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.
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 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
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 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.
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 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 communications; Network 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
16.
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
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
H04B 10/118 - Arrangements specific to free-space transmission, i.e. transmission through air or vacuum specially adapted for satellite communication
A system includes an optical source configured to generate an optical signal and illuminate a scene with the optical signal. A first spatial pattern generator comprising pixel elements is configured to form a mask, using the pixel elements, to mask a reflection of the optical signal received from the scene. A pattern controller is coupled to the first spatial pattern generator and configured to control the pixel elements individually to form the mask, and a detector is configured to measure an amplitude of the masked reflection of the optical signal. A digitizer is coupled to the detector and configured to digitize the measured amplitude into an amplitude value. A processor coupled to the pattern controller and the digitizer is configured to instruct the first pattern controller to form a first sequence of masks to sequentially mask reflections of the optical signal using the spatial pattern generator, store the amplitude value corresponding to the measured amplitude of the masked reflection of the optical signal for each mask in the first sequence of masks, and recover an array of signals from the scene based on the stored amplitude values and the first sequence of masks, wherein a number of the stored amplitude values and a number of masks in the first sequence of masks is less than a number of signals of the array of signals.
A septum orthomode transducer polarizer (SPOL) is presented comprising sidewall ridges which increase bandwidth in the presence of draft angles for injection molding manufacturing techniques. A SPOL with sidewall ridges is able to accommodate draft angles for injection molding while creating greater modal separation within the SPOL and increasing the resultant bandwidth. A horn aperture may be included with the SPOL, and the combined structure may be injection molded as a single part to realize significant cost and mass reductions.
A reflector antenna includes a reflector having a curved reflecting surface that extends around a longitudinal center axis, wherein the curved reflecting surface is defined by rotating a concave curve around the longitudinal center axis and wherein one end of the concave curve defines an apex on the longitudinal center axis. The reflector antenna may further include a ground plane extension having a flat reflecting surface abutting an edge of the reflector and extending radially away from the longitudinal center axis. A phased array feed may be arranged spaced apart from and opposite to the reflecting surfaces of the reflector and the ground plane extension. A tapered collar may be arranged adjacent to the phased array feed, wherein the tapered collar tapers outward away from the phased array feed and towards the reflector, and wherein the tapered collar comprises an inner reflective surface facing the reflector.
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 19/10 - 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
A propeller system for a tail section of an aircraft includes a propeller hub located at the tail section of the aircraft, a plurality of propeller blades mounted to and extending outwardly from the propeller hub, a propeller shaft coupled to the propeller hub and operable to rotate the propeller hub about an axis of rotation, and a propeller gearbox connected to the propeller shaft. The propeller gearbox is fluidly cooled by an airflow within the tail section. A spinner assembly surrounds the propeller hub. The spinner assembly includes at least one outlet opening formed therein downstream from the propeller hub relative to the airflow. The spinner assembly is rotatable to draw the airflow into at least one cooling flow inlet formed in the tail section and across the propeller gearbox to cool the propeller gearbox and out the at least one outlet opening.
A method for controlling a rotary wing aircraft includes determining a measured airspeed of the rotary wing aircraft based on data from a pitot probe, determining an estimated airspeed of the rotary wing aircraft based on rotor control commands, and determining a blended airspeed based on both the measured airspeed and the estimated airspeed.
G01P 5/16 - Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring differences of pressure in the fluid using Pitot tubes
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
A heterodyne phase-controlled beam-combiner system includes a laser source, a first beam splitter, a plurality of phase modulators, a tiled array and an optical mixer. The laser source generates a light beam, and the first beam splitter splits the light beam into multiple beamlets. A phase modulator tags each beamlet with an arbitrary phase dither signal corresponding to an arbitrary phase setpoint or offset, and a tiled array, including a number of lenslets, combines the tagged beamlets and directs the combined light to a second beam splitter. The optical mixer generates a heterodyne light including tagging information. A first output light of the second beam splitter is a target light directed to a target, and the arbitrary phase offset enables achieving a nonflat phase profile for beamlets to obtain the desired on-axis far-field intensity of the target light.
G02F 1/01 - Devices or arrangements for the control of the intensity, colour, phase, polarisation or direction of light arriving from an independent light source, e.g. switching, gating or modulating; Non-linear optics for the control of the intensity, phase, polarisation or colour
Methods and systems for implementing a Jupiter aerospace mission can enable delivery of a science payload to a Jupiter orbit on a direct Earth-to-Jupiter trajectory. Solar power and use of avionics also allow a fast assembly, integration, and test process compared to past outer Solar System missions. The spacecraft can include an aerodynamic forebody, a shell, and a thermal protection system. The spacecraft can manage the radiation environment, generate solar power, and return data to Earth with a robust radio-frequency (RF) amplification and antenna gain.
A joint system including a support device with a plurality of radial extensions extending in at least a first direction from the support device, each individual radial extension of the plurality of radial extensions terminating at a distal engagement end and a receiving device separate from the support device with a notch area to receive the distal engagement ends of each radial extension of the plurality of radial extensions and a contact area upon which a length of the radial extensions of the plurality of radial extensions engage when the distal engagement end of each radial extension of the plurality of radial extensions are engaged within the notch area. At least one radial extension of the plurality of radial extensions is configured to be flexible between a first position to provide for at least one of assembly and disassembly of the support device to the receiving device and a second position when the support device and the receiving device are assembled. Another system and method are also disclosed.
F16B 17/00 - Fastening means without screw-thread for connecting constructional elements or machine parts by a part of or on one member entering a hole in the other
F42B 15/36 - Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means
26.
MONOLITHIC ATTITUDE CONTROL MOTOR FRAME AND SYSTEM
A monolithic attitude control motor frame includes a monolithic structure including an outer surface of revolution and a plurality of side walls defining a plurality of cavities extending radially from the outer surface of revolution. Adjacent cavities of the plurality of cavities share a side wall or side wall portion therebetween. Each of the cavities is configured to receive an attitude control motor. A monolithic attitude control motor system includes a monolithic frame including an outer surface of revolution and a plurality of side walls defining a plurality of cavities extending radially from the outer surface of revolution. The system further includes a plurality of attitude control motors corresponding to the plurality of cavities, such that an attitude control motor of the plurality of attitude control motors is disposed in each cavity of the plurality of cavities.
Ray-tracing for terrain mapping is provided. A system of an aerial vehicle can identify points generated from data captured by a sensor of the aerial vehicle. The points can each indicate a respective altitude value of a portion of terrain. The system can determine, based on the altitude values of the points, a threshold altitude of the terrain, and can identify a boundary defined in part based on the threshold altitude of the terrain. The system can generate a terrain map for the terrain based on applying a ray-tracing process to the points. The ray-tracing process can be performed within the boundary, using the points as respective sources and the aerial vehicle as a destination. The system can present a graphical representation of the terrain map in a graphical user interface of the aerial vehicle.
Real-time light-detection and ranging point decimation is provided. A system of a vehicle can allocate, based on a resolution for data points, a region in the memory for a tree data structure. The region can have a fixed-size for a duration of a flight performed by the vehicle. The system can receive, subsequent to allocating the region in the memory, first points captured by a sensor of the vehicle at a first resolution, and convert the points to second points having a second resolution that is less than the first resolution. The system can then provide, for storage in the region in the memory, the tree data structure that stores the second points. The tree data structure can be used in a terrain map generation function.
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.
H05K 9/00 - Screening of apparatus or components against electric or magnetic fields
30.
Method, system and computer-readable storage medium for conducting on-demand human performance assessments using unstructured data from multiple sources
Embodiments include a method and system for conducting human performance assessment comprising memory devices for accessing and storing historical data from multiple sources of unstructured and structured assessment source data for a subject. The unstructured assessment source data includes free-form source data. The system includes a computing system with a user interface presented on a digital display device to enter assessment query (AQ) relating to the subject. The system includes a natural language processing engine to process an unstructured data search model based on the AQ and a semantic reasoner engine to apply unstructured and structured data search model to the assessment domain ontology for the subject to measure human performance and at the same time identify performance gaps. The system includes an assessment report generator to generate a report of the performance and gap assessments wherein the report is configured to be displayed on the display device.
A rotor assembly including a fixed fairing including an interface portion and a hub fairing including a depression. The depression is configured to receive at least a portion of the interface portion. The hub fairing is rotatable relative to the fixed fairing.
Systems and methods for automatically controlling landing gear responsive to detected aerial vehicle conditions. A system can receive, from one or more sensors of the aerial vehicle, altitude information and speed information of the aerial vehicle. The system can determine to lower landing gear of the aerial vehicle based on a change in a state of the aerial vehicle, and identify a condition corresponding to a type of the aerial vehicle and the state of the aerial vehicle. The system can compare the speed information and the altitude information to the condition to determine that a condition to lower landing gear is satisfied. Responsive to determining that the condition to lower the landing gear is satisfied, the system can provide a signal to lower the landing gear.
A self-aligning connector assembly includes a connector frame, a connector, and an alignment adapter. The connector frame includes an end plate. The connector extends from the connector frame and is configured to engage with a mating connector. The alignment adapter is coupled to the connector. The alignment adapter is movable between a first position and a second position. In the first position, the alignment adapter is spaced apart from the end plate and permits the connector to move relative to the connector frame. In the second position, the alignment adapter is engaged against the end plate and prevents movement of the connector relative to the connector frame.
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
H01R 13/642 - Means for preventing, inhibiting or avoiding incorrect coupling by position or shape of contact members
Systems and methods for transitioning between rotor positions based on detected parameters of an aircraft. One embodiment provides an aircraft comprising a rotor assembly and a controller. The controller is configured to monitor an operating characteristic of the aircraft. The controller is configured to select, in response to a rotor neutral state of the aircraft being enabled, one of a plurality of rotor neutral positions based on the operating characteristic, the plurality of rotor neutral positions including a first rotor neutral position configured for vertical takeoff of the aircraft and a second rotor neutral position configured for start-up and shutdown of the aircraft. The controller is configured to set the selected one of the plurality of rotor neutral positions as the rotor neutral position for the aircraft.
B64C 27/57 - 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 automatic or condition responsive, e.g. responsive to rotor speed, torque or thrust
35.
Outdoor entity and weapon tracking and orientation
Systems and methods for tracking entities and objects in an environment can include an entity-mounted instrumentation (EMI) and an object-mounted instrumentation (OMI). The OMI can include a first IMU array to detect the object orientation, and a TOF pulse transmitter to transmit a TOF pulse. The EMI can include a second IMU array to detect the entity orientation, a GPS receiver, and an array of TOF sensors to receive various versions of the TOF pulse. The EMI can determine a location and orientation of the entity using GPS data and orientation data generated by the second IMU array. The EMI can determine a relative location of the object using the various versions of the TOF pulse, and can determine a location of the object using the relative location of the object and the location of the entity. The EMI can determine the object orientation using data provided by the first IMU array.
G01S 19/48 - Determining position by combining or switching between position solutions derived from the satellite radio beacon positioning system and position solutions derived from a further system
G01S 19/43 - Determining position using long or short baseline interferometry
G01S 7/00 - RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES - Details of systems according to groups , ,
Systems and methods for communication in 4G and 5G broadband satellite networks are provided. The disclosed methods include Global Navigation Satellite System (GNSS)-independent methods, and GNSS assisted methods that do not require transmission of satellite ephemeris information from a base station to user equipment.
H04W 74/08 - Non-scheduled access, e.g. random access, ALOHA or CSMA [Carrier Sense Multiple Access]
H04W 74/00 - Wireless channel access, e.g. scheduled or random access
G01S 19/27 - Acquisition or tracking of signals transmitted by the system creating, predicting or correcting ephemeris or almanac data within the receiver
According to some embodiments, a method of nonlinear RF beamforming includes receiving a reference RF signal and computing linear beamformed signals. The method further includes determining a frequency content for each of the plurality of linear beamformed signals, determining a reduced subset of linear beamformed signals, and computing a minimum element-wise magnitude across the reduced subset of linear beamformed signals. The method further includes computing a FFT of a reference channel signal, computing an amplitude mask ratio between the minimum element-wise magnitude and the FFT of the reference channel signal, and applying a learned polynomial response to the amplitude mask ratio to create a modified amplitude mask. The method further includes applying the modified amplitude mask to the FFT of the reference channel signal to create a masked frequency response of the reference channel signal and computing an inverse FFT in order to generate a final beamformed signal.
H01Q 3/36 - 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 distribution of energy across a radiating aperture varying the phase by electrical means with variable phase-shifters
In one embodiment, systems and methods include using an ultrasonic cutter in a ground detection system to prevent damage to a substrate. The method of detecting a substrate comprises attaching a workpiece clamp to the substrate. The method further comprises cutting a layer of coating disposed on the substrate with an ultrasonic cutter, wherein the ultrasonic cutter operates at a frequency of about 20 kHz to about 40 kHz, wherein the layer of coating is non-conductive. The method further comprises contacting the substrate with the ultrasonic cutter.
A handheld device and method for entering data and controlling functions of an aerial vehicle are disclosed. The handheld device includes an interface that communicates with a processor and a memory of the aerial vehicle; input devices that receive input from an operator of the handheld device, a display device that displays information related to the input received from the operator via the input devices, and one or more processors. The one or more processors can receive input data from the input devices to modify a field value maintained in the memory of the aerial vehicle. The one or more processors can present, at the display device, an output data corresponding to the input data, and periodically transmit one or more signals to modify the field value maintained in the memory of the aerial vehicle via the interface based on the input data.
G05D 1/00 - Control of position, course, altitude, or attitude of land, water, air, or space vehicles, e.g. automatic pilot
G05D 1/10 - Simultaneous control of position or course in three dimensions
G06F 3/0362 - Pointing devices displaced or positioned by the user; Accessories therefor with detection of 1D translations or rotations of an operating part of the device, e.g. scroll wheels, sliders, knobs, rollers or belts
G06F 3/0482 - Interaction with lists of selectable items, e.g. menus
B64C 39/02 - Aircraft not otherwise provided for characterised by special use
40.
INLET SYSTEM WITH AN INBOARD DRAIN ASSEMBLY FOR A ROTORCRAFT ENGINE
A drain assembly includes a drain tube and a flapper assembly. The drain tube extends between a first tube end and a second tube end. The first tube end is configured to fluidly attach to an inlet plenum assembly of an engine system of a rotorcraft. The flapper assembly is positioned along the second tube end and comprises a flapper door that is configured to allow fluid to drain from the drain assembly to an engine compartment of the engine system of the rotorcraft. The flapper door is configured to prevent fluid, engine compartment gases, or flame from flowing into the drain assembly through the second tube end of the drain tube.
Provided herein are various improvements to optical-inertial stabilization systems, such as those employed on electro-optical systems that receive or emit optical energy. In one example, a system includes an optical reference element rigidly coupled to a primary mirror. The optical reference element propagates a reference signal through optic elements that form at least a portion of an optical path corresponding to the primary mirror. A measurement of the reference signal is made after propagation through the optic elements to determine errors associated with the optical path. The system can also include inertial sensors rigidly coupled to the primary mirror and optical reference element to form an assembly. The inertial sensors are configured to measure inertial rotation of the assembly. Rotational adjustments about two axes can be produced for the assembly based at least on the inertial rotation properties to correct for disturbance or drift.
G02B 26/08 - Optical devices or arrangements for the control of light using movable or deformable optical elements for controlling the direction of light
A rotor blade assembly for a rotary wing aircraft includes a main rotor blade body comprising an upper blade skin, a lower blade skin, an inboard end, an outboard end, and a trailing edge. The rotor blade assembly further includes a trailing edge actuator assembly. The trailing edge actuator assembly includes an upper actuator skin and a lower actuator skin defining a cavity and a trailing edge flap, a control panel disposed in the cavity and coupled to one of the upper actuator skin or the lower actuator skin and one or more actuators disposed in the cavity and configured to apply force to the control panel to cause the trailing edge flap to deflect. The trailing edge actuator assembly is coupled to the trailing edge of the main rotor blade body.
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
B64C 27/57 - 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 automatic or condition responsive, e.g. responsive to rotor speed, torque or thrust
A rotary wing aircraft includes a single main rotor hub configured to receive a rotor blade. The rotor blade includes a blade root, a blade tip, and a blade body. The blade body includes a leading edge and a trailing edge and defines a feathering axis. The leading edge and the trailing edge each include a first portion and a second portion that extend toward a first direction and a second portion, respectively. At a given radial location along the feathering axis, a local twist angle changes from a positive value to a negative value, a chord length decreases in value, a distance between the trailing edge and the feathering axis decreases in value, and the first portion of the leading edge extends toward the first direction. The rotor blade assembly also includes a trailing edge assembly having a trailing edge flap configured to be selectively deployed by an actuator.
An apparatus for securing first and second skins to a core in a composite rotor blade includes an elongated member configured to be installed through a passage in the core of the composite rotor blade. The elongated member has a first end configured to be attached to an outer surface of the first skin and a second end configured to be attached to an outer surface of the second skin. The apparatus also includes a first patch configured to adhere the first end to the outer surface of the first skin, and a second patch configured to adhere the second end to the outer surface of the second skin such the elongated member extends from the outer surfaces of the first and second skins through the passage in the core.
B29C 70/02 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising combinations of reinforcements and fillers incorporated in matrix material, forming one or more layers, with or without non-reinforced or non-filled layers
B29C 70/68 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers
B29D 99/00 - Subject matter not provided for in other groups of this subclass
45.
Additive friction stir deposition system for refractory metals
An additive friction stir deposition system for refractory metals is disclosed herein. The additive friction stir deposition system includes a tool assembly and an induction element. The tool assembly includes a metal shaft defining a shaft central channel, and a ceramic tip defining a tip central channel. The metal shaft and the ceramic tip are configured to interlock to prevent relative rotation therebetween. The induction element is positioned adjacent to the ceramic tip. As a refractory metal feedstock is fed through the shaft central channel and the tip central channel, the induction element heats the portion of the refractory metal feedstock within the tip central channel, but does not heat the ceramic tip itself. Accordingly, the refractory metal feedstock can be heated prior to application to a workpiece without heating the tip of the tool assembly, improving performance of the additive friction stir deposition system and the resulting workpiece.
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 friction; Friction welding
B33Y 30/00 - ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING - Details thereof or accessories therefor
Enhanced components and assemblies for microwave radio frequency (RF) antenna feed systems are provided. One example includes radiating probes that propagate RF signals to intermediate waveguides that feed polarizers or filters associated with horn antenna elements. The radiating probes can couple to corresponding transmit/receive circuitry using coaxial link elements. The radiating probes comprise tunable components which can be shaped/sized to produce desired output characteristics (e.g., frequency ranges and gain properties). Many radiating probes can be integrated into a cover plate assembly that feeds an array of horn antennas. Interface elements with integrated waveguides can provide RF sealing between radiating probes and provide radiative coupling from radiating probes to corresponding waveguides that feed the array of horn antennas.
A method of manufacturing a thin film optical apparatus includes providing a substrate and applying an alignment layer over the substrate. The alignment layer ranges from about 50 to 100 nm in thickness. The method includes imprinting a hologram with a desired optic pattern onto the alignment layer and applying at least one layer of mesogen material over the alignment layer.
A rotor blade assembly includes a rotor blade having inboard and outboard regions, a blade body, and an internal spar, the blade body defining leading and trailing edges. A trailing edge assembly extends from and is connected to the trailing edge, and has a trailing edge flap and an actuator configured to deploy the trailing edge flap between first and second positions. In one of the first and second positions, an upper surface of the trailing edge flap conforms in profile to an upper surface of the rotor blade, and in the other, the trailing edge flap is inclined relative to the blade. During hovering flight, at least one trailing edge flap segment is deflected to enhance hover performance. During forward flight, at least one trailing edge flap segment is either not deflected for reduced effect on forward flight or is deflected for additional thrust.
A deployment system for a spacecraft may include a fitting for coupling a deployable device to the spacecraft, and a moment bearing shear ball assembly. The moment bearing shear ball assembly may include a shear ball engaged within the fitting, and a moment collar mounted onto the shear ball. The moment collar may have a planar surface engaged with a planar surface of the fitting. A separation interface may be defined between at least one of (1) mating surfaces of the fitting and the shear ball and (2) mating surfaces of the fitting and the moment collar. Engagement of the shear ball within the fitting constrains shear forces in at least two axes and axial forces in at least a third axis. Engagement of the moment collar with the shear ball and the fitting constrains overturning moments of the shear ball about at least two axes, and axial forces in at least a third axis.
An aircraft includes an airframe, and a coaxial main rotor assembly including a static mast and an upper rotor assembly and a lower rotor assembly rotatable about a main rotor axis defined by the static mast. The upper rotor assembly and the lower rotor assembly are independently rotatable about the static mast. A propulsion system includes at least one propulsion source for directly driving at least one of the upper rotor assembly and the lower rotor assembly and a flight control system is operably coupled to the propulsion system. The flight control system is operable to independently control a rotational speed of the upper rotor assembly and the lower rotor assembly relative to the static mast.
Systems and methods for alerting reverse current conditions of vehicle charging systems. One embodiment provides an aircraft power system comprising an aircraft power source and a notification device. The notification device includes a control unit configured to monitor a supply of current from an external power supply to the aircraft power source and detect a reverse current condition of current flowing from the aircraft power source to the external power supply. In response to detecting the reverse current condition, the control unit is configured to provide a notification indicative of the reverse current condition
This disclosure relates to apparatuses, systems, and methods for controlling an aircraft. A computing system may identify a first command signal received via a flight control at a time point to control navigation of the aircraft through an environment. The computing system may attenuate the first command signal using a fade function over a time window relative to the time point to generate a second command signal. The computing system may input the second command signal to a model to generate predicted paths for the aircraft through the environment over the time window. The computing system may determine that at least one predicted path intersects with an obstacle in the environment during the time window. The computing system may generate a location to which to navigate the aircraft to avoid the obstacle. The computing system may perform an action to direct the aircraft to the location.
A rotary blade aircraft includes an airframe, a rotor shaft driven about a rotor axis, and a plurality of rotor blades driven by the rotor shaft about the rotor axis. The rotary blade aircraft includes a swashplate assembly coupled to the plurality of rotor blades. The swashplate assembly is operable to move the plurality of rotor blades about a respective longitudinal axis. The rotary blade aircraft includes a hydraulic control servo coupled between the airframe and the swashplate assembly. The hydraulic control servo is operable to move the swashplate assembly relative to the rotor axis. The rotary blade aircraft includes a harmonic control actuator coupled between the airframe and the swashplate assembly. The harmonic control actuator is operable independently relative to the hydraulic control servo to move the swashplate assembly relative to the rotor axis to reduce vibration at selected frequencies in the airframe.
B63H 5/08 - Arrangements on vessels of propulsion elements directly acting on water of propellers of more than one propeller
B64C 27/605 - Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical including swash plate, spider or cam mechanisms
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
F16H 1/32 - Toothed gearings for conveying rotary motion with gears having orbital motion in which the central axis of the gearing lies inside the periphery of an orbital gear
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 15/16 - Reflecting surfaces; Equivalent structures curved in two dimensions, e.g. paraboloidal
H01Q 3/14 - 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 the relative position of primary active element and a refracting or diffracting device
H01Q 5/35 - Individual or coupled radiating elements, each element being fed in an unspecified way for different propagation modes using two or more simultaneously fed points
H01Q 15/18 - Reflecting surfaces; Equivalent structures comprising plurality of mutually inclined plane surfaces, e.g. corner reflector
H01Q 3/26 - 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 distribution of energy across a radiating aperture
55.
Separable self-aligning waveguide connector using a ball detent assembly having ball elements engaged with mating divots
Provided herein are various examples of separable waveguide couplers. In one example, a collar element is provided to surround a member comprising a faying surface, a waveguide conduit, and alignment protrusions arranged radially about a perimeter of the faying surface, where the collar element is configured to accept insertion of a mating member comprising a mating faying surface and a mating waveguide conduit. A ball detent assembly is provided having a spring element that retains ball elements in holes formed through the collar element. The waveguide conduit and the mating waveguide conduit are configured to be aligned radially by at least engagement of the alignment protrusions with alignment channels in the mating member and restrained axially by at least engagement of the ball elements with mating divots in the mating member.
An optical system can include a mirror that reflects incoming light to a sensor for detection. The position and/or orientation of the mirror can be controlled to reflect incoming light from different locations and/or directions. Position and/or orientation of the mirror may be tracked and/or detected by an optical position sensor. The position sensor can transmit a beam to a reflector on the mirror, and the reflected beam can be received by the position sensor. Characteristics of the reflected beam can be measured to determine the position and/or orientation of the mirror. For example, the beam can be used for interferometric and/or intensity measurements, which can then be correlated with a position and/or orientation of the mirror.
G01B 9/02015 - Interferometers characterised by the beam path configuration
G01B 9/02003 - Interferometers characterised by controlling or generating intrinsic radiation properties using two or more frequencies using beat frequencies
A boresighting mechanism for adjusting an armament of an aircraft. The mechanism includes a housing comprising a proximal end, a distal end, and an inner cavity. The mechanism further includes a jackscrew with a threaded portion disposed in the inner cavity and an unthreaded portion extending from the proximal end of the housing. The mechanism further includes a follower threadedly coupled to the jackscrew at a first end within the inner cavity and extending from the distal end of the housing. The follower is configured to be coupled to an adjustment feature of the armament at a second end. The mechanism further includes an adjustment knob coupled to the unthreaded portion of the jackscrew and configured to rotate the jackscrew to thereby cause linear motion of the follower. The linear motion allows for adjustment of the armament via the adjustment feature.
An aircraft includes a main body having an empennage, a main rotor assembly mounted on the main body, and a movable control surface assembly supported on the empennage. The movable control surface assembly includes a tube extending from the empennage along a tube axis to a free end, the tube being supported for rotation about the tube axis with respect to the empennage, and a movable control surface mounted on the tube for rotation therewith. The movable control surface is supported on the tube by a connection element that couples the movable control surface to the free end of the tube to rotatably fix the movable control surface with respect to the tube.
A feed network is provided that includes a transmit section, a body section coupled to the transmit section, and a receive section coupled to the body section. The transmit section and the body section form a transmitter unit coupled to a first section of a core waveguide, wherein the first section of the core waveguide is a square waveguide. The body section and the receive section form a receiver unit coupled to a second section of the core waveguide, wherein the second section of the core waveguide is a circular waveguide.
According to an aspect, a method of assembling a mandrel includes assembling a plurality of members via interlocking features arranged at opposing edges of each member of the plurality of members to form a compartment, the assembled members having a collective outer surface that conforms to an inner surface of the spar. A support member is inserted into the compartment formed radially inward from the assembled members, the support member making contact with a portion of each member of the plurality of members.
B29C 33/48 - SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING - Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles with means for collapsing or disassembling
A rotor blade retention assembly is configured to connect a rotor blade to a central hub comprising a hub arm coupled to and extending radially outward from a hub bowl. The hub arm includes a hub arm lug. The rotor blade retention assembly includes a tension-torsion strap with an inboard end and an outboard end, the inboard end including an inboard pin hole and the outboard end including an outboard pin hole. The rotor blade retention assembly further includes an inboard blade pin and an outboard blade pin. The inboard blade pin is configured to extend through the hub arm lug and the inboard pin hole and to couple the inboard end of the tension-torsion strap to the hub arm. The outboard blade pin is configured to extend through a blade lug of a rotor blade and the outboard pin hole and to couple the outboard end of the tension-torsion strap to the rotor blade.
Systems and methods for power and data distribution on an aircraft. One embodiment provides an aircraft comprising a plurality of nodes, a power system controller, and an aircraft controller. Each node is connected to a plurality of LRUs, and each node includes a node controller. The power system controller is configured to control power distribution to each node. The aircraft controller is configured to transmit data to each node and to receive data from each node. The node controller includes an electronic processor and a memory. The node controller is configured to control power to the plurality of LRUs, receive first data from at least one LRU of the plurality of LRUs, and provide the first data to the aircraft controller. The node controller is further configured to receive second data from the aircraft controller and provide the second data to at least one LRU of the plurality of LRUs.
A satellite communication system includes a satellite, satellite base station (eNodeB or gNodeB) and a user equipment (UE). The satellite provides a number of satellite beams, and each satellite beam includes multiple cells. The base station communicates with the UE via a satellite using a narrowband internet of things (NB-IoT) waveform and an enhanced protocol. In particular, the base station and UE perform carrier aggregation by adding and/or deleting carriers in a cell, and the base station and UE perform a higher-order modulation and coding scheme (MCS) processing to support high data rates for user data transport.
H04W 4/80 - Services using short range communication, e.g. near-field communication [NFC], radio-frequency identification [RFID] or low energy communication
H04L 1/00 - Arrangements for detecting or preventing errors in the information received
Systems and methods for controlling an aerial vehicle to avoid obstacles are disclosed. A system can detect, based on a world model generated from sensor data captured by one or more sensors positioned on the aerial vehicle during flight, an obstacle for the aerial vehicle, and trigger an augmented manual control mode responsive to a speed of the aerial vehicle being less than a predetermined threshold and detecting the obstacle. The system can set, responsive to triggering the augmented manual control mode, a speed constraint for the aerial vehicle in a direction of the obstacle based on a distance between the aerial vehicle and the obstacle. The system can receive an instruction to navigate the aerial vehicle in the direction at a second speed, and adjust the instruction to replace the second speed with the speed constraint, causing the aerial vehicle to navigate at the speed constraint.
Distributed gain equalization circuits for use with radio frequency (RF) devices are provided. The distributed gain equalization circuits include a substrate layer, multiple transverse electromagnetic (TEM) line circuits disposed on the substrate layer and multiple traces disposed on the substrate layer, each trace connected to one or more of the TEM line circuits. The traces and TEM line circuits are configured to provide resistances, inductances and capacitances to eliminate the need for lumped or packaged resistors, inductors and capacitors. The distributed gain equalization circuit operates at millimeter wave frequencies and provides a compensating gain slope to counteract a negative gain slope of the RF device. Methods of manufacturing distributed gain equalization circuits are also provided.
A method of operating an aircraft based on movement of a control stick. The method includes creating a deadband of the control stick, where the deadband extends between the central axis and a first angular distance from the central axis, controlling, in response to the control stick being positioned within the deadband, the aircraft according to a first control mode, controlling, in response to the control stick being positioned outside of the deadband, the aircraft according to a second control mode, and adjusting a size of the deadband such that the deadband extends between the central axis and a second angular distance from the central axis.
A super-broadband waveguide feed network includes multiple receive (RX) full reject waveguide filters and multiple RX reject clone waveguide filters disposed in a clone carousel about an aperture port and configured to reject RX frequencies, and a branch line coupler configured to couple the multiple RX full reject waveguide filters and RX reject clone waveguide filters to other components of a waveguide feed network. The super-broadband waveguide feed includes an RX polarizer configured to couple to an end of the aperture port. The super-broadband waveguide feed is configured to be fabricated in one to three pieces composed of a single split plane on the zero-current region, and the super-broadband waveguide feed is circularly polarized.
A cockpit switch device can include a pushbutton switch, a bi-stable relay and a toggle component. The pushbutton switch can be configured to be manually actuated by a user into a command state. The bi-stable relay can be controlled by input commands from the pushbutton switch and input commands from a processor, and can be configured to control operation of one or more systems of an a aircraft. The toggle component can be connected to the pushbutton switch, the processor and the bi-stable relay. The toggle component can receive an input command signal from at least one of the pushbutton switch or the processor, and cause a state of the bi-stable relay to be flipped responsive to the input command signal from the at least one of the pushbutton switch or the processor.
B64D 43/00 - Arrangements or adaptations of instruments
H01H 47/22 - Circuit arrangements not adapted to a particular application of the relay and designed to obtain desired operating characteristics or to provide energising current for supplying energising current for relay coil
A circuit assembly includes a sealable enclosure and at least one electronic circuit element contained within the sealable enclosure. The at least one electronic circuit element includes a control circuit, a garnet, and a first polymer material applied on a surface of the control circuit and on a surface of the garnet. A second polymer material fills a remaining space defined within the enclosure, the second polymer material applied on an exposed surface of the first material.
A method includes identifying a plurality of measured strain gauge values of interest from a plurality of measured strain gauge values. The plurality of measured strain gauge values of interest corresponds to a plurality of temperature values of interest. The method further includes comparing the plurality of measured strain gauge values of interest to a plurality of expected strain gauge values of interest to determine a plurality of strain gauge correction values. The plurality of strain gauge correction values corresponds to the plurality of temperature values of interest. The method further includes correlating the plurality of strain gauge correction values to the plurality of temperature values of interest to determine a correction value-temperature relationship. The method also includes determining a corrected real-time strain gauge value by applying the correction value-temperature relationship to a real-time strain gauge value and a corresponding real-time temperature.
B64F 5/60 - Testing or inspecting aircraft components or systems
G01L 1/22 - Measuring force or stress, in general by making use of electrokinetic cells, i.e. liquid-containing cells wherein an electrical potential is produced or varied upon the application of stress using resistance strain gauges
B64C 9/00 - Adjustable control surfaces or members, e.g. rudders
71.
Rotor assembly connectable to rotor hub and having pitch control
A rotor blade assembly connectable to a rotor hub configured to rotate about a center axis includes a torsional pitch member coupled to the rotor hub, a torque tube coupled to the torsional pitch member, wherein the torsional pitch member extends away from the center axis through a portion of the torque tube, a blade coupled to the torque tube, and a pitch control member coupled to the torque tube and configured to control a pitch angle of the blade, wherein the torsional pitch member includes a first curvilinear channel and a second curvilinear channel each having a front side and a back side, wherein the first curvilinear channel and the second curvilinear channel are disposed adjacent to each other, such that the back side of the first curvilinear channel faces the back side of the second curvilinear channel.
A gear box includes a housing, an actuator coupled to the housing, and a bearing assembly pivotably coupled to the actuator. The bearing assembly including an outer raceway, a cylindrical housing positioned within the outer raceway, and an annular bearing positioned between the outer raceway and the housing. The cylindrical housing has a first end and a second end opposite the first end. A sensor is coupled to the first end of the cylindrical housing and configured to monitor an operating condition of the annular bearing. A linkage couples the actuator to the second end of the cylindrical housing and an output shaft is rotatably coupled to the bearing assembly.
The present disclosure is directed, in certain embodiments, a system for depositing material from a metal feedstock. The system includes a feedstock guide configured to guide a metal feedstock from a material feeder to extend beyond a terminal end of the feedstock guide. The system includes a ceramic collar disposed at the terminal end of the feedstock guide and configured to guide the metal feedstock extending from the terminal end of the feedstock guide to a deposition outlet of the ceramic collar. An induction coil disposed adjacent to the ceramic collar and configured to heat a portion of the metal feedstock within the ceramic collar, such that material of the metal feedstock can be deposited on a surface from the deposition end of the ceramic collar.
B33Y 30/00 - ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING - Details thereof or accessories therefor
B33Y 50/02 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
B33Y 70/00 - Materials specially adapted for additive manufacturing
74.
Housing and method of preparing same using a hybrid casting-additive manufacturing process
The present disclosure is directed, in certain embodiments, a component of a mechanical apparatus. The component includes a cast body with an initial structure formed by a mold and at least one feature deposited on the cast body using a solid state additive manufacturing process, such that in combination the initial structure and the at least one feature form a complete structure of the component.
Provided herein are various enhanced antenna structures for radio frequency communications. In one example, an antenna includes a single-arm spiral antenna having an antenna element configured to couple to a radio frequency link at a central node of the spiral. A ground element is disposed proximate to the central node of the spiral and configured to couple to a ground reference for the radio frequency link.
Multiple collimated laser beams can be arranged in a tightly packed non-overlapping array the goes through a telescope system to reduce the size of the beams and also the separation between the beam centers. The beams in the resulting smaller array then diverge until they reach a nonlinear lens, which collimates each of the beams individually so that all of the beams are collimated, pointing in the same direction and overlapping. The pulses in the beams are temporally separated from each other such that the nonlinear lens acts as a different lens for each of the beams. Such an arrangement facilitates scaling the far field average intensity by combining multiple temporally interleaved pulsed laser beams, allowing diverging pulsed laser beams to be collimated individually by utilizing the large nonlinear refractive index of certain materials.
An aircraft pilot incapacitation detection system includes a controller configured to determine, based on an input received from a flight control computer, a current flight parameter. The controller compares the current flight parameter to a corresponding predetermined flight metric associated with at least one of a predetermined flight plan or a benchmark for a predetermined flight stage. The controller determines, responsive to the comparison, that the aircraft is in an abnormal state and causes a first prompt by a user interface in communication with the controller, the first prompt being associated with a first time threshold. The controller determines whether the first time threshold is satisfied and, if so, subsequently initiates an emergency protocol and causes a second prompt associated with a second time threshold. Upon determining that the second time threshold has been satisfied, the controller carries out the emergency protocol.
Provided herein are various enhancements to spacecraft or other vehicles, including spacecraft docking mechanisms and vehicle mating systems. In one example, a vehicle mating mechanism includes a latch assembly of a vehicle having soft capture elements and hard capture elements. The soft capture elements accept a bar element of a mating vehicle and retain the bar element to within an envelope that provides a soft capture with the mating vehicle. The hard capture elements move within the envelope to engage the bar element and draw the bar element toward the vehicle to provide a hard capture with the mating vehicle. The vehicle mating mechanism can also include a cup-cone interface element of the vehicle that mates with a cup-cone interface element of the mating vehicle during the hard capture to establish an alignment between the vehicle and the mating vehicle.
An asymmetric, broadband, compact and low-PIM orthomode transducer comprised of two parts is presented. Mating of the two parts results in the formation of a choke flange as well as a critical impedance step which suppresses unwanted modes and enables broadband matching of the junction between the two parts. Furthermore, a cruciform-quatrefoil waveguide type is utilized that transitions to an aperture. This waveguide configuration can lead to a lower overall part length, an improved reflection, and reduced manufacturing costs.
A rotor blade retention assembly includes a central hub, a rotor blade including an upper outer surface, a lower outer surface, a blade hole, and a proximal end coupled to the central hub, a strap member extending along a portion of the rotor blade such that a distal end receiving portion extends into the blade hole, and a retainer assembly disposed within the blade hole and coupled to the strap member. The retainer assembly includes an upper bushing and a lower bushing slidably disposed within the blade hole. The upper bushing includes a counterbored portion. The retainer assembly also includes an outboard blade pin disposed within the distal end receiving portion and includes a blade pin inner cavity.
A load control unit includes a first input terminal configured to receive power, a second input terminal configured to receive load information, a first output terminal configured to provide a first portion of the power to a first load, a second output terminal configured to provide a second portion of the power to a second load, a memory, and an electronic processor communicatively connected to the memory, first input terminal, the second input terminal, the first output terminal, and the second output terminal. The electronic processor is configured to measure the power received via the first input terminal, receive load parameters via the second input terminal, and dynamically control, in response to measuring the power and receiving the load parameters, at least one of the first load or the second load based on the power that is measured and the load parameters that are received.
H02J 3/14 - Circuit arrangements for ac mains or ac distribution networks for adjusting voltage in ac networks by changing a characteristic of the network load by switching loads on to, or off from, network, e.g. progressively balanced loading
B64D 41/00 - Power installations for auxiliary purposes
H02J 3/00 - Circuit arrangements for ac mains or ac distribution networks
A bushing assembly for a structure having a first aperture is provided. The bushing assembly includes a first component configured to be received by the first aperture and having a second aperture. A maximum width of the first component defines an outer diameter. The bushing assembly further includes a second component positioned outside of the first aperture and coupled to the first component, the second component having a third aperture extending through the second component. The third aperture is dimensioned so as to be equivalent to the outer diameter of the first component, and the first component and the second component are formed as discrete components of the bushing assembly.
In embodiments, systems and methods include using a modular robotic inspection system to inspect a tubular of a vehicle or building. The modular robotic inspection system comprises a first modular robot and a second modular robot. Both the first modular robot and the second modular robot comprise a base, a plurality of wheels disposed around the base, wherein each of the plurality of wheels is coupled to the base through a set of extendable arms, wherein each one of the plurality of wheels is disposed at a distal end of one of the set of extendable arms, and a plurality of centralizing rollers disposed around the base, wherein each one of the plurality of centralizing rollers is disposed at a proximal end of one of the set of extendable arms. The first modular robot further comprises a motor operable to actuate the plurality of wheels of the first modular robot.
An actuation system for an aircraft can include an actuator and a plurality of clutches connected to and structured to be moved by the actuator. The actuation system can include a plurality of control levers connected to the plurality of clutches and structured to be moved by the plurality of clutches when the plurality of clutches are moved by the actuator. The actuation system can include a processor connected to the actuator and to the plurality of clutches. The processor can identify one or more clutches connected to one or more control levers of the plurality of control levers for controlling an operation of the aircraft, and cause the one or more clutches connected to the one or more control levers to be in an engaged stat. The processor can activate the actuator to cause movement of the one or more control levers via the one or more clutches.
Provided herein are various enhanced arrangements for arrays of aperture antennas, such as horn antennas or short backfire antennas. Examples include an array of aperture antennas having a wall thickness between apertures, and a conductive mesh positioned above the apertures such that openings of the conductive mesh are aligned with the apertures and positioned having a selected spacing between the conductive mesh and the apertures.
H01Q 21/06 - Arrays of individually energised antenna units similarly polarised and spaced apart
H01Q 19/02 - 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 - Details
Systems and methods for harvesting data for an electronic flight bag (EFB) device. The system includes an electronic communication device located in the aircraft and configured to receive aircraft state information transmitted in a first communication protocol via an electronic transponder located in the aircraft, decode the aircraft state information, repackage the aircraft state information as decoded in a second communication protocol, and transmit the aircraft state information as repackaged. The system also includes an electronic flight bag device communicatively coupled to the electronic communication device. The electronic flight bag device includes a transceiver configured to receive the aircraft state information as repackaged and transmitted via the electronic communication device. The system also includes an electronic processor configured to process the aircraft state information from the electronic communication device and perform flight performance planning based on the processed aircraft state information.
A wind estimation system for an aircraft includes a first sensor configured to sense a first position associated with an aircraft control component in a wind condition, a second sensor configured to sense a first configuration associated with a rotor system of the aircraft in the wind condition, and at least one controller in communication with at least one of the first sensor or the second sensor. The at least one controller is configured to determine a tip-path-plane angle of the aircraft based on the first position and the first configuration, and determine at least one of a current wind speed or current wind direction based on the tip-path-plane angle.
B64C 27/57 - 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 automatic or condition responsive, e.g. responsive to rotor speed, torque or thrust
Systems and methods for depicting aircraft traffic. One example system includes an electronic controller coupled to a transceiver and a display for displaying a traffic interface. The electronic controller is configured to provide, on the traffic interface, a map representing a travel area. The electronic controller is configured to provide, on the map, a first graphical representation of a first aircraft within the travel area. The electronic controller is configured to provide, on the map, a second graphical representation of a second aircraft within the travel area. The electronic controller is configured to receive, from the transceiver, a first location of the first aircraft. The electronic controller is configured to receive, from the transceiver, a second location of the second aircraft. The electronic controller is configured to, in response to determining that the second location is within a predetermined radius of the first location, transform the traffic interface to highlight a geometric area of the map based on the first location.
B64D 43/02 - Arrangements or adaptations of instruments for indicating aircraft speed or stalling conditions
G06F 3/0481 - Interaction techniques based on graphical user interfaces [GUI] based on specific properties of the displayed interaction object or a metaphor-based environment, e.g. interaction with desktop elements like windows or icons, or assisted by a cursor's changing behaviour or appearance
A system for providing instructions directed to facilitating the completion of an aerial mission in an environment includes one or more sensors mounted on a vehicle; a transceiver configured to transmit an instruction directed to facilitating the completion of the mission to an electronic display; and a server comprising a processor coupled to memory of the vehicle containing processor-readable instructions. The instructions causing the processor to, responsive to receiving a factor associated with the mission, compute the instruction directed to facilitating the completion of the mission based on adjusting a cost function, the factor being at least one of a boundary condition of the cost function or a constraint of the cost function.
An electrical conductor assembly for a rotor blade includes a substrate and at least one electrical conductor. The substrate includes an inboard end portion and an outboard end portion. The at least one electrical conductor is attached to the substrate and extends between the inboard end portion and the outboard end portion. The at least one electrical conductor is configured to transmit electricity along a length of the rotor blade. The inboard end portion and the outboard end portion are structured such that when the electrical conductor assembly is installed within the rotor blade, the inboard end portion is securable relative to the rotor blade and the outboard end portion is movable relative to the rotor blade.
B64C 27/68 - Transmitting means, e.g. interrelated with initiating means or means acting on blades using electrical energy, e.g. having electrical power amplification
H01B 7/18 - Protection against damage caused by external factors, e.g. sheaths or armouring by wear, mechanical force or pressure
H02G 15/007 - Devices for relieving mechanical stress
H02G 15/06 - Cable terminating boxes, frames or other structures
H01B 13/22 - Sheathing; Armouring; Screening; Applying other protective layers
91.
LANDING GEAR FEEDBACK CONTROL SYSTEM FOR AN AIRCRAFT
A control system for an aircraft, the system including a pilot input device configured to receive a pilot input, a plurality of sensors, each of the plurality of sensors positioned on a corresponding landing gear of the aircraft and configured to sense a parameter on the corresponding landing gear, and a controller in communication with the plurality of sensors, the controller configured to calculate an output command based on the pilot input and the sensed parameters of the landing gear, the output command including instructions for controlling a rotor of the aircraft.
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. automatic pilot
B05B 13/04 - Means for supporting work; Arrangement or mounting of spray heads; Adaptation or arrangement of means for feeding work the spray heads being moved during operation
93.
HELIDECK FLIGHT PATH TOOL FOR PORTABLE AND INSTALLED AIRCRAFT DISPLAYS
Systems and methods for a helideck approach path tool. One example system includes an electronic processor. The electronic processor is configured to determine a helideck identifier and retrieve, from a database storing data on a plurality of helidecks, helideck data corresponding to the helideck identifier. The helideck data includes a helideck azimuth and at least one obstacle characteristic. The electronic processor is configured to generate a graphical user interface including a helideck approach indicator object, which includes a compass ring, a graphical representation of the helideck aligned to the compass ring based on the helideck azimuth, and an obstacle indicator overlaid on the compass ring based on the at least one obstacle characteristic. The electronic processor is configured to present the graphical user interface on a display within the aircraft.
A system includes a printed circuit board (PCB). The PCB includes a radio frequency (RF) circuit that includes a plurality of circuit modules and signal trace lines. Each circuit module is electrically connected to at least one other circuit module by a signal trace line. The system includes a via fence comprising fence walls having at least two materials laminated using a printed wire board (PWB) process. The fence walls include a plurality of vias. The fence walls form a plurality of free-form RF isolation chambers, each chamber includes chamber walls that surround each circuit module outside of the PCB. The embodiments also include a method of manufacturing and/or isolating the system or components of the system.
Systems and methods include using an ultrasonic cutter tool to cut a seal. The system comprises an ultrasonic cutter tool disposed onto a railing system coupled to a platform, wherein the ultrasonic cutter tool is configured to translate along the railing system. The system further comprises a power source electrically coupled to the ultrasonic cutter tool, and an alignment mold disposed parallel to the railing system and offset by a distance. The system further comprises one or more roller bearing carriages coupled to the railing system, wherein each of the one or more roller bearing carriages comprises a set of roller bearings, wherein each set of roller bearings is disposed over the alignment mold, wherein each set of roller bearings is configured to translate along the alignment mold as each of the one or more roller bearing carriages translates along the railing system.
B26D 7/08 - Means for treating work or cutting member to facilitate cutting
B26D 5/08 - Means for actuating the cutting member to effect the cut
B26D 7/00 - CUTTING; DETAILS COMMON TO MACHINES FOR PERFORATING, PUNCHING, CUTTING-OUT, STAMPING-OUT OR SEVERING - Details of apparatus for cutting, cutting-out, stamping-out, punching, perforating, or severing by means other than cutting
B26D 7/26 - Means for mounting or adjusting the cutting member; Means for adjusting the stroke of the cutting member
96.
Marine traffic depiction for portable and installed aircraft displays
Systems and methods for detection and display of marine objects for an aircraft. One example system includes a transceiver configured to communicate with an Automatic Identification System (AIS) server and an electronic controller located within an aircraft. The electronic controller is configured to provide on a display an interface comprising a map representing a travel area. The electronic controller is configured to provide, on the map, a first graphical representation of the aircraft within the travel area. The electronic controller is configured to receive, via the transceiver, marine object data from the AIS server. The electronic controller is configured to periodically update, on the map, a second graphical representation of a first marine object within the travel area based on the marine object data.
An aircraft includes an airframe defining a first enclosed space, an engine bay disposed within the first enclosed space, and a cooling system. The engine bay includes a firebox defining a second enclosed space and an engine disposed at least partially within the second enclosed space. The cooling system is configured to selectively fluidly couple the first enclosed space with the second enclosed space.
B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
A62C 3/08 - Fire prevention, containment or extinguishing specially adapted for particular objects or places in vehicles, e.g. in road vehicles in aircraft
F01P 7/02 - Controlling of coolant flow the coolant being cooling-air
This disclosure relates to apparatuses, systems, and methods for handling faults on vehicles. One or more processors in a vehicle may receive, from a control unit in response to a detection of a fault in the vehicle, an indication of a degradation in a performance constraint of the vehicle. The processors may determine, responsive to the degradation in the performance constraint, that the vehicle is unable to execute a set of commands to control a movement of the vehicle along a trajectory. The processors may generate, in accordance with the degradation in the performance constraint, a modified set of commands that the vehicle is able to execute to control the movement of the vehicle along at least a portion of one or more trajectories. The processors may provide the modified set of commands to the control unit of the vehicle to control the movement of the vehicle.
A lightweight structure for a vehicle, in particular an aircraft, comprises a longitudinal member with a base web, which has a first busbar on a contact surface, and a cross member with a central web and a cross web extending transversely to the central web, the cross web being a first connecting conductor which extends in the area of a first end section of the cross member on a first surface and a second surface of the cross web oriented opposite to this, and a second connection conductor track which extends separately from the first connection conductor track at least on the first surface of the cross web. The cross member extends transversely to the longitudinal member and the cross member is connected at the first end section to the base member in such a way that the first connection conductor track is in contact with the first busbar of the base member. The lightweight structure also includes a flat carbon fiber structure battery connected to the central web of the cross member, a first collector of the carbon fiber structure battery being electrically connected to the first or the second connection conductor track and a second collector of the carbon fiber structure battery being electrically connected to the respective other connection conductor track.
H01M 50/249 - Mountings; Secondary casings or frames; Racks, modules or packs; Suspension devices; Shock absorbers; Transport or carrying devices; Holders specially adapted for aircraft or vehicles, e.g. cars or trains
B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
H01M 50/107 - Primary casings, jackets or wrappings of a single cell or a single battery characterised by their shape or physical structure having curved cross-section, e.g. round or elliptic
H01M 50/103 - Primary casings, jackets or wrappings of a single cell or a single battery characterised by their shape or physical structure prismatic or rectangular
A replacement tip section for a rotor blade, from which a legacy tip section was removed, includes a blade tip portion configured to be attached to an intermediate section of the rotor blade after removal of the legacy section. The intermediate section has a connection feature at an end of the intermediate section to which the blade tip portion is attachable. The replacement tip section includes a transition region configured to be attached to a forward end of the connection feature. The transition region is configured to form a leading edge of the rotor blade and extends from the blade tip portion to form an opening into which the intermediate section is attached. The transition region includes a first end having a first airfoil that conforms to the intermediate section airfoil at the connection feature, and a second end having a second airfoil that conforms to the blade tip portion.
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