacitor integrator configured to integrate the induced voltage onto an output voltage node; and a comparator configured to switch states once the switched capacitor integration has surpassed a reference trippoint.
G01R 27/26 - Measuring inductance or capacitanceMeasuring quality factor, e.g. by using the resonance methodMeasuring loss factorMeasuring dielectric constants
G01R 19/00 - Arrangements for measuring currents or voltages or for indicating presence or sign thereof
A method and system locate boundaries such as an edge of a composite ply using a laser projector and an imaging system that are angularly offset from each other to create parallax allowing a profile of the edge to be detected and measured.
G01B 11/25 - Measuring arrangements characterised by the use of optical techniques for measuring contours or curvatures by projecting a pattern, e.g. moiré fringes, on the object
A raceway is provided for containing a cable of an aircraft. The raceway includes an elongate base extending a length between end portions and extending a width between sides. The base is configured to be mounted to a structure of the aircraft. The base includes a guide that extends outwardly from a face of the base. The guide is arranged along the length and width of the base such that the guide is configured to bend a path of the cable along the length of the base.
B60R 16/02 - Electric or fluid circuits specially adapted for vehicles and not otherwise provided forArrangement of elements of electric or fluid circuits specially adapted for vehicles and not otherwise provided for electric
B64C 1/00 - FuselagesConstructional features common to fuselages, wings, stabilising surfaces or the like
H02G 3/00 - Installations of electric cables or lines or protective tubing therefor in or on buildings, equivalent structures or vehicles
31.
SYSTEMS, APPARATUS, AND METHODS FOR MOMENTUM MANAGEMENT FOR A SPACECRAFT
Systems, apparatus, and method for momentum management for a spacecraft are disclosed. An example spacecraft includes a body; an appendage moveably coupled to the body; a thruster carried by the body; machine-readable instructions; and processor circuitry to execute the machine-readable instructions to detect a change in angular momentum at the spacecraft during firing of the thruster; and in response to the detection, cause the appendage to move relative to the body to adjust a center of mass of the spacecraft relative to a net thrust vector associated with the thruster.
A tacking device for tacking together two overlapped or abutted layers of material includes a body portion having a first body portion end, one or more micro-heaters attached to the body portion at the first body portion end, and a switch in electrical communication with the one or more micro-heaters and configured to permit or prevent a flow of electric power to the one or more micro-heaters. A system and method for tacking together two overlapped or abutted layers of material are also provided.
A method and system for managing adhesion between a sheet of material and an electrostatic pad. The method includes applying a voltage across the electrostatic pad to establish a baseline voltage level thereacross and to generate an electrostatic potential across the electrostatic pad, bringing the electrostatic pad near or into contact with the sheet so that the sheet electrostatically adheres to the electrostatic pad, and monitoring a capacitance between the sheet and the electrostatic pad. If a drop in the capacitance occurs that is below a predetermined capacitance limit, then the voltage is increased to an elevated voltage level so as to increase the electrostatic adhesion between the electrostatic pad and the sheet. The system includes a voltage module, a monitoring module and a control module.
An electrostatic pad includes a first planar array of first electrodes arranged in a first pattern, and a second planar array of second electrodes arranged in a second pattern that is different from the first pattern, wherein the first and second planar arrays are disposed parallel to each other. A third layer of electrically insulative material may be sandwiched between the first and second planar arrays of respective first and second electrodes.
An aircraft includes a flight deck including a flight deck door configured to be moved between an open position and a closed position. A secondary barrier door is moveably coupled to one or more monuments. The secondary barrier door is configured to linearly slide between a stowed position in which a path to the flight deck is open, and a deployed position in which the path to the flight deck is closed.
A composite backing layer peel starter and methods of use are presented. A method of beginning removal of a backing layer from a composite material is presented. An impact force is applied to a corner of the backing layer with a polymeric material contact surface of a striker to adhere the polymeric material to the backing layer. The striker is pulled away from the backing layer to apply a lifting force to the backing layer.
Processing a vehicle maintenance transaction is provided. The method comprises receiving the transaction and entering the transaction into a blockchain ledger. In response to the transaction, an enhanced smart contract in the blockchain ledger executes. The enhanced smart contract specifies a number of compliance requirements to complete the transaction and automates a workflow for the transaction according to the compliance requirements. A number of notifications regarding the transaction are generated to a number of subscribers to the blockchain ledger. Confirmation of fulfillment of the compliance requirements is received from the subscribers to complete the transaction. The enhanced smart contract, verifies fulfillment of the compliance requirements, and completion of the transaction is recorded in the blockchain ledger.
Techniques for anomaly detection are disclosed. These techniques include identifying a plurality of three or more redundant sub-systems in a system. The techniques further include forming a plurality of combinations of the redundant sub-systems, each combination relating to a subset of the plurality of redundant sub-systems. The techniques further include identifying a first combination with the least variability among sub-systems, from among the plurality of combinations of redundant sub-systems. The techniques further include computing one or more nominal values for one or more parameters of a first sub-system, of the plurality of sub-systems, using the first combination, and detecting an anomaly in the first sub-system based on the computed one or more nominal values.
Disclosed herein is a system for determining a condition of an actuator-position sensor. The system comprises a first circuit electrically coupled with the actuator-position sensor to convert a voltage pattern generated by the actuator-position sensor to an output voltage. The system also comprises a comparator circuit electrically coupled with the first circuit and configured to determine if the output voltage of the first circuit exceeds a first threshold. The system further comprises an output device electrically coupled to the comparator circuit and configured to indicate a first output, associated with a first condition of the actuator-position sensor, when the output voltage of the first circuit exceeds the first threshold.
A forming die has a continuously configurable nip allowing a composite preform to be formed into continuous composite gap filler that has a variable cross-section along its length.
B29C 70/52 - Pultrusion, i.e. forming and compressing by continuously pulling through a die
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
41.
TITANIUM-BASED ALLOY COMPOSITIONS, ADDITIVELY MANUFACTURED COMPONENTS THAT INCLUDE THE COMPOSITIONS, ADDITIVE MANUFACTURING SYSTEMS THAT UTILIZE THE COMPOSITIONS, AND METHODS OF ADDITIVELY MANUFACTURING ADDITIVELY MANUFACTURED COMPONENTS
Titanium-based alloy compositions, additively manufactured components that include the compositions, additive manufacturing systems that utilize the compositions, and methods of additively manufacturing additively manufactured components are disclosed herein. The compositions comprising at least 4 weight percent (wt%) and at most 6.5 wt% aluminum, at least 1.5 wt% and at most 4.5 wt% vanadium, at least 1 wt% and at most 2.1 wt% cobalt, metallic solutes, and titanium. The composition includes at most 4.75 wt% of the metallic solute, which includes at least two of tin, chromium, iron, copper, and nickel.
An electrostatic tacking membrane assembly includes a membrane made of an elastic material, a plurality of electrostatic pads disposed on the membrane, one or more tacking elements disposed on the membrane, and a plurality of electrical leads disposed within or on the membrane and connected with the electrostatic pads and the one or more tacking elements. The electrostatic tacking membrane assembly may be positioned with the tacking elements disposed near or in contact with an overlapped or abutted area of two or more layers of material, and the tacking elements may be electrified and heated so as to bond together the two or more layers proximate the overlapped or abutted area.
B29C 65/78 - Means for handling the parts to be joined, e.g. for making containers or hollow articles
H02N 13/00 - Clutches or holding devices using electrostatic attraction, e.g. using Johnson-Rahbek effect
43.
TITANIUM-BASED ALLOY COMPOSITIONS, ADDITIVELY MANUFACTURED COMPONENTS THAT INCLUDE THE COMPOSITIONS, ADDITIVE MANUFACTURING SYSTEMS THAT UTILIZE THE COMPOSITIONS, AND METHODS OF ADDITIVELY MANUFACTURING ADDITIVELY MANUFACTURED COMPONENTS
Titanium-based alloy compositions, additively manufactured components that include the compositions, additive manufacturing systems that utilize the compositions, and methods of additively manufacturing additively manufactured components are disclosed herein. The compositions comprising at least 4 weight percent (wt %) and at most 6.5 wt % aluminum, at least 1.5 wt % and at most 4.5 wt % vanadium, at least 1.3 wt % and at most 2.1 wt % cobalt, metallic solutes, and titanium. The composition includes at most 4.5 wt % of the metallic solute, which includes at least two of tin, chromium, iron, copper, and nickel.
A nose gear spin down apparatus includes a spin down device and a resistance device. The spin down device is rotatable about a central longitudinal axis. The spin down device rotates about the central longitudinal axis after engagement with a spinning nose gear wheel of an aircraft. The resistance device contacts the spin down device without imparting a resistance to the spin down device. The resistance device imparts the resistance to the spin down device after conditions are met.
Techniques for anomaly detection are disclosed. These techniques include identifying a chain of operations for one or more systems, including a plurality of consecutive operations, and clustering operation phases in the chain of operations based on one or more operating conditions, using sensor data. The techniques further include computing statistical values for one or more parameters across the clustered operation phases, identifying one or more outlier parameters in the sensor data based on the computed statistical values, and excluding the one or more outlier parameters from the sensor data. The techniques further include computing one or more nominal values for one or more parameters of a first sub-system, of a plurality of sub-systems in the one or more systems, using the sensor data with the one or more outlier parameters excluded, and detecting an anomaly in the first sub-system based on the computed one or more nominal values.
Wing deployment apparatus and methods are disclosed herein. An example wing deployment apparatus includes a rotary actuator coupled to a torque coupler having a locking key disposed in an opening. The locking key moves between an outer radial position and an inner radial position. A lead screw is rotationally coupled to the torque coupler. The lead screw has a first recess to accept the locking key when the locking key is in the inner radial position. A nut is threadably engaged to the lead screw and includes a second recess to accept the locking key when the locking key is in the outer radial position. The locking key prevents movement of the nut along the axis of rotation when the locking key is in the outer radial position. A wing is operatively coupled to the nut to move the wing to a deployed position.
A system includes a control unit configured to receive one or more force signals from one or more force sensors coupled to one or both of a tool or an end effector. The one or more force signals are indicative of one or more forces exerted in relation to the tool or the end effector as the tool operates on one or more components to form an expanded hole. The control unit is further configured to compare the one or more forces in relation to force data associated with a reference expanded hole that is aligned with an alignment hole of the one or more components. The control unit is further configured to determine that the expanded hole caused a deformation when the one or more forces differ from the force data.
G01L 5/16 - Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes for measuring several components of force
B23B 49/00 - Measuring or gauging equipment on boring machines for positioning or guiding the drillDevices for indicating failure of drills during boringCentring devices for holes to be bored
48.
RADIO WAVE SIGNAL RECEIVER USING CONVOLUTIONAL NEURAL NETWORK TECHNOLOGY TO IMPROVE SIGNAL TO NOISE RATIO
Systems, apparatuses and methods can provide for technology to perform a discrete cosine transform (DCT) on a first digital signal to obtain a frequency domain signal, wherein the frequency domain signal contains energy in a plurality of frequency bins, apply convolutional neural network (CNN) operations on the frequency domain signal, and output a probability for each of the plurality of frequency bins in accordance with the CNN operations, wherein each probability indicates whether the energy in a corresponding frequency bin contains a transmitted signal.
A fastener configured to be attached to a panel and to support an item. The fastener has a body constructed from a first material and with the body having an opening that extends into the body at a first end. A flange constructed from a second material is connected to the body and sized to extend laterally outward beyond the body. The first material has a higher melting point than the second material. The first material has a lower transmissibility of UV light than the second material.
F16B 11/00 - Connecting constructional elements or machine parts by sticking or pressing them together, e.g. cold pressure welding
F16B 37/12 - Nuts or like thread-engaging members with thread-engaging surfaces formed by inserted coil-springs, discs, or the likeIndependent pieces of wound wire used as nutsThreaded inserts for holes
50.
Cart Compartment Cooling Using Aircraft Potable Water
Systems and methods for cooling an aircraft galley cart compartment by providing cooling from a potable water flow circuit directed from an aircraft potable water supply to provide direct and indirect cooling are disclosed.
An airport object location system comprising a number of vehicle location units, a sensor system, and a model generator. The number of vehicle location units is connected to a number of vehicles. The number of vehicle location units generate vehicle location information for the number of vehicles in an area including an operations surface at an airport and vehicle timestamps for the vehicle location information. The sensor system is connected to a reference vehicle. The sensor system is configured to generate sensor data for the area, wherein reference timestamps and reference location information are associated with the sensor data. The model generator is configured to correlate the vehicle location information for the vehicles with the sensor data using the vehicle timestamps, the reference location information, and the reference timestamps to form a dataset.
Compositions and coatings for thin films designed to protect surfaces and windows from environmental abrasion (e.g., sand, dust, and rubbing) that are transparent in visual and infrared wavelengths are disclosed. The compositions comprise thiol-containing copolymers comprising: (1) 10-(3-butyl-2-hexyl-6-(9-mercaptononyl)cyclohexyl) decane-1-thiol; and (2) a multifunctional terminally unsaturated hydrocarbon monomer; wherein (1) and (2) are combined to form a UV curable crosslinked thermoset polymer network and no particulate fillers are added to the composition. The films exhibit a specular transmission of greater than 70% in the visual spectrum at about 400-700 nm, and IR wavelengths at about 4-5 μm, and about 7.5-12 μm when applied to a surface of a substrate in a coating thickness of about 1-500 μm. A method for making the films involving an UV initiated thiol-ene curing mechanism is also provided.
An apparatus and method for predicting hot form die sliding are disclosed. The apparatus generates a 3D model of a hot form die, including a model upper die and a model lower die, which is fixed, relative to the model upper die. A hot forming process model is generated, and a baseline simulation is performed to determine a sliding direction of the model upper die within a sliding plane as it is pressed towards the model lower die along a z-axis. A spring coefficient is calculated at a spring reference point on the model upper die, that allows the model upper die to slide a specified distance in the sliding direction. If it is determined that some sliding is to be prevented, the apparatus generates model guides within the 3d model.
The present application is directed to a process for evaluating a design of an object. The process starts with an initial design. Machine learning using analytics based on historical data determines the probabilities for defects in the design. The evaluation also analyzes the design for structural requirements. The process analyzes the design based on a cost for the weight of the object and a cost to rework the design.
G06F 30/27 - Design optimisation, verification or simulation using machine learning, e.g. artificial intelligence, neural networks, support vector machines [SVM] or training a model
55.
JOSEPHSON JUNCTION-BASED CHARGE SENSING IN QUANTUM SYSTEMS
The present disclosure provides a method of charge sensing in a quantum system. The method includes supplying a bias current through a Josephson junction. The bias current is less than a first value of a critical current of the Josephson junction. The method further includes measuring an output voltage of the Josephson junction. Responsive to a change in charge of one or more charge islands coupled to the Josephson junction, the critical current is reduced to a second value less than the bias current, causing a voltage drop across the Josephson junction.
G01R 31/26 - Testing of individual semiconductor devices
H03K 17/92 - Electronic switching or gating, i.e. not by contact-making and -breaking characterised by the use of specified components by the use, as active elements, of superconductive devices
A composite laminate part such as a spar having reduced ply wrinkling is designed by generating a surrogate model of the part, and performing a geodesic strain analysis of the surrogate model. The results of the analysis are used to modify the part design to reduce strains in areas of the part that may cause ply wrinkling.
Methods and apparatus for forming a composite structure with a bend in a web and a number of flanges of the composite structure are presented. A flat uncured composite laminate is placed in contact with a forming surface of a mandrel. Pressure is applied to a portion of the flat uncured composite laminate over a kink region in the forming surface of the mandrel to form a bent laminate. The bent laminate and the mandrel are placed into a forming assembly. Overhanging portions of the bent laminate are bent into contact with sides of the mandrel by the forming assembly to form the composite structure, the composite structure having the bend in a web of the composite structure in contact with the forming surface of the mandrel and a number of flanges in contact with the sides of the mandrel.
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
B29C 70/08 - Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, with or without non-reinforced layers
B29C 70/16 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
A device includes one or more processors configured to obtain, from one or more sources of global data associated with aircraft traffic, historical data corresponding to historical usage metrics for a particular airport. The one or more processors are configured to process the historical usage metrics to generate a distribution model associated with usage of the particular airport. The one or more processors are configured to obtain, from the one or more sources of global data, data corresponding to current usage metrics for the particular airport. The one or more processors are also configured to determine, based on the distribution model and the current usage metrics for the particular airport, an airport congestion level for the particular airport.
An over-pressure vent (OPV) system is provided for a fuel tank of an aircraft. The OPV system includes an OPV valve configured to be coupled in fluid communication with a supply line of a nitrogen enriched air distribution system (NEADS) such that the OPV valve is configured to vent pressure from the supply line. The OPV valve is configured to be coupled in fluid communication with the supply line upstream from an outlet of the supply line from which the NEADS delivers nitrogen enriched gas to the fuel tank. The OPV valve is configured to sense a pressure within the supply line upstream from the outlet of the supply line.
An additive manufacturing system includes a first robotic arm and a print head with a nozzle. The first robotic arm is configured to hold a build part during a build process. The print head is configured to deposit source material layer by layer during the build process to construct the build part. The first robotic arm is configured to reorient the build part relative to the print head during the build process to modify an angle of a surface layer of the build part relative to the print head.
A system and a method include a heating layer including perforations extending from a first surface to a second surface opposite from the first surface. The perforations provide acoustic paths. The heating layer is configured to provide electrically resistive heating to a component. An acoustic layer can be coupled to the heating layer. The perforations extend to the acoustic layer.
B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
H05B 3/14 - Heating elements characterised by the composition or nature of the materials or by the arrangement of the conductor characterised by the composition or nature of the conductive material the material being non-metallic
H05B 3/28 - Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater non-flexible heating conductor embedded in insulating material
A system for forming a component includes one or more heaters configured to generate heat to form the component, wherein the component, upon formation, includes the one or more heaters. A method for forming a component includes generating, by one or more heaters, heat to form the component; and forming the component, at least in part, by said generating, wherein the component, upon formation, includes the one or more heaters.
B29C 35/02 - Heating or curing, e.g. crosslinking or vulcanising
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
A barrier door system to control movement of persons through an opening within a cabin area of an aircraft. The barrier door system includes a track with an elongated shape with a first end and a second end. A barrier door includes panels that are pivotally connected together and one or more pins that extend outward from a top edge of the barrier door and are configured to engage with the track. The panels are configured to pivot together in a folded configuration at a stowed position, and to pivot outward away from the track in an extended configuration to extend across the opening at the deployed position.
An aerospace panel includes a first skin, a second skin spaced apart from the first skin, and a first truss structure connecting the first skin to the second skin. The first truss structure includes a plurality of truss members. Each truss member is integral with the first skin and the second skin, such that the first skin, the second skin, and the first truss structure collectively form a single monolithic joint-free structure. At least one of the skins also includes at least one lattice region that includes a lattice grid and an array of openings.
A system for monitoring a presence of a life vest on an aircraft is disclosed. The system may comprise a sensor configured to output a first signal when the sensor detects the life vest and to output a second signal when the sensor fails to detect the life vest. The system may also comprise a first visual indicator in communication with the sensor. The first visual indicator may be activated based on the first signal. Further, the system may also comprise a second visual indicator in communication with the sensor. The second visual indication may be activated based on the second signal.
A target tracking apparatus includes a housing that defines an exterior surface and comprises an interior cavity, a distal opening, and an intermediate opening. The target tracking apparatus also includes a distal-end window attached to the housing over the distal opening and defining a distal end of the target tracking apparatus. The target tracking apparatus further includes an intermediate window attached to the housing over the intermediate opening. The target tracking apparatus additionally includes a first camera within the interior cavity, configured to capture images through the distal-end window, and fixed, relative to the housing, such that the first camera does not move relative to the housing. The target tracking apparatus also includes a second camera within the interior cavity, configured to capture images through the intermediate window, and fixed, relative to the housing, such that the second camera does not move relative to the housing.
A pick and place end effector configured to form a kink in a composite laminate. The pick and place end effector comprises a vacuum lift face configured to hold the composite laminate and move from a flat configuration to a forming configuration with an angle in the vacuum lift face to form the kink in the composite laminate; a number of motors configured to move the vacuum lift face between the flat configuration and the forming configuration; and a number of restraints configured to clamp portions of a composite laminate on opposite sides of the kink on the vacuum lift face during movement between the flat configuration and the forming configuration.
A manufacturing system to form a honeycomb core and a method of forming the same includes a sheet of fibrous material is fed into a perforation assembly. The sheet of fibrous material is perforated via the perforation assembly to form holes through the sheet of fibrous material. The sheet of fibrous material is cut to form layers. The layers are stacked on top of each other such that the holes of the layers align with each other and strips of adhesive bond the respective layers together to form a perforated stack. A coating is applied to the sheet of fibrous material at the holes. The perforated stack is expanded to form a honeycomb panel. The honeycomb panel is dipped in a solution, and the coating repels the solution. The solution adheres to the honeycomb panel except at the holes where the coating is applied to form the honeycomb core.
B31D 3/02 - Making articles of cellular structure, e.g. insulating board honeycombed structures
B32B 3/12 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
B32B 3/26 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layerLayered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a layer with cavities or internal voids
B32B 29/00 - Layered products essentially comprising paper or cardboard
B32B 29/06 - Layered products essentially comprising paper or cardboard specially treated, e.g. surfaced, parchmentised
A vacuum support system and vacuum support apparatus to support and maintain one or more workpieces via application of negative pressure. The vacuum support system includes a vacuum source and a vacuum support apparatus to support one or more workpieces thereon. The vacuum support apparatus includes a base frame and a cover member supported on the base frame. The base frame has a recessed region for fluidic communication with the vacuum source, and one or more support members arranged in the recessed region. The cover member has a gripping support surface to anchor one or more workpieces thereon via negative air pressure induced in the recessed region by the vacuum source.
An adjustable part-manufacturing tool and associated systems and methods are disclosed. The adjustable part-manufacturing tool includes a part-receiving receptacle defined by at least a first side and a second side. A first locating detail, including a first locating surface, is movably coupled to the tool body along the first side so that the first locating surface is selectively movable within the part-receiving receptacle in first opposing directions. A second locating detail, including a second locating surface, is movably coupled to the tool body along the second side so that the second locating surface is selectively movable within the part-receiving receptacle in second opposing directions. The second opposing directions are angled relative to the first opposing directions. Selective movement of the first locating surface and the second locating surface accommodates locating parts of different sizes on the first locating surface and the second locating surface within a specified tolerance.
B23K 37/04 - Auxiliary devices or processes, not specially adapted for a procedure covered by only one of the other main groups of this subclass for holding or positioning work
B23Q 1/62 - Movable or adjustable work or tool supports using particular mechanisms with sliding pairs only two sliding pairs only with perpendicular axes, e.g. cross-slides
B23Q 3/18 - Devices holding, supporting, or positioning, work or tools, of a kind normally removable from the machine for positioning only
71.
Automated Connectivity Boundary Determination and Network Performance
Determining aircraft wireless connectivity is provided. The method comprises collating network file server (NFS) logs from a number of missions for an aircraft at a number of airports and collating geolocation data of the aircraft at the airports during the missions. The NFS logs are parsed for wireless connectivity performance metrics, and the wireless connectivity performance metrics are cross-referenced with the geolocation data to determine wireless connectivity boundaries according to location within the airports.
H04L 43/0811 - Monitoring or testing based on specific metrics, e.g. QoS, energy consumption or environmental parameters by checking availability by checking connectivity
H04W 40/24 - Connectivity information management, e.g. connectivity discovery or connectivity update
H04W 64/00 - Locating users or terminals for network management purposes, e.g. mobility management
72.
SYSTEMS AND METHODS FOR SENSING LEVEL OF LIQUID WITHIN A CONTAINER
A system and a method include a container configured to retain one or more liquids. A liquid level sensor is disposed within the container. The liquid level sensor includes sensing elements configured to sense a level of the one or more liquids within the container. A control unit is in communication with the liquid level sensor. The control unit is configured to determine a status of each of the sensing elements based on signals received from the sensing elements.
A computing system including one or more processing devices configured to receive a first labeled image set including first images that each include one or more first regions of interest. The one or more processing devices are further configured to receive an unlabeled image set including a plurality of second images, and to identify second regions of interest included in the second images. The one or more processing devices are further configured to compute feature similarity values between the second and first regions of interest, identify a subset of the second regions of interest that have feature similarity values above a predetermined similarity threshold, and apply respective second labels to those second regions of interest. The one or more processing devices are further configured to construct a second labeled image set and train an image classification machine learning model with a training data set that includes the labeled image sets.
G06V 10/764 - Arrangements for image or video recognition or understanding using pattern recognition or machine learning using classification, e.g. of video objects
G06V 10/25 - Determination of region of interest [ROI] or a volume of interest [VOI]
G06V 10/46 - Descriptors for shape, contour or point-related descriptors, e.g. scale invariant feature transform [SIFT] or bags of words [BoW]Salient regional features
G06V 10/75 - Organisation of the matching processes, e.g. simultaneous or sequential comparisons of image or video featuresCoarse-fine approaches, e.g. multi-scale approachesImage or video pattern matchingProximity measures in feature spaces using context analysisSelection of dictionaries
G06V 20/70 - Labelling scene content, e.g. deriving syntactic or semantic representations
74.
METHODS AND APPARATUS FOR ONBOARD CAMERA CALIBRATION
Methods and apparatus for onboard camera calibration are disclosed. A disclosed apparatus for use with an aircraft includes interface circuitry communicatively coupled to a camera of the aircraft, the camera to capture an image, machine readable instructions, and programmable circuitry to at least one of instantiate or execute the machine readable instructions to generate randomized images from images stored in a data storage carried by the aircraft, determine at least one relationship between an image captured by the camera while the aircraft is in flight and the randomized images, and determine a parameter of the camera based on the at least one relationship to calibrate the camera.
A serrated fitting and method for installing fixed length roller tray segments spanning an aircraft fuselage integration zone. The serrated fitting includes a first surface for attachment to a fixed length roller tray segment. The serrated fitting also includes a serrated surface for engagement with a serrated plate attached to a floor beam of an aircraft. A fastener connects the serrated surface to the serrated plate and the floor beam through a pre-drilled hole in the floor beam. The pre-drilled hole is larger than the diameter of the fastener to accommodate accumulated tolerance between joined fuselage sections at a fuselage integration zone.
Apparatus and methods for transonic truss-braced wing aircraft are disclosed herein. An example aircraft disclosed herein includes a fuselage and a wing supported by a truss. The truss includes a pylon coupled to and extending from the fuselage and a strut attached to the wing. An engine is coupled to the pylon.
A substrate for receiving a print layer includes a reinforcement layer having a first surface and optionally a second surface opposite from the first surface. A first coating layer is coupled to the first surface of the reinforcement layer. The first coating layer is configured to receive and retain the print layer. The substrate is configured to be secured to a component.
A system for measuring parasitic capacitance coupling between adjacent first communication transmission line and second communication transmission line is disclosed. The system including: a parasitic tolerant capacitive based coupling measurement circuit (CBCM), the CBCM including: a capacitive auto-zeroing buffer configured to bias the second communication transmission line and displace coupling charge transferred from the first communication transmission line to a switched capacitor storage element; a capacitive trans-impedance amplifier configured to integrate displaced coupling charge onto an output voltage node; and a comparator configured to switch states once the capacitive trans-impedance amplifier integration has surpassed a reference trippoint.
A system for surface machining of a curved part, the system including a chassis, a first and second roller, and a cutting tool. The first and second rollers each being coupled to the chassis and configured to contact the surface of a curved part. The cutting tool is disposed between the first and second rollers and coupled to the chassis such that a distance between the cutting tool and the chassis is adjustable.
B23Q 17/09 - Arrangements for indicating or measuring on machine tools for indicating or measuring cutting pressure or cutting-tool condition, e.g. cutting ability, load on tool
80.
THERMOPLASTIC BRAIDING FOR THE MANUFACTURE OF COMPOSITE ARTICLES
A method of manufacturing a composite article comprises forming a braided lay-up including one or more braided layers around a braiding mandrel along at least a portion of a longitudinal axis of the braiding mandrel. Each braided layer may be formed by braiding tape segments of a fiber-reinforced thermoplastic resin tape applied at a tape tow orientation with thread segments applied at a thread tow orientation that is biased at an angle relative to the tape tow orientation. In an example, the thread segments include a thermoplastic resin thread that is integrated into a consolidated form of the braided lay-up following a consolidation process. In another example, the thread segments include a metallic thread that is removed from the braided lay-up prior to consolidation.
B29C 70/08 - Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, with or without non-reinforced layers
B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
B29K 305/00 - Use of metals, their alloys or their compounds, as reinforcement
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
D04C 1/02 - Braid or lace, e.g. pillow-laceProcesses for the manufacture thereof made from particular materials
D04C 1/06 - Braid or lace serving particular purposes
81.
Hydroacoustic Wave Detection Via an Underwater Cable
A hydroacoustic wave detection system that comprises a time delay generator and a hydroacoustic wave detector. The time delay generator is connected to an end of an underwater cable in which light signals travel in an optical fiber system in the underwater cable. The time delay generator is configured to introduce a time delay in the light signals received by the time delay generator to generate delayed light signals. The hydroacoustic wave detector is configured to control the time delay generator to generate a number of time delays. The hydroacoustic wave detector is configured to detect a presence of hydroacoustic waves for an event (e.g. underwater earthquake, underwater volcano, whale call) from an interferometric response determined using the light signals transmitted and the delayed light signals received. The hydroacoustic waves impinge on the underwater cable at a perturbation location along the underwater cable.
A gearbox decoupling apparatus and method for powering an accessory system. The gearbox decoupling apparatus employs a worm gear mechanism having an input worm pinion engaged with a worm gear wheel. A threaded rod is engaged with the worm gear wheel. A decoupling adapter is connected to the threaded rod. Rotation of the input worm pinion imparts movement of the decoupling adapter between a first position and a second position. When the decoupling adapter is in the first position, the decoupling adapter is mechanically engaged with a power take-off gear and a power take-off adapter. When the decoupling adapter is in the second position, the decoupling adapter is mechanically engaged with the power take-off gear and disengaged from the power take-off adapter thus allowing an accessory system to be powered by an alternate power source other than a main power source that is permanently connected to the power take adapter.
F16D 11/10 - Clutches in which the members have interengaging parts actuated by moving a non-rotating part axially with clutching members movable only axially
B64D 41/00 - Power installations for auxiliary purposes
A system for generating an integrated model is presented. The system comprises a central server having a plurality of clients, each client privately storing data accessible to the central server. A model trainer is configured to receive a model proposal from a first client and train the integrated model based on the model proposal and privately stored data for the plurality of clients without exposing the privately stored data for the plurality of clients to the first client. A model deployer is configured to disseminate the trained integrated model to one or more of the plurality of clients.
A system and method for dynamically controlling fluid pressure within a fluid flow circuit is disclosed. A fluid circulation system supplies working fluid through an inlet line and returns working fluid through an outlet line. A fluid management device is fluidically coupled to the inlet line and the outlet line. The fluid management device defines a pressure-controlled point. A first proportional valve and a first pressure sensor are disposed in the inlet line to selectively modulate and measure an inlet fluid pressure in the inlet line. A second proportional valve and a second pressure sensor are disposed in the outlet line to selectively modulate and measure an outlet fluid pressure in the outlet line. A controller is configured to maintain the inlet fluid pressure at a target inlet pressure and maintain the outlet fluid pressure at a target outlet pressure.
B41J 2/045 - Ink jet characterised by the jet generation process generating single droplets or particles on demand by pressure, e.g. electromechanical transducers
B05B 12/08 - Arrangements for controlling deliveryArrangements for controlling the spray area responsive to condition of liquid or other fluent material discharged, of ambient medium or of target
A system for image-based validation of a target object relative to a 3D control model is configured to retrieve a 3D control model, identify coordinates for each of the components, determine virtual camera locations using a camera placement algorithm to enable a multi-view image capture of all the components of the 3D control model, position virtual cameras at the determined camera locations, capture, by real-life cameras positioned at real-life camera locations respectively corresponding to the virtual camera locations, a 3D target model of the target object, receive the 3D target model captured by the real-life cameras, generate 2D target planar images of the target object, generate 2D control planar images of the control object, detect at least one difference between the 2D target planar images and the 2D control planar images, generate a validation output indicating the at least one difference, and output the validation output.
Method and system for reducing a temperature differential across a flight vehicle. The system includes an exterior of the flight vehicle. The exterior of the flight vehicle includes a first exterior panel being at a first initial temperature and a second exterior panel being at a second initial temperature to define an initial temperature differential. A fluid loop, containing a working fluid, is coupled to the first exterior panel and the second exterior panel such that heat is transferred from the first exterior panel to the working fluid to decrease the first initial temperature of the first exterior panel to a first altered temperature, and to heat the working fluid. The heated working fluid is circulated from the first exterior panel and used to heat the second exterior panel to a second altered temperature greater than the second initial temperature.
Fasteners pre-dosed with a curable sealant material encased within an at least partially-cured rupturable protective shell and methods are disclosed for the application of a selected curable sealant material dose to an aircraft assembly that is delivered simultaneously to an aircraft assembly location during fastener installation.
A system, a method, a device, and an apparatus include a control unit configured to determine contact resistance of one or more electrical contacts of one or more circuits by, at least in part, applying a test current to the one or more circuits, cycling a connection in relation to the one or more circuits a predetermined number of times, and determining steady behavior of the one or more circuits in response to a measurement for each cycle remaining within a predetermined threshold of a first measurement.
G01N 27/04 - Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating impedance by investigating resistance
H01H 1/60 - Auxiliary means structurally associated with the switch for cleaning or lubricating contact-making surfaces
90.
Barrier Center Latch with Delayed Over-Ride Feature
A barrier door system configured to be positioned at an opening within an interior of an aircraft. The barrier door system comprises a door that is movable between a stowed position away from the opening and a deployed position that extends across the opening. A lock is mounted to the door and configured to lock the door in the deployed position with the lock configured to be immediately movable from a locked position to an unlocked position from a forward side of the door and to delay moving from the locked position to the unlocked position from a rear side of the door.
A barrier door system to control movement of persons through an opening in an interior space of an aircraft. The barrier door system having a frame with outer members that extend around a gap. A barrier door has a first panel and a second panel that are pivotally connected together with the barrier door pivotally connected to the frame. The barrier door is movable between a stowed position and a deployed position. The stowed position includes the first panel and the second panel folded together in an overlapping configuration and positioned in the gap in the frame and away from the opening. The deployed position includes the first panel and the second panel positioned away from the gap and extending across the opening.
There is provided a tensioned tooling assembly for a thermoplastic composite stamp forming process. The tensioned tooling assembly includes a bottom tool having a bottom tool outer flange with a bottom end, a bottom tool outer radius, and a bottom tool outer curved surface. The bottom tool includes a plurality of tensioning protruding portions spaced apart on, and outwardly extending from, the bottom tool outer curved surface. Each tensioning protruding portion defines an angle formed from the bottom tool outer radius to the bottom end. The tensioned tooling assembly further includes a top tool having a top tool outer flange with a bottom end, a top tool outer radius, and a top tool outer curved surface. The top tool includes a plurality of corresponding portions formed in, and spaced apart on, the top tool outer curved surface, the plurality of corresponding portions corresponding to the plurality of tensioning protruding portions.
B29C 70/56 - Tensioning reinforcements before or during shaping
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
A method for forming composite parts includes loading an uncured composite material into a middle cavity of a chamber between an upper membrane and a lower membrane, wherein a lower cavity is defined below the lower membrane, and wherein an upper cavity is defined above the upper membrane, wherein a forming tool is disposed within the upper cavity. A vacuum is applied to the upper cavity, the middle cavity, and the lower cavity to remove at least a portion of gas entrapped within the uncured composite material. The vacuum is released from the upper cavity and the lower cavity, and the chamber is heated to a forming temperature of the uncured composite material. Pressure is controlled in the upper cavity and the lower cavity to form the heated composite material, wherein a greater pressure is applied to the lower cavity than to the upper cavity such that a pressure differential between the lower cavity and the upper cavity causes the heated composite material to form around the forming tool. The chamber is heated to a curing temperature to cure the heated composite material.
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
94.
REVERSE COUNTERSINK CUTTING ASSEMBLIES, REVERSE COUNTERSINKING ASSEMBLIES AND METHODS FOR REVERSE COUNTERSINKING A THROUGH HOLE IN A WORKPIECE
A reverse countersink cutting assembly includes a countersink cutting head, a depth stop sleeve and a fastener. The countersink cutting head includes a cutter distal portion, a cutting portion and a cutter proximal portion axially spaced along a longitudinal axis. The cutting portion defines a countersink cutting range. The depth stop sleeve includes a central cavity that coaxially receives the cutter proximal portion of the countersink cutting head. The depth stop sleeve also includes one or more projections that extend coaxially along the longitudinal axis to a predetermined point within the countersink cutting range to define a depth of cut for the reverse countersink cutting assembly. The fastener retains the depth stop sleeve on the countersink cutting head. A reverse countersinking assembly includes a pull shank assembly and the reverse countersink cutting assembly. A method for reverse countersinking a through hole in a workpiece is also disclosed.
B23B 35/00 - Methods for boring or drilling, or for working essentially requiring the use of boring or drilling machinesUse of auxiliary equipment in connection with such methods
A two-piece nested air intake scoop for an engine cowl and methods of assembly and manufacture. The nested air intake scoop includes an air intake scoop lower duct and an air intake scoop upper duct coupled to the air intake scoop lower duct. The air intake scoop upper duct is reversibly nested within the air intake scoop lower duct. Reversibly nested includes at least two surfaces of the air intake scoop upper duct airtight mechanically connected to at least two surfaces of the air intake scoop lower duct.
A ice protection system for a truss-braced wing of an aircraft is disclosed. The system includes a wing, a support strut, a joint coupling the support strut to the wing to form a structural truss of the truss-braced wing, a magnetic susceptor disposed on or within the joint, and an induction heating coil disposed on or within the truss-braced wing. The induction heating coil is configured to generate eddy currents inside the magnetic susceptor based on being driven with an alternating current (AC) excitation current. The eddy currents circulate through the magnetic susceptor causing joule heating of the magnetic susceptor to inhibit ice accumulation on the joint.
An arc fault detection system is disclosed. The arc fault detection system includes a plurality of capacitive arc fault sensors electrically connected to a plurality of different segments of an electrical power distribution system and an arc fault detector electrically connected to the plurality of capacitive arc fault sensors. Each capacitive arc fault sensor is configured to output an arc fault signal based at least on detecting a high frequency current generated from capacitively coupling with an electrical arc. The arc fault detector is configured to receive one or more arc fault signals from one or more capacitive arc fault sensors of the plurality of capacitive arc fault sensors and determine a location of an arc fault in the electrical power distribution system based at least on the one or more arc fault signals.
G01R 31/08 - Locating faults in cables, transmission lines, or networks
G01R 31/00 - Arrangements for testing electric propertiesArrangements for locating electric faultsArrangements for electrical testing characterised by what is being tested not provided for elsewhere
98.
SYSTEMS, METHODS, AND APPARATUS FOR LOCATING FAULTS OR CONDITIONS OF SYSTEMS
A portable electronic device for assisting a user in locating a condition of a system within a real-world environment is disclosed. The portable electronic device may include a display, an image capture device, and a processor. The processor may be configured to receive, from the image capture device, image data associated with a representation of the real-world environment and to align a virtual model with the real-world environment. The processor may also be configured to receive information associated with the condition of the system and to determine a location in the virtual model corresponding to the condition of the system. Further, the processor may provide a graphical indicator to be displayed over the representation of the real-world environment. The graphical indicator may be displayed at a location on the display that corresponds to a physical location of the condition of the system in the real-world environment.
Methods and apparatus for pointing logic in aircraft are disclosed. A disclosed example apparatus to aim an aiming device carried by an aircraft includes at least one memory, machine readable instructions, and processor circuitry. The processor is to at least one of instantiate or execute the machine readable instructions to determine a position of a target, determine an orientation of the aircraft, determine aiming points based on the orientation and a movement range of the aiming device, and determine a movement of at least one of the aircraft or the aiming device based on the aiming points and the position to orient the aiming device toward the target.
B64U 10/14 - Flying platforms with four distinct rotor axes, e.g. quadcopters
B64U 101/16 - UAVs specially adapted for particular uses or applications for conventional or electronic warfare for controlling, capturing or immobilising other vehicles
F41J 9/08 - Airborne targets, e.g. drones, kites, balloons
G05D 1/46 - Control of position or course in three dimensions
G05D 1/689 - Pointing payloads towards fixed or moving targets
100.
Thermoelectric Flexible Composite Materials for Energy Harvesting from an Aircraft Environment and an Aircraft Manufacturing Environment
Present apparatuses, systems, and methods are directed to the conservation of energy expended to power devices, components, systems, etc., on an aircraft, and to power aircraft manufacturing components used in the manufacture of an aircraft in an aircraft manufacturing facility using a highly flexible thermoelectric composite device to generate electrical current by converting waste heat into electrical energy.
B60L 50/60 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells using power supplied by batteries
B60L 50/90 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by specific means not covered by groups , e.g. by direct conversion of thermal nuclear energy into electricity
H10N 10/852 - Thermoelectric active materials comprising inorganic compositions comprising tellurium, selenium or sulfur
