Abstract: A device for use in magnetic resonance imaging (MRI) systems may include a superconducting main magnet coil; and a thermal radiation shield that encloses the superconducting main magnet coil. The shield may include an inner cylindrical bore tube, an outer cylindrical wall, and annular end walls welded between the annular cylindrical bore tube and the outer cylindrical wall to form a closed, hollow cylindrical vessel. A distribution of a position and length of welds that affix the annular end walls to the inner cylindrical bore tube may include a predetermined arrangement of welds of varying lengths interspersed with gaps of varying lengths.

Abstract: A method of releasing artificial satellites into Earth's orbit includes providing an orbital transport spacecraft able to move at orbital height and comprising a cargo area, hooking a plurality of satellites in said cargo area, housing said orbital transport spacecraft in a space launcher configured to reach an orbital height, releasing said orbital transport spacecraft at orbital height, when said space launcher reaches orbital height, by imparting a separation thrust to said orbital transport spacecraft, releasing satellites in sequence from the cargo area. The release of each satellite from the cargo area occurs in a respective predetermined direction and upon the orbital transport spacecraft has reached a respective predetermined position.

Abstract: A device for use in magnetic resonance imaging (MRI) systems may include a superconducting main magnet coil; and a thermal radiation shield that encloses the superconducting main magnet coil. The shield may include an inner cylindrical bore tube, an outer cylindrical wall, and annular end walls welded between the annular cylindrical bore tube and the outer cylindrical wall to form a closed, hollow cylindrical vessel. A distribution of a position and length of welds that affix the annular end walls to the inner cylindrical bore tube may include a predetermined arrangement of welds of varying lengths interspersed with gaps of varying lengths.

Abstract: A satellite module for attitude determination includes a containment body comprising at least one data acquisition board and a connection interface, at least one first-type sensor selected from a sun sensor, an earth sensor, a stellar sensor, a horizon sensor, in communication with the data acquisition board and at least one second-type sensor, different from the first type, selected from a sun sensor, an earth sensor, a stellar sensor, a horizon sensor, and in communication with the data acquisition board. The connection interface may be mounted on a first face of the containment body, the first-type sensor may be mounted on a second face of the containment body, and the second-type sensor may be mounted on a third face of the containment body.

Abstract: A method of releasing artificial satellites into Earth's orbit includes providing an orbital transport spacecraft able to move at orbital height and comprising a cargo area, hooking a plurality of satellites in said cargo area, housing said orbital transport spacecraft in a space launcher configured to reach an orbital height, releasing said orbital transport spacecraft at orbital height, when said space launcher reaches orbital height, by imparting a separation thrust to said orbital transport spacecraft, releasing satellites in sequence from the cargo area. The release of each satellite from the cargo area occurs in a respective predetermined direction and upon the orbital transport spacecraft has reached a respective predetermined position.