Abstract: A solar cell stack includes a first semiconductor solar cell having a p-n junction made of a first material with a first lattice constant, a second semiconductor solar cell having a p-n junction made of a second material with a second lattice constant, and the first lattice constant being at least 0.008 ? smaller than the second lattice constant, and a metamorphic buffer. The metamorphic buffer is formed between the first semiconductor solar cell and the second semiconductor solar cell. The metamorphic buffer includes a series of at least five layers. The lattice constant increases in the series in the direction of the semiconductor solar cell. The lattice constants of the layers of the metamorphic buffer are larger than the first lattice constant. Two layers of the buffer having a doping and the difference in the dopant concentration between the two layers being greater than 4E17 cm?3.

Abstract: A radiator for a geostationary satellite is disclosed having a radiative panel perpendicular to a radiation axis, and pivoting relative to the radiation axis, a mounting foot for the panel, a motor which rotates the mounting foot about a rotation axis, the radiation axis and the rotation axis being tilted relative to each other by an angle corresponding to the angle of the satellite's orbital plane relative to the ecliptic plane of the planet, and a guidance system for the panel, limiting rotation of the panel about the rotation axis, including a connecting arm pivoting relative to the satellite about a first axis and relative to the panel about a second axis concurrent with the first axis at a point of intersection of all the axes.

Abstract: A flap support for supporting a flap of a wing for an aircraft is disclosed and includes a load bearing fairing shell and a reinforcement structure at least partially received in the interior space of the fairing structure and mounted to the first and second side wall portions of the fairing shell. The fairing shell includes a front attachment device configured for attachment to a main wing, and the reinforcement structure includes an aft attachment device configured for attachment to the main wing. The flap support further includes a hinge device configured for forming an articulated connection to the flap.

Abstract: A method for forming a QCr0.8 alloy tapered cylindrical ring, including: heating a standard QCr0.8 alloy cylindrical part followed by upsetting and stretching at least twice to obtain a primary blank; heating the primary blank followed by upsetting and chamfering to obtain a secondary blank, where a diameter of a top end is greater than that of a bottom end; subjecting the secondary blank to backward extrusion to form a preform; machining the preform to remove a flash and a bottom residue; subjecting a bottom end of the preform to local bulging to enable a shape and a size thereof to match that of a drive roller in a forming tooling, so as to form a profiled ring blank; and rolling the profiled ring blank by a radial-axial ring rolling machine with the forming tooling to form the tapered cylindrical ring.

Abstract: An antenna includes ribs that have been folded to fit within a frame, a conductive mesh coupled to the ribs, an arm that has been folded to fit within the frame, and a feed disposed at a distal end of the arm.

Abstract: Technology is disclosed for a dispenserless multi-satellite launch configuration in which multiple satellites are interconnected to form a composite beam structure that provides stability independently of the launch vehicle. When in the launch configuration, the satellites are formed into a bundle, where each satellite connects by one or more simple connector along the edges of its inner facing vertical side to the satellite adjacent on each side. This composite beam structure provides a stable launch configuration independently of the launch vehicle. Each of the satellites also has one or more connectors along the bottom edge of the inner facing vertical side allowing the bundle to be attached to a ring type launch vehicle interface. Once launched, the satellites can be dispensed by releasing the connector.

Abstract: A ground antenna determines the current time and its own position from received signals that were transmitted by artificial earth satellites for communication. A high-gain multi-beam electrically-steered antenna is combined with a processing system to measure the angles between two or more satellites and determine the present distance to each satellite by the information broadcast on the TT&C channel. The knowledge of the angles and distances, as well as the trajectory of the satellites, can be combined with their locations as predicted by the satellite ephemeris data to triangulate the location of the receiver. This system is different from conventional GPS antennas because it does not require the cooperation of active communication with the satellites to derive a location estimate. The location is computed by the ground terminal, not by the satellite.

Abstract: A vacuum chamber may include an ambient side and a vacuum side. The vacuum chamber may be configured to carry a feedthrough that may include a hollow tube, a first O-ring captured by a first recess within the hollow tube and a rod extending through the hollow tube. The outer circumference of the rod may be configured to contact an entirety of an inner circumference of the first O-ring. A vacuum fitting having an inner circumference may be fixedly secured to the hollow tube. The rod may be operable to be linearly movable within the hollow tube and may be rotatably movable about an axis within the hollow tube. An object may be secured to the rod and may be linearly and rotatably moved within the vacuum chamber.

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: The present disclosure provides a system for printing 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 such 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 such feedstock through a feeder towards the support and may direct electrical current through such feedstock and into the support. The controller may subject such feedstock to heating such that at least a portion of such feedstock may deposit adjacent to the support. The controller may direct deposition of additional portions adjacent to the support and may direct an additional feedstock through such feeder and subject to heating.

Abstract: A system for injection of a useful radiation beam into an optical fiber is disclosed including a secondary radiation source, which is connected to the optical fiber such that a secondary radiation beam leaves by an end of the optical fiber. A variable deviation device, for deviating the useful radiation beam towards the end of the optical fiber, an optical detection assembly, identifying the direction of the secondary radiation beam, and an injection controller, for controlling the variable deviation device depending on the direction of the secondary radiation beam. The secondary radiation may be made up by an amplified spontaneous emission from a laser amplifier which is used for amplifying the useful radiation. The injection system may advantageously be used in a terminal for optical telecommunication by laser signals.

Abstract: Disclosed embodiments relate satellites using a Software-Defined Radio (“SDR”) system. In one example, a geostationary (GEO) satellite includes an antenna system including multiple antennas, each configured to provide a spot beam having an adjustable throughput for a terrestrial coverage area while the antenna is in an active state and the satellite is in orbit above the Earth, a front-end subsystem communicatively coupled to the antenna system having an input side including an input filter and an analog-to-digital converter, and an output side including an output filter and a digital-to-analog converter, and a software defined radio (“SDR”) communicatively coupled to the antenna system via the front-end subsystem. The SDR, in response to a surge modification request, modifies a throughput of each active antenna by increasing or decreasing a share of a satellite power budget allotted to the antenna by deactivating or activating a previously active or previously inactive antenna, respectively.

Abstract: In an embodiment, an apparatus includes an integrated circuit (IC) chip configured to receive a timing signal and a reference clock signal and generate a first reference time signal based on the timing signal and the reference clock signal. The IC chip includes a clock phase lock loop (PLL) configured to generate and provide a second reference clock signal at a higher frequency than the reference clock signal; the IC chip is further configured to generate a second reference time signal based on the first reference time signal and the second 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 second reference time signal has a finer count resolution than the first reference time signal for a same time period.

Abstract: A uniaxial optical multi-measurement imaging system includes an imaging lens column having an optical axis and configured to receive light from a scene from a single viewpoint. The imaging system also includes a light redistribution optic (LRO) in the shape of a thin pyramid shell with an apex. The LRO is centered along the optical axis with the apex pointing towards the imaging lens column. The LRO has planar sides with each side angled 45 degrees with respect to the optical axis and configured to reflect and transmit the light. The imaging system also includes a circumferential filter array (CFA) concentrically located around the LRO. The CFA is configured to filter the light reflected from or transmitted through the LRO. The imaging system includes multiple image sensors, each positioned to receive the light reflected from or transmitted through the LRO.

Abstract: In embodiments, a uniaxial optical multi-measurement sensor comprises a sensor housing having a center axis and a cylindrical surface and an array of electrically coupled light-sensitive pixel elements attached to the cylindrical surface. Each pixel element is positioned having its light-sensitive side facing towards the center axis. In this embodiment, a conical light redistribution optic is positioned along the center axis to direct or reimage uncollimated light entering the sensor housing onto the pixel elements. Also, in this embodiment, the pixel elements are positioned relative to the light redistribution optic to measure or image two or more properties of the uncollimated light entering the sensor housing of a single scene and from a single viewpoint.

Abstract: A 3D printer can print a structure by depositing material into a weld pool that is moving relative to a workpiece. An electrode wire can supply energy to the weld pool while being fed at a first feed rate into the weld pool. A second wire can be fed into the weld pool at a second feed rate to deposit additional material and thereby speed up the overall material deposition rate. All of the energy in the weld pool may be supplied by the electrode wire. The printer can dynamically control the first feed rate and the second feed rate during printing. A mathematical model can be used to determine the second feed rate as a function of the first feed rate, the energy put into the weld pool, and the print head travel speed. The second feed rate may optimize the material deposition rate according to the model.

Abstract: An aperture stop exploitation camera comprises an imaging lens column positioned along an optical axis and configured to transmit light from a scene from a single viewpoint and converge the light as it passes through the aperture stop. Also, the camera comprises a light redistribution optic (LRO) that is a thin V-shape having an apex. The LRO is centered along the optical axis with the apex pointing towards the imaging lens column. The LRO has two planar sides with each side angled 45 degrees with respect to the optical axis and each side configured to reflect and transmit the light transmitted from the imaging lens column into three independent, spatially separate images, each retaining all the spectral, polarimetric, and relative intensity information of the light from the scene. The camera comprises three image sensors, each image sensor positioned to receive one of the three independent, spatially separate images.