A power filtration system filters out a common mode signal from a DC conductor of a power system. The power filtration system comprises a first filter and at least one of a load or a power circuit. The first filter is connected to the DC conductor and configured to pass the common mode signal. The load is configured to dissipate the energy of the common mode signal. The power circuit is configured to conduct the common mode signal to an energy storage device.
H02M 1/12 - Dispositions de réduction des harmoniques d'une entrée ou d'une sortie en courant alternatif
H02J 1/10 - Fonctionnement de sources à courant continu en parallèle
H02J 1/14 - Équilibrage de la charge dans un réseau
H02J 7/00 - Circuits pour la charge ou la dépolarisation des batteries ou pour alimenter des charges par des batteries
H02J 7/02 - Circuits pour la charge ou la dépolarisation des batteries ou pour alimenter des charges par des batteries pour la charge des batteries par réseaux à courant alternatif au moyen de convertisseurs
H02M 1/44 - Circuits ou dispositions pour corriger les interférences électromagnétiques dans les convertisseurs ou les onduleurs
H02M 3/157 - 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 avec commande numérique
H02M 7/06 - 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 sans électrode de commande ou des dispositifs à semi-conducteurs sans éléctrode de commande
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
2.
SYSTEMS AND METHODS FOR CONTROLLING ADDITIVE MANUFACTURING PROCESSES
Systems and methods for controlling additive manufacturing processes are disclosed. The systems can include multiple laser directors, soot-removal devices, magnetic chucks, replenishable powder distribution blades, automated powder level detectors, and/or overall process automation techniques.
B29C 64/135 - Procédés de fabrication additive n’utilisant que des matériaux liquides ou visqueux, p. ex. dépôt d’un cordon continu de matériau visqueux utilisant des couches de liquide à solidification sélective caractérisés par la source d'énergie à cet effet, p. ex. par irradiation globale combinée avec un masque la source d’énergie étant concentrée, p. ex. lasers à balayage ou sources lumineuses focalisées
B29C 64/371 - Conditionnement de l’environnement en utilisant un environnement autre que l’air, p. ex. un gaz inerte
B29C 64/393 - Acquisition ou traitement de données pour la fabrication additive pour la commande ou la régulation de procédés de fabrication additive
B29C 64/40 - Structures de support des objets en 3D pendant la fabrication, lesdites structures devant être sacrifiées après réalisation de la fabrication
A method of routing communication among nodes and systems of an interplanetary network on an ad-hoc basis is described herein. For example, the communication routing described herein may not be pre-determined or static, but rather determined dynamically on a periodic basis, as transmission conditions change, as nodes are added or removed from the interplanetary network, periodically, and/or the like. The interplanetary network may include one or more nodes that have static and/or dynamic states. A node can include any extraterrestrial object or communication relay. The interplanetary network may also include one or more ground stations, which can include communication equipment (e.g., antennas, radar, transmission towers, etc.) located on Earth. To enable the ad-hoc communication routing, a ground station system and/or another processing device can continuously or periodically obtain orbital parameters from one or more nodes in the interplanetary network and generate updated contact plans.
Seals for gimbaling and/or fixed rocket engine nozzles, and associated systems and methods are disclosed. A representative rocket propulsion system includes a rocket engine having an exhaust nozzle, a seal plate carried by the exhaust nozzle, and a seal engaged with the seal plate. The seal includes at least one support, multiple pivotable first flaps, carried by the at least one support and positioned to contact the seal plate, and multiple pivotable second flaps, with an individual second flap positioned to shield a corresponding individual first flap. At least one forcing element is operatively coupled to at least one of the individual first flap or the individual second flap, to apply a pivoting force to the at least one of the individual first flap or the individual second flap.
A solar cell that incorporates a thin layer of transparent silicate, and a number of techniques for fabricating the thin layer of transparent silicate, are presented. The transparent silicate may be a protective coverglass on the solar cell or solar panel. Fabricating the coverglass may include vaporizing iron-depleted lunar regolith to produce vaporized transparent silicate and allowing the vaporized transparent silicate to condense onto a solar panel to form the coverglass. Vaporizing the iron-depleted lunar regolith to produce the vaporized transparent silicate may involve directing an electron beam onto the iron-depleted lunar regolith in a process of electron-beam physical vapor deposition (EBPVD). The iron-depleted lunar regolith may be electrolyte of a molten electrolysis process.
A device configured to couple a rounding ring to a tank is provided. In one aspect, the device includes a bracket having a first leg angled relative to a second leg, the first leg comprising a tank-facing side and a first opening, the second leg configured to couple to the rounding ring; a mount comprising a tank-facing side and a stud on a second side opposite the tank-facing side, the tank-facing side of the mount configured to place an adhesive into contact with the tank when the stud is inserted into the first opening of the bracket via the tank facing side of the first leg of the bracket; a spring between the second side of the mount and the tank-facing side of the first leg of the bracket when the stud is inserted into the first opening of the bracket; and a nut configured to couple to the stud and compress the spring when the stud is inserted into the first opening of the bracket and the second leg is coupled to the rounding ring. Movement of the nut away from the mount uncompresses the spring to place adhesive on the tank-facing side of the mount into contact with the tank.
Porous media and methods of manufacturing porous media, such as for use in aerospace parts, are described herein. In some embodiments, a porous medium comprises a monolithic structure having a plurality of vertically stacked metal layers. Individual ones of the metal layers can include an array of spaced apart weld beads, and the arrays of weld beads can be rotationally and/or laterally offset from one another. For example, the arrays of weld beads can be rotationally offset from another by an angle that is not a factor of 360 degrees. The weld beads can together define a plurality of non-discrete passageways extending through the monolithic structure.
B23K 26/064 - Mise en forme du faisceau laser, p. ex. à l’aide de masques ou de foyers multiples au moyen d'éléments optiques, p. ex. lentilles, miroirs ou prismes
B23K 26/34 - Soudage au laser pour des finalités autres que l’assemblage
A diffuser for separating a gas component and a liquid component of a liquid-gas mixture to reduce slosh in vehicle systems is described herein. The diffuser includes a wall with a gas end, a liquid end, and multiple vanes partially extending from the liquid side to the gas side. The vanes are spaced apart from each other by a given distance to permit the liquid to flow toward the liquid end via capillary action.
A variable flow area injector for a liquid rocket engine. The injector has a poppet with a variable outer width portion and a housing with a variable inner width portion. An annular flow path is defined between the variable width portions. Increased throttling of the engine passively increases the annular flow area of the injector by forcing the poppet in a distal direction. Decreased throttling allows a restoring spring to move the poppet in a proximal direction to decrease the annular flow area. A bellows can be included to dampen movement of the poppet. The bellows may be in a propellant-filled cavity separate from the main propellant flow path and have a series of openings through which the separate propellant flows.
F02K 9/42 - Moteurs-fusées, c.-à-d. ensembles fonctionnels portant à la fois le combustible et son oxydantLeur commande utilisant des propergols liquides ou gazeux
F02K 9/58 - Soupapes d'alimentation en combustible
F02K 9/80 - Moteurs-fusées, c.-à-d. ensembles fonctionnels portant à la fois le combustible et son oxydantLeur commande caractérisés par la commande de la poussée ou du vecteur poussée
Systems and methods for a fully reusable upper stage for a multi-stage launch vehicle are provided. The reusable upper stage uses an aerospike engine for main propulsion and for vertical landing. A heat shield can include a plurality of scarfed nozzles embedded radially around a semi-spherical surface of the heat shield, wherein inboard surfaces of the plurality of scarfed nozzles collectively define an aerospike contour. The heat shield can be actively cooled to dissipate heat encountered during reentry of the upper stage.
B64G 1/40 - Aménagements ou adaptations des systèmes de propulsion
B64G 1/62 - Systèmes de retour sur terreDispositifs de freinage ou d'atterrissage
B64G 1/64 - Systèmes pour réunir ou séparer des véhicules spatiaux ou des parties de ceux-ci, p. ex. aménagement pour l'accostage ou l'amarrage
F02K 9/42 - Moteurs-fusées, c.-à-d. ensembles fonctionnels portant à la fois le combustible et son oxydantLeur commande utilisant des propergols liquides ou gazeux
F02K 9/46 - Alimentation en propergols utilisant des pompes
F02K 9/88 - Moteurs-fusées, c.-à-d. ensembles fonctionnels portant à la fois le combustible et son oxydantLeur commande caractérisés par la commande de la poussée ou du vecteur poussée utilisant des tuyères de fusées auxiliaires
F02K 9/94 - Moteurs-fusées réallumables ou redémarrablesMoteurs-fusées fonctionnant d'une manière intermittente
Systems and methods for subscale testing of rocket engine injector stability. The system includes a combustion chamber with telescoping throat that is continuously axially moveable via an actuator. A modular injector plate comprises one or more first rocket engine injector elements configured to inject one or more propellants, such as a fuel and an oxidizer, into the chamber. The injector plate and/or the telescoping throat may be continuously translated, to thereby continuously vary a combustion volume of the chamber and create a dynamically tunable downstream boundary. The injectors are thus exposed to acoustic modes of varying frequency, covering the range of acoustic modes expected in a full scale rocket engine. The injector plate is removably attached to an upstream end of the chamber for replacement of the first injectors with different, second injectors for subsequent testing.
F02K 9/42 - Moteurs-fusées, c.-à-d. ensembles fonctionnels portant à la fois le combustible et son oxydantLeur commande utilisant des propergols liquides ou gazeux
F02K 9/64 - Chambres de combustion ou de poussée comportant des aménagements pour le refroidissement
F02K 9/86 - Moteurs-fusées, c.-à-d. ensembles fonctionnels portant à la fois le combustible et son oxydantLeur commande caractérisés par la commande de la poussée ou du vecteur poussée utilisant des tuyères à section réglable
F02K 9/96 - Moteurs-fusées, c.-à-d. ensembles fonctionnels portant à la fois le combustible et son oxydantLeur commande caractérisés par des aménagements spécialement conçus pour des tests ou des mesures
Systems and methods for subscale testing of rocket engine injector stability. The system includes a combustion chamber and a piston within the chamber that is continuously axially moveable via an actuator. An annular gap between the piston and a chamber sidewall provides a minimal cross-sectional flow area. A modular injector plate comprises one or more injector elements configured to inject a fuel and an oxidizer into the chamber. The piston is continuously translated, to thereby continuously vary a combustion volume of the chamber and to create a dynamically tunable downstream boundary. The injector elements are thus exposed to acoustic modes of varying frequency, covering the range of acoustic modes expected in a full scale rocket engine. The injector plate is removably attached to an upstream end of the chamber for replacement of the first injector elements with different, second injector elements for subsequent testing.
F02K 9/42 - Moteurs-fusées, c.-à-d. ensembles fonctionnels portant à la fois le combustible et son oxydantLeur commande utilisant des propergols liquides ou gazeux
F02K 9/64 - Chambres de combustion ou de poussée comportant des aménagements pour le refroidissement
F02K 9/86 - Moteurs-fusées, c.-à-d. ensembles fonctionnels portant à la fois le combustible et son oxydantLeur commande caractérisés par la commande de la poussée ou du vecteur poussée utilisant des tuyères à section réglable
F02K 9/96 - Moteurs-fusées, c.-à-d. ensembles fonctionnels portant à la fois le combustible et son oxydantLeur commande caractérisés par des aménagements spécialement conçus pour des tests ou des mesures
Methods and systems are presented for sintering a material, which may be in a granulated or powdered form, in a mold using microwave radiation. These methods and systems may lead to a sintered object that contracts (e.g., shrinks) away from sides of the mold so that it is able to be easily released from the mold. Accordingly, for example, sides of the mold need not be angled (e.g., with draft angles), which is generally done to molds to allow for the molded object to be releasable, such as by lifting or dumping out the molded part. A particular advantage of these methods and systems, besides not needing to distort a mold shape with draft angles, is that the contraction caused by microwave sintering may likely avoid chemical reactions or adhesion between the sides of the mold and the sintered object because the contraction causes a gap therebetween.
B22F 3/105 - Frittage seul en utilisant un courant électrique, un rayonnement laser ou un plasma
B22F 3/00 - Fabrication de pièces ou d'objets à partir de poudres métalliques, caractérisée par le mode de compactage ou de frittageAppareils spécialement adaptés à cet effet
B64G 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe
14.
Systems and methods for fluid barriers through permeable structures
Systems and methods are directed toward support structures for materials that include one or more flow passages to form a barrier between an inner wall of the support structures and the materials. The one or more flow passages may include ports or pores extending through a fluid-permeable material forming at least a portion of the support structure. A barrier fluid may be introduced at a first side of the inner wall and may be driven, such as using differential pressure, through the inner wall to from a barrier along a second side of the inner wall to reduce a likelihood of contact between the materials and the second side of the inner wall.
B65D 81/20 - Réceptacles, éléments d'emballage ou paquets pour contenus présentant des problèmes particuliers de stockage ou de transport ou adaptés pour servir à d'autres fins que l'emballage après avoir été vidés de leur contenu fournissant une ambiance spécifique pour le contenu, p. ex. température supérieure ou inférieure à la température ambiante sous vide ou pression superatmosphérique ou en atmosphère spéciale, p. ex. sous gaz inerte
B33Y 80/00 - Produits obtenus par fabrication additive
B65D 85/84 - Réceptacles, éléments d'emballage ou paquets spécialement adaptés à des objets ou à des matériaux particuliers pour produits chimiques corrosifs
A boiler system and methods of operating the system in a low-gravity environment are disclosed. The boiler system, which converts a cryogenic liquid to its gas phase, may be used in various types of space vehicles for various types of missions. The system principally operates using waste heat that is invariably produced during the many functions and processes that occur during space flight. The waste heat is collected and applied to a boiler tank in the system, where the cryogenic liquid is resultantly heated to a gas, which may be subsequently used or collected in one or more accumulator tanks, for example. Because waste heat is used in this liquid-to-gas conversion process, the boiler system consumes relatively low amounts of energy produced by, or stored in, a space vehicle.
Self-adaptive fabrics for space applications are provided. In one aspect, a fabric for use in space includes a structural fabric and a plurality of synthetic fibers woven into a self-adaptive fabric. The self-adaptive fabric is attached to the structural fabric. Each of the synthetic fibers includes a plurality of hollow cells containing a trapped gas. The synthetic fibers are formed of a material having a sufficient elasticity such that the diameter of each of the synthetic fibers is configured to increase when the environmental pressure decreases.
D03D 15/30 - Tissus caractérisés par la matière, la structure ou les propriétés des fibres, des filaments, des filés, des fils ou des autres éléments utilisés en chaîne ou en trame caractérisés par la structure des fibres ou des filaments
D03D 15/283 - Tissus caractérisés par la matière, la structure ou les propriétés des fibres, des filaments, des filés, des fils ou des autres éléments utilisés en chaîne ou en trame caractérisés par la matière des fibres ou des filaments formant les filés ou les fils à base de polymères synthétiques, p. ex. fibres polyamides ou fibres polyesters
D03D 15/56 - Tissus caractérisés par la matière, la structure ou les propriétés des fibres, des filaments, des filés, des fils ou des autres éléments utilisés en chaîne ou en trame caractérisés par les propriétés des filés ou des fils élastiques
17.
INDUCTION MELTING OF SILICON USING TANTALUM AS A HEAT-DELIVERY SEED
Methods and configurations for melting silicon by induction using tantalum as a heat-delivery seed are presented. The tantalum supports induction-generated electrical eddy currents and resultantly heats to relatively high temperatures. The heat of the tantalum then conducts into surrounding silicon, which melts. Because the tantalum does not melt at the relatively low melting temperature of silicon, the tantalum will not contaminate the molten silicon, which may thus have a high purity. The melted silicon may then be used in processes that form thin films on a substrate or ingots.
A linear actuator and a method of operating is provided. The linear actuator includes a housing having at least one wall made from an electrochromatic material configured to transform from an opaque to a translucent material in response to a voltage. A plunger is slidably coupled to the housing to move between a first position and a second position. An actuator is disposed between the plunger and the housing, the actuator being made from a heat sensitive material, the actuator being configured to change a length of the actuator in response to a change in temperature.
A method of additive manufacturing a structure having integrated passages is provided. In one aspect, the method includes forming first and second parts, each part having a near net shape. The first and second parts are formed by moving a friction stir tool configured to deposit a filler material. An inner surface of each part can be machined to form a generally smooth surface. The first and the second parts are joined to form a structure. The structure is machined to form a generally smooth outer surface. The method includes machining a plurality of grooves extending into the generally smooth outer surface of the structure. A tube is placed into each of the plurality of grooves and a layer of material is deposited to secure the tubes within the plurality of grooves. The method can include machining the outer surface to a predetermined shape.
B23K 20/12 - Soudage non électrique par percussion ou par une autre forme de pression, avec ou sans chauffage, p. ex. revêtement ou placage la chaleur étant produite par frictionSoudage par friction
A method and system for precipitating a solid using molten oxide electrolysis are presented. Using an electrical current for electrolysis in a first vessel, an oxide material is heated to form a liquid cathode. The first vessel also includes a corresponding anode. A portion of the liquid cathode is received into a second vessel that is separated from the first vessel by a conduit. The portion of the liquid cathode is allowed to cool. Precipitate of the cooled liquid cathode may then be collected in the second vessel. The precipitate may be a metal or metalloid, such as silicon. The method and system allow for continuous processing for production of a precipitate material, in contrast to batch processing of other methods or systems. For example, precipitate may be harvested from the second vessel while electrolysis is continuously performed in the first vessel.
A friction stir additive manufacturing device configured to join a first work-piece and a second work-piece is provided. In one aspect, the device includes a rotating spindle configured to deposit a filler material over a weld line as the device is advanced along an interface between the first work-piece and the second work-piece. The device also includes a deposition head configured to receive at least a portion of the spindle, the deposition head configured to remain stationary relative to the rotating spindle. The deposition head includes a first semi-cylindrical portion having an inner radius and an outer radius relative to a first axis, and a second semi-cylindrical portion having an inner radius and an outer radius relative to a second axis that is perpendicular to the first axis. The second semi-cylindrical portion can include a chamfered inner surface configured to define a weld profile.
B23K 20/12 - Soudage non électrique par percussion ou par une autre forme de pression, avec ou sans chauffage, p. ex. revêtement ou placage la chaleur étant produite par frictionSoudage par friction
B23K 103/20 - Alliages ferreux et aluminium ou ses alliages
22.
HATCH MECHANISM FOR SPACECRAFT, AND ASSOCIATED SYSTEMS AND METHODS
A representative hatch system can include a base portion surrounding an opening, a hatch portion movable relative to the base portion between a closed configuration and an open configuration, and a movement mechanism positioned to move the hatch portion relative to the base portion between the closed and open configurations. The movement mechanism can include four arms pivotably attached to the hatch portion and the base portion via four pivot axes. When the hatch portion is in the closed configuration, the axes can be coplanar. The axes can be spaced apart from a sealing plane between the hatch portion and the base portion. The arms can traverse a periphery of the hatch portion. A representative aerospace system can include a hatch system supported in a wall portion of an aerospace vehicle. The movement mechanism can keep the sealing surface of the hatch facing away from an interior of the vehicle.
E05D 15/04 - Suspensions pour battants avec bras fixés sur le battant pivotant autour d'un axe extérieur au battant
B64G 1/22 - Parties de véhicules spatiaux ou équipements spécialement destinés à être fixés dans ou sur ces véhicules
E05F 3/00 - Appareils de fermeture ou d'ouverture à dispositif de freinage, p. ex. ralentisseursStructure des dispositifs de freinage pneumatique ou à liquide
A method and system is presented for producing an extrusion of molten material that may be formed into an extended bead or filament. Among other possible applications, the extrusion of molten material may be used for constructing things, as in 3D printing or additive manufacturing, particularly if the extrusion is formed as an extended bead. In some implementations, the material may be lunar regolith that is melted by the system and extruded in a molten form, which subsequently cools to a solid on the surface(s) to which it is applied.
B05B 9/047 - Appareillages de pulvérisation pour débiter des liquides ou d'autres matériaux fluides, n'impliquant pas de mélange avec des gaz ou des vapeurs caractérisés par les moyens d'alimentation en liquide ou en autre matériau fluide comportant un réservoir sous pression ou compressibleAppareillages de pulvérisation pour débiter des liquides ou d'autres matériaux fluides, n'impliquant pas de mélange avec des gaz ou des vapeurs caractérisés par les moyens d'alimentation en liquide ou en autre matériau fluide comportant une pompe l'alimentation étant faite par un élément d'accompagnement placé dans le réservoir, p. ex. par une membrane ou un piston flottant
Accelerometer with Hall effect sensor. The accelerometer may have a rounded magnetic assembly with rounded flux concentrator, such as a C-shape or horseshoe. Opposing ends of the concentrator may each have a magnet and form a gap having a highly-concentrated, non-linear magnetic field. Opposing ends of the concentrator may have a reduced width, such as cone-shaped. A Hall sensor may be located within or near the gap. The sensor or magnet may be moveably supported by a spring. The sensor may move perpendicularly relative to a direction of the magnetic field lines. A second magnet may be included, for example adjacent the gap, to provide a second set of magnetic field lines with shallower gradient for lower sensitivity. Movement of the sensor within the two magnetic fields may provide multiple wide-ranging sensitivities, such as “X” V/g as well as X/500 mV/g or X/5,000 mV/g.
G01P 15/105 - Mesure de l'accélérationMesure de la décélérationMesure des chocs, c.-à-d. d'une variation brusque de l'accélération en ayant recours aux forces d'inertie avec conversion en valeurs électriques ou magnétiques au moyen de dispositifs sensibles aux champs magnétiques
G01R 33/07 - Mesure de la direction ou de l'intensité de champs magnétiques ou de flux magnétiques en utilisant des dispositifs galvano-magnétiques des dispositifs à effet Hall
A diffuser for separating a gas component and a liquid component of a liquid-gas mixture to reduce slosh in vehicle systems is described herein. The diffuser includes a wall with a gas end, a liquid end, and multiple vanes partially extending from the liquid side to the gas side. The vanes are spaced apart from each other by a given distance to permit the liquid to flow toward the liquid end via capillary action.
A slurry for use to form or repair a silicon carbide coating is provided. In one aspect, the slurry includes solid particles and a carbonaceous resin. The solid particles include silicon carbide particles, silicon particles, and carbon particles. A method of fabricating a silicon carbide coating is also provided. In one aspect, the method includes applying the slurry, heating the slurry, and forming the silicon carbide coating from the solid particles and the carbonaceous resin. A method of repairing a silicon carbide coating is also provided. In one aspect, the method includes applying the slurry to a damaged region of the silicon carbide coating, heating the slurry, and repairing the silicon carbide coating with the solid particles and the carbonaceous resin in the damaged region.
C04B 41/89 - Revêtement ou imprégnation pour obtenir au moins deux revêtements superposés de compositions différentes
C23C 24/10 - Revêtement à partir de poudres inorganiques en utilisant la chaleur ou une pression et la chaleur avec formation d'une phase liquide intermédiaire dans la couche
27.
DIRECT DRIVE WHEELS AND INTEGRATED THERMAL RADIATORS FOR A TERRAIN VEHICLE
Systems and methods for cooling an electric motor of a terrain vehicle are presented. In particular, embodiments are directed to cooling an electric drive stator and associated structures of an electric motor of a terrain vehicle. Configurations for such cooling may perform as a local heat radiator, thus avoiding a need for a system that includes pipes, circulating coolant, valves, and pumps for carrying heat to a central radiator. A cooling vessel is in thermal contact with a stator of a motor. The cooling vessel includes various features for dissipating heat collected from the stator or other parts of the motor.
H02K 1/20 - Parties fixes du circuit magnétique avec des canaux ou des conduits pour l'écoulement d'un agent de refroidissement
B60K 7/00 - Disposition du moteur dans ou jouxtant une roue motrice
H02K 21/14 - Moteurs synchrones à aimants permanentsGénératrices synchrones à aimants permanents avec des induits fixes et des aimants tournants avec des aimants tournant à l'intérieur des induits
28.
OPEN-CHANNEL SUPPORTED METAL-ORGANIC FRAMEWORK BASED GASEOUS CONTAMINANT REMOVAL
A system for regenerative carbon dioxide (CO2) removal in spacecraft cabin environmental conditions is described. Metal organic framework (MOF) adsorbents are integrated onto an oxide coated support material, such as a thin sheet or wire/wire mesh and implemented in an open-channel architecture. The support material may be titanium having an oxide surface layer that comprises titanium dioxide (TiO2) nanotubes. These structures provide a relatively large surface area for hosting MOF adsorbents. An integrated titanium support structure with MOFs may be more energy efficient and have greater flexibility in gas (e.g., air) flowrate as compared to traditional configurations of a packed bed reactor containing a pelletized form of adsorbent, such as zeolite.
B01J 20/22 - Compositions absorbantes ou adsorbantes solides ou compositions facilitant la filtrationAbsorbants ou adsorbants pour la chromatographieProcédés pour leur préparation, régénération ou réactivation contenant une substance organique
An improved current flowback prevention device that uses a Gallium Nitride (GaN) device or transistor to mitigate the effects of short circuits is described herein. For example, a GaN device may have an ideal diode-like behavior during reverse conduction. This characteristic of the GaN device can be used to protect electrical systems against short circuit incidents caused by upstream circuits or electronic components. As an illustrative example, a power regulator may be injecting current towards a direct current (DC) bus. While the power regulator is operating normally, the gate of the GaN device may be kept high to allow current to pass through the GaN device from the power regulator to the DC bus. If a short circuit event occurs, the gate of the GaN device may no longer receive a high signal and prevent current from passing through the GaN device.
H02H 3/16 - Circuits de protection de sécurité pour déconnexion automatique due directement à un changement indésirable des conditions électriques normales de travail avec ou sans reconnexion sensibles à un courant de défaut à la terre ou à la masse
H02H 1/00 - Détails de circuits de protection de sécurité
H02H 7/22 - Circuits de protection de sécurité spécialement adaptés aux machines ou aux appareils électriques de types particuliers ou pour la protection sectionnelle de systèmes de câble ou de ligne, et effectuant une commutation automatique dans le cas d'un changement indésirable des conditions normales de travail pour appareillage de distribution, p. ex. système de barre omnibusCircuits de protection de sécurité spécialement adaptés aux machines ou aux appareils électriques de types particuliers ou pour la protection sectionnelle de systèmes de câble ou de ligne, et effectuant une commutation automatique dans le cas d'un changement indésirable des conditions normales de travail pour dispositifs de commutation
Systems and methods herein are for a system-under-test (SUT). A library is provided with different invariants-as-code (InaC) source code which is to be complied for verifying the SUT. The different InaC source code includes different invariant features defined at least by respective preconditions and input conditions. The SUT is to perform test procedures executed within a test environment to provide differently formatted data, from which uniformly formatted time series data is generated. One or more compiled versions of the different InaC source code is executed with one or more parts of the uniformly formatted time series data to provide results of the SUT. The results of the SUT represent at least one invariant which is continuous over a state of the SUT.
Additive manufacturing devices with subtractive tools are provided. In one aspect, an additive manufacturing device includes a shoulder configured to rotate about a central axis, the shoulder including a central channel extending from a first end of the shoulder to a second end of the shoulder, the central channel configured to allow a filler material to pass through the shoulder from the first end towards the second end. The additive manufacturing device also includes a subtractive tool assembly including a subtractive tool and an insert sleeve. At least a portion of one or more cutting surfaces or edges of the subtractive tool extend outside the central channel of the shoulder when the subtractive tool is removably received in the insert sleeve and the insert sleeve is received in the central channel of the shoulder.
A recovery system for receiving rockets upon landing comprising a deceleration pool filled with liquid. The system may have a volume filled with the liquid having a desired density profile. An injection manifold injects gas into the liquid to create the density profile. The liquid may have a first density at a landing region of the pool and a second density greater than the first density away from the landing region, such as increasing in density radially outward from a center of the landing region. The pool may be located under a primary landing system intended to secure the landing rocket, such as a hook catch. The pool may be a contingency system for mitigating damage to a landing rocket that unsuccessfully attempts securing with the primary landing system.
Porous media and methods of manufacturing porous media, such as for use in aerospace parts, are described herein. In some embodiments, a porous medium comprises a monolithic structure having a plurality of vertically stacked metal layers. Individual ones of the metal layers can include an array of spaced apart weld beads, and the arrays of weld beads can be rotationally and/or laterally offset from one another. For example, the arrays of weld beads can be rotationally offset from another by an angle that is not a factor of 360 degrees. The weld beads can together define a plurality of non-discrete passageways extending through the monolithic structure.
B23K 26/064 - Mise en forme du faisceau laser, p. ex. à l’aide de masques ou de foyers multiples au moyen d'éléments optiques, p. ex. lentilles, miroirs ou prismes
B23K 26/34 - Soudage au laser pour des finalités autres que l’assemblage
A friction stir additive manufacturing system configured to extrude a material is provided. In one aspect, the system includes a spindle configured to rotate about a central axis, the spindle including a conical portion having a plurality of threads at a deposition end of the spindle. The system also includes a housing configured to remain stationary relative to the spindle, the housing including a wire inlet extending through a side wall of the housing, an interior surface of the side wall defining a truncated cone terminating at a material exit, the truncated cone configured to receive the conical portion of the spindle. The system also includes a feeding system configured to feed a wire through the wire inlet and into a gap between the spindle and the truncated cone of the housing.
B23K 20/12 - Soudage non électrique par percussion ou par une autre forme de pression, avec ou sans chauffage, p. ex. revêtement ou placage la chaleur étant produite par frictionSoudage par friction
B25J 9/02 - Manipulateurs à commande programmée caractérisés par le mouvement des bras, p. ex. du type à coordonnées cartésiennes
A friction stir additive welding screw is provided. In one aspect, the friction stir additive welding screw includes a first portion configured to be coupled to a friction stir additive welding device, and a second portion configured to penetrate a work-piece. The second portion includes a plurality of large threads, each large thread extending in a generally longitudinal direction. The second portion also includes a plurality of fine threads positioned along an edge of each large thread, and a plurality of teeth at a tip of second portion.
B23K 20/12 - Soudage non électrique par percussion ou par une autre forme de pression, avec ou sans chauffage, p. ex. revêtement ou placage la chaleur étant produite par frictionSoudage par friction
A representative tool system for polishing and/or finishing a surface can include an arbor portion and an interchangeable (i.e., modular) head portion. The arbor portion can include a body portion, one or more media collection elements, a rotation mechanism positioned to rotate the one or more media collection elements relative to the body portion, and one or more media distribution elements. The head portion can include a media distribution region for receiving a media distribution element, a media collection region for receiving a media collection element, and media channels connecting the media distribution region and the media collection region to one or more openings at the exterior perimeter of the head portion for passing the media to the exterior perimeter of the head portion. In some embodiments, the head portion can carry the one or more media collection elements.
A friction stir additive manufacturing system is provided. In one aspect, the system includes a spindle configured to rotate about a central axis, and a housing configured to receive at least a portion of the spindle, the housing configured to remain stationary relative to the spindle. The housing includes a wire inlet extending between an exterior surface of the housing and an interior surface of the housing, and a track extending from the wire inlet and partially around a circumference of an interior surface of the housing. The system also includes a feeding system configured to receive a wire from a roller and feed the wire through the wire inlet and into the track of the housing.
B23K 20/12 - Soudage non électrique par percussion ou par une autre forme de pression, avec ou sans chauffage, p. ex. revêtement ou placage la chaleur étant produite par frictionSoudage par friction
A friction stir additive welding device configured to join a first work-piece and second work-piece is provided. In one aspect, the device includes a nosecone having a sidewall extending from a first end to a second end, a channel extending from the first end to the second end along a longitudinal axis of the nosecone, and a screw positioned within the channel. The first end is configured to couple the nosecone to a robotic arm and the second end has a surface configured to be advanced along a weld line between the first and second work-pieces. A central axis of the screw defines an angle that is less than 90 degrees relative to a plane that is perpendicular to surfaces of the first and second work-pieces as the surface of the nosecone advances along the weld line.
B23K 20/12 - Soudage non électrique par percussion ou par une autre forme de pression, avec ou sans chauffage, p. ex. revêtement ou placage la chaleur étant produite par frictionSoudage par friction
39.
NOSECONES FOR FRICTION STIR ADDITIVE MANUFACTURING SYSTEMS, DEVICES, AND METHODS
A friction stir additive welding device configured to join a first work-piece and second work-piece is provided. In one aspect, the device includes a nosecone including a channel extending along a central axis and configured to receive a rotating screw. The device also includes a slot including a first opening in an outer sidewall of the nosecone, a second opening in a wall of the channel of the nosecone, and a passageway through the nosecone between the first opening and the second opening. The slot is configured to receive a portion of a structure positioned between the first work-piece and the second work-piece.
B23K 20/12 - Soudage non électrique par percussion ou par une autre forme de pression, avec ou sans chauffage, p. ex. revêtement ou placage la chaleur étant produite par frictionSoudage par friction
Systems and methods for aligning inertial measurement units (IMUs) with mounting structures. A system can include fiducials attachable to a fixture, a coordinate measuring machine (CMM) for measuring positions of the fiducials, inclinometers attachable to the fixture, and a rate table for receiving the fixture and posing the fixture with the inclinometers and/or the IMUs. A method can include determining a first rotation matrix between a coordinate frame associated with the fiducials and a reference coordinate frame, determining a second rotation matrix between the reference coordinate frame and a coordinate frame associated with a rate table, determining a third rotation matrix between the coordinate frame associated with the rate table and a coordinate frame associated with an IMU, and multiplying the three rotation matrices by data from an IMU. The reference coordinate frame can be a coordinate frame associated with the fixture or associated with one or more inclinometers.
G01C 25/00 - Fabrication, étalonnage, nettoyage ou réparation des instruments ou des dispositifs mentionnés dans les autres groupes de la présente sous-classe
G01C 9/02 - Mesure de l'inclinaison, p. ex. par clinomètres, par niveaux Détails
Systems and methods for photography of a spacecraft during space flight are provided. An autonomous deployable camera (ADC) may capture images and video of a portion of a rocket, such as a crew capsule, as it flies in space with the Earth's horizon in the background and astronauts within the crew capsule visible and recognizable through windows of the crew capsule. The ADC, being reusable, may land on the ground independent of landings or flight trajectories of the crew capsule or other parts of a rocket. The ADC may include a parachute to slow the descent of the ADC. The ADC may also include tracking hardware to allow the ADC to be relatively easily recovered on the ground. After recovery, images may be downloaded from the ADC.
F42B 15/08 - Projectiles autopropulsés, p. ex. roquettesMissiles pour le transport d'appareils de mesures
F42B 15/36 - Moyens de liaison entre le moteur-fusée et le corps d'une roquetteRaccords pour relier les différents étages d'une roquetteMoyens de désassemblage
F42B 30/00 - Projectiles non prévus ailleurs, caractérisés par la catégorie ou le type de munitions, p. ex. par le lanceur ou l'arme utilisés
H04N 23/698 - Commande des caméras ou des modules de caméras pour obtenir un champ de vision élargi, p. ex. pour la capture d'images panoramiques
42.
REDUCTION OF ASYMMETRICAL LOADING IN PARACHUTE INFLATION
Systems and methods for a parachute or parachute system are described. The parachute or parachute system includes two or more panels and includes at least one band which may be in a lateral direction relative to the two or more panels. The at least one band may be secured at different points which are lateral mid-points in individual contiguous ones of the two or more panels. Further, a first distance between an individual set of points of the different points may be shorter than twice a second distance. The second distance is a lateral distance from at least one point of the individual set of points to a seam of one panel of the two or more panels having the at least one point.
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
Rocket engines for aerospace vehicles. Technical and scientific consulting, research and
development, engineering, design, and prototyping in the
field of aerospace and aerospace-related advance
technologies; computer software design and development
services in the field of engineering, design, and modeling
of aerospace and aerospace-related advanced technologies;
technical and scientific consulting, research and
development, engineering, design, and prototyping in the
fields of astronomy, space and outer space exploration,
flight simulation, and aerospace vehicles, namely, launch
vehicles, spacecraft and rockets.
44.
COMBINATION CONTINUOUS WAVE AND PULSED LASER ADDITIVE MANUFACTURING SYSTEM AND RELATED METHODS
Additive manufacturing systems and associated methods are disclosed herein. In some embodiments, the additive manufacturing system includes a build chamber that has an active build region, an energy beam system positioned to direct energy beams toward the active build area, and a controller operably coupled to the energy beam system. During an additive manufacturing process, the controller can control the energy beam system to execute a hybrid sintering process. For example, for a first region of a planned build object, the controller can operate the energy beam system in a continuous wave mode to generate a first energy beam to sinter powder in the first region. Then, for a second region, the controller can operate the energy beam system in a pulsed mode to generate a second energy beam with to sinter the second region.
B22F 10/366 - Paramètres de balayage, p. ex. distance d’éclosion ou stratégie de balayage
B22F 10/25 - Dépôt direct de particules métalliques, p. ex. dépôt direct de métal [DMD] ou mise en forme par laser [LENS]
B23K 26/06 - Mise en forme du faisceau laser, p. ex. à l’aide de masques ou de foyers multiples
B23K 26/0622 - Mise en forme du faisceau laser, p. ex. à l’aide de masques ou de foyers multiples par commande directe du faisceau laser par impulsions de mise en forme
Stacked satellite dispensing systems are described herein. The disclosed systems can release individual satellites or small batches of satellites from a satellite stack in a controlled manner. Dispensing individual satellites at different locations in space can more evenly dispense satellites or to dispense satellites at distinct locations. A deployment system, including a motor, a cable, and spacers, can allow for the individual satellites to be deployed from the satellite stack. The disclosed satellite dispensing systems also include spacers that are positioned between two or more satellites to help attenuate the force of the mass of satellites stacked above.
Methods for a reusable space vehicle to land at substantially the same location as its launching site. The vehicle traveling in a particular orbit, which is a repeating ground track orbit, allows for launching and landing at the same location once per day. The repeating ground track orbits that allow for launching and landing at the same location once per day overfly the launch and landing site once per day. Launching and landing at the same site provides a number of direct advantages. For example, the just-landed vehicle may be transported a relatively short distance to the launch site, reconditioned relatively quickly, and be ready for a quick turn-around launch.
Transpiration-cooled systems having permeable and non-permeable portions are provided. In one aspect, a nozzle for a rocket engine includes a non-permeable outer layer, a plurality of walls, a permeable layer, and a plurality of cooling channels. The non-permeable outer layer forms a predetermined shape of the nozzle and defines an interior space. The plurality of walls extend generally orthogonal to the non-permeable outer layer and into the interior space. The permeable layer is disposed between each set of adjacent walls of the plurality of walls. The permeable layer is spaced a distance from the non-permeable outer layer. The plurality of cooling channels are formed between the permeable layer, the non-permeable outer layer, and a set of adjacent walls of the plurality of walls. The plurality of cooling channels are configured to transport a fluid.
A method of additive manufacturing a structure having integrated passages is provided. In one aspect, the method includes forming first and second parts, each part having a near net shape. The first and second parts are formed by moving a friction stir tool configured to deposit a filler material. An inner surface of each part can be machined to form a generally smooth surface. The first and the second parts are joined to form a structure. The structure is machined to form a generally smooth outer surface. The method includes machining a plurality of grooves extending into the generally smooth outer surface of the structure. A tube is placed into each of the plurality of grooves and a layer of material is deposited to secure the tubes within the plurality of grooves. The method can include machining the outer surface to a predetermined shape.
B23K 20/12 - Soudage non électrique par percussion ou par une autre forme de pression, avec ou sans chauffage, p. ex. revêtement ou placage la chaleur étant produite par frictionSoudage par friction
A kit for manufacturing a structure in space is provided. In one aspect, the kit includes an inflatable bladder having an internal wall configured to define an internal space of the structure when the bladder is inflated. The kit also includes a structural liner coupled to the internal wall of the inflatable bladder. The kit also includes one or more e-beam physical vapor deposition systems configured to be positioned within the internal space of the structure when the bladder is inflated. The one or more e-beam physical vapor deposition systems configured to form a metallic structural shell on the structural liner.
A system performs automatic cleaning of a membrane module that is used in a water treatment unit to remove impurities from water. The water treatment unit is part of a water purification system that also includes a membrane cleaning unit that is located remotely from the water treatment unit. While both are part of a water purification system, a membrane cleaning unit may be physically separated from a water treatment unit. Such separation of positioning and functionality may allow for parallel operations of water purification and membrane module cleaning.
B01D 41/00 - Régénération, à l'extérieur du filtre, de la substance filtrante ou des éléments filtrants utilisés dans la filtration des fluides liquides ou gazeux
51.
SYSTEMS, DEVICES, AND METHODS FOR SURFACE PREPARATION FOR BOND ENHANCEMENT IN ADDITIVE DEPOSITION PROCESSES
An additive friction stir deposition device is provided. In one aspect, the device includes a shoulder configured to rotate about a central axis. The shoulder includes a channel extending from a first end of the shoulder to a second end of the shoulder. The channel allows a filler material to pass through the shoulder from the first end towards the second end. The shoulder configured to deposit the filler material as the device is advanced along a deposition surface. The device also includes a wire brush skirt configured to co-rotate with the shoulder and contact the deposition surface as the device is advanced along the deposition surface. The device also includes a gas shroud configured to direct pressurized gas toward the deposition surface and remove contaminants as the device is advanced along the deposition surface.
B23K 20/12 - Soudage non électrique par percussion ou par une autre forme de pression, avec ou sans chauffage, p. ex. revêtement ou placage la chaleur étant produite par frictionSoudage par friction
B23K 20/14 - Dispositions pour empêcher ou réduire l'accès des gaz, ou utilisation de gaz protecteurs ou du vide pendant le soudage
A method of joining a first work-piece to a second work-piece is provided. Each of the first work-piece and the second work-piece include a top surface, an opposed bottom surface, and a side surface connecting the top surface and the opposed bottom surface. In one aspect, the method includes positioning the side surface of the first work-piece adjacent to the side surface of the second work-piece, and advancing a friction stir additive manufacturing tool across the top surface of the first work-piece and the top surface of the second work-piece along a weld line between the first work-piece and the second work-piece. As the friction stir additive manufacturing tool advances along the weld line, a filler material is deposited along the weld line and into a plurality of through holes formed in either or both of the first work-piece and the second work-piece. Each of the plurality of through holes includes a first opening on the top surface, a second opening on the opposed bottom surface, and a passageway through the work-piece between the first opening and the second opening. The method further includes joining the first work-piece and the second work-piece together.
B23K 20/12 - Soudage non électrique par percussion ou par une autre forme de pression, avec ou sans chauffage, p. ex. revêtement ou placage la chaleur étant produite par frictionSoudage par friction
53.
VIBRATING MECHANISM FOR CONTROLLING POWDER DISPENSING IN ADDITIVE MANUFACTURING SYSTEMS, AND RELATED SYSTEMS AND METHODS
Additive manufacturing systems and associated methods are disclosed herein. In some embodiments, the additive manufacturing system includes a build chamber that has an active build region, a support platform positioned in the active build region and movable in an upward direction, and a recoater arm positioned in the build chamber and movable in a first lateral direction above the active build region. The recoater arm can spread a powder over the active build region during a build process using first and second blades. The recoater arm can also include at least one orifice component positioned between the first and second blades to block a flow of the powder while the at least one orifice component is stationary and a vibrational component operably coupled to the at least one orifice component. The additive manufacturing system can also include a controller operably coupled to the vibrational component, to control operation of the vibrational component.
Additive manufacturing systems and associated methods are disclosed herein. In some embodiments, the additive manufacturing system includes a build chamber that has active build region, a support platform positioned in the active build region, a recoater arm, and a chamber-purging system. The recoater arm is movable in a lateral direction along a travel path above the active build region to spread a powder over the active build region. The chamber-purging system includes extendable input and return channels that are movable between a first position outside the travel path and a second position at least partially within the travel path.
Techniques and materials provide for thermal insulation for tanks, such as tanks for use in space flight missions. Microporous glass blocks may be used as an insulative bridge between spray-on foam insulation and a stainless steel wall of a tank, for example. Blocks of microporous glass may be mechanically attached to the interior of the tank, after which spray-on foam insulation is applied directly to the blocks. The bridging insulation provided by the microporous glass blocks allows the temperature of the stainless steel tank wall to exceed the usable temperature of the spray-on foam insulation by preventing a substantial portion of heat of the stainless steel wall from reaching the spray-on foam insulation. An insulated tank may instead comprise a tank wall that is a honeycomb-structured composite layer including an exterior skin, an interior skin, and a core that presents a relatively long thermal path, for improved thermal insulation.
Techniques and materials provide for thermal insulation for tanks, such as tanks for use in space flight missions. Microporous glass blocks may be used as an insulative bridge between spray-on foam insulation and a stainless steel wall of a tank, for example. Blocks of microporous glass may be mechanically attached to the interior of the tank, after which spray-on foam insulation is applied directly to the blocks. The bridging insulation provided by the microporous glass blocks allows the temperature of the stainless steel tank wall to exceed the usable temperature of the spray-on foam insulation by preventing a substantial portion of heat of the stainless steel wall from reaching the spray-on foam insulation. An insulated tank may instead comprise a tank wall that is a sandwich-structured composite layer including an exterior skin, an interior skin, and a core that presents a relatively long thermal path, for improved thermal insulation.
Additive manufacturing systems and associated methods are disclosed herein. In some embodiments, the additive manufacturing includes a build chamber that has a central portion and a peripheral portion, a support platform positioned in the central portion and a recoater arm movable in a lateral direction over the support platform. While moving, the recoater arm spreads a powder over the central portion during a build. The additive manufacturing system also includes a powder recycling system positioned to redirect excess amounts of the powder during the build. For example, the powder recycling system can include a powder receptacle positioned the second region of the peripheral portion and a recycling element positioned at least partially in the powder receptacle. The recycling element is movable between a first position abutting an overflow space in the powder receptacle to receive the excess powder and a second position closer to the central portion.
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
Systems and methods for securing an upright rocket. The rocket may be on a moveable platform, such as a landing area of a ship. The rocket may land on the deck, and the system may include cables that surround the landing area. The cables may be tightened about the rocket after the rocket has landed in an upright position. The system may include poles that telescope upward, such that the cables may tighten about the upright rocket at various heights along the body of the rocket.
Systems and methods are provided for wirelessly transferring power to a multi-junction photovoltaic cell of a space apparatus via a light emission system. The light emission system uses multiple lasers emitting different wavelengths and/or photon energies to produce electron-hole pairs in each layer of the multi-junction photovoltaic cell to prompt power generation by the multi-junction photovoltaic cell. The light emission system may be located on Earth or on another space apparatus. The multi-junction photovoltaic cell can convert sunlight and the light emitted by the light emission system into electrical energy.
H02J 50/30 - Circuits ou systèmes pour l'alimentation ou la distribution sans fil d'énergie électrique utilisant de la lumière, p. ex. des lasers
B64U 50/31 - Alimentation en énergie électrique ou distribution de celle-ci générée par des panneaux photovoltaïques
H01L 31/047 - Matrices de cellules PV incluant des cellules PV comportant plusieurs jonctions verticales ou plusieurs jonctions en forme de tranchées en V formées dans un substrat semi-conducteur
H01L 31/05 - Moyens d’interconnexion électrique entre les cellules PV à l’intérieur du module PV, p.ex. connexion en série de cellules PV
H01L 31/055 - Dispositifs à semi-conducteurs sensibles aux rayons infrarouges, à la lumière, au rayonnement électromagnétique d'ondes plus courtes, ou au rayonnement corpusculaire, et spécialement adaptés, soit comme convertisseurs de l'énergie dudit rayonnement e; Procédés ou appareils spécialement adaptés à la fabrication ou au traitement de ces dispositifs ou de leurs parties constitutives; Leurs détails adaptés comme dispositifs de conversion photovoltaïque [PV] Éléments optiques directement associés ou intégrés à la cellule PV, p.ex. moyens réflecteurs ou concentrateurs de lumière où la lumière est absorbée et réémise avec une longueur d’onde différente par l’élément optique directement associé ou intégré à la cellule PV, p.ex. en utilisant un matériau luminescent, des concentrateurs fluorescents ou des dispositions de convers
H01L 31/0725 - Cellules solaires à jonctions multiples ou dites "tandem"
60.
HEATING AND DEPOSITION FOR BENEFICIATION OF LUNAR REGOLITH
Methods and configurations for solar heating and beneficiation of a material, such as raw mine-extracted material like lunar rocks or regolith, are presented. Beneficiation may have an end-goal of purifying the material and/or removing particular impurities or undesired substances from the material. For example, purification or elimination of particular substances from a bulk material may be achieved by vaporizing, via solar or electron beam heating, a portion of the bulk material that does not include the particular substances. The bulk material, sans the particular substances, may be subsequently condensed onto a cold substrate as a thin film, which itself may be placed in a subsequent beneficiation iteration for further elimination of selected substances.
A heat exchanger system, in particular a vacuum spray boiler, cools a hot fluid by spraying a coolant onto chambers carrying the hot fluid. This process may be performed in i) a vacuum, as in space, ii) atmospheric pressure, as on a launch pad of a space vehicle, or iii) any pressure therebetween. The heat exchanger system may incorporate a plate-fin heat exchanger. A coolant spray apparatus, used for spraying the coolant, and the heat exchanger are integrated within a vacuum chamber. The coolant, subsequent to changing to a vapor state after being sprayed onto the heat exchanger, may be exhausted to outside the system.
F28D 5/02 - Appareils échangeurs de chaleur comportant des ensembles de canalisations fixes pour une seule des sources de potentiel calorifique, les deux sources étant en contact chacune avec un côté de la paroi de la canalisation, utilisant l'effet réfrigérant de l'évaporation naturelle ou forcée dans lesquels la source de potentiel calorifique soumise à évaporation s'écoule sous forme de pellicule continue ou ruisselle librement sur les canalisations
Systems, a device, and methods of operating the device are disclosed. The device acquires cryogenic liquid in a tank in low-gravity and provides the liquid to an end user, such as a rocket engine. The device helps reduce vortex flows that tend to occur in tanks. The device, the liquid therein, and liquid in the tank may be cooled by a fluid flow from a thermodynamic vent or cryocooler. Such cooling may resultantly reduce pressure in the tank. Thus, the device may provide tank pressure control in space vehicles with cryogenic propellant. The device may have an annular shape that allows flow to a main tank output port to be substantially uninterrupted so as to have a relatively low pressure drop.
Techniques and systems are used to fabricate a thermal protection systems (TPS) for placement on various parts of a structure, such as a spacecraft. The TPS may comprise syntactic foam as a spray-on foam insulation (SOFI), which may be sprayed onto a surface. Alternatively, the TPS may comprise syntactic foam that is applied as preformed panels that are adhered or mechanically attached to a surface. Performance of a syntactic foam may be improved by including an aluminosilicate nanotube material, such as halloysite nanotubes, in a matrix material. The halloysite nanotubes may be hydrated and treated with a silane couplant before being mixed into the matrix material, which may be a two-part silicone based syntactic insulator material, for example. The halloysite nanotubes, in addition to acting as a filler and reinforcement for the syntactic insulator material, release water during oblation, thus contributing to the effectiveness of a TPS.
B64G 1/58 - Protection thermique, p. ex. boucliers thermiques
C08J 9/00 - Mise en œuvre de substances macromoléculaires pour produire des matériaux ou objets poreux ou alvéolairesLeur post-traitement
C08J 9/32 - Mise en œuvre de substances macromoléculaires pour produire des matériaux ou objets poreux ou alvéolairesLeur post-traitement à partir de compositions contenant des microbilles, p. ex. mousses syntactiques
Systems and methods for pointing photovoltaic arrays for optimal power generation. One or more methods among a plurality of methods for pointing an array may be used by a spacecraft control system to point the array. Example methods to use to point the photovoltaic array relate to analyzing current output, analyzing image data, and analyzing computational knowledge of reflective bodies or light sources. The spacecraft may be further controlled to reduce shadow by re-orienting, receiving light reflected off spacecraft, and orienting a photovoltaic array relative to incoming light sources based on topographic properties of the array such as cell grooves.
B64G 1/36 - Appareils de guidage ou de commande, p. ex. de commande d'assiette par des capteurs, p. ex. par des capteurs solaires, des capteurs d'horizon
B64G 1/44 - Aménagements ou adaptations des systèmes fournissant l'énergie utilisant des radiations, p. ex. panneaux solaires déployables
G01J 1/42 - Photométrie, p. ex. posemètres photographiques en utilisant des détecteurs électriques de radiations
G01S 3/786 - Systèmes pour déterminer une direction ou une déviation par rapport à une direction prédéterminée utilisant le réglage d'une orientation des caractéristiques de directivité d'un détecteur ou d'un système de détecteurs afin d'obtenir une valeur désirée du signal provenant de ce détecteur ou de ce système de détecteurs la valeur désirée étant maintenue automatiquement
H02S 20/32 - Structures de support mobiles ou réglables, p. ex. pour réglage de l’angle spécialement adaptées pour le suivi du soleil
65.
Nuclear thermal propulsion system with reactor direct drive of cryocooler turbine
Systems and methods for nuclear reactor direct drive of a cryocooler turbine. A nuclear thermal propulsion (NTP) system may have a nuclear reactor that heats a thermal working fluid for directly driving the turbine to power a cryogenic fluid management (CFM) system for keeping propellant at cryogenic temperatures. The features may be used on NTP rockets. The propellant may be liquid hydrogen.
B64G 1/40 - Aménagements ou adaptations des systèmes de propulsion
F02K 9/42 - Moteurs-fusées, c.-à-d. ensembles fonctionnels portant à la fois le combustible et son oxydantLeur commande utilisant des propergols liquides ou gazeux
A vehicle is described herein that is capable of operating in space. The vehicle comprises a memory that stores computer-executable instructions. The vehicle further comprises a processor in communication with the memory, wherein the computer-executable instructions, when executed by the processor, cause the processor to: derive an equation of motion for the vehicle; determine an initial guess of a first value of a costate of the vehicle; determine the first value of the costate for a minimum propellant transfer in averaged orbit dynamics using the equation of motion, the initial guess, and a single shooting technique; determine a second value of the costate for the minimum propellant transfer in full-state orbit dynamics using the first value of the costate and the single shooting technique; and adjust a path of the vehicle to cause the vehicle to travel along an optimal transfer in full-state orbit dynamics.
Techniques and systems involve a magnetically enhanced cryogenic boiler that produces, without requiring pumps, high pressure gaseous oxygen from liquid oxygen for use in a spacecraft or other applications. The boiler heats, using a heat exchanger element, a closed container of liquid oxygen to boil the liquid oxygen at constant volume and increasing the pressure in the container. When a desired target pressure is reached, the boiler may release and transfer the high pressure fluid into a gaseous oxygen accumulator for storage. Magnets may be used to draw low pressure liquid oxygen into the boiler and to keep the liquid oxygen on or near one or more heat exchanger elements in the boiler, by exploiting paramagnetism of oxygen. The magnets produce a magnetic field that maintains relatively strong thermal contact between the heat exchanger elements and the liquid oxygen, even in the absence of gravity.
F28D 1/02 - Appareils échangeurs de chaleur comportant des ensembles de canalisations fixes pour une seule des sources de potentiel calorifique, les deux sources étant en contact chacune avec un côté de la paroi de la canalisation, dans lesquels l'autre source de potentiel calorifique est une grande masse de fluide, p. ex. radiateurs domestiques ou de moteur de voiture avec des canalisations d'échange de chaleur immergées dans la masse du fluide
F17C 7/04 - Vidage des gaz liquéfiés avec changement d'état, p. ex. vaporisation
F28F 27/02 - Commandes ou dispositifs de sécurité spécialement adaptés pour les appareils d'échange ou de transfert de chaleur pour commander la répartition des sources de potentiel calorifique entre des canaux différents
68.
SYSTEMS AND METHODS FOR LOW-THRUST PROPULSION TRAJECTORY OPTIMIZATION USING A MINIMUM TIME TRANSFER
A terrestrial-based system for is described herein that can determine a minimum time transfer for an extraterrestrial vehicle. The terrestrial-based system comprises a memory that stores computer-executable instructions. The terrestrial-based system further comprises a processor in communication with the memory, wherein the computer-executable instructions, when executed by the processor, cause the processor to: derive an averaged equation of motion for the extraterrestrial vehicle; determine an initial guess of a first value of a costate of the extraterrestrial vehicle; determine the first value of the costate for the minimum time transfer in averaged orbit dynamics; determine a second value of the costate for the minimum time transfer in full-state orbit dynamics; generate instructions for causing the extraterrestrial vehicle to travel along an optimal transfer in full-state orbit dynamics; and cause the extraterrestrial vehicle to adjust trajectory based on the generated instructions.
A terrestrial-based system for is described herein that can determine a minimum propellant transfer for an extraterrestrial vehicle. The terrestrial-based system comprises a memory that stores computer-executable instructions. The terrestrial-based system further comprises a processor in communication with the memory, wherein the computer-executable instructions, when executed by the processor, cause the processor to: derive an averaged equation of motion for the extraterrestrial vehicle; determine an initial guess of a first value of a costate of the extraterrestrial vehicle; determine the first value of the costate for the minimum propellant transfer in averaged orbit dynamics; determine a second value of the costate for the minimum propellant transfer in full-state orbit dynamics; generate instructions for causing the extraterrestrial vehicle to travel along an optimal transfer in full-state orbit dynamics; and cause the extraterrestrial vehicle to adjust trajectory based on the generated instructions.
A vehicle is described herein that is capable of operating in space. The vehicle comprises a memory that stores computer-executable instructions. The vehicle further comprises a processor in communication with the memory, wherein the computer-executable instructions, when executed by the processor, cause the processor to: derive an equation of motion for the vehicle; determine an initial guess of a first value of a costate of the vehicle; determine the first value of the costate for a minimum time transfer in averaged orbit dynamics using the equation of motion, the initial guess, and a single shooting technique; determine a second value of the costate for the minimum time transfer in full-state orbit dynamics using the first value of the costate and the single shooting technique; and adjust a path of the vehicle to cause the vehicle to travel along an optimal transfer in full-state orbit dynamics.
The present invention relates to battery immersion cooling of battery cells through vaporization of a dielectric liquid, such as through nucleate boiling. The boiling point of the liquid can be adjusted through control of the pressure to which the dielectric liquid is exposed. The quantity of liquid dielectric material is selected to adsorb the complete reaction energy of the electrical parallel cells in case of thermal runaway, leading to no propagation, flame or explosion.
Apparatus for mitigating propagation of thermal events between battery cells within a battery module assembly (10) is provided. The apparatus comprises one or more of several features that function to prevent a runaway thermal event within one battery cell (48) from triggering a fire or other thermal event within another battery cell within the battery module assembly (10). The apparatus may comprise one or more of: (i) a compressive wrap (88) applied to a battery cell (48); (ii) a layered barrier material (104) positioned between adjacent battery cells (48); (iii) silicone rubber supports (94) positioned adjacent the battery terminals (62. 64), (iv) a light-weight, fire-resistant housing composite panel, and (v) rupturable diaphragms (36) configured to vent gases and ejecta from a battery cell undergoing a thermal event.
H01M 10/0525 - Batteries du type "rocking chair" ou "fauteuil à bascule", p. ex. batteries à insertion ou intercalation de lithium dans les deux électrodesBatteries à l'ion lithium
H01M 10/647 - Éléments prismatiques ou plans, p. ex. éléments de type poche
H01M 10/653 - Moyens de commande de la température associés de façon structurelle avec les éléments caractérisés par des matériaux électriquement isolants ou thermiquement conducteurs
H01M 10/658 - Moyens de commande de la température associés de façon structurelle avec les éléments par isolation ou protection thermique
H01M 50/178 - Dispositions pour introduire des connecteurs électriques dans ou à travers des boîtiers adaptées à la forme des cellules pour des cellules en forme de poches ou de sacs souples
H01M 50/209 - Bâtis, modules ou blocs de multiples batteries ou de multiples cellules caractérisés par leur forme adaptés aux cellules prismatiques ou rectangulaires
H01M 50/211 - Bâtis, modules ou blocs de multiples batteries ou de multiples cellules caractérisés par leur forme adaptés aux cellules en forme de poche
H01M 50/229 - Matériau composite constitué d'un mélange de matériaux organiques et inorganiques
H01M 50/231 - MonturesBoîtiers secondaires ou cadresBâtis, modules ou blocsDispositifs de suspensionAmortisseursDispositifs de transport ou de manutentionSupports caractérisés par le matériau des boîtiers ou des bâtis ayant une structure en couches
H01M 50/293 - MonturesBoîtiers secondaires ou cadresBâtis, modules ou blocsDispositifs de suspensionAmortisseursDispositifs de transport ou de manutentionSupports caractérisés par des éléments d’espacement ou des moyens de positionnement dans les racks, les cadres ou les blocs caractérisés par le matériau
H01M 50/358 - Passages externes d’évacuation des gaz sur le couvercle ou sur le boîtier de batterie
H01M 50/367 - Passages internes d’évacuation des gaz dans le couvercle ou le boîtier de la batterieSystèmes d’évent à double couvercle
H01M 50/503 - Interconnecteurs pour connecter les bornes des batteries adjacentesInterconnecteurs pour connecter les cellules en dehors d'un boîtier de batterie caractérisées par la forme des interconnecteurs
H01M 50/507 - Interconnecteurs pour connecter les bornes des batteries adjacentesInterconnecteurs pour connecter les cellules en dehors d'un boîtier de batterie comprenant un arrangement de plusieurs barres omnibus réunies dans une structure de conteneur, p. ex. modules de barres omnibus
H01M 50/548 - Bornes caractérisées par la position des terminaux sur les cellules sur des côtés opposés de la cellule
H01M 50/55 - Bornes caractérisées par la position des terminaux sur les cellules sur le même côté de la cellule
H01M 50/553 - Bornes spécialement adaptées aux cellules prismatiques, de type poche ou rectangulaires
73.
VOLTAGE-CURRENT PHASE-BASED METHOD FOR LINEAR AND ROTARY TRANSFORMER SYSTEMS, AND ASSOCIATED SYSTEMS AND METHODS
A representative phase-shift based method for using a transformer system to detect movement of an object, and associated systems and methods are disclosed. A representative transformer system detects movement of an object and includes an excitation coil configured to receive an excitation coil input signal that results from an input sinusoidal signal. The transformer further includes first and second sensing coils, and a core configured to be operatively coupled to the object. The core moves relative to the first and second sensing coils when the object moves. First and second impedance loads are connected to the first and second sensing coils, respectively. The two impedance loads have different phase-shifting characteristics. A phase-shift sensing circuit determines a phase-shift between the excitation coil input signal and the input sinusoidal signal that is correlated with a position of the core relative to the first and second sensing coils.
G01D 5/20 - Moyens mécaniques pour le transfert de la grandeur de sortie d'un organe sensibleMoyens 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 déterminéTransducteurs 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
H01F 21/06 - Inductances ou transformateurs variables du type pour signaux continûment variables, p. ex. variomètres par déplacement du noyau ou d'une partie du noyau par rapport à l'enroulement ou aux enroulements dans l'ensemble
A method of additive manufacturing a structure having integrated passages is provided. In one aspect, the method includes forming first and second parts, each part having a near net shape. The first and second parts are formed by moving a friction stir tool configured to deposit a filler material. An inner surface of each part can be machined to form a generally smooth surface. The first and the second parts are joined to form a structure. The structure is machined to form a generally smooth outer surface. The method includes machining a plurality of grooves extending into the generally smooth outer surface of the structure. A tube is placed into each of the plurality of grooves and a layer of material is deposited to secure the tubes within the plurality of grooves. The method can include machining the outer surface to a predetermined shape.
B23K 20/00 - Soudage non électrique par percussion ou par une autre forme de pression, avec ou sans chauffage, p. ex. revêtement ou placage
B23K 20/12 - Soudage non électrique par percussion ou par une autre forme de pression, avec ou sans chauffage, p. ex. revêtement ou placage la chaleur étant produite par frictionSoudage par friction
A method of additive manufacturing a part having integrated passages is provided. In one aspect, the method includes forming a part having a near net shape by moving a friction stir tool to deposit a filler material in a predetermined formation. The tool can include a rotating spindle having a channel configured to hold the filler material. The method can include machining the near net shape part to form a plurality of grooves extending into a surface of the part, the plurality of grooves sized and shaped to each receive a tube. The method can include placing a tube into each of the plurality of grooves and moving the tool across the surface of the part and depositing additional material configured to secure the tubes within the plurality of grooves. The method can include machining the additional material deposited over the tubes to a predetermined shape.
B23K 20/12 - Soudage non électrique par percussion ou par une autre forme de pression, avec ou sans chauffage, p. ex. revêtement ou placage la chaleur étant produite par frictionSoudage par friction
Transpiration-cooled systems having permeable and non-permeable portions are provided. In one aspect, a nozzle for a rocket engine includes a non-permeable outer layer, a plurality of walls, a permeable layer, and a plurality of cooling channels. The non-permeable outer layer forms a predetermined shape of the nozzle and defines an interior space. The plurality of walls extend generally orthogonal to the non-permeable outer layer and into the interior space. The permeable layer is disposed between each set of adjacent walls of the plurality of walls. The permeable layer is spaced a distance from the non-permeable outer layer. The plurality of cooling channels are formed between the permeable layer, the non-permeable outer layer, and a set of adjacent walls of the plurality of walls. The plurality of cooling channels are configured to transport a fluid.
Drill jigs for positioning mounting holes using metrology processes, and associated systems and methods, disclosed. A representative drill jig system for positioning holes to be made in an object can include a drill jig having a plurality of movable plates. The plates can include: a rotatable plate carrying a hole pattern for positioning the holes to be made; a first translatable plate that is translatable along a first axis; a second translatable plate that is translatable along a second axis that is perpendicular to the first axis; and a base plate carrying one or more attachment elements positioned and configured to grasp the object. In some embodiments, the plates are manually movable via one or more adjusters. In some embodiments, the drill jig includes one or more servos for moving one or more of the plates under computer control, such as in a feedback loop using one or more encoders.
B23B 35/00 - Méthodes d'alésage ou de perçage ou autres méthodes de travail impliquant l'utilisation de machines à aléser ou à percerUtilisation d'équipements auxiliaires en relation avec ces méthodes
78.
Rocket thrust structure assembly, and associated systems and methods
Aerospace systems, and systems and methods for assembling an aerospace system or another system or structure, are disclosed. A representative system can include a propellant tank with a dome-shaped head; attachment features on the dome-shaped head; and a thrust structure with legs attached to the attachment features. A representative method can include forming shims to be positioned between the legs and the attachment features. The shims can be formed based on digital characterizations of mounting faces on the attachment features within a reference coordinate system. The method can include positioning a drill jig within the reference coordinate system and using the drill jig to make holes in the shims and/or the attachment features for fastening the legs to the attachment features. A drill jig can include plates that are movable relative to each other. At least one of the plates can include a mounting hole pattern.
B64G 1/40 - Aménagements ou adaptations des systèmes de propulsion
B64F 5/00 - Tracé, fabrication, assemblage, nettoyage, entretien ou réparation des aéronefs, non prévus ailleursManipulation, transport, test ou inspection de composants d’aéronefs, non prévus ailleurs
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p. ex. gabarits à cet effet
G05B 19/418 - Commande totale d'usine, c.-à-d. commande centralisée de plusieurs machines, p. ex. commande numérique directe ou distribuée [DNC], systèmes d'ateliers flexibles [FMS], systèmes de fabrication intégrés [IMS], productique [CIM]
G06F 30/15 - Conception de véhicules, d’aéronefs ou d’embarcations
Systems and methods for a fully reusable upper stage for a multi-stage launch vehicle are provided. The reusable upper stage uses an aerospike engine for main propulsion and for vertical landing. A heat shield can include a plurality of scarfed nozzles embedded radially around a semi-spherical surface of the heat shield, wherein inboard surfaces of the plurality of scarfed nozzles collectively define an aerospike contour. The heat shield can be actively cooled to dissipate heat encountered during reentry of the upper stage.
B64G 1/62 - Systèmes de retour sur terreDispositifs de freinage ou d'atterrissage
B64G 1/64 - Systèmes pour réunir ou séparer des véhicules spatiaux ou des parties de ceux-ci, p. ex. aménagement pour l'accostage ou l'amarrage
F02K 9/42 - Moteurs-fusées, c.-à-d. ensembles fonctionnels portant à la fois le combustible et son oxydantLeur commande utilisant des propergols liquides ou gazeux
F02K 9/46 - Alimentation en propergols utilisant des pompes
F02K 9/88 - Moteurs-fusées, c.-à-d. ensembles fonctionnels portant à la fois le combustible et son oxydantLeur commande caractérisés par la commande de la poussée ou du vecteur poussée utilisant des tuyères de fusées auxiliaires
F02K 9/94 - Moteurs-fusées réallumables ou redémarrablesMoteurs-fusées fonctionnant d'une manière intermittente
An improved robotic device motion planning system that is capable of producing motion plans for accomplishing a task that are deterministic and at a higher success rate than typical systems is described herein. For example, the improved robotic device motion planning system may implement a hybrid motion planning approach in which the robotic device motion planning system initially attempts to develop a motion plan for a robotic device using a real-time motion planning algorithm. If the robotic device motion planning system is unable to develop a motion plan using a real-time motion planning algorithm, then the robotic device motion planning system may attempt to develop the motion plan using a sampling method.
Quick disconnect devices for high pressure fluid transfer, and associated systems and methods are disclosed. A representative quick disconnect system includes a first connector and a second connector. The second connector can have an opening sized and shaped to receive a first end of the first connector. The second connector can include a poppet positioned to open the first connector when the first connector is connected to the second connector. The second connector can include an inner sleeve moveable between a first position wherein the poppet head forms a fluid-tight seal with the annular seat of the inner sleeve, and a second position wherein the second end portion is open to permit fluid flow through the end portion of the inner sleeve. In some embodiments, the inner sleeve is pressure balanced in every direction.
F16L 37/34 - Accouplements du type à action rapide avec moyens pour couper l'écoulement du fluide avec un obturateur dans chaque extrémité de tuyau avec deux clapets dont l'un au moins est ouvert automatiquement au moment de l'accouplement au moins un des clapets étant du type à manchon, c.-à-d. un manchon étant mobile autour d'un corps cylindrique fixe
F16L 37/35 - Accouplements du type à action rapide avec moyens pour couper l'écoulement du fluide avec un obturateur dans chaque extrémité de tuyau avec deux clapets dont l'un au moins est ouvert automatiquement au moment de l'accouplement au moins un des clapets possédant un canal axial communiquant avec des ouvertures latérales
A representative system includes an alignment tool for aligning attachment interfaces of horizontally-oriented launch vehicle portions. The tool can include a receiver assembly for connecting to a first launch vehicle portion and an actuation assembly for connecting to a second launch vehicle portion. When a first connecting element of the receiver assembly is engaged with a second connecting element of the actuation assembly, the second connecting element can apply force to the receiver assembly, and the actuator assembly applies an opposite force to the second launch vehicle portion, to align fastening features in the launch vehicle portions and/or to reshape the launch vehicle portions. A representative method includes connecting the alignment tool to the launch vehicle portions and operating the tool to apply oppositely-directed forces to align the launch vehicle portions for installing fasteners to connect the launch vehicle portions. One or more bracing beams can connect two tools together.
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p. ex. gabarits à cet effet
B23P 19/10 - Alignement de pièces qui doivent être assemblées entre elles
B23Q 3/18 - Dispositifs permettant de maintenir, supporter ou positionner les pièces ou les outils, ces dispositifs pouvant normalement être démontés de la machine pour positionner uniquement
83.
SOLAR HEATING FOR THIN FILM EVAPORATION AND DIRECTIONAL SOLIDIFICATION
Configurations for solar heating and processing of a material, such as a metal or metalloid, are presented. Such processing may have an end-goal of purifying the material or depositing the material as a thin film on a substrate. The use of solar heating allows these processes to occur without electricity, which may be a scarce resource on the moon. Metals and metalloids derived from lunar regolith or other impure feedstocks may lead to materials with impurities. Generally, materials, such as silicon, need to be purified before being utilized. Techniques for solar heating may be applied to purification of these materials. Purification may be achieved by melting, via solar heating, and resolidifying slowly from one direction to another using a directional solidification process.
Systems and methods for receiving a descending rocket, which may be at sea. The rocket may descend vertically with the nose higher than the nozzle. The rocket body may be angled as it descends. A boom arm with hooks may extend at an angle to the rocket body to engage a cable suspended by a semisubmersible platform at sea. The platform may include a dampened cable and lateral straps for securing and rotating the rocket into a horizontal orientation. The platform may receive a ship and purge water to elevate the platform for placing the horizontal rocket onto the ship.
A solar cell that incorporates a thin layer of iron oxide (FeOx), and a number of techniques for fabricating the solar cell, are presented. The thin layer of iron oxide, which may be derived from lunar regolith, may be the emitter of the solar cell. The solar cell may be a silicon hetero-junction (HJ) solar cell. The FeOx may be present in place of amorphous silicon (a-Si:H), MoOx, or various organic materials, for example. An emitter comprising FeOx may be beneficial for solar cell fabrication on the moon.
H01L 31/072 - Dispositifs à semi-conducteurs sensibles aux rayons infrarouges, à la lumière, au rayonnement électromagnétique d'ondes plus courtes, ou au rayonnement corpusculaire, et spécialement adaptés, soit comme convertisseurs de l'énergie dudit rayonnement e; Procédés ou appareils spécialement adaptés à la fabrication ou au traitement de ces dispositifs ou de leurs parties constitutives; Leurs détails adaptés comme dispositifs de conversion photovoltaïque [PV] caractérisés par au moins une barrière de potentiel ou une barrière de surface les barrières de potentiel étant uniquement du type PN à hétérojonction
H01L 31/18 - Procédés ou appareils spécialement adaptés à la fabrication ou au traitement de ces dispositifs ou de leurs parties constitutives
Architectures and methods of operation for a pump for pumping two-phase magnetic fluids are described. The pump is capable of such pumping and may operate with no moving parts. Instead, the pump operates by selectively activating and deactivating each of a series of electrical circuits to control the presence or absence of magnetic fields applied to the two-phase magnetic fluid. The two-phase magnetic fluid may include liquid phase and gas phase, which may be in the form of bubbles. Though a presence of bubbles in a liquid may lead to cavitation and failure in some pumps, pumps for pumping two-phase magnetic fluids can avoid such a failure mechanism, in addition to avoiding another failure mechanism of wear and tear on moving parts.
F04B 17/00 - Pompes caractérisées par leur combinaison avec des machines motrices ou moteurs particuliers qui les entraînent ou par leur adaptation à ceux-ci
F04B 15/00 - Pompes adaptées pour travailler avec des fluides particuliers, p. ex. grâce à l'emploi de matériaux spécifiés pour la pompe elle-même ou certaines de ses parties
An acoustic blanket absorbs acoustic energy and reduces noise in a launch vehicle. The acoustic blanket may be overlaid on a wall of a payload fairing of the launch vehicle. Materials and construction of the acoustic blanket allow for a relatively thin and light sound barrier. The acoustic blanket may comprise vertically-lapped polyester that is overlaid with a lightweight melamine foam. This combination of materials creates an acoustic impedance mismatch between layers that leads to absorption of acoustic energy across a relatively broad range of frequency bands. The acoustic blanket has a particular heat seal pattern that helps absorb noise while allowing the acoustic blanket to be relatively soft and flexible, which is useful for attaching the acoustic blanket to a curved wall of a fairing or other launch vehicle shapes. The acoustic blanket utilizes micro-perforations on multiple sides to allow for movement of air/venting while maintaining the bulk materials inside.
B32B 27/06 - Produits stratifiés composés essentiellement de résine synthétique comme seul composant ou composant principal d'une couche adjacente à une autre couche d'une substance spécifique
B32B 3/26 - Produits stratifiés comprenant une couche ayant des discontinuités ou des rugosités externes ou internes, ou une couche de forme non planeProduits stratifiés comprenant une couche ayant des particularités au niveau de sa forme caractérisés par une couche continue dont le périmètre de la section droite a une allure particulièreProduits stratifiés comprenant une couche ayant des discontinuités ou des rugosités externes ou internes, ou une couche de forme non planeProduits stratifiés comprenant une couche ayant des particularités au niveau de sa forme caractérisés par une couche comportant des cavités ou des vides internes
B32B 5/18 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par le fait qu'une des couches contient un matériau sous forme de mousse ou essentiellement poreux
B32B 7/02 - Propriétés physiques, chimiques ou physicochimiques
B32B 7/14 - Liaison entre couches utilisant des adhésifs interposés ou des matériaux interposés ayant des propriétés adhésives appliqués en disposition espacée, p. ex. en bandes
B32B 27/08 - Produits stratifiés composés essentiellement de résine synthétique comme seul composant ou composant principal d'une couche adjacente à une autre couche d'une substance spécifique d'une résine synthétique d'une sorte différente
B32B 27/36 - Produits stratifiés composés essentiellement de résine synthétique comprenant des polyesters
B32B 37/06 - Procédés ou dispositifs pour la stratification, p. ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par le procédé de chauffage
B64C 7/00 - Structures ou carénages non prévus ailleurs
Systems and methods for high performance, professional-grade photography and filmmaking in a spacecraft during space flights are provided. The systems may include an imaging studio, which is a partially enclosed volume within a spacecraft. The imaging studio may enable photography during microgravity coast phases of space flight while allowing astronauts to tend to non-photographic activities. The imaging studio may allow for commercially-valuable imagery that includes a background of an illuminated, curved Earth horizon. Imagery may also involve, among other things, a unique microgravity environment. Such imagery, without use of an imaging studio as described herein, may otherwise require artificial visual effects that may appear less realistic. Additionally, the novelty of capturing images during an actual space flight may itself be valuable.
Techniques and systems are used to fabricate relatively large composite structures. Fabrication may be performed automatically by a system comprising a relatively large robotic structure configured to hold and to operate various interchangeable end effectors, each having respective functions for fabricating composite structures. The end effector is positioned by the fabricating system to perform various fabrication functions, such as 3D printing, among other things. The fabricating system may include an x-y-z positioning system, a staging area to accommodate a mold, one or more end effectors, an applicator attached to the end effector, and a docking station to store multiple end effectors.
B29C 64/165 - Procédés de fabrication additive utilisant une combinaison de matériaux solides et liquides, p. ex. une poudre avec liaison sélective par liant liquide, catalyseur, inhibiteur ou absorbeur d’énergie
B29C 64/232 - Moyens d’entraînement pour un mouvement le long de l'axe orthogonal au plan d’une couche
B29C 64/236 - Moyens d’entraînement pour un mouvement dans une direction dans le plan d’une couche
B29C 70/38 - Empilage automatisé, p. ex. utilisant des robots, par application de filaments selon des modèles prédéterminés
A representative spacecraft system includes a connecting device, which in turn includes a housing having a common port opening, a first connecting element carried by the housing and positioned to connect with a corresponding first spacecraft connecting structure having a first configuration, and a second connecting element carried by the housing and positioned to connect with a corresponding second spacecraft connecting structure having a second configuration different than the first configuration. At least one of the first and second connecting elements is moveable relative to the other between an operational position and a non-operational position, and each of the first and second connecting elements, when connected to the corresponding first or second spacecraft connecting structure, is positioned to allow transport through the common port opening.
3, can use the electric propulsion systems and methods to achieve a quasi-steady acceleration less than or equal to 1.0 μg for durations of 180 consecutive days or longer.
Ventilation enclosures (10) for use with battery assemblies (11) and methods of cooling battery assemblies using the same are provided. The ventilation enclosures (10) comprise one or more sidewalls (14, 16) having a plurality of inwardly projecting dimples (26) formed therein. The dimples (26) physically contact a battery assembly housing (13) to provide for conductive heat transfer between the housing and the enclosure (10). The dimples (26) also improve convective heat transfer away from the battery assembly housing (13) by inducing more turbulent air flow within the space (20) located between the housing and the ventilation enclosure (10).
A phase change material (PCM) heat exchanger system for a rocket or other spacecraft is described. The PCM heat exchanger utilizes phase-change material to store heat absorbed from a hot working fluid. The PCM heat exchanger may be configured as an integrated modular double brazed layout that includes folded fins to distribute heat from a working fluid (e.g., hydraulic fluid) to PCM. A modular configuration may enable a heat exchanger system to be scaled up or down by adding or removing modules to meet cooling requirements for particular rockets and their flights.
F28D 20/02 - Appareils ou ensembles fonctionnels d'accumulation de chaleur en généralAppareils échangeurs de chaleur de régénération non couverts par les groupes ou utilisant la chaleur latente
B64G 1/58 - Protection thermique, p. ex. boucliers thermiques
94.
BASALT FIBER REINFORCED SYNTACTIC THERMAL PROTECTION SYSTEM
Techniques and systems are used to fabricate portions of a thermal protection systems (TPS) for placement on or adjacent to a tank or other part of a structure, such as a spacecraft. The TPS may comprise syntactic foam as a spray-on foam insulation (SOFI)), which may be sprayed onto a surface. Alternatively, the TPS may comprise syntactic foam that is applied as preformed panels that are adhered or mechanically attached to a surface. Performance of a syntactic foam may be improved by including basalt fibers in a matrix material of the syntactic foam to make a basalt fiber reinforced syntactic TPS. The basalt fibers may be combined and interspersed with microspheres in the matrix material.
C08J 9/32 - Mise en œuvre de substances macromoléculaires pour produire des matériaux ou objets poreux ou alvéolairesLeur post-traitement à partir de compositions contenant des microbilles, p. ex. mousses syntactiques
C08J 3/21 - Formation de mélanges de polymères avec des additifs, p. ex. coloration en présence d'une phase liquide le polymère étant prémélangé avec une phase liquide
95.
Transpiration-cooled systems having permeable and non-permeable portions
Transpiration-cooled systems having permeable and non-permeable portions are provided. In one aspect, a nozzle for a rocket engine includes a non-permeable outer layer, a plurality of walls, a permeable layer, and a plurality of cooling channels. The non-permeable outer layer forms a predetermined shape of the nozzle and defines an interior space. The plurality of walls extend generally orthogonal to the non-permeable outer layer and into the interior space. The permeable layer is disposed between each set of adjacent walls of the plurality of walls. The permeable layer is spaced a distance from the non-permeable outer layer. The plurality of cooling channels are formed between the permeable layer, the non-permeable outer layer, and a set of adjacent walls of the plurality of walls. The plurality of cooling channels are configured to transport a fluid.
Transpiration-cooled systems having permeable and non-permeable portions are provided. In one aspect, a nozzle for a rocket engine includes a non-permeable outer layer, a plurality of walls, a permeable layer, and a plurality of cooling channels. The non-permeable outer layer forms a predetermined shape of the nozzle and defines an interior space. The plurality of walls extend generally orthogonal to the non-permeable outer layer and into the interior space. The permeable layer is disposed between each set of adjacent walls of the plurality of walls. The permeable layer is spaced a distance from the non-permeable outer layer. The plurality of cooling channels are formed between the permeable layer, the non-permeable outer layer, and a set of adjacent walls of the plurality of walls. The plurality of cooling channels are configured to transport a fluid.
A method of joining a first work-piece to a second work-piece is provided. Each of the first work-piece and the second work-piece include a top surface, an opposed bottom surface, and a side surface connecting the top surface and the opposed bottom surface. In one aspect, the method includes positioning the side surface of the first work-piece adjacent to the side surface of the second work-piece, and advancing a friction stir additive manufacturing tool across the top surface of the first work-piece and the top surface of the second work-piece along a weld line between the first work-piece and the second work-piece. As the friction stir additive manufacturing tool advances along the weld line, a filler material is deposited along the weld line and into a plurality of through holes formed in either or both of the first work-piece and the second work-piece. Each of the plurality of through holes includes a first opening on the top surface, a second opening on the opposed bottom surface, and a passageway through the work-piece between the first opening and the second opening. The method further includes joining the first work-piece and the second work-piece together.
B23K 20/12 - Soudage non électrique par percussion ou par une autre forme de pression, avec ou sans chauffage, p. ex. revêtement ou placage la chaleur étant produite par frictionSoudage par friction
98.
Deposition head for friction stir additive manufacturing devices and methods
A friction stir additive manufacturing device configured to join a first work-piece and a second work-piece is provided. In one aspect, the device includes a rotating spindle configured to deposit a filler material over a weld line as the device is advanced along an interface between the first work-piece and the second work-piece. The device also includes a deposition head configured to receive at least a portion of the spindle, the deposition head configured to remain stationary relative to the rotating spindle. The deposition head includes a first semi-cylindrical portion having an inner radius and an outer radius relative to a first axis, and a second semi-cylindrical portion having an inner radius and an outer radius relative to a second axis that is perpendicular to the first axis. The second semi-cylindrical portion can include a chamfered inner surface configured to define a weld profile.
B23K 20/12 - Soudage non électrique par percussion ou par une autre forme de pression, avec ou sans chauffage, p. ex. revêtement ou placage la chaleur étant produite par frictionSoudage par friction
B23K 103/20 - Alliages ferreux et aluminium ou ses alliages
99.
Liquid rocket engine injector with variable flow area
A variable flow area injector for a liquid rocket engine. The injector has a poppet with a variable outer width portion and a housing with a variable inner width portion. An annular flow path is defined between the variable width portions. Increased throttling of the engine passively increases the annular flow area of the injector by forcing the poppet in a distal direction. Decreased throttling allows a restoring spring to move the poppet in a proximal direction to decrease the annular flow area. A bellows can be included to dampen movement of the poppet. The bellows may be in a propellant-filled cavity separate from the main propellant flow path and have a series of openings through which the separate propellant flows.
F02K 9/42 - Moteurs-fusées, c.-à-d. ensembles fonctionnels portant à la fois le combustible et son oxydantLeur commande utilisant des propergols liquides ou gazeux
F02K 9/58 - Soupapes d'alimentation en combustible
Rocket components having internal heat fins are described herein. The disclosed components have internal heat fins that mitigate buckling and uneven force application by adding thermal capacity to the component without adding component stiffness. This reduces a thermal force fight (i.e., tension versus compression between cold and hot areas, respectively), which inhibits the buckling loads on the propellant tank. The internal heats fins also provide for a reduced mass of the propellant tank wall relative to a propellant tank wall without internal heat fins. By reducing the thermal force fight, as discussed above, less material can be used which further allows for thinner welds to be used (i.e., less welding material).
B64G 1/58 - Protection thermique, p. ex. boucliers thermiques
B64G 1/40 - Aménagements ou adaptations des systèmes de propulsion
F28F 3/02 - Éléments ou leurs ensembles avec moyens pour augmenter la surface de transfert de chaleur, p. ex. avec des ailettes, avec des évidements, avec des ondulations
