Abstract: Automated methods and systems for tuning parameters of detectors based on metrics are provided. The tuning methods and systems include using machine learning to adjust registers used for setting detector parameters in an automated fashion to achieve optimal performance in a time-efficient manner. The tuning process can include determining available registers provided by the detector and setting values within those registers to a starting value. A binary search in either direction from the starting value is then performed to determine the limits of the parameter values for each register. The register values can then be optimized in view of selected metrics.

Abstract: Wire buffer systems that can buffer one or more wires are described. The wire buffer system can include a buffer tube. The buffer tube can include entry passages, exit passages, an outer cylinder, and an inner cylinder. The inner cylinder can be fixed in a position coaxial with the outer cylinder. Flexible wire guides can be coupled to the entry passage. The flexible wire guide can extend in a spiral around the inner cylinder and exit the buffer tube through the exit passage. The wire buffer systems can further include measurement systems. The measurement systems can include time-of-flight (TOF) sensors, linear rails, and carriages.

Abstract: A waveguide component for an orthomode junction or an orthomode transducer includes a common waveguide with a longitudinal direction, the common waveguide includes at least a first portion and a second portion with different cross-sections, and two coupling probes, each arranged orthogonally to the longitudinal direction. The coupling probes are further arranged to couple to different polarization components of an electromagnetic field present in the common waveguide. The second portion of the common waveguide has a cross-section with at most two-fold rotational symmetry.

Abstract: A system and method for transferring energy and mass (supplies) in low-gravity environments. The system comprises a launcher and a receiver. The launcher hurls a capsule at a high velocity such that, when caught by the receiver, a portion of the kinetic energy of the launched capsule is converted to potential energy and stored. The stored energy is used at the receiver end for applications such as living habitats, mining operations, life-support systems, etc. In some instances, a portion of the initial energy is used to lob the capsule back, if desired. Launchers and receivers can be set up in different spatial configurations in a low-gravity environment such as in a circle with a centrally located launcher, a launcher downstream of a chain of receivers, or other configurations.

Abstract: In one embodiment of the present disclosure, an antenna apparatus includes a housing assembly including a radome portion and a lower enclosure portion, wherein the radome portion and lower enclosure portion are couplable to form an inner compartment for housing antenna components of the antenna assembly, an antenna stack assembly disposed within the inner compartment, wherein the antenna stack assembly generates heat when in operation, and a heat transfer system within the inner compartment configured to facilitate the flow of heat toward the radome portion.

Abstract: The present disclosure presents lighting control systems and related methods. One such system comprises a light emitting device comprising a plurality of channels, each channel of the plurality of channels including one or more light emitting diodes configured to emit light at a respective predominant wavelength, and a plurality of direct current drivers, each direct current driver of the plurality of direct current drivers supplying power to a respective channel of the plurality of channels. The system further includes a router module that is configured to communicate with the light emitting device; and a graphical user interface configured to specify and control a plurality of parameters of each channel of the plurality of channels, wherein the plurality of parameters enable adjustment of a spectral content, intensity, and schedule of illumination, in addition to enabling a DC mode of operation or a pulse width modulation (PWM) mode of operation.

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: Measures, including a method, system, and computer program, for performing in-mission photogrammetry while an imaging platform is surveying a target environment. A plurality of images of the target environment are captured by the imaging platform. At the imaging platform, a representative subset of images is identified from the captured plurality of images. The imaging platform transmits the identified representative subset to a processing node. At the processing node, the transmitted representative subset is processed to generate a virtual model of the target environment.

Abstract: Systems, methods, and computer-readable media are provided for hybrid beamforming. An example method can include determining a plurality of digital beamforming weights associated with a plurality of digital beamforming paths between digital beamformers and groups of analog beamforming circuits in a phased array antenna, each digital beamforming path being coupled to a group of analog beamforming circuits and each analog beamforming circuit being coupled to a respective set of antenna elements of the phased array antenna, and determining analog beamforming weights associated with the groups of analog beamforming circuits. The analog beamforming weights are estimated to put analog beamforming paths associated with the groups of analog beamforming circuits in a desired phase and gain relationship with each other.

Abstract: In an embodiment, an apparatus includes an antenna assembly configured to transmit and receive beams in time-varying directions, and a beam steering controller configured to determine a first beam pointing vector by searching for a satellite from a plurality of satellites included in the communication system. The antenna assembly maintains a communication link with a satellite of the plurality of satellites by determining a plurality of beam pointing vectors that converge to increasing signal quality measurements, the satellite associated with the first beam pointing vector. The beam steering controller is configured to obtain, from the satellite, satellite ephemeris information of the satellite and one or more of remaining satellites of the plurality of satellites. The beam steering controller is configured to determine an orientation of the antenna assembly based on the satellite ephemeris information and the plurality of beam pointing vectors.

Abstract: A method of encrypting data, in particular encrypting data in dependence on a user verification confidence level. An encryption algorithm is provided, data is input into the encryption algorithm, along with a public key and an access structure comprising the user verification confidence level. The encryption algorithm is run to output a cypher text of encrypted data, whereby the access structure is embedded into the cypher text such that only an entity satisfying the access structure can decrypt the cypher text.

Abstract: A rodent protection insert for a structure opening including a flexible polymer foam sheet having a protective mesh sheet carried on a front side which moves independently of the foam sheet. A securing member maintains a mechanical connection between the flexible polymer foam sheet and the mesh sheet. An airflow port is disposed in the flexible polymer foam sheet that includes a removable plug for controlling airflow through the airflow port. A perimeter edge of the flexible polymer foam sheet compresses against and conforms to interior wall surfaces within a structure opening when mounted to form an airtight seal against the interior wall surfaces and hold the foam sheet in place. The protective mesh sheet engages the interior wall surfaces when the flexible polymer foam sheet is compressed in the structure opening so that the protective mesh sheet stabilizes and supports the flexible polymer foam sheet within the structure opening.

Abstract: A method for determining an electron density in a portion of an ionosphere includes: receiving, at a satellite in orbit, a signal transmitted from a ground-based transmitter through a portion of the ionosphere between the satellite and the ground transmitter; receiving, at the satellite, a reflection of the signal from a portion of the ionosphere above the satellite; and determining, based on the signal received at the satellite transmitted from the ground-based transmitter through the portion of the ionosphere between the satellite and the ground-based transmitter and the reflection of the signal received from the portion of the ionosphere above the satellite, an electron density of the portion of the ionosphere above the satellite.

Abstract: A multibeam antenna is provided comprising a direct radiating array, DRA, and a reflector arranged to reflect signals radiated from the DRA in a transmission mode and to reflect signals to the DRA in a reception mode. The antenna is a very high throughput satellite (VHTS) antenna providing global coverage with narrow, high gain beams.

Abstract: A satellite propellant tank includes a tank body and a dome attached to the tank body to enclose an interior volume for propellant storage. One or more cavities are formed in the dome. One or more propellant control components are located in the one or more cavities formed in the dome.

Abstract: For model predictive control for a spacecraft formation, a method calculates a virtual point that represents a plurality of spacecraft orbiting in a spacecraft formation. The method calculates an outer polytope boundary and an inner polytope boundary relative to the virtual point for a given spacecraft of the plurality of spacecraft. The method maneuvers the given spacecraft to within the inner polytope boundary using model predictive control (MPC) to minimize fuel consumption.

Abstract: A system, architecture and method for data handling, computation, and communication for Earth-based and space-based activities through the use of ground and space-based systems. The system architecture may include a Core Space Layer. The system architecture may further include an Earth User Layer, a Relay Layer, a Computing Layer, a Terrestrial Communications Layer, and a Space User Layer. The Computing Layer is a cloud-based architecture that serves to reduce bandwidth burdens on Earth-Space trunk by processing data into manageable streams of information. The Core Space Layer contains LEO satellites, one of which may act as a dedicated computing node. The Core Space Layer may operate in a public and/or private mode with a first constellation of LEO satellites operating in a private mode and a second constellation of LEO satellites operating in a public mode.

Abstract: Suspension system structures and methods are provided. A system as disclosed includes a supported object that is mounted to a post by a first two axis gimbal. The system also includes a reaction mass that is mounted to the post by a second two axis gimbal. The supported object and the reaction mass are connected to one another by a drive assembly. The drive assembly transfers a rotation of the reaction mass about either of the two axes in a first direction to a rotation of the supported object about a parallel axis in an opposite direction.

Abstract: A modular satellite apparatus for testing materials in a space setting is provided. The apparatus includes a lower member and an upper member, as well as rear support members, medial support members, front support members, and side members that each extend between the lower member and the upper member. They apparatus also includes attachment members connected to an external surface of the lower member and configured to connect to an external platform. The apparatus further includes a plurality of mounting members on an internal surface of the lower member or the side members, and a plurality of heatsinks. The lower member includes a plurality of heatsink receiving holes formed therein to receive portions of the heatsinks to connect the heatsinks to the lower member.