Methods and systems for generating a recovery scheduling solution in response to a scheduling disruption are disclosed. A method includes receiving a request to modify an original schedule operations solution based on disruptive events, computing a flight recovery solution to reschedule disrupted flights, generating a crew recovery solution using the flight recovery solution that includes covered and uncovered flights by assigning flight crews to rescheduled disrupted flights, iteratively generating recommendations to delay or cancel uncovered flights until a best recovery solution is obtained, the best recovery solution including a crew recovery solution with a least amount of uncovered flights, iteratively generating, by the processing device, subsequent flight and crew recovery solutions based on the recommendations, generating a passenger recovery solution based on the best recovery solution and re-assigning disrupted passengers to the rescheduled disrupted flights, and configuring the airline recovery scheduling solution.
G06Q 10/06 - Ressources, gestion de tâches, des ressources humaines ou de projets; Planification d’entreprise ou d’organisation; Modélisation d’entreprise ou d’organisation
Systems and methods of generating a recovery scheduling solution in response to a scheduling disruption are disclosed. A method includes receiving a request to modify an original schedule operations solution based on disruptive events associated with flights, wherein the disruptive events causes the disruption, computing a flight recovery solution based on rescheduling flights with a minimum number of breaks in original crew-pairings and a minimum number of breaks in original passenger connections for connecting flights in order to reschedule disrupted flights, generating a crew recovery solution using the flight recovery solution by assigning flight crews to rescheduled disrupted flights, generating a passenger recovery solution based on the crew recovery solution and reassigning disrupted passengers to the rescheduled disrupted flights, and configuring the airline recovery scheduling solution using flight, crew, and passenger recovery solutions in order to transmit the recovery scheduling solution to an operations control center.
G06Q 10/02 - Réservations, p.ex. pour billetterie, services ou manifestations
G06Q 10/04 - Prévision ou optimisation spécialement adaptées à des fins administratives ou de gestion, p. ex. programmation linéaire ou "problème d’optimisation des stocks"
3.
SYSTEMS AND METHODS FOR PROVIDING AN UNMANNED & MANNED AIR TRAFFIC MANAGEMENT MASTER SERVICES ARCHITECTURE
Systems and methods provide a services architecture. An air mobility platform locally stores a native application at. The air mobility platform receives a first request for a first service and data identifying the first user as a priority user type or a non-priority user type. A second request for a second service and data related to the second user identifies the user type is received. The air mobility platform calculates a priority for the first request. If the priority for the first request exceeds the priority for the second request, a third party application is accessed for the first request. The air mobility platform submits the data related to the first request from the third party application to at least one of the first unmanned aerial vehicle or the first user.
Systems and methods for trajectory planning for an unmanned aerial vehicle. A mission specification for fulfillment by an unmanned aerial vehicle is received. The mission specification identifies a waypoint, an optimization criterion, and information identifying the unmanned aerial vehicle. It is determined whether candidate flight trajectories are available. Maneuvers from a motions library that defines available maneuvers are modeled to identify candidate flight trajectories to the waypoint which satisfy a restriction condition and do not conflict with a flight plan for another aerial vehicle. If candidate flight trajectories are available, desired flight trajectories are selected. A mission approval is submitted to a receiving party.
Systems and methods for providing surveillance services for an unmanned vehicle are described herein. One embodiment of a method includes receiving surveilled data from a surveillance monitor regarding the unmanned aerial vehicle and at least one other aircraft, receiving trajectory data from at least one trajectory data source, and comparing the surveilled data with the trajectory data to determine whether the unmanned aerial vehicle is on path to collide with a third party aerial vehicle. In some embodiments, in response to determining that the unmanned aerial vehicle is on path to collide with the third party aerial vehicle, the method includes determining an alternate route for the unmanned aerial vehicle; and communicating at least a portion of the alternate route to the unmanned aerial vehicle.
Systems and methods for providing an aviation approval services platform. One embodiment of a method includes receiving customer data. The customer data may include data related to an operator, data related to a vehicle, and/or data related to an intended operation of the vehicle by the operator. The method may include determining compliance requirements of a regulatory authority for approving an approval application for the operator and/or the vehicle for the intended operation, determining whether the customer data is sufficient to meet the compliance requirements of the regulatory authority for the intended operation, and in response to determining that the customer data is not sufficient to meet the compliance requirements, providing a recommendation for meeting the compliance requirements. In some embodiments, in response to determining that the customer data is sufficient to meet the compliance requirements, submitting an application to the regulatory authority on behalf of the operator.
Methods, apparatus, systems and articles of manufacture are disclosed for distributed, multi-node, low frequency radar systems for degraded visual environments. An example system includes a transmitter to transmit a radar signal. The example system includes a distributed network of radar receivers to receive the radar signal at each receiver. The example system includes a processor to determine a first range and a first angular position of a background point based on return time, wherein the first range and the first angular position are included in first data; determine a second range and a second angular position of the background point based on doppler shift, wherein the second range and the second angular position are included in second data; determine a refined range and a refined angular position, wherein the refined range and refined angular position are included in third data, and generate a radar map based on third data.
Generation of scripts that facilitate execution of tasks within different run-time environments that utilize different languages and syntax is provided herein. A system comprises a memory that stores executable components and a processor, operatively coupled to the memory, that executes the executable components. The executable components comprise an identification manager component that identifies one or more elements of input data. The input data can comprise test data that comprises respective identifications of an input variable, an output variable, a test vector comprising an initial value of a test input, and an expected output variable against which test results are compared. The executable components can also comprise a template tool component that generates output data that facilitates execution of tasks within different run-time environments that utilize different languages and syntax.
A method and decoupler for disengaging an output shaft from an engine in a back drive event with a backdrive decoupler. The backdrive decoupler includes an output shaft, drive shaft wherein the output shaft is selectively coupled to the drive shaft. Permanent magnets are used to transmit torque from the drive shaft to the output shaft. In a backdrive event, the decoupler decouples the output shaft from the drive shaft by uncoupling the torque transfer.
F02C 7/275 - Entraînement du rotor pour le démarrage mécanique
F01D 19/00 - Démarrage des "machines" ou machines motrices; Dispositifs de régulation, de commande ou de sécurité en rapport avec les organes de démarrage
Systems and methods for reducing switching losses in an electrical system in an aircraft are provided. In one example implementation, a method can include receiving DC power at an inverter of an electrical power system of an aircraft. The inverter can be a multiphase inverter having at least one bridge circuit for each output phase of the inverter. Each bridge circuit can include a plurality of switching elements. The method can include generating, by one or more control devices, a plurality of duty cycle commands for operation of the plurality of switching elements for each bridge circuit. The method can include operating, by the one or more control devices, the inverter in accordance with the plurality of duty cycle commands to generate a multiphase AC power output from the inverter. The plurality of duty cycle commands can be generated at least in part using a space vector modulation process.
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
H02M 7/5395 - 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 avec commande automatique de la forme d'onde ou de la fréquence de sortie par modulation de largeur d'impulsions
B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
Provided is an annular matching device indulging a spherical bearing including an inner surface, and an exterior surface movably attached to the inner surface, the inner and exterior surfaces including a bore. Also included is a fastener configured to extend through a first workpiece and through the bore. The spherical bearing is configured to be placed in a second workpiece; and the second workpiece is configured to be moved adjacent to the first workpiece via an engager.
A method and apparatus for a gas turbine engine including a core engine a nacelle surrounding at least a portion of the core engine and defining an interior with an opening. An access door for the opening to provide selective access to the opening where the access door provides pressure relief for the interior.
F02C 7/045 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs destinés à supprimer le bruit
F02C 7/28 - Agencement des dispositifs d'étanchéité
A propeller blade (18) spanning radially from a root (32) to a tip (34) and spanning axially from a leading edge (36) to a trailing edge (38) spaced from the leading edge forming an airfoil (39) therebetween where a sweep line (62) can be defined as a spline fitted through points which are positioned along the chord line. The propeller blade having at least one spline (40, 42) defining the leading edge or trailing edge.
An apparatus and method for deicing a surface (66) upon which ice accumulates, on for example an aircraft wing. The apparatus and method for the deicing module include an actuating component, a casing (28), and a movable member (36). The movable member breaks ice that has accumulated on a surface of the wing.
B64D 15/16 - Dégivrage ou antigivre des surfaces externes des aéronefs par dispositifs mécaniques, p.ex. des gaines ou des bourrelets fixés ou incorporés à la surface et soumis à des pulsations
15.
ADVANCED METHOD AND AIRCRAFT FOR PRE-COOLING AN ENVIRONMENTAL CONTROL SYSTEM USING A THREE WHEEL TURBO-MACHINE
A method and aircraft for providing bleed air to environmental control systems of an aircraft using a gas turbine engine, including determining a bleed air demand for the environmental control systems, selectively supplying low pressure and high pressure bleed air to the environmental control systems, wherein the selectively supplying is controlled such that the conditioned air stream satisfies the determined bleed air demand.
F02C 3/13 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur ayant des raccordements variables du fluide de travail entre des turbines ou des compresseurs ou entre des étages de différents rotors
F02C 6/04 - 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
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
F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
F02C 9/18 - Commande du débit du fluide de travail par prélèvement, par bipasse ou par action sur des raccordements variables du fluide de travail entre des turbines ou des compresseurs ou entre leurs étages
B64D 13/02 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret l'air étant pressurisé
F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p.ex. l'air
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
16.
ENHANCED METHOD AND AIRCRAFT FOR PRE-COOLING AN ENVIRONMENTAL CONTROL SYSTEM USING A TWO WHEEL TURBO-MACHINE WITH SUPPLEMENTAL HEAT EXCHANGER
A method and aircraft for providing bleed air to environmental control systems of an aircraft using a gas turbine engine, including determining a bleed air demand for the environmental control systems, selectively supplying low pressure and high pressure bleed air to the environmental control systems, wherein the selectively supplying is controlled such that the conditioned air stream satisfies the determined bleed air demand.
F02C 3/13 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur ayant des raccordements variables du fluide de travail entre des turbines ou des compresseurs ou entre des étages de différents rotors
F02C 6/04 - 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
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
F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
F02C 9/18 - Commande du débit du fluide de travail par prélèvement, par bipasse ou par action sur des raccordements variables du fluide de travail entre des turbines ou des compresseurs ou entre leurs étages
B64D 13/02 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret l'air étant pressurisé
F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p.ex. l'air
B60K 17/10 - Agencement ou montage des transmissions sur les véhicules caractérisées par la disposition, l'emplacement ou le type de mécanisme de transmission à fluide
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
A damping system can include a sensor disposed to measure an amplitude of a speed ripple of a drive shaft of a generator, and can include a feed forward circuit connected to the sensor and to the generator. The feed forward circuit can determine a phase angle formed by a load resistance and a load capacitance driven by the generator, calculate a voltage signal value based on the amplitude and the phase angle, and can adjust a DC link voltage provided by the generator and across the load resistance according to the voltage signal value.
H02P 23/04 - Dispositions ou procédés pour la commande de moteurs à courant alternatif caractérisés par un procédé de commande autre que la commande par vecteur spécialement adaptés pour amortir les oscillations des moteurs, p.ex. pour la réduction du pompage
18.
ADVANCED METHOD AND AIRCRAFT FOR PRE-COOLING AN ENVIRONMENTAL CONTROL SYSTEM USING A DUAL COMPRESSOR FOUR WHEEL TURBO-MACHINE
A method and aircraft for providing bleed air to environmental control systems of an aircraft using a gas turbine engine, including determining a bleed air demand for the environmental control systems, selectively supplying low pressure and high pressure bleed air to the environmental control systems, wherein the selectively supplying is controlled such that the conditioned air stream satisfies the determined bleed air demand.
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
There is provided a valve assembly that includes a retaining ring disposed within a cavity formed by adjoining a retainer and a disk member. The retaining ring can be disposed at a slant with respect to an inner surface of the cavity.
A method and modular system for assembling a power system architecture includes a direct current (DC) output module having a first DC input and a DC output, a common power module having a DC input/output and an alternating current (AC) input/output, an AC output module having an AC input and a first AC output, and an exciter power module having a second DC input and a second AC output.
H02J 5/00 - Circuits pour le transfert d'énergie électrique entre réseaux à courant alternatif et réseaux à courant continu
H02M 7/219 - Transformation d'une puissance d'entrée en courant alternatif en une puissance de sortie en courant continu 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 dans une configuration en pont
H02M 1/00 - APPAREILS POUR LA TRANSFORMATION DE COURANT ALTERNATIF EN COURANT ALTERNATIF, DE COURANT ALTERNATIF EN COURANT CONTINU OU VICE VERSA OU DE COURANT CONTINU EN COURANT CONTINU ET EMPLOYÉS AVEC LES RÉSEAUX DE DISTRIBUTION D'ÉNERGIE OU DES SYSTÈMES D'ALI; TRANSFORMATION D'UNE PUISSANCE D'ENTRÉE EN COURANT CONTINU OU COURANT ALTERNATIF EN UNE PUISSANCE DE SORTIE DE CHOC; LEUR COMMANDE OU RÉGULATION - Détails d'appareils pour transformation
Provided is a valve assembly system including a flowbody including a channel formed at an inner surface thereof, a butterfly plate disposed within the channel and rotatably mounted within the flowbody. The system also includes a pair of dual-sided pistons that receive differential pressure at an input side and an output side of the valve assembly system. A spring is controlled for biasing against at least one of the dual-sided pistons based on the differential pressure, and to rotate the butterfly plate to regulate the differential pressure and the valve assembly system to a predetermined output pressure.
One example aspect of the present disclosure is directed to a method for measuring engine performance. The method includes receiving first parameters related to engine performance prior to an engine wash event. The method includes receiving second parameters related to engine performance after the engine wash event. The method includes determining an engine performance prior to the engine wash event based on the first parameters. The method includes determining an engine performance after the engine wash event based on the second parameters. The method includes determining an effectiveness of the engine wash event based on the engine performance prior to the engine wash event and the engine performance after the engine wash event.
G06Q 10/06 - Ressources, gestion de tâches, des ressources humaines ou de projets; Planification d’entreprise ou d’organisation; Modélisation d’entreprise ou d’organisation
One example aspect of the present disclosure is directed to a method for measuring engine performance. The method includes receiving a plurality of parameters related to engine performance. The method includes receiving an indication of an engine wash event. The method includes determining an effectiveness of the engine wash event based on the plurality of parameters. The method includes performing a comparison of the effectiveness of the engine wash event with an expected effectiveness of the engine wash event. The method includes performing a control action based on the comparison.
G06Q 10/06 - Ressources, gestion de tâches, des ressources humaines ou de projets; Planification d’entreprise ou d’organisation; Modélisation d’entreprise ou d’organisation
24.
DETERMINING A PASSENGER SERVICE PARAMETER FOR FLIGHT DISRUPTION
Systems and methods for determining a passenger service parameter for flight disruption are provided. A method can include receiving, by one or more processors, data indicative of user selection of flight disruption criteria. The method can further include determining, by the one or more processors, at least one impacted passenger based at least upon the data indicative of the user selection. The method can further include determining, by the one or more processors, an alternate flight accommodation for the at least one impacted passenger. The method can further include determining, by the one or more processors, a flight delay for the at least one impacted passenger based at least upon the alternate flight accommodation. The method can further include determining, by the one or more processors, a passenger service parameter associated the at least one impacted passenger based at least upon the flight delay.
G06Q 10/06 - Ressources, gestion de tâches, des ressources humaines ou de projets; Planification d’entreprise ou d’organisation; Modélisation d’entreprise ou d’organisation
A method and decoupler for disengaging an output shaft from an engine in a back drive event with a backdrive decoupler. The backdrive decoupler includes a threaded shaft and a retention mechanism selectively coupling the output shaft to the threaded shaft. In a backdrive event, the decoupler decouples the output shaft from a drive shaft.
F02C 7/277 - Entraînement du rotor pour le démarrage mécanique par une turbine
F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
F16D 9/06 - Accouplements avec organe de sécurité pour le désaccouplement par rupture due au cisaillement
F16D 11/04 - Embrayages dans lesquels les organes ont des parties qui se pénètrent mutuellement désembrayés par le contact avec un organe fixe d'une pièce montée sur l'embrayage avec organes d'embrayage mobiles selon l'axe uniquement
F16D 41/22 - Roues libres ou embrayages à roue libre avec anneau ou disque d'embrayage déplacés selon l'axe, du fait du mouvement perdu entre les organes de mise en œuvre
A method and decoupler for disengaging an output shaft from an engine in a back drive event with a backdrive decoupler. The backdrive decoupler includes an output shaft, drive shaft, and a retention mechanism selectively coupling the output shaft to the drive shaft. In a backdrive event, the decoupler decouples the output shaft from the drive shaft.
F02C 7/268 - Entraînement du rotor pour le démarrage
F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
F02C 7/275 - Entraînement du rotor pour le démarrage mécanique
F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
Systems and methods for distributing electrical power in an aircraft are provided. More particularly, in one embodiment, a system (100) can include one or more gas turbine engines (104) configured to provide propulsion and electrical power to an aircraft (102). The system can further include one or more electrical engines (108) configured to provide propulsion for the aircraft. The system can include one or more first electrical power systems (122) configured to provide power to the one or more electrical engines for one or more electrical power propulsion loads for the aircraft. The system can further include one or more second electrical power systems (124) configured to provide power for one or more non-propulsion electrical power loads of the aircraft.
A solid hydrogen reaction system and method of liberating hydrogen gas includes the utilization of a reactor having a body that defines a reaction chamber, having a first narrow end and a second wider end such that the reactor has an increasing cross-sectional area from the first end toward the second end, for facilitating a reaction to liberate hydrogen gas stored in a hydrogen storage solid located within the reaction chamber.
C01B 3/06 - Production d'hydrogène ou de mélanges gazeux contenant de l'hydrogène par réaction de composés inorganiques comportant un hydrogène lié électropositivement, p.ex. de l'eau, des acides, des bases, de l'ammoniac, avec des agents réducteurs inorganiques
B01J 7/02 - Appareillage pour la production de gaz par voie humide
C01B 3/00 - Hydrogène; Mélanges gazeux contenant de l'hydrogène; Séparation de l'hydrogène à partir de mélanges en contenant; Purification de l'hydrogène
A system and method for manufacturing a part in a mold having a mold cavity including a printhead for depositing a first material within the mold cavity, and an injection head for depositing a second material within the mold cavity. A part can be made in the mold cavity by the cooperative use of both injection molding and additive manufacturing steps.
B29C 45/00 - Moulage par injection, c. à d. en forçant un volume déterminé de matière à mouler par une buse d'injection dans un moule fermé; Appareils à cet effet
B29C 70/48 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.à d. d'objets distincts utilisant des moules opposables, p.ex. pour déformer des préimprégnés [SMC] ou des "prepregs" avec une imprégnation des renforcements dans le moule fermé, p.ex. moulage par transfert de résine [RTM]
B29C 67/00 - Techniques de façonnage non couvertes par les groupes , ou
B29C 45/33 - Moules comportant des éléments de moule transversalement mobiles, p.ex. radialement
B29L 31/08 - Pales pour rotors, stators, ventilateurs, turbines ou dispositifs analogues, p.ex. hélices
B29K 105/10 - Présentation, forme ou état de la matière moulée contenant des agents de renforcement, charges ou inserts de grande longueur, p.ex. ficelles, mèches, mats, tissus ou fils orientés
30.
METHOD AND AIRCRAFT PROVIDING BLEED AIR TO AN ENVIRONMENTAL CONTROL SYSTEM
A method and aircraft for providing bleed air to environmental control systems of an aircraft using a gas turbine engine, including determining a bleed air demand for the environmental control systems, supplying low pressure and high pressure bleed air to the environmental control systems, wherein the proportional supplying is controlled such that the conditioned air stream meets the determined bleed air demand.
B64D 13/02 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret l'air étant pressurisé
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
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
An air turbine starter (ATS) assembly includes a rotatable pinion gear (72) wherein the rotatable pinion gear is coupled to a combustion engine (10), a speed sensor (78) measuring the rotational speed (302) of the rotatable pinion gear (72), a torque sensor (79) providing a torque output (304) indicative of a torque experienced by the pinion gear (72), and a controller module configured to operate a starting sequence for the ATS assembly such that the rotational speed (302) is controllably increased while the torque output (304) is kept below the start sequence torque threshold (310).
F02C 7/277 - Entraînement du rotor pour le démarrage mécanique par une turbine
F01D 19/00 - Démarrage des "machines" ou machines motrices; Dispositifs de régulation, de commande ou de sécurité en rapport avec les organes de démarrage
F02N 11/08 - Circuits spécialement adaptés pour le démarrage des moteurs
F02N 15/10 - Dispositifs de sécurité non prévus ailleurs
32.
METHOD AND APPARATUS FOR STARTING AN AIRCRAFT ENGINE AND OPERATING A POWER ARCHITECTURE FOR AN AIRCRAFT
A method and apparatus for starting and operating at least a first starter/generator (S/G) and a second S/G using at least one bi-directional converter and at least one of an AC power source and a first DC power source, including selectively starting at least one of the first S/G or second S/G in an AC start mode or in a DC start mode, and supplying electrical power to a set of electrical loads.
Systems and methods for controlling a DC to AC inverter providing a multiphase output at a fundamental frequency are provided. More particularly, a synchronous reference frame control scheme can be employed to regulate a DC to AC inverter to attenuate error at various frequencies of interest for the DC to AC inverter. According to particular example aspects of the present disclosure, the synchronous reference frame control scheme can include control structures to provide for attenuation of the negative sequence and zero sequence currents, leading to reduced total harmonic distortion and voltage unbalance in the output voltage of the inverter.
H02M 1/12 - Dispositions de réduction des harmoniques d'une entrée ou d'une sortie en courant alternatif
H02M 7/538 - 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 push-pull
34.
TURBINE ENGINE WITH ANTI-ICE ASSEMBLY, BLEED AIR VALVE, AND METHOD OF OPERATING
An anti-ice valve, a turbine engine including an anti-ice valve assembly and a method of operating an anti-ice valve where an anti-ice valve has a housing and a valve element configured to control a flow of hot bleed air through the housing, and a muscle air passage extending through the housing, a cooling air passage extending through the housing, and a heat exchanger located within the housing and having heat transfer surfaces in thermal communication with the muscle air passage and the cooling air passage.
F01D 17/14 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage
35.
METHOD AND APPARATUS FOR COOLING A HEAT-GENERATING MODULE
A liquid cooling circuit includes a liquid reservoir for coolant, a heat-generating module, a conduit fluidly coupling the heat-generating module with the liquid reservoir, and a pump configured to move the coolant through the conduit to cool the heat-generating module. The liquid cooling circuit is configured such that the movement of the coolant relative to the heat-generating module transfers heat from the heat-generating module to the coolant.
Air starter and methods for determining hydrostatic lock in a combustion engine during a start sequence with an air starter, including during the start sequence of the combustion engine, monitoring a speed parameter indicative of a rotational speed of the turbine air starter and a pressure parameter indicative of an inlet air pressure of the turbine air starter, and determining that a hydrostatic lock condition exists in the combustion engine based on both the speed threshold and the pressure threshold.
A method and regulator for regulating a power converter includes an integrator circuit coupled with a voltage output from the power converter, a comparator circuit receiving a target voltage signal indicating a target voltage output of the power converter, and the integrated voltage signal as inputs, and a driving circuit receiving the comparator output signal and configured to drive the power converter, wherein the regulating system controls the power converter to generate a voltage output consistent with the target voltage output on a cycle per cycle basis.
H02M 1/00 - APPAREILS POUR LA TRANSFORMATION DE COURANT ALTERNATIF EN COURANT ALTERNATIF, DE COURANT ALTERNATIF EN COURANT CONTINU OU VICE VERSA OU DE COURANT CONTINU EN COURANT CONTINU ET EMPLOYÉS AVEC LES RÉSEAUX DE DISTRIBUTION D'ÉNERGIE OU DES SYSTÈMES D'ALI; TRANSFORMATION D'UNE PUISSANCE D'ENTRÉE EN COURANT CONTINU OU COURANT ALTERNATIF EN UNE PUISSANCE DE SORTIE DE CHOC; LEUR COMMANDE OU RÉGULATION - Détails d'appareils pour transformation
A method for operating an electrical circuit for controllably delivering power from a power source to an electrical load including a switch further configured to operate in a first conducting mode and a second non-conducting mode, and a controller, the method includes ceasing delivering power from the power source to the electrical load.
A wet cavity electric machine includes a stator core having two stator poles formed by a post and a wire wound about the post to form a stator winding, with the stator winding having end turns, and a rotor having two rotor poles and configured to rotate relative to the stator and a channel for liquid coolant to flow through the rotor, and at least one fluid port in fluid communication with the channel and the stator winding end turns wherein the end turns will be exposed to liquid coolant passing through the channel.
H02K 1/32 - Parties tournantes du circuit magnétique avec des canaux ou des conduits pour l'écoulement d'un agent de refroidissement
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 9/22 - 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
H02K 3/52 - Fixation des enroulements de pôles saillants ou de leurs connexions
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
40.
METHOD AND APPARATUS FOR AN ELECTRICAL FAULT DETECTING SYSTEM FOR A CABLE
An electrical fault detecting system (10) for a circuit includes a conductor (20) delivering an electrical signal from a source (12) to a destination (14), a sheath (22) encircling the conductor, and a fault detection circuit (18). The sheath further includes an electrical insulator layer (24) and a conductive shield (26) encircling the conductor. The fault detection circuit is configured to detect a change in the electrical characteristics of the conductor and/or conductor sheath.
G01R 31/02 - Essai des appareils, des lignes ou des composants électriques pour y déceler la présence de courts-circuits, de discontinuités, de fuites ou de connexions incorrectes de lignes
An aircraft starting and generating system includes a starter/ generator and an inverter/converter/controller (200) that is connected to the starter/generator and that generates AC power to drive the starter/generator in a start mode for starting a prime mover of the aircraft, and that converts AC power, obtained from the starter/ generator after the prime mover have been started, to DC power in a generate mode of the starter/generator. A four leg inverter is coupled with a DC power output (452) of the starter/generator and has an inverter/converter/controller (ICC) (580) with a four leg MOSFET-based bridge configuration that drives the starter/generator in a start mode for starting a prime mover of the aircraft, and converts DC power to AC power in a generate mode of the starter/generator. A four leg bridge gate driver (560) is configured to drive the four leg MOSFET- based bridge (580) during start and generate mode using bi-polar pulse width modulation (PWM).
An aircraft starting and generating system includes a starter/generator that includes a main machine (110), an exciter (120), and a permanent magnet generator (130). The system also includes an inverter/converter/controller (200) that is connected to the starter/generator and that generates AC power to drive the starter/generator in a start mode for starting a prime mover of the aircraft, and that converts AC power, obtained from the starter/generator after the prime mover have been started, to DC power in a generate mode of the. A load-leveling unit (LLU) (450) is selectively coupled with a DC power output from the starter/generator and has an inverter/converter/controller (ICC) with an LLU metal oxide semiconductor field effect transistor (MOSFET)-based bridge configuration (480) that supplies DC power to the DC power output in a supply mode, and that receives DC power from the DC power output, in a receive mode. A LLU bridge gate driver is configured to drive the LLU MOSFET-based bridge during a supply mode and a receive mode using bi-polar pulse width modulation (PWM).
H02J 7/34 - Fonctionnement en parallèle, dans des réseaux, de batteries avec d'autres sources à courant continu, p.ex. batterie tampon
F02N 11/04 - Démarrage des moteurs au moyen de moteurs électriques les moteurs étant associés avec des générateurs de courant
H02M 3/158 - 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 comprenant plusieurs dispositifs à semi-conducteurs comme dispositifs de commande finale pour une charge unique
An aircraft starting and generating system includes a starter/generator that includes a main machine, an exciter, and a permanent magnet generator. The system also includes an inverter/converter/controller that is connected to the starter/generator and that generates AC power to drive the starter/generator in a start mode for starting a prime mover of the aircraft, and that converts AC power, obtained from the starter/generator after the prime mover have been started, to DC power in a generate mode of the starter/generator. A main bridge gate driver is configured to drive a MOSFET-based bridge during start mode using Space Vector Pulse Width Modulation (SVPWM) and during generate mode using reverse conduction based inactive rectification.
H02P 9/30 - Dispositions pour la commande de génératrices électriques de façon à obtenir les caractéristiques désirées à la sortie par variation du champ utilisant des tubes à décharge ou des dispositifs à semi-conducteurs utilisant des dispositifs à semi-conducteurs
F02N 11/04 - Démarrage des moteurs au moyen de moteurs électriques les moteurs étant associés avec des générateurs de courant
A heat sink assembly for use with at least one heat-emitting component where the heat sink assembly includes a first phase change material conductively coupled to the at least one heat-emitting component and changing phase at a first temperature and a second phase change material conductively coupled to the first phase change material and changing phase at a second temperature, which is greater than the first temperature.
An airflow generator (10, 110, 210) and array of airflow generators for use with an object (12, 112, 212) where each of the airflow generators (10,110, 210) includes a flexible structure (20,120, 220) having a first side (22, 122, 222) spaced from a portion of the object (12, 112, 212) to define an air space (15, 115, 215) therebetween and at least one piezoelectric structure (24, 124, 224) located on the flexible structure (20, 120, 220).
An airflow generator (10) having a first plate (12), a second plate (14) where the second plate (14) is spaced from the first plate (12) to define a cavity (28) there between, a joint (30) operably coupled to the first plate (12) and the second plate (14) and joining them together, piezoelectrics (34) located on each of the first plate (12) and the second plate (14) wherein actuation of the piezoelectrics (34) results in movement of the first plate (12) and the second plate (14) to increase the volume of the cavity (28) to draw air in (200) and then decrease the volume of the cavity (28) to push out the drawn in air (202).
An air-cooling system (10, 110, 210) utilizing a synthetic jet or airflow generator (20, 120, 220) and airflow generators utilizing piezoelectrics (26, 126, 226) to cool heat-emitting elements (12, 112, 212). Actuation of the piezoelectrics (26, 126, 226) results in movement of one or more flexible structures (22, 24, 122, 124, 221) to increase the volume of one or more cavities (28, 30, 32, 128, 228, 230, 232) to draw air in and then decrease the volume of the one or more cavities (28, 30, 32, 128, 228, 230, 232) to push out the drawn in air.
A method for slow starting a reciprocating engine (10) having a crankshaft (12), a piston (14), a piston chamber (30) and a pneumatic starter (52), by applying a force to the crankshaft (12) via the pneumatic starter (52) while disabling the fuel injection, sensing an engine characteristic (engine speed, starter speed, starter torque, etc.), comparing the sensed engine characteristic to a diagnostic profile and determining if a fault (hydrostatic lock) is present in the engine (10). In case of a diagnosed fault, the start is interrupted. Otherwise the pneumatic starter speed is increased, the engine is fueled and the start is processed as usual.
F02N 15/10 - Dispositifs de sécurité non prévus ailleurs
F02N 7/08 - Appareils de démarrage comportant un moteur ou un appareil auxiliaire entraîné par fluide les moteurs étant du type rotatif
F02D 41/22 - Dispositifs de sécurité ou d'avertissement en cas de conditions anormales
F02D 41/06 - Dispositions de circuits pour produire des signaux de commande introduisant des corrections pour des conditions particulières de fonctionnement pour le démarrage ou le réchauffage du moteur
A fault monitoring system for an aircraft includes a processor having a fault diagnosis algorithm, a memory connected to the processor, a plurality of sensors located at selected nodes in an electrical network of the aircraft and connected to the processor, and a data collection algorithm in one of the processor or the plurality of sensors. Each sensor is configured to continuously monitor voltage and current of the electrical network at its selected node and to transmit data representative of the monitored voltage and current to the processor. Upon the occurrence of a fault event, the data collection algorithm selects a subset of the data related to the fault event and at least one sensor transmits a selected subset of the data to one of the processor or the memory.
An exhaust section for an aircraft gas turbine engine includes an exhaust nozzle in a downstream serial flow relationship with the gas turbine engine having a fan section, a compressor section, a combustion section, a turbine section, and an exhaust section. The compressor section compresses intake air from the fan section, which is mixed with fuel and combusted into hot gases in the combustion section. The hot gases drive the turbines of the turbine section, and are expelled from the gas turbine engine at the exhaust section.
H02K 44/10 - Générateurs magnétohydrodynamiques - Détails de structure des électrodes
F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
B64D 33/04 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des sorties d'échappement ou des tuyères
B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
A ball valve assembly (10) includes a housing (12) having a chamber (13) with an inlet (15) and outlet (17) defining a flow passage (23), a ball (14) with a through passage (21), a linear actuator (18) and a rotation converter (16) configured to rotate the ball (14) upon actuation of the linear actuator (18) to control the flow of a fluid through the flow passage (21).
F16K 31/163 - Moyens de fonctionnement; Dispositifs de retour à la position de repos actionnés par un fluide et avec un mécanisme autre qu'une tige va-et-vient, entre le moteur à fluide et l'élément de fermeture le fluide agissant sur un piston
F16K 5/06 - Robinets à boisseau consistant seulement en un dispositif obturateur dont au moins une des faces d'obturation a la forme d'une surface de solide de révolution plus ou moins complète, le mouvement d'ouverture et de fermeture étant essentiellement rota dont les boisseaux sont à surface sphérique; Leurs garnitures d'étanchéité
An electrical generator for an aircraft includes a gas turbine engine having an exhaust section defining an exhaust cavity through which combustion exhaust gases are emitted in a direction defining an exhaust vector, and a magnetohydrodynamic generator having a magnetic field generator forming a magnetic field having at least some magnetic field lines perpendicular to the exhaust vector, and at least one electrode pair, comprising at least one positive electrode and at least one negative electrode, arranged relative to the exhaust section wherein movement of charged particles entrained in the exhaust gas along the exhaust vector generates a DC power output at the at least one electrode pair.
A health management unit for an aircraft and method of monitoring health information of an aircraft and transmitting information from the aircraft including determining capabilities of one or more radios onboard the aircraft, selecting one of the multiple radios to transmit the transmission based, and transmitting the transmission utilizing the selected radio.
H04Q 9/00 - Dispositions dans les systèmes de commande à distance ou de télémétrie pour appeler sélectivement une sous-station à partir d'une station principale, sous-station dans laquelle un appareil recherché est choisi pour appliquer un signal de commande ou
A method of controlling data communication in a communications network having a plurality of remote input units providing data and a plurality of subscriber units utilizing at least some of the data. The data from the remote input units may be formatted into a format suitable for subscriber units, and/or may be processed to be useful to the subscriber units. The formatted and/or processed data is then provided over the communications network to the subscribing units.
An aircraft power distribution system (22) includes at least one DC power source, a first DC power distribution bus (34) and a second DC power distribution bus (36), a tie bus (33) coupling the at least one DC power source, first DC power distribution bus, and second DC distribution bus, wherein the first or second DC power distribution buses are selectively coupled and decoupled to the tie bus by means of a solid-state poer controller (SSPC) (46, 48, 62, 64, 66).
H02J 1/10 - Fonctionnement de sources à courant continu en parallèle
H02J 9/06 - Circuits pour alimentation de puissance de secours ou de réserve, p.ex. pour éclairage de secours dans lesquels le système de distribution est déconnecté de la source normale et connecté à une source de réserve avec commutation automatique
H02J 1/00 - Circuits pour réseaux principaux ou de distribution, à courant continu
An inverter phase leg (100) for an AC-DC inverter (10, 20) includes a high supply line (12, 22) and a low supply line (14, 24) across which a DC voltage is provided. A high side gate controlled switch (110) is connected to the high supply line and a low side gate controlled switch (114) is connected to the low supply line, with an output node (104) between the high side switch and the low side switch. An inverting driver (116) is connected to the high side gate controlled switch (114) and a source of first DC voltage is provided between the output node (104) and the inverting driver (116). A digital isolator (120) is connected between the inverting driver (116) and a control signal (128) for switching the inverter phase leg (100). The driving voltage of the inverting driver (116) is set to cause the output voltage to be zero until the input voltage exceeds the first DC voltage.
An aircraft including a jet engine including a core having a compressor and combustion chamber, and a particulate sensor located within the core and a particulate detection method for an aircraft having a jet engine where the method includes sensing particulates within the core and providing a corresponding value for the sensed particulates and providing an indication related thereto.
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
G01M 15/14 - Test des moteurs à turbine à gaz ou des moteurs de propulsion par réaction
F02C 7/05 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs pour empêcher la pénétration d'objets ou de particules endommageantes
F02C 7/052 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs pour empêcher la pénétration d'objets ou de particules endommageantes comportant des dispositifs séparateurs de poussière
F02C 7/055 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs pour empêcher la pénétration d'objets ou de particules endommageantes comportant des grilles, des écrans ou des dispositifs protecteurs
F02C 9/00 - Commande des ensembles fonctionnels de turbines à gaz; Commande de l'alimentation en combustible dans les ensembles fonctionnels de propulsion par réaction alimentés en air ambiant
G01N 15/06 - Recherche de la concentration des suspensions de particules
B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion
A rotor assembly (40) for an electric machine including a core (42) having at least one post (44) about which a winding may be wound, and a cap (52) coupled to the post (44) and having a portion overlying a winding (46), wherein the cap (52) comprises a plurality of laminations and the core (42) does not comprise a plurality of laminations.
H02K 1/32 - Parties tournantes du circuit magnétique avec des canaux ou des conduits pour l'écoulement d'un agent de refroidissement
H02K 3/52 - Fixation des enroulements de pôles saillants ou de leurs connexions
H02K 9/02 - Dispositions de refroidissement ou de ventilation par l'air ambiant s'écoulant à travers la machine
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
A method of starting an aircraft having at least a first starter/generator (S/G) and a second S/G using at least one DC/AC inverter/converter and at least one of an AC power source and a first DC power source, the method includes selectively starting at least one of the first S/G or second S/G in an AC start mode and in a DC start mode.
A power system for an aircraft having a plurality of power-consuming components, some of which have transient power requirements, which is greater than the average power requirement, the power system includes at least one generator, a power distribution buss, a non-battery power source, a battery power source, and a power controller selectively coupling the non-battery power source and the battery power source to the power distribution buss to satisfy the transient power requirements.
H02J 7/34 - Fonctionnement en parallèle, dans des réseaux, de batteries avec d'autres sources à courant continu, p.ex. batterie tampon
H02J 9/06 - Circuits pour alimentation de puissance de secours ou de réserve, p.ex. pour éclairage de secours dans lesquels le système de distribution est déconnecté de la source normale et connecté à une source de réserve avec commutation automatique
A rotor assembly for an electric machine includes a core and a cap wherein electrical windings are wound about the rotor assembly to define a pole. The rotation of the rotor and rotor pole relative to a stator generates a current supplied from the electric machine to a power consuming device.
A rotor assembly for an electric machine includes a core having at least one post and a cap wherein electrical windings are wound about the rotor assembly to define a pole. The rotation of the rotor and rotor pole relative to a stator generates a current supplied from the electric machine to a power consuming device.
A method for controlling the supply of power to a power system for an aircraft having a plurality of power-consuming components includes supplying power to the power system with a generator having a power output, determining a power requirement of the power system, and supplying the power to the power-consuming components.
H02J 7/34 - Fonctionnement en parallèle, dans des réseaux, de batteries avec d'autres sources à courant continu, p.ex. batterie tampon
H02J 9/06 - Circuits pour alimentation de puissance de secours ou de réserve, p.ex. pour éclairage de secours dans lesquels le système de distribution est déconnecté de la source normale et connecté à une source de réserve avec commutation automatique
64.
FASTENING ASSEMBLY FOR ELECTRIC MACHINE AND RECTIFIER THEREFOR
A method of assembling a rotating rectifier having multiple radially spaced bus bars with a corresponding fastener to an electrical machine having at least one machine with a stator and a rotor mounted on a rotating shaft, the method includes inserting the rotating rectifier into a hollow portion of the rotating shaft, axially aligning the fasteners with a corresponding radial opening in the rotating shaft, inhibiting an inward radial movement of the fasteners by inserting an inhibiting tool into an interior defined by the multiple radially spaced bus bars, and at least partially securing the fasteners to a corresponding fastener on at least one of the rotor and rotating shaft while the inhibiting tool resides in the interior.
A turbofan engine includes a turbine engine having a rotatable fan and a generator. The generator further includes a main machine, an exciter, and a generator control unit for controlling the excitation of the main machine. A rotor assembly is located within one of the blades, and a stator assembly that is along a rotational path of the rotor assembly whereby the operation of the turbine engine rotates the fan, which rotates the rotor assembly along its rotational path past the stator assembly to generate electricity.
F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
F02C 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes ; Entrées d'air pour ensembles fonctionnels de propulsion par réaction
F02C 6/00 - Ensembles fonctionnels multiples de turbines à gaz; Combinaisons d'ensembles fonctionnels de turbines à gaz avec d'autres appareils; Adaptations d'ensembles fonctionnels de turbines à gaz à des applications particulières
66.
JET ENGINE ASSEMBLY AND METHOD FOR GENERATING ELECTRICITY
A jet engine assembly includes a jet engine having at least one spool and a generator. The generator comprising a rotor and a stator, with the rotor being operably coupled to the at least one spool, and an electronic commutator controlling the rotation of a magnetic field of the rotor such that the electric motor generates electricity. Also, a method of generating electricity from a generator having a stator and a rotor, the method comprising controlling a rotation of a magnetic field to generate electricity.
A turbofan engine having a thrust reverser having at least one movable control surface, movable to and from a reversing position where at least a portion of the bypass air flow is at least partially reversed, a thrust reverser actuation system having multiple actuators and a lockout mechanism movable between an inhibit condition, wherein movement of the multiple actuators is prevented, and a permit condition, wherein movement of the multiple actuators is permitted.
F02C 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes ; Entrées d'air pour ensembles fonctionnels de propulsion par réaction
F02C 7/04 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction
F02C 9/00 - Commande des ensembles fonctionnels de turbines à gaz; Commande de l'alimentation en combustible dans les ensembles fonctionnels de propulsion par réaction alimentés en air ambiant
F02K 3/00 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant
A method for displaying a flight plan having at least one waypoint on a flight display of a flight deck of an aircraft having known flight constraints, including receiving a user input for a user-inputted waypoint and generating an alternative waypoint when the user-inputted waypoint is not suitable and displaying same.
A method and system for a multi-spectrum celestial navigation system includes a first sensor responsive to at least a first and a second wavelength band of electromagnetic radiation. The sensor is configured to generate a first output related to the first wavelength band of electromagnetic radiation and to generate a second output related to the second wavelength band of electromagnetic radiation. The system also includes a processor programmed to receive the first and second outputs, determine a position of the sensor with respect to one or more stars using a stored star catalog and the received first and second outputs, and output the determined position.
A method and system for a motion compensated input device are provided. The motion compensated input device includes an input device configured to receive a physical input from a user and convert the physical input into a physical input signal representative of the physical input, a motion sensing device configured to sense acceleration forces of at least one of the input device and the user, the acceleration forces introducing an error into the physical input, and an input compensator configured to adjust the physical input signal using the acceleration forces to generate a compensated input signal representative of the physical input.
A method and system for an integrated ejector valve assembly is provided. The integrated ejector valve assembly includes a first valve assembly configured to control a flow of relatively lower pressure fluid from a first inlet port, a second valve assembly configured to control a flow of relatively higher pressure fluid from a second inlet port, a first actuation chamber configured to close the first valve assembly, a second actuation chamber configured to close the second valve assembly, and a third actuation chamber configured to open the second valve assembly.
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
F16K 11/22 - 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 plusieurs éléments de fermeture ne se déplacent pas comme un tout actionnés par des organes de commande distincts chacun étant propre à une soupape, p.ex. conjugués pour former clapet à voies multiples
F01D 17/14 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage
72.
METHODS AND SYSTEMS FOR NO-BREAK POWER TRANSFER WITH A CONVERTER
A method is provided for using a temporary power source to transfer a power bus from a first power source to a second power source. The first power source operates at a first electrical frequency, and the second power source operates at a second electrical frequenq that is different from the first electrical frequenq The method includes adjusting the output frequency of the lemporan power source to match the first electrical frequency and supph mg power to the pow er bus from the temporary pow er source The method also includes disconnecting the first power source from the power bus. The method further includes adjusting the output frequency of the temporan power source to match the second electrical frequenq. The method further includes coupling the second power source to the power bus.
H02J 3/00 - Circuits pour réseaux principaux ou de distribution, à courant alternatif
H02J 9/06 - Circuits pour alimentation de puissance de secours ou de réserve, p.ex. pour éclairage de secours dans lesquels le système de distribution est déconnecté de la source normale et connecté à une source de réserve avec commutation automatique
73.
SYSTEM AND METHOD FOR TRANSFERRING POWER BETWEEN AN AIRCRAFT POWER SYSTEM AND ENERGY STORAGE DEVICES
A method for transferring power in an aircraft between an energy storage device and a power system. The method includes determining an amount of power required by the power system, determining a predetermined amount of power from a generator, comparing the power required by the power system to the predetermined power of the generator, and transferring power to the energy storage device from the power system or to the power system from the energy storage device based on the comparing.
H02J 1/16 - Circuits pour réseaux principaux ou de distribution, à courant continu Équilibrage de la charge dans un réseau utilisant des machines dynamo-électriques accouplées à des volants
H02J 7/14 - Circuits pour la charge ou la dépolarisation des batteries ou pour alimenter des charges par des batteries pour la charge de batteries par des générateurs dynamo-électriques entraînés à vitesse variable, p.ex. sur véhicule
H02J 7/34 - Fonctionnement en parallèle, dans des réseaux, de batteries avec d'autres sources à courant continu, p.ex. batterie tampon
74.
ELECTRIC ENERGY STORAGE INTEGRATED WITHIN OR PROXIMATE TO ELECTRICALLY DRIVEN FLIGHT CONTROL ACTUATORS
An apparatus for use with a flight control actuator and method for assembling the same is provided. The apparatus includes a motor drive system (100) and a control unit. The motor drive system (100) includes a capacitor-based energy storage (120) configured to store and provide energy within or proximate to the actuator. The control unit is coupled to the motor drive system and is configured to facilitate managing power within or proximate to the actuator.
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
B64C 13/50 - Dispositifs de transmission avec amplification de puissance utilisant l'énergie électrique
H02M 3/158 - 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 comprenant plusieurs dispositifs à semi-conducteurs comme dispositifs de commande finale pour une charge unique
75.
METHOD AND SYSTEMS FOR REQUIRED TIME OF ARRIVAL PERFORMANCE DISPLAY
A method and system for a required time of arrival (RTA) performance graphic display is provided. The system includes a processor programmed to receive a required time of arrival and a first visual display communicatively coupled to the processor. The first visual display includes an RTA graphic having a dial substantially symmetric about an axis, a first marker indicative of a current estimated time of arrival (ETA) at a predetermined waypoint, a second marker indicative of a value of the RTA relative to the current ETA value and a selected RTA time tolerance value, a first indication representing a first time the vehicle can attain the predetermined waypoint, a second indication representing a last time the vehicle can attain the predetermined waypoint, a third indication representing the uncertainty of the ETA in an early arrival direction, and a fourth indication representing the uncertainty of the ETA in a late arrival direction.
G01C 23/00 - Instruments combinés indiquant plus d’une valeur de navigation, p.ex. pour l’aviation; Dispositifs de mesure combinés pour mesurer plusieurs variables du mouvement, p.ex. la distance, la vitesse ou l’accélération
G05D 1/10 - Commande de la position ou du cap dans les trois dimensions simultanément
A system and methods for reducing vibration in a rotatable member are provided. The system includes a blade tracking sensor (62), a rotatable member comprising an adjustable aspect and a control computer (64). The control computer is configured to determine an axial position of each blade (40), determine a first blade that is displaced by a greatest distance along the axis in a first direction, modify an aspect of the first blade to facilitate reducing a vibration in the rotary blade system, determine if the vibration level in the rotary blade system is reduced, and select another rotatable member to modify such that a vibration in the rotary blade system is facilitated being further reduced.
A high-integrity, N-lane computer processing module (Module), N being an integer greater than or equal to two. The Module comprises one Hosted Application Element and I/O Element per processing lane, a Time Management unit (TM) configured to determine an equivalent time value for a request made by software running on each of the N processing lanes, irrespective as to when the request is actually received and acted on by each of the N processing lanes, and a Critical Regions Management unit (CRM) configured to enable critical regions within the respective lane to be identified and synchronized across all of the N processing lanes.
A refueling drogue assembly including a refueling drogue receptacle, a control unit including a duct, and a refueling hose connector adapted to rigidly couple the control unit to an aerial refueling hose. In some embodiments, the control unit is flexibly coupled to the refueling drogue receptacle. In some embodiments, the control unit is adapted to change an orientation of at least a portion of the duct relative to a longitudinal axis of the control unit.
An aircraft starting and generating system includes a starter/generator that includes a main machine, an exciter, and a permanent magnet generator. The system also includes an inverter/converter/controller that is connected to the starter/generator and that generates AC power to drive the starter/generator in a start mode for starting a prime mover of the aircraft, and that converts AC power, obtained from the starter/generator after the prime mover have been started, to DC power in a generate mode of the starter/generator. The exciter includes a stator and a rotor, and wherein the exciter rotor includes a three-phase AC winding.
A butterfly valve for controlling the flow of fluid within a bore, including a butterfly and at least one ring extending at least one of substantially and completely around a perimeter of the butterfly and adapted to develop an expansion force in the radial direction when the at least one ring is in a contracted state with respect to the radial direction, wherein the at least one ring is secured to the butterfly in the contracted state and radial expansion due to the developed expansion force of the at least one ring is effectively restrained, wherein the butterfly valve is adapted to operate, when placed in a bore, without friction or substantially without friction between the at least one ring and the bore when the butterfly valve is placed in a closed position within the bore.
A communication system and method includes a main bus that operates in accordance with a standard limited to a linear topology, a bus controller coupled to the main bus and configured to send and receive messages on the main bus, and a first remote terminal coupled to the main bus and configured to send and receive messages on the main bus including the messages sent by the bus controller. The system and method also includes a repeater coupled to the main bus and configured to send and receive messages on the main bus including the messages sent by the bus controller and by the first remote terminal, and second and third remote terminals coupled to the repeater, wherein the second and third remote terminals send and receive messages on the main bus via the repeater.
An air cooling apparatus for an aircraft includes a cabinet that is configured to house a plurality of modules in a plurality of module accepting regions, respectively, wherein the cabinet has a backplane region. The apparatus further includes a plurality of air flow passages provided between adjacent ones of the respective module accepting regions of the cabinet. The apparatus also includes a primary air flow unit for providing primary air flow from the backplane region and through the plurality of air flow passages, to thereby cool the plurality of modules housed within the cabinet.
A video storage uplink system includes a controller, a power input, an external input, a first and second memory partition, a switching interface, a communications unit and a data retrieval interface. The external camera input is configured to receive image data acquired by a plurality of video cameras mounted to the exterior of an aircraft. The switching interface is configured to receive airborne status signals from a squat switch mounted to the landing gear. The first memory partition stores image data received when the aircraft is on the ground. The second memory partition stores image data received when the aircraft is airborne. The communications unit is configured to transmit image data stored in the first and second memory partition. Alternatively, the data retrieval interface, provides access to data stored in the first and second memory partition via a physical connector. Using crash protected solid state memory partitions allow data retrieval for air or ground accident investigations.
An electronic assembly cooling system including a module case assembly that has a module case wall. The system includes a first and second air driver and an electronic assembly located in-front of the module case wall. The system conducts thermal energy from the electronic assembly from in-front of the module case wall to in-back of the module case wall, and directs air driven by the first air driver past the module case wall in-front of the module case wall to cool the electronic assembly via convective heat transfer. The system directs air driven by the second air driver past the module case wall in-back of the wall to transfer the thermal energy conducted from the electronic assembly from in-front of the module case wall to in-back of the module case wall to the air driven by the second air driver via conductive heat transfer to cool the electronic assembly.
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