Abstract: Techniques for articulating a sunshield to shade portions of a spacecraft are disclosed. In one aspect, a spacecraft includes a body and an articulable sunshield. The spacecraft is configured to operate in an orbital plane, such that the spacecraft has a yaw axis within the orbital plane and directed from a spacecraft coordinate system origin toward nadir, a pitch axis orthogonal to the orbital plane and passing through the spacecraft coordinate system origin, and a roll axis orthogonal to the pitch axis and the yaw axis and passing through the spacecraft coordinate system origin. The sunshield is configured to rotate about an axis substantially parallel to the pitch axis such that a selected location of an exterior portion of the body is shaded from the Sun by a surface of the sunshield irrespective of seasonal and diurnal variations in orientation of the spacecraft with respect to the Sun.

Abstract: An Unmanned Air Vehicle control station, comprising critical systems implementing safety involved functions, non-critical systems implementing non-safety involved functions and a gateway computer. The critical systems comprise at least two redundant critical computers, a redundant critical network and critical back-up network, and at least two redundant UAV-specific computers that implement UAV-specific functions and communicate with the UAV, wherein the at least two critical computers and the at least two UAV-specific computers are connected to the critical network and to the critical back-up network. The non-critical systems comprise at least one non-critical computer, and a non-critical network, wherein the at least one non-critical computer is connected to the non-critical network.

Abstract: Methods and systems for analyzing and processing digital data comprising a plurality of infra-red (IR) video images acquired by thermography system are used to compute video data from the raw and smoothed video data acquired for the performance of non-destructive evaluation. New video data types computed may include but are not limited to contrast evolution data such as normalized contrast, converted contrast and normalized temperature contrast. Additionally, video data types computed comprise surface temperature, surface temperature rise and temperature simple contrast.

Abstract: Unmanned aerial vehicles (1), and methods of flying such, comprising at least four rotors (2) arranged such that the plane of rotation of each rotor (2) is co-planar with a face of a notional polyhedron, and wherein each face of the notional polyhedron is co-planar with the plane of rotation of at least one rotor (2). Such methods comprise: a first step of flying the vehicle (1) using a first rotor set (2a-c) to provide lift; and, a second step using a second rotor set (2d-f) to provide lift; wherein, the second rotor set (2d-f) includes at least one rotor (2) that is not used to provide lift in the first step or that operates so that airflow through the rotor (2) is in the opposite direction to that through the rotor (2) during the first step; and, wherein at least one of the first and second sets (2a-c, 2d-f) comprises a plurality of rotors (2).

Abstract: A method to control operation of a robot includes generating at least one virtual image by an optical 3D measurement system and with respect to a 3D measurement coordinate system, the at least one virtual image capturing a surface region of a component. The method further includes converting a plurality of point coordinates of the virtual image into point coordinates with respect to a robot coordinate system by a transformation instruction and controlling a tool element of the robot using the point coordinates with respect to the robot coordinate system so as to implement the operation.

Abstract: In an on-orbit configuration, a spacecraft having a center of mass and a pitch axis passing through the center of mass includes a main body, a first solar array, and a first thruster is operable in a geostationary orbit with the first solar array deployed, proximate to a first north or south surface of the main body, such that a rotational axis of the deployed first solar array is substantially parallel to the pitch axis. The first thruster is disposed proximate to a second north or south surface of the main body, the first thruster having a thrust vector that is approximately coaligned with the pitch axis, the second surface being opposite to the first north or south surface. No solar array is proximate to the second surface.

Abstract: A method for controlling the temperature of an electric propulsion system. The electric propulsion system includes a discharge channel, an anode, a cathode, an injection system and a magnetic circuit. The injection system injects propellant gas into the discharge channel and the magnetic circuit has at least one magnetic winding to generate a magnetic field in the discharge channel. The temperature at a reference thermal point of the electric propulsion system is determined. The electric propulsion system is heated by the Joule effect by applying a current to the magnetic circuit when the determined temperature is below a minimum temperature predetermined during a stop phase of the electric propulsion system.

Abstract: Provided is a circuit structural body is formed into a shape including: A circuit structural body, including: a multilayer board, which includes a plurality of layers of a first to N-th tri-plate structural bodies each including a first to N-th (N is an integer of 2 or more) planar conductors; an interlayers connection conductor, which is configured to connect the first to N-th planar conductors to each other; and a side-surface ground conductor, which is formed on a side surface of the multilayer board, and is approximately parallel to and near the interlayers connection conductor.

Abstract: A low electrical and thermal resistance FinFET device includes a semiconductor body, a fin body on the substrate wafer, an isolation structure forming a fin connecting region, a gate dielectric on the fin body extending above the isolation structure, a FinFET gate electrode on the gate dielectric, a heavily-doped buried layer in the semiconductor body extending under said fin, and a vertical conductive region extending from the semiconductor body surface to the heavily-doped buried layer. Additionally, a fin body-to-buried layer implanted region disposed in the fin connecting region provides a low electrical and thermal resistance shunt from the fin body to the heavily-doped buried layer.

Abstract: A method for producing a light-emitting diode with a stacked structure, having a first region and a second region and a third region, wherein all three regions have a substrate and an n-doped lower cladding layer and an active layer generating electromagnetic radiation, wherein the active layer includes a quantum well structure, and a p-doped upper cladding layer, and the first region additionally has a tunnel diode formed on the upper cladding layer and composed of a p+ layer and an n+ layer, and an n-doped current distribution layer. The current distribution layer and the n-doped contact layer are covered with a conductive trace. At least the lower cladding layer, the active layer, the upper cladding layer, the tunnel diode, and the current distribution layer are monolithic in design. The second region has a contact hole with a bottom region.

Abstract: A method and system for rendering the quaternion shape and orientation of a three-dimensional structure. The proposed system and method keeps track of twist/roll angles and updates its effect on pitch and yaw orientations. The system relies on a single or multi-core optical fiber or multi-fiber bundle containing fiber Bragg grating sensors (FBGs) arrayed in rosettes at 45° deltas and spaced at uniform intervals along the entire length of the structure to be monitored. A tunable laser is used to interrogate the sensors using optical frequency domain reflectometry (OFDR), which detects shifts in the wavelength reflected by the sensors in response to strain on the fibers. Each sensor is continuously queried by software which determines the strain magnitude (?L/L) for each fiber at a given triplet. Given these measured strain values, the software implements a novel quaternion approach to rendering the 3D shape of the fiber including twist.

Abstract: A wheel alignment guide that provides a visual indication of the desired placement of an apparatus. The wheel alignment guide includes one or more body members defining an opening to surround a portion of the apparatus, such as a wheel. The wheel of the apparatus is disposed within the opening of the wheel alignment guide after a desired position of the apparatus is selected, and the wheel may be pivoted via concave edges of the one or more body members. If the apparatus is moved during operation, the apparatus may be repositioned due to the placement of the wheel alignment guide. Accordingly, the wheel alignment guide eliminates the need for inefficient markers and potentially-dangerous adhesives, particularly in an operating room.

Abstract: The present invention relates to a service satellite having a body, a controller and a docking unit. The docking unit includes at least two foldable, adjustable gripping arms pivotally mounted on the satellite body, each gripping arm being pivotable relative to the satellite body, and a gripping end at each free end of the gripping arms, wherein the gripping ends are adapted and configured to capture and grip a target portion of an orbiting satellite. Each gripping arm is controllable independently by the controller, which coordinates the motion of the arms.

Abstract: A capsulation satellite module for transferring a payload by an earth-launch vehicle to an outer space. The capsulation satellite module comprises a casing defining a hermetically sealed inner cavity therewithin. The casing includes a continuous sidewall and first and second cover assemblies mounted to axially opposite sides of the sidewall so as to delimit the hermetically sealed inner cavity within the casing. The first cover assembly defines a first gas chamber therein extending over the inner cavity of the casing. The second cover assembly defines a second gas chamber therein extending over the inner cavity of the casing. Each of the first gas chamber and the second gas chamber are fluidly connected to the sealed inner cavity and to each other through the sealed inner cavity to maintain predetermined pressure and temperature within the cavity.

Abstract: A method for operating an, at least temporarily, unmanned aircraft or spacecraft wherein a flight procedure of the aircraft or spacecraft is carried out in controlled airspace using a previously cleared flight plan, wherein a C2 link is at least temporarily unavailable, and wherein at least one sensor device of the aircraft or spacecraft identifies a dangerous and/or emergency situation which makes it necessary to deviate from the cleared flight plan. To have available a method which makes it possible for an at least temporarily unmanned aircraft or spacecraft to react independently to particular dangerous and/or emergency situations and to avoid damaging events, a control device of the aircraft or spacecraft independently uses a wireless data link to a supervisory authority in order to agree to a changed flight plan containing at least one change.

Abstract: Advanced environmental barrier coating bond coat systems with higher temperature capabilities and environmental resistance are disclosed. These bond coat systems can be applied to ceramic substrates such as SiC/SiC ceramic matrix composite substrates, and can provide protection from extreme temperature, mechanical loading and environmental conditions, such as in high temperature gas turbines. Example bond coat systems can include either an advanced silicon/silicide component, an oxide/silicate component, or a combination thereof.

Abstract: A Cooperative Service Valve includes a fitting connected to a valve body via a tube, a stem configured to fit within the valve body. The stem includes a stem first end having a first seal and configured to movably fit within a tube first end, a sealing portion connected to the stem first end and configured, in a first position, to provide a second seal between the sealing portion and an inner surface of the stem body, a fluid flow portion comprising openings for allowing liquid or gaseous media to pass through the Cooperative Service Valve when the stem is in a second position and a stem second end configured to secure a poppet guide, a poppet and a spring associated with the poppet that biases the poppet against a seal to yield a third seal. The first, second and third seals open and close in a particular order to allow or prevent fluid from flowing through the stem.