Collective control using vertical velocity is provided. A system can include a data processing system comprising one or more processors, coupled with memory. The data processing system can receive, from a sensor, a velocity of an aerial vehicle along a vertical axis of a body of the aerial vehicle. The data processing system can generate a command for collective control of a pitch of blades of a rotor of the aerial vehicle based on a comparison of the velocity with a reference. The data processing system can control, via an actuator, the pitch of the blades of the rotor in accordance with the command.
A method for identifying a precise localization and mapping of an altitudinal system with respect to dynamic surfaces is presented. The method includes receiving a time-dependent map of a patch of a dynamic surface. The time-dependent map is captured by a first altitudinal system having a known location with respect to the dynamic surface. The method includes receiving a terrain map of a first set of terrain features of the patch of the dynamic surface. The terrain map is captured by a second altitudinal system having an approximate location with respect to the dynamic surface. The method includes comparing the first set of terrain features to a second set of terrain features stored in a database, and identifying, based on the comparison of the first set of terrain features and the second set of terrain features, a precise location of the second altitudinal system with respect to the dynamic surface.
In an embodiment, a method includes producing a mixed feedstock of at least three halogenated monomer feedstocks. A first of the at least three halogenated monomer feedstocks includes an SP3 carbon, a second of the at least three halogenated monomer feedstocks includes an SP2 carbon, and a third of the at least three halogenated monomer feedstocks includes at least two SP1 carbons. The method further includes producing a polyorbital-hybrid pre-ceramic polymer comprising the SP1 carbons, the SP2 carbon, and the SP3 carbon. The polyorbital-hybrid pre-ceramic polymer is produced by reducing the mixed feedstock such that one or more halogen atoms are removed from the mixed feedstock. The method also includes fabricating the polyorbital-hybrid pre-ceramic polymer into a greenware form and producing a polyorbital-hybrid ceramic carbon comprising the SP1 carbons, the SP2 carbon, and the SP3 carbon. The polyorbital-hybrid ceramic carbon is produced by thermolyzing the polyorbital pre-ceramic polymer.
A method of coupling a first structure to a second structure includes providing a first bushing within an opening in an upper surface of the first structure, without the first bushing extending into a second opening in the second structure. The method further includes providing an inner opening of the first bushing which defines an inner diameter, and providing a fastener at least partially within the first bushing and at least partially within the second opening. An outer surface of the fastener defines an outer diameter. The first bushing and the fastener are configured such that a space between the outer surface of the fastener and the inner opening of the first bushing defines a gap dimensioned to increase in a direction away from the upper surface of the first structure.
An artificial intelligence (AI) system includes an agent to learn a policy and provide an action; the agent can be a neural network. The AI system further includes a processor to process information associated with the action and provide a state and a reward to the agent. The state is based on a number of state variables, and the agent further updates the policy based on multiple updates of the state variables to achieve the highest reward.
Provided herein are various enhancements for aperture antenna arrays and electronically steered arrays (ESAs). A modular subarray is provided that includes horn apertures coupled to corresponding waveguide polarizers coupled to transmit waveguide filters and receive waveguide filters that establish transmit ports and receive ports. The transmit ports and the receive ports are coupled through a waveguide adapter plate to individual isolation cavities each formed in a body of an amplifier-filter module that houses amplifier/filter elements and couple transmit radio frequency signaling and receive radio frequency signaling to coaxial connections penetrating the isolation cavities. The subarray also includes a circuit card assembly comprising the coaxial connections coupled to stripline links formed by a printed circuit board, wherein the stripline links couple to beamforming circuitry, and a high-density digital connector mounted to the circuit card assembly and configured to carry input/output radio frequency signaling for the subarray to/from the beamforming circuitry.
A cable management drive system for extending and retracting cable bundles is provided. The cable management drive system includes a cable bundle configured to provide power signals or data signals to an industrial robot configured to perform a service. The cable bundle is configured to couple to the industrial robot. The cable management drive system includes a plurality of drive wheels coupled to a drive mechanism and configured to cause the cable bundle to be extended to facilitate a deployment of the industrial robot to perform the service and to be retracted to facilitate a withdrawal of the industrial robot upon performance of the service, and a driver system coupled to the plurality of drive wheels and the drive mechanism. The driver system is configured to power the drive wheels and the drive mechanism to cause the cable bundle to be extended and retracted.
B65H 75/36 - Cores, formers, supports, or holders for coiled, wound, or folded material, e.g. reels, spindles, bobbins, cop tubes, cans specially adapted or mounted for storing and repeatedly paying-out and re-storing lengths of material provided for particular purposes, e.g. anchored hoses, power cables without essentially involving the use of a core or former internal to a stored package of material, e.g. with stored material housed within casing or container, or intermittently engaging a plurality of supports as in sinuous or serpentine fashion
Provided herein are various enhancements for solar panels and associated solar arrays. In one example, a method of manufacturing includes forming, by an additive manufacturing process, a stackup of half-panels comprising connected pairs of the half-panels each having an integrated construction comprising a webbing structure connected to a skin layer substantially covering a face. The method also includes separating the stackup into detached pairs of the half-panels, assembling a selected detached pair of the half-panels into a full panel, and attaching photovoltaic cells to a selected face of the full panel.
H02S 40/36 - Electrical components characterised by special electrical interconnection means between two or more PV modules, e.g. electrical module-to-module connection
Systems and methods are disclosed for using a pressure relief shipping adapter to reduce the internal pressure of a container. A pressure relief shipping adapter includes a body comprising a first portion, a transitional portion, and a second portion. The first portion comprises a set of protrusions and a hole disposed through the set of protrusions. The second portion comprises an outlet disposed at a second end of the body. The outlet is concentric with an inlet disposed at the first end of the body. The transitional section is disposed between the first portion and the second portion. The pressure relief shipping adapter also includes an internal chamber within the body.
A lighting device for foreign object debris (FOD) detection is included. The lighting device includes a light source configured to emit light onto a surface, and a diffuser coupled to the light source and configured to cause the emitted light to impinge the surface in at least a partially planar pattern, so as to create a darkfield lighting effect with respect to the surface. The lighting device further includes a cylindrical rod including a first end portion and a second end portion, in which the first end portion is configured to couple to the light source and the diffuser and the second end portion is configured to be manually held by a user of the portable lighting device.
B64F 5/60 - Testing or inspecting aircraft components or systems
F21L 4/02 - Electric lighting devices with self-contained electric batteries or cells characterised by provision of two or more light sources
F21V 33/00 - Structural combinations of lighting devices with other articles, not otherwise provided for
F21Y 107/30 - Light sources with three-dimensionally disposed light-generating elements on the outer surface of cylindrical surfaces, e.g. rod-shaped supports having a circular or a polygonal cross section
F21Y 113/13 - Combination of light sources of different colours comprising an assembly of point-like light sources
A marking end effector for a robotic system is disclosed for marking a target surface. The end effector includes a housing including a cylindrical cavity and guide slots. The end effector also includes a marker holder assembly including a cylindrical marker holder and guide bearings. A biasing member is provided between the marker holder assembly and a base of the cavity. The marker holder rotates and translates when the end effector is advanced toward the target surface, and a pattern is correspondingly marked on the surface.
An active optical compressive sensing system includes an optical source to generate light for illuminating a target and a pattern generator to generate a pattern. A pattern controller controls an operation of the pattern generator to cause generation of a desired pattern. The pattern is a spatial filtering pattern that enables data compression by generating sparse scattered data. Applying the pattern allows a logarithmic resource scaling.
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
F21V 8/00 - Use of light guides, e.g. fibre optic devices, in lighting devices or systems
An apparatus for sanding or polishing a surface includes a sanding housing having an inlet and an outlet, where the inlet and the outlet are fluidly connected. The apparatus also includes a sander attached to the sanding housing. The apparatus also includes sanding head removably attached to the outlet of the sanding housing. The sanding head is used to sand or polish the surface. The sander actuates the sanding head. The apparatus also includes a fluid supply line connecting the inlet of the sanding housing to a fluid supply source. The apparatus also includes a handle attached to at least one of the sander and the fluid supply source. The fluid supply source provides a fluid through the fluid supply line and the sanding head to cool the surface.
A system includes a robotic arm, a rotisserie control linkage, and a computer system. The robotic arm includes a touch probe and laser head. The rotisserie control linkage is configured to couple to a transport cart. The computer system is communicatively coupled to the robotic arm and the rotisserie control linkage and is configured to control the system to probe, using the touch probe of the robotic arm, a transparent outer layer of an aircraft canopy located on the transport cart in order to determine surface measurements of the aircraft canopy. The computer system also controls the system to ablate, using a plurality of predetermined parameters and the laser head of the robotic arm, an interface layer located between the transparent outer layer and the aircraft canopy, wherein movements of the robotic arm during the ablation are based on the surface measurements.
B23K 26/50 - Working by transmitting the laser beam through or within the workpiece
B23K 26/57 - Working by transmitting the laser beam through or within the workpiece the laser beam entering a face of the workpiece from which it is transmitted through the workpiece material to work on a different workpiece face, e.g. for effecting removal, fusion splicing, modifying or reforming
G01B 11/00 - Measuring arrangements characterised by the use of optical techniques
G05B 19/42 - Recording and playback systems, i.e. in which the programme is recorded from a cycle of operations, e.g. the cycle of operations being manually controlled, after which this record is played back on the same machine
Provided herein are various enhancements for radio frequency (RF) horn antenna systems and arrays. An example apparatus includes a horn antenna array formed in a single workpiece of material comprising horn antenna elements with integrated feed networks. Each of the integrated feed networks comprise a waveguide interface flange having a port, and a filter element having a serpentine cavity coupled to the port that is at least partially formed by a base section, where a separation interface is established between the base section and an attachable cap that forms a remainder of the serpentine cavity. Each of the integrated feed networks also comprise a polarizer element having a waveguide cavity that couples between the serpentine cavity of the filter element and an associated horn antenna element that forms a signal aperture.
H01Q 21/06 - Arrays of individually energised antenna units similarly polarised and spaced apart
H01P 1/161 - Auxiliary devices for mode selection, e.g. mode suppression or mode promotionAuxiliary devices for mode conversion sustaining two independent orthogonal modes, e.g. orthomode transducer
According to some embodiments, a computer-implemented method accesses, using a computer server, a plurality of electrical wiring harnesses, testing criteria, and a wireless harness automated measurement system (WHAMS). The computer-implemented method generates a test plan for the plurality of electrical wiring harnesses based on the testing criteria. The computer-implemented method selects a plurality of wireless test modules (WTMs) using the test plan and the WHAMS. The computer-implemented method generates a plurality of test instructions based on the test plan and the plurality of WTMs. The computer-implemented method performs, using the plurality of WTMs, one or more tests on the plurality of electrical wiring harnesses according to the plurality of test instructions. The computer-implemented method wirelessly communicates, using the plurality of WTMs, test results to the computer server for display.
According to some embodiments, a system includes a wireless transceiver, an electrical wiring harness, and a wireless test module (WTM) operable to physically couple to the electrical wiring harness. The WTM comprising a chassis and a variable front end connected to the chassis using hot-swap connectors. The WTM wirelessly receives, using the wireless transceiver, a plurality of test instructions according to an automated test plan from a computer system. The WTM performs, using the variable front end, one or more tests on the electrical wiring harness according to the plurality of test instructions. The WTM wirelessly communicates, using the wireless transceiver, test results to the computer system.
According to some embodiments, an apparatus for charging a wireless harness automated measurement system (WHAMS) includes a charging cart, a mobile frame, a plurality of light-emitting diode (LED) indicators, and a plurality of charging slots. The charging cart may charge a plurality of wireless test modules (WTMs) of the WHAMS. The mobile aluminum frame may support the charging cart. The plurality of light-emitting diode (LED) indicators may identify a status of the plurality of the WTMs during testing of the WHAMS. The plurality of charging slots may charge the plurality of WTMs. Each of the plurality of charging slots is associated with a respective one of the plurality of LED indicators.
H02J 50/00 - Circuit arrangements or systems for wireless supply or distribution of electric power
H02J 13/00 - Circuit arrangements for providing remote indication of network conditions, e.g. an instantaneous record of the open or closed condition of each circuitbreaker in the networkCircuit arrangements for providing remote control of switching means in a power distribution network, e.g. switching in and out of current consumers by using a pulse code signal carried by the network
H02J 50/30 - Circuit arrangements or systems for wireless supply or distribution of electric power using light, e.g. lasers
H02J 50/40 - Circuit arrangements or systems for wireless supply or distribution of electric power using two or more transmitting or receiving devices
A rotor system of a rotary wing aircraft includes a rotor hub including a hub arm, a rotor blade rotatably coupled to the hub arm about a longitudinal axis of the hub arm, and a first brake assembly. The first brake assembly includes a rod coupled to the rotor blade coupling and a brake shoe coupled to the rod. The brake shoe is configured to apply a force on the hub arm. An axial position of the rod is adjustable to vary the force of the brake shoe on the hub arm.
According to some embodiments, a computer-implemented method is applied to calibrate a wireless test module (WTM) of a wireless harness automated measurement system (WHAMS) using a computer server and a calibration fixture. The WTM includes a plurality of field effect transistors (FETs). The calibration fixture includes a plurality of resistors. The method measures, using the calibration fixture, a first/second resistance value of the plurality of FETs from a first/second internal measurement test for the WTM. The method determines a resistance calibration value by subtracting the first resistance value from the second resistance value. The method measures a plurality of calibration factors to determine a measured resistor value for a target resistor value for a respective resistor of the calibration fixture.
G01R 1/20 - Modifications of basic electric elements for use in electric measuring instrumentsStructural combinations of such elements with such instruments
G01R 1/28 - Provision in measuring instruments for reference values, e.g. standard voltage, standard waveform
G01R 15/14 - Adaptations providing voltage or current isolation, e.g. for high-voltage or high-current 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
G01R 31/26 - Testing of individual semiconductor devices
21.
Systems and Methods for a Battery Pack of a Wireless Harness Automation Measurement System
According to some embodiments, a system includes a wireless charging battery, a wireless battery pack holder, an injected molded pogo pin holder comprising a plurality of pogo pins, and a wireless charging receiver. The wireless battery pack holder is operable to contain the wireless charging battery. The injected molded pogo pin holder is coupled to the wireless battery pack holder using a set of screws. The injected molded pogo pin holder is operable to couple to a wireless test module (WTM). The wireless charging receiver is operable to wirelessly charge the wireless charging battery.
H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
H01M 10/42 - Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
H02J 13/00 - Circuit arrangements for providing remote indication of network conditions, e.g. an instantaneous record of the open or closed condition of each circuitbreaker in the networkCircuit arrangements for providing remote control of switching means in a power distribution network, e.g. switching in and out of current consumers by using a pulse code signal carried by the network
22.
Systems and Methods for Hot-Swap Connectors of a Wireless Harness Automated Measurement System
According to some embodiments, a system includes a wireless test module (WTM) side hot-swap connector located between a chassis of a first WTM and a variable front end of the first WTM. The variable front end of the first WTM may mate to an aircraft connector. The WTM side hot-swap connector may mate to a front end side hot-swap connector of the variable front end of the first WTM. The WTM side hot-swap connector includes a female connector, an alignment peg configured to couple to the variable front end of the first WTM, a slip ring configured to secure the first WTM in place, and an electrically erasable programmable read-only memory (EEPROM) read/write wire integrated on a circuit board operable to read/write data of the aircraft connector.
H01R 13/66 - Structural association with built-in electrical component
B64F 5/60 - Testing or inspecting aircraft components or systems
H01R 13/631 - Additional means for facilitating engagement or disengagement of coupling parts, e.g. aligning or guiding means, levers, gas pressure for engagement only
According to some embodiments, a system includes a computer system and a plurality of wireless test modules. Each wireless test module includes a wireless transceiver and physically couples to an electrical wiring harness. The computer system sends test instructions to the plurality of wireless test modules according to an automated test plan. Each wireless test module wirelessly receives one or more of the plurality of test instructions from the computer system using the wireless transceiver and performs one or more tests on the electrical wiring harness according to received one or more test instructions from the computer system. Each wireless test module wirelessly communicates test results to the computer system using the wireless transceiver.
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
G01R 31/50 - Testing of electric apparatus, lines, cables or components for short-circuits, continuity, leakage current or incorrect line connections
24.
Enhanced bandwidth for secure optical communications
Provided herein are various techniques and equipment for establishing secure non-classical communications between distant nodes. In one example, a method includes introducing, by at least one photon source, source photons into corresponding waveguides configured to convert the source photons into randomly timed pairs of resultant non-classical photons having corresponding polarization states. The method also includes providing first photons of each of the pairs for measurement of the corresponding polarization states and timing, and providing second photons of each of the pairs for combination into a beam for transfer to a distant node and establishment of a cryptographic key, where the second photons from one of the waveguides is presented in an orthogonal polarization before combination.
Embodiments provide a universal bushing system that includes a base plate, vertical plates, and universal vector bushing apparatuses. The vertical plates are mounted to base plate and are separated by predetermined distance on base plate to position a workpiece. The bushing apparatuses are coupled to vertical plates. Each apparatus includes first knob, second knob, bushing element, and pivoting portion. The first knob includes threaded structures. The second knob is coupled to first knob via the threaded structures. The bushing element includes a recess with threaded tracks to allow the second knob to be placed. The pivoting portion includes a first end coupled to bushing element and a second end to pivotally connect to a vertical plate. Each of the first knob, the second knob, the bushing element, and the pivoting portion forms a hollow portion concentric at longitudinal axis that forms a slotted path to receive a threaded shaft.
A rotor assembly for a rotary wing aircraft includes a rotor hub including a hub arm and a central opening. The rotor assembly further includes a hydraulic actuation cylinder positioned in the central opening, a pitch change shaft assembly including a pitch change shaft positioned partially within the hydraulic actuation cylinder, a pitch beam coupled to a distal end of the pitch change shaft and configured to be coupled to a rotor blade rotatably mounted to the hub arm. The rotor assembly additionally includes at least one guide rod coupled to the rotor hub and slidably coupled to an opening in the pitch change shaft.
B64C 27/80 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement for differential adjustment of blade pitch between two or more lifting rotors
B64C 27/10 - Helicopters with two or more rotors arranged coaxially
B64C 27/64 - Transmitting means, e.g. interrelated with initiating means or means acting on blades using fluid pressure, e.g. having fluid power amplification
27.
INTEGRATED STRUCTURAL INTEGRITY MANAGEMENT SYSTEM FOR AIRCRAFT
Systems and methods for structural integrity management system for an aircraft. The system includes an electronic processor configured to receive information regarding damage to a component of the aircraft, update a digital twin model associated with the aircraft based on the received information, and perform a rapid structural analysis using the updated digital twin model. The electronic processor is further configured to determine, based on the results of the rapid structural analysis and either or both of a historic use of the aircraft and a current future usage profile of the aircraft, an actionable direction, and perform the actionable direction.
Provided herein are various enhancements for waveguide structures used in radio frequency feed components. In one example, an apparatus includes a septum polarizer having first feed ports and a common port, a high-pass filter coupled to the common port of the septum polarizer, and a multi-port orthomode transducer (OMT) coupled to the high-pass filter and providing an antenna port. The apparatus also includes hybrid couplers coupled to low-pass filters fed from the multi-port OMT, and magic tee elements cross-coupled to the hybrid couplers and providing second feed ports.
H01Q 1/50 - Structural association of antennas with earthing switches, lead-in devices or lightning protectors
H01P 1/161 - Auxiliary devices for mode selection, e.g. mode suppression or mode promotionAuxiliary devices for mode conversion sustaining two independent orthogonal modes, e.g. orthomode transducer
Provided herein are various enhanced systems, apparatuses, and techniques for optical communication among a constellation of satellites. One example includes establishing an initial cross-connect configuration comprising optical communication links among a constellation of satellites. In the initial cross-connect configuration, the satellites can optically communicate with both adjacently positioned and non-adjacently positioned satellites in the constellation. The satellites obtain angular states of the optical communication links resultant from orbital motion of the satellites. When angular states of a portion of the optical communication links reach an exclusion range, the satellites establish a subsequent cross-connect configuration to avoid optically communicating within the exclusion range.
H04B 10/00 - Transmission systems employing electromagnetic waves other than radio-waves, e.g. infrared, visible or ultraviolet light, or employing corpuscular radiation, e.g. quantum communication
Systems and methods for controlling an aircraft to hold altitude using GPS altitude readings. One example system includes a GPS inertial navigation system, an altimeter, a human machine interface, and one or more electronic processors coupled to the GPS inertial navigation system, the altimeter, and the human machine interface. The one or more electronic processors configured to receive, from the human machine interface, a user input selecting a reference altitude. The one or more electronic processors configured to receive, from the altimeter, a current altitude for the aircraft. The one or more electronic processors configured to: when the current altitude does not exceed an altitude threshold, operate the aircraft in an altimeter altitude hold mode based on the reference altitude; and when the current altitude exceeds the altitude threshold, operate the aircraft in a GPS altitude hold mode based on the reference altitude using the GPS inertial navigation system.
Systems and methods for an overheating control system for an electrical power harness disposed within an enclosure of an aircraft. The system includes a temperature sensor disposed within the enclosure and communicatively coupled to an electronic processor. The electronic processor is configured to monitor, via the temperature sensor, a temperature within the enclosure, compare the temperature to a predetermined threshold, and adjust a power output provided to one or more supply lines of the harness based on an amount in which the temperature exceeds the predetermined threshold.
Technology is disclosed herein to generate an indication of a potential that a lightning event will result in ignition based on satellite data. In an implementation, a computing system obtains data associated with a lightning event. The data includes a location of the lightning event and one or more measurements of the lightning event captured by a sensor. The computing system identifies characteristics of the lightning event based at least on the one or more measurements. The computing system predicts the ignition potential of the lightning event based at least on the lightning characteristics and the fuels characteristics.
G01W 1/10 - Devices for predicting weather conditions
A62C 3/02 - Fire prevention, containment or extinguishing specially adapted for particular objects or places for area conflagrations, e.g. forest fires, subterranean fires
A clutch having an inner ring, an outer ring, a plurality of sprags positioned between the inner ring and the outer ring, and a spring biasing each of the plurality of sprags towards the outer ring. Each of the plurality of sprags are movable between a disengaged position spaced from the inner ring and an engaged position contacting both the inner ring and the outer ring to rotationally unitize the inner ring and the outer ring.
F16D 43/18 - Internally controlled automatic clutches actuated entirely mechanically controlled by angular speed with centrifugal masses actuating the clutching members directly in a direction which has at least a radial componentInternally controlled automatic clutches actuated entirely mechanically controlled by angular speed with centrifugal masses themselves being the clutching members with friction clutching members
B64D 41/00 - Power installations for auxiliary purposes
F16D 41/07 - Freewheels or freewheel clutches with intermediate wedging coupling members between an inner and an outer surface the intermediate members wedging by pivoting or rocking, e.g. sprags between two cylindrical surfaces
F16D 45/00 - Freewheels or freewheel clutches combined with automatic clutches
F16D 41/06 - Freewheels or freewheel clutches with intermediate wedging coupling members between an inner and an outer surface
F16D 43/14 - Internally controlled automatic clutches actuated entirely mechanically controlled by angular speed with centrifugal masses actuating the clutching members directly in a direction which has at least a radial componentInternally controlled automatic clutches actuated entirely mechanically controlled by angular speed with centrifugal masses themselves being the clutching members
34.
Quantum Neural Network Systems and Methods Using Quantum Embedding
According to an embodiment, a method includes removing a last feed forward layer from a pre-trained neural network. The method further includes appending the pre-trained neural network with a secondary last feed forward layer configured to output a plurality of parameters. The method further includes updating each one of the plurality of parameters by: 1) multiplying each one of the plurality of parameters by a first factor to produce a plurality of resultant parameters; and 2) adding a second term to each one of the plurality of resultant parameters, wherein both the first factor and the second term vary due to backpropagation. The method further includes using a loss function to determine the distance between a known class embedding and an input from an input dataset. Lastly, the method includes updating one or more weights associated with the number of variables in the pre-trained neural network.
According to an embodiment, a method includes receiving a pre-trained neural network and removing a last feed forward layer from the pre-trained neural network. The method further includes appending the pre-trained neural network with a secondary last feed forward layer, a quantum circuit, and another feed forward layer, and determining a number of measurements from the quantum circuit based on a plurality of qubits and a plurality of parameters output from the secondary last feed forward layer. The method further includes using a cross-entropy loss function to determine the difference between a probability distribution, output from the last feed forward layer, for a number of variables and a true value for each of the number of variables. Lastly, the method includes updating one or more weights associated with the number of variables in the pre-trained neural network through an optimizer.
A phased array antenna is provided that includes a plurality of antenna elements arranged in a plurality of subarrays. A plurality of first beamformers is coupled to respective elements of the plurality of antenna elements, and a plurality of second beamformers is coupled to respective subarrays of the plurality of subarrays. A controller is configured to steer a phase center for each of the plurality of subarrays using the plurality of first beamformers so that the phase centers for the plurality of subarrays are irregularly spaced.
H01Q 3/38 - Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system varying the relative phase or relative amplitude of energisation between two or more active radiating elementsArrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system varying the distribution of energy across a radiating aperture varying the phase by electrical means with variable phase-shifters the phase-shifters being digital
H04B 7/06 - Diversity systemsMulti-antenna systems, i.e. transmission or reception using multiple antennas using two or more spaced independent antennas at the transmitting station
A rotor blade includes a spar with forward end, an aft end, and a substantially oval cross-section. The cross-section includes an upper portion tapering from a first thickness to a smaller, second thickness beginning between about 55% and about 65% of the distance to the aft end from the forward end and ending between about 65% and about 75% of the distance to the aft end measured from the forward end, and a lower portion tapering from a third thickness to a smaller, fourth thickness beginning between about 55% and about 65% of the distance to the aft end from the forward end and ending between about 65% and about 75% of the distance to the aft end measured from the forward end. The rotor blade further includes an upper blade skin, a lower blade skin, and a leading edge sheath.
LEO satellites of orbital planes are configured to communicate with at least one GEO satellite based at least on present line of sight. GEO satellites are configured to communicate with ground gateways and convert among uplink communications and optical communications of GEO-to-LEO optical links established with selected LEO satellites and comprising optical beams within a wavelength multiplexed arrangement individually assigned to corresponding LEO satellites in each orbital plane. Selected LEO satellites are configured to optically demultiplex a GEO-to-LEO optical link into local optical beams on optical fibers, direct a demultiplexed assigned optical beam of an incoming LEO optical link from a previous in-plane LEO satellite to an onboard destination with an optical splitter on a corresponding optical fiber, and multiplex the local optical beams on the optical fibers for an outgoing free space LEO optical link directed to a subsequent in-plane LEO satellite.
In one embodiment, a method of automated missile launcher reloading includes aligning one or more collars of a shelving system with a path of a canister and activating one or more rollers of the shelving system to translate the canister into the one or more collars. The method also includes coupling a first collar of the one or more collars to the canister and adjusting the one or more collars to align the canister with a path of a launcher cell. The method further includes translating the one or more collars into the path of the launcher cell to feed the canister into the launcher cell.
A bearing anti-creep interface having a drive shaft, a bearing race, and a hub. The drive shaft extends along a rotational axis. The bearing race has an inner surface press-fit onto the drive shaft and an axial end surface defining a bearing race interface surface. The hub has an inner surface rotationally coupled to the drive shaft and an axial end surface defining a hub interface surface. The hub interface surface is in contact with the bearing race interface surface to form an interlockingjoint. The interlocking joint is configured to transfer rotational creep force of the bearing race about the rotational axis and relative to the drive shaft into an axial pressure force applied to the hub in a direction parallel with the rotational axis.
F16C 19/26 - Bearings with rolling contact, for exclusively rotary movement with bearing rollers essentially of the same size in one or more circular rows, e.g. needle bearings for radial load mainly with a single row of rollers
A temporary fastener actuation tool includes a protrusion, multiple spring clips, and a bearing shaft. The protrusion includes a groove that matches a shape of an indentation of a temporary fastener. Each spring clip includes an end that is aligned with an end of the protrusion. The spring clips are configured to hold the indentation of the temporary fastener secure against the protrusion. The temporary fastener actuation tool further includes a first bearing that is coupled to the bearing shaft and is configured to contact a cylindrical body of the temporary fastener and hold the cylindrical body stationary. The temporary fastener actuation tool further includes a second bearing coupled to the bearing shaft that is configured to contact a stem of the temporary fastener and to rotate the stem. The temporary fastener actuation tool further includes a motor shaft coupled to the bearing shaft.
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
F16B 19/10 - Hollow rivetsMulti-part rivets fastened by expanding mechanically
42.
Automated Temporary Fastener Actuation Apparatus and System
A temporary fastener actuation tool includes a protrusion, multiple spring clips, and a bearing shaft. The protrusion includes a groove that matches a shape of an indentation of a temporary fastener. Each spring clip includes an end that is aligned with an end of the protrusion. The spring clips are configured to hold the indentation of the temporary fastener secure against the protrusion. The temporary fastener actuation tool further includes a first bearing that is coupled to the bearing shaft and is configured to contact a cylindrical body of the temporary fastener and rotate the cylindrical body of the temporary fastener in a first direction. The temporary fastener actuation tool further includes a second bearing coupled to the bearing shaft that is configured to contact a stem of the temporary fastener and to rotate the stem in a second direction. A motor shaft is coupled to the bearing shaft.
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
F16B 19/10 - Hollow rivetsMulti-part rivets fastened by expanding mechanically
43.
Wide angle phased array fed reflector for radio frequency antennas
Provided herein are various enhancements for radio frequency antennas and antenna arrangements. In one example, an apparatus comprises a reflector for radio frequency energy having a reflector surface comprising a paraboloid of revolution that establishes an inverted truncated conical shape with a concave nappe. The reflector surface is configured to interact with the radio frequency energy to direct at least a portion of the radio frequency energy towards a feed array mounted about a perimeter of the inverted truncated conical shape.
H01Q 9/28 - Conical, cylindrical, cage, strip, gauze or like elements having an extended radiating surface Elements comprising two conical surfaces having collinear axes and adjacent apices and fed by two-conductor transmission lines
H01Q 19/10 - Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces
Provided herein are various enhanced assemblies and techniques for forming high-power radio frequency coaxial splitters. In one example, an apparatus includes an input coaxial port having a center conductor coupled to a first longitudinal end of a generally cylindrical conductor member formed along a longitudinal axis within a housing forming a cavity about the conductor member. Output coaxial ports are included having center conductors coupled to generally square output branches arrayed at a second longitudinal end about the conductor member in a plane perpendicular to the longitudinal axis. A thermal shunt is included comprising a thermal connection between the housing and a recess formed into the conductor member along the longitudinal axis at the second longitudinal end.
A method includes receiving, using radio frequency (RF) collectors, RF signals from a target object. The RF signals of target object may be converted to In-phase and Quadrature (I/Q) data. Navigation data of each RF collector may be determined and I/Q data of each of RF collectors are paired. Processing functions may be applied on paired I/Q data. Using paired I/Q data, one or more of time difference of arrival (TDOA) measurement data and frequency difference of arrival (FDOA) measurement data between each pair of the RF collectors are determined. One or more of TDOA measurement data, FDOA measurement data and navigation data of each RF collector are converted to message data. A trajectory of target object may be estimated based on confidence measure of one or more of TDOA and FDOA measurement data. Using estimated trajectory of target object for displaying on a display device of a computing device.
G01S 5/02 - Position-fixing by co-ordinating two or more direction or position-line determinationsPosition-fixing by co-ordinating two or more distance determinations using radio waves
G01S 11/02 - Systems for determining distance or velocity not using reflection or reradiation using radio waves
G01S 19/39 - Determining a navigation solution using signals transmitted by a satellite radio beacon positioning system the satellite radio beacon positioning system transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
Provided herein are various enhancements for solar arrays and photovoltaic systems for spacecraft, vehicles, and other applications. In one example, an assembly includes a base layer having a generally circular shape and comprising a plurality of gores interspersed by radial folds. The assembly includes a photovoltaic array coupled to the gores, and a tensioning element configured to apply circumferential tension about a central node of the base layer. The assembly includes a structural element disposed about an outer perimeter of the base layer against which the circumferential tension is conveyed for deployment of the base layer from a stowed configuration into a deployed configuration.
Provided herein are various enhancements for antenna systems and directed radio frequency energy structures. In one example, an apparatus includes a baseplate, an antenna array comprising a plurality of Vivaldi antenna elements arranged about an axis perpendicular to the baseplate, and feed elements coupled to each of the Vivaldi antenna elements through the baseplate.
H01Q 21/24 - Combinations of antenna units polarised in different directions for transmitting or receiving circularly and elliptically polarised waves or waves linearly polarised in any direction
H01Q 13/08 - Radiating ends of two-conductor microwave transmission lines, e.g. of coaxial lines, of microstrip lines
In one embodiment, systems and methods include an aircraft vehicle comprising a body, a first wing coupled to the body, and a second wing coupled to the body, wherein the second wing has a length greater than the first wing, wherein each of the first wing and the second wing comprises a plurality of segments, wherein the second wing comprises a wing pylon system. The wing pylon system comprises one of the plurality of segments of the second wing, a payload, and a pylon coupling the payload to the one of the plurality of segments, the pylon being disposed underneath the one of the plurality of segments, and the payload being disposed underneath the pylon. A center of lift and a center of gravity for the aircraft vehicle are aligned and each is offset from a central axis of the body.
B64C 3/26 - Construction, shape, or attachment of separate skins, e.g. panels
B64C 3/28 - Leading or trailing edges attached to primary structures, e.g. forming fixed slots
B64U 101/60 - UAVs specially adapted for particular uses or applications for transporting passengersUAVs specially adapted for particular uses or applications for transporting goods other than weapons
49.
Automated Pre-Weld Tube Cleaning Using Laser Ablation
A system includes a laser drive assembly and a computer system. The laser drive assembly includes a laser that emits a laser beam to clean an end of a tube, a first motor that changes an angle of the laser beam with respect to the end of the tube, a second motor that moves the laser laterally, and a third motor that rotates the laser drive assembly around the end of the tube. The computer system is configured to clean the end of the tube by operating the laser to emit the laser beam, adjusting the angle of the laser beam with respect to the end of the tube by operating the first motor, adjusting the distance between the laser and the end of the tube by operating the second motor, and rotating the laser drive assembly around the end of the tube by operating the third motor.
A system including an apparatus for determining the presence of ice on an external surface of a structure is provided. The apparatus includes a sensor that includes first and second parallel ink or paint conductive traces separated by a gap. The apparatus also includes a circuit configured to measure the impedance or change in impedance between the first and second parallel ink or paint conductive traces.
According to some embodiments, a method includes determining test predictions by performing an inference process using a checkpointed learning model and test vectors. The checkpointed learning model includes hyperparameters and weights. The method further includes determining an attribution map by performing one or more attribution processes using the test predictions and the test vectors. The method further includes determining a score for each particular hyperparameter by analyzing the attribution map using an association classifier. The method further includes determining, based on the analysis by the association classifier, whether each particular hyperparameter should be frozen or tuned again. The method further includes updating the hyperparameters and weights of the neural network when it is determined that at least one particular hyperparameter should be tuned again.
A rotor blade configured to be installed on a rotary-wing aircraft includes a main blade body including an inboard end configured to be coupled to a rotor blade hub and an outboard end. The rotor blade includes a blade tip removably coupled to the outboard end of the main blade body, the blade tip including an inner cavity. The rotor blade further includes a tip block including an inboard portion coupled to the outboard end of the main blade body and a cantilevered portion extending beyond the outboard end of the rotor blade and into the inner cavity of the blade tip.
A method of manufacturing an electrical conductor assembly includes attaching a substrate and at least one electrical conductor to a cable assembly machine, tensioning the substrate, and holding the substrate stationary while wrapping the at least one electrical conductor around the substrate. The at least one electrical conductor is wrapped around the substrate independent of the tension on the substrate.
Embodiments disclose a network system that includes a memory that may be configured to store registration information of a computing device and a hardware processor communicatively coupled to the memory. The processor may be configured to detect application data specifying a network connection request from stream of data packets of the client computing device. From registration information, a type of computing device may be detected and a type of wireless service from the application data and network connection request of computing device may be determined. The processor may determine different access networks available for type of wireless service of client computing device. A data flow architecture and service interface may be created to establish network connection with core networks by integrating different access networks and translation of data flow may be performed according to the data flow architecture and service interface for wireless communication with the core networks.
H04L 41/5041 - Network service management, e.g. ensuring proper service fulfilment according to agreements characterised by the time relationship between creation and deployment of a service
H04L 41/5003 - Managing SLAInteraction between SLA and QoS
H04W 76/16 - Setup of multiple wireless link connections involving different core network technologies, e.g. a packet-switched [PS] bearer in combination with a circuit-switched [CS] bearer
55.
METHOD AND SYSTEM FOR IMPROVING NETWORK PERFORMANCE TO REDUCE INTERFERENCE
Embodiments disclose a computer-implemented method. The method includes detecting a stream of network packets for a computing device by a network controller. Based on the stream of network packets, the method includes detecting available frequency channels of a plurality of network stations by the network controller. The network controller may determine and select a plurality of available frequency channels of the plurality of network stations to transmit the stream of network packets. Then, the method performs one or more of: duplicating data of the stream of network packets over the plurality of available frequency channels, beam re-assignment over one or more network stations of the plurality of network stations and beam duplication over the plurality of network stations.
A system for superadditivity for remote sensing and communication includes coupling optics to direct several input pulses received over a communication channel to an interaction medium. A probe beam entering the interaction medium at an angle performs state preparation and manipulation. A detector reads the output light of the interaction medium. Orthogonality states of symbols represented by the plurality of input pulses are affected by the communication channel, and the interaction medium provides the output light via local entanglement of the plurality of input pulses and the probe beam.
Radio frequency (RF) polarizer feeds and associated waveguide structures having twist features are discussed herein. In one example, a first waveguide segment spans a longitudinal axis between a feed port and a twist port and includes two stacked rounded rectangular elements skewed in minor axis alignment with respect to each other and having major axes perpendicular to the longitudinal axis. A second waveguide segment spans the longitudinal axis between the twist port and a polarizer port and is coupled to the first waveguide segment at the twist port. The second waveguide segment includes first ridge elements that span longitudinally from the twist port on first opposing walls of the second waveguide segment, and second ridge elements that span longitudinally from the twist port on second opposing walls of the second waveguide segment.
According to some embodiments, a spacecraft includes an electronics housing having a sun-facing side. The spacecraft further includes a peel-and-stick thermal control material coupled to the sun-facing side of the electronics housing. The peel-and-stick thermal control material includes a non-metallic optical interface coating, a carrier film, and an adhesive.
Enhanced components and assemblies for connector-less radio frequency (RF) interconnect systems are provided. One example includes two circuit boards each with a broadside coupling feature comprising a tapered circuit board trace having a terminal portion. The circuit boards are positioned in close proximity to establish a desired gap, and a dielectric material is positioned within the gap between circuit boards. The broadside coupling features of the circuit boards are then configured to convey RF signals over the gap without electrical contact.
H01P 5/18 - Conjugate devices, i.e. devices having at least one port decoupled from one other port consisting of two coupled guides, e.g. directional couplers
H05K 1/14 - Structural association of two or more printed circuits
60.
Systems and methods for scaling quantum key transmission to enhance security
Information can be transmitted through classical and quantum communication channels in parallel and at rates that enhance secure communication. The quantum communication is scaled to a transmission rate of 10 GHz or more, which matches the rate of classical communication transmission. During transmission of information (e.g., a message) through a classical channel, a quantum channel can transmit quantum key information used to construct a new key (e.g., a new decryption key) from the prior key. As a result, the same key is not reused for decryption and can be discarded after use. Further, a multiplexing system can encode and transmit both classical and quantum communication at the GHz-level transmission rate as a single optical beam, while a demultiplexing can receive and decode the information from the single optical beam.
The present disclosure is directed to unmanned aerial vehicle (UAV) comprising a convertible body operably coupled to at least one sensor, and further configured to rotate at least about a longitudinal axis, thereby providing a full field of regard for the at least one sensor, and a plurality of arms extending laterally from the convertible body, each arm of the plurality of arms having a rotor assembly coupled thereto.
Systems and methods for providing tactile feedback via an inceptor. A control system for an aircraft includes an inceptor and a controller. The inceptor includes a grip portion moveable between a plurality of positions and one or more motors to apply a variable force to the grip portion. The controller is coupled to the one or more motors. The controller includes an electronic processor and a memory. The controller is configured to operate in a first operating mode, select a first tactile feedback profile associated with the first operating mode, and control the one or more motors based on the first tactile feedback profile. The controller is further configured to detect a transition from the first operating mode to a second operating mode, select a second tactile feedback profile associated with the second operating mode, and control the one or more motors based on the second tactile feedback profile.
A lubricant system includes a first gearbox defining a first internal cavity, a second gearbox defining a second internal cavity, a first lubricant cooler positioned external the first and second internal cavities, a second lubricant cooler positioned external the first and second internal cavities, and a plurality of fluid passages fluidly connecting the first lubricant cooler and second lubricant coolers to each of the first gearbox and the second gearbox. The first lubricant cooler and the second lubricant cooler are configured to hold lubricant. The fluid passages include a first main fluid passage fluidly connecting the first lubricant cooler to the first gearbox, a second main fluid passage fluidly connecting the second lubricant cooler to the second gearbox, a first auxiliary passage fluidly connecting the first lubricant cooler to the second gearbox, and a second auxiliary passage fluidly connecting the second lubricant cooler to the first gearbox.
Systems and methods for sensing targets within an ambient environment. One example system includes a human machine interface and an electronic processor. The electronic processor is configured to receive sensor data including a plurality of targets. The electronic processor is configured to select a clutter mitigation model and generate, with the clutter mitigation model, a subset of the plurality of targets based on the sensor data. The electronic processor is configured to receive, from the human machine interface, an operator sensitivity setting. The electronic processor is configured to generate, with a machine learning mapping function, a post-processing parameter based on the operator sensitivity setting. The electronic processor is configured to process the subset of the plurality of targets based on the post-processing parameter to select, from the subset, a display target. The electronic processor is configured to display, via the human machine interface, the display target.
G01S 13/524 - Discriminating between fixed and moving objects or between objects moving at different speeds using transmissions of interrupted pulse modulated waves based upon the phase or frequency shift resulting from movement of objects, with reference to the transmitted signals, e.g. coherent MTi
G01S 13/56 - Discriminating between fixed and moving objects or between objects moving at different speeds for presence detection
65.
Automated non-contact thickness inspection and projection system
In one embodiment, systems and methods include using an inspection and projection system to measure the thickness of a coating and provide visual guidance for secondary operations. The inspection and projection system comprises a robotic arm operable to rotate about a plurality of axes, wherein an end effector is disposed at a distal end of the robotic arm. The inspection and projection system further comprises a linear rail system, wherein the robotic arm is coupled to the linear rail system, and wherein the robotic arm is operable to translate along the linear rail system. The inspection and projection system further comprises a frame, wherein the linear rail system is disposed on top of the frame, and an information handling system coupled to the frame, wherein the information handling system is operable to actuate the robotic arm and the linear rail system.
G05D 1/00 - Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
G05D 1/227 - Handing over between remote control and on-board controlHanding over between remote control arrangements
B05B 13/04 - Means for supporting workArrangement or mounting of spray headsAdaptation or arrangement of means for feeding work the spray heads being moved during operation
Motion steering under kino dynamic constraints is provided. A system can receive an indication to return to a route generated for autonomous navigation by the aircraft to a destination. The system can generate a vector field formed of a plurality of vectors that merge into the route. The vector field can be generated responsive to the indication to return to the route. The system can provide instructions to steer the aircraft toward the destination along the route via one or more vectors of the plurality of vectors in the vector field. The instructions can be based on a cost function applied to the vector field.
Systems and methods for providing situational awareness to pilots of an aircraft. One example system includes an electronic processor configured to receive a raw sensor value for an operational characteristic of the aircraft and generate a processed sensor value based on the raw sensor value. The electronic processor is configured to provide the processed sensor value to a flight control system. The electronic processor is configured to generate a first digital gauge object that includes a graphical representation of the raw sensor value. The electronic processor is configured to generate a second digital gauge object that includes a graphical representation of the processed sensor value and a graphical representation indicating that the processed sensor value is being displayed. The electronic processor is configured to present the first digital gauge object on a first display of the aircraft and the second digital gauge object on a second display of the aircraft.
According to some embodiments, an interface assembly for coupling an orthogonal circuit board to a main circuit board includes a frame, signal pins, and dielectric retainers. The frame is electrically coupled to a ground signal of the orthogonal circuit board. The dielectric retainers electrically isolate the plurality of signal pins from the frame. The frame includes an interface surface configured to electrically couple the frame to a plurality of ground spring pins of a spring interposer of the main circuit board. Each particular signal pin of the interface assembly includes a pin head configured to electrically couple the particular signal pin to a particular one of a plurality of signal spring pins of the spring interposer. The interface surface of the frame and the pin heads of the plurality of signal pins form a coplanar surface.
H01R 12/73 - Coupling devices for rigid printing circuits or like structures coupling with the edge of the rigid printed circuits or like structures connecting to other rigid printed circuits or like structures
H01R 12/72 - Coupling devices for rigid printing circuits or like structures coupling with the edge of the rigid printed circuits or like structures
H05K 1/14 - Structural association of two or more printed circuits
According to some embodiments, an interface assembly for coupling an orthogonal circuit board to a main circuit board includes a frame, signal pins, and dielectric retainers. The frame is electrically coupled to a ground signal of the orthogonal circuit board. The dielectric retainers electrically isolate the plurality of signal pins from the frame. The frame includes an interface surface configured to electrically couple the frame to a plurality of ground spring pins of a spring interposer of the main circuit board. Each particular signal pin of the interface assembly includes a pin head configured to electrically couple the particular signal pin to a particular one of a plurality of signal spring pins of the spring interposer. The interface surface of the frame and the pin heads of the plurality of signal pins form a coplanar surface.
B32B 5/12 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by the relative arrangement of fibres or filaments of adjacent layers
B32B 3/28 - 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 characterised by a layer comprising a deformed thin sheet, e.g. corrugated, crumpled
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
B32B 7/12 - Interconnection of layers using interposed adhesives or interposed materials with bonding properties
Systems and methods for providing cooling and fire suppression for battery modules of an aircraft. One embodiment described herein provides an aircraft including a plurality of battery modules and a battery thermal management system. Each battery of the plurality of battery modules includes a housing. The battery thermal management system includes a storage vessel containing a cooling propellant, a conduit fluidly coupling the storage vessel to an interior of the housing of each of the plurality of battery modules, a vessel valve controlling a flow rate of the cooling propellant from the storage vessel to the conduit, and a venting system. The venting system includes one or more nozzles extending to an exterior of the aircraft and in fluid communication with the interior of the housing of each of the plurality of battery modules. The one or more nozzles direct the cooling propellant to the exterior of the aircraft.
H01M 10/6568 - Liquids characterised by flow circuits, e.g. loops, located externally to the cells or cell casings
H01M 10/48 - Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte
A system and method for operating and fabricating microelectronics for use in extreme-temperature operating environments is disclosed. The microelectronics are designed for operating at conditions that may include temperatures greater than three hundred degrees Celsius. The system and method include one or more modules that each comprise a substrate, a package lid, and an integrated circuit die. A package lid that encloses the integrated circuit die and is disposed on the opposite side of the integrated circuit die from that of a substrate. A thermo-mechanical attachment layer is provided between the integrated circuit die and package lid. Additionally, one or more microfabricated metal pillars that incorporate both thermo-mechanical pathways and signal pathways are provided to connect the integrated circuit die to the substrate.
A fastener removal assembly comprises a drive housing operable to receive a drive unit, wherein the drive housing comprises a shaft configured to rotate based on operation of the drive unit, the shaft extending downwards and out of the drive housing. The fastener removal assembly further comprises a set of gripping jaws disposed under the drive housing and around a portion of the shaft and a first pneumatic actuator coupled to the set of gripping jaws configured to actuate the set of gripping jaws to expand and retract. The fastener removal assembly further comprises at least one second pneumatic actuator disposed on top of the first pneumatic actuator. The fastener removal assembly further comprises an intermediate coupler, wherein the intermediate coupler is coupled to a side of the drive housing, and wherein the at least one second pneumatic actuator is coupled to a bottom side of the intermediate coupler.
A system including an apparatus for determining the presence of ice on an external surface of a structure is provided. The apparatus includes a sensor that includes first and second parallel ink or paint conductive traces separated by a gap. The apparatus also includes a circuit configured to measure the impedance or change in impedance between the first and second parallel ink or paint conductive traces.
Embodiments provide a method executed by a secure remote direct memory (RDMA) system. The method includes detecting, by the secure RDMA system, a connection request to create an encrypted connection between a first computing device and a second computing device. An encryption key is shared between the first computing device and the second computing device. In response to sharing the encryption key, accessing a plurality of images of a plurality of memories of the second computing device. The plurality of images of the plurality of memories includes memory addresses. The method includes receiving an access request specifying a range of memory addresses from the first computing device based on accessing the plurality of images of the plurality of memories. The method includes creating an encrypted tunnel between the first computing device and the second computing device to share memory information based on the range of memory addresses of the plurality of memories, in response to the access request.
Embodiments provide a system for managing traffic packets of application components. The system includes a security controller. The security controller may be coupled to a plurality of application components. The security controller includes one or more memories and a plurality of processors. The one or more memories are operable to store a set of application components features of each application component of the plurality of application components. The processors may be coupled with the memories and a processor may be configured to perform one or more steps. The processor receives traffic packets from a set of the plurality of application components coupled to the security controller. The processor receives traffic packets from a set of the plurality of application components coupled to the security controller. The processor inspects the traffic packets of the set of the plurality of application components to determine an application component feature of each of the application components in the set of the plurality of application components. The processor compares the application component feature of each of the application components with the set of application components features. The processor performs one or more operations to manage the traffic packets of each of the set of the plurality of application components based on comparing the application component feature of each of the set of the plurality of application components with the set of application components features.
Printable high-strength alloys, including aluminum alloys can be produced in an additive manufacturing process. Such alloys can include aluminum-silver (“Al—Ag”) alloys that are produced by a laser melting process using a powder bed fusion. The results of the process and the characteristics of the produced alloy can be determined by controlling at least an energy beam power, an energy beam speed, and/or an energy beam size. The operational parameters can be controlled with high precision to produce a printable, high-strength aluminum alloy.
B22F 10/31 - Calibration of process steps or apparatus settings, e.g. before or during manufacturing
B22F 10/36 - Process control of energy beam parameters
B22F 12/00 - Apparatus or devices specially adapted for additive manufacturingAuxiliary means for additive manufacturingCombinations of additive manufacturing apparatus or devices with other processing apparatus or devices
A lens installation system that includes a tool for a keyhole in an imaging system housing. The tool includes a base having a first diameter dimensioned to fit below a lens housing cavity of an imaging system housing. The base has a top end forming a shoulder to seat the shoulder below the lens housing cavity. The tool includes a lens centering seat integrated with the base. The seat includes a ring and a recessed cavity within the ring. The ring is defined by an outer surface dimensioned to contact an inner diameter of an inner surface of the keyhole below the lens housing cavity, a first sloped surface providing a chamfered edge that is inclined for a distance above the outer surface, and a second sloped surface descending from an upper edge of the first sloped surface by a predetermined distance.
G02B 27/62 - Optical apparatus specially adapted for adjusting optical elements during the assembly of optical systems
G02B 1/02 - Optical elements characterised by the material of which they are madeOptical coatings for optical elements made of crystals, e.g. rock-salt, semiconductors
G02B 7/00 - Mountings, adjusting means, or light-tight connections, for optical elements
G02B 13/14 - Optical objectives specially designed for the purposes specified below for use with infrared or ultraviolet radiation
78.
Digital holographic tomography turbulence measurements
Localized measurement of turbulent airflows is provided using enhanced techniques of digital holography with computed tomography. In an implementation, an optical beam is diffracted to produce an array of signal beams which propagate at different angles through a test volume that includes a test article. A reference beam is optically interfered with the array of signal beams after propagating through the test volume, producing a corresponding array of holograms simultaneously detected by a single digital holographic sensor. Digitized versions of the holograms are processed to produce a signal field for each test beam. Computed tomography is then applied to the signal fields to determine path-resolved turbulence measurements.
Methods and systems for providing a cold plate assembly include providing a base and a cover. The cover can be fixedly coupled to the base. Each of the base and the cover can include spaced internal ribs, which can form flow paths when the base and cover are fixedly coupled together. The internal ribs of the base and the cover can have spaced tabs that can be fixedly coupled to the other of the base or the cover. The base and the cover may also include spaced external or outer sacrificial ribs.
B23K 20/12 - Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by frictionFriction welding
B23P 15/26 - Making specific metal objects by operations not covered by a single other subclass or a group in this subclass heat exchangers
A gearbox includes a housing defining an interior. The housing includes outer walls and inner walls defining other structure within the housing, and at least one wall of the housing includes a semi-hollow volume. A main lubricant reservoir is disposed within the interior of the housing, and at least one pump is arranged in the interior of the housing for pumping lubricant from the main lubricant reservoir and distributing the lubricant throughout the housing. The semi-hollow volume of the at least one wall stores lubricant during normal operation of the pump, and when a loss of lubricant occurs within the housing, lubricant seeps from the semi-hollow volume to distribute lubricant throughout the housing.
According to some embodiments, a system includes a three-dimensional (3D) printer, a hydraulic press, and a kiln. The three-dimensional printer includes a print bed, a first printhead, and a second printhead. The first printhead is configured to deposit a layer of a first powder on the print bed. The second printhead is configured to deposit a layer of a second powder on the print bed. The hydraulic press is configured to compress a greenware to form a compressed greenware. The kiln is configured to heat the compressed greenware to a reaction temperature to form an object. The object is surrounded by an excess of the first powder. The kiln is also configured to heat the object surrounded by the excess of the first powder to a melting temperature. The melting temperature is at least the melting point of the first powder and less than the melting point of the object.
A rotor blade configured to be installed on a rotary wing aircraft includes a spar including an inboard portion extending from a root of the rotor blade to a first spanwise position of the rotor blade and an outboard portion meeting the inboard portion at the first spanwise position. The rotor blade further includes an upper skin and a lower skin coupled the outboard portion of the spar. The first spanwise position is defined by a most inboard point at which the upper and lower skins are coupled to the spar. The inboard portion includes a top layer, a bottom layer, and an inner cavity. The top layer has a substantially constant first thickness and the bottom layer has a substantially constant second thickness, and the distance between an outer surface of the top layer and an outer surface of the bottom layer is substantially constant.
A control input operable by a user for controlling movement of an aircraft includes a base portion configured for coupling to a support surface, the base portion biased towards a neutral position defined along a central axis and pivotable to a plurality of angular positions relative to the central axis. The control input also includes a grip portion having inputs for controlling movement of the aircraft and pivotally coupled to the base portion, the grip portion pivotable between a first position in which the grip portion extends from the base portion and a second position in which the grip portion is pivoted relative to the base portion. Further, the control input includes a lock mechanism for locking the grip portion in the first position wherein releasing the lock mechanism allows the grip portion to move to the second position.
B64C 13/14 - Initiating means actuated personally lockable
B64C 27/56 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement characterised by the control initiating means, e.g. manually actuated
84.
AUTOMATED MIXING SYSTEM FOR CARTRIDGES CONTAINING MATERIALS
Current cartridge-style mixers due not have the ability to measure mixing performance nor determine the need for maintenance based on performance. Risks of non-homogeneous mixing and insufficient maintenance can exist with cartridge-style mixers. A mixing system comprises a mixing apparatus, a first switch, a magnetic switch, and a controller. The mixing apparatus is configured to receive a cartridge and to mix a material. The mixing apparatus comprises a linear actuator configured to translate the cartridge or plunger in a vertical direction and a spindle configured to rotate a plunger. The first switch is configured to measure a number of strokes per unit of time of operating the linear actuator. The magnetic switch is configured to measure a speed of the spindle. The controller is configured to receive one or more mixing parameters, actuate the spindle and the linear actuator, and actuate a light to indicate if there was sufficient mixing.
B01F 27/805 - Mixers with rotary stirring devices in fixed receptaclesKneaders with stirrers rotating about a substantially vertical axis wherein the stirrers or the receptacles are moved in order to bring them into operative positionMeans for fixing the receptacle
B01F 31/20 - Mixing the contents of independent containers, e.g. test tubes
B01F 35/212 - Measuring of the driving system data, e.g. torque, speed or power data
In one embodiment, systems and methods include using an evaporator coil with a solid oxide fuel cell generator to generate energy for an aircraft vehicle. The system comprises a solid oxide fuel cell generator operable to generate energy. The system further comprises a first tank fluidly coupled to the solid oxide fuel cell generator configured to discharge a fluid to the solid oxide fuel cell generator and to receive the fluid from an evaporator coil coupled to the solid oxide fuel cell generator. The system further comprises a second tank fluidly coupled to the first tank and having a volume of the fluid, wherein the second tank is configured to discharge the fluid to the first tank, wherein the evaporator coil receives the discharged fluid from the second tank and increases the temperature of the discharged fluid prior to the first tank receiving the discharged fluid.
Provided herein are various enhancements for antenna systems and directed radio frequency energy structures. In one example, an apparatus includes an antenna array comprising a plurality of antenna elements formed by waveguide structures embedded within a substrate and positioned about a longitudinal axis of the substrate to form at least two concentric ring arrangements of antenna elements. Apertures of the waveguide structures are configured to emit or receive radio frequency (RF) energy generally along the longitudinal axis. Feed elements are coupled to each of the waveguide structures on an end opposite of the apertures, and configured to couple the RF energy for the antenna array.
H01Q 1/52 - Means for reducing coupling between antennas Means for reducing coupling between an antenna and another structure
H01Q 3/22 - Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system varying the orientation in accordance with variation of frequency of radiated wave
H01Q 21/20 - Arrays of individually energised antenna units similarly polarised and spaced apart the units being spaced along, or adjacent to, a curvilinear path
H01Q 21/30 - Combinations of separate antenna units operating in different wavebands and connected to a common feeder system
Load volume predication for slung loads of aerial vehicles are disclosed. A system can identify parameters of a load. The system can determine a volume occupied by a superposition of locations of the cone. The system can receive from sensors or models, characteristics of an environment associated with the aerial vehicle or the load. The system can detect an obstacle in the environment. The system can take a navigational action in response to detecting the obstacle.
G05D 1/00 - Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
G05D 1/10 - Simultaneous control of position or course in three dimensions
B64U 101/60 - UAVs specially adapted for particular uses or applications for transporting passengersUAVs specially adapted for particular uses or applications for transporting goods other than weapons
88.
Actuator for pitch control for a rotor system of an aircraft
A propeller assembly for an aircraft includes a main shaft rotatable about a propeller axis, a rotor hub mounted to the main shaft, and a plurality of blades coupled to the rotor hub. Each blade is rotatably coupled to the rotor hub for rotation about a blade rotation axis. A control system rotates each blade about the corresponding blade rotation axis and includes a ball screw coupled to the main shaft for rotation about the propeller axis and configured to translate along the propeller axis, an actuator beam mounted on the ball screw, and a ball nut coupled to the ball screw. When the ball nut rotates relative to the ball screw, the ball screw translates relative to the main shaft along the propeller axis. A differential transmission is configured to rotate the ball nut relative to the ball screw such that the ball screw is translated.
A rotor blade for a rotary wing aircraft includes a leading edge and a trailing edge defining a chordwise direction. The leading edge defines a forward end of the rotor blade and the trailing edge defines an aft end of the rotor blade. The rotor blade has a center of gravity and an aerodynamic center along the chordwise direction. The center of gravity is aft of the aerodynamic center.
A rotary shaft assembly includes a rotary shaft having a first end portion, a second end portion opposite the first end portion, a longitudinal axis extending centrally through the first and second end portions, and a shaft body that defines a bore between the first and second end portions. An anti-flailing mechanism is positioned within the bore of the shaft body. The anti-flailing mechanism is coupled to rotary shaft and extends at least partially between the first and second end portions to contain the rotary shaft about the longitudinal axis when the rotary shaft fails.
B64C 27/10 - Helicopters with two or more rotors arranged coaxially
B64C 27/14 - Direct drive between power plant and rotor hub
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
B64C 27/82 - RotorcraftRotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting-rotor torque or changing direction of rotorcraft
A hybrid propulsion system extracts electrical power using a combined heat engine and electrical generator. The propulsion system includes a gas generator, an electrical power generator disposed upstream of the gas generator and configured to be driven by a power turbine, an output power shaft mated to the power turbine and extending through a central axis of the gas generator and power generator unit, an engine enclosure circumferentially surrounding the power generator, and a shroud disposed between the power generator and the engine enclosure. The electrical power generator includes at least one rotating member and a stationary conductive member, wherein the at least one rotating member includes a magnetic portion, and rotation of the at least one rotating member relative to stationary conductive member generates a current transmissible by one or more coupled power output cables.
F01D 15/10 - Adaptations for driving, or combinations with, electric generators
H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
A vibration control assembly includes a housing having an interior region and an inner mass including a cage disposed within the interior region of the housing and being rotatable within the housing about a first axis and a gyroscope wheel disposed within the cage and rotatable about a second axis other than the first axis. At least one driving source includes a stator and is operable to interact with a magnetic field of the inner mass to drive rotation of the inner mass about at least one of the first axis and the second axis, wherein the at least one driving source is mounted within the interior region of the housing.
Provided herein are various magnetoelectric dipole antenna arrays and multi-array arrangements for handling radio frequency signals. In one example, an antenna array includes a baseplate conductively coupled to sets of plate elements by support members that position the plate elements at selected distances offset from a surface of the baseplate. Antenna probes are arranged in orthogonal pairs positioned within gaps between a corresponding set of plate elements, with each antenna probe comprising a conductive strip having a feed section coupled to a radio frequency connection through the baseplate, a transverse section generally parallel with the baseplate, and a terminal section directed back toward the baseplate. Dielectric structures for each pair of antenna probes comprise a dielectric material having channels that recess the conductive strips therein and a dielectric spacer positioned between overlapping transverse sections of the antenna probes.
H01Q 21/06 - Arrays of individually energised antenna units similarly polarised and spaced apart
H01Q 21/26 - Turnstile or like antennas comprising arrangements of three or more elongated elements disposed radially and symmetrically in a horizontal plane about a common centre
H01Q 21/08 - Arrays of individually energised antenna units similarly polarised and spaced apart the units being spaced along, or adjacent to, a rectilinear path
Provided herein are various enhanced systems, apparatuses, and techniques for on-surface analysis of celestial or terrestrial surfaces, such as for discovery and analysis of water ice deposits, locations, abundances, and depths. An example herein includes a swarm of spherical payloads sequentially deployed by a deployment host across a large area of a surface to impact the surface, sense properties of the surrounding environment using avionics and scientific instrumentation, and to establish a communication network to collect and transmit collected data.
Provided herein are various enhanced techniques for ultraviolet decontamination via emission of ultraviolet radiation and tracking emission exposure. An example method includes obtaining an emission characteristic for a radiation source. The method also includes capturing a depth map of a scene comprised of one or more objects and processing the depth map and an emission characteristic to determine an indication of exposure levels of the one or more objects to radiation emitted by the radiation source. An exposure visualization is generated based at least on the indication of exposure levels and displaying the exposure visualization.
A heating system for a component within a compartment of a spacecraft includes a fuel source, a gas generator, and a heat sink. The fuel source includes hydrazine. The gas generator is in fluid communication with the fuel source. The gas generator includes a catalyst. The catalyst is configured to decompose the hydrazine and generate an exhaust gas. The heat sink is thermally coupled to the gas generator and configured to receive heat from the exhaust gas of the gas generator. The heat sink is thermally coupled to the component within the compartment of the spacecraft to transfer heat from the exhaust gas to the component.
Provided herein are various improvements to antenna stabilization systems, such as employed on confocal phased array reflector antenna arrangements. In one example, a system includes a feed structure for a main reflector, the feed structure comprising an electronically scanned array (ESA) feed and a sub-reflector. The sub-reflector is configured to propagate a signal between the ESA feed and the main reflector. The system also includes a star tracker element coupled to the feed structure and configured to determine orientation information relative to star alignment, and laser distancing elements coupled to the feed structure and configured to determine distance measurements relative to the main reflector. A control system is configured to determine pointing errors of the main reflector based at least on the orientation information and the distance measurements, and these pointing errors can be used by the ESA feed to adjust steering of a signal towards a target.
H01Q 19/18 - Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces having two or more spaced reflecting surfaces
H01Q 3/20 - Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical relative movement between primary active elements and secondary devices of antennas or antenna systems for varying relative position of primary active element and a reflecting device wherein the primary active element is fixed and the reflecting device is movable
H01Q 3/34 - Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system varying the relative phase or relative amplitude of energisation between two or more active radiating elementsArrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system varying the distribution of energy across a radiating aperture varying the phase by electrical means
H01Q 1/28 - Adaptation for use in or on aircraft, missiles, satellites, or balloons
A method of modifying a rotor blade is provided for a rotor blade including a spar having an inboard portion with a substantially constant overall height, the inboard portion further including a top layer having a substantially constant first thickness and a bottom layer having a substantially constant second thickness. The method includes removing a root portion of the inboard portion to thereby modify the rotor blade and installing a cuff configured to couple to the rotor blade to an aircraft.
According to an embodiment, a method includes identifying, by a first network component, data and determining a security level from a plurality of security levels associated with the data. The method also includes determining an encryption scheme from a plurality of encryption schemes to apply to the data and applying, using a Quantum Resistant Ledger (QRL), the encryption scheme to the data to generate encrypted data. The method further includes communicating the encrypted data to a second network component.
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
H04L 9/30 - Public key, i.e. encryption algorithm being computationally infeasible to invert and users' encryption keys not requiring secrecy
100.
DIGITAL CONTENT MANAGEMENT THROUGH ON-DIE CRYPTOGRAPHY AND REMOTE ATTESTATION
A system for digital rights management including a processor in a platform and a memory device comprising instructions that when executed configure the processor to perform operations. The operations may include determining whether a digital media is locally installed in a platform before initiating an operating system, and launching a first UEFI application configured to generate attestation data and communicate attestation based data to a server through an encrypted medium in response to determining the digital media is not installed. The operations may also include receive a binary file of the digital media and a first decryption key and performing a sealing of the binary file using a sealing enclave of the first UEFI application and generating a local decryption second key based on the first key and local entropy. The operations may also include installing the sealed binary file on local storage.
G06F 21/53 - Monitoring users, programs or devices to maintain the integrity of platforms, e.g. of processors, firmware or operating systems during program execution, e.g. stack integrity, buffer overflow or preventing unwanted data erasure by executing in a restricted environment, e.g. sandbox or secure virtual machine
G06F 21/57 - Certifying or maintaining trusted computer platforms, e.g. secure boots or power-downs, version controls, system software checks, secure updates or assessing vulnerabilities
patents
