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 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 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: 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 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: 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 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.

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 valve assembly has a housing and a poppet-carrying portion. The housing includes an inlet port, an outlet port, an opening, and a assembly portion including helical grooves. The poppet-carrying portion is configured to be inserted through the opening and engage with the assembly portion. The poppet-carrying portion comprises a poppet head, a closure including protruding arms, convolutions, and a stopping portion. The convolutions extend between the poppet head and the closure and provide compliance such that the poppet head is movable relative to the closure. The stopping portion extends from the closure toward the poppet head and is spaced apart from the poppet head by a maximum compression distance. At a first fluid pressure, the protruding arms engage with the helical grooves, and the poppet head is positioned in a pre-load position that prevents the fluid from discharging through the outlet port.

Abstract: A downhole rotary drive apparatus (10) for driving a bit (12) used to drill or ream a borehole (B) comprises a body (14) configured for coupling to, or forming part of, a tubular string (S1:S2:S3) for running into the borehole (B) and an output shaft (16) at least partially disposed within and rotatably mounted to the body (14). A plurality of rotary drives (32) are disposed around the body (14), each having a rotor (36). The apparatus (10) further comprises a transmission arrangement (46) comprising a drive component mounted on at least one of the rotors (36) of the rotary drives (32) and a driven component mounted on the output shaft (16). The driven component is disposed radially inwards of the drive component such that an inner surface of the drive component engages an outer surface of the driven component, rotation of the driven component by the drive component driving rotation of the output shaft (16).

Abstract: Methods, non-transitory computer readable media, and verifier and/or prover devices or query verification apparatuses are disclosed that generate a first commitment from received data and send the received data to a prover device for insertion into a table of a database. A query result and an overall proof are received from the prover device in response to a received query forwarded to the prover device and associated with the database table. The overall proof is generated from one or more partial proofs comprising one or more commitments generated from one or more intermediate values. The query result and an indication the query result was verified are returned in response to the received query after verifying the query result based on a second commitment to the query result generated using the first commitment and the overall proof.

Abstract: A modem is configurable on a satellite, user terminal or gateway generates a radio frequency (RF) signal using an orthogonal frequency division multiplexing (OFDM) protocol including a radio frame including one or more bursts. A burst of the one or more bursts includes a first portion including burst detection data, a second portion including channel characteristic estimation data, a third portion including payload data, and fourth and fifth portions including pilot data. The first portion in a time domain is included in the burst prior to the second, third, fourth, and fifth portions. The first portion can include a pseudo-random noise sequence inserted in the time domain. The same physical modem can be configured to transmit signals on an uplink or downlink between a user terminal and a satellite or on the uplink or downlink between the satellite and the gateway.

Abstract: A system and method for protecting secret data items using multiple layers of encryption with multiple encryption keys, a Secure Element, and a sandbox on an electronic device includes a secret data item manager. The secret data item manager encrypts secret data items using a hardware encryption key and the Secure Element. It encrypts the transient secret cipher data with an account encryption key to generate and store repository account cipher data. It further encrypts the account encryption key to generate and store the repository account key cipher data with a root encryption key. The manager also derives a secondary encryption key from a user account password, encrypts the root encryption key with the secondary key to generate the transient root encryption key, encrypts the transient root encryption key using the hardware key to generate the repository root encryption key cipher data, and stores repository root encryption key cipher data.

Abstract: Integrated devices comprising integrated circuits and energy storage devices are described. Disclosed energy storage devices correspond to an all-solid-state construction, and do not include any gels, liquids, or other materials that are incompatible with microfabrication techniques. Disclosed energy storage device comprises energy storage cells with electrodes comprising metal-containing compositions, like metal oxides, metal nitrides, or metal hydrides, and a solid state electrolyte.

Abstract: A receiver is provided for use with a global navigation satellite system (GNSS) comprising multiple satellites. The receiver comprises a receiver clock and at least one antenna for receiving multiple signals over multiple respective channels, each channel being defined by a transmitting satellite and a receiving antenna at opposing ends of the channel. The receiver further comprises at least one correlator for calculating cross-correlation functions between (i) the signals received over the multiple channels and (ii) reference versions of the navigation signals provided by the receiver. The receiver is configured to use the calculated cross-correlation functions to perform a joint estimate of (i) a clock bias of the receiver clock relative to the time reference maintained by the GNSS, and (ii) a composite channel comprising the combined contribution of the multiple channels as a function of time-delay.

Abstract: A device for orienting a load about a main axis X and a secondary axis Y is disclosed having a first shaft, called transmission shaft, intended to support the load and configured to be rotated about the main axis and the secondary axis, a second shaft configured to be rotated about the main axis X, a third shaft configured to be rotated about a third axis of rotation, in the same direction as the main axis, a first connection component between the transmission shaft and the second shaft, configured to prevent relative movements between the transmission shaft and the second shaft in, on the one hand, a degree of rotational freedom about the main axis X and, on the other hand, three degrees of translational freedom.