A capping system may include a cap and an interface panel. The cap may be closed against the interface panel by a release mechanism and by a seal under preloaded stress state within the cap. The cap may be configured to be ejected along a trajectory or path which is away from a launch vehicle trajectory or path based in part on the release mechanism being disengaged and based in part on a seal being released from the preloaded stress state.
Systems and methods for forming metal wire are presented. A system may include a cylindrical vessel that has a threaded wall so as to have a continuous helical groove on the inside surface of the vessel wall. Molten metal settled at the bottom of the vessel may be centrifugally forced into the helical groove when the vessel is spun at a sufficient rate of rotation. Subsequently, after the molten metal in the groove has cooled to a solid, a wire has been formed, which may then be extracted from the helical groove.
B22D 13/10 - Accessoires pour machines à couler par centrifugation, p. ex. moules, leur garnissageMoyens pour l'alimentation en métal liquide, pour le nettoyage des moules ou pour l'extraction des pièces
B22D 13/02 - Coulée par centrifugationCoulée utilisant la force centrifuge de pièces longues, pleines ou creuses, p. ex. de tuyaux, coulées dans des moules tournant autour de leur axe longitudinal
B22D 13/12 - Commande, surveillance, spécialement adaptées à la coulée centrifuge, p. ex. pour des raisons de sécurité
3.
SYSTEMS AND METHODS FOR THERMAL DISSIPATION USING A VARIABLE GEOMETRY RADIATOR
A lunar structure comprising: a base configured to provide active thermal energy dissipation; a retractable mast coupled to the base, the retractable mast comprising deployable interlocking actuated bands, wherein the deployable interlocking actuated bands extend in a vertical direction upward from the base; and a thermal dissipation system coupled to the base, the thermal dissipation system comprising a variable geometry radiator system configured to provide passive thermal energy dissipation, wherein the variable geometry radiator system comprises a radiator and is configured to adjust the radiator from a first position in which the radiator is in a folded configuration at the base to a second position in which the radiator is extended to form a substantially flat plane.
B64G 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe
E04H 12/18 - ToursMâts ou pylônesCheminées d'usineChâteaux d'eauProcédés d'édification de ces structures mobiles ou avec des sections mobiles, p. ex. tournantes ou télescopiques
4.
SYSTEMS AND METHODS FOR LUNAR UTILITY WITH NAVIGATION, ADVANCED REMOTE SENSING, AND AUTONOMOUS BEAMING FOR ENERGY REDISTRIBUTION
A lunar structure comprising: a base comprising legs to couple to a planetary body; a retractable mast coupled to the base, the retractable mast comprising deployable interlocking actuated bands, wherein the deployable interlocking actuated bands extend away from the base; a payload coupled to a top portion of the retractable mast, the payload comprising a plurality of individual housing portions that are each configured to store an operational component; a solar power system coupled to the top portion of the retractable mast, the solar power system configured to extend downward from the top portion of the retractable mast; a thermal dissipation system coupled to the retractable mast and the base, the thermal dissipation system configured to expel thermal energy from the payload to an external environment; and a thermal consolidation system coupled to the retractable mast, and configured to maintain thermal energy in an enclosure that surrounds the base.
E04H 12/18 - ToursMâts ou pylônesCheminées d'usineChâteaux d'eauProcédés d'édification de ces structures mobiles ou avec des sections mobiles, p. ex. tournantes ou télescopiques
B64G 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe
H02S 20/30 - Structures de support mobiles ou réglables, p. ex. pour réglage de l’angle
Stacked satellite dispensing systems are described herein. The disclosed systems have a full stack of satellites with multiple sub-stacks. Each of the multiple sub-stacks has a respective sub-stack strut that stabilizes the sub-stack of satellites. A full stack strut stabilizes the full stack of all the sub-stacks of satellites. The sub-stack struts and the full stack strut can traverse an external sidewall of the satellites, and, in some examples, extend diagonally along the external sidewalls. Each sub-stack of satellites is stacked, then its respective sub-stack strut is extended along the external sidewall of the sub-stack. After each sub-stack strut is secured, the full stack strut is secured along the external sidewall of the full stack of satellites.
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 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 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
9.
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
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 metal encapsulated ceramic tile thermal insulation system for rockets and associated methods is disclosed. A representative system includes a launch vehicle having a first end and a second end generally opposite the first end and includes a heat shield positioned at the second end. The heat shield includes a plurality of thermal protection apparatuses, where individual of the thermal protection apparatuses include ceramic tiles encapsulated by inner and outer metal layers, which are positioned on opposing top and bottom surfaces of the ceramic tiles. The plurality of thermal protection apparatuses includes a plurality of pins positioned within corresponding holes drilled through the ceramic tiles and are secured to the metal layers. The outer metal layer can protect the ceramic tile from tool strikes and debris and can also prevent water from reaching and being absorbed by the ceramic file.
B32B 15/04 - Produits stratifiés composés essentiellement de métal comprenant un métal comme seul composant ou comme composant principal d'une couche adjacente à une autre couche d'une substance spécifique
12.
HIGH TEMPERATURE THERMAL PROTECTION SYSTEM FOR ROCKETS, AND ASSOCIATED METHODS
A high temperature thermal protection systems for rockets, and associated methods, is disclosed. A representative system includes a launch vehicle having a first end and a second end generally opposite the first end. The launch vehicle is elongated along a vehicle axis extending between the first and second ends and carries a propulsion system having at least one nozzle positioned at the second end of the launch vehicle. A thermal protection apparatus positioned around the nozzle is used to provide cooling and/or insulation to the nozzle during the flight of the launch vehicle. The thermal protection apparatus can include multiple fabric layers and an insulation layer stacked and stitched together. The fabric layers can include metal alloy fibers. In representative systems, the thermal protection apparatus can further include provisions for water that saturates the insulation layer to provide further insulating and/or cooling effects.
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 5/08 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par les caractéristiques de structure d'une couche comprenant des fibres ou des filaments les fibres ou filaments d'une couche étant disposés d'une certaine manière ou étant faits de substances différentes
13.
ROCKET TANK LIQUID LEVEL DETERMINATION, AND ASSOCIATED SYSTEMS AND METHODS
Rocket tank liquid level determination, and associated systems and methods. A representative system includes a computer-readable medium having instructions that, when executed, receive an image corresponding to a view of the liquid in the rocket tank, identify an edge between the liquid and a wall of the tank, and, based on at least one of a size, shape, location, or orientation of the edge, estimate a level of the liquid in the tank. In addition to or in lieu of determining the liquid level, the system can determine a characteristic of a sloshing motion of the liquid in the tank, and, based at least on the characteristic of the sloshing motion, direct operation of a forcing element that imparts a force to the rocket to at least partially counteract a force placed on the rocket by the sloshing motion of the liquid in the tank.
B64G 1/22 - Parties de véhicules spatiaux ou équipements spécialement destinés à être fixés dans ou sur ces véhicules
B64G 1/24 - Appareils de guidage ou de commande, p. ex. de commande d'assiette
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
G01F 23/00 - Indication ou mesure du niveau des liquides ou des matériaux solides fluents, p. ex. indication en fonction du volume ou indication au moyen d'un signal d'alarme
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
14.
VERTICAL LANDING SYSTEMS FOR SPACE VEHICLES AND ASSOCIATED METHODS
Methods and systems for vertically landing space vehicles are described herein. In one embodiment, a reusable space vehicle lands in a vertical, nose-up orientation by engaging a system of cables suspended from an elevated framework during a controlled descent.
Severe weather agility thrusters, and associated systems and methods are disclosed. A representative system includes a launch vehicle having a first end and a second end generally opposite the first end, and is elongated along a vehicle axis extending between the first and second ends. A propulsion system is carried by the launch vehicle and has at least one main engine having a corresponding nozzle positioned toward the first end to launch the launch vehicle. At least one laterally-directed thruster is positioned toward the second end of the launch vehicle. The system further includes a controller in communication with the launch vehicle and programmed with instructions that, when executed, direct the launch vehicle in a first direction during vehicle ascent, direct the launch vehicle in a second direction, opposite the first direction, during vehicle descent, and direct activation of the at least one laterally-directed thruster to guide the launch vehicle during descent.
A contoured roller set and associated systems and methods are disclosed herein A male roller having a convex surface and a pair of female rollers each having a concave surface can receive a generally thin sheet of material and impart a doubly- curved shape to the sheet The convex and concave surfaces of the male and female rollers can have a radius of curvature chosen to match a radius of curvature of the sheet of material The rollers are positioned and shaped to urge the sheet between the female rollers to cause the sheet to curve toward the male roller.
Eyeball seals for a gimbaled rocket engines, and associated systems and methods are disclosed. A system in accordance with a particular embodiment includes a rocket body, an engine carried by and movable relative to the rocket body, and a seal assembly. The seal assembly can include a sealing surface carried by one of the rocket body and the engine, and a seal element carried by the other of the rocket body and the engine. The seal element is in contact with the sealing surface. The seal assembly can further include a cylinder and a piston slideably received in the cylinder, with one of the piston and the cylinder carrying the seal element. The cylinder includes ports that are in fluid communication with a region external to the rocket body. Accordingly, pressures external to the rocket body can force the seal element and/or the sealing surface into contact with each other.
F02K 9/84 - 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 mobiles
Technology for predicting and correcting a trajectory is described. The technology can create a model to predict a position of the reusable launch vehicle at a time in the future; observe a wind condition during ascent of the reusable launch vehicle; store the observed wind condition in a wind map; predict during ascent a position and a terminal lateral velocity of the reusable launch vehicle at a terminal altitude; and correct a flight trajectory of the reusable launch vehicle based on the wind map.
Technology is described for enabling a reusable launch vehicle to compensate for wind prior to engaging propulsion during approach to landing. The technology can cause the reusable launch vehicle to begin un-powered descent; determine a first rotation angle of the reusable launch vehicle about a specified vertical descent path, the first rotation angle corresponding to a first attitude of the reusable launch vehicle selected to stabilize the reusable launch vehicle on the vertical descent path based on a wind speed and angle; and prior to engaging a propulsion device, command a second rotation angle for the reusable launch vehicle, the second rotation angle corresponding to a second attitude that, when the propulsion device is engaged, will cause the reusable launch vehicle to remain at least approximately at the vertical descent path.
Multiple-use rocket engines and associated systems and methods are disclosed. A method in accordance with a particular embodiment includes launching a two-stage vehicle have a first stage and a second stage carried by the first stage. The first stage can be powered with a first rocket engine having first rocket engine components, including a first combustion chamber, arranged in a first component configuration. The method can further include separating the second stage from the first stage, and powering the second stage with a second rocket engine having second engine components arranged in a second component configuration. The second rocket engine components can include a second combustion chamber that is interchangeable with the first combustion chamber. In further particular embodiments, recovered engine components from the first stage may be used to power the second stage of the same or a different two-stage vehicle.
Launch vehicles with fixed and deployable deceleration surfaces and associated systems and methods are disclosed. A system in accordance with a particular embodiment includes a launch vehicle that has a first end and a second end generally opposite the first end, and is elongated along a vehicle axis extending between the first and second ends. The vehicle carries an exposed outwardly facing surface having a first region positioned or positionable to have a first cross-sectional area generally normal to the vehicle axis toward the first end of the vehicle, and a second region positioned or positionable to have a second cross-sectional area generally normal to the vehicle axis toward the second end of the vehicle. The system can further include a propulsion system carried by the launch vehicle and having at least one nozzle positioned toward the first end of the vehicle to launch the launch vehicle.
Vehicles with bidirectional control surfaces and associated systems and methods are disclosed. In a particular embodiment, a rocket can include a plurality of bidirectional control surfaces positioned toward an aft portion of the rocket. In this embodiment, the bidirectional control surfaces can be operable to control the orientation and/or flight path of the rocket during both ascent, in a nose-first orientation, and descent, in a tail-first orientation for, e.g., a tail-down landing.
Modular friction welding heads and associated systems and methods are disclosed herein. A friction welding system in accordance with a particular embodiment includes a carrier fixture positioned to carry a workpiece, a head support positioned proximate to the carrier fixture, and a modular friction welding head releasably carried by the head support. At least one of the carrier fixture and the head support can have a guide structure with a constrained motion path positioned to guide relative motion between the modular friction welding head and the carrier fixture. A controller can be operatively coupled to the modular friction welding head and programmed with instructions to control the operation of the friction welding head.
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
brevets
