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
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.
An aircraft beacon light includes a plurality of primary light sources for emitting light into at least two spatial sectors, wherein the at least two spatial sectors include a forward sector and at least one of an aft sector, a starboard lateral sector, and a portside lateral sector; and a light transmissive cover, which covers the plurality of primary light sources. The plurality of primary light sources are arranged and configured for providing an FAR-compliant aircraft beacon light output of the aircraft beacon light, in case of the light transmissive cover being in a non-eroded state. The aircraft beacon light also includes at least one booster light source for selectively emitting a booster light output into the forward sector. The at least one booster light source is controllable independently of the plurality of primary light sources.
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
5.
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.
A system for controlling in-flight services using gestures is disclosed. The system comprises: a gesture detection device; an actuator; and a controller. The controller is configured to: receive a detected free space gesture from the gesture detection device; compare the detected free space gesture to a plurality of identified free space gestures; responsive to identifying a free space gesture from the plurality of identified free space gestures, identify an associated in-flight service based on the identified free space gesture; and responsive to identifying the associated in-flight service, send a first command to the actuator to perform the associated in-flight service.
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 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 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 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
12.
EXTERIOR AIRCRAFT LIGHT, AIRCRAFT COMPRISING AN EXTERIOR AIRCRAFT LIGHT, AND METHOD FOR PROVIDING AN EXTENT OF EROSION OF AN EXTERIOR SURFACE OF A LIGHT TRANSMISSIVE COVER OF AN EXTERIOR AIRCRAFT LIGHT
An exterior aircraft light includes a support and a light transmissive cover having a light transmissive body with an interior surface and an exterior surface. The light includes at least one light source arranged between the support and the light transmissive cover; and a first light detector. The light transmissive cover has a first light guide path within the light transmissive body from a first light entry region to a first light exit region, wherein the first light detector is arranged to receive light that travels along the first light guide path and that exits the light transmissive cover at the first light exit region. The first light detector is configured to provide sensor measurements corresponding to the amount of light incident on the first light detector.
A protective cover for a fuselage-mounted exterior aircraft light includes a fuselage-facing mounting side for mounting the protective cover to an exterior aircraft light housing or to an exterior skin of an aircraft; a light transmissive forward facing light emission surface; and an air deflection zone, which is shaped to direct a portion of an impinging air stream (A) along and over the forward facing light emission surface for shielding the forward facing light emission surface from the impinging air stream (A).
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
19.
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.
A pixel system for an imaging device can include one or more pixels comprising a pulse trigger assembly configured to detect a pulse at one or more threshold voltages, a timer system forming part of and/or connected to the one or more pixels, the timer system comprising one or more trigger switches. The pulse trigger assembly can be configured to activate the one or more trigger switches in response to detecting the pulse at the one or more threshold values. The pixel system can include a time-of-flight (TOF) module operatively connected to the one or more pixels and/or the timer system to determine a TOF based on an output from the timer system while simultaneously performing either or both passive imaging and asynchronous laser pulse detection.
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 system for displaying an artificial horizon in an enclosed space. The system includes a first plurality of visual effect sources located in the enclosed space and configured to generate a first visual effect of the artificial horizon consistent with an orientation detected by an orientation sensor. The system further includes a second plurality of visual effect sources separate from the first plurality of visual effect sources and located in the enclosed space and configured to generate a second visual effect of the artificial horizon different from the first visual effect consistent with the orientation detected by the orientation sensor.
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
B64C 25/36 - Arrangements or adaptations of wheels, tyres or axles in general
28.
LIGHT MODULE FOR AN ELONGATED INTERIOR AIRCRAFT LIGHT, ELONGATED INTERIOR AIRCRAFT LIGHT, AND METHOD OF ASSEMBLING AN ELONGATED INTERIOR AIRCRAFT LIGHT
A light module for an elongated interior aircraft light comprises a plurality of light sources, which are configured for emitting light of different colors and which are arranged next to each other, forming an array of light sources extending between a first end and a second end along a longitudinal direction (LD). The plurality of light sources include a first light source, which is arranged at the first end, and a second light source, which is arranged at the second end. The first and second light sources are those from the plurality of light sources that result in a difference of the illuminating properties between the first and second light sources being the smallest difference that is possible for all potential pairs of light sources formed from the plurality of light sources.
B64D 11/00 - Passenger or crew accommodation; Flight-deck installations not otherwise provided for
F21S 4/28 - Lighting devices or systems using a string or strip of light sources with light sources held by or within elongate supports rigid, e.g. LED bars
29.
AIRCRAFT BEACON LIGHT, AIRCRAFT COMPRISING AN AIRCRAFT BEACON LIGHT, AND METHOD OF DETERMINING A HEALTH STATUS OF AN AIRCRAFT BEACON LIGHT
An aircraft beacon light comprises an annular light source support having a plurality of light passing portions; a plurality of light sources, arranged on the annular light source support for a radially outwards emission of light flashes; a light detector for sensing a light output level of at least a subset of the plurality of light sources; and at least one optical element for shaping a beacon light output from light emitted by the plurality of light sources, the at least one optical element having at least one light guiding portion for capturing stray light from at least said subset of the plurality of light sources and for guiding said stray light through the plurality of light passing portions and towards the light detector.
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 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 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 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
42.
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
43.
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 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.
AIRCRAFT PASSENGER SERVICE UNIT, AIRCRAFT PASSENGER SERVICE UNIT ASSEMBLY, AND METHOD OF DETERMINING SPATIAL POSITIONS AND/OR ORIENTATIONS OF A PLURALITY OF AIRCRAFT PASSENGER SERVICE UNITS
An aircraft passenger service unit, which is configured for being installed in a passenger cabin of an aircraft. The unit includes at least two near field communication interfaces, wherein each of the at least two near field communication interfaces is configured for a wireless exchange of messages with a corresponding near field communication interface of a neighboring aircraft passenger service unit. The messages include information that identifies the aircraft passenger service unit and the near field communication interface sending the respective message.
H04B 5/00 - Near-field transmission systems, e.g. inductive loop type
B64D 11/00 - Passenger or crew accommodation; Flight-deck installations not otherwise provided for
G01S 1/68 - Marker, boundary, call-sign, or like beacons transmitting signals not carrying directional information
G01S 1/04 - Beacons or beacon systems transmitting signals having a characteristic or characteristics capable of being detected by non-directional receivers and defining directions, positions, or position lines fixed relatively to the beacon transmitters; Receivers co-operating therewith using radio waves - Details
G01S 1/70 - Beacons or beacon systems transmitting signals having a characteristic or characteristics capable of being detected by non-directional receivers and defining directions, positions, or position lines fixed relatively to the beacon transmitters; Receivers co-operating therewith using electromagnetic waves other than radio waves
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.
An aircraft light unit is disclosed herein. The aircraft light unit includes a housing having a first side and an opposing second side, a light coupled to the first side of the housing, a circuit board assembly coupled to second side of the housing, a thermoelectric cooler coupled to the circuit board assembly and configured to dissipated heat from the circuit board assembly, and a heat sink disposed over the thermoelectric cooler and configured to dissipate heat from the thermoelectric cooler.
F21S 45/47 - Passive cooling, e.g. using fins, thermal conductive elements or openings
F21V 29/54 - Cooling arrangements using thermoelectric means, e.g. Peltier elements
G05B 19/4155 - Numerical control (NC), i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form characterised by programme execution, i.e. part programme or machine function execution, e.g. selection of a programme
B64D 47/06 - Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
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 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.
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
58.
SYSTEMS AND METHODS FOR LANDING GEAR ACTUATION VIA TRUNNION DRIVE
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.
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 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
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 aircraft passenger service unit, which is configured for being installed in a passenger cabin of an aircraft, includes a seat detection sensor for determining a position and/or an orientation of at least one passenger seat, which is located in the vicinity of, in particular below, the aircraft passenger service unit.
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
75.
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.
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.
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
84.
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
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.
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 aircraft passenger cabin light. The light has: an elongated shape having a longitudinal direction (L) comprises: a cabin wall illumination assembly, which extends along the longitudinal direction (L) of the aircraft passenger cabin light and which is configured for illuminating a portion of a wall of an aircraft passenger cabin; and a plurality of personal reading light units for providing personal reading light illumination to passengers. The plurality of personal reading light units are arranged in an array extending along the longitudinal direction (L) of the aircraft passenger cabin light Said array is arranged along the cabin wall illumination assembly.
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
91.
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
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 aircraft exterior anti-collision light system includes a plurality of anti-collision lights and a bus, wherein each of the plurality of anti-collision lights is coupled to the bus. Each of the plurality of anti-collision lights comprises at least one light source and is configured to emit a sequence of light flashes (R,W). Each of the plurality of anti-collision lights is configured to carry out an initialization routine in response to an activation command. Each of the plurality of anti-collision lights is configured to transmit an activation status message on the bus, after the initialization routine has been carried out. Each of the plurality of anti-collision lights is configured to listen on the bus for activation status messages and to log activation status messages received on the bus. Each of the plurality of anti-collision lights is configured to set a timing of (R,W) depending on the activation status messages.
An aircraft overhead passenger service unit comprises a plurality of oxygen masks for supplying oxygen to aircraft passengers in an emergency situation; and at least two different oxygen mask storage portions, which are spaced apart from each other in a longitudinal direction (L). The plurality of oxygen masks are stored in the at least two different oxygen mask storage portions. The aircraft overhead passenger service unit further comprises an oxygen mask controller, which is switchable between at least two different configurations. The at least two different oxygen mask storage portions are individually associated with the at least two different configurations, with each of the at least two different configurations effecting a release of only the oxygen masks of the associated oxygen mask storage portion in the emergency situation.
A light assembly includes a mounting bracket, a light coupled to the mounting bracket, a guide sensor coupled to the mounting bracket, a movement mechanism coupled to the mounting bracket, and a controller operably coupled to the light assembly. The controller is configured to receive data from the guide sensor and command actuation of the movement mechanism in response to the data received from the guide sensor.
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.
ABSTRACT 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. Date Recue/Date Received 2023-04-12
F15B 13/00 - SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR - Details of servomotor systems
F16H 61/4157 - Control of braking, e.g. preventing pump over-speeding when motor acts as a pump
A time-of-flight sensor threshold circuit outputs a threshold voltage to a time-of-flight sensor, the threshold reducing over the duration of a time-of-flight measurement, which reduction can occur continually during the measurement. The circuit is provided with an initial threshold voltage portion to set the threshold voltage corresponding to a selected maximum threshold value, a time-dependent portion, to charge and discharge over time, to or from a current control portion, a threshold voltage ramp control portion to lower the threshold value over time by charging or discharging the time-dependent portion to or from the current control portion at a selected rate, and a synchronizing portion to synchronize current flow to or from the current control portion with a synchronizing input signal synchronized with an illumination pulse from a connected illuminator.
G01S 7/4865 - Time delay measurement, e.g. time-of-flight measurement, time of arrival measurement or determining the exact position of a peak
G01S 17/14 - Systems determining position data of a target for measuring distance only using transmission of interrupted, pulse-modulated waves wherein a voltage or current pulse is initiated and terminated in accordance with the pulse transmission and echo reception respectively, e.g. using counters
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
100.
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