Described herein, is a sensing textile for a spacecraft, comprising an aerospace-grade fabric substrate having a surface and one or more sensing fibers coupled to the aerospace-grade fabric substrate, wherein at least a subset of the sensing fibers extends above the surface of the substrate. In some embodiments, the sensing fibers comprises one or more of an impact sensor, a charge sensor, a thermal sensor or radiative surface. Some embodiments, the sensing fibers are configured to form one or more patterned topologies about the surface of the aerospace-grade fabric substrate. In some embodiments, the patterned topologies comprises one or more of a pile, looped pile, waffle, spacer, seersucker, pliss, or an embroidery.

A single-person spacecraft includes a pressurized crew enclosure, an external equipment bay, and an overhead crown assembly.

The present disclosure provides a satellite system with orbital debris avoidance. In one embodiment, the satellite system includes debris sensor circuitry to scan orbital debris items in an orbital debris field; and sensor controller circuitry to determine a search window within the orbital debris field based on, at least, uncertainties associated with a velocity of the satellite (Vsatellite) and uncertainties associated with a velocity of at least one debris item (Vdebris), the sensor controller circuitry also to control the debris sensor circuitry to detect the at least one debris item within the search window.

The present disclosure provides a satellite system with orbital debris avoidance. In one embodiment, the satellite system includes debris sensor circuitry to scan orbital debris items in an orbital debris field; and sensor controller circuitry to determine a search window within the orbital debris field based on, at least, uncertainties associated with a velocity of the satellite (Vsatellite) and uncertainties associated with a velocity of at least one debris item (Vdebris), the sensor controller circuitry also to control the debris sensor circuitry to detect the at least one debris item within the search window.

A multi-layer insulation includes a plurality of layers that are laminated on each other. A detection layer that is at least one of the plurality of layers has a piezoelectric film, and a pair of electrode parts installed on both surfaces of the piezoelectric film.

A multi-layer insulation includes a plurality of layers that are laminated on each other. A detection layer that is at least one of the plurality of layers has a piezoelectric film, and a pair of electrode parts installed on both surfaces of the piezoelectric film.

In a search and tracking method for full time-domain laser detection of space debris, a set of latest precision orbital parameters of a debris object and start and end moments of a current transit of the object are first obtained. Search-specific guidance data is generated based on the above information and in combination with estimation of a maximum along-track error of the orbital parameters of the object during the current transit. A DLR system performs multi-elevation search on the object based on the search-specific guidance data, obtains a plurality of pieces of detection data of the object after detecting the object during the search, determines an along-track error of the orbital parameters of the object based on the detection data, and corrects the orbital parameters of the object in real time based on the along-track error, so as to guide the DLR system to subsequently track and detect the object.

Enclosures for facilitating activities in space, and associated systems and methods, are disclosed. A representative system includes a spacecraft having an enclosed interior volume (which can be formed by an inflatable membrane) and one or more unmanned aerial vehicles (UAVs) carried by the spacecraft and positioned to deploy into the enclosed interior volume. The system can include a remote-control system to control the one or more UAVs from a terrestrial location while the spacecraft is in space. A wireless charging system can provide electrical power to the one or more UAVs. A representative method includes configuring one or more controllers to launch a first spacecraft to a first orbit, launch a second spacecraft to a second orbit, move the first spacecraft to the second orbit, dock the first spacecraft with the second spacecraft, and broadcast an event within an interior volume of the first spacecraft to a terrestrial location.

Enclosures for facilitating activities in space, and associated systems and methods, are disclosed. A representative system includes a spacecraft having an enclosed interior volume (which can be formed by an inflatable membrane) and one or more unmanned aerial vehicles (UAVs) carried by the spacecraft and positioned to deploy into the enclosed interior volume. The system can include a remote-control system to control the one or more UAVs from a terrestrial location while the spacecraft is in space. A wireless charging system can provide electrical power to the one or more UAVs. A representative method includes configuring one or more controllers to launch a first spacecraft to a first orbit, launch a second spacecraft to a second orbit, move the first spacecraft to the second orbit, dock the first spacecraft with the second spacecraft, and broadcast an event within an interior volume of the first spacecraft to a terrestrial location.

Systems and methods for transferring, storing, and/or processing materials, such as fuel or propellant, in space, are disclosed. A representative system includes a flexible container that is changeable between a stowed configuration in which the flexible container is contained within a satellite, and a deployed configuration in which the flexible container extends away from the satellite. The system can include a tanker with a storage container to dock with and refuel a satellite. Another representative system includes a controller programmed with instructions that position a spacecraft with a storage container in a first orbit, transfer the spacecraft to a second orbit, dock the spacecraft with a satellite in the second orbit, transfer material between the storage container and the satellite, undock the spacecraft from the satellite, and, optionally, return the spacecraft to the first orbit. An androgynous coupling system with mechanical and fluid connectors facilitates docking and material transfer.