Abstract: Methods, non-transitory computer readable media, and query verification apparatuses are disclosed that receive data, store the data into a table of a database, and receive a query that is associated with the database table. A query plan and a query result are generated for the query, one or more partial proofs are generated from one or more commitments, and an overall proof is generated from the one or more partial proofs. Each of the one or more partial proofs is associated with at least one node of the query plan in some examples, which can include a directed acyclic graph. The overall proof is returned along with the query result in response to the query to facilitate verification of the query result. One or more GPUs are configured to generate the one or more commitments in some examples to thereby accelerate the verification process and improve database scalability.

Abstract: A multi-mode thruster system for use in a spacecraft includes a microwave source; a cavity coupled to the microwave source and including a first inlet to receive a first fluid and a second inlet to receive a second fluid; and a nozzle provided at one end of the cavity. The thruster operates in a microwave electrothermal thruster (MET) mode to (i) generate a standing wave in the cavity using the microwave source and (ii) raise a temperature of the first fluid to generate a first hot gas that exits the cavity via the nozzle to generate thrust. The thruster operates in a chemical propulsion mode to (i) produce a reduction-oxidation reaction between the first fluid and the second fluid and (ii) generate a second hot gas that exits the cavity via the nozzle to generate thrust.

Abstract: Described are energy storage devices employing a gas storage structure, which can accommodate or store gas evolved from the energy storage device. The energy storage device comprises an electrochemical cell with electrodes comprising metal-containing compositions, like metal oxides, metal nitrides, or metal hydrides, and a solid state electrolyte.

Abstract: A connector backshell assembly includes a module hood sealable against a connection port having a first connector, a harness hood configured to house a second connector mateable with the first connector, a backshell configured to provide strain relief to a wire harness extending from the second connector and securable on the harness hood after the second connector is housed within the harness hood, and a latch assembly having a latch handle moveable from a first position into a second position to move the harness hood into sealing engagement with the module hood.

Abstract: A fluid tank for integration into a structure of an unmanned aircraft includes a shell having a first axial wall, an oppositely arranged second axial wall, an upper side, a lower side, and an enclosed interior, at least one receiving chamber in the interior for storing fluid, and a collection chamber, which is arranged on the lower side and which is fluidically connected to the at least one receiving chamber. The collection chamber includes a bottom surface, through which there extends a drain, wherein a covering surface is arranged above the bottom surface and covers at least a portion of the collection chamber. At least one flow opening could be arranged on an upper side of the collection chamber, which flow opening allows gas bubbles to escape in the direction of the upper side of the fluid tank.

Abstract: [Problem] To provide a spacecraft having a more effective arrangement of amplifiers. [Solution] Provided is a spacecraft comprising: a main body having a housing space for housing an electronic device within; an oscillator configured to output a radio wave including a frequency in a predetermined frequency band; an amplifier disposed on an exterior of the main body so as to be exposed to space and configured to amplify the power of the radio wave output by the oscillator; and an antenna, disposed on the exterior of the main body, for emitting the radio wave to the outside at the power amplified by the amplifier.

Abstract: A spacecraft is disclosed, comprising a deployable spacecraft body (110) comprising a plurality of sub-systems (321-324) for controlling operations of the spacecraft, and a plurality of panels (101, 102) and a plurality of hinges (112-115) each connecting adjacent ones of the plurality of panels, the hinges being arranged to permit the plurality of panels to be folded into a stowed configuration and unfolded into a deployed configuration, wherein the plurality of sub-systems are fixed to and supported by one or more of the plurality of panels. By forming the body of the spacecraft from a deployable structure, the overall size of the spacecraft can be significantly reduced in the stowed configuration.

Abstract: A method for making small diameter NiTi metal alloy components, including balls, comprising providing a metal powder comprising nickel, titanium, and a transition metal, consolidating the metal powder into cylindrical rods, and cutting the cylindrical rods into segments. The segments are then machined into spheres slightly larger than the finished ball size diameter. The spheres are heat treated to solutionize and dissolve all phases and subsequently cooled without the need for rapid quenching due to the influence of the transition metal to suppresses the formation of soft phases in the spheres, wherein such soft phases prevent hardening, to achieve a Rockwell hardness of HRC 58-62. Finally, the hardened spheres are polished until the desired finished ball size diameter and surface finish is achieved.

Abstract: A high conductance thermal link (1) includes a thermal conductive strap (2) having pyrolytic graphite layers arranged in stacks (5) and polyimide film (6) at least partially covering each stack (5). Adhesive material is between the pyrolytic graphite layers. The thermal conductive strap (2) has two opposite ends (4) and two end fittings (3, 3?) that house the corresponding ends (4) of the thermal conductive strap (2). An adhesive material is in the ends (4) of the thermal conductive strap (2) between the pyrolytic graphite layers and between the stacks (5) of pyrolytic graphite layers. At least one of the ends (4) of the thermal conductive strap (2) has a geometry including protrusions (7) separated by intermediate gaps (8).

Abstract: A booster system for a launch vehicle includes a plurality of core boosters and a plurality of patchy boosters. The plurality of core boosters and the plurality of patchy boosters are arranged in an inner space of a rocket casing of the launch vehicle, and the plurality of patchy boosters is separatable from the launch vehicle.

Abstract: An acoustic transponder provides information related to the transponder when the transponder is receiving an acoustic interrogating signal. The transponder includes a power supply, an electronic circuit connected to the power supply, and one or more transducers receiving and emitting the acoustic signal. The electronic circuit includes a sequence generator. The transponder further includes an amplification and modulation unit, an extraction filter, and a suppression filter. The extraction filter is adapted to extract the received acoustic interrogating signal and suppress other signals prior to being input to the amplification and modulation unit which are configured to modulate the received acoustic signal according to a sequence generated by the sequence generator and to amplify the modulated signal. The suppression filter is adapted to suppress the received acoustic interrogating signal from the amplified and modulated signal.

Abstract: A low-earth orbit (LEO) satellite includes a global positioning receiver configured to receive first signaling from a first plurality of non-LEO navigation satellites. An inter-satellite transceiver is configured to send and receive inter-satellite communications with other LEO navigation satellites. At least one processor is configured to execute operational instructions that cause the at least one processor to perform operations that include: determining an orbital position of the LEO satellite based on the first signaling; and generating a navigation message based on the orbital position. A navigation signal transmitter configured to broadcast the navigation message to at least one client device, the navigation message facilitating the at least one client device to determine an enhanced position of the at least one client device based on the navigation message and further based on second signaling received from a second plurality of non-LEO navigation satellites.

Abstract: A feedthrough for use in a vacuum chamber is provided and includes a hollow tube having a length, an inner circumference, and a first recess located within the inner circumference. The feedthrough also includes a first O-ring captured by the first recess within the hollow tube. The feedthrough further includes a rod extending through an entirety of the length of the hollow tube. An outer circumference of the rod is configured to contact an entirety of an inner circumference of the first O-ring, and a vacuum fitting is fixedly secured to the hollow tube.

Abstract: Described herein are systems, methods, media, and devices for generating a satellite program for contacting satellites. In some embodiments, data including one or more targets for accessing a satellite constellation is obtained. Based on the data, a set of representations may be generated and candidate satellite constellation access programs may be determined based on the set of representations. For each program, a first score may be computed for each target to obtain a first set of scores, and a second score may be computed for each first score of the first set of scores to obtain a second set of scores. A satellite constellation access program may be selected from the candidate satellite access programs based on the second set of second scores.

Abstract: The method and system for merging information aimed at merging the instances of individuals, a data-processing system performs the following steps: generating the instances of individuals using an ontology which defines, for each property of each instance of an individual, an evolution model to be applied to the property, evolution model representing the evolution of reliability of the property over time in relation to variability of the property over time; preforming the merging of information by comparing, two-by-two, the generated instances of individuals with instances of individuals stored in a knowledge base, performing, for each shared property, a calculation of similarity distance by applying at least evolution model defined for the property, so as to define a coefficient of confidence for each property in order to decide whether or not to merge the instances of individuals; and updating the knowledge base with the instances of individuals resulting from information merging.

Abstract: A hybrid rocket engine with a vortex flow field injection system that produces a high-speed sustained vortex flow field is described. The hybrid rocket engine includes a generally cylindrical injection chamber with an inner circumference to comprise an outer edge of a solid propellant grain in the hybrid rocket engine. The engine also includes an injection system that has a throttle valve and an injector that injects injection fluid into the engine and produces a vortex flow-field for the injected fluid. The injector includes at least one primary feed line that distributes the injection fluid throughout a pre-swirl chamber and multiple orifices along an inner edge of the injection chamber. The pre-swirl chamber connects to the injection chamber and at least one of the primary feed lines and redirects a primary fluid flow of the injected fluid from a primary axial direction to a centrifugal direction.

Abstract: A waveguide polarizer for converting between a linearly polarized electromagnetic field in a first waveguide and a circularly polarized electromagnetic field in a second waveguide is provided. The waveguide polarizer includes a structure interconnecting the first and second waveguide which includes a waveguide excitation arrangement with a bifilar helical shape. A circularly polarized antenna arranged to be connected to the first waveguide of the waveguide polarizer and a satellite arrangement are also provided.

Abstract: The present invention relates to a release system (1, 2, 3, 4, 5), that includes a segmented structural element (10) comprising: a first segment (10a) designed to be coupled to a first structure, a second segment (10b) designed to be coupled to a second structure, and a solder joint (11) joining respective ends of said first (10a) and second (10b) segments, thus holding down the first and second structures with respect to one another; wherein said solder joint (11) is electromagnetically heatable and includes a solder alloy having a predefined melting temperature.