Abstract: An aircraft has a first antenna arrangement, a payload and a processing unit. The first antenna arrangement is designed to wirelessly receive electromagnetic signals. The processing unit is coupled to the first antenna arrangement, on the one hand, and to the payload, on the other hand. The processing unit is designed to modulate an electromagnetic signal received by the first antenna arrangement and thereby to generate a first modulated signal and to forward it to the payload. The payload is designed to use the first modulated signal as working signal. A radiofrequency power signal on an uplink is thus remodulated into a payload working signal, such that the payload working signal is able to be used directly by the payload without rectification into a DC voltage.

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.

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 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: 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 release system for the release of satellites from a launch vehicle is provided that includes: (i) a torsion bar, having a first end which is fixed by means of support means to a launch vehicle and is locked in rotation around a longitudinal axis of the torsion bar, and a second end which is connected by means of hinge means to the launch vehicle and is free to rotate around the longitudinal axis; (ii) at least one launch arm extending perpendicularly from the torsion bar and comprising (a) a torsion lever having a first end which is fixed to the torsion bar in an integral manner, and (b) a guide having a first end connected to a second end of the torsion lever, and a second free end; (iii) at least one slider which is fixed in an integral manner to a satellite to be launched and arranged to engage the guide in a sliding manner; and (iv) and a limit stop element designed to act upon the torsion lever to stop the rotation of the launch arm around the longitudinal axis.

Abstract: A layout method and apparatus based on a genetic algorithm are provided. The method includes: determining a gene code mode based on standard part information and layout part information; generating an initial population based on the gene code mode, the initial population including a plurality of gene codes, and the gene codes including standard code segments and layout code segments, and corresponding to layout schemes of standard parts and layout parts; acquiring fitness of each gene code; determining a dominant gene code based on the fitness; performing a double-point crossing operation and a double-point mutation operation on the dominant gene code to generate a next generation gene code, so as to form a dominant population; and if a preset termination condition is met, determining the layout scheme corresponding to the dominant gene code in the dominant population as a target layout scheme.

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 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: The present disclosure provides a system for printing at least a portion of a three-dimensional (3D) object. The system may comprise a source of at least one feedstock, a support for supporting at least a portion of the 3D object, a feeder for directing at least one feedstock from the source towards the support, and a power supply for supplying electrical current. The system may comprise a controller operatively coupled to the power supply. The controller may receive a computational representation of the 3D object. The controller may direct the at least one feedstock through a feeder towards the support and may direct electrical current through the at least one feedstock and into the support. The controller may subject such feedstock to Joule heating such that at least a portion of such feedstock may deposit adjacent to the support, thereby printing the 3D object in accordance with the computational representation.

Abstract: An example of an apparatus includes a spacecraft body and a solar array that is attached to the spacecraft body. In addition, a solar array spring element is configured to provide a force between the solar array and one or more components of a neighboring spacecraft in a stack of spacecraft.

Abstract: A process for the production of a layer structure of a nitride semiconductor component on a silicon surface, comprising: provision of a substrate having a silicon surface; deposition of an aluminium-containing nitride nucleation layer on the silicon surface of the substrate; optional: deposition of an aluminium-containing nitride buffer layer on the nitride nucleation layer; deposition of a masking layer on the nitride nucleation layer or, if present, on the first nitride buffer layer; deposition of a gallium-containing first nitride semiconductor layer on the masking layer, wherein the masking layer is deposited in such a way that, in the deposition step of the first nitride semiconductor layer, initially separate crystallites grow that coalesce above a coalescence layer thickness and occupy an average surface area of at least 0.16 ?m2 in a layer plane of the coalesced nitride semiconductor layer that is perpendicular to the growth direction.

Abstract: A method (50) for image acquisition by a spacecraft (10) comprising an observation instrument (20) and a laser transmission module (30), the method includes: acquiring an image of a calibration area referred to as a calibration image, by the observation instrument (S50), obtaining reference data associated with the calibration area (S51), determining a pointing error of a laser line of sight by comparing the calibration image and the reference data (S52), controlling the pointing of the spacecraft by correcting the pointing error, in order to point the laser line of sight towards a laser reception module (S53), and transmitting data to the laser reception module by the laser transmission module (S54).

Abstract: A method of calculating ionospheric scintillation includes calculating a motion-corrected perturbation of a GNSS radio signal received by a monitoring device deployed in an oceanic environment. The method includes calculating the ?? using the high rate phase of the GNSS signal adjusted by removing the change in distance between the monitoring device and the GNSS satellite. The calculating the ?? may further include passing the adjusted high rate phase through a high pass filter to remove a drift motion of the monitoring device. The method further includes calculating the S4 through calculating a tilt angle between the antenna of the monitoring device with the GNSS satellite and adjusting the antenna gain through known gain pattern of the antenna. The wave height of the oceanic environment may be calculated by detrending the antenna height to remove low frequency motion when a high rate position of the monitoring device is calculated.

Abstract: A synchronization correction method, a master device, and a slave device are provided. The method includes: transmitting a synchronization signal frame to a slave device during a first period of an ith second, where the synchronization signal frame includes a synchronization header, a first pulse per second (1PPS) signal, first time of date information, and first phase compensation information, where the first phase compensation information is configured to request the slave device to correct a transmission time point at which a first reference 1PPS signal is transmitted during a second period of the ith second; receiving the first reference 1PPS signal from the slave device during the second period of the ith second; and determining second phase compensation information transmitted to the slave device according to a receiving time point at which the first reference 1PPS signal is received during a first period of an (i+1)th second.

Abstract: An apparatus to separate water droplets from an air stream. The apparatus includes an elongated tube, a reservoir, and a helix structure. The elongated tube has a first end, a second end, a longitudinal axis, an inner surface, an inlet opening at the first end of the elongated tube, the inlet opening arranged to accept the air stream tangentially relative to the longitudinal axis, and an outlet opening at the second end of the elongated tube. The reservoir is positioned at a second end of the elongated tube. The helix structure is positioned within the elongated tube and includes an upper surface, a lower surface arranged opposite the upper surface, an outer edge, and a variable pitch along a length of the elongated tube, the variable pitch providing a variable interior angle between an inner wall of the elongated tube and the upper surface of the helix structure.

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: The present teachings is generally directed to facilitating satellite and terrestrial internet communications. In some embodiments, configuration information for configuring a communications device may be retrieved. The configuration information may be provided to the communications device, and the communications device may be caused to be configured based on the configuration information. Responsive to receiving a first data signal from a first satellite, the communications device may be configured to generate and output a second data signal based on the first data signal, the first data signal including first data encoded using one or more space-based communication protocols, and the second data including second data encoded using one or more terrestrial-based communication protocols.

Abstract: A device for creating a stiffened region on an outer structure of an aircraft for subsequently providing a service access if required is disclosed having an outer structure, a reinforcing plate which is mounted in a predetermined installation region on an inner side of the outer structure and forms a contact surface between the reinforcing plate and the outer structure. The reinforcing plate has a through-opening along the surface normal of the contact surface, and a connecting material which connects the reinforcing plate to the outer structure in an edge region of the contact surface by substance-to-substance bonding and/or by interlocking engagement.

Abstract: A telescopic mast is disclosed including coaxial segments that can be controlled from a stowed position to a deployed position, a set of guide systems disposed between the adjacent segments, a set of systems for synchronising the segments during deployment and a system for driving the segments from the stowed position to the deployed position. Each segment includes the same determined number of angle sections secured together and extending over the entire length of the segment, the number of angle sections being at least three, each segment having a cross-section forming a polygon whose angle sections occupy the vertices of the polygon, each angle having a flat central portion bordered by two side wings, the angle sections of two adjacent segments facing one another. Each guide system is disposed between two adjacent segments being fastened on one of the angle sections of one of the two adjacent segments.