A shield assembly for protection of vehicles traveling in space consisting of at least five layers that would replace the thin metal impact shield in Whipple shields fabricated using the current art that employs only a single metal. All of the layers in the present invention are metallic. At least three different metals must be used in this invention. FIG. 1 shows the basic embodiment of the transparent blast protection assembly. The shield assembly (10) comprises a first metal layer (20), a second metal layer (30), a third metal foam layer (40), a fourth metal layer (50), and a fifth metal layer (60). At least one spacer component (70) is used to create and maintain a space between the structure requiring impact protection (80) and the shield assembly.

A shield assembly for protection of vehicles traveling in space consisting of at least five layers that would replace the thin metal impact shield in Whipple shields fabricated using the current art that employs only a single metal. All of the layers in the present invention are metallic. At least three different metals must be used in this invention. FIG. 1 shows the basic embodiment of the transparent blast protection assembly. The shield assembly (10) comprises a first metal layer (20), a second metal layer (30), a third metal foam layer (40), a fourth metal layer (50), and a fifth metal layer (60). At least one spacer component (70) is used to create and maintain a space between the structure requiring impact protection (80) and the shield assembly.

The present invention relates to spacecraft shielding, articles comprising such shielding as well as processes of making and using spacecraft shielding and articles comprising such shielding. Such shields are made by a 3D process that provides significant shield geometry and composition flexibility and yields shields that have significantly improved shield performance. Such shields may be efficiently be manufactured in space.

The present invention relates to spacecraft shielding, articles comprising such shielding as well as processes of making and using spacecraft shielding and articles comprising such shielding. Such shields are made by a 3D process that provides significant shield geometry and composition flexibility and yields shields that have significantly improved shield performance. Such shields may be efficiently be manufactured in space.

A solar generator comprises a flexible support, an array of solar cells, electrical transfer conductors, blocking diodes, the solar cells being formed along different transverse strings, the solar cells situated in a same string being electrically connected in series, each string comprising two opposite ends, respectively of positive polarity and of negative polarity. The positive polarity end of each string of solar cells is individually connected to a respective blocking diode via an electrical transfer conductor dedicated to the string, the electrical transfer conductors dedicated to the different strings being independent of one another, the blocking diodes being located at the proximal end of the solar generator, outside of the array of solar cells.

A solar generator comprises a flexible support, an array of solar cells, electrical transfer conductors, blocking diodes, the solar cells being formed along different transverse strings, the solar cells situated in a same string being electrically connected in series, each string comprising two opposite ends, respectively of positive polarity and of negative polarity. The positive polarity end of each string of solar cells is individually connected to a respective blocking diode via an electrical transfer conductor dedicated to the string, the electrical transfer conductors dedicated to the different strings being independent of one another, the blocking diodes being located at the proximal end of the solar generator, outside of the array of solar cells.

A spacecraft for removing space debris is disclosed. The spacecraft includes a satellite bus, a shield member foldable on an outer side face of the satellite bus and disposed facing towards space debris to reduce a movement speed of the space debris, and a support member configured to support the shield member with respect to the satellite bus, in which the shield member includes a central panel configured to overlap one face of the satellite bus, a plurality of first panels connected to peripheral sides of the central panel and radially extended, and a plurality of second panels located between the first panels.

Provided is a bulkhead structure for shielding a space facility (100) installed in outer space from an external space, the bulkhead structure including: a pressurized wall (11) that sealingly covers a periphery of the space facility (100) such that an internal space (14) of the space facility (100) has a predetermined air pressure; and a protective wall (12) that is provided on a side outward from the periphery of the pressurized wall (11) at an interval from the pressurized wall (11) and protects an outer periphery of the pressurized wall (11). At least a part of an outer wall space (15) formed between the pressurized wall (11) and the protective wall (12) is filled with water.

Provided is a bulkhead structure for shielding a space facility (100) installed in outer space from an external space, the bulkhead structure including: a pressurized wall (11) that sealingly covers a periphery of the space facility (100) such that an internal space (14) of the space facility (100) has a predetermined air pressure; and a protective wall (12) that is provided on a side outward from the periphery of the pressurized wall (11) at an interval from the pressurized wall (11) and protects an outer periphery of the pressurized wall (11). At least a part of an outer wall space (15) formed between the pressurized wall (11) and the protective wall (12) is filled with water.

A core element for use with an inflatable or expandable spacecraft is claimed. The core element has a plurality of panels connected by hinges so that the core element can be packed into a smaller volume for loading into a launch vehicle. Upon deployment in space, the core element can be unpacked and can enclose a larger volume than that in the packed state. Multiple core elements can be used to cover a spacecraft to a desired degree.