A method for braking an aircraft is disclosed herein. The method includes receiving, by a brake controller, a first signal from a position sensor of a first pedal, receiving, by the brake controller, a second signal from a pedal sensor of the first pedal, determining, by the brake controller, that the pedal is being pressed based on the first and second signals, and sending, by the brake controller, an instruction to apply a brake pressure in response to the determination that the pedal is being pressed.
An ice protection system for an aircraft component includes a plurality of heaters. The aircraft component has at least two section and a junction area. At least one of the heaters is an H-shape carbon allotrope heater designed to apply heat to the junction area and prevent ice accumulation in the junction area.
B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
H05B 3/14 - Heating elements characterised by the composition or nature of the materials or by the arrangement of the conductor characterised by the composition or nature of the conductive material the material being non-metallic
A device for extracting a deeply embedded helical coil is provided. The device includes a shaft, the shaft comprising a proximal end and a distal end; and a blade coupled to the distal end of the shaft, wherein the blade is configured to traverse into a mounting hole to engage the deeply embedded helical coil free of contact with a side of the mounting hole and wherein the deeply embedded helical coil is at least three to five thread pitches below a surface of the mounting hole.
B25B 27/30 - Hand tools or bench devices, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for for assembling objects other than by press fit or detaching same positioning or withdrawing springs, e.g. coil or leaf springs
A method of forming a metallic coating a workpiece is disclosed herein. The method includes receiving a sacrificial deposition rod formed of a first material, receiving a workpiece of a second material, forming a coating of the first material from the sacrificial deposition rod onto the workpiece, the coating having a first thickness, and machining the coating to a second thickness that is less than the first thickness.
A composite drive shaft includes a web-based body defining a longitudinal axis. The web-based body has a first composite layup end section, a second composite layup end section that is opposite to the first composite layup end section, a first spiral composite element extending between the first composite end section and the second composite layup end section, and a second spiral composite element extending between the first composite end section and the second composite layup end section. The first spiral composite element and the second composite spiral element are embedded into the first composite layup end section, and the second composite layup end section. The first composite spiral element and the second composite spiral element are arranged in a bi-directional orientation relative to the longitudinal axis. The first spiral composite element and the second spiral composite element are arranged at pre-determined angles and possess a uni-directional fiber-reinforced polymer-matrix composite structure.
A system is provided for translating sections of an icing wind tunnel to expand a size range of water droplets. The system includes: a set of actuators coupled to a set of sections of the icing wind tunnel; and a controller coupled to the set of actuators, wherein the controller is configured to: receive data relating to a water droplet generated within the icing wind tunnel; determine a directional impact on a model within the icing wind tunnel based upon the data relating to the water droplet; and adjust at least one of the set of sections of the icing wind tunnel in at least one of an up or a down direction in a subsequent test.
A testing device includes a first member to be positioned on one surface of a part to be tested. A second member to be positioned on an opposed surface of the part to be tested. One of the first and second members have an ultrasonic transmitter and the other has an ultrasonic receiver. At least one of the first and second members have at least one magnetic element and the other of the first and second member have at least one magnetic or at least one ferromagnetic metallic element such that when one of the first and second members moves along the surface of the tested part the other of the first and second members will move along an opposed surface with the one of the members.
A method of testing a part includes placing a first member on a part to be tested. A second member is placed on an opposed surface of the part. One of the members has an ultrasonic transmitter and the other has an ultrasonic receiver. At least one of the members has at least one magnetic element and the other has at least one of a magnetic element or a ferromagnetic metallic element which is attracted to magnets. One of the members moves along the surface of the part such that magnetic attraction causes the other to move along the opposed surface of the part with the one of the members. A controller causes an ultrasonic signal to be sent from the transmitter through the part to be tested which is received by the receiver and then analyzed by an ultrasonic testing machine.
G01N 29/22 - Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object - Details
A heating arrangement for a valve includes a thermally conductive heating wire embedded within a body of the valve. Also provided is a valve body formed by additive manufacture and having a thermally conductive heating wire embedded therein to which electric power is applied to cause the thermally conductive heating wire to generate heat in the valve body. A method of manufacture is also provided.
A flexible diaphragm coupler includes a flange having a central support and a flange element extending radially outwardly from the central support. The flange element includes a rim portion having an axially facing surface. The axially facing surface includes a plurality of interlock elements. A diaphragm member is disposed between the first flange and the second flange. The diaphragm member includes a diaphragm element. The diaphragm element includes a central support element and a disc member extending radially outwardly from the central support element. The disc member includes a rim element having an axially facing surface portion including a plurality of interlock members that connect with the plurality of interlock elements.
B64D 35/08 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the transmission being driven by a plurality of power plants
F16D 1/02 - Couplings for rigidly connecting two coaxial shafts or other movable machine elements for connecting two abutting shafts or the like
F16D 3/16 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts
11.
ELECTRONIC PULSE INJECTION SYSTEM FOR AN ICING WIND TUNNEL
A system is provided for dispersing supercooled liquid water in an icing wind tunnel. The system includes a spray bar; a spray nozzle coupled to the spray bar; a pressure control valve coupled to the spray bar; and a controller coupled to the pressure control valve and the spray nozzle. The controller is configured to receive input identifying a selected liquid water content and a selected water droplet size for dispersing the supercooled liquid water in the icing wind tunnel; configure an injector duty cycle of the spray nozzle to generate the selected liquid water content; and configure the pressure control valve to generate the selected water droplet size, wherein configuring the spray nozzle and the pressure control valve disperses the supercooled liquid water in the icing wind tunnel.
B05B 12/06 - Arrangements for controlling delivery; Arrangements for controlling the spray area for controlling time, or sequence, of delivery for effecting pulsating flow
B05B 12/08 - Arrangements for controlling delivery; Arrangements for controlling the spray area responsive to condition of liquid or other fluent material discharged, of ambient medium or of target
A system for releasing a blowout panel and softcover release of an evacuation slide in an aircraft is provided. The system includes a first actuator, a second actuator; and a controller. The controller is configured to receive an indication that an evacuation event has begun; and, responsive to receiving the indication of the evacuation event beginning: send a first signal to the first actuator that magnetizes a first magnetostriction material within the first actuator, thereby releasing the blowout panel of a packboard compartment in which the evacuation slide is present; and send a second signal to the second actuator that magnetizes a second magnetostriction material within the second actuator, thereby releasing a key-loop of lacing associated with the softcover in which the evacuation slide is present in the packboard compartment.
A shaft assembly includes a composite tube and an impact shield. The composite tube has a longitudinal centerline axis and the impact shield may be disposed around the composite tube and may extend along a length of the composite tube. A gap may be defined between the composite tube and the impact shield. Generally, shaft assembly is configured to inhibit impact damage to the composite tube and/or facilitate visual detection of damage from impacts. The shaft assembly may further include a shock absorbing sleeve disposed in the gap between the composite tube and the impact shield.
A system is provided for measuring a thickness of a preform material. The system includes a material detection device and a controller, wherein the controller is configured to: receive, from the material detection device, a signal indicating a presence of the preform material; responsive to receiving the signal, receive a first set of measurements along at least a portion of a length of the preform material; convert the first set of measurements into a second set of measurements; and record the second set of measurements.
A system for controlling tension on textile material used in forming a preform is disclosed herein. The system includes a sensor and a controller, where the controller is configured to: receive a signal, from the sensor, indicative of a compressive force applied by the textile material feeding into the system; determine whether the compressive force is within range of a setpoint of the tension for the textile material; and responsive to the compressive force being outside the range, send a command of at least one of an increase or a decrease of the tension on the textile material.
A brake system and method of braking for an aircraft are provided. The brake system includes a primary brake control unit and an alternate brake control unit. In response to the primary brake control unit being placed in an active mode, the primary brake control unit is configured to send data on a set of channels to control brake operation of at least one brake, while the alternate brake control unit is configured to monitor brake temperature on another, separate set of channels coupled to at least one brake temperature sensor associated with the at least one brake.
B60T 8/88 - Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force responsive to a speed condition, e.g. acceleration or deceleration with failure responsive means, i.e. means for detecting and indicating faulty operation of the speed responsive control means
B60T 8/17 - Using electrical or electronic regulation means to control braking
B60T 8/171 - Detecting parameters used in the regulation; Measuring values used in the regulation
B60T 8/92 - Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force responsive to a speed condition, e.g. acceleration or deceleration with failure responsive means, i.e. means for detecting and indicating faulty operation of the speed responsive control means automatically taking corrective action
A heat shield panel comprising an inner heat shield layer and an outer heat shield layer, the inner heat shield layer and the outer heat shield layer each having two outer edges wherein the outer edges of the inner heat shield layer and the outer edges of the inner heat shield layer are substantially aligned and are affixed to each other to form heat shield panel edges, and wherein the inner heat shield layer is formed of two or more segments each having an inner edge, the inner edges of the segments being arranged to move relative to each other.
A portable container for being loaded into and unloaded from a compartment of an aircraft, the portable container comprises a power source comprising one or more rechargeable batteries and coupling circuitry configured to electrically couple one or more of the rechargeable batteries to an electrical connector, and a housing comprising the power source, wherein the power source is operable to discharge one or more of the rechargeable batteries and transmit a discharge current via the electrical connector, and wherein the electrical connector comprises an interface portion operable to be physically connectable with a corresponding interface portion of another electrical connector to electrically couple the electrical connector to the another electrical connector.
A rinse device has a housing part and a rinse head. The rinse head has a plurality of openings through which the pressurised fluid is ejected. The housing part includes an outer housing tube and an inner piston movable axially relative to the outer housing tube, and a sealed air-filled cavity defined therebetween, and a spring attached at a first end to the outer housing tube and at a second end to the piston, and wherein the rinse head is attached to the piston at the second end of the housing part, such that the spring is biased to hold the piston at a first axial position relative to the outer housing tube until a force exerted by the pressure of the fluid inside the housing part exceeds the sum of an axial force of the spring and the force from the pressure of the air in the air cavity.
A torque plate barrel for use with a brake system is disclosed herein. The torque plate barrel includes a barrel body having an outer diameter, an inner diameter, and an axial length extending from a first end to an opposing second end, wherein the inner diameter varies along the axial length and the outer diameter is fixed along the axial length.
A method of fabricating a composite component, includes forming a fibrous preform by forming a first ceramic particle layer over a first textile layer, the first ceramic particle layer having a first group of ceramic particles, disposing a second textile layer over the first ceramic particle layer, forming a second ceramic particle layer over the second textile layer, the second ceramic particle layer having a second group of ceramic particles, and disposing a third textile layer over the second ceramic particle layer. The method further includes densifying the fibrous preform.
C04B 35/622 - Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
C04B 35/563 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides based on boron carbide
C04B 41/91 - After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone of only ceramics involving the removal of part of the materials of the treated articles, e.g. etching
22.
SOLENOID/MAGNETIC HOLD BRAKE WITH POWER OFF MAGNET HOLD FUNCTION
A power drive unit (PDU) having a magnetic hold brake for use in an aircraft is disclosed herein. The PDU includes a wheel configured to convey cargo through a portion of the aircraft, a motor coupled to the wheel, a brake disk, a solenoid configured to apply a first force to move the brake disk in a first direction to resist rotation of the motor, wherein the solenoid is further configured to apply a second force to move the brake disk in a second direction opposite the first direction to allow the motor to rotate, and a magnet configured to apply a third force to the brake disk, the third force being in the first direction to apply a drag force to the motor.
B64D 9/00 - Equipment for handling freight; Equipment for facilitating passenger embarkation or the like
F16D 55/02 - Brakes with substantially-radial braking surfaces pressed together in axial direction, e.g. disc brakes with axially-movable discs or pads pressed against axially-located rotating members
F16D 63/00 - Brakes not otherwise provided for; Brakes combining more than one of the types of groups
F16D 65/18 - Actuating mechanisms for brakes; Means for initiating operation at a predetermined position arranged in or on the brake adapted for drawing members together
A piston assembly for engaging two selectively engageable parts comprising: a housing defining a piston cylinder; a piston; and an adjuster assembly comprising: a piston stroke limiter configured to limit the length of a return stroke of the piston from an extended stroke position and a retracted stroke position, the piston stroke limiter comprising a spring and a spring guide; and a crushable body, acting between the piston and the piston stroke limiter, the crushable body being arranged to reduce in axial length when a length of an extension stroke exceeds a length of a retraction stroke to maintain the length of the return stroke; wherein the crushable body comprises an inner crushable thin-walled tube surrounding at least a portion of the piston and an outer crushable thin-walled tube mounted around and radially outwards of the inner crushable tube.
A hybrid water storage system for an aircraft includes separate variable volumes for respectively storing/holding potable water and gray water occupying a common container. The hybrid water storage system is generally configured to draw potable water from a first variable volume in order to provide fresh water to one or more aircraft appliances (e.g., sinks, showers, ice-makers, etc.), and the used potable water (i.e., the potable water that is collected in drains from the aircraft appliances), referred to herein as gray water, is routed to a second variable volume that occupies the same container as the first variable volume.
A metallic part is disclosed. The part may comprise a functionally graded monolithic structure characterized by a variation between a first material composition of a first structural element and a second material composition of at least one of a second structural element. The first material composition may comprise an alpha-beta titanium alloy. The second material composition may comprise a beta titanium alloy.
An actuator is disclosed herein. The actuator includes a drive body including a bottom surface, the bottom surface having a first side and an opposing second side, a magneto strictive material disposed within the drive body and contacting the first side of the bottom surface of the drive body, a solenoid disposed within the drive body and surrounding the magneto strictive material, a drive rod extending through the magneto strictive material and through the bottom surface of the drive body, and a spring disposed adjacent the second side of the bottom surface of the drive body, wherein the drive rod extends through the spring.
A wheel assembly is disclosed herein. The wheel assembly includes a torque bar extending in a first direction, a retainer plate coupled to the torque bar, the retainer plate having a first side formed into a first U-channel, the first U-channel formed in a second direction perpendicular to the first direction, a heat shield panel having a first side formed into a second U-channel, the second U-channel of the heat shield panel being formed in a third direction opposite the second direction, and a retention clasp formed from a portion of the heat shield panel, the retention clasp formed over an open end of the second U-channel.
A device for extracting a deeply embedded helical coil is provided. The device includes a shaft, the shaft comprising a proximal end and a distal end; and a blade coupled to the distal end of the shaft, wherein the blade is configured to traverse into a mounting hole to engage the deeply embedded helical coil free of contact with a side of the mounting hole and wherein the deeply embedded helical coil is at least three to five thread pitches below a surface of the mounting hole.
B23P 11/00 - Connecting or disconnecting metal parts or objects by metal-working techniques, not otherwise provided for
B25B 27/30 - Hand tools or bench devices, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for for assembling objects other than by press fit or detaching same positioning or withdrawing springs, e.g. coil or leaf springs
A method includes imaging a first graybody with a focal plane array (FPA), wherein the first graybody has a first emissivity, and imaging a second graybody having a lower emissivity than the first graybody. The method includes using data captured while imaging the first and 5 second graybodies to perform non-uniformity correction (NUC) of the FPA.
A piston assembly is disclosed herein. The piston assembly includes a piston having a first end, an opposing second end, and a sidewall extending from the first end to the second end, the piston further including a cavity at least partially defined by the sidewall, a spring guide having a first end and an opposing second end, the spring guide disposed within the cavity of the piston and adjacent the sidewall, an insulator having a first portion extending from the second end of the piston and a second portion disposed within the piston, an insulator shield disposed adjacent the first portion of the insulator, and a component coupled to the second end of the spring guide, the component being offset from the insulator shield by a distance.
F16D 65/84 - Features relating to cooling for disc brakes
F16D 65/18 - Actuating mechanisms for brakes; Means for initiating operation at a predetermined position arranged in or on the brake adapted for drawing members together
A cable cutter assembly for an aircraft hoist is disclosed, and includes an actuator assembly (e.g., at least one pressurized fluid cavity, a first outlet port, and a solenoid that includes a coil and an armature). The armature is movable between closed and open positions relative to the first outlet port (e.g., via an actuation force), with the armature engaging the first outlet port for the closed position (e.g., a valve seal incorporated by the armature) and being spaced from the first outlet port for the open position. A cutter body includes a cutter body cavity that is fluidly connected with the first outlet port. A cutter is movably disposed within the cutter body cavity. Disposing the armature in the open position (e.g., via energizing the coil) fluidly connects the pressurized fluid cavity with the cutter body cavity to move the cutter in a cable cutting direction.
A friction disk may comprise a first wear surface formed from a carbon fiber-carbon matrix composite material. A wear plug may be located in an opening defined by the carbon fiber-carbon matrix composite material. The wear plug may extend axially from the wear surface. The wear plug may comprise a rod or a particulate.
B29C 70/54 - Component parts, details or accessories; Auxiliary operations
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
A method of controlling an aircraft braking system includes initiating the aircraft braking system by receiving a first brake command at a primary system to actuate braking via the primary system, receiving the first brake command at an alternate system, and in response to the primary system losing an ability to control a brake, controlling the braking of the brake via the alternate system.
B60T 8/94 - Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force responsive to a speed condition, e.g. acceleration or deceleration with failure responsive means, i.e. means for detecting and indicating faulty operation of the speed responsive control means automatically taking corrective action on a fluid pressure regulator
A heat shield for a wheel assembly may comprise a plurality of heat shield segments, a plurality of shield bumpers may be coupled to a radially outward surface of each heat shield segment, and a plurality of heat shield retainers coupled to the plurality of heat shield segments. Each heat shield retainer may include a first bumper standoff and a second bumper standoff located over a first radially outward surface of the heat shield retainer. Each of the first bumper standoff and the second bumper standoff may comprise an attachment portion coupled to the first radially outward surface of the heat shield retainer and a bumper portion defining a bumper opening.
An aircraft braking system is disclosed that includes a first pedal, first and second pedal sensors for the first pedal, a first brake control unit (e.g., primary), and a separate second brake control unit (e.g., secondary). The first pedal position sensor is operatively interconnected with one of the first brake control unit and the second brake control unit, while the second pedal position sensor is operatively interconnected with the other of the first brake control unit and the second brake control unit. Outputs from these pedal sensors may be used to control operation of the aircraft braking system in at least some fashion.
A clip assembly for a rotor disk of a brake assembly, the clip assembly comprising: a half-cap clip arranged to fit over an end of a lug of the rotor disk, the half-cap clip having two opposing sides and an end across the two opposing sides, and a top and bottom surface, the top and bottom surfaces, the sides and the end defining a receptacle to receive the rotor lug, the half-cap clip having an aperture in each of the sides; and a pin having a pin head and a pin body extending from the pin head along an axis (A) of the pin, the pin having a cross-section defining an elongate shape having rounded ends; and wherein the apertures in the sides of the half-cap clip are shaped to receive the pin body.
A retainer for connecting two panels of a heat shield assembly, the retainer comprising: a central elongate panel having a length l and a width w, a top end, a bottom end and first and second long sides extending from the top end to the bottom end; a first side panel extending along the first long side of the central elongate panel and a second side panel extending along the second long side of the central elongate panel; and wherein reinforcement features are applied to a surface of the central elongate panel.
A seal plate disposable between a pair of preforms for chemical vapor infiltration is disclosed. The seal plate may include a plurality of first channels that extend completely through the seal plate and that are located between an inner annulus and outer annulus of the seal plate. The seal plate may further include a plurality of second channels that also extend completely through the seal plate and that are located also between an inner annulus and outer annulus. The first channels may differ from the second channels in at least one respect (e.g., the first channels may be of a different width than the second channels). The first channels may provide an inlet for the chemical vapor infiltration of the preform, while the second channels may provide an outlet for the chemical vapor infiltration of the preform.
A method for forming an oxidation protection system on a composite structure may comprise applying a ceramic layer slurry to the composite structure and heating the composite structure to form a ceramic layer on the composite structure. The ceramic layer slurry may comprise aluminum and silicon carbide powder in a sol. The ceramic layer may comprise alumina, silicon carbide and silicon oxycarbide.
C04B 35/622 - Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
C04B 35/565 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides based on silicon carbide
C04B 41/50 - Coating or impregnating with inorganic materials
A bidirectional latching device for securing a cargo in a vehicle may have a latch catch assembly and a latch head. The latch catch assembly may selectably engage with the latch head. When engaged with the latch head, the latch catch assembly may lock the latch head in position to resist movement and the latch head may secure the cargo in the vehicle. When disengaged from the latch head, the latch catch assembly may release the latch head and the latch head may move to a stowed position. The latch catch assembly may lock the latch head to resist movement in one or more directions of movement. The latch head may be shaped to secure the cargo in the vehicle in at least two directions. Thus, cargo may be secured more efficiently by requiring a reduced number of latch devices because the disclosed latch device is bidirectional.
A tray connector is disclosed herein. The tray connector includes a first side rail, a second side rail, parallel to the first side rail, a cross member extending from the first side rail to the second side rail, a pin extending from within the cross member and through the first side rail, and a tab configured to retract the pin.
A method of manufacturing a carbon structure can comprise: infiltrating the carbon structure with a silicon oxycarbide (SiOC) precursor sol; and densifying the carbon structure by chemical vapor infiltration (CVI) to form a carbon and ceramic matrix composite material, the carbon and ceramic matrix composite material comprising between 0% and 15% by weight of a plurality of ceramic particles from the ceramic compound, densifying the carbon structure including adjusting a temperature gradient across the carbon structure.
C04B 35/56 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides
C04B 35/52 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbon, e.g. graphite
43.
IN-SITU SILICON OXYCARBIDE FORMATION IN CARBON-CARBON COMPOSITES
A method of making a carbon-carbon composite may comprise forming a silicon oxycarbide (SiOC) precursor sol and infiltrating a fibrous preform with the SiOC precursor sol. A SiOC forming heating treatment may be performed on the fibrous preform to form SiOC particles. The fibrous preform may be densified using chemical vapor infiltration to form a densified fibrous preform.
C04B 35/56 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides
C04B 35/52 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbon, e.g. graphite
44.
SYSTEMS AND METHODS FOR AIR CARGO CONTAINER DAMAGE MONITORING
A method of monitoring cargo loading by an aircraft field device may be used to detect damage to cargo and ULDs, reducing the need for manual inspection of the cargo and/or eliminate the need for constant human monitoring of cargo loading. The method may comprise scanning ULDs and receiving image data of the ULDs, and sending the data to an on ground infrastructure network. The on ground infrastructure network may classify ULD type and classify damage to the ULDs. The damage classification may be received by the field device. The field device may generate an alert and/or halt cargo loading in response to the damage classification.
A clip for a rotor disk of a brake assembly, the clip arranged to fit over an end of a lug of the rotor disk, the clip having two opposing sides and an end portion across the two opposing sides, and a top portion, the top portion, the sides and the end portion each having an inner surface and an outer surface, and the inner surface of the top portion, the sides and the end portion together defining a receptacle to receive the rotor lug, in use, the clip having at least one aperture in each of the sides; the clip further comprising a reinforcement member extending from the inner surface of the end portion internal of the receptacle, between the two sides.
A clip for a rotor disk of a brake assembly, the clip formed of sheet metal to fit in a slot between, and to, ends of adjacent rotor lugs around the periphery of the rotor disk, wherein the clip is shaped to have a main body portion that is substantially rectangular in form and shaped and sized to fit, in use, onto an inner peripheral surface defined by the slot between the ends of two adjacent lugs, and to extend across the length of the slot from a first main body portion edge to a second opposite main body portion edge; and wherein the clip further comprises first and second end portions that extend from the respective ends of the main body portion at an angle, wherein each end portion comprises an outwardly protruding section and an end clip portion.
An actuator for opening a hermetically sealed cylinder is disclosed herein. The actuator includes an actuation chamber configured to receive pressurized gas, the actuation chamber at least partially defined by a top wall and a bottom wall, a cutter body disposed within the actuation chamber between the top wall and the bottom wall, the cutter body including a top portion and a bottom portion, a cutting edge extending from the bottom portion of the cutter body, and a spring disposed between the top portion of the cutter body and the bottom wall of the actuation chamber.
A retainer for connecting two panels of a heat shield assembly, the retainer comprising: a central elongate panel having a length l and a width w, a top end, a bottom end and first and second long sides extending from the top end to the bottom end; a first side panel extending along the first long side of the central elongate panel and a second side panel extending along the second long side of the central elongate panel; a first U-shaped fold joining the central elongate panel first long side to the first side panel, and a second U-shaped fold joining the second long side to the second side panel.
B60B 7/04 - Wheel cover discs, rings, or the like, for ornamenting, protecting, or obscuring, wholly or in part, the wheel body, rim, hub, or tyre sidewall built-up of several main parts
A clip assembly for a rotor disk of a brake assembly, the clip assembly comprising: a clip formed of sheet metal to fit over an end of a lug of the rotor disk, the clip shaped to have a top surface that extends in a first plane from a first side and then transitions, at an opposite, second side, by a first bend into a front surface that extends in a second plane from a third side at the first bend to a fourth side and transitions by a second bend to an under-surface extending in a third plane to a fifth end, the top surface, the first bend, the front surface, the second bend and the under surface together defining a hook configuration such that, in use, the top surface fits over a top surface of the lug onto which it is mounted.
A retainer for connecting two panels of a heat shield assembly, the retainer comprising: a central elongate panel having a length 1 and a width w, a top end, a bottom end and first and second long sides extending from the top end to the bottom end; a first side panel extending along the first long side of the central elongate panel and a second side panel extending along the second long side of the central elongate panel; and wherein the central elongate panel is corrugated, with corrugations running along the length of the central elongate panel from the top end to the bottom end.
A stator disk assembly for a brake assembly is disclosed. The stator disk assembly includes at least a pair lugs with a recess disposed therebetween, along with a separate stator clip that is separately mounted on each lug of this pair. The stator clip are configured such that a spline of a torque plate that is disposed in the recess will contact only the stator disk and not either of the stator clips in at least certain conditions (e.g., during a braking operation; until crushing of the stator disk). For instance, each of the two ends of each stator clip may be recessed back from the adjacent-most sidewall of the lug on which the stator clip is mounted.
A lightbox is disclosed herein, comprising a lower panel, a back panel connected to the lower panel and extending upward from the lower panel, wherein the back panel is coated in a reflective material, an inner lens connected to the lower panel and extending upward from the lower panel, the inner lens being adjacent the back panel, a first cavity at least partially defined by the back panel and the inner lens, an outer lens connected to the lower panel and extending upward from the lower panel, the outer lens being adjacent the inner lens and opposite the back panel, and a first LED adjacent the lower panel and oriented to emit a light away from the lower panel and into the first cavity.
G02F 1/1335 - Structural association of cells with optical devices, e.g. polarisers or reflectors
F21K 9/68 - Optical arrangements integrated in the light source, e.g. for improving the colour rendering index or the light extraction - Details of reflectors forming part of the light source
F21K 9/69 - Optical arrangements integrated in the light source, e.g. for improving the colour rendering index or the light extraction - Details of refractors forming part of the light source
A landing gear actuation system is disclosed herein. The landing gear actuation system includes a trunnion sprocket coupled to a movable member, a drive motor, and a flexible drive member extending between and to the motor and the trunnion sprocket. The motor is configured to move the flexible drive member, wherein the movement of the flexible drive member moves the trunnion sprocket and the movable member. The flexible drive member may be a belt or a chain.
F16H 19/08 - Gearings comprising essentially only toothed gears or friction members and not capable of conveying indefinitely-continuing rotary motion for interconverting rotary motion and oscillating motion
A fluid level sensor assembly includes a tubular housing arranged to be fitted into a fluid flow path of a system between a fluid line an inlet to a valve (1′), wherein the tubular housing defines an axial flow channel extending through the tubular housing from a first end to a second end, along an axis A, for fluid to flow from the fluid line of the system to the valve inlet, the tubular housing further comprising a sensor channel extending from the second end of the flow channel towards the first end substantially parallel to, and in fluid communication with the axial flow channel, wherein the assembly further comprises first and second sensor parts located in the sensor channel that communicate with each other.
G01F 23/263 - Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm by measuring physical variables, other than linear dimensions, pressure or weight, dependent on the level to be measured, e.g. by difference of heat transfer of steam or water by measuring variations of capacity or inductance of capacitors or inductors arising from the presence of liquid or fluent solid material in the electric or electromagnetic fields by measuring variations in capacitance of capacitors
G01F 15/00 - MEASURING VOLUME, VOLUME FLOW, MASS FLOW, OR LIQUID LEVEL; METERING BY VOLUME - Details of, or accessories for, apparatus of groups insofar as such details or appliances are not adapted to particular types of such apparatus
55.
SHORT RANGE DATA TRANSFER IN WIRELESS CARGO APPLICATIONS
A controller is disclosed herein. The controller includes a processor and a memory operatively coupled to the processor. The memory includes instructions stored thereon that, when executed by the processor, cause the processor to receive authentication credentials for controlling a cargo handling system via an access point. The access point uses a short-range wireless communication protocol. The instructions further cause the processor to connect to the cargo handling system via a wireless communication protocol, receive control of the cargo handling system, and send commands to the cargo handling system.
An aircraft brake insulator assembly for a brake mechanism of an aircraft includes a torque barrel assembly and a multi-layer insulator. The torque barrel assembly includes a torque plate and a torque barrel coupled to the torque plate. The multi-layer insulator is configured to be located between a piston housing of the brake mechanism and the torque plate. The multi-layer insulator includes a first insulator layer and a second insulator layer contacting the first insulator layer.
B32B 3/26 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by a layer with cavities or internal voids
B32B 7/05 - Interconnection of layers the layers not being connected over the whole surface, e.g. discontinuous connection or patterned connection
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 9/04 - Layered products essentially comprising a particular substance not covered by groups comprising such substance as the main or only constituent of a layer, next to another layer of a specific substance
B32B 9/00 - Layered products essentially comprising a particular substance not covered by groups
A power drive unit for moving cargo relative to a cargo bay of an aircraft is disclosed herein. The power drive unit includes a lift cam coupled to camshaft, a drive wheel coupled to a drive shaft, and an induction motor having a first output shaft and a second output shaft, the first output shaft configured to drive the drive shaft and the second output shaft configured to drive the camshaft.
The present disclosure provides assemblies, systems and characterization methods of welded joints for thermoplastic components. More particularly, the present disclosure provides assemblies, systems and characterization methods of welded joints for thermoplastic components (e.g., thermoplastic-based fiber-reinforced composites) utilizing visualization agents (e.g., pigments and/or fluorescent agents). The present disclosure provides for assemblies, systems and characterization methods of welded joints for thermoplastic components and/or thermoplastic-based composites with enhanced visualization, sufficient for qualitative and quantitative assessment of the welded interconnected areas.
A fiber reinforced composite component may include interleaved textile layers and ceramic particle layers coated with matrix material. The fiber reinforced composite component may be fabricated by forming a fibrous preform and densifying the fibrous preform. The fibrous preform may be fabricated by performing a silicon melt infiltration after the densification process. A plurality of pores defined by the carbon matrix material are infiltrated with a silicon material and the fibrous preform is heated to a melt temperature until a desired percentage (e.g., at least 50%) of the carbon matrix material is converted into silicon carbide or another oxidation resistant material.
A heat shield for a wheel assembly may comprise a plurality of heat shield segments and a plurality of heat shield retainers coupled to the plurality of heat shield segments. A plurality of shield bumpers may be coupled to a radially outward surface of each heat shield segment of the plurality of arcuate heat shield segments. A first retainer bumper may be located over a first radially outward surface of each heat shield retainer of the plurality of heat shield retainers.
A drive shaft for transferring torque including a tubular insert extending along an axis and defining a first layer of the drive shaft including at least one straight portion and at least one undulation, wherein the tubular insert includes a first material having a first deformation temperature, and a polymeric tubular covering defining a second layer of the drive shaft surrounding the tubular insert including a second material having a deformation temperature lower than the deformation temperature of the first material, wherein the covering includes at least one straight portion adjacent to the straight portion of the tubular insert and at least one undulation adjacent to the at least one undulation of the tubular insert.
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
Stator clips may be disposed in the recesses of aircraft brake stator disks to increase the lug strength of the stator disk. The clips may interface with the splines of a torque plate and may comprise ridges that reduce contact between the torque plate barrel and the clip, while maintaining the overall integrity of the clip structure. Furthermore, reduced contact may enable a reduction in drag, improving brake performance.
A stator disk assembly for a brake assembly is disclosed. The stator disk assembly includes at least a pair lugs with a recess disposed therebetween, along with a separate stator clip that is separately mounted on each of the lugs. The stator clips are configured such that a spline of a torque plate barrel that is disposed in the recess will contact only the stator disk and not either of the stator clips in at least certain conditions (e.g., during a braking operation). For instance, each of the two ends of each stator clip may be recessed back from the adjacent-most sidewall of the lug on which the stator clip is mounted.
A cargo handling system is disclosed herein. The cargo handling system includes a conveyance surface a power drive unit for moving cargo along the conveyance surface where the power drive unit disposed in the conveyance surface and a cargo detector coupled to the power drive unit. The cargo detector includes an image sensor having a sensing surface, the sensing surface being oriented towards the cargo, a shutter disposed between the image sensor and the cargo, and a pin hole disposed in the shutter.
Systems and methods for forming an oxidation protection system on a composite structure are provided. In various embodiments, the oxidation protection system comprises a boron-glass layer formed on the composite substrate and a silicon-glass layer formed over the boron-glass layer. Each of the boron-glass layer and the silicon-glass layer include a glass former and a glass modifier. The boron-glass layer includes a boron compound comprising a mixture of boron carbide (B4C) powder and cubic boron nitride (BN) powder.
C04B 35/5831 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on borides, nitrides or silicides based on boron nitride based on cubic boron nitride
C04B 35/563 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides based on boron carbide
C04B 35/565 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides based on silicon carbide
C04B 35/58 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on borides, nitrides or silicides
C04B 35/14 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxides based on silica
A method of forming a composite component is provided. The method includes locating a fibrous preform, providing a slurry, mixing the slurry with sacrificial fibers, injecting the slurry into the fibrous preform, heating the fibrous preform, forming channels in the fibrous preform, and densifying the fibrous preform. The sacrificial fibers are suspended in the fibrous preform along an injection pathway such that heating the sacrificial fibers forms the channels along the injection pathway as the sacrificial fibers are burned away.
A silicone heater assembly is provided. The silicone heater includes a heater and a thermal pad. The thermal pad is configured to couple to the heater. The thermal pad is configured to conform to a plumbing infrastructure to be heated.
An anti-icing system may comprise a deicing boot of an elastomeric material comprising a plurality of tubes, wherein the deicing boot comprises a first set of tubes and a second set of tubes, wherein each of the first set of tubes and the second set of tubes have a corresponding end, and wherein the corresponding end is coupled to a continuous dual wrap end closure.
B64D 15/16 - De-icing or preventing icing on exterior surfaces of aircraft by mechanical means, e.g. pulsating mats or shoes attached to, or built into, surface
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 15/22 - Automatic initiation by icing detector
69.
SOLENOID OPERATED PRESSURE CARTRIDGE FOR INFLATION SYSTEM
An inflation valve arrangement includes an actuation cavity housing connected to a pneumatic valve, the actuation cavity housing comprising an actuation cavity and a piston rod extending from the actuation cavity at least partially into a main fluid channel of the pneumatic valve in an initially extended position for securing the pneumatic valve in a closed position. The arrangement further comprises a solenoid actuated pressure cartridge connected to the actuation cavity housing. The solenoid actuated pressure cartridge comprises a self-contained source of actuation gas. In response to the solenoid actuated pressure cartridge being energized, the solenoid operated pressure cartridge is configured to release the actuation gas from the pressure cavity into the actuation cavity, thereby retracting the piston rod into the actuation cavity, and opening the pneumatic valve body to release a source of inflation gas to an inflation device.
F16K 31/42 - Operating means; Releasing devices actuated by fluid by means of electrically-actuated members in the supply or discharge conduits of the fluid motor
F16K 24/06 - Devices, e.g. valves, for venting or aerating enclosures for aerating only
A cargo handling system is disclosed herein. The cargo handling system includes a ball panel for moving and storing cargo and a cargo restraining device disposed within the ball panel. The cargo restraining device includes a base, a cam head having a rounded base portion, the rounded base portion having a lock slot formed therein, a shaft securing the cam head to the base, and a spring-loaded lock plate configured to engage the lock slot.
An inspection system is disclosed herein. The inspection system includes a control system and a hub assembly. The control system includes a base having a top surface and configured to move horizontally forward and backward, an upright member extending orthogonally from the top surface of the base and configured to move vertically up and down, the upright member having a top surface, and an elongated member extending orthogonal to the upright member having a proximal end and a distal end, the proximal end connected to the top of the upright member, wherein the elongated member is configured to rotate. The hub assembly is connected to the distal end of the elongated member. The hub assembly includes a spring-loaded arm extending orthogonally from the hub assembly and a sensor connected to a distal end of the spring-loaded arm.
Disclosed is a buoyancy tube for a life raft having: a first panel including: a first panel top edge and a first panel bottom edge, the first panel top edge defines a first repeating pattern, and the first panel bottom edge defines a second repeating pattern that is a rotated version of the first panel top edge; a second panel that has a same shape as the first panel, the first and second panels connected by a first elongated seam and a second elongated seam that are non-overlapping with one another, the first and second panels, when connected, define outer an inner boundaries of the life raft, the outer boundary defines an outer polygon having outer sides and the inner boundary defines an inner polygon having inner sides such that each of the plurality of outer sides is parallel with one of the plurality of inner sides.
A joint for a composite frame includes a first composite rod, a first shell abutting the first composite rod, a second shell abutting the first composite rod and disposed opposite the first shell relative to the first composite rod. The first and second shells are joined together such that composite rod is fixed therebetween. A method of forming joints of composite frame includes forming a composite frame by interconnecting a plurality of composite rods formed by an Automated Fiber Placement (AFP) manufacturing method around a mandrel, applying a first shell to the plurality of composite rods at a first location where composite rods are interconnected, applying a second shell at the first location opposite the first shell relative to the composite rods, and joining the first and second shells together with the composite rods at the first location disposed between the first and second shells.
A light system for an evacuation slide may include a readiness indicator light assembly. The readiness indicator light assembly may comprise a first light emitting diode configured to emit a first color and a second light emitting diode configured to emit a second color. The light system may be configured to power the first light emitting diode after initial deployment of the evacuation slide and to power the second light emitting diode after the internal pressure of the evacuation slide is greater than a minimum pressure threshold.
G08B 5/36 - Visible signalling systems, e.g. personal calling systems, remote indication of seats occupied using electromagnetic transmission using visible light sources
H05B 45/22 - Controlling the colour of the light using optical feedback
A method of forming a B4C layer as a component of an oxidation protection system as component of oxidation protection system on a carbon-carbon composite material may include forming a liquid mixture comprising a boron-compound and a carbon-compound. The method may further include applying the liquid mixture on the carbon-carbon composite material. The boron compound may comprise boric acid (H3BO3). In various embodiments, the carbon-compound comprises phenolic resin. In various embodiments, the method further includes heating the carbon-carbon composite material after applying the liquid mixture on the carbon-carbon composite material to from a boron carbide (B4C) layer.
A fiber de-gassing membrane includes a plurality of membrane fibers. At least one of the membrane fibers has a first stiffness. The membrane includes reinforcing fibers. The reinforcing fibers are positioned adjacent to at least one of the membrane fibers. The reinforcing fibers have a second stiffness. The second stiffness is greater than the first stiffness.
B01D 69/02 - Semi-permeable membranes for separation processes or apparatus characterised by their form, structure or properties; Manufacturing processes specially adapted therefor characterised by their properties
77.
Temperature compensated shock strut visual health indicator systems and methods
A temperature compensating shock strut health indicator system for use with a shock strut comprises a visual indicator comprising a plurality of sectors and a pointer configured to rotate with respect to the visual indicator to point to one of the plurality of sectors. The sector to which the pointer points to is dependent on the shock strut stroke (i.e., the position of the piston with respect to the cylinder). In various embodiments, the visual indicator includes various rings that correspond to a different temperature compensated ideal stroke whereby a crew member can correspond the pointer to the appropriate ring depending on ambient temperature. In various embodiments, the pointer comprises a temperature sensitive material configured to cause the pointer to rotate with respect to the visual indicator to actively compensate for temperature.
F16F 9/32 - Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium - Details
Systems and methods for operating a hoist and hook assembly may method comprising determining a clutch slip via a clutch sensor, determining an overload via a load sensor, and cutting a cable coupled to the hoist and hook assembly in response to the clutch slip determination and the overload determination.
An inflatable girt for an evacuation slide may comprise a sleeve section, an upper section coupled to the sleeve section, and a lower section coupled to at least one of the sleeve second and the upper section. The sleeve section defines a plurality of first inflatable chambers. The upper section defines a plurality of second inflatable chambers. The lower defines a plurality of third inflatable chambers.
An inflatable for an evacuation system may comprise a nano-fiber material defining an inflation chamber. The nano-fiber material may include a nano-fiber fabric formed of woven nano-fibers, an interior thermoplastic polymeric coating formed over a first side of the nano-fiber fabric and oriented toward the inflation chamber, and an exterior thermoplastic polymeric coating formed over a second side of the nano-fiber fabric and oriented away from the inflation chamber.
D06M 15/564 - Polyureas, polyurethanes or other polymers having ureide or urethane links; Precondensation products forming them
D03D 15/283 - Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used characterised by the material of the fibres or filaments constituting the yarns or threads synthetic polymer-based, e.g. polyamide or polyester fibres
A regulator valve assembly may comprise: a housing defining an actuator cavity and a piston head cavity; a piston rod comprising a piston head disposed within the piston head cavity and a rod end disposed within the actuator cavity; and a disc retainer within the housing. The actuator cavity can have a top region of the actuator cavity and a bottom region of the actuator cavity. The piston head cavity can comprise a regulator inlet and an inlet port. The disc retainer can be coupled to a proximate seating surface of the inlet port, wherein a first face of a membrane disc is coupled to a lateral seating surface of the inlet port disposed between the piston head cavity and the disc retainer. Also disclosed are methods of using and manufacturing regulator valve assemblies.
F16K 31/06 - Operating means; Releasing devices magnetic using a magnet
F16K 31/40 - Operating means; Releasing devices actuated by fluid in which fluid from the conduit is constantly supplied to the fluid motor with electrically-actuated member in the discharge of the motor
82.
Solenoid actuated pressure regulator for inflation system
A valve arrangement for inflating an inflatable device includes a valve body comprising an inlet, an outlet, a main fluid channel, a first ball detent, and a second ball detent. A lifter and a sleeve are located in the main fluid channel. A locking ball is disposed at least partially within a locking ball aperture disposed in the sleeve. A piston is coupled to the lifter and fluidly coupled to a command pressure cavity of the valve body. A spring biases the lifter toward a ball locking position whereby the lifter urges the locking ball at least partially into the first ball detent. A valve operation initiator controls a flow of pressurized gas into the command pressure cavity to urge the lifter to a ball releasing position to free the sleeve, as to the locking ball, to translate to an open position to fluidly couple the inlet with the outlet.
F16K 31/40 - Operating means; Releasing devices actuated by fluid in which fluid from the conduit is constantly supplied to the fluid motor with electrically-actuated member in the discharge of the motor
F16K 17/40 - Safety valves; Equalising valves with fracturing member, e.g. fracturing diaphragm, fusible joint
A spacer assembly includes a shaft, a spacer having a first end and a second end, the spacer configured to receive the shaft; a collar configured to couple with the shaft at the first end to secure the shaft in the spacer when the shaft is received by the spacer, a lever configured to couple with the shaft at the first end, the lever configured to rotate the shaft, and a screw configured to fasten the lever to the spacer.
A hydraulic fluid system is disclosed herein. The hydraulic fluid system includes a hydraulic motor including an output shaft, a reduction gear box having a first side and an opposing second side, the reduction gear box being coupled to the output shaft at the first side and coupled to a reduction shaft at the second side, and a magneto-rheological fluid brake (MRF) brake coupled to the reduction shaft.
F15B 15/02 - Mechanical layout characterised by the means for converting the movement of the fluid-actuated element into movement of the finally-operated member
F03C 2/08 - Rotary-piston engines of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing
F04C 15/00 - Component parts, details or accessories of machines, pumps or pumping installations, not provided for in groups
F16F 9/53 - Means for adjusting damping characteristics by varying fluid viscosity, e.g. electromagnetically
F16H 61/44 - Control of exclusively fluid gearing hydrostatic with more than one pump or motor unit in operation
F16H 61/444 - Control of exclusively fluid gearing hydrostatic with more than one pump or motor unit in operation by changing the number of pump or motor units in operation
A method for forming an aircraft component includes forming an inner portion of the aircraft component. The method further includes forming an outer layer of the aircraft component using extrusion of an elastomeric material. The method further includes coupling the outer layer of the aircraft component to the inner portion of the aircraft component.
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 7/12 - Interconnection of layers using interposed adhesives or interposed materials with bonding properties
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 25/08 - Layered products essentially comprising natural or synthetic rubber comprising rubber as the main or only constituent of a layer, next to another layer of a specific substance of synthetic resin
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 37/12 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by using adhesives
86.
OBSERVATION LOGGING VIA QR CODE FOR AIRLINE PERSONNEL
A method of logging an observation or maintenance request of an aircraft, the method can comprise: scanning, by a personal internet device connected to a network, a machine-readable code; directing the personal internet device to a user interface of an aircraft log database based on the machine-readable code; and transmitting, by the personal internet device, a log entry to the aircraft log database over the network, wherein the log entry comprises a description of the observation. The method can further comprise transmitting an alert notification to an aircraft maintenance system. An aircraft log system can comprise a personal internet device, a machine-readable code disposed on an aircraft, and an aircraft log database. The aircraft log system can further comprise a manufacturer log database.
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
G06K 7/14 - Methods or arrangements for sensing record carriers by corpuscular radiation using light without selection of wavelength, e.g. sensing reflected white light
B64F 5/60 - Testing or inspecting aircraft components or systems
G01S 19/38 - Determining a navigation solution using signals transmitted by a satellite radio beacon positioning system
A torque barrel for use with a brake system may comprise a torque barrel having a cylindrical structure including an inner surface, an outer surface, a first opening at a first end, and a second opening at an opposing second end; and a longitudinal hole disposed through the outer surface of the barrel between a first spline of the plurality of splines and a second spline of the plurality of splines.
A diaphragm for separating fluid chambers in a fluid assembly. The diaphragm includes a sheet of flexible material having a central region and a peripheral Region, and wherein the peripheral region is provided with a larger dimension peripheral feature extending axially from the plane of the sheet.
F16K 7/12 - Diaphragm cut-off apparatus, e.g. with a member deformed, but not moved bodily, to close the passage with flat, dished, or bowl-shaped diaphragm
F16K 31/126 - Operating means; Releasing devices actuated by fluid the fluid acting on a diaphragm, bellows, or the like
F16K 27/02 - Construction of housings; Use of materials therefor of lift valves
A closure assembly for a fluid port having a fluid flow channel defined along an axis, the channel ending in a port opening. The assembly includes: a closure cap extending in a first plane arranged to seat across, and close the port opening, in use, in a closed state, a guide arm extending from the cap in a second plane substantially perpendicular to the first plane; a lifting guide to accommodate and retain the guide arm for movement of the guide arm in the second plane as the cap moves axially away from the opening; and a pivot mechanism between the guide arm and the lifting guide about which the cap is able to pivot relative to the lifting guide to an open position.
An energy harvesting roller for a cargo handling system may comprise a shaft and a sleeve located on the shaft. A piezoelectric member may be coupled to the sleeve. A shell may be located radially outward of the piezoelectric member and configured to rotate relative to the sleeve. A radially inward surface of the shell may define at least one of a plurality of grooves or a plurality of protrusions.
H02N 2/18 - Electric machines in general using piezoelectric effect, electrostriction or magnetostriction producing electrical output from mechanical input, e.g. generators
H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
B65G 39/09 - Arrangements of bearing or sealing means
A tie down for a cargo handling system may comprise a carriage. the carriage may include a first sidewall surface, a second sidewall surface opposite the first sidewall surface, a first surface extending from the first sidewall surface to the second sidewall surface, and a second surface opposite the first surface. A first rail interface pin may be configured to extend from the first sidewall surface. A second rail interface pin may be configured to extend from the second sidewall surface. A seat fitting channel may be formed in the carriage and may extend between the first sidewall surface and the second sidewall surface.
A landing gear actuation system is disclosed herein. The landing gear actuation system includes an attachment point integral to a movable member, a flexible pull member having a first end coupled to the attachment point, and a motor configured to move the flexible pull member, wherein the movement of the flexible pull member moves the attachment point and the movable member.
F16F 1/02 - Springs made of steel or other material having low internal friction; Wound, torsion, leaf, cup, ring or the like springs, the material of the spring not being relevant
A wear debris delivery system includes a brake component fabricated from a ceramic matrix composite (CMC). The brake component includes a stator disk, the stator disk having at least one wear surface, and a torque plate barrel having a series of axially extending stator splines, wherein the stator splines are configured to support the stator disk. The wear debris delivery system includes an injector configured to inject wear debris into the brake component such that the wear debris travels through the torque plate barrel to the stator disk via the stator splines.
F16D 55/22 - Brakes with substantially-radial braking surfaces pressed together in axial direction, e.g. disc brakes with axially-movable discs or pads pressed against axially-located rotating members by clamping an axially-located rotating disc between movable braking members, e.g. movable brake discs or brake pads
94.
Z-DIRECTION REINFORCED COMPOSITES AND METHODS OF FORMING Z-DIRECTION REINFORCED COMPOSITES
A fiber reinforced composite component may include interleaved fiber layers and ceramic particle layers coated with matrix material. The fiber reinforced composite component may be fabricated by forming a fibrous preform, needling the fibrous preform to form a plurality of z-direction fibers, and densifying the fibrous preform. The fibrous preform may be fabricated by forming a first ceramic particle layer over a first fiber layer, disposing a second fiber layer over the first ceramic particle layer, forming a second ceramic particle layer over the second fiber layer, and disposing a third fiber layer over the second ceramic particle layer.
B32B 3/26 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by a layer with cavities or internal voids
B32B 5/06 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by a fibrous layer needled to another layer, e.g. of fibres, of paper
B32B 5/16 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by features of a layer formed of particles, e.g. chips, chopped fibres, powder
B32B 5/30 - 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 comprising granules or powder
The present disclosure provides assemblies, systems and methods of quality control and service inspection for metallic electro-mechanical components. More particularly, the present disclosure provides assemblies, systems and methods of quality control and service inspection for metallic electro-mechanical components (e.g., stator components) utilizing fluorescent agents. The present disclosure provides both (i) surface/assembly designs, and (ii) methods of their inspection. In the present disclosure, fluorescent agents can be mixed with protective and/or added layers to serve as bright contrast media under a light source (e.g., ultraviolet (“UV”) light source). It is noted that in a case of imperfect coating or service corrosion, gaps in reflection can serve as clear indications of either inadequate quality or excessive corrosion-driven degradation of the components.
G01N 17/02 - Electrochemical measuring systems for weathering, corrosion or corrosion-protection measurement
G01N 21/33 - Investigating relative effect of material at wavelengths characteristic of specific elements or molecules, e.g. atomic absorption spectrometry using ultraviolet light
Ice may form along the leading edge of an aircraft wing. A pneumatic deicing system may be configured to crack and dislodge ice along the leading edge of the wing. The pneumatic deicing system may comprise a deicing boot assembly having a deicing boot attached to the leading edge, and a gas generator fluidly coupled to the deicing boot assembly. The gas generator may comprise a propellant and may decompose the propellant, liberating a compressed gas. The compressed gas may be directed to the deicing boot assembly, inflating the deicing boot, which may crack and dislodge the ice.
An aircraft evacuation slide assembly may be comprised of a plurality of composite textiles. Each composite textile may comprise a fabric substrate, an inner polyurethane coating, and an outer heat reflective coating. The outer heat reflective coating may comprise nanofillers that improve polymer properties, such as mechanical, barrier, thermal, flame retardancy, and electrical properties. Moreover, the outer heat reflective coating may comprise nanofillers that enable hot air welding and radio frequency welding of the plurality composite textiles to form the aircraft evacuation slide assembly.
Ice may form along the leading edge of an aircraft wing or horizontal and vertical stabilizers. A pneumatic deicer system may be configured to inflate and dislodge ice along the leading edge of lift and control surfaces. The pneumatic deicer system may comprise a laser welded deicing boot attached to the leading edge. The compressed air can be directed to the deicing boot, inflating the deicing boot along inflatable tubes formed by laser welds, which can crack and dislodge the ice. A method of manufacturing a laser welded pneumatic deicer boot is also disclosed.
B64D 15/16 - De-icing or preventing icing on exterior surfaces of aircraft by mechanical means, e.g. pulsating mats or shoes attached to, or built into, surface
B32B 27/12 - Layered products essentially comprising synthetic resin next to a fibrous or filamentary layer
B32B 3/08 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by added members at particular parts
B32B 7/12 - Interconnection of layers using interposed adhesives or interposed materials with bonding properties
B29C 65/14 - Joining of preformed parts; Apparatus therefor by heating, with or without pressure using wave energy or particle radiation
A vane for use in a rotary vane pump. The vane has a length L extending between a first edge of the vane and a second edge of the vane and a width W extending perpendicular to said length, the width extending between a third edge of said vane and a fourth edge of the vane, and further comprising a channel extending through said vane and provided at a position along said length L of said vane. The channel maybe positioned away from said first and second edges such that said vane has a constant length L along its width. The width of the channel may vary in shape between first and second points along the length of the vane. The channel may have a triangular shape, a rectangular shape or a circular shape. A method for detecting the decrease in length of the vane is also described.
An aircraft wing may comprise an airfoil having deicing zone, an anti-icing zone, and an ice runback control zone. An aircraft wing may comprise an electro-thermal ice protection system disposed in the aircraft wing. The electro-thermal ice protection system may be disposed along the deicing, anti-icing, and ice runback control zones of the airfoil to improve aerodynamic performance of the aircraft and reduce ice formation along the wings of the aircraft.
patents
