Abstract: A solar array structure for a spacecraft includes one or a pair of flexible blanket or other foldable solar arrays and a deployable frame structure. The deployable frame structure includes a T-shaped yoke structure, a T-shaped end structure, and one or more rigid beams, the T-shaped yoke structure connectable to the spacecraft. When deployed, the frame structure tensions the flexible blanket solar array or arrays between the T-shaped yoke structure and the T-shaped end structure. When stowed, the flexible blanket solar array or arrays are folded in an accordion manner to form a stowed pack or packs between the cross-member arms of the T-shaped yoke structure and the T-shaped end structure, also stowed in its own Z-fold arrangement. The cross-member arms of the T-shaped end structure can include a solar array that can provide power before deployment while the flexible blanket solar array is stowed.

Abstract: An on-orbit servicing spacecraft includes an engagement system to engage a space vehicle or object to be serviced or tugged, so as to form a space system, and an electronic reaction control system to cause the spacecraft to rotate about roll, yaw, and pitch axes to control attitude and displacement along given trajectories to cause the spacecraft to carry out given maneuvers.

Abstract: A system includes a plurality of satellites in orbit around a celestial body in a plurality of orbital planes. Each satellite includes an imaging device having a field of view (FOV) to capture an image of a sky that includes celestial image features of resident space object (RSO), stars, and/or planets. The satellite processor is configured to receive image data from sensors in the imaging device, to increase a positional detection accuracy of the celestial image features by defocusing imaging optics of the imaging device, to capture image data in a volume of the sky as the FOV of the imaging device on each satellite moves in an orbital plane, and generate by a centralized computer at least 1,000 celestial image features using the image data transmitted from each of the satellites.

Abstract: Disclosed are a polymer-stabilized liquid crystal composition and the use thereof. The composition comprises one or two polymerizable compounds represented by general formula I: (I), and further comprises a negative dielectric anisotropy liquid crystal composition, wherein the negative dielectric anisotropy liquid crystal composition has a dielectric anisotropy of ????1.5; and the added amount of the polymerizable compound(s) represented by general formula I is 0.1-0.5% of the total mass of the negative dielectric anisotropy liquid crystal composition. A polymer film formed after the polymerization of the provided liquid crystal composition containing the polymerizable compound(s) has a very good uniformity, such that the problem of liquid crystal displays having poor display can be improved.

Abstract: An apparatus and a method of use are disclosed herein. The apparatus comprises a disaggregated fault tolerant backplane having a front side and a back side with at least two daughter card slots configured on the front side and configured to receive slot fanout signals over the backplane. The apparatus further comprises at least two switch boards (SBs) configured to provide electrical power to the at least two daughter card slots and at least one main fanout board (MFB) configured to send and receive SB control signals to and from the at least two SBs. The at least one MFB connects to the backplane through at least one MFB connector configured on the back side of the backplane. In one embodiment, the MFB receives control signals from the daughter card slots and sends slot fanout signals to the daughter card slots.

Abstract: A rocket engine is provided with a propellant valve controlling the output of a propellant tank. The valve is configured to induce a vortex in the propellant as it passes the propellant valve. Plural rocket engines may be supplied by a single valve, the valve inducing a vortex in the propellant which is then supplied to plural propellant lines configured to enhance the vortex induced by the valve.

Abstract: A three-dimensional print head apparatus including a hopper, a nozzle, a barrel, and a heating system. The apparatus may further include a fume extraction system and a dry air purge system. The hopper may have a cavity and a lower aperture. The nozzle may have an upper aperture and a lower aperture. The heating system may be positioned along the barrel, and the dry air purge system may be in fluid communication with the hopper.

Abstract: A cryogenic engine for a space apparatus is provided. The cryogenic engine includes an injector body, a thrust chamber, and a spark plug, where the injector body is provided therein with an accommodating space; the spark plug is provided on one side of the injector body, and an electrode provided on the spark plug extends into the accommodating space; the thrust chamber is provided on the other side of the injector body and is communicated with the accommodating space; the injector body is provided with a combustion improver flow channel and a combustible agent flow channel; and the combustion improver flow channel and combustible agent flow channel are connected with the accommodating space.

Abstract: A method for operating an at least temporarily unmanned aircraft, wherein a flight is performed according to a prior flight plan in an airspace controlled by a control instance. A flight direction is determined during the flight via a control device influenced via a data connection by a control instance. The data connection is temporarily unavailable, and a hazardous or emergency situation requiring deviation from the flight plan, is identified by the control device based on first sensor data. An avoidance route is determined by the control device based on a second sensor data, the avoidance route including a avoidance manoeuvre avoiding the hazardous or emergency situation, the avoidance route is used in the meantime to fly towards a destination area with the least possible volume of air traffic; and the necessary avoidance manoeuvre(s) are performed based on the second data by the control device in an autonomous staggering procedure.

Abstract: A satellite includes a first radiator panel, a second radiator panel, a space defined between the first radiator panel and the second radiator panel, and one or more first heat-generating components located in the space. Each of the first heat-generating components is attached to at least one of the first or second radiator panels. The satellite further includes a third radiator panel extending from the space and one or more second heat-generating components located in the space, each of the second heat-generating components is attached to the third radiator panel.

Abstract: Systems and methods for providing a high gain antenna are disclosed. The antenna can include an array of active antenna elements disposed on a first side of a first circuit board. The active antenna elements are grouped into a number of super elements. Each super element occupies at least a portion of an outside edge of an area containing the active antenna elements. Passive antenna elements can be disposed so as to surround the area containing the active antenna elements. Passive circuit components can be disposed on a second side or on an intermediate layer of the first circuit board. Active circuit components can be disposed on a second circuit board. The active components can be supplied with power and control signals. The first and second circuit boards can be held together by a housing. The antenna can be configured as conformal array antennas.

Abstract: A two-part coupling for use in joining sections of pipe without additional fasteners is disclosed. The two-part coupling includes integral coupling features molded by additive manufacturing technology. The two-part coupling increases reliability, reduces weight, and provides ease of manufacture. The coupling distributes a fluid load so that the coupling can withstand pressures and leak rates in accordance with stringent standards. The two-part coupling can be coupled and de-coupled using a locking and release mechanism built into the integral parts. Assembly is made easier because the geometry of the coupling is amenable to additive manufacturing. Because the two-part coupling requires a lesser degree of precision, machined parts are not required.

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 launch system and method for orbital or suborbital air-launch of a payload involving releasably coupling a launch vehicle with a towed aircraft via an articulatable carriage to form an air-launch assembly, towing the air-launch assembly via a tow aircraft and interconnected tow cable to a first altitude, releasing the air-launch assembly from tow at or above the first altitude, activating the towed aircraft propulsion system and initiating a pull-up and climb maneuver of the towed aircraft to a second altitude, articulating the articulatable carriage to shift the air-launch assembly from a stowed position to a deployed position with the launch vehicle spaced from the towed aircraft, releasing the launch vehicle from the articulatable carriage and thus from the towed aircraft, and activating the launch vehicle propulsion system for further altitude gain or to meet specific mission requirements.

Abstract: A collecting implement includes a cylindrical body portion having a stretchability; and a hollow portion formed in the body portion, wherein the hollow portion includes an inlet portion which is formed such that one end side of the body portion is open and through which a material is introduced; and a collecting portion which is formed continuously from the inlet portion and contains the material. In the collecting portion, a predetermined part is more stretchable than a part of the collecting portion other than the predetermined part so that the predetermined part can bulge toward an outer side of the body portion when the material introduced from the inlet portion is contained.

Abstract: A flat panel antenna fed by a planar feed array and steered by varactors performs the function of a single beam phased array antenna. This flat panel antenna has a planar array to passively amplify radio frequency (RF) signals, and a transmitarray metasurface having an array of unit cells to steer the antenna's main beam. It uses varactors to dynamically control the phase shift for each unit cell.

Abstract: A multibeam Radio Frequency (RF) lens antenna is designed as a receiver for Global Navigation Satellite System (GNSS) applications, such as GPS (Global Positioning System), Galileo, GLONASS, COMPASS, and others. The RF lens and plurality of associated feed elements and receiver circuits combine to form a plurality of resulting high-gain relatively narrow beams that, taken together, allow reception of signals from GNSS satellites over the entire upper hemisphere. Any kind of RF lens can be used, where the lens can be of homogeneous or inhomogeneous, dielectric or metamaterial/metasurface construction. The benefit of this approach to build a GNSS receiver over existing alternatives is increased gain and decreased noise at each receiver, which improves the signal to noise ratio (SNR) and improves the accuracy and reliability of the position and time measurements, while also reducing the impact of, and sensitivity to, interference, jamming, and spoofing signals.

Abstract: Precision flow restrictors and techniques for manufacturing the same for ion thruster manifolds are disclosed. Flow restricting features are moved out of the manifold base and into separate flow restrictors, allowing a wider range of manufacturing techniques and materials to be applied. Quality control can be performed at the level of the flow restrictors as subcomponents, ensuring that only good parts with ideal flow characteristics make it into the final assembly and improving the yield rate of the final manifold assembly.

Abstract: A multiple hold-down and release device for spacecraft includes a central structure including a central section with a cylindrical inner hole, an inner axial shaft insertable into the inner hole. A release bolt aligns with the inner axial shaft. A main bushing is partially arranged inside the inner hole and axially guided by guiding bushings on the main bushing and the inner hole. The main bushing includes a protrusion and internal retainer spring. Arms protruding from the central section are axially preloaded by a pusher opposite the central section. Connecting levers each connect to the end of the corresponding arm by the pusher. Hold-down assemblies on the periphery of the device each include a hold-down support and a fastener with conical contact surfaces, a torsion spring around a torsion spring shaft, and articulated with the corresponding hold-down support by the corresponding torsion spring shaft.

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.