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 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: 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 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 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: An antenna system that includes a plurality of lens sets. Each lens set includes a lens and at least one feed element. At least one feed element is aligned with the lens and configured to direct a signal through the lens at a desired direction.

Abstract: An antenna system that includes a plurality of lens sets. Each lens set includes a lens and at least one feed element. At least one feed element is aligned with the lens and configured to direct a signal through the lens at a desired direction.

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: In accordance with at least one aspect of this disclosure, a method includes flushing a cell stack for a predetermined amount of time as a function of an amount of combustible gas remaining in the cell stack. The method also includes operating a cell stack for a predetermined amount of time, then shutting down the cell stack and ceasing operation of the cell stack for a predetermined amount of time. Flushing occurs after shutting down a cell stack power supply. The method further includes restarting operation of the cell stack after flushing.

Abstract: A low-earth orbit (LEO) satellite operates to: determine an orbital position of the LEO satellite based on the first signaling and based on precise point positioning (PPP) correction data associated with the constellation of non-LEO navigation satellites, wherein the PPP correction data includes orbital correction data and timing correction data associated with the constellation of non-LEO navigation satellites, and wherein the PPP correction data is received separate from the first signaling; determine, based on the inter-satellite communications, an error condition associated with one of the other LEO navigation satellites of the constellation of LEO navigation satellites; and broadcast a navigation message based on the orbital position, wherein the navigation message includes a timing signal and the orbital position associated with the LEO satellite, correction data associated with the constellation of non-LEO navigation satellites, and an alert signal that indicates the error condition associated with one

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.

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: 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: The present application relates to techniques for proactively monitoring and detecting failures associated with downlinking data during satellite passes. In some embodiments, first data representing a performance of a hardware device during a satellite pass may be obtained and performance metrics may be computed based on the first data. Second data may be generated based on the performance metrics and a first machine learning model may be used to determine changepoints within the second data and times associated with each changepoint. A second machine learning model may be used to determine a likelihood that the satellite pass will be successful based on at least one of the quantity of changepoints or the times associated with each changepoint, and a quality of service (QoS) score of a client may be updated based on the likelihood.

Abstract: An electric propulsion simulator console (EPSC) which electronically simulates an electric propulsion assembly of a spacecraft as well as propulsion fuel control components and positioning components of the spacecraft. The EPSC simulates a spacecraft thruster electrical interface can test four thruster interfaces simultaneously and continuously. The simulator additionally facilitates the testing of spacecraft fault detection, isolation, and recovery by simulating failed magnet circuits, open anode paths, and flameout conditions. The EPSC includes an electrical propulsion unit load simulator adapted to receive propulsion unit control signals from a spacecraft under test and a spacecraft propulsion unit positioner simulator the simulator adapted to display a simulated state of three axes of movement for at least one propulsion unit positioner responsive to positioning signals received from the spacecraft under test.