Abstract: A system for extracting oxygen from powdered metal oxides, the system comprising a container comprising an electrolyte in the form of meltable or molten salt, at least one cathode, at least one anode, a power supply, and a conducting structure, wherein the cathode is shaped as a receptacle having a porous shell, which has an upper opening, the cathode being arranged in the electrolyte with the opening protruding over the electrolyte, wherein the conducting structure comprises a plurality of conducting elements and gaps between the conducting elements, wherein the power supply is connectable to the at least one cathode and the at least one anode to selectively apply an electric potential across the cathode and the anode, wherein the conducting structure is insertable into the cathode, such that the conducting elements reach into an inner space of the cathode, wherein the conducting structure is electrically connectable to the cathode, and wherein the system is adapted for reducing at least one respective metal

Abstract: A modular building unit for construction of a building comprises a structural frame 40 suitable for interconnection to another modular building unit in construction of the building; and a stud frame wall 80/82 internal to and fixed to the frame. The modular building unit is suitable for handling as a shipping container for transport.

Abstract: Technology is disclosed herein for deploying stacked spacecraft. When the spacecraft are stacked corresponding z-axis magnetic torque rods of the spacecraft will align with each other along a z-axis. Thus, collectively the stack of spacecraft have one or more sets of magnetic torque rods aligned with the z-axis. Just prior to deploying the spacecraft the one or more sets of magnetic torque rods are operated to hold the stack of spacecraft together. For example, the north magnetic pole of the magnetic torque rod in one spacecraft may face the south magnetic pole of the magnetic torque rod in an adjacent spacecraft. To deploy the top spacecraft, the polarity of the z-axis magnetic torque rod(s) in the top spacecraft is/are reversed. After the spacecraft is clear of the stack the magnetic torque rod(s) in the deployed spacecraft may be de-activated. Then another spacecraft may be deployed in a similar manner.

Abstract: An offshore rocket transport and launch method includes S1: assembling a rocket horizontally; S2: loading the assembled rocket as a whole into a transport cage; S3: transporting, by a transport vehicle, the transport cage loaded with the rocket to a wharf by land horizontal transport; S4: transferring the transport cage loaded with the rocket to a transport ship, and transporting the transport cage loaded with the rocket to an offshore rocket launch pad by sea transport; S5: hoisting, by a hoisting device, the transport cage loaded with the rocket to the rocket launch pad; S6: opening the transport cage, transferring the rocket to a launching position, and hoisting the transport cage away from the rocket launch pad; and S7: launching the rocket. The method effectively facilitates the offshore rocket transport and launch process, and prevents the rocket from being affected by the external environment during the launch process.

Abstract: A connector loading device may comprise a receptacle, a plurality of light sources, and a controller. The receptacle may comprise a first plurality of holes. The first plurality of holes are configured to respectively line up with a second plurality of holes in a connector when the connector is inserted in the receptacle. Each one of the first plurality of holes comprises a respective and corresponding one of a plurality of unique indexes. The plurality of light sources respectively correspond to the first plurality of holes. Each one of the plurality of light sources, when initiated, is configured to illuminate light from a bottom of its respective one of the first plurality of holes through a top of its respective one of the first plurality of holes. The controller is configured to receive an input and initiate a one of the plurality of light sources corresponding to the index.

Abstract: Systems, methods, and non-transitory media are provided for synchronization of multi-user uplink transmissions. An example method can include receiving, by a user terminal, a downlink radio frame transmitted by a satellite; determining, by the user terminal, a downlink propagation delay associated with the downlink radio frame and an uplink propagation delay associated with an uplink radio frame from the user terminal to the satellite; based on the downlink propagation delay and the uplink propagation delay, determining, by the user terminal, an uplink transmission delay indicating an amount of time to delay a transmission of the uplink radio frame to the satellite so the uplink radio frame is received at the satellite at a same target time as one or more additional uplink radio frames from one or more additional user terminals; and transmitting, by the user terminal, the uplink radio frame at a time corresponding to the uplink transmission delay.

Abstract: Disclosed herein are system, method, and computer program product embodiments for assessing performance of a player of a game. An embodiment operates by monitoring for an input from the player of the game, receiving the input from the player of the game, and determining a characteristic of the game resulting from the input from the player. Based on the input from the player, a performance of the player is assessed. The performance of the player relating to one or more metrics of the game is monitored, and is assessed by comparing the input from the player during the period of time to an optimal input during the period of time in the game.

Abstract: A stacked, monolithic, upright metamorphic, terrestrial concentrator solar cell having exactly five subcells and having a metamorphic buffer, wherein a first subcell has a first lattice constant G1 and consists essentially of germanium, a second subcell has a second lattice constant and GaInAs, a third subcell has the second lattice constant G2 and AlGaInAs, a fourth subcell has the second lattice constant G2 and InP, a fifth subcell has the second lattice constant G2 and InP, G1<G2 applies to the lattice constants, the metamorphic buffer is arranged between the first subcell and the second subcell and has the first lattice constant G1 on a bottom side facing the first subcell and the second lattice constant G2 on a top side facing the second subcell, and all of the semiconductor layers of the concentrator solar cell arranged above the first subcell are epitaxially produced on the preceding subcell.

Abstract: Systems and methods for providing a spacecraft are provided. The spacecraft includes a main structural member that extends between end panels of the spacecraft, and that defines a first interior volume. A fuel tank is disposed within and conforms to at least a portion of the first interior volume. The fuel tank can itself include a central void that defines a second interior volume. The main structural member and the fuel tank can be cylindrical. Payload items or components of the spacecraft can be disposed within the second interior volume.

Abstract: A solid state power amplifier uses a Doherty power amplifier that can be implemented as a monolithic microwave integrated circuit. By adjusting the DC bias of the amplifying stages in each branch of the Doherty amplifier, the output power, linearity, and DC power can be adjusted to provide a specified output, where the specification for the output can include the maintaining of desired DC power and linearity. The Doherty power amplifier can be used in a satellite payload or other application utilizing solid state power amplifiers, while providing the proper amount of RF output power and DC power. A single amplifier can have its bias levels adjusted for different output levels, helping to minimize the number of designs that are required for a given satellite payload, reducing the variety of parts in a satellite payload.

Abstract: An orbital transfer vehicle system for cargo delivery is described herein. An orbital transfer vehicle (OTV) resides in space at a staging orbit. The OTV is configured for interfacing with a cargo pod at an insertion orbit to form a mated stack including the OTV and the cargo pod. The OTV is further configured for providing propulsion and rendezvous operations for transporting the mated stack to an intended target destination. Upon completion of delivery of the cargo pod to its intended target destination, the OTV then releases the cargo pod and returns to the staging orbit.

Abstract: A space station includes a housing that defines an interior space. An inner chamber is located in the interior space and defines an inner cavity that is sealable from the remainder of the interior space. At least one bulkhead is arranged in the interior space to partition the interior space into at least two compartments that are hermetically sealable from one another. One compartment can be accessed from another compartment via the inner cavity of the inner chamber. The inner cavity is sealable against each compartment. Openings in an outer surface of the housing enable crew members to leave a damaged compartment through the opening. Thus, alternative routes exist to leave a damaged compartment, i.e., either through the inner cavity or through the opening in the outer surface of the housing. When one compartment is damaged, the adjacent compartments are still operative because they are sealed from the damaged compartment.

Abstract: A rocket propulsion system that may include a supersonic rocket nozzle with a supersonic divergent section, and a heat transfer system configured to transfer heat from the supersonic rocket nozzle to a propellant where a portion of the propellant may be selectively injected, combusted, and expanded in the supersonic nozzle generating an additional thrust. In examples, the heated propellant may be used to power a pump system to feed the rocket engine.

Abstract: A rocket propulsion system that may include a supersonic rocket nozzle with a supersonic divergent section, and a heat transfer system configured to transfer heat from the supersonic rocket nozzle to a propellant where a portion of the propellant may be selectively injected, combusted, and expanded in the supersonic nozzle generating an additional thrust. In examples, the heated propellant may be used to power a pump system to feed the rocket engine.

Abstract: A system for managing resources and scheduling is disclosed. The system includes a client computer, software executable by the client computer for providing a user interface, a server in data communication with the client computer, a database for storing data in a hierarchical data structure, and a data fusion engine executing on the server. The hierarchical data structure includes a parent node and child nodes linked to the parent node. The data fusion engine is configured to log a workflow to at least one of the child nodes based on user input received via the user interface. A related method and software is also disclosed.

Abstract: These inventions are directed to creating interactive experiences in remote locations across networks that involve actions by users at either end that solicit reactions at remote ends creating an immersive shared environment and experience that allows users to feel they are within the same space. These experiences manifest in various scenarios of play by different playground structures that are illustrated and described in this application. In particular, these inventions create shared interactive playgrounds for children to participate in and enjoy.

Abstract: Disclosed herein are system, method, and computer program product embodiments for assessing performance of a player of a game. An embodiment operates by monitoring for an input from the player of the game, receiving the input from the player of the game, and determining a characteristic of the game resulting from the input from the player. Based on the input from the player, a performance of the player is assessed. The performance of the player relating to one or more metrics of the game is monitored, and is assessed by comparing the input from the player during the period of time to an optimal input during the period of time in the game.

Abstract: A radiator structure for a satellite is provided. A first radiator panel adapted to be positioned on a first side of a central body, and a second radiator panel adapted to be positioned on a second side of the central body. Other implementations include a third radiator panel positioned on a third side of the central body. The apparatus also includes at least one heat pipe embedded between a first face and a second face of each radiator panel and extending from the first radiator panel through the first radiator panel and through the second radiator panel. The heat pipe structurally supports the first radiator panel and the second radiator panel relative to the intermediate radiator panel. A method of manufacturing a radiator structure is also provided.

Abstract: Process control parameters are predicted to fabricate an object using deposition. An input design geometry is provided for the object. A training data set includes past post-build physical inspection data for a plurality of objects that comprise at least one object that is different from the object to be physically fabricated; and training data generated through a repetitive process of randomly choosing values for each of multiple process control parameters and scoring adjustments to the multiple process control parameters as leading to either undesirable or desirable outcomes, the outcomes based respectively on the presence or absence of defects detected in a fabricated object arising from the process control parameter adjustments. A machine learning algorithm is trained using the provided training data set and a predicted optimal set of the multiple process control parameters is generated for initiating and performing the deposition process to fabricate the object.

Abstract: The system can include: a vehicle 100 and a stabilizer 200. However, the system can additionally or alternatively include any other suitable set of components. The system functions to facilitate vehicular transport (e.g., via a cabin). Additionally, the system can provide impact attenuation and/or mitigate rebound of the vehicle during a water landing. Additionally or alternatively, the system can function to provide aquatic stabilization of the vehicle and/or cabin thereof. However, the system 100 can provide any other suitable functionalities.