A harmonic gear system, having: a housing; an input shaft having an aft end within the housing that defines a wave generator; a wave generator bearing; first and second nested cup-shaped flex splines that are grounded to the housing, the first and second flex splines are biased by the wave generator via the wave generator bearing; an output shaft having a forward end that is within the housing, and a radial flange at the forward end; first and second nested circular splined shafts within the housing, the first and second circular splined shafts are connected to the radial flange of the output shaft and are driven by ones of the first and second flex splines, to thereby drive the output shaft; and a bearing between the first and second circular splined shafts.
F16C 19/18 - Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for both radial and axial load with two or more rows of balls
2.
Cross-bleed safety mechanism for a linear hydraulic actuator
Apparatus and associated methods relate to passively limiting a load of a stalled linear hydraulic actuator that actuates a kinematic device. Damage to a stalled linear hydraulic actuator, associated mounting structure(s), any associated linking mechanism(s), and/or a kinematic device controlled thereby can be prevented quickly and without necessarily forfeiting control of the kinematic device. Such damage prevention can be performed using a cross-bleed safety mechanism connected in parallel with the linear hydraulic actuator. The cross-bleed safety mechanism includes a bilaterally moveable spool within a hydraulic cylinder. The bilaterally moveable spool is located between hydraulic chambers that are in fluid communication with corresponding chambers of the linear hydraulic actuator. In response to being sufficiently displaced from an equilibrium position in each direction of movement by a pressure difference thereacross, the bilaterally moveable spool unblocks bypass channels thereby limiting the stalled linear actuator.
F15B 13/04 - Fluid distribution or supply devices characterised by their adaptation to the control of servomotors for use with a single servomotor
F16K 11/07 - Multiple-way valves, e.g. mixing valvesPipe fittings incorporating such valvesArrangement of valves and flow lines specially adapted for mixing fluid with all movable sealing faces moving as one unit comprising only sliding valves with linearly sliding closure members with cylindrical slides
3.
INTERWOVEN HEAT EXCHANGER CORE WITH END FACE FEATURES
Heat exchangers include a housing with an internal structure that defines sets of first and second fluid passages such that a first fluid within the first fluid passages is prevented from mixing with a second fluid in the second fluid passages. An inlet manifold defines an inlet plenum for receiving the first fluid and directing the first fluid into openings of the first fluid passages. The openings are defined in an inlet end face of the internal structure within the inlet manifold. A set of flow directors are arranged on the inlet end face and are configured to direct a flow of the first fluid into the openings of the set of first fluid passages, with each flow director defining an end face passage that is one of the second fluid passages of the set of second fluid passages.
F28F 9/22 - Arrangements for directing heat-exchange media into successive compartments, e.g. arrangements of guide plates
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
F28F 27/02 - Control arrangements or safety devices specially adapted for heat-exchange or heat-transfer apparatus for controlling the distribution of heat-exchange media between different channels
4.
METAMATERIAL DESIGN ECOSYSTEM USING PHYSICS MODELING AND MACHINE LEARNING
A computer assisted design ecosystem for materials design includes a computer system including a memory and a processor. The memory stores a computer aided design ecosystem including a physics analysis module and a machine learning analysis module. The physics module includes a physics based reflectance simulation and a ratio of solar absorptivity to thermal emissivity module. The machine learning module includes a machine learning based surrogate model, a compute-aware Bayesian sampling module, and a machine learning metamaterial representation. The memory and processor are configured to utilize the machine learning module and the physics module to iteratively determine a suitable metamaterial structure and composition in response to receiving at least one set of design constraints.
G16C 60/00 - Computational materials science, i.e. ICT specially adapted for investigating the physical or chemical properties of materials or phenomena associated with their design, synthesis, processing, characterisation or utilisation
G06F 30/27 - Design optimisation, verification or simulation using machine learning, e.g. artificial intelligence, neural networks, support vector machines [SVM] or training a model
A power converter assembly includes a power converter, a sensor and a controller. The converter includes an alternating current (AC) port and a direct current (DC) port, wherein the AC port is configured to receive AC power and the DC port is configured to output DC power. The power converter also includes a plurality of MOSFET switches that include a body diode coupled between the AC port and the DC port. The a controller connected to the sensor and configured to drive gates of the plurality of MOSFET switches. The controller can determining that current through the body diode of a first switch of the plurality of MOSFET switches exceeds the threshold and then command a gate of the first switch to allow conduction through a conduction region and disallow condition when the current falls.
H02M 7/797 - Conversion of AC power input into DC power outputConversion of DC power input into AC power output with possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only
Hamilton Sundstrand Space Systems International, Inc. (USA)
Inventor
Schuster, Ashley Rose Himmelmann
Woldemariam, Beakal Teshome
Hoang, Thao
Monson, Timothy
Litton, Kevin
Gay, Thomas
Myers, Casey
He, Liana J.
Abstract
Waste collection and processing systems for use in low-gravity environments include a toilet having a bowl and a lid; a waste tank having an inlet and an outlet, with the bowl fluidly coupled to the inlet of the waste tank; a first valve arranged between the bowl and the waste tank and selectively operable to allow fluid connection between the bowl and the waste tank; a second valve arranged at a first outlet of the waste tank and selectively operable to allow for solid waste and liquid waste within the waste tank to be directed to a waste outlet; and a third valve arranged at a second outlet of the waste tank and selectively operable to allow for gases to be removed from the waste tank and directed to at least one of an occupied space, an external environment, or a waste reclamation system.
A method for joining thermoplastic composite components is provided that includes: providing a first thermoplastic composite (FTC) component having an FTC first zone and an FTC second zone; providing a second thermoplastic composite (STC) component having an STC first zone and an FTC second zone; forming a joint region between the FTC and STC components by disposing them in a stepped arrangement, wherein each material ply within the FTC first zone overlaps a material ply within the STC first zone by a first overlap distance, and at least one material ply within the FTC second zone overlaps a material ply within the STC second zone by a second overlap distance, and at least one material ply within the FTC second zone overlaps a material ply within the STC second zone by the first overlap distance; and joining the FTC and STC components by applying an elevated temperature and pressure.
A battery system includes an anode circuit configured to urge a flow of anolyte therethrough to an anode side of an electrode and a cathode circuit configured to urge a flow of catholyte therethrough to a cathode side of the electrode. An electric circuit is operably connected to the electrode to utilize electrical energy generated via a chemical reaction between the flow of anolyte and the flow of catholyte at the electrode. The flow of anolyte is driven through the anode circuit by thermal expansion and/or thermal contraction of one or more components of the anode circuit. The flow of catholyte is driven through the cathode circuit by thermal expansion and/or thermal contraction of one or more components of the cathode circuit.
In accordance with at least one aspect of this disclosure, a system includes a hydrogen generator configured to decompose Alane to produce a flow of hydrogen and aluminum and a fuel cell fluidly connected to the hydrogen generator configured to receive the flow of hydrogen from the hydrogen generator and receive a flow of oxidizer to chemically generate electrical power and produce a flow of product water as a byproduct. The hydrogen generator is configured to receive the flow of product water to react with the aluminum and with Alane remaining in the hydrogen generator to generate an additional flow of hydrogen and heat, wherein the additional flow of hydrogen is provided to the fuel cell.
H01M 8/065 - Combination of fuel cells with means for production of reactants or for treatment of residues with means for production of gaseous reactants by dissolution of metals or alloysCombination of fuel cells with means for production of reactants or for treatment of residues with means for production of gaseous reactants by dehydriding metallic substances
A cold plate is provided and includes an additively manufactured integral components layered together to form a unitary body. The additively manufactured integral components include a cold plate body having a region on which a power module is disposable and defining a first interior channel extending across the region in a first plane, a frame to support the cold plate body and a cooling boss. The frame defines a second interior channel communicative with the first interior channel and extends along a periphery of the cold plate body in the first plane. The cooling boss is attached to the frame. The cooling boss defines a third interior channel communicative with the second channel and extends in a second plane transverse to the first plane.
Hamilton Sundstrand Space Systems International, Inc. (USA)
Inventor
Schuster, Ashley Rose Himmelmann
Woldemariam, Beakal Teshome
Hoang, Thao
Monson, Timothy
Litton, Kevin
Gay, Thomas
Myers, Casey
He, Liana J.
Abstract
Waste collection and processing systems for use in low-gravity environments include a toilet having a bowl and a lid with a waste tank having an inlet and an outlet, wherein the bowl of the toilet is fluidly coupled to the inlet of the waste tank. A waste bag is arranged within the waste tank to capture human waste deposited into the waste tank from the toilet bowl. The waste bag is permeable to gases and impermeable to liquid waste and solid waste. A filter assembly is fluidly coupled to the outlet of the waste tank and configured to treat air that passes through the filter assembly. A first valve is operably arranged between the bowl and the waste tank and a second valve is operably arranged between the waste tank and the filter assembly.
Hamilton Sundstrand Space Systems International, Inc. (USA)
Inventor
Schuster, Ashley Rose Himmelmann
Woldemariam, Beakal Teshome
Hoang, Thao
Monson, Timothy
Litton, Kevin
Gay, Thomas
Myers, Casey
He, Liana J.
Abstract
Waste collection and processing systems for use in low-gravity environments include a toilet having a bowl and a lid; a first waste tank having an inlet and an outlet, with the bowl of the toilet selectively fluidly coupled to the inlet of the first waste tank; a second waste tank having an inlet and an outlet, with the bowl of the toilet is selectively fluidly coupled to the inlet of the second waste tank; a controller configured to selectively operate each of the first waste tank and the second waste tank between reclamation modes of operation and collection modes of operation. When the first waste tank is operated in the reclamation mode of operation the second waste tank is operated in the collection mode of operation and vice versa.
Hamilton Sundstrand Space Systems International, Inc. (USA)
Inventor
Schuster, Ashley Rose Himmelmann
Woldemariam, Beakal Teshome
Hoang, Thao
Monson, Timothy
Litton, Kevin
Gay, Thomas
Myers, Casey
He, Liana J.
Abstract
Waste collection and processing systems for use in low-gravity environments include a toilet having a bowl and a lid, the toilet configured to receive solid human waste; a liquid waste collection system comprising a liquid waste receptacle configured to receive liquid human waste; a first waste tank fluidly coupled to the toilet; a second waste tank fluidly coupled to the liquid waste collection system; a third waste tank fluidly coupled to the liquid waste collection system, wherein the first waste tank, the second waste tank, and the third waste tank are each configured to be operated between reclamation modes of operation and collection modes of operation; and a waste outlet configured to selectively receive an airflow from each of the first waste tank, the second waste tank, and the third waste tank.
An apparatus for adjusting aircraft inceptor trim includes an inceptor centring device mechanically coupled to a control shaft that rotates in response to inceptor inputs. The inceptor centring device includes an inceptor centring spring preloaded with a preload force to provide a first biasing force to bias the control shaft to an inceptor neutral position. The apparatus has a trim mechanism, mechanically coupled to the inceptor centring device, and includes a trim locking device having a locked state and an unlocked state. A resistance force of the trim mechanism with the trim locking device in the unlocked state is less than the preload force, such that when the trim mechanism is in the unlocked state, actuation of the inceptor adjusts the position of the inceptor centring device to alter the degree of trim.
A journal bearing shaft is provided and includes a single monolithic body. The single monolithic body includes a tie rod, an end cap integrally connected to and extending radially outwardly from an end of the tie rod and defining openings, a journal bearing interface portion integrally connected to and extending aft from a distal edge of the end cap and a bi-metal heat exchanger integrally connected to and extending aft from an aft edge of the journal bearing interface portion and including an exterior body formed of a first material and heat exchange fins formed of a second material differing from the first material and extending radially between the exterior body and the tie rod.
A compressor includes a compressor rotor and a motor disposed about a common axis. The motor includes a rotor shaft coupled to the compressor rotor and configured to drive the compressor rotor; a thrust shaft disposed at an opposite end of the motor from the rotor shaft; a tie rod disposed on the common axis and extending through the rotor shaft, thrust shaft, and the compressor rotor; a first journal bearing disposed about the rotor shaft and concentrically about the common axis to radially support the rotor shaft; a journal bearing support disposed concentrically about the first journal bearing; and a cooling fluid inlet disposed adjacent to the bearing support and in fluid communication with the first journal bearing. The rotor shaft includes a plurality of orifices. The tie rod axially retains the compressor rotor at a forward end and the motor at an aft end.
A hydraulic drag brake is provided for use with a driveline. The hydraulic drag brake includes a fluid circuit including first and second loops, a first valve disposed along the first loop to allow a flow of fluid through the first loop in a first direction and to prevent a flow of the fluid through the first loop in a second direction, a second valve disposed along the second loop and a pump coupled to the driveline and configured to pump the fluid through the fluid circuit in the first direction and across the first valve with the driveline occupying a retracted position or engaging in an extend motion and in the second direction and over the second valve with the driveline occupying an extended position.
Embodiments of the disclosure provide an electric power distribution (EPD) system that includes a first conversion module electronically connected between a voltage source and a bus. The first conversion module includes a transformer system electronically connected to a first converter circuit having a first maximum voltage rating. The voltage source provides a voltage source output, and the first maximum voltage rating is less than the voltage source output.
Embodiments of the disclosure provide an electric power distribution (EPD) system that includes a first power conversion system electronically connected between a first voltage source and a bus, along with a second power conversion system electronically connected between the bus and a first load. The first power conversion system is operable to, responsive to receiving power that originated from the first voltage source in a first modality, generate a first voltage and provide the first voltage to the bus. The second power conversion system is operable to, responsive to receiving a bus-voltage of the bus, generate a second voltage and provide the second voltage to the first load. The bus-voltage is greater than the second voltage.
H02J 1/12 - Parallel operation of dc generators with converters, e.g. with mercury-arc rectifier
H02J 50/23 - Circuit arrangements or systems for wireless supply or distribution of electric power using microwaves or radio frequency waves characterised by the type of transmitting antennas, e.g. directional array antennas or Yagi antennas
H02J 50/27 - Circuit arrangements or systems for wireless supply or distribution of electric power using microwaves or radio frequency waves characterised by the type of receiving antennas, e.g. rectennas
H02J 50/30 - Circuit arrangements or systems for wireless supply or distribution of electric power using light, e.g. lasers
H02M 3/158 - Conversion of DC power input into DC power output without intermediate conversion into AC by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only with automatic control of output voltage or current, e.g. switching regulators including plural semiconductor devices as final control devices for a single load
20.
SYSTEM FOR DETECTING SERIES ARC FAULTS IN ELECTRIC CABLING
A power supply system includes: a DC power supply, a load to be powered by the power supply, and a DC electrical conductor electrically connected at a first end to the power supply and at a second end to the load. The system further includes: a fault detection system configured to detect a series arc event in the DC electrical conductor, the fault detection system includes: a sense line conductor having a high impedance termination at the second end; a differential amplifier having a first input connected to the sense line conductor at a first terminal(S) and a second input connected to the DC electrical conductor at a second terminal (L), and an output providing a voltage differential output; and a comparator to compare the voltage differential output to a predetermined voltage differential threshold, the comparator providing a fault output dependent on the comparison.
A compliant consolidation block is provided. The compliant consolidation block includes a non-articulating component, a first articulating self-aligning component coupled to the non-articulating component, and two second articulating self-aligning components coupled to the first articulating self-aligning component. The first articulating self-aligning component is configured to articulate with respect to the non-articulating component. Each of the two second articulating self-aligning components are individually configured to articulate with respect to the first articulating self-aligning component.
Embodiments of the disclosure provide an aircraft health monitoring system having an in-flight controller. The controller is configured to, responsive to a determination that an aircraft is in-flight, access a sensor network system of the aircraft to generate in-flight system health (IFSH) information. A transmission operation is initiated that transmits the IFSH information through a wireless communications path to a ground-based flight monitoring system. The ground-based flight monitoring system is operable to initiate an aircraft management operation associated with the aircraft.
A compressor includes a compressor rotor and a motor disposed about a common axis. The motor includes a rotor shaft coupled to the compressor rotor and configured to drive the compressor rotor; a thrust shaft disposed at an opposite end of the motor from the rotor shaft; a tie rod disposed on the common axis and extending through the rotor shaft, thrust shaft, and the compressor rotor, the tie rod axially retaining the compressor rotor at a forward end and the motor at an aft end; a cooling fluid inlet disposed at an aft end of the motor; and a motor rotor cooling flow path extending from the thrust shaft to the rotor shaft. The rotor shaft includes a plurality of orifices that open to a cavity on a backside of the compressor rotor and fluidly couple the motor rotor cooling flow path to the cavity.
A water separator for use in an environmental control system of an aircraft including an outer housing having an upstream end, a downstream end, and a central longitudinal axis. A plurality of vanes are arranged within the outer housing and are spaced about the central longitudinal axis. A plurality of flow channels are formed between the plurality of vanes and the outer housing. The plurality of flow channels have a spiral-like configuration about the central longitudinal axis. At least one ring vane is arranged within the outer housing and extends parallel to the longitudinal axis.
A water separator for use in an environmental control system of an aircraft includes an outer housing having an upstream end, a downstream end, and a longitudinal axis. A vane assembly is arranged within the outer housing and is spaced about the longitudinal axis. The vane assembly defines a plurality of flow channels. At least one flow channel of the plurality of flow channels is located radially outward of another flow channel of the plurality of flow channels. The plurality of flow channels have a spiral-like configuration about the longitudinal axis and a flow length of the plurality of flow channels is equal.
B01D 45/16 - Separating dispersed particles from gases or vapours by gravity, inertia, or centrifugal forces by centrifugal forces generated by the winding course of the gas stream
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
A fuel delivery system for a gas turbine engine includes a fuel source and a main fuel pump configured to deliver a first flow of fuel to a combustor assembly of the gas turbine engine under a first, relatively high fuel demand operating condition of the gas turbine engine. A secondary fuel pump is configured to deliver a second flow of fuel to the combustor assembly under a second, relatively low fuel demand operating condition of the gas turbine engine.
A gas turbine engine includes a combustor section, and a turbine section including a turbine configured to be driven by a flow of combustion products from the combustor section. A thermophotovoltaic cell is positioned at at least one of the combustor section or the turbine section. The thermophotovoltaic cell is configured to convert radiant heat energy from at least one of the combustor section or the turbine section into electrical energy. A method of operating a gas turbine engine includes combusting a mixture of fuel and air at a combustor section, driving a turbine of a turbine section via urging of combustion products from the combustor section to the turbine, and converting radiant thermal energy from at least one of the combustor section or the turbine section to electrical energy via a thermophotovoltaic cell positioned at at least one of the combustor section or the turbine section.
F02C 3/14 - Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
28.
DIFFERENTIAL MODE INDUCTOR FOR HIGH POWER AEROSPACE FILTERING APPLICATIONS
A differential mode inductor includes a core and a winding assembly. An outer core ring stack includes a stack of outer laminated sheets defining an upper ring surface and a lower ring surface. Each of the upper and lower ring surfaces extend from an outer ring surface to an inner ring surface which surrounds a core central opening in which a center core leg stack is disposed. The center core leg stack includes a stack of center laminated sheets. Each center laminated sheet includes a center core leg. The center core leg stack is separated from the outer core ring stack by a distance to define a core gap region configured to store magnetic energy resulting from the magnetic field. A winding assembly is disposed in the core central opening and includes a plurality of coil windings configured to produce a magnetic field in response to electrical current flowing therethrough.
A bearing system for a rotatable shaft includes a bearing shaft coaxial with the rotatable shaft, a bearing coaxial with the bearing shaft, a bearing housing surrounding the bearing and having a plurality of retention channels disposed axially along the bearing housing, and a dampening assembly comprising a plurality of circumferential seal elements disposed within each of the plurality of retention channels. A first subset of the plurality of seal elements is formed from a first material and a second subset of the plurality of seal elements is formed from a second material.
F16C 33/78 - Sealings of ball or roller bearings with a diaphragm, disc, or ring, with or without resilient members
F16C 19/04 - Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for radial load mainly
30.
INTEGRATED PNEUMATIC AND ELECTRIC CABIN AIR COMPRESSOR
A pressurization system for a vehicle includes a plurality of medium sources including a first medium source, a second medium source, and a third medium source. A cabin air compressing device is arranged in fluid communication with the plurality of medium sources. The cabin air compressing device includes a shaft, a compressor connected to the shaft and at least one turbine connected to the shaft. The compressor has a compressor inlet fluidly coupled to the first medium source and a compressor outlet fluidly connected to an inlet of a downstream environmental control system pack. Energy extracted within the at least one turbine is configured to drive the compressor.
An LLC voltage converter for converting a DC input voltage to a DC output voltage includes a transformer and a controller. The controller is arranged to monitor an operational parameter and operate the LLC voltage converter in a first mode, in which the transformer has a first turns ratio, when a value of the operational parameter is within a first range. In response to determining that the value of the operational parameter has changed to be outside the first range and inside a second range, the controller is arranged to transition the LLC voltage converter from operating in the first mode to operate in a second mode, in which the transformer has a second turns ratio. The first range at least partially overlaps the second range.
H02M 3/335 - Conversion of DC power input into DC power output with intermediate conversion into AC by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate AC using devices of a triode or a transistor type requiring continuous application of a control signal using semiconductor devices only
An electric motor drive system for a propulsion device. The system includes a battery stack having an earth terminal and an end terminal and an electric motor electrically connected to be powered by the battery stack. The motor is configured to be connected to drive the propulsion device, The system also includes: a power converter electrically connected between the battery stack and the electric motor; and a switch between the power converter and the battery stack. The switch is arranged to switch between a first state electrically connecting the end terminal of the battery stack to the power converter to provide a maximum battery voltage to the power converter, and a second state electrically connecting a tap point from one or more intermediate nodes, intermediate the earth terminal and the end terminal, of the battery stack, to provide a voltage less than the maximum battery voltage to the power converter.
B64D 35/022 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants for electric power plants of hybrid-electric type
B64D 31/16 - Power plant control systemsArrangement of power plant control systems in aircraft for electric power plants
H01M 10/42 - Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
A shroud reinforcement is provided for a shroud that is coaxial with and partially surrounds a rotor and that includes tubular and flange sections and a transition section axially interposed between the tubular and flange sections. The shroud reinforcement includes first fiber-reinforced polymer-matrix composite reinforcement elements with fibers extending along an axial dimension of the rotor and being disposed to reinforce the transition section and second fiber-reinforced polymer-matrix composite reinforcement elements with fibers extending along a circumferential dimension of the rotor and being disposed to reinforce the transition section.
An aircraft includes an electrical system having at least one cooled electrical component. The at least one cooled electrical component is a low grade heat source. The aircraft further includes a cooling system with a coolant loop passing through the at least one cooled electrical component and through a first adsorption cooler. The first adsorption cooler is configured to cool coolant in the cooling loop using an adsorption process.
A piston retainer plate includes a first end, a second end opposite the first end, a piston pocket extending from the first end to the second end, a straight annular surface extending from the first end, an angled annular surface extending at an angle from the second end, a curved annular surface connected to the straight annular surface and the angled annular surface, the curved annular surface being between the straight annular surface and the angled annular surface, and a curved vent within the curved annular surface. The straight annular surface, the angled annular surface, and the curved annular surface define the piston pocket.
A fuel pumping system for delivering fuel to an engine component includes a boost pump having a boost pump outlet and a main pump having a main pump inlet and a main pump outlet. The main pump inlet is fluidly connected to the boost pump outlet via a main pump feed conduit. A fuel control conduit is fluidly connected to the main pump outlet and to the engine component. A third pump has a third pump inlet and a third pump outlet. The third pump outlet is fluidly connected to the engine component. A third pump conduit is fluidly connected to the main pump outlet and to the third pump inlet. A valve is operable to control a fuel flow to the third pump in response to a pressurization demand of the engine component.
A method for applying a sulfonation treatment to a thermoplastic part includes forming a sulfonation barrier on the thermoplastic part by applying a sealant tape onto the thermoplastic part, applying a sulfonation fluid to a portion of a thermoplastic surface of the thermoplastic part to sulfonate the thermoplastic part at the thermoplastic surface, removing the sulfonation fluid from the portion of the thermoplastic surface, applying a neutralizing agent to the portion of the thermoplastic surface, washing the portion of the thermoplastic surface, and applying at least one coating to the portion of the thermoplastic surface.
B05D 3/10 - Pretreatment of surfaces to which liquids or other fluent materials are to be appliedAfter-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials by other chemical means
B05D 1/32 - Processes for applying liquids or other fluent materials using means for protecting parts of a surface not to be coated, e.g. using stencils, resists
38.
MID-PRESSURE WATER SEPARATION FOR ENVIRONMENTAL CONTROL SYSTEM
A water separator for use in an environmental control system of an aircraft includes an outer housing having an upstream end, a downstream end, and a central longitudinal axis. A plurality of vanes are arranged within the outer housing and are spaced about the central longitudinal axis. The plurality of vanes have an inlet end proximate to the upstream end and an outlet end proximate to the downstream end. An exterior edge of each of the plurality of vanes is in contact with an interior surface of the outer housing and a hollow channel is defined by an interior edge of the plurality of vanes. A plurality of flow channels is formed between the plurality of vanes and the outer housing. The plurality of flow channels has a spiral-like configuration about the central longitudinal axis.
An actuation assembly includes a control valve, a first actuator and a second actuator fluidly connected to the control valve via plumbing. The first actuator has a first extend port and the second actuator having a second extend port. A flow control device fluidly connected to the first actuator and the second actuator is operable to balance a flow rate of a fluid at the first actuator with the flow rate of the fluid at the second actuator. The flow control device is arranged within the plumbing, at a position between the control valve and the first extend port and the second extend port.
A method for making an article includes inputting a digital model of the article into an additive manufacturing apparatus or system comprising an energy source, wherein the energy source is a ring laser having a beam size and repeatedly applying energy from the ring laser to successively applied incremental quantities of a powder particles to fuse the powder particles to form the article corresponding to the digital model. Applying the energy includes passing the energy from the ring laser through an optical system to narrowing a width of the beam size to create a smaller beam size before the energy reaches the powder particles.
A thermoplastic part for an aircraft includes a thermoplastic skin, a conductive metal layer, a thermoplastic resin film, and a paint coating. The thermoplastic skin includes an inner skin side and an outer skin side. The conductive metal layer includes an inner layer side and an outer layer side. The inner layer side is disposed at the outer skin side of the thermoplastic skin. The thermoplastic resin film including an inner film side and an outer film side. The inner film side is disposed at the outer layer side of the conductive metal layer. The thermoplastic resin film includes a sulfonated thermoplastic resin material forming a sulfonated region of the thermoplastic resin film at the outer film side. The paint coating is disposed on the outer film side of the thermoplastic resin film coincident with the sulfonated region.
B32B 15/08 - Layered products essentially comprising metal comprising metal as the main or only constituent of a layer, next to another layer of a specific substance of synthetic resin
B32B 15/02 - Layered products essentially comprising metal in a form other than a sheet, e.g. wire, particles
B32B 15/20 - Layered products essentially comprising metal comprising aluminium or copper
B32B 27/28 - Layered products essentially comprising synthetic resin comprising copolymers of synthetic resins not wholly covered by any one of the following subgroups
C08J 5/12 - Bonding of a preformed macromolecular material to the same or other solid material such as metal, glass, leather, e.g. using adhesives
A method for applying a sulfonation treatment to a thermoplastic part includes installing a gas sulfonation assembly on one or more surfaces of the thermoplastic part by forming a vacuum bag on the one or more surfaces. The vacuum bag forms a sealed cavity between the vacuum bag and a treatment portion of the one or more surfaces. The method further includes drawing a vacuum in the sealed cavity with the gas sulfonation assembly, directing a sulfonating gas into the sealed cavity with the gas sulfonation assembly to sulfonate the treatment portion, removing the sulfonating gas from the sealed cavity with the gas sulfonation assembly, removing the gas sulfonation assembly from the thermoplastic part, applying a neutralizing agent to the treatment portion, and applying at least one coating to the treatment portion.
B05D 3/04 - Pretreatment of surfaces to which liquids or other fluent materials are to be appliedAfter-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials by exposure to gases
43.
Distributed electrical generators for turbofan engines
An apparatus for generating electrical power includes a rotating member surrounded by a fixed structure. The apparatus also includes at least one magnet, each of which is located on the rotating member. The apparatus further includes at least one distributed generator module located on the fixed structure and configured to generate an electrical power signal responsive to movement of the at least one magnet past the at least one distributed generator module. The at least one distributed generator module is configured to be independently activated and deactivated responsive to a control signal.
H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
F01D 15/10 - Adaptations for driving, or combinations with, electric generators
H02K 11/04 - Structural association of dynamo-electric machines with electric components or with devices for shielding, monitoring or protection for rectification
A fluid delivery system is provided including a reservoir including oil, a hydraulic pump in fluid communication with the reservoir, and a heat exchanger system. The heat exchanger system is in fluid communication with the hydraulic pump, a generator, and an engine gearbox. The hydraulic pump is configured to deliver the oil to the heat exchanger system. The heat exchanger system is configured to provide the oil according to first temperature criteria to the generator and provide the oil according to second temperature criteria to the engine gearbox.
An environmental control system includes a component having a component inlet and a component outlet and a flow path fluidly connected to the component inlet and the component outlet. The flow path includes a turn upstream from the component inlet. At least one flow diverter element is arranged within the flow path between the turn and the component outlet. The at least one flow diverter element is positioned to uniformly distribute a flow across the component inlet.
A shouldered shaft assembly of a variable displacement, bent axis piston pump is provided. The shouldered shaft assembly includes a bearing retainer housing including radially inwardly facing tilt pad bearings and axially facing tilt pad thrust bearings and a shouldered shaft. The shouldered shaft is disposed in the bearing retainer housing and includes a first shaft section, a second shaft section and an axial surface. The second shaft section has a larger diameter than the first shaft section and includes an outer diameter (OD) surface. The OD surface faces and fluid-dynamically interacts with the radially inwardly facing tilt pad bearings. The OD surface is formed to define microscopic surface texturing for increased fluid-dynamic interaction. The axial surface extends between the first shaft section and the second shaft section. The axial surface faces and fluid-dynamically interacts with the axially facing tilt pad thrust bearings.
A time-interleaved analogue-to-digital converter including a first analogue-to-digital converter and a second analogue-to-digital converter, each arranged to sample a respective analogue input periodically and produce a respective digital output based on the sampled analogue input, and also including a signal interleaving portion, arranged to combine the digital outputs to produce a digital output signal. The time-interleaved analogue-to-digital converter is configured for operation both in an operational mode and a calibration mode. In the operational mode, the second analogue-to-digital converter is arranged to sample the analogue input a first time period after the first analogue-to-digital converter samples the analogue input. In the calibration mode, the second analogue-to-digital converter is arranged to sample the analogue input simultaneously with the first analogue-to-digital converter, or a second time period apart from a time at which the first analogue-to-digital converter samples the analogue input. The second time period is shorter than the first time period.
A resonant circuit for a DC-DC power converter. The resonant circuit includes: a resonant inductance and a resonant capacitance. The resonant capacitance is provided by two capacitors configured to be connected in series to an input switching stage of a DC-DC power converter, and the resonant inductance comprising a resonant inductor connected in series with a first of the capacitors. The resonant circuit can be part of a DC-DC power converter. The converter can include: input DC voltage bus; an input switching stage connected across the input DC bus; the resonant circuit; a voltage converter; and an output rectifier stage; wherein the voltage converter comprises an auto transformer having an input side inductance comprising a first inductance part (P11) and a second inductance part (P21) in series and a tap output between the first and second inductance part, wherein the voltage converter has a conversion ratio of (P11+P21)/P21.
H02M 3/00 - Conversion of DC power input into DC power output
H02M 3/335 - Conversion of DC power input into DC power output with intermediate conversion into AC by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate AC using devices of a triode or a transistor type requiring continuous application of a control signal using semiconductor devices only
H02M 7/5387 - Conversion of DC power input into AC power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only, e.g. single switched pulse inverters in a bridge configuration
A fire extinguisher assembly for a vehicle includes a mounting cradle having a base comprising a base plate, the base plate partially defining an internal volume, a puncturing device disposed in the internal volume, and at least one discharge head fluidly connected to the internal volume. The fire extinguisher assembly further includes a vessel removably mounted to the mounting cradle and supported by the base plate. The vessel contains at least one fire suppression agent.
An aircraft flight control apparatus includes a control input device comprising a moveable control input component and a feeling feedback apparatus. A processing apparatus is arranged to use user information to determine a control input profile and generate at least one aircraft control signal and/or control the feeling feedback apparatus to apply force to the control input component. The processing apparatus is arranged to generate the at least one aircraft control signal and/or control the feeling feedback apparatus based at least partially on the control input profile.
A system is provided including one or more piezoelectric assemblies, where the one or more piezoelectric assemblies include a plurality of piezoelectric transducers. The system includes amplifier circuitry coupled to the plurality of piezoelectric transducers and configured to provide an alternating-current (AC) voltage signal to one or more piezoelectric transducers of the plurality of piezoelectric transducers, based on a target configuration associated with removing regolith dust from a vehicle operable in a space environment. The one or more piezoelectric transducers are configured to vibrate based on a magnitude and a frequency of the AC voltage signal.
H10N 39/00 - Integrated devices, or assemblies of multiple devices, comprising at least one piezoelectric, electrostrictive or magnetostrictive element covered by groups
B60S 1/66 - Other vehicle fittings for cleaning for cleaning vehicle exterior
An electric aircraft includes system for operating the aircraft. The electric aircraft includes a wing having a first control surface, a second control surface, a battery and a gearbox mechanically coupled to the first control surface. The first control surface is operated, and a voltage is induced from mechanical energy generated during a deceleration of the first control surface that occurs while operating the first control surface, wherein an airflow across the first control surface causes the deceleration. The induced voltage can be stored at the battery or used to operate the second control surface using the induced voltage.
B64C 23/00 - Influencing air flow over aircraft surfaces, not otherwise provided for
B64C 13/50 - Transmitting means with power amplification using electrical energy
B64D 35/026 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants for electric power plants the electric power plant being integral with the propeller or rotor
A time-interleaved analogue-to-digital converter including a first analogue-to-digital converter, a second analogue-to-digital converter, and a third analogue-to-digital converter, each arranged to sample an analogue input and produce a respective digital output based on the sampled analogue input, and also including a signal interleaving portion, arranged to combine the digital outputs from the analogue-to-digital converters to produce a digital output signal. The time-interleaved analogue-to-digital converter is configured for operation both in an operational mode, and in a compensation mode when the third analogue-to-digital converter is non-functional. In the operational mode, the first and second analogue-to-digital converter sample the analogue input respectively at a first frequency and a second frequency. In the compensation mode, the first and second analogue-to-digital converter sample the analogue input respectively at a third frequency and a fourth frequency. The third frequency is higher than the first frequency, and the fourth frequency is higher than the second frequency.
Hamilton Sundstrand Space Systems International, Inc. (USA)
Inventor
Ruiz, Gabriel
Miranda, Joseph
Abstract
A heat exchanger is provided and includes a heat exchanger core and an integral slurper circuit. The integral slurper circuit includes multiple slurper bars integrally formed with the heat exchanger core as a single, monolithic body. Each of the multiple slurper bars includes a hollow shell. The hollow shell is elongate in a longitudinal dimension thereof, which is aligned with a direction of flow of humid air exiting the heat exchanger core. The hollow shell is formed to define an interior and to define holes arranged along a length of the hollow shell by which water that is condensed out of the humid air is drawn into the interior.
F28D 1/047 - Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, in which the other heat-exchange medium is a large body of fluid, e.g. domestic or motor car radiators with the heat-exchange conduits immersed in the body of fluid with tubular conduits the conduits being bent, e.g. in a serpentine or zig-zag
A structural complexity analysis system includes a system modeling language (SysML) module and a numerical computation module. The SysML module determines a complexity interaction profile of an engineering system, which includes a plurality of nodes and a plurality of connectors, each connector establishing a connection between a sub-set of nodes among the plurality of nodes, and determines a complexity node profile of parts, which defines a complexity of at least one node among the plurality of nodes. The SysML module further generates an interfaces table based on the complexity interaction profile, and generates generate a node table based on the complexity node profile. The numerical computation module receives the interfaces table and the node table, and applies at least one numerical computation tool to the interfaces table and the node table to determine an overall structural complexity of the engineering system.
A system includes a vortex tube. A first thermoelectric terminal is in thermal communication with the first outlet of the vortex tube. A second thermoelectric terminal is in thermal communication with the second outlet of the vortex tube. An electrical circuit is electrically connected to the first thermoelectric terminal and to the second thermoelectric terminal for electrical conduction of Peltier-effect thermoelectric current. The systems and methods described herein can be used to enhance temperature difference generated in a vortex tube, and/or to harvest energy from the temperature difference in a vortex tube.
F24H 3/08 - Air heaters with forced circulation the air being kept separate from the heating medium, e.g. using forced circulation of air over radiators by tubes
H10N 10/10 - Thermoelectric devices comprising a junction of dissimilar materials, i.e. devices exhibiting Seebeck or Peltier effects operating with only the Peltier or Seebeck effects
H10N 10/817 - Structural details of the junction the junction being non- separable, e.g. being cemented, sintered or soldered
57.
WASTE MANAGEMENT SYSTEM WITH BUILT-IN PIEZOELECTRIC BASED INTERFACES FOR WATER RECOVERY AND STERILIZATION VIBRATION
A system is provided. The system includes: a receptacle; one or more piezoelectric transducers included in the receptacle; and amplifier circuitry coupled to the one or more piezoelectric transducers and configured to provide an alternating-current (AC) voltage signal to the one or more piezoelectric transducers, based on a target configuration associated with recovering water from a substance included in the receptacle. The one or more piezoelectric transducers are configured to vibrate based on a magnitude and a frequency of the AC voltage signal. The system is configured to extract a mist form of the water from the substance, based on the vibration of the one or more piezoelectric transducers.
In accordance with at least one aspect of this disclosure, a composite rotor includes a first rotor portion defining a first rotational axis and having a first magnet therein and a second rotor portion defining a second rotational axis and having a second magnet therein. A stator portion is disposed radially between the first rotor portion and the second rotor portion. The first rotor portion and the second rotor portion are formed of composite filaments and/or composite tape, and the composite filaments and/or composite tape are wrapped in both a first direction and a second direction different from the first direction relative to the first and second rotation axes.
H02K 16/02 - Machines with one stator and two rotors
H02K 15/02 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies
Hamilton Sundstrand Space Systems International, Inc. (USA)
Inventor
Schuster, Ashley Rose Himmelmann
Hoang, Thao
Monson, Timothy
Abstract
A commode test system for use in Earth's gravity field at Earth's surface is provided. The commode test system includes a commode disposed at Earth's surface, a blower to generate airflow into the commode, a gas-filled bolus having a neutral buoyancy in Earth's gravity field at Earth's surface and recording devices to record movements of the gas-filled bolus in the airflow relative to the commode.
A circuit board system includes a printed circuit board (PCB) having a first side and a second side opposite the first side. A plurality of plated through holes (PTHs) are defined through the PCB from the first side to the second side. A respective pad is defined at each end of each PTH of the plurality of PTHs. The PCB includes circuit traces electrically interconnecting among the plurality of PTHs for forming PCB circuitry. A coverlay is adhered to the first side of the PCB for insulating voltages among the plurality of PTHs.
A system is provided including one or more piezoelectric assemblies, wherein the one or more piezoelectric assemblies include a plurality of piezoelectric transducers. The system includes amplifier circuitry coupled to the plurality of piezoelectric transducers and configured to provide an alternating-current (AC) voltage signal to one or more piezoelectric transducers of the plurality of piezoelectric transducers, based on a target configuration associated with removing regolith dust. The one or more piezoelectric transducers are configured to vibrate based on a magnitude and a frequency of the AC voltage signal.
B08B 7/02 - Cleaning by methods not provided for in a single other subclass or a single group in this subclass by distortion, beating, or vibration of the surface to be cleaned
An electrical system for an aircraft comprises a local controller configured to control a power source for an aircraft using droop control in accordance with a droop gain. The local controller is configured, in response to receiving a command, to adjust the droop gain from a first value to a second value progressively over a time interval according to a predetermined function of time.
Hamilton Sundstrand Space Systems International, Inc. (USA)
Inventor
Schuster, Ashley Rose Himmelmann
Litton, Kevin
Abstract
A modified tank for use in microgravity environments is provided. The modified tank includes a membrane defining an interior and including an inlet leading to the interior and first and second outlets from the interior. The modified tank further includes first and second filters for the first and second outlets, respectively, and an outlet wiping pair. The outlet wiping pair includes a wiper in the interior and a wiping boss at an exterior of the membrane. The wiping boss is operably coupled to the wiper whereby operation of the wiping boss causes the wiper to wipe at least one of the first and second filters.
B08B 3/10 - Cleaning involving contact with liquid with additional treatment of the liquid or of the object being cleaned, e.g. by heat, by electricity or by vibration
B08B 9/045 - Cleaning the internal surfacesRemoval of blockages using cleaning devices introduced into and moved along the pipes moved by externally powered mechanical linkage, e.g. pushed or drawn through the pipes the cleaning devices being rotated while moved
64.
WELDING THERMOPLASTIC COMPOSITE AND HONEYCOMB CORE
A manufacturing method for manufacturing a welded thermoplastic composite and honeycomb core structure is provided. A thermoplastic composite and honeycomb structure is generated by positioning a first thermoplastic composite skin on a support structure, positioning a first thermoplastic film over the first thermoplastic composite skin, positioning a honeycomb core over the first thermoplastic film, positioning a second thermoplastic film is positioned over the honeycomb core, and positioning a second thermoplastic composite skin over the second thermoplastic film. The second thermoplastic composite skin is ultrasonically welded to the honeycomb core. The thermoplastic composite and honeycomb structure is then flipped over, and the first thermoplastic composite skin is then ultrasonically welded to the honeycomb core.
B29C 65/08 - Joining of preformed partsApparatus therefor by heating, with or without pressure using ultrasonic vibrations
B29C 65/00 - Joining of preformed partsApparatus therefor
B29K 105/12 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of short lengths, e.g. chopped filaments, staple fibres or bristles
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
B32B 3/12 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
B32B 27/08 - Layered products essentially comprising synthetic resin as the main or only constituent of a layer next to another layer of a specific substance of synthetic resin of a different kind
B32B 27/12 - Layered products essentially comprising synthetic resin next to a fibrous or filamentary layer
B32B 27/28 - Layered products essentially comprising synthetic resin comprising copolymers of synthetic resins not wholly covered by any one of the following subgroups
65.
DELAMINATION AND EDGE DAMAGE REPAIR ON THERMOPLASTIC COMPOSITES
A method of repairing a thermoplastic composite material is disclosed herein. The method includes placing the thermoplastic composite material on a supporting anvil, placing an energy transmission material on top of the thermoplastic composite material, and applying an ultrasonic welder to the thermoplastic composite material to consolidate and repair the thermoplastic composite material. Another method of repairing a thermoplastic composite material is disclosed herein. The method includes placing an energy transmission material on a supporting anvil, placing the thermoplastic composite material on top of the energy transmission material, and applying an ultrasonic welder to the energy transmission material to consolidate and repair the thermoplastic composite material.
A fuel delivery system for a gas turbine engine includes a fuel source and a main fuel pump configured to deliver a first flow of fuel to a combustor assembly of the gas turbine engine under a first fuel demand operating condition of the gas turbine engine. A secondary fuel pump is arranged in a fluidly parallel relationship with the main fuel pump. The secondary fuel pump is configured to deliver a second flow of fuel to the combustor assembly under a fuel demand second operating condition, different from the first fuel demand operating condition of the gas turbine engine.
A system can include a chassis and a multilayer structure disposed within the chassis, the multilayer structure configured to attract and electrically isolate an arc. The multilayer structure can include one or more outer layers configured and adapted to attract the arc and an inner layer configured and adapted to electrically isolate the arc. The one or more outer layers can include a first outer layer and a second outer layer. The inner layer can be sandwiched between the first outer layer and the second outer layer.
Hamilton Sundstrand Space Systems International, Inc. (USA)
Inventor
Channegowda, Parikshith
Dwari, Suman
Riar, Baljit
Futrell, Michael Anthony
Abstract
An alternating current to direct current (AC to DC) power converter assembly that converts a plurality of low voltage alternating current (AC) inputs into a high voltage DC power output. The converter includes two or more AC to DC power converters, each of the two or more AC to DC power converters including: a low power AC power input configured to receive an AC input from a low power AC power source; and a low power DC power output. The converter also includes two or more isolated DC to DC power converters, each DC to DC power converter electrically coupled at least one of the AC to DC power converters, wherein each DC to DC power converter includes an output and wherein each of the DC to DC power converters are connected in series to produce the high power DC power output.
An air cycle system for a gas turbine engine includes a heat exchanger having an air cycle inlet. An air cycle machine includes an air cycle machine outlet and an annular flexible interface coupling connecting the air cycle inlet to the outlet. The flexible interface coupling includes a receiving portion having a flared region across which a diameter of a heat exchanger portion increases and a landing portion across which the diameter of the heat exchanger portion is maintained. An air cycle machine portion is received in the receiving portion and includes an outlet flange and a diffuser radially inward of the outlet flange. The outlet flange includes a radially outward facing surface contacting a radially inward facing surface of the landing portion. The diffuser is configured to move axially and radially relative to the outlet flange.
A decentralized scheduler node for an unstable network of heterogenous nodes collects status information including a resource capacity of each of a network of nodes with which it is in communication. For each current computation job in its input queue, the scheduler node determines which connected nodes have suitable resource capacity to execute the current job and a reliability of each suitable node based on statistical evaluation of its historical availability for job deployment. From the set of suitably powerful and reliable candidate nodes, the scheduler node selects a candidate node of sufficient resource capacity for deployment of the current job based on the probability of a subsequent job appearing during the execution time of the current job, the subsequent job having an equivalent or greater resource requirement and thus at risk of waiting in the input queue if the selected node is required for executing the subsequent job.
An acoustic panel assembly includes an acoustic panel. The acoustic panel includes an acoustic core arranged along a transverse direction and a longitudinal direction. The acoustic core extends between and to an inner core side and an outer core side. The acoustic core includes a plurality of cell rows distributed transversely along the acoustic core. Each cell row of the plurality of cell rows includes a plurality of cells distributed longitudinally along the respective cell row of the plurality of cell rows. Each cell of the plurality of cells includes a first transverse panel, a second transverse panel, a first longitudinal panel, a second longitudinal panel, and an oblique panel. Each of the first transverse panel and the second transverse panel includes a plurality of apertures. The oblique panel extends transversely between and to the first transverse panel at the outer core side and the second transverse panel at the inner core side.
A method for forming an acoustic panel assembly for an aircraft propulsion system is provided that includes: forming a plurality of cell rows of an acoustic core by, for each cell row of the plurality of cell rows, cutting and folding a sheet to form each cell row with a plurality of cells, and each cell includes a first transverse panel, first and second longitudinal panels and an oblique panel, and the first and second longitudinal panels extend transversely from the first transverse panel; positioning the cell rows on an inner skin extending circumferentially about an axial centerline; attaching the longitudinal panels of a cell to the oblique panel of that cell, and attaching each cell row of the plurality of cell rows to at least one other cell row to form the acoustic core.
A gas turbine engine is provided that includes an annular engine flange, an annular center body, and a plurality of fastener assemblies. The annular engine flange has an engine flange attachment flange (EFAF) that includes a plurality of EFAF apertures. Each EFAF aperture has an EFAF aperture inner diameter. The center body assembly has a center body assembly attachment flange (CBAAF). The CBAAF includes a plurality of CBAAF apertures, and each CBAAF aperture has an CBAAF aperture inner diameter. Each fastener assembly includes a fastener and first and seconds. The fastener has a collar that has an outer radial surface. In assembled form, the collar of each fastener assembly is disposed within a respective CBAAF aperture and is in contact with the engine flange, the first nut fixes the fastener to the engine flange, and the second nut fixes the center body assembly attachment flange to the engine flange.
An assembly for an aircraft propulsion system includes an exhaust center body. The exhaust center body includes an inner skin, a perforated outer skin, a first bulkhead, a second bulkhead and an acoustic chamber. The inner skin extends circumferentially about an axis. The inner skin extends axially along the axis between and connected to the first bulkhead and the second bulkhead. A radius from the axis to the inner skin changes as the inner skin extends axially along the axis. The perforated outer skin extends circumferentially about the inner skin. The perforated outer skin extends axially along the axis between and is connected to the first bulkhead and the second bulkhead. The acoustic chamber extends axially uninterrupted within the exhaust center body between the first bulkhead and the second bulkhead. The acoustic chamber extends radially within the exhaust center body between the inner skin and the perforated outer skin.
A vessel mounting system for a vehicle includes a first flexible strap configured to circumscribe the vessel in a first direction, a second flexible strap configured to circumscribe the vessel in a second direction such that the second flexible strap and the first flexible strap overlap in at least one location, a strap mating coupler securing the first flexible strap to the second flexible at the at least one location, and at least one coupling device connected to the first flexible strap configured to mate with a structure on the vehicle. Each of the first flexible strap and the second flexible strap includes a plurality of clamp sleeves connected in an end-to-end manner.
A62C 31/28 - Accessories for delivery devices, e.g. supports
A62C 3/08 - Fire prevention, containment or extinguishing specially adapted for particular objects or places in vehicles, e.g. in road vehicles in aircraft
A passive filter assembly can include a filter bowl configured to enclose a filter element therein, a fluid inlet in fluid communication with the filter bowl, a fluid outlet in fluid communication with the filter bowl downstream of the fluid inlet, and a filter cap disposed gravitationally below the filter bowl and configured to receive denser fluid components separated from a bulk fluid when the denser fluid components fall into the filter cap. The filter bowl can be shaped to allow the bulk fluid to swirl therein. The fluid inlet can be configured to cause the bulk fluid entering through the fluid inlet to swirl within the filter bowl to be centrifuged to separate one or more denser fluid components from the bulk fluid. The fluid outlet can be configured to receive a filtered flow downstream of a filter element.
An assembly for an aircraft propulsion system includes a translating structure and a thrust reverser. The thrust reverser includes a blocker door, an actuation linkage and a fairing. The blocker door is pivotally coupled to the translating structure. The blocker door includes a door surface and a channel projecting into the blocker door from the door surface. The door surface forms an outer peripheral boundary of a flowpath when the translating structure is stowed. The door surface projects into the flowpath when the translating structure is deployed. The actuation linkage is pivotally coupled to the blocker door. The actuation linkage is disposed in the channel when the translating structure stowed. The fairing projects away from the door surface into the flowpath. The fairing forms an aerodynamic cover over the channel when the translating structure is stowed.
An aircraft power system for power a plurality of loads of an aircraft includes a first secondary power distribution assembly (SPDA) network configured to manage electrical power delivered to a first load among the plurality of loads, and a second SPDA network configured to manage electrical power delivered to a second load among the plurality of loads. The aircraft power system further includes a synthetic load management system (SLMS) in signal communication with the first SPDA and the second SPDA. The SLMS is configured to reference at least one operational condition of the aircraft and historical data corresponding to the first load and the second load. The SLMS is configured to predict load demands of the of the first load and the second load operating at different operating conditions based on the historical data.
Thermal management systems include a vapor cycle and a liquid cycle sharing a common working fluid. The vapor cycle includes, along a vapor cycle flow path, a compressor and a condenser. The liquid cycle includes, along a liquid cycle flow path, a fluid driver, a load, a regulator valve, and a phase change material heat exchanger. A cold sink is thermally coupled to a heat load. A separator is configured to separate liquid and vapor portions of the working fluid and direct the liquid into the liquid cycle and the vapor into the vapor cycle. The separator is part of both the vapor cycle and the liquid cycle. The regulator valve controls a temperature of the working fluid within the liquid cycle at a location upstream of the phase change material heat exchanger to control a mode of operation of the phase change material heat exchanger.
F25B 43/04 - Arrangements for separating or purifying gases or liquidsArrangements for vaporising the residuum of liquid refrigerant, e.g. by heat for withdrawing non-condensible gases
F25B 13/00 - Compression machines, plants or systems, with reversible cycle
A heat exchanger includes an outer shell enclosing an interior space. An inlet extends through the outer shell and is in fluidic communication with the interior space. An outlet extends through the outer shell and is in fluidic communication with the interior space. At least one phase change element is inside the interior space and includes a core comprising a phase change material.
An acoustic panel assembly includes an acoustic panel including an acoustic core arranged along a transverse direction and a longitudinal direction. The acoustic core extends between and to an inner core side and an outer core side. The acoustic core includes a plurality of cell rows distributed transversely. Each cell row of the plurality of cell rows includes a plurality of cells distributed longitudinally along the respective cell row of the plurality of cell rows. Each cell of the plurality of cells includes a first transverse panel, a second transverse panel, a first longitudinal panel, a second longitudinal panel, and an oblique panel extending between the inner core side and the outer core side. Each cell row of the plurality of cell rows includes a primary folded sheet and a secondary folded sheet. Each of the primary folded sheet and the secondary folded sheet forms the first transverse panel, the first longitudinal panel, and the second longitudinal panel for each cell of the plurality of cells.
An assembly for an aircraft propulsion system includes a fixed structure, a translating structure and a thrust reverser. The thrust reverser includes a blocker door, a structure link and a door link. The blocker door is pivotally coupled to the translating structure. The structure link includes a first structure link arm, a second structure link arm and a structure link mount connected to the first structure link arm and the second structure link arm. The first structure link arm and the second structure link arm are each pivotally coupled to the fixed structure. The first structure link arm and the second structure link arm laterally converge towards one another as the first structure link arm and the second structure link arm extend longitudinally towards the structure link mount. The door link extends longitudinally between and is pivotally coupled to the structure link mount and the blocker door.
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
83.
THRUST REVERSER WITH BLOCKER DOOR OPENING CONTROL DEVICE(S)
An assembly is provided for an aircraft propulsion system. This assembly includes a fixed structure, a translating structure and a thrust reverser. The translating structure is configured to translate between a stowed position and a deployed position. The thrust reverser includes a blocker door, an actuation linkage and a spring cartridge. The blocker door is pivotally coupled to the translating structure. The actuation linkage operatively couples the blocker door to the fixed structure. The spring cartridge is coupled to the blocker door and the translating structure. The spring cartridge is configured to bias the blocker door closed.
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
In accordance with at least one aspect of this disclosure, a system includes, a collection arm configured to collect an aerosol sample from a cloud and a detection module operatively connected to the collection arm configured to analyze a composition of the sample from the cloud. In certain embodiments, one or more of the collection arm and/or the detection module can be configured to couple to a mobile platform, including for example, a land vehicle, aircraft, or watercraft. In certain embodiments one or more of the collection arm and/or the detection module can be configured to couple to a stationary structure, for example a building
A deployable drains mast for draining fluids from a propulsion system is provided. The deployable drains mast includes a bordered structure. The bordered structure includes a plurality of exterior walls forming a cavity. The bordered structure further includes at least one drain opening to the cavity located at a first end of the bordered structure. The at least one drain opening configured to receive a drain line from a component of a core compartment of the propulsion system. The bordered structure further includes at least one drain exit from the cavity located at a second end of the bordered structure opposite the first end. The drain exit configured to expel the fluid.
A method for controlling a fuel system for a gas turbine engine is disclosed. The method includes directing fuel from an outlet of a main pump to an inlet of a fuel oil cooler. Fuel is directed from an outlet of the fuel oil cooler to a fuel control. The fuel control is in fluidic communication with a burner of the gas turbine engine. Fuel is directed from the outlet of the main pump to the fuel control through a fuel-oil-cooler bypass valve whenever an augmentor pump of the fuel system is actively pumping fuel to an augmentor of the gas turbine engine. The fuel-oil-cooler bypass valve forms a bypass flow path around the fuel oil cooler.
An ion generator includes a high voltage source, a body defining a central axis, and multiple arms extending from the body. The body has a primary conductive line electrically coupled to the high voltage source, and a first insulating covering surrounding the primary conductive line. Each arm has an emitter array and a secondary conductive line. The emitter array is disposed at a distal end of the arm relative to the body. The secondary conductive line is electrically coupled to the primary conductive line at a proximal end of the arm relative to the body and extends to the emitter array. The arms are distributed about the central axis, such that the orientations of the emitter arrays and the connection of each arm to the central body are distributed helically, spirally, or symmetrically with respect to other arms, relative to the central axis.
An apparatus is provided for an aircraft which includes an aircraft component. The aircraft component includes a first plate section, a second plate section and an elastic expansion section laterally between the first plate section and the second plate section. The elastic expansion section is configured to elastically deform to increase a lateral width between the first plate section and the second plate section. The aircraft component is formed from at least an elastomeric matrix and a fiber layer at least partially embedded within the elastomeric matrix. A bead is formed in the fiber layer laterally between a first portion of the fiber layer and a second portion of the fiber layer. The first portion of the fiber layer is disposed in the first plate section. The second portion of the fiber layer is disposed in the second plate section. The bead is disposed in the elastic expansion section.
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
89.
TURBO CABIN AIR COMPRESSOR SURGE RELIEF ENERGY RECOVERY
An aircraft air supply system for generating pressurized air includes a compressor configured to receive and pressurize a flow of outside air, a turbine operatively coupled to the compressor by a shaft and configured to drive the compressor, a fluid pathway fluidly connecting the compressor to an environmental control system pack, an outflow pathway fluidly connecting a cabin of the aircraft to the turbine, a surge relief pathway fluidly connecting the compressor to the outflow pathway and the turbine, and a surge relief valve disposed within the surge relief pathway. In a first operational state, the surge relief valve is open to allow a flow of surge relief air to flow from the compressor to the outflow pathway via the surge relief pathway, the surge relief air further flowing through the turbine.
B64D 13/02 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being pressurised
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
A propulsion system includes a gas turbine engine and a nacelle. The nacelle has inner and outer nacelle portions, an upper bifurcation, and a fluid drain system. The inner nacelle portion is disposed radially outside of the gas turbine engine. The outer nacelle portion is disposed radially outside of the inner nacelle portion. An annular bypass duct is disposed between the inner and outer nacelle portions. The upper bifurcation extends through the bypass duct between the inner and outer nacelle portions. The fluid drain system includes a catch tray engaged with a drain mast. The catch tray is disposed radially inside of an inner nacelle wall. The drain mast extends through the bypass duct between the catch tray and a drain mast outer radial end. The outer radial end of the drain mast is engaged with the outer nacelle portion. The drain mast includes first and second fluid passages.
F01D 25/32 - Collecting of condensation waterDrainage
91.
Gear pump with suction housing element providing a tight seal between suction and high-pressure chamber to increase pump efficiency and method of providing tight seal
A gear pump includes a pump housing, a two meshed with a driven gear, a suction housing, and a suction cavity. The suction housing includes a body portion having first and second sealing disposed adjacent to outer diameters of the gears. A suction chamber wall is disposed between the first and second sealing surfaces and a sealing land is adjacent to a planar running surface of the pump housing. A flange of the suction housing has a third sealing surface disposed in contact with gear faces of the gears. The suction cavity is open to the inlet and defined in part by the suction chamber wall.
F04C 27/00 - Sealing arrangements in rotary-piston pumps specially adapted for elastic fluids
F04C 18/18 - Rotary-piston pumps specially adapted for elastic fluids of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing of other than internal-axis type with toothed rotary pistons with similar tooth forms
92.
SYSTEM FOR SUPPLYING SOURCE AIR TO AN AIR SEPARATION MEMBRANE OF A FUEL INERTING SYSTEM
A system supplying air to an ASM of an aircraft inerting system, having: a first compressor, a turbine and a motor-generator coupled to each other; a second compressor coupled to the turbine and ASM; a first flow-path receiving cabin air and having: a first branch coupled to the first compressor; and a second branch coupled to the turbine, the motor-generator operates in a generator mode when pressure in the first flow-path is above a threshold; a second flow-path coupled between the first compressor and second compressor; a third flow-path coupled between the second compressor, a fuel tank and ASM; a first heat exchanger coupled to the second branch of the first flow-path to heat flow through the second branch before providing it to the turbine; and a second heat exchanger coupled to the second flow-path between the first compressor and second compressor to cool the flow through the second flow-path.
In accordance with at least one aspect of this disclosure, a modular valve system includes, at least a first valve. The first valve can be configured to connect to one or more additional valves. The first valve includes, a first housing having a first inlet and a first outlet with a cylindrical flow path through the housing defined between the first inlet and the first outlet along a flow axis, where a diametral plane is defined diametrically spanning the cylindrical flow path.
F16K 1/22 - Lift valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces with pivoted closure members with pivoted discs or flaps with axis of rotation crossing the valve member, e.g. butterfly valves
F16K 27/02 - Construction of housingsUse of materials therefor of lift valves
F16K 31/46 - Mechanical actuating means for remote operation
In accordance with at least one aspect of this disclosure, a limiting system for defining a rotational limit of a valve disc of a butterfly valve can include, a crank configured to be disposed on a terminal end of a valve shaft and configured to connect to a drive linkage to drive the crank and rotation of the valve disc. The crank can include a crank arm extending radially outward from the shaft. The crank stop can be configured to contact a portion of the second connecting flange of the first valve to physically limit rotation of the crank and the valve disc within a predefined rotational quadrant.
F16K 31/52 - Mechanical actuating means with crank, eccentric, or cam
F16K 1/22 - Lift valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces with pivoted closure members with pivoted discs or flaps with axis of rotation crossing the valve member, e.g. butterfly valves
In accordance with at least one aspect of this disclosure, a retaining clip system for retaining an alignment of a valve disc within a valve housing can include, a c-shaped retaining clip configured to be disposed on a shaft of the valve and a shim pack including a plurality of shims configure to axially bound the retaining clip on the shaft.
F16K 1/22 - Lift valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces with pivoted closure members with pivoted discs or flaps with axis of rotation crossing the valve member, e.g. butterfly valves
96.
MULTIPLEXED BI DIRECTIONAL CONVERTERS FOR HYBRID ELECTRIC AIRCRAFT PROPULSION
A system includes a low pressure machine, a high pressure machine, a motor controller device, a first set of switches configured to selectively couple the low pressure machine to an inverter or a rectifier included in the motor controller device, based on a control signal, and a second set of switches configured to selectively couple the high pressure machine to the inverter or the rectifier, based on the control signal.
A LLC voltage converter for converting a DC input voltage to a DC output voltage. The LLC voltage converter includes: a transformer having an input winding and an output winding, a controller and a current sensor. The current sensor measures a primary current through the input winding of the transformer and provides a measurement of the primary current to the controller. The controller determines when a secondary current, through the output winding of the transformer, is substantially zero based on the measurement of the primary current and a maximum value of the primary current.
H02M 3/335 - Conversion of DC power input into DC power output with intermediate conversion into AC by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate AC using devices of a triode or a transistor type requiring continuous application of a control signal using semiconductor devices only
A heat exchange fin pack includes a plurality of rows of channel sections, each row comprising a plurality of adjacent legs, with each pair of adjacent legs connected to each other by, alternately, an upper crest part and a lower peak part. The legs and the upper crest part or the lower peak part define therebetween a channel section for fluid flow therethrough. The channel sections of each row are offset in a direction substantially transverse to the direction of flow from the adjacent channel sections of adjacent rows, thus forming a lanced offset fin pack in which the channel sections of adjacent rows combine to form staggered flow channels. Each channel section is formed to have a region of restricted diameter compared to another or other regions of that channel section.
A cooling structure for a rotary electric machine, the structure includes an annular radiator body defining an axis X between a first end and a second end, the annular body having a radially inner wall and a radially outer wall and a plurality of channels defined between the radially inner wall and the radially outer wall. Each channels extends from the first end to the second end, each channel having a radially varying profile along the length of the channel to interrupt the linear flow of fluid along the channel and to cause continuous changes in flow direction as the fluid flows from one end of the channel to the other.
The present disclosure relates to a fire suppression composition comprising a hydrobromofluoroalkene compound of formula CnX2n, where: n is an integer from 2 to 6; each X is independently selected from the group consisting of Br, F, Cl and H, provided at least one X is Br; and the compound does not contain —CF3 or —CF2—.
