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.

An object is to notify an appropriate intrusion alert by determining whether debris will intrude into an orbit area of a satellite constellation. A passage determination unit (110) determines whether debris will pass through a satellite orbit area, based on satellite orbit forecast information in which a forecast value of an orbit of a satellite is set and debris orbit forecast information in which a forecast value of an orbit of debris is set. When it is determined that debris will pass through the satellite orbit area, an alert generation unit (120) generates an intrusion alert (111) including a predicted time, predicted location coordinates, and predicted velocity vector information that relate to passage of the debris. An alert notification unit (130) notifies the intrusion alert (111) to a management business device (40) used by a management business operator that manages a satellite that flies in the satellite orbit area.

An improved debris generator that can be used as part of a space object modeling (SOM) system to turn any active spacecraft into a debris sensor for characterizing and cataloging space debris. The space debris generator includes an extractor which extracts satellite sensor data into a sensor store, an impact agent which estimates “on the fly” new debris field objects generated by the collision, and an injector which stores the enhanced object data on a central server for near-term mitigation of impact driven breakup events. The impact agent is an artificial neural network trained using a large number of simulations of impact events.

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.

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.

An improved system for concentrating, collecting, and transmitting sunlight, comprises: a first plurality of lens panels that is disposed in at least one location in an origin for collecting sunlight; a central collection point that receives the collected sunlight, said collected sunlight being transmitted from the collection point to at least one concentrating lens, said at least one concentrating lens generating a sharp and strong beam, which is transmitted to a first satellite; a first reflecting portion that reflects the concentrated beam to a second satellite; and a second reflecting portion that reflects the concentrated beam through a second pre-defined distance to an at least one receiver unit, said at least one receiver unit transmitting the sunlight to a receiving point that is disposed in at least one location in the destination for collecting sunlight. The sunlight collected in the destination can be used for various purposes.

An improved system for concentrating, collecting, and transmitting sunlight, comprises: a first plurality of lens panels that is disposed in at least one location in an origin for collecting sunlight; a central collection point that receives the collected sunlight, said collected sunlight being transmitted from the collection point to at least one concentrating lens, said at least one concentrating lens generating a sharp and strong beam, which is transmitted to a first satellite; a first reflecting portion that reflects the concentrated beam to a second satellite; and a second reflecting portion that reflects the concentrated beam through a second pre-defined distance to an at least one receiver unit, said at least one receiver unit transmitting the sunlight to a receiving point that is disposed in at least one location in the destination for collecting sunlight. The sunlight collected in the destination can be used for various purposes.

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

A spacecraft for changing an orbit or an attitude of a target in outer space by irradiating the target with a laser, the spacecraft includes: a laser apparatus configured to generate the laser; a focusing unit configured to converge the laser; a detecting unit configured to acquire detection information including a distance between the spacecraft and the target; and an irradiation control unit configured to control the focusing unit on the basis of the distance so that the laser converges on the target.