In one embodiment, systems and methods include using an eddie-bolt inspection tool to measure one or more eddie-bolts. An eddie-bolt inspection tool comprises a body; a valve; a light-emitting diode (LED); a battery; a first position switch; a second position switch; a cap; a nose piece; and a cover; wherein the cap is disposed on top of the body, wherein the body is disposed on top of the nose piece, where the nose piece is at least partially disposed within the body, wherein the cover is disposed around and on at least a portion of the body, wherein the body comprises: a first side; a second side; a third side; a fourth side; and an opening.
G01B 11/02 - Measuring arrangements characterised by the use of optical techniques for measuring length, width, or thickness
B64F 5/60 - Testing or inspecting aircraft components or systems
B64C 1/12 - Construction or attachment of skin panels
F16B 29/00 - Screwed connection with deformation of nut or auxiliary member while fastening
F16B 39/28 - Locking of screws, bolts, or nuts in which the locking takes place during screwing down or tightening by special members on, or shape of, the nut or bolt
G01B 11/08 - Measuring arrangements characterised by the use of optical techniques for measuring diameters
A septumless polarizer is an OMT polarizer which is formed without a traditional thin septum which bridges the gap from the first assembly half to the second assembly half when the polarizer is split in the zero-current region of the rectangular waveguides (RHCP and LHCP ports). The septumless polarizer utilizes a dual-axis-stepped feature, which is included in one half of the polarizer only, creates the illusion of a traditional thin septum and actually improves performance. A close-proximity fastener scheme is enabled along with a fully encompassing pressure lip and contact pressure risks are mitigated.
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 25/00 - Antennas or antenna systems providing at least two radiating patterns
H04B 1/00 - TRANSMISSION - Details of transmission systems not characterised by the medium used for transmission
3.
MULTISEGMENT ARRAY-FED RING-FOCUS REFLECTOR ANTENNA FOR WIDE-ANGLE SCANNING
A multisegment array-fed reflector antenna includes a feed array consisting of a number of subarrays and a multisegment reflector to reflect multiple beams of the feed array into a number of elevation angles. A support structure couples the multisegment reflector to the feed array. The multisegment reflector includes two or more ring-focus parabolic segments, and each ring-focus parabolic segment is a parabolic surface extending along a circle around the support structure.
H01Q 19/17 - 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 wherein the surfaces are concave the primary radiating source comprising two or more radiating elements
H01Q 19/19 - 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 comprising one main concave reflecting surface associated with an auxiliary reflecting surface
A multipaction-proof waveguide filter includes a main cavity and a number of corrugations extending from the main cavity. The main cavity includes corrugation interconnect regions between the plurality of corrugations. The corrugation interconnect regions include sloped surfaces, and the corrugations include flared nonparallel sidewalls. Due to the introduced sloped surfaces and flares, an increased Q is achieved, improved roll off is observed and multipaction risks are mitigated.
A Reconfigurable, Flexible Multi-User (RFMU) electronically steered antenna (ESA) includes a top panel and a number of side panels that enable many contacts simultaneously with varying gain requirements from a single, in situ, installation. The top panel includes multiple subarrays and can communicate with flyover satellites, and the side panels can communicate with satellites flying past a side of the ESA. The top panel and the side panels can achieve a beam steering that covers a full or partial, variable gain, hemispheric field-of-view (FoV). The RFMU ESA terminal top and side panels are scalable using flexible modular building blocks. This enables increased contacts, increased gain or a combination thereof sized to meet desired performance.
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
A panel assembly for use with a spacecraft includes a payload, a radiator panel and a heat pipe. The payload is configured to generate waste heat during operation. The radiator panel is spaced apart from the payload and is configured to dissipate waste heat. The heat pipe is coupled to the payload and the radiator panel. The heat pipe includes a compliant portion to permit the radiator panel to move relative to the payload. Further the heat pipe is configured to transfer waste heat from the payload to the radiator panel.
F28D 15/02 - Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls in which the medium condenses and evaporates, e.g. heat-pipes
H01L 23/42 - Fillings or auxiliary members in containers selected or arranged to facilitate heating or cooling
7.
HOSTED, COMPACT, LARGE-APERTURE, MULTI-REFLECTOR ANTENNA SYSTEM DEPLOYABLE WITH HIGH-DISSIPATION FEED
A hosted multi-reflector antenna system includes a primary reflector, a subreflector, an aperture, a feed structure and an anti-jam housing. The feed structure includes an electronically steered antenna (ESA). The subreflector directs a reflected beam between a primary reflector and an ESA, and the anti-jam housing encloses the subreflector and the ESA. The antenna system is thermo-elastically decoupled and thermally self-sufficient, accommodates thermal dissipation of the feed structure, and can maintain a precise antenna alignment.
H01Q 15/16 - Reflecting surfaces; Equivalent structures curved in two dimensions, e.g. paraboloidal
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 19/19 - 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 comprising one main concave reflecting surface associated with an auxiliary reflecting surface
8.
PLASMA CREATION AND HEATING VIA MAGNETIC RECONNECTION IN AN ENCAPSULATED LINEAR RING CUSP
In one embodiment, a fusion reactor includes an enclosure, one or more internal magnetic coils suspended within an interior of the enclosure and co-axial with a center axis of the enclosure, one or more encapsulating magnetic coils co-axial with the center axis of the enclosure, the encapsulating magnetic coils having a larger diameter than the internal magnetic coils, one or more mirror magnetic coils co-axial with the center axis of the enclosure, and one or more magnetic reconnection coils co-axial with the center axis of the enclosure, wherein the one or more magnetic reconnection coils, when pulsed by a power source, are disposed to reconfigure one or more magnetic fields within the enclosure. The reconfiguration, or magnetic reconnection, of the one or more magnetic fields is disposed to increase energy in the magnetic fields, thereby facilitating the conditions operable to generate plasma, and further, when the magnetic fields are collapsed, releasing the energy into the plasma.
A printed circuit board (PCB) device including one or more insulating layers and one or more conducting layers arranged to form a layer stack; and one or more blind holes disposed along a side edge of the layer stack and parallel to a plane of the layer stack. Each of the one or more blind holes along the side edge of the layer stack is configured to receive a pin. Each pin can make an electrical connection with a corresponding blind hole.
In one embodiment, a system includes a thermionic emitter and a heater at least partially surrounding the thermionic emitter. The heater is configured to heat the thermionic emitter. The heater includes a first end, a second end opposite the first end, and a plurality of hollow insulating tubes that each run from the first end to the second end. The heater also includes a heater wire that runs through each of the hollow insulating tubes, The heater wire is configured to be resistively heated by an electrical current passed through the heater wire.
H05B 3/14 - Heating elements characterised by the composition or nature of the materials or by the arrangement of the conductor characterised by the composition or nature of the conductive material the material being non-metallic
In one embodiment, a system includes a cathode and a thermionic emitter installed at least partially within the cathode tube of the cathode. The thermionic emitter is in a shape of a hollow cylinder. The hollow cylinder includes an outer surface and an unsmooth inner surface. The outer surface is configured to contact an inner surface of the cathode tube. The unsmooth inner surface includes a plurality of structures that provide an increase in surface area over a smooth surface.
A plasma confinement system includes an enclosure, one or more internal magnetic coils suspended within the enclosure in a plasma region, and one or more supports configured to support the one or more internal magnetic coils suspended within the enclosure. Each support of the one or more supports includes a first end and a second end opposite the first end. The first end is coupled to an interior portion of the enclosure and the second end is coupled to a component disposed within the plasma region. Each support further includes electrical conducting material disposed between the first end and the second end. The electrical conducting material is configured to, when supplied with one or more electrical currents, generate a magnetic field having a magnetic field gradient that varies along the support from the first end to the second end.
A communication system consists of a satellite constellation including a number of NGSO satellites, one or more gateways and a control center. The satellites facilitate communication for multiple user terminals. Each gateway communicates with the satellites and user terminals and provides connectivity to the terrestrial networks, and the control center controls operation of the satellites, the gateways and the user terminals. The satellites, the user terminals, the gateways and the control center include hardware that may be software-defined network (SDN) enabled to ensure efficient admission control, precision handover management and quality-of-service (QoS) enforcement algorithms.
A communication system includes a satellite constellation, one or more gateways and a network controller. The satellite constellation includes multiple satellites to facilitate communication between a number of user terminals (UTs). Each gateway communicates with one or more of the satellites. The network controller controls operation of the satellites, the gateways and the UTs. The satellites, the UTs, the gateways and the network controller include hardware that may also be software-defined network (SDN) enabled to ensure a persistent end-to-end data packet forwarding including proactive updates and reactive updates to forwarding tables. The proactive updates handle deterministic and time-synchronized link connectivity changes and the reactive updates handle ad hoc link connectivity changes.
A system comprising non-transitory and tangible memory comprising program instructions for performing an extended laser active ranging (LEAR) procedure having a first mode and a second mode. The system includes a processor configured to execute the program instructions to cause the processor to receive selection of a region-of-interest (ROI) having a pixel cluster; and cause laser ranging using a laser ranging system in the first mode. The process is configured to determine whether a laser ranging reflection (ERR) signal is received by a laser photodetector of a gimbal during the first mode. If the ERR signal is not received, the processor performs the second mode of the LEAR procedure initialized to a center of the selected ROI to search for a reflective surface in the ROI of an imaged real-world view of an ambient scene and registered to the pixel cluster to find a small target.
A lower-body exoskeleton using electromyography for direct force amplification is disclosed. The embodiments relate generally to powered exoskeletons and, in particular, to a powered lower-body exoskeleton using electromyography for direct force amplification, where the powered lower-body exoskeleton has no load-bearing interface to receive an external load, and the powered lower-body exoskeleton has no load-bearing ground contact configured to transfer an external load to the ground.
Disclosed herein is a padded and prewired exoskeleton harness. The exoskeleton harness comprises a clothing article including a clothing material to receive at least a portion of a user. In certain embodiments, the clothing material includes a fabric and at least one patch with a greater coefficient of static friction and greater thickness than the fabric to increase the friction between the user and the exoskeleton, thereby increasing coupling and power transfer therebetween. In certain embodiments, the exoskeleton harness includes at least one internal electronic port positioned at an interior of the clothing material to electronically communicate with one of a plurality of skin-mounted biosensors. The internal ports are prewired within the clothing material to an external electronic port for communicating with the exoskeleton. The prewiring of the exoskeleton harness facilitates connection between skin-mounted sensors and a data acquisition (DAQ) system.
A41D 13/05 - Professional, industrial or sporting protective garments, e.g. surgeons' gowns or garments protecting against blows or punches protecting only a particular body part
In one embodiment, an electronic display assembly includes a microlens layer and a pixel array layer. The microlens-layer includes a plurality of cells. The pixel array layer is adjacent to the microlens layer. The pixel array layer includes a plurality of pixels. Bach, cell of the plurality of cells includes a. transparent lenslet and one or both of: a plurality of opaque walls configured to prevent light from bleeding into adjacent cells; and a filter layer on one end of each cells of the plurality of cells. The filter- layer is configured to limit light passing through the filter layer to a specific incident angle.
In one embodiment f an electronic display assembly includes a circuit board, a first microlens layer on a first side of the circuit board; and a second microlens layer on an opposite side of the circuit board from the first microlens layer. The first microlens layer includes a first plurality of microlenses, and the second microlens layer includes a second plurality of microlenses, The electronic- display assembly further includes an image sensor layer adjacent to the first microlens layer and a display layer adjacent to the second microlens array. The Image sensor layer includes sensor pixels for detecting incoming light through the first microlenses, and the display layer includes display pixels for emitting light through the second microlenses. The electronic display assembly emulates transparency by emitting light from the second microlenses at angles that correspond to angles of the incoming light detected through the first microlenses.
H01L 25/16 - Assemblies consisting of a plurality of individual semiconductor or other solid state devices the devices being of types provided for in two or more different main groups of groups , or in a single subclass of , , e.g. forming hybrid circuits
A fusion reactor includes a fusion plasma reactor chamber. A magnetic coil structure is disposed inside of the fusion plasma reactor chamber, and a structural component is also disposed inside of the fusion plasma reactor chamber. The structural component couples the magnetic coil structure to the fusion plasma reactor chamber. A superconducting material is disposed at least partially within the structural component. A plurality of cooling channels are disposed at least partially within the structural component. An insulating material is disposed at least partially within the structural component.
Automatic electromyography (EMG) electrode selection for robotic devices is disclosed A plurality of signals from a corresponding plurality of sensors coupled to a skin of a user is received For each pair of at least some pairs of the plurality of sensors, a sensor pair signature is generated based on differences in signals that are generated by the respective pair of sensors Each of the sensor pair signatures is compared to a predetermined sensor pair signature to identify a particular pair of sensors A signal difference between two signals generated by the particular pair of sensors is subsequently utilized to generate a command to drive a motor
An adjustable force exoskeleton hip joint system. The system includes a hip joint. The hip joint includes a first member rotatable about a hip joint rotation axis, the first member configured to be coupled to one of a lower body link or an upper body link. The hip joint further includes a second member rotatable about the hip joint rotation axis, the second member configured to be coupled to the other of the lower body link or the upper body link. The system further includes an adjustable force mechanism coupled to at least one of the first member and the second member. The adjustable force mechanism includes an actuator coupled to the first member, the actuator comprising a motor configured to selectively apply an adjustable force to the second member to inhibit rotation of the first member with respect to the second member.
B25J 13/08 - Controls for manipulators by means of sensing devices, e.g. viewing or touching devices
B25J 19/00 - Accessories fitted to manipulators, e.g. for monitoring, for viewing; Safety devices combined with or specially adapted for use in connection with manipulators
Transfer of objects between spacecraft can be achieved in a low gravity environment. A capture device can be part of a module that facilitates visualization of a vessel that approaches the capture device. The module can facilitate positioning of the capture device for reception of the vessel. The capture device can include spring-loaded locking arms that both allow receipt and prevent escape of the vessel. At least a portion of each locking arm can extend radially inwardly and axially toward a cushion damper of the capture device. The locking arms can move radially away from each other upon application of a force from the vessel that is axially toward the cushion damper. The locking arms can move radially toward each other upon application of a force from the vessel that is axially away from the cushion damper.
An aerial vehicle includes a fuselage, a wing, and a wing shift device. The wing shift device is configured to be coupled to the fuselage. The wing shift device comprises a plurality of apertures for coupling the wing to the aerial vehicle. The plurality of apertures are configured to permit the wing to be shifted in a forward or aft direction along the fuselage based on a center of gravity of the aerial vehicle.
A helicopter includes a propulsion system (110), gimbal assembly (160), and a controller (182). The propulsion system includes a first rotor assembly (130a) and a coaxial counter-rotating second rotor assembly (130b). The first rotor assembly comprises a first motor (120a) coupled to a first rotor and the second rotor assembly comprises a second motor (120b) coupled to a second rotor. A housing (410) securing a gimbal assembly comprises a first portion and a second portion, the first portion being coupled to the propulsion system and the second portion being coupled to the fuselage (180); and the housing separates a first gimbal motor (165a) from a second gimbal motor (165b) thereby providing pitch and roll control during flight.
An apparatus includes a drive mechanism, a first cylinder comprising a first piston coupled to the drive mechanism, and a second cylinder comprising a second piston. The first cylinder includes a first fluid reservoir and a second fluid reservoir, with the first piston disposed between the first fluid reservoir and the second fluid reservoir. The second cylinder includes a third fluid reservoir and a fourth fluid reservoir, with the second piston disposed between the third fluid reservoir and the fourth fluid reservoir. The apparatus further includes a first fluid line coupling the first fluid reservoir to the fourth fluid reservoir, and a second fluid line coupling the second fluid reservoir to the third fluid reservoir. The first piston comprises a threaded portion disposed in a threaded aperture of the first cylinder.
F15B 7/00 - Fluid-pressure actuator systems in which the movement produced is definitely related to the output of a volumetric pump; Telemotors
F15B 3/00 - Intensifiers or fluid-pressure converters, e.g. pressure exchangers; Conveying pressure from one fluid system to another, without contact between the fluids
In one embodiment, a hybrid aircraft includes a fixed-wing propulsion system and a multirotor propulsion system. The multirotor propulsion system includes a propeller coupled to a motor shaft. A motor drives the propeller via the motor shaft. The hybrid aircraft further includes a magnetic orientation detent to prevent the propeller of the multirotor propulsion system from rotating when power to the multirotor propulsion system is removed. The magnetic orientation detent further includes a plurality of magnets coupled to the circumference of the motor shaft and a detent magnet magnetically coupled to the plurality of magnets.
B64C 27/30 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with provision for reducing drag of inoperative rotor
B64C 19/00 - Aircraft control not otherwise provided for
B64C 27/24 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with rotor blades fixed in flight to act as lifting surfaces
28.
MULTIPLE-EYE, SINGLE-DISPLAY, ULTRAWIDE-FIELD-OF-VIEW OPTICAL SEE-THROUGH AUGMENTED REALITY SYSTEM
An optical system is provided. The optical system includes a lens element and a lens element holder. The optical system also includes a display device holder that is configured to hold a display device having a single light-emitting panel. The lens element includes a right-eye reflective surface and a left-eye reflective surface. The right-eye reflective surface includes a first plurality of different surface elements oriented to reflect and collimate light from corresponding different regions of a first portion of the light-emitting panel toward a predetermined right-eye location, and the left-eye reflective surface includes a second plurality of different surface elements oriented to reflect and collimate light from corresponding different regions of a second portion of the light-emitting panel toward a predetermined left-eye location.
G02B 30/36 - Stereoscopes providing a stereoscopic pair of separated images corresponding to parallactically displaced views of the same object, e.g. 3D slide viewers using refractive optical elements, e.g. prisms, in the optical path between the images and the observer
G02B 7/02 - Mountings, adjusting means, or light-tight connections, for optical elements for lenses
A one-piece heat exchanger manufactured using an additive manufacturing process is described. The heat exchanger includes a plurality of channels formed therein. At least some of the plurality of channels may be configured to provide structural support to the heat exchanger to reduce its weight. Different coolant media may be used in a first set and a second set of the plurality of channels to provide different types of cooling in an integrated one-piece heat exchanger structure. The one-piece heat exchanger may have improved thermal conductive properties, and may improve cost and time delays associated with some conventional techniques.
An intermediate link for a tool arm assembly is provided. The intermediate link includes first and second connectors that are at least partially rotatable about respective first and second rotation axes. The intermediate link includes first and/or second lock rotation mechanisms that are configured to selectively prevent rotation of the first and second connectors.
B25J 19/00 - Accessories fitted to manipulators, e.g. for monitoring, for viewing; Safety devices combined with or specially adapted for use in connection with manipulators
The present disclosure relates to exoskeletons and in some embodiments, a variable or adjustable force exoskeleton hip joint. There is provided a system comprising a hip joint. The hip joint of the system comprises: a rotation axis, a first member rotatable about the rotation axis and having a lower body connection location configured to be coupled to a lower body link; and a second member rotatable about the rotation axis and having an upper body connection location configured to be coupled to an upper body link. The hip joint for the system further comprises: an adjustable force mechanism coupled to at least one member of the first member and the second member and configured to apply an adjustable force to the at least one member to hinder rotation of the upper body connection location with respect to the lower body connection location in a rotational direction.
A yaw brake mechanism is described for maintaining a yawing structure, such as a nacelle of a fluid turbine, at a desired orientation or azimuthal heading about a reference or yaw axis. The yaw brake mechanism uses one or more rotor locks and one or more receptacles that cooperate with one another to achieve the locking function. One of the rotor locks is actuatable so that a portion thereof can be engaged in one of the receptacles to lock the yawing structure. The number of rotor locks and receptacles can be selected to allow the yawing structure to achieve any azimuth heading around the full 360 degrees of the yaw axis with various degrees of accuracy. The yaw brake mechanism allows the yawing structure to maintain multiple headings while being subjected to extreme moment and force loads in a low mass, low height, low cost solution.
ABSTRACT In one embodiment, a wing includes a low pressure side, a high pressure side opposite the low pressure side, and a drag reducing apparatus coupled to the low pressure using an adhesive. The drag reducing apparatus includes a first side coupled to the low pressure side of the wing, and a second side opposite the first side, the second side comprising a plurality of vortex generators arranged in an array configuration, the array configuration of vortex generators operable to weaken a wingtip vortex generated by the wing by generating one or more vane vortices near an end of the low pressure side of the wing. CA 2913710 2019-03-20
In one embodiment, a wing includes a low pressure side, a high pressure side opposite the low pressure side, and a drag reducing apparatus coupled to the low pressure using an adhesive. The drag reducing apparatus includes a first side coupled to the low pressure side of the wing, and a second side opposite the first side, the second side comprising a plurality of vortex generators arranged in an array configuration, the array configuration of vortex generators operable to weaken a wingtip vortex generated by the wing by generating one or more vane vortices near an end of the low pressure side of the wing.
Methods are provided for implementing schemes for embedding a particular optimization problem into a particular hardware solution employing unique graph embedding techniques. The disclosed methods implement an adiabatic quantum optimization in a quantum computing device or a quantum processor. Heuristics for graph minor embedding are employed to map a problem graph structure of a particular binary unconstrained optimization problem onto a physical graph structure (topology) of the quantum computing device or quantum processor to provide an optimized hardware implementation. Known constraints that are presented with current schemes in their application to particular hardware solutions are avoided, including limited qubit connectivity and the presence of faulty qubits.
In an embodiment, a method includes, for each field of view of a plurality of fields of view forming a field of regard, positioning a rotating disk in a first position corresponding to a first section of a plurality of sections. Each section of the plurality of sections may have a different focal length. The method further includes receiving a first image representing a first field of view, analyzing the first image, adjusting the plurality of mirrors based on the analysis, positioning the rotating disk in a second position corresponding to a second section, and receiving a second image representing the first field of view captured while the rotating disk was in the second position. The method further includes generating a range image of the field of view using at least the first image and the second image, and determining a range to a target using the range image.
Aspects of the disclosure provide a method for configuring a Quantum Annealing (QA) device. Then QA device has a plurality of qubits and a plurality of couplers at overlapping intersections of the qubits. The method includes mapping a node of a neural network that have a plurality of nodes and connections between the nodes to a qubit in the QA device, and mapping a connection of the neural network to a coupler at an intersection in the QA device where two qubits corresponding to two nodes connected by the connection intersect. The method further includes mapping a node of the neural network to a chain of qubits. In an embodiment, a coupling between qubits in the chain is configured to be a ferromagnetic coupling in order to map the node of the neural network to the chain of qubits.
A disclosed apparatus for use with a conduction-cooled card assembly may include a frame comprising first and second thermally conductive portions adapted to engage respective thermal management interfaces on opposite sides of a conduction cooling frame for at least one circuit card. The apparatus may also include a passageway extending between first and second openings in the frame so as to allow cooling fluid to flow into the first opening, through the passageway, and out of the second opening. According to a disclosed method, an insert may be installed between components of a mezzanine connector so as to increase a height of the connector. In some implementations, the installing of the insert may be performed while the first and second components of the mezzanine connector are mounted on a host card and a mezzanine card, respectively, so that installation of the insert between the first and second components increases a spacing between the host card and the mezzanine card.
In one embodiment, a fusion reactor includes two internal magnetic coils suspended within an enclosure, a center magnetic coil coaxial with the two internal magnetic coils and located proximate to a midpoint of the enclosure, a plurality of encapsulating magnetic coils coaxial with the internal magnetic coils, and two mirror magnetic coil coaxial with the internal magnetic coils. The fusion reactor further includes one or more heat injectors operable to inject a beam of neutral particles toward the center of the enclosure.
G21B 1/05 - Thermonuclear fusion reactors with magnetic or electric plasma confinement
G21B 1/15 - Particle injectors for producing thermonuclear fusion reactions, e.g. pellet injectors
H05H 1/14 - Arrangements for confining plasma by electric or magnetic fields; Arrangements for heating plasma using applied magnetic fields only wherein the containment vessel is straight and has magnetic mirrors
40.
MAGNETIC FIELD PLASMA CONFINEMENT FOR COMPACT FUSION POWER
A infusion reactor(110) includes two internal magnetic coils(140) suspended within an enclosure( 120), a center magnetic coil(130) coaxial with the two internal magnetic coils(140) and located proximate to a midpoint of the enclosure, a plurality of encapsulating magnetic coils(150) coaxial with the internal magnetic coils, and two mirror magnetic coil (160)coaxial with the internal magnetic coils. The encapsulating magnetic coils(160) preserve the magnetohydrodynamic (MHD) stability of the fusion reactor by maintaining a magnetic wall that prevents plasma within the enclosure from expanding.
G21B 1/05 - Thermonuclear fusion reactors with magnetic or electric plasma confinement
H05H 1/14 - Arrangements for confining plasma by electric or magnetic fields; Arrangements for heating plasma using applied magnetic fields only wherein the containment vessel is straight and has magnetic mirrors
A fusion reactor includes an enclosure having a first end, a second end, and a midpoint substantially equidistant between the first and second ends of the enclosure. The fusion reactor includes two internal magnetic coils suspended within the enclosure and positioned on opposite sides of the midpoint of the enclosure, one or more encapsulating magnetic coils positioned on each side of the midpoint of the enclosure, two mirror magnetic coils positioned on opposite sides of the midpoint of the enclosure, and one or more cooling lines within each of the internal magnetic coils. The cooling lines carry a coolant and are operable to remove heat from the internal magnetic coils. The one or more encapsulating magnetic coils and the two mirror magnetic coils are coaxial with the internal magnetic coils. The magnetic coils are operable, when supplied with electric currents, to form magnetic fields for confining plasma within the enclosure.
G21B 1/05 - Thermonuclear fusion reactors with magnetic or electric plasma confinement
H05H 1/14 - Arrangements for confining plasma by electric or magnetic fields; Arrangements for heating plasma using applied magnetic fields only wherein the containment vessel is straight and has magnetic mirrors
42.
SYSTEM FOR SUPPORTING STRUCTURES IMMERSED IN PLASMA
A fusion reactor includes an enclosure having a first end, a second end opposite the first end, and a midpoint substantially equidistant between the first and second ends of the enclosure. The fusion reactor includes two internal magnetic coils suspended within the enclosure and positioned on opposite sides of the midpoint of the enclosure, one or more encapsulating magnetic coils positioned on each side of the midpoint of the enclosure, two mirror magnetic coils positioned on opposite sides of the midpoint of the enclosure, and one or more support stalks for supporting the two internal magnetic coils suspended within the enclosure. The one or more encapsulating magnetic coils and the two mirror magnetic coils are coaxial with the internal magnetic coils. The magnetic coils are operable, when supplied with electric currents, to form magnetic fields for confining plasma within the enclosure.
G21B 1/05 - Thermonuclear fusion reactors with magnetic or electric plasma confinement
H05H 1/14 - Arrangements for confining plasma by electric or magnetic fields; Arrangements for heating plasma using applied magnetic fields only wherein the containment vessel is straight and has magnetic mirrors
A variable pitch system for a water or wind turbine includes a hydraulic system that includes a first hydraulic system (90) and a second, redundant hydraulic system (92) that are completely contained in a nose region of the turbine. The first and second hydraulic systems (90, 92) can each be used during operation on a predetermined operating schedule. In addition, each of the first and second hydraulic systems (90, 92) can also include a pressure relief valve to limit back pressure on the hydraulic system from dynamic loads on the turbine blades. The pitch of all the blades (34) are changed simultaneously using a common linear to rotary actuating mechanism. To aid in cooling, the hydraulic reservoirs (100) for the first and second hydraulic systems (90, 92) can be attached to the front wall of the nose housing (40), and fins (120) can be provided on the exterior of the nose housing (40) at the front end to enhance heat extraction.
F03D 7/02 - Controlling wind motors the wind motors having rotation axis substantially parallel to the air flow entering the rotor
B63H 3/08 - Propeller-blade pitch changing characterised by use of non-mechanical actuating means, e.g. electrical fluid
B64C 11/38 - Blade pitch-changing mechanisms fluid, e.g. hydraulic
F03B 3/06 - Machines or engines of reaction type; Parts or details peculiar thereto with substantially axial flow throughout rotors, e.g. propeller turbines with adjustable blades, e.g. Kaplan turbines
F03B 17/06 - Other machines or engines using liquid flow, e.g. of swinging-flap type
44.
ENCAPSULATING MAGNETIC FIELDS FOR PLASMA CONFINEMENT
In one embodiment, a fusion reactor includes an enclosure, an open-field magnetic system comprising one or more internal magnetic coils suspended within the enclosure, and one or more encapsulating magnetic coils coaxial with the one or more internal magnetic coils of the open-field magnetic system. The one or more encapsulating magnetic coils form a magnetosphere around the open-field magnetic system. The open-field magnetic system and the one or more encapsulating magnetic coils, when supplied with electrical currents, form magnetic fields for confining plasma within the enclosure.
G21B 1/05 - Thermonuclear fusion reactors with magnetic or electric plasma confinement
H05H 1/14 - Arrangements for confining plasma by electric or magnetic fields; Arrangements for heating plasma using applied magnetic fields only wherein the containment vessel is straight and has magnetic mirrors
45.
MAGNETIC FIELD PLASMA CONFINEMENT FOR COMPACT FUSION POWER REACTOR
A fusion reactor (110) which includes a plurality of internal magnetic coils (140) suspended within an enclosure (120), one or more center magnetic coils (130) coaxial with the plurality of internal magnetic coils (140), a plurality of encapsulating magnetic coils (150) coaxial with the internal magnetic coils, and a plurality of mirror magnetic coils (160) coaxial with the internal magnetic coils. The encapsulating magnetic coils (150) maintain a magnetic wall that prevents plasma within the enclosure from expanding.
G21B 1/05 - Thermonuclear fusion reactors with magnetic or electric plasma confinement
H05H 1/14 - Arrangements for confining plasma by electric or magnetic fields; Arrangements for heating plasma using applied magnetic fields only wherein the containment vessel is straight and has magnetic mirrors
A tidal turbine system includes yaw drive (200) for rotating the turbine between a first position associated with tidal flow and a second position associated with tidal ebbs. The yaw drive is capable of moving the tidal turbine to a position where the tidal turbine is pointed substantially directly into the tidal flow in the first position and substantially into the tidal ebb in a second position. A method for harvesting tidal energy includes rotating the tidal turbine between one of the first position and the second position.
F03B 13/26 - Adaptations of machines or engines for special use; Combinations of machines or engines with driving or driven apparatus; Power stations or aggregates characterised by using wave or tide energy using tide energy
47.
LOW COST, HIGH-PERFORMANCE, SWITCHED MULTI-FEED STEERABLE ANTENNA SYSTEM
An apparatus for satellite communication may include a reflector configured to redirect electromagnetic energy. Each of multiple feeds may be positioned at a predetermined location with respect to the reflector. A feed-switching mechanism may be configured to selectively activate for use at least one of the multiple feeds. A steering mechanism may be configured to steer the reflector such that a focal point of the reflector approximately coincides with a position of an activated feed of the multiple feeds. The reflector may be mechanically independent of the plurality of feeds and the feed-switching mechanism.
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 19/17 - 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 wherein the surfaces are concave the primary radiating source comprising two or more radiating elements
48.
SCHEDULE MANAGEMENT SYSTEM AND METHOD FOR MANAGING AIR TRAFFIC
A system and method to improve efficiency in aircraft maneuvers meant to accommodate time-related constraints in air traffic, information related to flight performance and atmospheric conditions is gathered onboard an aircraft, then transmitted to an air traffic control center, in the event of a delay or any other event which necessitates an alteration in an aircraft trajectory, the data is sent to a decision support tool to compute and provide alternative trajectories, preferably including operator- preferred trajectories, within air traffic constraints. Air traffic controllers can then offer an alternative trajectory to an aircraft that is more efficient, cost effective, and/or preferable to the aircraft operator.
A solar tracking assembly includes a spine and a plurality of paired brackets connected to the spine. The brackets are positioned on opposite sides of the spine and at least one of the paired brackets includes wheels to allow rolling movement of the spine. An array arm is attached to each bracket and is moveable from a shipping position to a deployed position, and at least one solar array panel is secured to each array arm. A method of installing a solar panel assembly includes assembling in a secondary automated process at least one solar panel assembly in an offsite location, loading the solar panel assembly in the shipping position on a truck, transporting the truck to a deployment site, and off-loading the solar panel assembly from said truck.
A contour caul including two or more higher Tg regions that follow geometries of a composite structure and an expansion region located between the higher Tg regions. The expansion region has a lower glass-liquid transition temperature than the higher Tg regions. Also, a method making a composite structure.
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
51.
EFFICIENT HEALTH MANAGEMENT, DIAGNOSIS AND PROGNOSIS OF A MACHINE
Mechanisms for generating an analysis result about a machine (14) are provided. A device generates a first health management (HM) analysis result regarding a machine based on real-time first sensor information received during a first period of time and on a first version HM analytic model. The device provides, to an off-board device, a plurality of sensor information comprising the real-time first sensor information and that is generated during the first period of time. The device receives a second version HM analytic model that is based at least in part on the plurality of sensor information and fault information that identifies actual faults that have occurred on the machine (14). The device generates a second HM analysis result regarding the machine (14) based on real-time second sensor information received during a second period of time and on the second version HM analytic model.
G01M 99/00 - Subject matter not provided for in other groups of this subclass
B60R 16/02 - Electric or fluid circuits specially adapted for vehicles and not otherwise provided for; Arrangement of elements of electric or fluid circuits specially adapted for vehicles and not otherwise provided for electric
G07C 5/00 - Registering or indicating the working of vehicles
52.
METHODS AND SYSTEMS FOR INFERRING AIRCRAFT PARAMETERS
A method and system suitable for inferring trajectory predictor parameters of aircraft for the purpose of predicting aircraft trajectories. The method and system involve receiving trajectory prediction information regarding an aircraft, and then using this information to infer (extract) trajectory predictor parameters of the aircraft that are otherwise unknown to a ground automation system. The trajectory predictor parameters can then be applied to one or more trajectory predictors of the ground automation system to predict a trajectory of the aircraft. In certain embodiments, the method and system can utilize available air-ground communication link capabilities, which may include data link capabilities available as part of trajectory-based operations (TBO).
A vehicle suitable for use in high-altitude applications use may include a gas impermeable body and a flexible barrier separating the body into multiple sections or compartments. The compartments may include a lift compartment for holding lift gas, such as lighter than air gas, and a ballast compartment for holding a ballast, such as heavier than air gas. A valve may permit passage of the ballast from the ballast compartment to an exterior of the body. The body may have an oblong shape, with fins attached to an exterior back end thereof. The vehicle may have only internal ballast compartments, without including a hopper external to the body.
A lightweight beam may have a triangular prism core and a triaxial fabric cover wrapped around the core, with at least one rod proximate an apex of the core. The rod may extend substantially parallel to a centerline of the core. Multiple lightweight beams may be joined to form a larger lightweight structure.
A vacuum-forming system for deforming a forming blank is disclosed. The system includes a tool and at least one regulator bag disposed adjacent to the tool. The regulator bag includes a sealed bag having an exterior and an interior and a first volume and a defined passage from the interior to the exterior of the regulator bag. The passage is configured such that the regulator bag has a rate of deflation wherein the sealed bag will deflate from the first volume to a second volume over a determined period of time while the exterior of the sealed bag is at a determined reduced pressure. The system also includes a vacuum membrane coupled to the tool, the membrane configured to form a vacuum space enclosing the forming blank and the at least one regulator bag.
Methods and systems suitable for negotiating air traffic trajectory modification requests received from multiple aircraft that each has trajectory parameters. The methods include transmitting from at least a first aircraft a first trajectory modification request to alter the altitude, speed and/or lateral route thereof. A first conflict assessment is then performed to determine if the first trajectory modification request poses a conflict with the altitudes, speeds and lateral routes of other aircraft. If a conflict is not identified, the first trajectory modification request is granted and the first aircraft is notified of the first trajectory modification request being granted. Alternatively, if a conflict is identified, the first trajectory modification request is not granted and the first aircraft is notified thereof. If the first trajectory modification request was not granted, the first trajectory modification request is placed in a queue, which is periodically processed to perform subsequent conflict assessments.
A trajectory-based sense-and-avoid system (168) for use on an aircraft (100) is provided that utilizes 4-D constructs (166, 192), such as 4-D trajectories or 4-D polytopes, to maintain separation from other aircraft (118) and/or to avoid collisions with other aircraft (118). In certain embodiments the trajectory-based sense-and-avoid system (168) utilizes 4-D trajectories provided from an external source and/or 4-D trajectories estimated based on a variety of data sources during operation.
Embodiments of the present invention provide a prognostics and health management (PHM) system for one or more electronic, electro-mechanical, pneudraulic and mechanical devices (35A-35F) of an aircraft, and associated diagnostic methods (80) and computer program products (90). The system includes a tangible and non-transitory memory preloaded with prognostics and health management signature data (60); one or more sensors (33) that are adapted to monitor the one or more devices (35A-35F); and a logic device (50) adapted to calculate an address and to access the tangible and non-transitory memory using the calculated address in real time. One or more portions of the calculated address are responsive to one or more parameter values associated with the sensors (33) so that sensor parameter data determines the address into the memory. In the PHM system, the logic device (50) is further adapted to generate a PHM alert (52) in real time responsive to a value of the PHM signature data accessed at the address.
G01R 31/00 - Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
59.
SYSTEMS AND METHODS FOR BUOYANCY MANAGEMENT IN AN AIRSHIP
An airship comprising a hull configured to be inflated with a first gas, a ballonet in the hull, the ballonet configured to be inflated with a second gas that is heavier than the first gas; a fan configured to draw the second gas into the ballonet; an inflatable landing system; a duct configured in the ballonet to allow access to components in the airship, and a valve coupled to the ballonet. The valve provides a pathway for air to flow between the ballonet and a plenum chamber, the plenum chamber is formed by the airship, a landing surface, and the inflatable landing system when the inflatable landing system is in contact with the landing surface.
An airship comprising a hull configured to be inflated with a first gas; a ballonet in the hull, the ballonet configured to be inflated with a second gas that is heavier than the first gas; a fan configured to draw the second gas into the ballonet; an inflatable landing system; a duct configured in the ballonet to allow access to components in the airship; and a valve coupled to the ballonet. The valve provides a pathway for air to flow between the ballonet and a plenum chamber, the plenum chamber is formed by the airship, a landing surface, and the inflatable landing system when the inflatable landing system is in contact with the landing surface.
An airship recovery system is disclosed including a first cushion pad configured to create a suction force on an outer portion of the airship to capture the airship during landing. An arm is coupled to the first cushion pad and movable between at least two different vertical positions. In an embodiment the air is movable in multiple degrees of freedom. An actuator device is coupled to move the arm. A sensor device is incorporated to detect the location of the airship relative to the recovery system. A controller is utilized to receive signals from the sensor device regarding the location of the airship and output command signals to the actuator to move the arm and the first cushion pad toward a desired contact location on the airship.
A drill countersinking and seal groove machining tool to accommodate an accurate drill countersinking and seal groove machining operation. The linear compensator tool applies sufficient force to react to the drilling or seal groove machining process, but not so much force as to distort the work piece being drilled or machined. The tool ensures that the reactant force does not exceed the machine force override allowances. Varying spring rates and/or air pressures on the linear compensator system will accommodate most applications. The tool absorbs over travel of the machining tool, in order to ensure that the surface to be machined is always in contact with the machining tool.
The invention relates to carbon nanotube arrays and methods for the preparation of carbon nanotube arrays. The carbon nanotube arrays include an aligned carbon nanotube array, wherein at least one of the ends of the carbon nanotube array includes a coating layer that is infused into the carbon nanotube array.
C23C 30/00 - Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
H01L 21/768 - Applying interconnections to be used for carrying current between separate components within a device
H01L 23/532 - Arrangements for conducting electric current within the device in operation from one component to another including external interconnections consisting of a multilayer structure of conductive and insulating layers inseparably formed on the semiconductor body characterised by the materials
65.
INERTIAL MEASUREMENT WITH AN IMAGING SENSOR AND A DIGITIZED MAP
The present invention relates to a system and method for determining vehicle attitude and position from image data detected by sensors in a vehicle. The invention uses calculated differences between the locations of selected features in an image plane and the location of corresponding features in a terrain map to determine the attitude of the vehicle carrying the sensors with respect to a ground frame of reference.
A hybrid air vehicle is disclosed in which a cover is provided for a plurality of air cushioned landing pads to reduce drag when airborne. The pad is inflatable to provide an air cushioned during touchdown and deflatable during flight of the air vehicle. The cover can include a first cover portion and a second cover portion. A first cover roller of the first cover portion and a matching second cover roller of the second cover portion abut to cover the corresponding pad. The first cover roller and the second cover roller, which are separate and free from a physical linkage there between, are separable in an eyelid fashion to expose the corresponding pad. A separation gap between the first cover roller and the second cover roller is increased or decreased by roller straps to cover or expose the corresponding pad.
An apparatus comprising a power take-off shaft includes an outer shaft and an inner shaft. The outer shaft includes an outer periphery and an inner periphery. The inner shaft includes an outer periphery and an inner periphery. A notch is configured around at least a portion of the outer periphery of the inner shaft, and a self-lubricating material is disposed on at least a portion of the notch.
F02B 67/00 - Engines characterised by the arrangement of auxiliary apparatus not being otherwise provided for, e.g. the apparatus having different functions; Driving auxiliary apparatus from engines, not otherwise provided for
F16N 7/40 - Arrangements for supplying oil or unspecified lubricant from a stationary reservoir or the equivalent in or on the machine or member to be lubricated with a separate pump; Central lubrication systems in a closed circulation system
68.
HOLLOW CORE WAVEGUIDE FOR LASER GENERATION OF ULTRASONIC WAVES
A laser transmission system for an ultrasonic workpiece detection system operating in the wavelength range be-tween 3um and 5um. The system comprises a source (102) coupled via a first lens assembly (104) and first hollow core waveguide to an optical fibre (108). The system optical exit comprises a further hollow core waveguide (110) coupling the optical fibre to an exit lens assembly (112).
A system (30), program product (39), and method to perform automated three- dimensional image registration of a part (43) within an inspection cell (49), are provided. The system (30) can include a laser-ultrasound inspection device (31) having a scanning head (61) to generate ultrasonic surface displacements in a part (43), an inspection laser (55), and an interferometer (59) to collect phase modulated light reflected by the part (43). The system (30) can also include a part position locator (33) positioned to measure a distance between points on a surface of the part (43) and a scanning laser reference location. The system (30) can also include a database (45) containing computer-aided design models (41) for each part (43) of interest, and a model (47) of the inspection cell (49). The system (30) can further include a laser ultrasound inspection computer (35) communication with the laser-ultrasound inspection device (31) and the part position locator (33), and laser ultrasound inspection program product (39) adapted to perform automated three-dimensional image registration of the part (43).
An ultrasonic non-destructive evaluation (NDE) system operable to inspect target materials is provided. This ultrasonic NDE system includes an articulated robot, an ultrasound inspection head, a processing module, and a control module. The ultrasound inspection head couples to or mounts on the articulated robot. The ultrasound inspection head is operable to deliver a generation laser beam, a detection laser beam, and collect phase modulated light scattered by the target materials. The processing module processes the phase modulated light and produces information about the internal structure of the target materials. The control module directs the articulated robot to position the ultrasound inspection head according to a predetermined scan plan.
G01N 29/22 - Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object - Details
An apparatus, program product, and related methods for gravity stabilizing a suspended load are provided. The apparatus includes an center of gravity stabilized automated adjusting load bar in communication with a mobile cart which allows an operator to enable automated stabilization of a load. The adjusting load bar includes redundant first and second control and drive systems. A third control system can both monitor sensed data and the movement commands of first and second control systems, and can monitor the resulting physical movements. If a movement command and the resulting movement does not match or if there is an out of tolerance mismatch between movement commands of the first and the second control systems, the third control system can automatically detect this condition and shift into an emergency stop condition.
A system, method, and apparatus for the rigid alignment of drill bits with ergonomic drill motors is disclosed. An adjustable nosepiece adapter is mounted to the ergonomic drill motor adjacent the drill bit chuck. The adapter has a split clamp portion on its distal end for receiving a pressure foot. A guide bushing fits in the proximal end of the pressure foot. A coil spring is located in the pressure foot and allows the guide bushing to telescope within the pressure foot. The drill bit extends through the guide bushing, pressure foot, and adapter and is secured to the chuck. The distal end of the guide bushing fits closely within a hole in a template that is secured to the workpiece to provide holes that are more accurately formed in the workpiece.
B23B 45/14 - Means for holding or guiding the drilling device or for securing it to the work; Thrust stands
B23B 49/00 - Measuring or gauging equipment on boring machines for positioning or guiding the drill; Devices for indicating failure of drills during boring; Centring devices for holes to be bored
Embodiments of the present invention relates to an improved laser for the optical detection of ultrasound. The primary task of this "first" detection laser is to illuminate the spot where a "second" laser is used to generate ultrasound in the part under test. The scattered light from the first laser is collected and analyzed with an interferometer to demodulate the surface vibrations caused by the return echoes of the ultrasound at the surface of the part. The improved detection laser (first laser) is constructed using a diode- pumped fiber laser to produce a high power single -frequency laser source.
A sensor system and method comprising employing a window comprising a material with a bulk resistivity that is substantially uniform throughout the window and sensing electromagnetic radiation through the window.
patents
