Abstract: Systems and methods of manufacture of radiator fins. In one embodiment, a radiator fin made of carbon fiber is provided. In one aspect, the radiator fin is made of carbon fibers forming an interlaced pattern. In another aspect, the interlaced carbon fiber radiator fin is attached directly to a heat pipe, the heat pipe connected to a heat source.

Abstract: A method is provided for partially or completely manufacturing a spacecraft in an extraterrestrial environment, thereby allowing the spacecraft to be transported from Earth in a form that is better able to withstand forces associated with a rocket launch and traversing Earth's atmosphere. Such a form may allow the spacecraft to be significantly smaller than it would need to be if it had to be in a completed form at the time of transportation. Two forms of spacecraft that may be built by such method are also disclosed. In an aspect, the disclosed devices may be configured to be manufactured, assembled, deployed, and utilized in a timely and efficient manner.

Abstract: Solar cell assembly that includes at least first and second solar cells arranged adjacent each other to form a row. First electric contact pad of first solar cell is positioned adjacent to second electric contact pad of second solar cell and second electric contact pad of first solar cell is positioned adjacent to first electric contact pad of second solar cell. Interconnectors connect each first electric contact pad of first solar cell with adjacent second electric contact pad of second solar cell and each second electric contact pad of first solar cell with adjacent first electric contact pad of second solar cell. Each interconnector is sized so that, between adjacent cells, interconnector is below first electric contact pad. Cover glass is provided on a front surface of each solar cell, and each interconnector is provided with a cover member covering a front surface of interconnector.

Abstract: A cleaning assembly for leading edges of airfoils, in particular airfoil profiles of aircraft or spacecraft, has a cleaning device that is provided with at least one cleaning member and is intended for applying mechanical pressure to a planar region of an airfoil, and has a drive having at least one drive element, which drive moves the cleaning device along the surface to be cleaned. It is proposed to adhesively hold the cleaning device on the airfoil by the at least one cleaning member and/or for the at least one cleaning member to have a sticky surface and for the at least one cleaning member to be dimensionally stable and have flexible contours.

Abstract: A vehicle for intercepting a target object orbiting in space is provided, comprising a launching portion for driving the vehicle into an orbit, and an interception portion for intercepting a target object when the vehicle is in orbit, wherein the interception portion comprises means for engaging with the target object and wherein the launching portion is arranged to drive the vehicle into a first elliptical orbit and the vehicle is arranged to adopt a second elliptical orbit when engaged with the target object in which the first elliptical orbit is arranged so as to intersect the orbit of the target object at an interception point, and the second elliptical orbit is such that the vehicle is arranged to move from the interception point towards the Earth's atmosphere when engaged with the target object.

Abstract: Apparatus and methods are disclosed for obtaining a correlation function between a Direct Sequence Spread Spectrum (DSSS) signal and a spreading code. A plurality of code replica samples are stored in memory at a relatively low sampling rate compared to the sampling rate at which the input DSSS signal is sampled. A correlation operator is obtained by reproducing the stored code replica samples, in order to obtain a correlation operator with the same number of samples as the block of DSSS signal samples currently being processed. For example, when the sampling rate of the DSSS signal is equal to an integer N multiple of the sampling rate used for the code replica samples, the stored replica samples are reproduced N times to obtain the correlation operator. The correlation operator is then multiplied by the block of DSSS signal samples and integrated to obtain a correlation function.

Abstract: A system for producing and dispensing pressurized hydrogen includes: a hydrogen generator, in particular an electrolyser, a hydraulic drive, two or more hydrogen storage tanks, and a hydrogen dispensing unit, wherein each of the hydrogen storage tanks is capable of discharging hydrogen at a constant pressure by movement of an internal piston, wherein at least one of the hydrogen storage tanks is arranged to act as compressor by actuation of the internal piston by the hydraulic drive, and wherein at least one of the hydrogen storage tanks is arranged to act as a constant pressure tank for storing and discharging hydrogen at a constant pressure.

Abstract: The invention relates to a microwave circular polarizer including: a first outer conductor; a second outer conductor connected to the first outer conductor forming a first step discontinuity therewith; and a third outer conductor connected to the second outer conductor forming a second step discontinuity therewith. An inner conductor is provided which extends inside and is spaced apart from the first, second and third outer conductors. The first and second outer conductors are axially asymmetric with respect to the inner conductor, and the third outer conductor is axially symmetric with respect to the inner conductor. The microwave circular polarizer includes first and second rectangular waveguide ports in signal communication with an internal cavity through, respectively, a first rectangular aperture and a second rectangular aperture formed through the first outer conductor. The microwave circular polarizer further includes a first septum and a second septum.

Abstract: The disclosure concerns a joint (1) for releasably connecting a first space craft element (2) to a second space craft element (3) comprising a first flange (4) on the first space craft element (2) and a second flange (5) on the second space craft element (3). The joint (1) comprises first shoe portions (6) and second shoe portions (13) formed as sectors of a solid of revolution, keeping the flanges (4, 5) together in a longitudinal direction, The shoe portions are positioned next to each other in a circumferential direction the reference to a longitudinal direction of the space crafts. The first shoe portions being arranged to, at a prevailing Coulomb friction, not allow self-locking and the second show portions are arranged to allow self-locking.

Abstract: A spacecraft includes payload equipment and bus equipment, each of the payload equipment and the bus equipment being coupled with a secondary structure arrangement. The spacecraft is configured to structurally interface with a launch vehicle upper stage only by way of an exoskeletal launch support structure (ELSS) that provides a first load path between a launch vehicle upper stage and the secondary structure arrangement. The spacecraft is configured to deploy from the launch vehicle upper stage by separating from the ELSS. In some implementations, the first load path is the only load path between the spacecraft and the launch vehicle upper stage, and substantially all of the ELSS remains with the launch vehicle upper stage. Because the secondary structure may be substantially less massy then the ELSS, subsequent orbit raising maneuvers may then be executed with a spacecraft having a reduced dry mass.

Abstract: Aerogels, aerogel composites and methods of making the same are discussed. One example method can include the act of creating a Boehmite colloid and adding a hydrolyzed silicon precursor to form a sol. A reinforcement can be infused with the sol, gelled to form a gel, then dried to form an aerogel composite. Such a method can also include the acts of performing one or more solvent exchanges and subjecting the gel composite to subcritical drying. Additionally, such a method can include the act of heat treating the aerogel composite. The aerogel composite can be used in high temperature, flexible seals capable of withstanding temperatures, pressures, and compression levels associated with aerodynamic heating generated during flight and in aerospace applications. The aerogel composite also can be used in thermal protection systems designed for fire protection for structures or in personnel fire protective equipment.

Abstract: An actuating apparatus for a polyphase motor includes five phase terminals for connecting of in each case one phase of the polyphase motor, a high terminal for applying a supply voltage (UB), a low terminal for applying a reference potential of the supply voltage (UB), a control device, wherein the control device is adapted, in four of the five phase terminals, to impress a pulse-width-modulated voltage pattern by connecting the phase terminals to the high terminal or the low terminal so that in the first phase terminal, an evaluation signal which is dependent on the angle of rotation of the polyphase motor is produced, and wherein the control device is adapted to determine the angle of rotation and/or a commutation condition of the polyphase motor from the evaluation signal.

Abstract: A bi-state driver circuit for switching an output terminal between a first predetermined voltage level and a high impedance state, which involves a first string of transistors connected between the output terminal and the first predetermined voltage level at least a first transistor arranged closer to the first predetermined voltage level, a second transistor arranged closer to the output terminal, a voltage divider circuit connected between the output terminal and a voltage level of a control signal attaining voltage levels between the first predetermined voltage level and a second predetermined voltage level, including at least one intermediate node having an intermediate voltage level between a voltage level of the output terminal and the voltage level of the control signal, and a second string of transistors connected between the intermediate node of the voltage divider circuit and the second predetermined voltage level, and including at least a third transistor.

Abstract: A solar cell stack having a first semiconductor solar cell that has a p-n junction of a first material with a first lattice constant and a second semiconductor solar cell that has a p-n junction of a second material with a second lattice constant. The solar cell stack has a metamorphic buffer that includes a sequence of a first, lower layer and a second, center layer, and a third, upper layer, and includes an InGaAs or an AlInGaAs or an InGaP or an AlInGaP compound. The metamorphic buffer is formed between the first and second semiconductor solar cells and the lattice constant in the metamorphic buffer changes along the buffer's thickness dimension. The lattice constant of the third layer is greater than the lattice constant of the second layer, and the lattice constant of the second layer is greater than the lattice constant of the first layer.

Abstract: A prime mover is combined with a flywheel storage device and a control system to implement a flywheel pulse and glide system in a vehicle. In one embodiment, the control system is configured to cycle power delivery between the prime mover and the flywheel storage device to power the vehicle. The prime mover, when activated by the control system, is configured to power the vehicle and spin up the flywheel storage device to capture a sufficient amount of energy.

Abstract: An energy-saving loop heat pipe apparatus and an application. The loop heat pipe apparatus comprises a capillary pump component and an evaporation unit component. The loop heat pipe apparatus further comprises at least one heat exchanger disposed between the capillary pump component and the evaporation unit component for heating, by using heat of a circulating working medium in the loop heat pipe, the circulating working medium about to enter the evaporation unit component. By providing heat exchangers between the evaporation unit component and the capillary pump component, the energy-saving loop heat pipe apparatus may use heat of a gas-phase working medium flowing out of the evaporation unit component to heat a liquid-phase working medium about to enter the evaporation unit component, so that waste heat is utilized to the fullest extent and energy is saved.

Abstract: A service satellite for providing station keeping services to a host satellite has a body, and a gripping mechanism attached to the body. The gripping mechanism is adapted to attach to an interface ring extending from an external surface of the host satellite to form an interconnection between the host satellite and the service satellite through the externally extending interface ring. Attaching the gripping mechanism to the interface ring forms an interconnected unit having a combined center of mass. The service satellite has at least two movable thrusters and at least one controller. The at least one controller maintains the interconnected unit in a substantially stationary orbit by selectively orienting the two thrusters such that the thrust vectors from the two thrusters do not pass through the combined center of mass, and are each offset from the combined center of mass.

Abstract: A method for optimizing the architecture of the power supply of a load, includes the following steps: determination of a mission profile (16) sizing according to the power required by the load over time; definition of the sources of energy storage for hybridization; association of a characteristic behavior model with each source of energy storage; determination of the couples of sources of energy storage that can generate the mission profile with a minimum mass; and determination, from the potential couples of sources of energy storage, of the couple with the weakest mass.

Abstract: A method is provided for the nanostructuring and oxidation of a surface, which has an anodizable metal and/or an anodizable metal alloy, both being coated with an oxide layer, by way of a laser or particle radiation in an inert or reactive atmosphere and subsequent anodization. As a result, oxide nanostructures are formed on the entire surface, in titanium or titanium alloys in the form of nanotubes.

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.