A power converter for providing power to a load includes a buck converter having a DC input and a DC output and that is configured to receive a DC voltage at the DC voltage input and provide DC output voltage at the DC output. The converter also includes a voltage monitor that monitors a voltage provided at the DC output and a selectively connectable transient suppression circuit connected across that DC output and connected to the voltage monitor. The selectively connectable transient suppression circuit includes a dissipation circuit and a suppression circuit switch connected in series with the dissipation circuit that controls charge dissipation from the DC output into the dissipation circuit based on the voltage monitor determining that the voltage across the DC output is above a threshold.
H02M 3/156 - Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant continu sans transformation intermédiaire en courant alternatif par convertisseurs statiques utilisant des tubes à décharge avec électrode de commande ou des dispositifs à semi-conducteurs avec électrode de commande utilisant des dispositifs du type triode ou transistor exigeant l'application continue d'un signal de commande utilisant uniquement des dispositifs à semi-conducteurs avec commande automatique de la tension ou du courant de sortie, p.ex. régulateurs à commutation
A harmonic gearset, having: a drive shaft; first and second ground gears spaced apart from each other along the drive shaft; an output gear disposed on the drive shaft, between the first and second ground gears; a first flexspline disposed radially between the drive shaft, the first ground gear and the output gear; and a second flexspline disposed radially between the drive shaft, the second ground gear and the output gear, wherein the first and second flexsplines are axially adjacent to each other.
Examples described herein provide a method that includes storing, in a first buffer associated with a first ADC of a DSP, resolver sine values collected from first, second, and third resolvers. The method further includes storing, in a second buffer associated with a second ADC of the DSP, resolver cosine values collected from the first, second, and third resolvers. The method further includes storing, in a third buffer associated with a third ADC of the DSP, resolver excitation values collected from the first, second, and third resolvers. The method further includes determining a midpoint value of the resolver excitation values, determining a sine amplitude based at least in part on the resolver sine values and the midpoint value, and determining a cosine amplitude based at least in part on the resolver sine values and the midpoint value. The method further includes identifying a quadrant of a resolver position.
A resistance temperature detector includes a single channel analog to digital converter (ADC) comprising a first channel input and a reference voltage input. The detector also includes a resistance temperature detector (RTD) element connected to the first channel input and a current sense element in series with the RTD element. The current sense element is connected to the reference voltage input. The detector also includes a power source connected to the RTD element and a controller configured to: receive an output of the single channel ADC to determine a temperature at the RTD element. The output of the single channel ADC comprises a bit representation of a ratio between a first voltage across the RTD element and a reference voltage across the current sense element.
An actuator arm lock (28) suitable for use with an actuator (10) which has an actuator arm (14) and an actuator body (12) is disclosed. The actuator arm lock (28) comprises a lock ring (26) suitable for clamping around an actuator arm (14). The lock ring (26) comprises a circumferentially extending element (30) and a locking element (32). The circumferentially extending element (30) comprises first and second element ends (34, 36) and an inner surface (74) which faces towards the actuator arm (14) when the actuator arm lock (28) is in use, and the circumferentially extending element (30) is configured to partially extend around the actuator arm (14). The locking element (32) comprises first and second locking ends (44, 46) and is configured to extend at least between the first and second element ends (34, 36) of the circumferentially extending element (30). The first locking end (44) of the locking element (32) is engaged with or engageable with the first element end (34) of the circumferentially extending element (30), and the locking element (32) is engaged with or engageable with the second element end (36) of the circumferentially extending element (30). The locking element (32) may be reversibly reconfigured between a locked configuration in which the actuator arm lock (28) clamps onto the actuator arm (14), and an unlocked configuration in which the actuator arm lock (28) is loose on the actuator arm (14).
F15B 20/00 - Dispositions propres à la sécurité pour systèmes de manœuvre utilisant les fluides; Utilisation des dispositifs de sécurité dans les systèmes de manœuvre utilisant des fluides; Mesures d'urgence pour les systèmes de manœuvre utilisant des fluides
B64C 7/00 - Structures ou carénages non prévus ailleurs
A voltage measurement system and method is provided. Aspects include a comparator having a positive and a negative input terminal, a processor configured to supply a reference voltage signal to the negative input terminal, wherein the positive input terminal receives an input voltage, setting the reference voltage signal to a zero voltage signal, determine a line frequency of the input voltage based on a timing signal from the comparator and determining a first pulse width of the input signal based on the timing signal, set the reference voltage to a PWM signal with a fixed duty cycle, receive the timing signal from the output of the comparator, determine a rising edge and a falling edge associated with the input voltage based on the timing signal, and determine a peak value of the input voltage based on a second pulse width between the rising and falling edge.
Aerostructure actuator systems include first and second shaft portions having respective first and second mandrels and a clutch assembly arranged within the first mandrel and connecting the shaft portions. The clutch assembly includes a post with a post extension fixedly connected to the second mandrel. A first bearing is installed on the post extension to frictionally engage with a portion of the post. A second bearing is installed on the post. A spacer is arranged between the bearings and is fixedly attach to the first mandrel. A load setting nut is configured to engage with the post extension and apply a compressive force to the bearings and spacer against the post. The compressive force defines a coupling limit between the shaft portions. The clutch assembly is configured to rotationally decouple the shaft portions from each other if a relative rotational speed between the shaft portions exceeds the coupling limit.
A motor drive system includes a direct current (DC) bus that provides a DC link voltage across a DC link capacitor, and a split DC link mid-point circuit connected in parallel with the DC link capacitor. The split DC link mid-point circuit establishes a mid-point reference based on the DC link voltage. A power inverter is in signal communication with the DC bus. The power inverter includes one or more gate driver units configured to drive one or more corresponding switches. Each gate driver unit includes a mid-point ground connection that is connected to the mid-point reference. The split DC link mid-point circuit can define a voltage divide that establishes the mid- point reference and can be used to monitor the DC link voltage.
H02P 27/06 - Dispositions ou procédés pour la commande de moteurs à courant alternatif caractérisés par le type de tension d'alimentation utilisant une tension d’alimentation à fréquence variable, p.ex. tension d’alimentation d’onduleurs ou de convertisseurs utilisant des convertisseurs de courant continu en courant alternatif ou des onduleurs
H02J 1/00 - Circuits pour réseaux principaux ou de distribution, à courant continu
H02M 1/08 - Circuits spécialement adaptés à la production d'une tension de commande pour les dispositifs à semi-conducteurs incorporés dans des convertisseurs statiques
H02P 27/08 - Dispositions ou procédés pour la commande de moteurs à courant alternatif caractérisés par le type de tension d'alimentation utilisant une tension d’alimentation à fréquence variable, p.ex. tension d’alimentation d’onduleurs ou de convertisseurs utilisant des convertisseurs de courant continu en courant alternatif ou des onduleurs avec modulation de largeur d'impulsions
9.
COMMON SIGNAL CONDITIONING CIRCUIT FOR TEMPERATURE SENSOR
A ratiometric temperature measurement system includes a sensing circuit to measure a temperature and a controller to determine a resistance corresponding to the sensing circuit. The sensing circuit includes a temperature sensing circuit and a current sensor. The sensing circuit utilize an electrical current to output a first voltage indicative of a first voltage differential across the temperature sensing circuit and to output a second voltage indicative of a second voltage differential across the current sensor. The controller is configured to determine a resistance corresponding to the temperature sensing circuit based at least in part on the first and second voltage differentials. The controller determines a temperature value indicative of the measured temperature based on the resistance.
Assemblies having a first structure, a second structure movable relative to the first structure, and an actuator system arranged therebetween and configured to control relative movement therebetween. The actuator system includes a drive shaft, a first element configured to be driven in a first direction, and a second element configured to be driven in a second direction. A spar is fixedly connected to the first structure and a spar connection pivotably connects the first element to the spar at a fixed coupler. The drive shaft, the first element, and the second element are housed within the second structure. Rotation of the second element causes a translation motion of the drive shaft away from the first structure and rotation of the first element about the fixed coupler such that the second structure is translated and rotated relative to the first structure.
A stator (2) for an electrical machine is provided. The stator comprises: an annular housing (22) extending around a central axis (X-X); a first circumferential flow channel (46) extending around the housing; a second circumferential flow channel (48) axially spaced from the first circumferential flow channel and extending around the housing; and a plurality of windings (8). The plurality of windings are circumferentially spaced about the housing to form a passage (50) between each two adjacent windings. Each passage is in fluid communication with both the first circumferential flow channel and the second circumferential flow channel. The first circumferential flow channel is closed to flow at a first circumferential location and the second circumferential flow channel is closed to flow at a second circumferential location, removed from the first circumferential location so as to form a first set of passages (S1) connected in parallel and a second, separate set of passages (S2) connected in parallel. The stator is configured such that coolant flows through the first set of passages from the first circumferential flow channel to the second circumferential flow channel and then flows from the second circumferential flow channel through the second set of passages to the first circumferential flow channel.
H02K 9/19 - Dispositions de refroidissement ou de ventilation pour machines avec enveloppe fermée et circuit fermé de refroidissement utilisant un agent de refroidissement liquide, p.ex. de l'huile
H02K 3/24 - Enroulements caractérisés par la configuration, la forme ou le genre de construction du conducteur, p.ex. avec des conducteurs en barre avec des canaux ou des conduits pour un agent de refroidissement entre les conducteurs
An electronic controller is provided and includes a printed wiring board (PWB) on which electronics are operably disposed, a power supply configured to supply power to the electronics, a heat sink and one or more thermal conductors anchored to the PWB to assume and move between first and second connection states in first and second thermal conditions, respectively. The first connection states are characterized in that the one or more thermal conductors are thermally attached to the PWB and the power supply and thermally disconnected from the heat sink. The second connection states are characterized in that the one or more thermal conductors are thermally attached to the PWB and the power supply and to the heat sink.
There is provided a magnet carrier 200 for carrying magnets in an outer rotor machine, the magnet carrier comprising: an axis of rotation A; a hub portion 210; a tapered portion 220 extending radially outwardly from the hub portion, the tapered portion having an inner side 222 and an outer side 224, and a radially outer region 226 spaced from the hub; a flange portion 230 extending circumferentially from, and away from, the inner side of the tapered portion, the flange portion having a radially outwardly facing surface 232 and a radially inwardly facing surface 234, the radially inwardly facing surface for supporting the magnets, and the flange portion having a proximal region 236 and a distal region 238 that are proximal and distal to the tapered portion respectively; and a curved corner portion 240 connecting the radially outer region of the tapered portion to the proximal region of the flange portion, wherein each of the hub portion, the tapered portion, the corner portion and the flange portion of the magnet carrier are made of a carbon fibre composite and each portion leads into the next portion so as to provide a continuous composite body from the hub portion to the distal region of the flange portion.
14.
HINGE-LINE ACTUATOR FOR ROTATING AN AIRCRAFT CONTROL SURFACE
A hinge-line actuator has: a drive shaft; first and second ground gears spaced apart along the drive shaft, wherein the first and second output gears include first and second contoured outer gear surfaces; and an output gear disposed on the drive shaft and disposed between the first and second ground gears, wherein the output gear includes a third contoured outer gear surface; an actuator housing that includes: contoured first, second and third gear seats that, respectively, seat the first, second and third outer gear surfaces.
B64C 13/34 - Dispositifs de transmission sans amplification de puissance ou dans les cas où l'amplification de puissance est sans objet mécaniques utilisant des engrenages
F16H 1/24 - Transmissions à engrenages pour transmettre un mouvement rotatif sans engrenages à mouvement orbital comportant des engrenages dont les éléments engrenés sont essentiellement autres que des dentures à développante ou cycloïdales
F16H 35/18 - Dispositifs tournants pour organes que l'on peut mettre en rotation, p.ex. arbres
A compensator circuit for a PWM active rectifier, the compensator circuit (7) comprising a look up table (7b) containing compensating voltage values for given values of input phase current and input voltage frequency, and a low pass filter (7a) arranged to filter the input phase current to the rectifier based on a filter bandwidth determined according to the input voltage frequency, the compensator circuit arranged to receive measured input current and voltage frequency values and to output corresponding compensation voltage values from the look up table, the compensation voltages to be provided, in use, to the rectifier to adjust the switching pattern of the rectifier.
H02M 1/12 - Dispositions de réduction des harmoniques d'une entrée ou d'une sortie en courant alternatif
H02M 1/08 - Circuits spécialement adaptés à la production d'une tension de commande pour les dispositifs à semi-conducteurs incorporés dans des convertisseurs statiques
H02M 7/04 - Transformation d'une puissance d'entrée en courant alternatif en une puissance de sortie en courant continu sans possibilité de réversibilité par convertisseurs statiques
16.
POLYMERIC THREAD INSERT FOR HIGH LOAD LEADSCREW AND NUT
Leadscrew and nut actuators are described. The leadscrew and nut actuators include a leadscrew having an external thread and formed from a first material, a nut configured to receive the leadscrew, the nut having an internal thread and formed from a second material, and an insert arranged between the internal thread of the nut and the external thread of the leadscrew, the insert configured to transfer force between the external thread and the internal thread and prevent material contact between the leadscrew and the nut. The insert is formed of a third material different from the first material and the second material.
A torque limiter (TL) is provided for torque transmission (TT) to downstream components. The TL includes an input shaft, an output shaft and a torsional spring which is preloadable by a preload torque whereupon the torsional spring is fittable about the output shaft with the output shaft fit about the input shaft. For input shaft rotation, first TT paths proceed from the input shaft to the output shaft through the torsional spring when downstream torque of the downstream components deceeds the preload torque and a second TT path proceeds from the input shaft to an external structure when the downstream torque exceeds the preload torque.
F16D 7/00 - Accouplements à glissement, p.ex. glissant en cas de surcharge, pour absorber les chocs
B64C 13/38 - Dispositifs de transmission avec amplification de puissance
F16D 3/12 - Accouplements extensibles, c. à d. avec moyens permettant le mouvement entre parties accouplées durant leur entraînement adaptés à des fonctions particulières spécialement adaptés à un emmagasinage de l'énergie pour absorber les chocs ou vibrations
18.
DRIVE-THROUGH FRICTION CLUTCH AS A TENSILE LOAD DISCONNECT
An actuator assembly for a cowl door is provided. The actuator assembly includes a housing, an actuator configured to drive cowl door extension and cowl door retraction and to support the cowl door during the cowl door extension and the cowl door retraction and a clutch assembly interposed between the actuator and the housing. The clutch assembly is configured to engage a capability of the actuator to drive the cowl door retraction when the cowl door loads the actuator.
E05F 15/60 - Mécanismes pour battants mus par une force motrice utilisant des actionneurs électriques
F16D 7/02 - Accouplements à glissement, p.ex. glissant en cas de surcharge, pour absorber les chocs du type à friction
F16D 13/04 - Embrayages à friction avec moyens pour les actionner ou les maintenir en prise, fournis par une force prélevée, au moins partiellement, sur l'un des arbres à embrayer
19.
COMPOUND HARMONIC GEAR SYSTEM WITH DUAL OUTPUT ARMS
Disclosed is a gear system, having: first and second ground gear; a drive shaft disposed along a rotation axis of the gear system and configured to rotate about the rotation axis; and an output gear supported by the first and second ground gear and configured to rotate by engagement between a wave generator portion of a drive shaft, a wave generator bearing, a flex spline, the output gear and the first and second ground gear, the output gear defining: an output gear body; and first and second output arms respectively extending radially outward from opposite sides of the output gear body to respectively define first and second radial inner ends and radial outer ends of the first and second output arms, so that the first and second radial outer ends are disposed on a radial axis that extends through a radial center of the gear system.
Provided are embodiments for a method for variable differential transformer demodulation using a hybrid algorithm. The method can obtain a first feedback signal over a first half of a first cycle and a second feedback signal over a first half of a second cycle, and obtain a first calibration signal and a second calibration signal during a second half cycle of the first cycle. The method can also obtain an excitation signal over a second half of the second cycle, and determine a sensor position of the variable differential transformer based on the first feedback signal, the second feedback signal, and the excitation signal. Also provided are embodiments for a system for variable differential transformer demodulation using a hybrid algorithm.
G01D 5/22 - Moyens mécaniques pour le transfert de la grandeur de sortie d'un organe sensible; Moyens pour convertir la grandeur de sortie d'un organe sensible en une autre variable, lorsque la forme ou la nature de l'organe sensible n'imposent pas un moyen de conversion déterminé; Transducteurs non spécialement adaptés à une variable particulière utilisant des moyens électriques ou magnétiques influençant la valeur d'un courant ou d'une tension en faisant varier l'inductance, p.ex. une armature mobile influençant deux bobines par une action différentielle
A propeller blade having a blade body including a blade base, a blade tip, a pressure side surface, and, a suction side surface. Each of the pressure side surface and the suction side surface extend between the blade base to the blade tip. An end plate is provided on the blade body. The end plate is exposed to an airflow and positioned at the blade base. The end plate projects outwardly of at least a portion of one of the pressure side surface and the suction side surface.
A shaft monitoring system includes a rotatable shaft having a target element coupled thereto that rotates along with the shaft. A proximity sensor is located adjacent to the target element. The proximity sensor measures an inductance of the target element based on one or both of a volume of the target element and a distance between the target element and the proximity sensor, and generates a proximity sensor output signal based on the measured inductance. A signal processing system determines at least one of a position of the shaft, a rotational speed of the shaft, and a rotational direction of the shaft based on the proximity sensor output signal.
G01P 3/36 - Dispositifs caractérisés par l'emploi de moyens optiques, p.ex. en utilisant la lumière infrarouge, visible ou ultraviolette
G01D 5/20 - Moyens mécaniques pour le transfert de la grandeur de sortie d'un organe sensible; Moyens pour convertir la grandeur de sortie d'un organe sensible en une autre variable, lorsque la forme ou la nature de l'organe sensible n'imposent pas un moyen de conversion déterminé; Transducteurs non spécialement adaptés à une variable particulière utilisant des moyens électriques ou magnétiques influençant la valeur d'un courant ou d'une tension en faisant varier l'inductance, p.ex. une armature mobile
G01P 13/04 - Indication du sens positif ou négatif d'un mouvement linéaire ou du sens horaire ou anti-horaire d'un mouvement de rotation
Electric motors and stators thereof are described. The stators of the electric motors include a first header, a second header fluidly connected to the first header, a plurality of windings fluidly connected to the first header and the second header to receive a cooling fluid passing from the first header to the second header along one or more flow channels, and one or more phase-change material elements arranged to thermally interact with at least one of the first header, the second header, the one or more flow channels, and the plurality of windings.
H02K 3/24 - Enroulements caractérisés par la configuration, la forme ou le genre de construction du conducteur, p.ex. avec des conducteurs en barre avec des canaux ou des conduits pour un agent de refroidissement entre les conducteurs
H02K 9/19 - Dispositions de refroidissement ou de ventilation pour machines avec enveloppe fermée et circuit fermé de refroidissement utilisant un agent de refroidissement liquide, p.ex. de l'huile
H02K 9/20 - Dispositions de refroidissement ou de ventilation pour machines avec enveloppe fermée et circuit fermé de refroidissement utilisant un agent de refroidissement liquide, p.ex. de l'huile dans lesquels l'agent de refroidissement se vaporise dans l'enveloppe de la machine
H02K 9/22 - Dispositions de refroidissement ou de ventilation par un matériau solide conducteur de la chaleur s'encastrant dans, ou mis en contact avec, le stator ou le rotor, p.ex. des ponts de chaleur
A stator includes a stator hub, a plurality of stator teeth extending from stator hub that define a stator slot and at least one winding disposed in the stator slot, the winding including a cooling passage formed therein through. The cooling passage is connected to an inlet plenum and an outlet plenum. The stator can also include coil separators that include cooling passages.
H02K 3/24 - Enroulements caractérisés par la configuration, la forme ou le genre de construction du conducteur, p.ex. avec des conducteurs en barre avec des canaux ou des conduits pour un agent de refroidissement entre les conducteurs
H02K 3/30 - Enroulements caractérisés par leur matériau d'isolement
H02K 3/32 - Enroulements caractérisés par la configuration, la forme ou la réalisation de l'isolement
H02K 3/34 - Enroulements caractérisés par la configuration, la forme ou la réalisation de l'isolement entre conducteurs ou entre conducteur et noyau, p.ex. isolement d'encoches
H02K 9/19 - Dispositions de refroidissement ou de ventilation pour machines avec enveloppe fermée et circuit fermé de refroidissement utilisant un agent de refroidissement liquide, p.ex. de l'huile
25.
HEADER GUIDING FLUID FLOW TO AND FROM COOLING CHANNELS IN A HIGH DENSITY MOTOR
A header for an electric machine that include a stator core and one or more windings that include coolant passages formed therein. The header includes an inlet to receive a coolant, an outlet though which the coolant exits the header, an inlet plenum fluidly connected to the inlet, and an outlet plenum fluidly separated from the inlet plenum and fluidly connected to the outlet. The inlet and outlet plenums each have a varying cross section that varies from a top of the header as compared to a bottom of the header.
H02K 3/24 - Enroulements caractérisés par la configuration, la forme ou le genre de construction du conducteur, p.ex. avec des conducteurs en barre avec des canaux ou des conduits pour un agent de refroidissement entre les conducteurs
H02K 9/19 - Dispositions de refroidissement ou de ventilation pour machines avec enveloppe fermée et circuit fermé de refroidissement utilisant un agent de refroidissement liquide, p.ex. de l'huile
F16K 11/06 - Soupapes ou clapets à voies multiples, p.ex. clapets mélangeurs; Raccords de tuyauteries comportant de tels clapets ou soupapes; Aménagement d'obturateurs et de voies d'écoulement spécialement conçu pour mélanger les fluides dont toutes les faces d'obturation se déplacent comme un tout comportant uniquement des tiroirs
F15C 3/02 - Eléments de circuits ayant des parties en mouvement utilisant des clapets à bobines
F16K 51/00 - Autres détails non particuliers aux types de soupapes ou clapets ou autres appareils d'obturation
System and methods for motor drive electronics are provided. Aspects include receiving, by a controller on a motor driver electronics (MDE) component, voltage data associated with a thermoelectric generator, wherein the MDE component is configured to operate an electric motor, and wherein the MDE component comprises a power card including one or more components, determining a temperature reading based on the voltage data, enacting an action associated with the MDE component based at least in part on the temperature reading.
H02P 29/68 - Commande ou détermination de la température du moteur ou de l'entraînement basée sur la température d’un composant d’entraînement ou d’un composant semi-conducteur
29.
MULTI-ELEMENT PROPELLER BLADE DEICER SCHEME FOR BALANCED THREE-PHASE ELECTRICAL LOADS
Provided are embodiments for deicing an aircraft propeller having a plurality of blades of an aircraft. An example method includes performing a first heating, by a first plurality of heating elements connected to a first portion of each of the plurality of blades, for a first period of time, the first portion of each of the plurality of blades of the propeller defining a first deicing zone. The method further includes, subsequent to expiration of the first period of time, performing a second heating, by a second plurality of heating elements connected to a second portion of each of the plurality of blades, for a second period of time, the second portion of each of the plurality of blades of the propeller defining a second deicing zone.
ABSTRACT Disclosed is a piston position control system that includes a fluid control valve configured to control a position of a piston. The piston position control system includes a controller having stored instructions operable to receive a piston position command. The stored instructions are operable to receive a first time-of-flight and a second time-of- flight. The stored instructions are operable to operate the fluid control valve to adjust the position of the piston according to the piston position command based on a position estimate defined by the first time-of-flight, t1 and the second time-of- flight, t2. The stored instructions are operable to adjust the position estimate to operate the fluid control valve based on a baseplate temperature derived from a fluid temperature defined by the first time-of-flight and the second time-of-flight. CA 3064813 2019-12-11
ABSTRACT A method of monitoring a power drive unit installed on an aircraft is provided. The method includes causing, by a controller, sensors to measure an angular position at corresponding locations along at least one wing of the aircraft. The controller, as part of the method, receives the angular position from the one or more sensors and analyzes the angular position to generate feedback information to implement the monitoring of the power drive unit. CA 3064625 2019-12-10
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
G01D 5/22 - Moyens mécaniques pour le transfert de la grandeur de sortie d'un organe sensible; Moyens pour convertir la grandeur de sortie d'un organe sensible en une autre variable, lorsque la forme ou la nature de l'organe sensible n'imposent pas un moyen de conversion déterminé; Transducteurs non spécialement adaptés à une variable particulière utilisant des moyens électriques ou magnétiques influençant la valeur d'un courant ou d'une tension en faisant varier l'inductance, p.ex. une armature mobile influençant deux bobines par une action différentielle
A method of manufacturing a component is described. The method comprises: making a preform from a powdered material, the preform having a density in a range from 70 to 95% of theoretical density of the material; and sintering the preform using a Field Assisted Sintering Technique (FAST) process to produce a component having a density of greater than 97% of the theoretical density of the material. Components, in particular low aspect components, formed by said method are also described.
B29C 64/153 - Procédés de fabrication additive n’utilisant que des matériaux solides utilisant des couches de poudre avec jonction sélective, p.ex. par frittage ou fusion laser sélectif
Disclosed is a compound harmonic gearbox having: a first ground gear and a second ground gear being interconnected about a stationary shaft to form a housing, wherein only the first ground gear includes gearbox mounting features; an output flange partially encased within the housing; a flex spline within the housing that drives the output flange; a wave generator within the housing that drives the flex spline; an input shaft with an input gear that drives the wave generator, the input shaft extending through the first ground gear, wherein the output flange is configured to rotate completely around the stationary shaft by rotating the input shaft.
An actuator is provided and includes first and second shafts, a friction plate affixed to the second shaft, a one-way clutch that includes an inner diameter portion affixed to the first shaft, an outer diameter portion and a one-way clutch portion interposed between the inner and output diameter portions and a bearing. The bearing is disposed such that a compressive load path is formed from the first shaft, through the bearing and the outer diameter portion and to the friction plate and the second shaft. The one-way clutch portion is configured for free-wheeling during forward rotation of the first shaft that permits forward rotation transmission to the second shaft and for jamming during reverse rotation of the first shaft to create a drag event on the friction plate that inhibits reverse rotation transmission to the second shaft.
Disclosed is a compound harmonic gear motor having: first and second ground gears connected by a stationary shaft; a wave generator including an outer surface that can rotate completely around the stationary shaft, the wave generator including a rotor and a stator, wherein rotation of the rotor causes rotation of the outer surface; a flex spline surrounding the outer surface of the wave generator that is driven to rotate by rotation of the outer surface of the wave generator; and an output flange including internal teeth that mate with the flex spline to cause rotation of the output flange completely around the stationary shaft.
F16H 3/04 - Transmissions à engrenages pour transmettre un mouvement rotatif à rapport de vitesse variable ou pour inverser le mouvement rotatif sans engrenages à mouvement orbital dentés intérieurement
F16H 9/00 - Transmissions pour transmettre un mouvement rotatif à rapport de vitesse variable ou pour inverser un mouvement rotatif par des organes flexibles sans fin
F16H 35/00 - Transmissions ou mécanismes ayant d'autres caractéristiques de fonctionnement particulières
H02K 7/116 - Association structurelle avec des embrayages, des freins, des engrenages, des poulies ou des démarreurs mécaniques avec des engrenages
36.
AIRCRAFT PROPELLER ELECTRIC BLADE PITCH CHANGE AND CONTROL
A propeller assembly of an aircraft includes a hub, a plurality of propeller blades extending from the hub and secured thereto and a propeller blade pitch change system located at at least one propeller blade of the plurality of propeller blades. The propeller blade pitch change system includes a pitch change actuator located in the propeller blade, and a drive mechanism operably connected to the pitch change actuator and to the propeller blade to urge rotation of the propeller blade about a propeller blade axis.
A thermal desorber assembly includes a housing and a desorption heater element mounted in the housing with a sample cavity defined between the desorption heater element and an inner wall of the housing. An outlet port is defined in the housing. A flow channel connects the sample cavity in fluid communication with the outlet port for conveying analytes from the sample cavity to the outlet port for introducing the analytes to a spectrometer.
An aerodynamic blade is provided and includes a blade body and a light module. The blade body includes an inboard end and a tip outboard of the inboard end. The blade body is connectable with a hub at the inboard end such that rotations of the hub drive rotations of the tip about a rotational axis. The light module is disposed in the tip and configured to activate in response to the rotations of the tip about the rotational axis to emit light visible at an exterior of the blade body
B64D 47/02 - Aménagements ou adaptations des dispositifs de signalisation ou d'éclairage
H05B 47/115 - Commande de la source lumineuse en réponse à des paramètres détectés en détectant la présence ou le mouvement d'objets ou d'êtres vivants
F21K 9/00 - Sources lumineuses utilisant des dispositifs à semi-conducteurs en tant qu’éléments générateurs de lumière, p.ex. utilisant des diodes électroluminescentes [LED] ou des lasers
A composite part is provided and includes a component, a first set of first composite plies with finite lengths and a second set of second composite plies with finite lengths. A respective end of each of the first composite plies is wrapped around the component in a clockwise wrapping direction and includes first fibers. A respective end of each of the second composite plies is wrapped around the component in a counter-clockwise wrapping direction and includes second fibers.
B29C 53/40 - Cintrage et assemblage, p.ex. pour la fabrication d'objets creux par cintrage de feuilles ou de bandes perpendiculairement à l'axe longitudinal de l'objet à former et assemblage des bords pour la fabrication d'objets de longueur définie, c. à d. d'objets séparés
An inverted compound harmonic drive including: a wave generator configured to receive rotational input; a flex spline disposed radially within the wave generator that receives energy due to the rotation of the wave generator, the flex spline including a plurality of inner facing splines that include an axial center spline, a first axial end spline being adjacent to and forward of the axial center spline, and a second axial end spline adjacent to and aft of the axial center spline; an output gear meshes with the axial center spline; a first ground gear adjacent to and forward of the output gear that meshes with the first axial end spline; and a second ground gear adjacent to an aft of the output gear that meshes with the second axial end spline.
F16H 3/04 - Transmissions à engrenages pour transmettre un mouvement rotatif à rapport de vitesse variable ou pour inverser le mouvement rotatif sans engrenages à mouvement orbital dentés intérieurement
B64C 13/34 - Dispositifs de transmission sans amplification de puissance ou dans les cas où l'amplification de puissance est sans objet mécaniques utilisant des engrenages
B64C 13/50 - Dispositifs de transmission avec amplification de puissance utilisant l'énergie électrique
F16H 9/00 - Transmissions pour transmettre un mouvement rotatif à rapport de vitesse variable ou pour inverser un mouvement rotatif par des organes flexibles sans fin
F16H 35/00 - Transmissions ou mécanismes ayant d'autres caractéristiques de fonctionnement particulières
Disclosed is a corrosion inhibition coating, comprising: a base comprising a silicate matrix, wherein aluminum, an aluminum alloy, or a combination thereof, is present within the silicate matrix; and an inhibitor comprising: zinc molybdate, cerium citrate, magnesium metasilicate, a metal phosphate silicate, or a combination thereof, wherein a curing temperature of the corrosion inhibition coating is about 20°C to about 190°C, preferably about 20°C to about 120°C. Also disclosed is a substrate coated with the corrosion inhibition coating, wherein the substrate is a peened part.
C09D 1/02 - Compositions de revêtement, p.ex. peintures, vernis ou vernis-laques, à base de substances inorganiques silicates de métaux alcalins
C09D 1/04 - Compositions de revêtement, p.ex. peintures, vernis ou vernis-laques, à base de substances inorganiques silicates de métaux alcalins avec des adjuvants organiques
An ion mobility spectrometer for analyzing a vapor sample including a multi- ring ion source for receiving a vapor sample, wherein the multi-ring ion source includes a series of rings, wherein each ring of the multi-ring ion source includes an ionizing layer on an inner surface thereof, for charging at least a portion of the vapor sample and creating an ionized vapor sample.
H01J 49/04 - Dispositions pour introduire ou extraire les échantillons devant être analysés, p.ex. fermetures étanches au vide; Dispositions pour le réglage externe des composants électronoptiques ou ionoptiques
43.
AIRCRAFT HAVING HYBRID-ELECTRIC PROPULSION SYSTEM WITH ELECTRIC STORAGE LOCATED IN WINGS
An aircraft includes a fuselage defining a longitudinal axis between a forward end and a aft end. At least one airfoil is laterally extending from the fuselage defining an airfoil axis. An electrical system has an electric storage. The electric storage is positioned within the airfoil.
B64C 3/32 - Voilures spécialement adaptées pour le montage des groupes propulseurs
B64D 27/02 - Aéronefs caractérisés par le type ou la position des groupes moteurs
B64D 29/02 - Nacelles, carénages ou capotages des groupes moteurs montés dans les ailes
B64D 29/06 - Fixation des nacelles, carénages ou capotages
B64D 33/08 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des systèmes de refroidissement des ensembles fonctionnels de propulsion
B64D 37/04 - Disposition de ceux-ci à l'intérieur ou sur les aéronefs
An indicator for a hybrid electric powerplant for an aircraft can be configured to indicate at least an amount or percentage of a total power and/or total torque, and an amount or percentage of an electric motor power and/or electric motor torque. For example, the indicator can be a graphical user interface (GUI) of an aircraft cockpit display.
An electrical power system is disclosed for an aircraft having a hybrid-electric propulsion system, which includes a battery assembly for storing energy, an electric motor controller operatively connected to the battery assembly for conditioning and controlling power to an electric motor, and an electric motor receiving power through the motor controller for delivering torque to a shaft of the hybrid-electric propulsion system.
B60L 58/10 - Procédés ou agencements de circuits pour surveiller ou commander des batteries ou des piles à combustible, spécialement adaptés pour des véhicules électriques pour la surveillance et la commande des batteries
B60L 15/20 - Procédés, circuits ou dispositifs pour commander la propulsion des véhicules à traction électrique, p.ex. commande de la vitesse des moteurs de traction en vue de réaliser des performances désirées; Adaptation sur les véhicules à traction électrique de l'installation de commande à distance à partir d'un endroit fixe, de différents endroits du véhicule ou de différents véhicules d'un même train pour la commande du véhicule ou de son moteur en vue de réaliser des performances désirées, p.ex. vitesse, couple, variation programmée de la vitesse
H02H 3/00 - Circuits de protection de sécurité pour déconnexion automatique due directement à un changement indésirable des conditions électriques normales de travail avec ou sans reconnexion
H02J 1/00 - Circuits pour réseaux principaux ou de distribution, à courant continu
H02J 7/00 - Circuits pour la charge ou la dépolarisation des batteries ou pour alimenter des charges par des batteries
H02P 7/00 - Dispositions pour réguler ou commander la vitesse ou le couple de moteurs électriques à courant continu
H05K 10/00 - Dispositions pour améliorer la sécurité de fonctionnement d'un équipement électronique, p.ex. en prévoyant une unité de réserve similaire
46.
AIRCRAFT HAVING HYBRID-ELECTRIC PROPULSION SYSTEM WITH ELECTRIC STORAGE LOCATED IN FUSELAGE
An aircraft includes a fuselage defining a longitudinal axis between a forward end and an aft end. The aircraft includes an electrical system having an electric storage. The electric storage is positioned within the fuselage.
B64C 1/16 - Fuselages; Caractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés spécialement adaptés pour le montage du groupe propulseur
B64D 27/02 - Aéronefs caractérisés par le type ou la position des groupes moteurs
B64D 29/02 - Nacelles, carénages ou capotages des groupes moteurs montés dans les ailes
B64D 29/06 - Fixation des nacelles, carénages ou capotages
B64D 33/08 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des systèmes de refroidissement des ensembles fonctionnels de propulsion
B64D 37/04 - Disposition de ceux-ci à l'intérieur ou sur les aéronefs
An actuator system includes one or more mechanical elements and a temperature radio frequency identification (RFID) tag connected to at least one of the one or more mechanical elements. The temperature RFID tag includes an RFID tag connected to a temperature sensitive element that includes: a first contact; a second contact; and a conduction path between the first and second contacts. In a normal operational state the conduction path creates an electrical pathway between the first contact element and second contact element and when in an over-temperature state the conduction path does not create an electrical pathway between the first contact and the second contact. The RFID tag is connected to the first contact and the second contact such that when the temperature sensitive element is in the normal operation state the RFID tag does not transmit information does when the temperature sensitive element is in the over-temperature state.
G01K 7/16 - Mesure de la température basée sur l'utilisation d'éléments électriques ou magnétiques directement sensibles à la chaleur utilisant des éléments résistifs
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
A method of controlling discharge of a holdup capacitor in a power system having a voltage source, a holdup capacitor and a load. The method including operably connecting the voltage source to the load, monitoring a first voltage of the voltage source, and if the first voltage of the voltage source drops below a selected threshold, directing energy from the holdup capacitor to the load via a first path, and directing energy from the holdup capacitor to the load via a second path if a selected condition is satisfied.
H02J 9/00 - Circuits pour alimentation de puissance de secours ou de réserve, p.ex. pour éclairage de secours
B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
H02J 13/00 - Circuits pour pourvoir à l'indication à distance des conditions d'un réseau, p.ex. un enregistrement instantané des conditions d'ouverture ou de fermeture de chaque sectionneur du réseau; Circuits pour pourvoir à la commande à distance des moyens de commutation dans un réseau de distribution d'énergie, p.ex. mise en ou hors circuit de consommateurs de courant par l'utilisation de signaux d'impulsion codés transmis par le réseau
49.
PROPELLER BLADE ANGLE CLOSED LOOP CONTROL BY SOLENOID MODULATION
A system for controlling a propeller having a plurality of blades having a primary control system and a backup control system. The primary control system including a sensor responsive to a propeller state, and a controller connected to the sensor and to an electrohydraulic control actuator. The electrohydraulic control actuator connected via a bypass valve to a hydraulic actuator that controls at least a blade angle of a blade of the propeller. The controller generating commands to the electrohydraulic control actuator based on at least the propeller state. The backup control system including a second controller, an electrohydraulic solenoid operably connected to the bypass valve. The backup control system operable to hydraulically disable the primary control system via the bypass valve upon the occurrence of a selected condition, the second controller modulates the operation of the electrohydraulic solenoid to control the bypass actuator based on the propeller state.
Disclosed is a corrosion inhibition coating, comprising: a base comprising a matrix and a metal within the matrix; and an inhibitor comprising: zinc molybdate, cerium citrate, magnesium metasilicate, a metal phosphate silicate, or a combination thereof, wherein the metal within the matrix comprises aluminum, an aluminum alloy, zinc, a zinc alloy, magnesium, a magnesium alloy, or a combination thereof. Also disclosed is a substrate coated with the corrosion inhibition coating.
Provided are embodiments for operating an autonomous mode change circuit for solenoid drivers. The embodiments include initiating an operation of a solenoid, and receiving a command to control the operation of the solenoid. The embodiments also include controlling, by a drive circuit, a switch coupled to the solenoid based at least in part on the command, and detecting at least one of a current or voltage of the solenoid, and subsequently controlling the operation of the solenoid based at least in part on the detection.
H01F 7/18 - Circuits en vue d'obtenir des caractéristiques de fonctionnement souhaitées, p.ex. pour un fonctionnement lent, pour l'excitation successive des enroulements, pour l'excitation à grande vitesse des enroulements
H03K 17/00 - Commutation ou ouverture de porte électronique, c. à d. par d'autres moyens que la fermeture et l'ouverture de contacts
A rotary actuator including: an electric motor including: a left shaft projecting out towards a left-hand side; a left motor operably connected to the left shaft; a right shaft projecting out towards a right-hand side; and a right motor operably connected to the right shaft; an actuator housing operably connected to the right shaft; a left outer actuator shaft operably connected to the actuator housing; a left inner actuator shaft operably connected to the left shaft; and an output gearbox including: a ring gear rigidly connected to the left outer actuator shaft; a center gear located within the ring gear, the center gear being operably connected to the left inner actuator shaft; a planetary gear interposed between the ring gear and center gear, the planetary gear meshing with the ring gear and center gear; and an actuator stub operably connected to the planetary gear.
H02K 7/116 - Association structurelle avec des embrayages, des freins, des engrenages, des poulies ou des démarreurs mécaniques avec des engrenages
B64C 13/50 - Dispositifs de transmission avec amplification de puissance utilisant l'énergie électrique
F16H 1/22 - Transmissions à engrenages pour transmettre un mouvement rotatif sans engrenages à mouvement orbital comportant plus de deux organes engrenés avec dispositions pour répartir le couple entre plusieurs arbres intermédiaires
F16H 37/06 - Combinaisons de transmissions mécaniques non prévues dans les groupes comportant essentiellement et uniquement des transmissions à engrenages ou à friction avec dispositions pour répartir le couple entre plusieurs arbres intermédiaires
A servovalve comprising: a fluid transfer valve assembly comprising a supply port and a control port; a moveable valve spool (2) arranged to regulate flow of fluid from the supply port to the control port in response to a control signal; and a drive assembly configured to axially move the valve spool relative to the fluid transfer assembly in response to the control signal to regulate the fluid flow; wherein the drive assembly comprises a first fluid channel (11') providing a flow path for fluid from the supply port to a first end of the spool (2) and provided with a first flow control orifice (20), a second fluid channel (12') providing a flow path for fluid from the supply port to a second end of the spool (2) and provided with a second flow control orifice (21) and a rotating element (8) provided with a cam profile, located between the first flow control orifice and the second flow control orifice, and drive means (17) arranged to rotate the rotating element (8) to vary the rotational position of the cam profile with respect to the first and second flow control orifice, in response to the control signal, to control flow from the first and second flow control orifice and this to control movement of the valve spool (2).
F15B 13/042 - Dispositifs de distribution ou d'alimentation du fluide caractérisés par leur adaptation à la commande de servomoteurs pour utilisation avec un servomoteur unique actionnés par la pression du fluide
F15B 13/02 - Dispositifs de distribution ou d'alimentation du fluide caractérisés par leur adaptation à la commande de servomoteurs
F16K 11/076 - Soupapes ou clapets à voies multiples, p.ex. clapets mélangeurs; Raccords de tuyauteries comportant de tels clapets ou soupapes; Aménagement d'obturateurs et de voies d'écoulement spécialement conçu pour mélanger les fluides dont toutes les faces d'obturation se déplacent comme un tout comportant uniquement des tiroirs à éléments de fermeture articulés à pivot à faces d'obturation épousant la surface d'un solide de révolution
F16K 31/04 - Moyens de fonctionnement; Dispositifs de retour à la position de repos magnétiques utilisant un moteur
F16K 37/00 - Moyens particuliers portés par ou sur les soupapes ou autres dispositifs d'obturation pour repérer ou enregistrer leur fonctionnement ou pour permettre de donner l'alarme
54.
LINEAR ACTUATOR WITH TESTABLE CONE NO-BACK AND TORQUE LIMITER
A cone brake no-back includes an input no-back disk, an output no-back disk; and a no-back ball ramp mechanism operably connected to the input no-back disk and the output no back disk. An input no-back cone is operably connected to and supportive of the input no-back disk. The input no-back cone is axially loaded by an input no-back spring. An output no-back cone is operably connected to and supportive of the output no-back disk. The output no-back cone is axially loaded by an output no- back spring. A no-back input shaft is operably connected to the input no-back disk and the output no back disk, and a no-back output shaft is operably connected to the output no back disk.
F16D 59/00 - Freins automatiques, p.ex. entrant en action à une vitesse prédéterminée
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
B64C 13/28 - Dispositifs de transmission sans amplification de puissance ou dans les cas où l'amplification de puissance est sans objet mécaniques
F16D 67/00 - Combinaisons d'accouplements et de freins; Combinaisons d'embrayages et de freins
F16H 25/22 - Mécanismes à vis avec billes, rouleaux ou organes similaires entre pièces travaillant en conjugaison; Eléments essentiels pour l'utilisation de ces organes
The embodiments include a method for operating and a circuit for H-type multilevel power converter. The embodiments include power supply voltage rails and a neutral point, and a DC link capacitor coupled to the power supply voltage rails. Also the embodiments include an H-bridge switching network, wherein the H- bridge switching network is coupled to the power supply voltage rails, the neutral point and an output inverter stage, and the output inverter stage, wherein the output inverter stage comprises one or more pairs of switches that are coupled to an output phase and are configured to operate in a complementary mode.
H02M 7/5387 - Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant alternatif sans possibilité de réversibilité par convertisseurs statiques utilisant des tubes à décharge avec électrode de commande ou des dispositifs à semi-conducteurs avec électrode de commande utilisant des dispositifs du type triode ou transistor exigeant l'application continue d'un signal de commande utilisant uniquement des dispositifs à semi-conducteurs, p.ex. onduleurs à impulsions à un seul commutateur dans une configuration en pont
56.
PIEZO TORQUE TUBE STRAIN GAUGE WITH PIEZO GENERATOR
A torque tube sensor to measure torque on a torque tube includes a sensor body including at least a first body section and a second body section and one or more strain gauges including a first strain gauge disposed in the first body section, the first strain gauge including a piezo-electric layer that produces a voltage based on deflection of the layer. The sensor also includes a first transmitter that includes a controller, a power generator and wireless transmitter, wherein the controller receives the voltage produced by the piezo-electric layer.
G01L 3/10 - Dynamomètres de transmission rotatifs dans lesquels l'élément transmettant le couple comporte un arbre élastique en torsion impliquant des moyens électriques ou magnétiques d'indication
G01B 7/16 - Dispositions pour la mesure caractérisées par l'utilisation de techniques électriques ou magnétiques pour mesurer les déformations dans un solide, p.ex. au moyen d'une jauge de contrainte à résistance
A control surface disconnect detection system includes a mechanical disconnect detection device that includes: a first contact element; a second contact element; and a mechanical fuse that includes a conduction path. In a normal operational state the conduction path creates an electrical pathway between the first contact element and second contact element and when in a control surface disconnected state the conduction path does not create an electrical pathway between the first contact element and the second contact element. The system also includes a radio frequency identification (RFID) tag connected to the first contact element and the second contact element such that when the mechanical disconnect detection device is in the normal operation state the RFID tag does not transmit information, and when the mechanical disconnect detection device is in the control surface disconnected state the RFID tag does transmit information.
An over torque detection system includes a mechanical torque sensor and a radio frequency identification (RFID) tag. The mechanical torque sensor includes first and second contact elements and a moveable element coupled to the first contact element. In a normal operational state the moveable element is in contact with the second contact element and creates an electrical pathway between the first and second contact elements and when in over torque operational state the movable element moves such that it does not contact the second contact element. The RFID tag is connected to the first contact element and the second contact element such that when the mechanical torque sensor is in the normal operation state the RFID tag does not transmit information, and when the mechanical torque sensor is in the over torque operation state the RFID tag does transmit information.
G01L 5/00 - Appareils ou procédés pour la mesure des forces, du travail, de la puissance mécanique ou du couple, spécialement adaptés à des fins spécifiques
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
B64C 3/50 - Variation de la courbure par volets de bord d'attaque ou de bord de fuite
B64C 13/28 - Dispositifs de transmission sans amplification de puissance ou dans les cas où l'amplification de puissance est sans objet mécaniques
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
G01L 3/00 - Mesure du couple, du travail, de la puissance ou du rendement mécanique en général
A blade for a propeller including a blade composite structure includes a Fiber Bragg Grating (FBG) or an Extrinsic Fabry-Perot Interferometric (EFPI) sensor embedded in the blade composite structure. The sensor is configured to receive a signal from a controller operatively connected to the FBG or EFPI sensor, and transmit a signal, responsive to the received signal, to a processor operatively connected to the sensor. The signal response is indicative of a stress measurement indicating a structural characteristic of the blade composite structure. The signal response provides information to determine, based on the signal response, whether the structural characteristic of the blade composite structure is within a predetermined limit indicative of structural integrity of the blade composite structure.
G01L 1/24 - Mesure des forces ou des contraintes, en général en mesurant les variations des propriétés optiques du matériau quand il est soumis à une contrainte, p.ex. par l'analyse des contraintes par photo-élasticité
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
A system includes a turbo pump configured to convert a tank compressed gas or an engine compressed gas into at least one of electrical power, hydraulic power, or pneumatic power. The system also includes a storage tank configured to store the tank compressed gas. The system also includes a bleed line configured to port the engine compressed gas from the gas turbine engine to the turbo pump. The system also includes a propellant selector valve having an off position in which the turbo pump is prevented from receiving either the tank compressed gas or the engine compressed gas, a tank position in which the tank compressed gas from the storage tank is ported through the propellant selector valve to the turbo pump, and an engine position in which the engine compressed gas from the bleed line is ported through the propellant selector valve to the turbo pump.
B64D 25/00 - Appareils ou dispositifs pour circonstances critiques, non prévus ailleurs
A62C 3/08 - Prévention, limitation ou extinction des incendies spécialement adaptées pour des objets ou des endroits particuliers dans les véhicules, p.ex. les véhicules routiers dans les avions
A62C 35/02 - Matériel installé à demeure avec des réservoirs pour délivrer la substance extinctrice
B64D 13/00 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret
B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
61.
COUNTER-ROTATING PROPELLER SYSTEM WITH CAPABILITY TO STOP ROTATION OF ONE ROW
A propeller system has a pair of rotors and a pair of blade sets and at least one a drive input to drive a first of the rotors and blade sets and a second of the rotors and blade sets. The blade sets are positioned such that when both are driven, air will be driven across the first blade set and then across the second blade set. There is a pitch change mechanism to change an angle of incidence of the blade in at least one blade sets. There is a device for selectively stopping rotation of at least one of the first or second rotor and blade set while still allowing rotation of the other rotor and blade set. The pitch change mechanism of the stopped blade set can still change the angle of incidence when the device has stopped rotation. A method is also disclosed.
B64C 11/46 - Aménagements ou caractéristiques de construction des hélices multiples
B64C 11/30 - Mécanismes de changement de pas des pales
B64D 35/06 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions caractérisée par le fait que la transmission entraîne plusieurs hélices ou rotors les hélices ou rotors tournant en sens inverse
62.
METHOD AND SYSTEM FOR DETECTING RESOLVER/SYNCHRO FAULTS
Embodiments herein relate to a sensor fault measurement system. The system includes a sensor having a primary winding, a first secondary winding and a second secondary winding and a wiring harness operably connected to the primary winding, first secondary winding and second secondary winding of the sensor. The system also includes a controller operably connected to the wiring harness. The controller includes a bias network configured to apply a common mode DC voltage bias of opposite sign to the first sensor output and the second sensor output respectively, and a fault sense circuit configured to monitor the DC voltage bias on first sensor output and the DC voltage bias on second sensor output, and identify a sensor fault if at least one of the DC voltage bias on first sensor output and the DC voltage bias second sensor output is impacted beyond a selected threshold.
A retainer assembly is adapted to secure a removable electronic unit within an avionics equipment mounting tray. The retainer assembly includes a latch having a base portion and a handle portion. The base portion is pivotally coupled to one of the removable electronic unit and the avionics equipment mounting tray. The handle portion projects outward from the base portion. The base portion includes a cam surface adapted to releasably contact the other of the removable electronic unit and the avionics equipment mounting tray.
F16B 2/16 - Brides ou colliers, c. à d. dispositifs de fixation dont le serrage est effectué par des forces effectives autres que la résistance à la déformation inhérente au matériau dont est fait le dispositif utilisant des rouleaux ou des billes
64.
CONTROL OF MULTIPLE FLIGHT CONTROL SURFACE SYSTEMS USING SINGLE POWER DRIVE UNIT
A secondary flight control system is provided. The secondary flight control system comprising: a first flight control surface system; a second flight control surface system; and a power distribution unit operably connected to the first flight control surface system and the second flight control surface system, wherein the power distribution unit is configured to generate torque to actuate the first flight control surface system and the second flight control surface system.
According to one embodiment, linear motor translator assembly for use in an electromagnetic actuator is provided. The linear motor translator assembly comprises: a cylindrical housing having a first end, a second end opposite the first end, a flanged portion at the second end, and a blind hole initiating at the second end and extending into the cylindrical housing to a blind hole base; a tubular body located within the blind hole, the tubular body including a plurality of permanent magnets; and an end cap securely fastened to the flanged portion.
B64C 11/44 - Mécanismes de changement de pas des pales électriques
B64C 27/68 - Transmissions, p.ex. en liaison avec les moyens déclenchant ou agissant sur les pales utilisant l'énergie électrique, p.ex. avec un amplificateur de puissance électrique
66.
ACTUATOR ASSEMBLY HAVING SELF-LUBRICATING COMPONENTS
An actuator assembly includes a housing, a piston rod, and an end gland. The housing defines a housing bore that extends along a first axis between a first housing end and a second housing end. The piston rod is at least partially disposed within the housing bore. The piston rod defines a piston bore that extends from a first piston end towards a second piston end along the first axis. The end gland has a first end gland surface that engages the piston rod and a second end gland surface that engages the housing bore. The end gland defines a first gland groove that extends from the first end gland surface towards the second end gland surface. The first gland groove is arranged to receive a self-lubricating filler that engages the piston rod. A self-lubricating bushing may also be provided to deposit a lubricant into the piston bore.
E05F 15/53 - Mécanismes pour battants mus par une force motrice utilisant des actionneurs à pression de fluide pour battants pivotants
B64D 29/00 - Nacelles, carénages ou capotages des groupes moteurs
F15B 15/14 - Dispositifs actionnés par fluides pour déplacer un organe d'une position à une autre; Transmission associée à ces dispositifs caractérisés par la structure de l'ensemble moteur le moteur étant du type à cylindre droit
F15B 15/22 - Autres parties constitutives pour accélérer ou ralentir le mouvement
F16C 33/10 - Structures relatives à la lubrification
F16C 33/12 - Composition structurale; Emploi de matériaux spécifiés ou de traitement particulier des surfaces, p.ex. contre la rouille
F16J 15/56 - Autres joints pour tiges à mouvement alternatif
F16N 15/00 - Lubrification avec substances autres que l'huile ou la graisse; Lubrification caractérisée par l'utilisation de lubrifiants particuliers dans des appareils particuliers ou dans des conditions particulières
A pressure relief valve (PRV) is provided. The PRV includes a first housing part and a second housing part. The first housing part includes first major and minor surfaces and a first deformed corner at an intersection of the first major and minor surfaces. The second housing part includes second major and minor surfaces and a second deformed corner at an intersection of the second major and minor surfaces. The first and second housing parts are disposed with the first and second minor surfaces facing oppositely at a distance to define a metering hole. The first and second deformed corners are deformed by a coining ball to cooperatively form a coined seat at the metering hole for seating and re-seating a sealing ball. The first and second deformed corners have respective radii of curvatures resulting from deformation which are larger than that of the sealing ball.
F16K 17/02 - Soupapes ou clapets de sûreté; Soupapes ou clapets d'équilibrage fermant sur insuffisance de pression d'un côté
F16K 17/04 - Soupapes ou clapets de sûreté; Soupapes ou clapets d'équilibrage fermant sur insuffisance de pression d'un côté actionnés par ressort
F16K 25/00 - SOUPAPES; ROBINETS; VANNES; COMMANDES À FLOTTEURS; DISPOSITIFS POUR VENTILER OU AÉRER - Détails constitutifs relatifs au contact entre corps de soupapes ou de clapets et leurs sièges
A hydraulic piston actuator, which may be used for an aircraft nacelle assembly, includes a housing, a piston, an end gland, and a bearing ring. The housing is concentrically disposed along an axis. The piston is adapted to axially reciprocate within the housing. The end gland is disposed radially between the housing and the piston. The bearing ring is disposed radially between the end gland and the piston.
E05F 15/50 - Mécanismes pour battants mus par une force motrice utilisant des actionneurs à pression de fluide
E05F 15/53 - Mécanismes pour battants mus par une force motrice utilisant des actionneurs à pression de fluide pour battants pivotants
B64D 33/00 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs
F15B 15/14 - Dispositifs actionnés par fluides pour déplacer un organe d'une position à une autre; Transmission associée à ces dispositifs caractérisés par la structure de l'ensemble moteur le moteur étant du type à cylindre droit
A system for controlling the movement of an aircraft engine cowl door includes an actuator assembly having a housing and a screw shaft arranged at least partially within a hollow interior of the housing. The screw shaft is rotatable about an axis relative to the housing. A transmission system is coupled to the screw shaft to impart rotation to the screw shaft about the axis. A nut is engaged with the screw shaft and a piston rod having a rod end mounted thereto connects the nut to the cowl door of the engine. The nut is translatable relative to the screw shaft to transition the cowl door between a first position and a second position.
E05F 15/622 - Mécanismes pour battants mus par une force motrice utilisant des actionneurs électriques utilisant des électromoteurs rotatifs pour battants pivotants manœuvrés par mécanismes "pousser-tirer" utilisant des mécanismes à écrou et vis
B64D 33/00 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs
A check valve includes a housing, a first valve, and a second valve. The housing has a first portion that defines a first chamber and a second portion that defines a second chamber. The first valve is disposed within and is movable relative to the housing. The second valve is at least partially extends into the first valve. Responsive to a fluid flow in a first direction, the second valve and the first valve moves towards a proximal end of the housing and the fluid flow flows around the first valve towards a component.
F15B 20/00 - Dispositions propres à la sécurité pour systèmes de manœuvre utilisant les fluides; Utilisation des dispositifs de sécurité dans les systèmes de manœuvre utilisant des fluides; Mesures d'urgence pour les systèmes de manœuvre utilisant des fluides
71.
ACTUATOR WITH VIBRATION ATTENUATION USING VISCO ELASTIC MATERIALS
An actuator is provided for an aircraft engine and includes a tubular base layer and a visco-elastic layer adhesively disposed on the tubular base layer.
E06B 5/00 - Portes, fenêtres ou fermetures analogues à buts particuliers; Structures de cadrage à leur effet
F16F 15/04 - Suppression des vibrations dans les systèmes non rotatifs, p.ex. dans des systèmes alternatifs; Suppression des vibrations dans les systèmes rotatifs par l'utilisation d'organes ne se déplaçant pas avec le système rotatif utilisant des moyens élastiques
An actuator assembly includes a housing, a piston rod, and a lost motion device. The housing defines a housing bore that extends along a first axis from a first housing end towards a second housing end. The piston rod is at least partially disposed within the housing bore. The piston rod defines a piston bore that extends from a first piston end towards a second piston end along the first axis. The lost motion device is at least partially disposed within the housing bore and extends into the piston bore. The lost motion device and the piston rod are arranged to move relative to the housing along the first axis.
B66F 3/32 - Moyens pour éviter les à-coups excessifs en fin de mouvement
E05F 15/53 - Mécanismes pour battants mus par une force motrice utilisant des actionneurs à pression de fluide pour battants pivotants
B64D 29/00 - Nacelles, carénages ou capotages des groupes moteurs
F15B 15/14 - Dispositifs actionnés par fluides pour déplacer un organe d'une position à une autre; Transmission associée à ces dispositifs caractérisés par la structure de l'ensemble moteur le moteur étant du type à cylindre droit
F15B 15/22 - Autres parties constitutives pour accélérer ou ralentir le mouvement
A method of developing a flex spline and circular gear tooth profile for a harmonic actuator is provided. The method includes defining circular gear and flex spline centroids based on gear ratio calculations, finding mid-points between the centroids of the circular gear and the centroids of the flex spline and transforming the mid-points into a mapping of the tooth profile for respective teeth of the circular gear and the flex spline.
B64C 13/34 - Dispositifs de transmission sans amplification de puissance ou dans les cas où l'amplification de puissance est sans objet mécaniques utilisant des engrenages
F16H 23/00 - Transmissions à plateaux oscillants; Transmissions à manivelles obliques
F16H 25/04 - Transmissions comportant essentiellement et uniquement des systèmes came et galet ou des mécanismes à vis et écrous pour transmettre un mouvement rotatif
A linear actuator (2) comprises an actuator housing (4) defining a bore (28). A drive element (8) is received in the actuator housing bore (28). The drive element (8) comprises tubular portions (42) receiving first and second ball nuts (12) arranged at respective distal ends (60) thereof. The ball nuts (12) are threaded in opposite directions to one another. The drive element (8) further comprises a drive coupling (44). The actuator (2) further comprises first and second ball screws (14) operatively engaged with the first and second ball nuts (12). Rotation of the drive element (8) and thus the ball nuts (12) relative to said ball screws (14) causes the ball screws (14) to move together in a linear path in opposite directions from one another.
F16H 25/22 - Mécanismes à vis avec billes, rouleaux ou organes similaires entre pièces travaillant en conjugaison; Eléments essentiels pour l'utilisation de ces organes
An electromechanical rotary actuator includes a drive member, a motor disposed inside and directly coupled to the drive member, and an output arm. The motor has a rotor configured toward an outside of the motor and directly coupled to an input of the drive member and a stator configured toward an inside of the motor and positioned inside the rotor. The output arm is disposed about the motor and is drivably connected to the drive member. The output arm defines an arcuate opening.
F16H 1/04 - Transmissions à engrenages pour transmettre un mouvement rotatif sans engrenages à mouvement orbital comportant uniquement deux organes engrenés
B64C 13/34 - Dispositifs de transmission sans amplification de puissance ou dans les cas où l'amplification de puissance est sans objet mécaniques utilisant des engrenages
B64C 13/50 - Dispositifs de transmission avec amplification de puissance utilisant l'énergie électrique
F16H 1/10 - Transmissions à engrenages pour transmettre un mouvement rotatif sans engrenages à mouvement orbital comportant uniquement deux organes engrenés dont les axes sont parallèles un des organes étant denté intérieurement
F16H 37/12 - Transmissions comportant principalement une transmission à engrenages ou à friction, des maillons ou des leviers, des cames, ou bien des organes appartenant à deux des trois types ci-dessus au moins
H02K 7/14 - Association structurelle à des charges mécaniques, p.ex. à des machines-outils portatives ou des ventilateurs
A method for braking a motor in a high lift system of an aircraft, the high lift system comprising a central power drive unit for moving high lift surfaces arranged at a wing through providing rotational power by means of a transmission shaft to a plurality of drive stations operably coupled with the high lift surfaces; which power drive unit is operatively coupled to a controller and comprises at least one electric motor coupled therewith. The method includes determining a braking requirement for the at least one electric motor, measuring at least one of a current command to the motor and a current speed and direction of the at least one electric motor, based on the braking requirement, applying a braking command to the at least one electric motor, and reducing the braking command as the at least one electric motor comes to rest.
An inverted harmonic gear actuator is provided and includes a motor stator and a motor rotor radially disposed within the motor stator. The inverted harmonic gear actuator also includes a wave generator radially disposed within the motor rotor, where the wave generator has a radially inner surface with a cammed shape. An actuator output shaft is radially disposed within the wave generator. A flex spline is radially interposable between the radially inner surface of the wave generator and the actuator output shaft. The flex spline is deformable to conform to the radially inner surface of the wave generator and drive rotation of the actuator output shaft slower than rotation of the motor rotor.
B64C 13/34 - Dispositifs de transmission sans amplification de puissance ou dans les cas où l'amplification de puissance est sans objet mécaniques utilisant des engrenages
F16H 1/02 - Transmissions à engrenages pour transmettre un mouvement rotatif sans engrenages à mouvement orbital
H02K 7/116 - Association structurelle avec des embrayages, des freins, des engrenages, des poulies ou des démarreurs mécaniques avec des engrenages
A predictive system is provided and includes a torque-limiter, a sensor disposed to sense a condition of the torque-limiter and a processing system. The processing system is coupled to the sensor and configured to process readings of the sensor, to calculate whether the condition of the torque-limiter is indicative of degradation or failure incidents based on the readings being processed and to determine whether an action should be taken based on a calculation result.
F16D 7/06 - Accouplements à glissement, p.ex. glissant en cas de surcharge, pour absorber les chocs du type à rochet avec billes ou rouleaux intermédiaires
G01M 13/022 - Accouplements ou embrayages de transmission de puissance
B64C 13/28 - Dispositifs de transmission sans amplification de puissance ou dans les cas où l'amplification de puissance est sans objet mécaniques
A solenoid electrical diagnostic system includes a solenoid circuit operable in response to an electrical current. A low-side switch includes a low-side input configured to receive a pulsed voltage signal and a low-side output in signal communication with the solenoid circuit. The low-side switch continuously switches between an on-state and an off-state based on the pulsed voltage signal to adjust a level of the current flowing through the solenoid circuit. A solenoid monitoring unit generates a low-side output state signal based on an output voltage at the low- side output, and a low-side input state signal based on an input voltage at the low- side input. The solenoid electrical diagnostic system further includes an electronic hardware controller determines at least one operating condition of the solenoid circuit based on a comparison between the state signals and a threshold value.
F15B 19/00 - Test des systèmes ou appareils de manœuvre utilisant la pression d'un fluide, dans la mesure où ils ne sont pas prévus ailleurs
F15B 20/00 - Dispositions propres à la sécurité pour systèmes de manœuvre utilisant les fluides; Utilisation des dispositifs de sécurité dans les systèmes de manœuvre utilisant des fluides; Mesures d'urgence pour les systèmes de manœuvre utilisant des fluides
A fast shut-off solenoid circuit network includes a solenoid circuit and a current dissipation circuit. The solenoid circuit is operable in response to an electrical current, and configured to operate in an enable mode and a disable mode. The current dissipation circuit is configured to dissipate the current discharged from the solenoid circuit in response to invoking the disable mode. The fast shut-off solenoid circuit network further includes a dissipation bypass circuit. The dissipation bypass circuit is configured to divert the current discharged by the solenoid circuit away from current dissipation circuit when operating in the enable mode.
H01F 7/18 - Circuits en vue d'obtenir des caractéristiques de fonctionnement souhaitées, p.ex. pour un fonctionnement lent, pour l'excitation successive des enroulements, pour l'excitation à grande vitesse des enroulements
A new type of coupling assembly for rotatably coupling two shafts is described. A new type of method for rotatably coupling two shafts is also described. The coupling assembly comprises a first shaft extending longitudinally between a first end and a second end and having a radially extending flange at said second end; a second shaft extending longitudinally between a first end and a second end and having a radially extending hollow receiving member at said first end, the flange being positioned within the hollow receiving member; and wherein said hollow receiving member comprises an inner cylindrical surface comprising at least one longitudinally extending member groove ; and wherein said flange comprises an outer cylindrical surface comprising at least one longitudinally extending flange groove; said coupling assembly further comprising a barrel-shaped roller bearing provided to extend longitudinally within and in contact with both said flange groove and said receiving member groove and further wherein said flange groove and/cr said member groove has a longitudinal concave barrel shape for receiving and contacting said barrel shaped roller bearing.
A ram air turbine (RAT) is provided and includes a turbine assembly including blades and a hub to which the blades are connected, a generator or a pump and a drivetrain mechanically interposed between the turbine assembly and the generator or the pump. Each blade includes an exterior, airfoil-shaped structure defining an interior and support structures disposed within the interior which connect with an inner surface of the exterior, airfoil-shaped structure and which define hollow regions within the interior.
A torque limiting assembly is disclosed comprising: an input shaft 4; an output shaft 6; a drive bush 10; a motion converter mechanism 25; a casing 48; and at least one engagement member 46 for engaging the casing 48. In a low torque mode, rotation of the input shaft 4 drives rotation of the drive bush 10, motion converter mechanism 25 and output shaft 6. In a high torque mode, rotation of the motion converter mechanism 25 relative to the output shaft 6 urges the motion converter mechanism 25 axially to drive rotation of the drive bush 10 relative to the input shaft 4. The engagement member 46 is coupled to both the drive bush 10 and the input shaft 4 such that when the drive bush 10 is rotated relative to the input shaft 4, the engagement member 46 is urged to engage the casing 48 so as to prevent or inhibit rotation of the input shaft 4 relative to the casing 48.
F16D 43/20 - Embrayages automatiques à commande interne actionnés entièrement mécaniquement commandés par le couple, p.ex. embrayages à déclenchement en cas de surcharge, embrayages à glissement avec dispositifs par lesquels le couple fait varier la pression d'embrayage
F16D 7/00 - Accouplements à glissement, p.ex. glissant en cas de surcharge, pour absorber les chocs
84.
METHOD TO MEASURE AIRCRAFT HIGH-LIFT SYSTEM BRAKE RESPONSE TIME
A braking test for a high lift system. The system including a plurality of high lift surfaces movably arranged at a wing, a plurality of drive stations coupled with the high lift surfaces via a transmission shaft, a power drive unit coupled with the transmission shaft including an electric motor operably coupled with a brake, and a control unit operably coupled to the power drive unit. The control unit executing a method for testing the brake, including actuating an electric motor, acquiring a sensor output of a sensor coupled during the actuating of the motor and determining a motion of the motor, activating a selected brake under test, measuring an elapsed time until the brake has arrested the motion, and determining if the elapsed time is less than a threshold. Generating a brake failure signal for the selected brake if the elapsed time exceeds the threshold.
An aircraft is provided. The aircraft includes a pressurized volume and an air conditioning system. The air conditioning system operates in a first mode when the aircraft is performing high altitude operations and a second mode when the aircraft is performing low altitude operations. The first mode includes when a first medium, a second medium, and a third medium are mixed by the air conditioning system to produce a chamber ready medium. The second mode comprises when only the first medium and the second medium are mixed by the air conditioning system to produce the chamber ready medium. The air conditioning system provides the chamber ready medium to the pressurized volume.
B64D 13/00 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret
F24F 5/00 - Systèmes ou appareils de conditionnement d'air non couverts par ou
86.
AIRCRAFT SLAT AND FLAP CONTROL WITH RADIO FREQUENCY IDENTIFICATION TAGS
Disclosed is a system for monitoring wing control on an aircraft that includes a plurality of radio frequency identification device (RFID) tags attachable to a movable wing portion. The system includes a RFID reader attachable to a stationary wing portion and configured to communicate with at least two RFID tags, and a controller. The controller includes a processor connected to the RFID reader. The processor transmits at least two carrier signals via the RFID reader to the at least two RFID tags. Each of the transmitted carrier signals have a different carrier frequency. The processor also receives at least two reflected signals from the at least two RFID tags. The processor determines, based on the reflected signal from the at least two RFID tags, at least one of a motion of the movable wing portion and a distance of the movable wing portion.
B64C 13/00 - Systèmes de commande ou systèmes de transmission pour actionner les gouvernes, les volets hypersustentateurs, les aérofreins ou les destructeurs de portance (spoilers)
G01S 13/74 - Systèmes utilisant la reradiation d'ondes radio, p.ex. du type radar secondaire; Systèmes analogues
87.
ADVANCED ENVIRONMENTAL CONTROL SYSTEM IN AN INTEGRATED SPLIT PACK ARRANGEMENT WITH TWO BLEED/OUTFLOW HEAT EXCHANGERS
An environmental control system for providing conditioned air to a volume of an aircraft includes a ram air circuit including a ram air shell with at least one heat exchanger positioned therein. A dehumidification system is arranged in fluid communication with the ram air circuit and at least one compressing device is arranged in fluid communication with the ram air circuit and the dehumidification system. A plurality of mediums is receivable within the environmental control system. A first medium of the plurality of mediums is provided from the volume of the aircraft via at least one valve.
B64D 13/06 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret l'air étant climatisé
B64D 13/00 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret
88.
ADVANCED ENVIRONMENTAL CONTROL SYSTEM IN AN INTEGRATED PACK ARRANGEMENT WITH ONE BLEED/OUTFLOW HEAT EXCHANGER
An environmental control system of an aircraft includes a ram air circuit having a ram air shell with at least one heat exchanger positioned therein. A dehumidification system is arranged ill fluid communication with the ram air circuit and a plurality of compressing devices is arranged in fluid communication with the ram air circuit and the dehumidification system.
B64D 13/06 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret l'air étant climatisé
B64D 13/00 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret
89.
ADVANCED ENVIRONMENTAL CONTROL SYSTEM IN AN INTEGRATED SPLIT PACK ARRANGEMENT WITH ONE BLEED/OUTFLOW HEAT EXCHANGER
An environmental control system of an aircraft includes a ram air circuit including a ram air shell having at least one heat exchanger positioned therein. A dehumidification system is arranged in fluid communication with the ram air circuit and at least one compressing device is arranged in fluid communication with the ram air circuit and the dehumidification system. The at least one compressing device includes a turbine and a compressor operably coupled via a shaft. A fan is operably coupled to the ram air circuit. At least one compressing device is arranged non-linearly with the ram air circuit such that an axis of rotation of the fan is offset from the axis of the shaft.
B64D 13/06 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret l'air étant climatisé
B64D 13/00 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret
A heating arrangement has a positive temperature coefficient ("PTC") heater. A resistor is electrically in series with the PTC heater sized and configured to limit current through the PTC heater and the resistor below a selected value.
A heater electrical short protection arrangement has a heating layer that is at least partially electrically conductive. A conductive layer is initially electrically insulated from the heating layer. A circuit in electrical communication with the conductive layer is configured to halt a supply of electrical energy to the heating layer in response to current flowing into the conductive layer.
H05B 1/02 - Dispositions de commutation automatique spécialement adaptées aux appareils de chauffage
B64D 11/00 - Arrangements pour passagers ou équipage; Installations de postes de pilotage non prévues ailleurs
B64D 13/08 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret l'air étant climatisé l'air étant réchauffé ou refroidi
A detent alignment mechanism assembly is provided and includes a shaft, a lock mechanism configured to selectively occupy an unlocked position at which the shaft is movable and a locked position at which the shaft is immovable, a detent mechanism coupled to the shaft and formed to define detent positions for the shaft to assume and move between and a detent alignment mechanism configured to provide to an operator of the shaft feedback and assistance corresponding to assumptions of the detent positions by the shaft during movements thereof by the operator.
G05G 5/06 - Moyens pour interdire, limiter ou inverser le mouvement de certaines pièces d'un mécanisme de commande, p.ex. verrouillage des organes de commande pour maintenir les organes de commande, seulement sur une ou sur un nombre limité de positions définies
B64C 13/14 - Dispositifs amorçant la mise en œuvre actionnés par l'homme blocables
F16D 71/04 - Mécanismes pour amener les organes rotatifs dans une position prédéterminée de repos permettant le choix entre plusieurs positions
G05G 5/03 - Moyens pour attirer l'attention de l'opérateur sur l'arrivée de l'organe de commande dans une position de commande ou de repère; Création d'une sensation, p.ex. moyens pour générer une force antagoniste
A sensor for detecting relative movement between two adjacent components includes a first member, a second member rotatable about an axis relative to the first member, and a fuse element including a first electrical contactor connected to the first member and a second electrical contactor connected to the second member. When the first member and the second member are skewed, the first electrical contactor and the second electrical contactor are not in electrical contact.
G01B 7/31 - Dispositions pour la mesure caractérisées par l'utilisation de techniques électriques ou magnétiques pour tester l'alignement des axes pour tester l'alignement des axes
An airplane is provided. The airplane includes a first medium at a first pressure, a second medium at a second pressure, a third medium at a third pressure; and an air conditioning system. The air conditioning system includes a compressor, a first heat exchanger configured to transfer heat from the first medium to the third medium, a second heat exchanger configured to reject heat from the first medium, a third heat exchanger configured to reject heat from the second medium, a first turbine configured to receive the first medium, and a second turbine configured to receive the second medium.
B64D 13/00 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret
F24F 5/00 - Systèmes ou appareils de conditionnement d'air non couverts par ou
F25B 11/00 - Machines, installations ou systèmes à compression utilisant des turbines, p.ex. des turbines à gaz
95.
AN ENVIRONMENTAL CONTROL SYSTEM WITH AN OUTFLOW HEAT EXCHANGER
An airplane is provided. The airplane includes a pressurized volume and an air conditioning system. The pressurized volume provides a first medium. The air conditioning system includes a heat exchanger and a compressor. The heat exchanger transfers heat from a second medium to the first medium. The compressor receives the second medium. The compressor is upstream of the heat exchanger in a flow path of the second medium.
B64D 13/00 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret
F24F 5/00 - Systèmes ou appareils de conditionnement d'air non couverts par ou
F25B 11/00 - Machines, installations ou systèmes à compression utilisant des turbines, p.ex. des turbines à gaz
96.
AN ENERGY FLOW OF AN ADVANCED ENVIRONMENTAL CONTROL SYSTEM
An airplane is provided. The airplane includes a compressing device. The compressing device includes a turbine with a first inlet and a second inlet. The turbine provides energy by expanding mediums. The first inlet is configured to receive a first medium of the mediums. The second inlet is configured to receive a second medium of the mediums. The compressing device includes a compressor and a motor. The compressor receives a first energy derived from the first and second mediums being expanded across the turbine during a first mode of the compressing device, receives a second energy derived from the first medium being expanded across the turbine during a second mode of the compressing device, and compresses the second medium in accordance with the first mode or the second mode. The motor provides a supplementary energy to the compressor.
F25B 11/00 - Machines, installations ou systèmes à compression utilisant des turbines, p.ex. des turbines à gaz
B64D 13/00 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret
F24F 5/00 - Systèmes ou appareils de conditionnement d'air non couverts par ou
97.
MULTIPLE NOZZLE CONFIGURATIONS FOR A TURBINE OF AN ENVIRONMENTAL CONTROL SYSTEM
An airplane is provided. The airplane includes a pressurized medium, a turbine, and a valve. The turbine includes at least one nozzle. The valve is located upstream of the turbine. The valve provides the pressurized medium to the at least one nozzle of the turbine according to an operational mode.
B64D 13/00 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret
F24F 5/00 - Systèmes ou appareils de conditionnement d'air non couverts par ou
F25B 11/00 - Machines, installations ou systèmes à compression utilisant des turbines, p.ex. des turbines à gaz
98.
MIXING RAM AND BLEED AIR IN A DUAL ENTRY TURBINE SYSTEM
A system is provided. The system includes a first medium at a first pressure, a second medium at a second pressure, and a medium conditioning sub-system. The medium conditioning sub-system includes a compressor, a first heat exchanger, a second heat exchanger, and a turbine. The turbine receives the first medium and the second medium.
F24F 5/00 - Systèmes ou appareils de conditionnement d'air non couverts par ou
B64D 13/00 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret
99.
AN ENERGY FLOW OF AN ADVANCED ENVIRONMENTAL CONTROL SYSTEM
An airplane is provided. The airplane includes a compressing device including a turbine and a compressor. The turbine includes first and second inlets and provides energy by expanding one or more mediums. The first inlet is receives a first medium of the one or more mediums. The second inlet receives a second medium of the one or more mediums. The compressor receives a first energy derived from the first and second mediums being expanded across the turbine during a first mode of the compressing device, receives a second energy derived from the first medium being expanded across the turbine during a second mode of the compressing device, and compresses the second medium in accordance with the first mode or the second mode.
B64D 13/00 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret
F02C 6/08 - Ensembles fonctionnels de turbines à gaz délivrant un fluide de travail chauffé ou pressurisé à d'autres appareils, p.ex. sans sortie de puissance mécanique délivrant des gaz comprimés le gaz étant prélevés sur le compresseur de la turbine à gaz
F24F 5/00 - Systèmes ou appareils de conditionnement d'air non couverts par ou
F25B 11/00 - Machines, installations ou systèmes à compression utilisant des turbines, p.ex. des turbines à gaz
An airplane is provided. The airplane includes a first medium, a second medium, and an air conditioning. The air conditioning system includes a first turbine, a compressor, and a mixing point. The compressor is located upstream of the turbine in a flow path of the first medium. The mixing point is a location at which the first medium mixes with the second medium. The mixing point is downstream of the compressor and upstream of the turbine.
B64D 13/00 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret
F24F 5/00 - Systèmes ou appareils de conditionnement d'air non couverts par ou
F25B 11/00 - Machines, installations ou systèmes à compression utilisant des turbines, p.ex. des turbines à gaz
brevets
