Abstract: A field-assembled satellite communications terminal has a plurality of discrete, modular aperture blocks. Each aperture block contains an electrically steered antenna aperture, and a plurality of interconnection ports for power and data communications between the plurality of aperture blocks. The plurality of interconnection ports are removably connectable by the end user in the field. The terminal further has a signal processing system for receiving, processing, and generating signals to and from the apertures. The aperture blocks are connected to each other in the field and self-configure to form an electrically-steered antenna.

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: A spatial indexing system receives a video that is a sequence of frames depicting an environment, such as a floor of a construction site, and performs a spatial indexing process to automatically identify the spatial locations at which each of the images were captured. The spatial indexing system also generates an immersive model of the environment and provides a visualization interface that allows a user to view each of the images at its corresponding location within the model.

Abstract: Integrated devices comprising integrated circuits and energy storage devices are described. Disclosed energy storage devices correspond to an all-solid-state construction, and do not include any gels, liquids, or other materials that are incompatible with microfabrication techniques. Disclosed energy storage device comprises energy storage cells with electrodes comprising metal-containing compositions, like metal oxides, metal nitrides, or metal hydrides, and a solid state electrolyte.

Abstract: A method for authorizing the flight of an aircraft provided with a hybrid power plant having at least one heat engine and at least one electric motor electrically connected to an electrical energy source comprising several electrical accumulators. The method comprises extracting (STP1), while on the ground, an electrical energy or an electrical power to be extracted from the electrical energy source during a predetermined time period and determining (STP2) for the electrical accumulators, respective initial values of an operating parameter, calculating (STP3) an average value from the initial values, determining (STP4) a minimum value from the measured initial values, issuing an authorization when a difference between the average value and the minimum value is less than a threshold and a prohibition when said difference between the average value and the minimum value is greater than or equal to the threshold.

Abstract: A diode arrangement, including a semiconductor diode with a p/n junction. A first electrical contact is formed on an upper side and a second electrical contact is formed on an underside. The semiconductor being designed in an uncased manner as a flat die and having a planar upper side and a planar underside, and the metal-plated upper side forming the first contact of the semiconductor diode, and the metal-plated underside forming the second contact. A first flat metallic conductor has a first contact surface and a second contact surface spaced a distance apart from the first contact surface by a connecting piece. A second flat metallic connector has a first contact surface and a second contact surface spaced a distance from the first contact surface by a connecting piece. The metal-plated upper side is connected in a materially bonded manner to the first contact surface of the first metallic connector.

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: 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: 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: 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: A communication system with increased throughput for providing communication between transceivers via a wireless communication channel through multiple, N, single input, single output, SISO, links provided for a corresponding number, N, of data sequences, wherein each transceiver includes a transmitter having spreading units each configured to spread in an operation mode of the communication system a data sequence with an associated predefined unique spreading code sequence to generate a spread data sequence multiplexed to an antenna unit of the respective transceiver configured to transmit the spread data sequences via the wireless communication channel to antenna units of other transceivers of the communication system.

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: 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: 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: 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: 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.