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: 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: 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: 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.

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: A counter-swarm firework includes a shell casing, multiple streamers positioned in the shell casing, a burst charge positioned in the shell casing and configured to disperse the multiple streamers from the shell casing when discharged, a pusher plate positioned in the shell casing between the burst charge and the multiple streamers, a fire suppressant layer positioned between the burst charge and the pusher plate, and a kick charge configured to launch the shell casing and its contents prior to discharging the burst charge. The fire suppression layer may be configured to suppress heat generated by the discharge of the burst charge.

Abstract: The cabin conditioning system can include a cabin air loop, a refrigerant loop, and a set of thermal rejection components. The system can optionally include a phase-change fluid loop. However, the cabin conditioning system can additionally or alternatively include any other suitable set of components. The cabin conditioning system functions to condition a cabin interior (and/or an air volume therein) of a vehicle, such as an atmospheric and/or space-flight capsule. Additionally or alternatively, the system can function to reject heat from the vehicle interior and/or vehicle power systems (e.g., avionics components thereof). Additionally or alternatively, the system can function to maintain the humidity of air within the cabin interior. However, the cabin conditioning system can include any other suitable components.

Abstract: A display arrangement for presenting video information to a human operator in a vehicle senses vehicle movements and movements of a head mounted display unit. Based on vehicle movements and movements of the display unit, a virtual scenario with background video data and application video data are generated to a display arrangement. The background video data are modified so background video moves opposite to vehicle movements. The application video data are modified so application video moves according to vehicle movement. A perspective onto the application video can be modified based on relative movements of the display unit with respect to the vehicle. This may reduce conflicts between sensory impressions of the vestibular system and eyes of the operator because movements of the vehicle and movements of the display unit are considered when generating and modifying the background and application video data presented to the operator.

Abstract: A toilet for a zero-gravity condition, having: a seat extending from a first end to a second end, and from a first side to a second side; a leg rest at the first end of the seat that is level with the seat; a backrest at the second end of the seat that extends away from the seat, toward an outer end of the toilet, a first sidewall at the first side of the seat and a second sidewall at the second side of the seat, the sidewalls extend away from the seat toward the outer end of the toilet; a basin extending away from the seat toward an inner end of the toilet; a first inflatable member extending about the leg rest, the sidewalls and the backrest, the first inflatable member is configured to inflate against a back, sides and under legs of a person seated against the seat.

Abstract: A spacecraft includes: a main-reflection unit configured to reflect and emit a radio wave outside, a sub-reflection unit configured to face the main-reflection unit, a radiator arranged to face the sub-reflection unit and configured to radiate the radio wave in a direction of the sub-reflection unit, a main body configured to be able to accommodate at least one part of the sub-reflection unit therein, and a delivery device connected to the sub-reflection unit and configured to deliver the sub-reflection unit, at least one part of which is accommodated in the main body, to a position where the sub-reflection unit is able to reflect the radio wave radiated from the radiator to the main-reflection unit and cause the main-reflection unit to radiate the radio wave outside.

Abstract: A structural component for an aircraft, spacecraft or rocket has a ply of fiber reinforced polymer, a first carbon nanotube mat; and a metallic layer, wherein the carbon nanotube mat and the metallic layer are arranged on the ply of fiber reinforced polymer to form a hybrid lightning strike protection layer. A component for manufacturing such a structural component, a method for manufacturing a component of this type, a method for manufacturing a structural component and an aircraft or spacecraft with such a structural component are described.

Abstract: To facilitate on-orbit servicing, such as for a refueling operation, techniques are presented for a servicing satellite to cut through the multi-layer insulation blanket of a client satellite to provide access to the client satellite without releasing unacceptable quantities of foreign object debris from the multi-layer insulation. The serving satellite includes a sealing tool, such as a pair of heater rollers, that apply pressure and heat to the insulating blanket to melt the inner layers and seal the outer layers together. The servicing satellite can then use a cutting tool to cut the sealed region and access the client satellite.

Abstract: A satellite orbiting in one of a plurality of orbital planes of a satellite constellation system at an altitude range corresponding to low earth orbit includes at least one processor configured to generate satellite state data, and to generate a navigation signal based on the satellite state data. The satellite includes at least one transmitter configured to transmit the navigation signal for receipt by at least one client device on earth. Each of the plurality of orbital planes includes a corresponding one of a plurality of satellite subsets of a plurality of satellites of the satellite constellation system. Each of the plurality of orbital planes is within the altitude range, and the plurality of orbital planes includes a set of inclined orbital planes at a non-polar inclination.

Abstract: Systems and methods for providing a solar cell array with a reduced magnetic field are provided. The systems include a plurality of solar cells arrayed on a first surface side of a substrate. The solar cells are electrically connected to one another in series by a first conductor structure at least partially disposed on the first surface side of the substrate, forming a solar cell or supply circuit. A second conductor structure in series with the solar cell circuit is at least partially disposed on the second surface side of the substrate, forming a return harness. The supply circuit and the return harness define current paths that are opposite one another, and that are separated from one another by the substrate. The first and second conductor structures can be formed from conductive traces on the first and second sides respectively of the substrate.

Abstract: Spacecraft and antenna apparatus that can be more easily deployed from a stored state can include: a main-reflection unit including a plurality of ribs formed to be deployable in a stored state in which the ribs are folded and a sheet body provided between a plurality of the ribs and configured to be capable of reflecting a radio wave radiated from a radiator and emitting the radio wave outside, and a restriction member configured to restrict deployment of the plurality of ribs in the stored state, and release the restriction by operation of a restriction release member different from the main-reflection unit.

Abstract: Technology is disclosed herein for preventing or at least significantly reducing shock to spacecraft such as satellites when releasing a hold-down rod assembly that clamps the spacecraft to, for example, a launch vehicle adaptor. The hold-down rod assembly has tension rods that may be pre-loaded at considerable tension in order to hold down a stack of spacecraft in a launch configuration. In an embodiment, pneumatic actuators are used to slowly release the tension in the tension rods. Therefore, shock to the spacecraft is prevented or at least significantly reduced.

Abstract: Systems and methods for localized work return path of additive manufacturing systems are described. Localized grounding connects the printed surface directly to the work return, and shortens the length of grounding and/or the return cables compared to substrate-based grounding.

Abstract: For maneuvering a spacecraft, a method calculates a virtual point that represents a plurality of spacecraft orbiting in a spacecraft formation. The method iteratively calculates a desired trajectory relative to the virtual point for a given spacecraft of the plurality of spacecraft using a relative orbital elements (ROE) state x of the virtual point and the given spacecraft. Model predictive control maintains the given spacecraft within an ROE constraint for a given time interval subject to a fuel consumption. In response to determining a drift trajectory of the given spacecraft is outside of a trajectory tolerance of the desired trajectory, maneuvering the given spacecraft to within the trajectory tolerance using a maneuver trajectory determined using the model predictive control.