Abstract: A double capsule assembly includes an outer capsule and an inner capsule configured to be positioned within the outer capsule. The inner capsule is configured to have a sample positioned therein. The double capsule assembly is configured to be placed in a solid media assembly to analyze or synthesize the sample.
Type:
Grant
Filed:
July 16, 2019
Date of Patent:
November 22, 2022
Assignee:
United States of America as represented by the Administrator of the National Aeronautics and Space Administration
Abstract: A method for manufacturing in space a rigid structure having a lattice is disclosed. The method includes creating of at least two framework elements from a coil of metal strip or wire, and creating of the lattice by cold-connecting the framework elements.
Abstract: A supercritical water oxidation vortex reactor has a reactor shell configured to contain a pressurized and heated material including water, a burner assembly configured to create a supercritical core region in the material in the reactor shell, the supercritical core region including water above its critical point, an injector assembly configured to inject into the enclosed volume a subcritical wash stream including water below its critical point and an aspirator arranged in the enclosed volume and configured to remove a processed flow including purified water from an upper portion of the supercritical core region. The supercritical water oxidation vortex reactor is configured with an upward helical flow to transfer precipitated ionic compounds out of the supercritical core region, through a transcritical intermediate region, and into the subcritical wash stream where they re-dissolve.
Type:
Grant
Filed:
March 3, 2021
Date of Patent:
November 22, 2022
Assignee:
United States of America as Represented by the Administrator of National Aeronautics and Space Administration
Abstract: In one embodiment of the present disclosure, an antenna assembly includes a patch antenna array including an upper patch antenna layer, a lower patch antenna layer, and a spacer therebetween, wherein the spacer includes a plurality of apertures defined by cell walls, wherein the each aperture aligns with an upper patch antenna element and a lower patent antenna element from the patch antenna array.
Type:
Grant
Filed:
June 3, 2020
Date of Patent:
November 22, 2022
Assignee:
Space Exploration Technologies Corp.
Inventors:
David Milroy, Duncan E. Adams, Ersin Yetisir
Abstract: A plate folding and unfolding device and a solar panel structure are provided. The plate folding and unfolding device includes a cam fixed with first plate piece, and a rotating shaft is disposed inside the cam in an axial direction of the cam; a connecting rod, where the connecting rod includes a first end and a second end that are opposite to each other, the first end is connected vertically to the rotating shaft, and the second end is fixed to a second plate piece; a positioning shaft, where the positioning shaft is disposed, on the connecting rod; and an elastic piece, where the elastic piece is disposed on the connecting rod, one end of the elastic piece is connected to the positioning shaft, where a groove that accommodates the positioning shaft is disposed at at least one location of the outer peripheral surface of the cam.
Type:
Grant
Filed:
April 29, 2019
Date of Patent:
November 22, 2022
Assignee:
SHENZHEN KUANG-CHI SPACE TECH. CO., LTD.
Abstract: A semiconductor layer stack, a component made therefrom, a component module, and a production method is provided. The semiconductor layer stack has at least two layers (A, B), which, as individual layers, each have an energy position of the Fermi level in the semiconductor band gap, E F - E V < E G 2 applying to the layer (A) and E L - E F < E G 2 applying to the layer (B), with EF the energy position of the Fermi level, EV the energy position of the valence band, EL the energy position of a conduction band and EL?EV the energy difference of the semiconductor band gap EG, the thickness of the layers (A, B) being selected in such a way that a continuous space charge zone region over the layers (A, B) results.
Type:
Application
Filed:
July 19, 2022
Publication date:
November 17, 2022
Applicants:
OTTO-VON-GUERICKE-UNIVERSITAET MAGDEBURG, AZUR SPACE SOLAR POWER GMBH
Abstract: The disclosure describes various aspects of a space-based radioisotope production system and methods use. In one aspect, a propellant is accelerated by decay energy to yield thrust. The decay energy is provided by activating a target material. In one aspect, a radioisotope rocket thruster may be recharged or “reactivated” in a space-borne charging station. The activated isotopes may also be used generate electricity. The space-borne charging station may also be used for irradiating other items in space for any number of purposes.
Abstract: A storage system has a first pouch for receiving an electronic device, and a second pouch for receiving the first pouch. The first pouch is at least partially surrounded by the second pouch when the first pouch is received in the second pouch. The first pouch has a first fabric layer. Furthermore, the first pouch has an insulating layer which is adjacent to the first fabric layer and is designed to absorb material arising in the event of combustion. The second pouch is closable in such a manner that, in the closed state of the second pouch, an opening for dissipating heat energy remains.
Type:
Application
Filed:
July 21, 2020
Publication date:
November 17, 2022
Applicants:
Airbus Defence and Space GmbH, Airbus Operations GmbH
Inventors:
Jan Hadidom, Jana Schuett, Thomas Vielhaben
Abstract: A beamforming network for use with a plurality of antenna elements arranged in a planar array of linear sub-arrays includes first and second sets of beamforming sub-networks. Each beamforming sub-network in the first set of beamforming sub-networks is associated with a respective one of the linear sub-arrays and is adapted to generate, via the associated linear sub-array, fan beams along respective beam directions in a first set of beam directions. Each beamforming sub-network in the second set of beamforming sub-networks is associated with a respective one of the beam directions in the first set of beam directions. For each beamforming sub-network in the second set of beamforming sub-networks, each of the output port is coupled to an input port of a respective beamforming sub-network in the first set of beamforming sub-networks that corresponds to the associated beam direction. The application further relates to a multibeam antenna comprising such beamforming network.
Abstract: A space vehicle element configured to be at least partially destroyed during re-entry of a space vehicle into the atmosphere comprises a heat generating part comprising a metallo-thermal composition for providing additional heat during re-entry of the space vehicle into the atmosphere by an exothermic reaction of the metallo-thermal composition. The destruction of the space vehicle element is expedited by the additional heat provided by the heat generating part. The heat generating part is at least partially integrated within the space vehicle element or at least partially surrounds a portion of the space vehicle element. The application further relates to a corresponding method of manufacturing a space vehicle element configured to be destroyed during re-entry of the space vehicle into the atmosphere.
Abstract: A device for determining an attitude of a satellite is disclosed, the satellite having an attitude control system comprising a gyroscopic actuator including a flywheel mounted so as to be rotatable around an axis of rotation and carried by a gimbal articulated to rotate around an axis of rotation. The device includes an attitude sensor configured to measure the attitude of the satellite, a position sensor configured to measure the angular position of the gimbal around its axis of rotation, a speed sensor configured to measure the rotational speed of the flywheel, and a processing circuit configured to determine the attitude of the satellite by using the measurement of the angular position of the gimbal, the measurement of the rotational speed of the flywheel, and the measurement of the attitude of the satellite.
Abstract: A method for producing a tubular body with reduced internal stress uses 3D printing. The tubular body has an outer wall with a stiffening structure extending along at least part of the outer wall. The method sets a printing plane for 3D printing with a 3D printer, and prints a tubular body layer in the printing plane with the 3D printer. The tubular body layer has an outer wall layer and a stiffening structure layer extending in the printing plane along a periphery of the outer wall layer. The stiffening structure layer has at least two portions spaced apart from one another. The method produces an outer wall with a stiffening structure for a tubular body with reduced internal stress.
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 device for carrying fuel in aircraft and spacecraft includes a carrier element having a longitudinal axis, and a fuel tank with a side wall and a chamber at least partially delimited by the side wall. The tank is arranged in the carrier element. The chamber and the side wall extend in a direction along the longitudinal axis. The side wall has a pressure-receiving component that converts a pressure from the chamber on the side wall into a contraction force acting on the side wall along the longitudinal axis. The contraction force compensates for an expansion force, resulting from the pressure from the chamber and acting on the side wall along the longitudinal axis. This provides an improved device for carrying fuel in aircraft and spacecraft, wherein the aircraft and spacecraft has constant flight mechanical properties because of the device.
Type:
Grant
Filed:
November 14, 2019
Date of Patent:
November 8, 2022
Assignee:
AIRBUS DEFENCE AND SPACE GMBH
Inventors:
Michael Stamm, Clemens Brand, Winfried Lohmiller