Abstract: A stacked multi-junction solar cell with a first subcell having a top and a bottom, and with a second subcell. The first subcell is implemented as the topmost subcell so that incident light first strikes the top of the first subcell and after that strikes the second subcell through the bottom. A first tunnel diode is arranged between the bottom of the first subcell and the second subcell. A window layer is arranged on the top of the first subcell, and the band gap of the window layer is larger than the band gap of the first subcell. A cover layer is arranged below metal fingers and above the window layer, and an additional layer is arranged below the cover layer and above the window layer. A thickness of the additional layer is less than the thickness of the window layer.

Abstract: The present disclosure is directed a process for the electrolytic polishing of a metallic substrate, including the steps of (i) providing an electrolyte in an electrolytic cell having at least one electrode, (ii) disposing a metallic substrate as an anode in the electrolytic cell, (iii) applying a current at a voltage of 270 to 315 V from a power source between the at least one electrode and the metallic substrate, and (iv) immersing the metallic substrate in the electrolyte, wherein the electrolyte includes at least one acid compound, at least one fluoride compound, and at least one complexing agent.

Abstract: A structural component, in particular for an aircraft, spacecraft or rocket, has a ply of fiber reinforced polymer; a first carbon nanotube mat; and a metallic layer, wherein the carbon nanotube mat and the metallic layer are arranged on the ply of fiber reinforced polymer to form a hybrid lightning strike protection layer. A component for manufacturing such a structural component, a method for manufacturing a component of this type, a method for manufacturing a structural component and an aircraft or spacecraft with such a structural component are described.

Abstract: A method of localizing a device within an environment includes a step, in which a first location information is acquired that is representative of a first specified position. In another step, a first sensor information is acquired that is representative of the first specified position. In another step, the first sensor information is allocated to the first location information in order to generate a first condition information that is unique for the first specified position. In another step, a knowledge base is provided which includes the first condition information. In another step, the device provides a current sensor information indicating a current condition of the environment present at the current position of the device. In another step, the device is localized based on a matching between the current sensor information and the plurality of condition information.

Abstract: A spacecraft includes a propulsion subsystem including at least two electric thrusters, an electrical interface assembly that couples electrical conductors from the thrusters to a spacecraft harness, a pneumatic interface assembly that controls flow rate of propellant to the thrusters and a thruster support module (TSM) including a pointing arrangement and a mounting arrangement. A proximal portion of the mounting arrangement is coupled with a distal portion of the pointing arrangement; the at least two electric thrusters are disposed on a distal portion of the mounting arrangement; the electrical interface assembly and the pneumatic interface assembly are disposed on the proximal portion of the mounting arrangement. The mounting arrangement is configured to limit heat transfer between the thrusters and (b) one or more of the proximal portion of the mounting arrangement, the electrical interface assembly and the pneumatic interface assembly.

Abstract: A spacecraft includes a propulsion system including an inert gas stored in a set of pressurant tanks, one or more electric thrusters operable with the inert gas, one or more cold gas thrusters operable with the inert gas; and a pneumatic arrangement including commandable valves.

Abstract: In an embodiment, an apparatus includes a first integrated circuit (IC) chip configured to receive a timing signal and a reference clock signal; a second IC chip configured to receive the timing signal from the first IC chip and the reference clock signal; and a third IC chip configured to receive the timing signal from the second IC chip and the reference clock signal. The second IC chip is electrically coupled between the first and third IC chips. The first, second, and third IC chips are configured to generate respective first, second, and third reference time signals based on the timing signal and the reference clock signal. Each of the first, second, and third reference time signals is associated with a count of a number of cycles of the reference clock signal starting from a same particular cycle of the reference clock signal.

Abstract: The disclosure provides an apparatus for depositing poly(p-xylylene) onto a component (4). The apparatus comprises (i) a platen, (ii) an electrode, and (iii) a first feed means. The platen comprises an electrically conductive material, is electrically connected to an electrical power supply and is configured to support a component. The electrode is electrically insulated from the platen. The first feed means is configured to feed a poly(p-xylylene) monomer to the platen. Furthermore, the component either comprises an electrically conductive material or consists of an electrically insulating material. If the component consists of an electrically insulating material the electrical power supply is an alternating current power supply and generated an alternating electrical field which couples to the component, and is thereby able to penetrate through the component to create the plasma.

Abstract: In embodiments, an apparatus includes a beamformer including a plurality of inputs and a plurality of outputs, a plurality of input vias, and a plurality of output vias. Each input of the plurality of inputs electrically couples to a respective input via of the plurality of input vias. Each output of the plurality of outputs electrically couples to a respective output via of the plurality of output vias. The beamformer is included in a first layer, wherein the plurality of input vias are configured to electrically couple to termination trace ends of a plurality of hierarchical networks provided on at least second and third layers, and wherein the plurality of hierarchical networks comprises at least three hierarchical networks.

Abstract: A propulsion system for a spacecraft includes at least one chemical propulsion engine, at least one electrical propulsion engine, and a propellant feed system that includes a propellant supply system including at least one tank to store a common propellant. The propellant supply system is configured to deliver a controlled flow of the common propellant to both the chemical propulsion engine and the electrical propulsion engine. Also disclosed is the use of a common propellant in a spacecraft and a method of providing a common propellant to an electrical and a chemical propulsion engine.

Abstract: A Hall-effect thruster assembly includes a plurality of magnetic sources for creating a magnetic circuit. The plurality of magnetic sources are positioned between a first end and a second, opposite end of the Hall-effect thruster. The plurality of magnetic sources define a longitudinal axis extending through the first end and the second end. The first end is configured as a discharge end. A mount assembly is coupled to the second end. The mount assembly is configured to secure the plurality of magnetic sources to a spacecraft. A magnetic element is supported by the mount assembly. The magnetic element is positioned relative to the plurality of magnetic sources by the mount assembly.

Abstract: A propulsion system for a spacecraft includes at least one electrical propulsion engine comprising at least one neutraliser; and a pressurant gas system comprising a pressurant gas which is fed directly into the at least one neutraliser.

Abstract: As an improvement to existing matrix-like power/communications systems, a decentralized array of power and communications components defining a self-configuring modular electrical system which is comprised of components that are completely scalable, easily replaceable, intelligent and combinable in a series, parallel, bypassed state or even capable of elegantly switching in a spare cell(s) to replace a dead cell while interfacing with common battery power chemistry, an external power supply input, a standardized bi-directional data communication input and is combinable and arrangeable into practically any mechanical footprint whereby energy density and communications capability is maximized along with simplicity in accordance with weight and balance considerations and integrated as an autonomous system at the lowest possible cost while being survivable in the harshest of environments including physical shock, vibration, vacuum, radiation, thermal, and electromagnetic interference and providing a communication

Abstract: A sensor system to provide data for use to control manufacture of an optical fiber in microgravity including a diameter sensor to monitor a diameter of a fiber drawn from a preform material, a tension sensor to monitor tension of the fiber as the fiber is pulled from the preform material to a storage device and a controller in communication with at least one of the diameter sensor and the tension sensor to evaluate sensor data to determine at least one of a speed and rate at which the fiber is pulled from the preform material.

Abstract: An electric thruster comprises a propellant delivery system, wherein the propellant delivery system comprises: a pipe for carrying propellant; a valve which is adapted to adjust a volume or mass flow of the propellant in the pipe; and an expansion actuator which is adapted to actuate the valve for adjusting the volume or mass flow of the propellant. The electric thruster further comprises at least one tank which is adapted to receive propellant for the electric thruster; and a discharge chamber. The at least one tank thereby at least partially encloses an end of the discharge chamber and/or an element thermally coupled with the discharge chamber, and the valve of the propellant delivery system is arranged between the tank and the end of the discharge chamber.

Abstract: A Metalorganic chemical vapor phase epitaxy or vapor phase deposition apparatus, having a first gas source system, a reactor, an exhaust gas system, and a control unit, wherein the first gas source system has a carrier gas source, a bubbler with an organometallic starting compound, and a first supply section leading to the reactor either directly or through a first control valve, the carrier gas source is connected to an inlet of the bubbler through a first mass flow controller by a second supply section, an outlet of the bubbler is connected to the first supply section, and the carrier gas source is connected to the first supply section through a second mass flow controller by a third supply section, the first supply section is connected to an inlet of the reactor through a third mass flow controller.

Abstract: A modular and scalable system to transfer space articles between space orbits. In one embodiment, the system employs a rendezvous vehicle which docks with a space article in an initial orbit, the connected stack then docking with a locomotive vehicle which maneuvers to a targeted orbit where the space article is detached. In one feature, the rendezvous vehicle and locomotive vehicle use a common propellant and the space article is a satellite.

Abstract: A scalable, extensible, multi-tenancy multi-mission configurable spacecraft system is provided that allows applications to be deployed and managed across many spacecraft. One embodiment includes a plurality of satellites in orbit, where each satellite includes an antenna, a memory configured to store a non-virtualized operating system and one or more software applications, and a processor connected to the antenna and the memory. The processor is configured to run the non-virtualized operating system and to run the one or more software applications. The processors and the applications can be managed by ground terminals or other satellites.

Abstract: A scalable plurality of shape memory alloy (SMA) elements are configured to provide a continuous rotation actuator system. The plurality of SMA elements are coupled to a Ring Gear element, as well as to a Sun Gear element and a provision for thermal cycle return assist of the SMA elements. A plurality of Transmission elements provide for controlled rotary actuation in a desired direction with lock capability that provides for continuous rotary motion even as the SMA elements undergo reciprocating rotary action during their thermal cycling without running into system component rotation limits. The innovation distinguishes over other innovative approaches by way of at least the Ring Gear element, the manner of lock control, and the return assist element.

Abstract: In an embodiment, an apparatus includes a first integrated circuit (IC) chip configured to receive a timing signal and a reference clock signal; a second IC chip configured to receive the timing signal from the first IC chip and the reference clock signal; and a third IC chip configured to receive the timing signal from the second IC chip and the reference clock signal. The second IC chip is electrically coupled between the first and third IC chips. The first, second, and third IC chips include respectively first, second, and third phase lock loop (PLL). The first, second, and third IC chips are configured to generate respective first, second, and third reference time signals based on the timing signal and the reference clock signal. The first, second, and third PLLs are synchronized to each other based on the respective first, second, and third reference time signals.