Abstract: The invention concerns a method of providing a space extended reality service on earth, including: acquiring, by means of one or more acquisition systems/devices installed on a space platform, real-time data related to a surrounding space environment and/or to one or more astronauts in the space environment; generating, by means of a computer graphics processing device/system, based on the acquired real-time data and on synthetic data, a three-dimensional extended reality environment reproducing the space environment and one or more three-dimensional avatar(s) of the astronaut(s) reproducing movements and/or actions and/or facial expressions and/or voice of the astronaut(s), wherein the synthetic data digitally represent the space environment and/or the astronaut(s); and providing one or more users on earth with a space extended reality service based on the generated three-dimensional extended reality environment and avatar(s).

Abstract: A method for securing a geographical area encompassing a route. A map of the area is obtained. A weapon is associated with a firing modeling consisting of a probability model of hitting its target when shooting, as a function of the firing distance. Positions of potential shelters of threats on the map are determined by using a trained artificial intelligence device. The modeling is applied for each weapon and potential shelter while relating the shots to the route and summing all the probabilities of hitting its target on each portion of the route. The potential shelters most likely to constitute attack threats along the route are determined. A path is defined in order to address these potential shelters most likely to constitute attack threats.

Abstract: The present disclosure relates to a reactor device (2) for converting powdered metal oxides, in particular metal oxides contained in regolith, to metal powder and molecular oxygen (O2), the reactor device (2) comprising a cathode reactor vessel (8) providing a receiving space (14) for the powdered metal oxides and adapted to be connected to an electron source (21) such that the powdered electrode oxides can be converted to the metal powder and oxygen ions (O2?) by the application of an electrical potential, and an anode reactor vessel (4) adapted to be connected to an electron sink (22) to attract the oxygen ions (O2?) travelling through an electrolyte (6) from the cathode reactor vessel (8) to the anode reactor vessel (4) during operation of the reactor device (2); wherein the anode reactor vessel (4) at least partially surrounds the cathode reactor vessel (8).

Abstract: The present invention discloses a satellite communication method and system based on network coding and modulated-retro reflection.

Abstract: The method and the system of this invention center around the innovative concept of an orbit-independent spacecraft comprised of a physical structure that provides multiple docking devices placed in a spatial relationship and orientation on the exterior of the spacecraft. The docking devices provide a standard interface to the spacecraft by which to attach and detach modular components (payloads). Payloads to be docked to the spacecraft have identical docking devices as part of their physical assemblies. A payload that has been launched into space is navigated towards the spacecraft using a transfer vehicle. Payload and spacecraft docking devices are brought into physical contact where internal locking mechanisms create a secure attachment of the payload to the spacecraft. Physical connections within the payload and spacecraft docking devices are made, allowing the payload to access bus capabilities such as electrical power, data communications, sensor readings, and thermal management from the spacecraft.

Abstract: A mode conversion apparatus includes a first freeform-surface mirror to reflect incident light provided from a front-end optical system and output the reflected light in a first direction, and a second freeform-surface mirror to reflect the reflected light and output mode-converted light in a second direction where surface shapes of the first and second mirrors are determined based on a freeform-surface coefficient determined by at least five optical parameters of a distance from the first mirror to a confocal point of the first mirror and the second mirror, a distance from the confocal point to the second mirror, a distance from a waist of the incident light to the first mirror, a distance from the second mirror to a waist of the mode-converted light, and an incident angle of the incident light for the first mirror and an incident angle of the reflected light for the second mirror.

Abstract: In various example embodiments, a system and method for tracking objects in a three-dimensional space is disclosed. One method includes receiving detections representing targets, increasing a classification of a track in response to a detection matching the track, decreasing a classification of a track in response to no detections matching the track, and processing detections according to a classification level of the track.

Abstract: Systems and methods for pointing a high gain antenna or other directional instrument connected to a platform by a gimbal are provided. A control system as disclosed can include a flight computer having a processor for executing software and a motor control board having a controller for implementing at least portions of a control algorithm. The software executed by the processor generates pointing commands and implements a Kalman filter included in a feedback loop in the form of a linear Kalman filter disturbance estimator of the control algorithm implemented by the controller. The control algorithm can further implement a proportional control position loop and a proportional control rate loop. Each axis of the gimbal is provided with an instance of the control algorithm and the Kalman filter. Moreover, the processor can be operated at a rate that is less than a rate at which the controller is operated.

Abstract: A new password manager for safely autofilling login user login credentials performs multiple layers of security check to protect users' confidential data. User interface elements of a computing source, such as a web page or a mobile app, are parsed for determining that password input fields are present. In such a case, a autofill control is displayed for activating user authentication for accessing the password manager. The password manager determines a computing source identifier of the computing source, determines a list of context identifiers corresponding to the computing source, performs computing security check, matches the computing source identifier to an account, and selects an account. The password manager then performs account security check on the selected account. When the security check is successful, the password manager autofills the login password input field with login data associated with the selected account.

Abstract: In one embodiment, an air-scoop includes an air inlet that air molecules enter the air-scoop through at an orbital speed when the air-scoop is moving through an atmosphere at the orbital speed. The air-scoop also includes a rotor that is rotated by a motor at a rotational speed, and the rotor includes multiple rotatable blade stages. A first one of the rotatable blade stages has a blade configuration that maximizes transparency of the first one of the rotatable blade stages to air molecules entering the air-scoop through the air inlet at the orbital speed when the rotor is rotating at the rotational speed. A last one of the rotatable blade stages has a blade configuration that maximizes opacity of the last one of the rotatable blade stages to air molecules in the air-scoop flowing directionally toward the air inlet when the rotor is rotating at the rotational speed.

Abstract: A hybrid propulsion unit, for a space vehicle or rocket, includes an external body defining a combustion chamber configured to receive a block of solid propellant, a pressurized reservoir configured to receive a liquid propellant, and a nozzle to eject the combustion gases produced by the reaction of the propellants. The pressurized reservoir being placed inside the external body, surrounded by the block of solid propellant. The propulsion unit further includes a plurality of liquid-propellant injectors disposed axially between parts of the solid propellant to improve the efficacy of the combustion. A space vehicle, of the launch vehicle type, equipped with such hybrid propulsion unit.

Abstract: Technology for orbit raising of multiple spacecraft launched with a single launch vehicle. Two or more spacecraft are configured in a stacked launch configuration in which a lower spacecraft is mechanically coupled with a payload adapter of a launch vehicle with one or more upper spacecraft above the lower spacecraft. Propellant that is stored in the lower spacecraft during launch is transferred to an upper spacecraft in the stack after launch. The propellent may be used by the upper spacecraft for an orbit raising maneuver that raises the orbit of at least the upper spacecraft from a first orbit to a second orbit. Storing the propellant in the lower spacecraft lowers the center of mass of the stack during launch. Lowering the center of mass reduces the structural bending moment of the stack during launch, which allows a greater total launch mass.

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: A field-assembled satellite communications terminal has a plurality of discrete, modular aperture blocks. Each aperture block contains an electrically steered antenna aperture, and a plurality of interconnection ports for power and data communications between the plurality of aperture blocks. The plurality of interconnection ports are removably connectable by the end user in the field. The terminal further has a signal processing system for receiving, processing, and generating signals to and from the apertures. The aperture blocks are connected to each other in the field and self-configure to form an electrically-steered antenna.

Abstract: The present invention relates to a medium composition for culture of extraembryonic endoderm stem cells, and more specifically, to a medium composition for in vitro culture of extraembryonic endoderm stem cells.

Abstract: A method for transferring a spacecraft (10), such as an artificial satellite, from an initial elliptical orbit (30) to a final geostationary orbit (50), the spacecraft taking at least one intermediate elliptical orbit (40) propelled by electric propulsion means (12, 13), the method includes: when the spacecraft is in an intermediate orbit, a nominal thrust step (410) in which the propulsion means generate nominal thrust while the spacecraft is on at least part of a first orbital arc (41) passing through the apogee A of the intermediate orbit, and a minimum thrust step (420), in which the propulsion means are partly stopped or slowed while the spacecraft is on at least part (43) of a second orbital arc (42) passing through the perigee P of the intermediate orbit, the two orbital arcs being complementary.

Abstract: An unreal engine-based automatic light arrangement method includes: acquiring a house type model and basic data imported into an unreal engine, the basic data being data obtained after a house type image file of the house type model is parsed (S101); on the basis of first object data and second object data in the basic data, respectively creating an indoor light source and a light-supplementing light source in a room region of the house type model (S102); creating an outdoor light source for the house type model, and creating a later volume on an outer side of the house type model by using a preset light arrangement rule, such that the house type model is wrapped in the later volume (S103); and adjusting parameters of the later volume, and setting light tracking parameters in the later volume, so as to render light arrangement of the house type model (S104).

Abstract: A surface bio-contamination assay kit (1) comprising a disposable swab cartridge (2) comprising a swab (29); a sampler (3) designed to removably receive the cartridge (2) and to wipe the cartridge swab (29) on a surface to be collect a sampled, along a predetermined sampling path (4) designed to cover a predetermined surface area; and a bio-contamination meter (5) designed to removably receive the cartridge (2) after sampling and to measure bio-contamination of the collected sample on the cartridge (2).

Abstract: Embodiments provide a spacecraft airlock system. Embodiments provide a method and apparatus for attaching space exposed payloads to a space station. The spacecraft airlock system provides a defined volume of space payload to the international space station. The airlock further includes a means of attaching to a space station, a closed structure attached to said means, said means of attaching is capable of robotic manipulation, and a cooling system for cooling payload components within said closed structure.