Abstract: A system (100) and method (300) for launching multiple satellites from a launch vehicle is provided. The system includes a mechanical structure (102) which has one or more mounting means (104A-F), a control unit (106) for controlling the one or more mounting means for positioning and separating the multiple satellites in the mechanical structure, an image capturing system for monitoring the positioning of each satellite in the mechanical structure. The mounting means are adapted to position the satellites in axial, inclined and radial separations at a distance to ensure that each satellite will not come in contact with each other in short duration as well as long duration of orbit evolution.

Abstract: The present application relates to a hermetically sealed higher capacity lithium ion cells for various applications including space, and a method for their manufacture. In particular, the present invention provides hermetically sealed lithium ion cells of higher capacity (40-100 Ah) with very high capacity retention capability.

Abstract: A multiplexer and a method for combining radio frequency (RF) data are provided. The method is described below. The first output management circuit receives first data and second data and determines whether a first power of the first data and a second power of the second data match a default rule. The first output management circuit output first output data including the second data to a combine circuit coupled to the first output management circuit in response to the first power and the second power not matching the default rule. The combine circuit receives multiple output data from the output management circuits respectively and combines the output data to output combined RF data. The output management circuits include the first output management circuit. The output data includes the first output data.

Abstract: Systems and methods for additive layer manufacturing of metallic components, such as rocket engines and propellant supply systems, are provided. Methods include melting the surface of a work piece to form a weld pool; adding wire to the weld pool and moving a heat source relative to the work piece to progressively form a new layer of metallic material on the work piece; cooling the formed layer; stress relieving (e.g., peening) the cooled layer; applying a secondary operations either sequentially or simultaneously; and repeating the above steps as required to form components layer by layer. Systems and methods of supplying a first propellant to the rocket engine of a launch vehicle are also provided, where the first propellant is supplied through a heat exchanger for generating mechanical energy to pump the first propellant into the rocket engine, and electrical energy to pump a second propellant into the rocket engine.

Abstract: A method for testing the total dose effect of a SiC MOSFET device, realizing verification of the complex total dose effect of the SiC MOSFET. The test steps sequentially comprise: testing a tested device before irradiation; performing annealing treatment on the tested device before irradiation; performing an irradiation test on the tested device; performing annealing treatment on the tested device after irradiation; performing test data analysis and processing on the tested device after irradiation. In the test process, threshold voltage shift caused by total dose radiation-induced defects and threshold voltage shift caused by near interface trap charges inherent near a SiC MOSFET interface are measured respectively, comprehensive analysis and calculation are carried out on the test result, the total dose effect resistance capability of the SiC MOSFET device can be given, and a certain guiding effect on device reinforcement is achieved.

Abstract: A ground-based node of a satellite system operates by: communicating control data with LEO navigation satellites in LEO around the earth; transmitting corrections data to the LEO navigation satellites; receiving a first collection of observations based on signaling from non-LEO navigation satellites in non-LEO around the earth, the signaling including collected observations from the non-LEO navigation satellites; receiving a second collection of observations based on navigation messages from the LEO navigation satellites, wherein the navigation messages facilitate client devices to determine their enhanced position when received in conjunction with second signaling from the non-LEO navigation satellites, and wherein the navigation messages are generated by the LEO navigation satellites in response to the corrections data; updating the corrections data based on the first collection of observations, the second collection of observations and based on telemetry data corresponding to the LEO navigation satellites

Abstract: A connection unit comprising two female connectors configured to be connected to respective circuit branches of a fluidic line and a coupling element for coupling the connectors together and establish a fluidic connection between the circuit branches, wherein the connectors are provided with first, normally closed sealing elements to define a sealing termination of the circuit branches when the connectors are disconnected from each other; the coupling element includes a double-male connector separable from the female connectors and provided with a pair of shanks that can be coupled to the respective female connectors and a control element movable between a first position where the coupling element can be coupled to the connectors in a mechanical pre-coupling condition without fluidic connection between the female connectors and a second position where the shanks of the double-male connector engage the respective female connectors and establish a fluidic connection therebetween.

Abstract: In an embodiment, a method includes determining a first beam pointing vector associated with an antenna assembly by searching for a satellite from a plurality of satellites. The method includes maintaining a communication link with the satellite by determining a plurality of beam pointing vectors that converge to a signal quality value. The method includes obtaining, from the satellite, satellite ephemeris information of the satellite and one or more of remaining satellites of the plurality of satellites. The method includes determining an estimated orientation of the antenna assembly based on one or more of the satellite ephemeris information and the plurality of beam pointing vector. The method includes determining a second beam pointing vector based on the estimated orientation, the satellite ephemeris information, and an approximate position information of the antenna assembly.

Abstract: Systems and methods for satellite Synthetic Aperture Radar (SAR) artifact suppression for enhanced three-dimensional feature extraction, change detection, and/or visualizations are described. In some aspects, the described systems and methods include a method for suppressing artifacts from complex SAR data associated with a scene. In some aspects, the described systems and methods include a method for creating a photo-realistic 3D model of a scene based on complex SAR data associated with a scene. In some aspects, the described systems and methods include a method for identifying three-dimensional (3D) features and changes in SAR imagery.

Abstract: In an embodiment, an apparatus includes one or more timing components configured to generate a reference time signal based on a timing signal and a reference clock signal. The apparatus includes phase lock loop (PLL) configured to generate a synchronized output clock signal based on the reference clock signal and the reference time signal.

Abstract: A primary structure (100) for a spacecraft (200) including an interface ring (10) and a predetermined number of panels defining a box arranged to close an interior volume of the spacecraft. The box is connected to the interface ring. Side panels of the box are parallel to a geometric axis (A) of the interface ring, the interface ring is temporarily fastened to a system supporting the spacecraft in a launcher. Each panel is a one-piece panel formed by machining a metal material. The side panels at the base of the box are connected to the interface ring (10) via damping inserts (60).

Abstract: An on-orbit recycling method for a buffer foam of a cargo spacecraft includes the following steps: mechanically cutting a shaped PU foam into foam micro-blocks, and putting the foam micro-blocks into a packaging bag for packaging, where the packaging bag is filled with a foaming adhesive; the foaming adhesive includes a component A and a component B, which are independently packaged in a two-component packaging bag; and the component A and the component B are separated by a film; and squeezing the film between the component A and the component B, such that the two components are fully mixed, foamed and expanded to finally burst the two-component packaging bag, where after the packaging bag is burst, the foaming adhesive expands into gaps of the foam micro-blocks; and in a microgravity state of space, the foaming adhesive expands and fills uniformly in all directions and fully infiltrates the foam micro-blocks.

Abstract: [Problem] To provide a spacecraft having a more effective arrangement of amplifiers. [Solution] Provided is a spacecraft comprising: a main body having a housing space for housing an electronic device within; an oscillator configured to output a radio wave including a frequency in a predetermined frequency band; an amplifier disposed on an exterior of the main body so as to be exposed to space and configured to amplify the power of the radio wave output by the oscillator; and an antenna, disposed on the exterior of the main body, for emitting the radio wave to the outside at the power amplified by the amplifier.

Abstract: The present disclosure provides a time delay integration (TDI) sensor using a rolling shutter. The TDI sensor includes multiple pixel columns. Each pixel column includes multiple pixels arranged in an along-track direction, wherein two adjacent pixels or two adjacent pixel groups in every pixel column have a separation space therebetween. The separation space is equal to a pixel height multiplied by a time ratio of a line time difference of the rolling shutter and a frame period, or equal to a summation of at least one pixel height and a multiplication of the pixel height by the time ratio of the line time difference and the frame period. The TDI sensor further records defect pixels of a pixel array such that in integrating pixel data to integrators, the pixel data associated with the defect pixels is not integrated into corresponding integrators.

Abstract: A first network probe is associated with a first router and with a first end-point of the first router, and a second network probe is associated with a second router and with a second end-point of the second router. The first network probe periodically injects flag packets in parallel to the traffic of a communication tunnel between the first and second end-points, with each flag packet including timestamp information expressing a time reference for the injection of the flag packet. Information relating to a timing variation in traffic in the communication tunnel is gathered, with the timing variation being measured due to a difference between the timestamp information contained in the flag packets and timestamp information relating to the instant the flag packets were captured by the second probe. Possible congestion situations experienced by the communication tunnel are assessed as a function of the gathered information.

Abstract: A plasma arc torch assembly is capable of additively manufacturing articles. A device may additively manufacture at least a portion of an article using the plasma arc torch assembly. A device may deactivate at least one plasma arc associated with the plasma arc torch assembly. A device may perform plasma arc surface smoothing of the article using the plasma arc torch assembly.

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: A spacecraft trash disposal apparatus and method are disclosed. The spacecraft trash disposal apparatus includes an airlock, an inflatable trash enclosure holding trash, and a pressure regulating system. The spacecraft trash disposal apparatus permits wet and dry trash to be transported from the inside of a spacecraft via the inflatable trash enclosure holding the trash. The inflatable trash enclosure is ejected to the surrounding vacuum of space without causing trash or liquids to escape from the inflatable trash enclosure. The pressure regulating system permits reduction of pressure inside the inflatable trash enclosure from typically atmospheric to a lower pressure while the airlock is depressurizing without going to a full vacuum. This lower pressure is such that, at a given temperature, the liquid trash is prevented from boiling. The lower pressure permits a lightweight inflatable trash enclosure for low cost spacecraft trash disposal.

Abstract: In an embodiment, an apparatus includes an integrated circuit (IC) chip configured to receive a timing signal and a first reference clock signal and generate a first reference time signal based on the timing signal and the first reference clock signal. The IC chip is configured to generate a second reference time signal based on the first reference time signal and a second reference clock signal, different from the first reference clock signal The second reference time signal specifies a count of a number of cycles of the second reference clock signal starting from a particular cycle of the second reference clock signal. The IC chip is configured to synchronize one or more actions performed by the IC chip based on one or more of the first reference time signal or the second reference time signal.