Disclosed is a micrometeoroid and debris protection system (MDPS) for a thermal control system on a spacecraft. The MDPS comprises a radiator face-sheet, a truss attached to the radiator face-sheet, and a thermally transparent bumper disposed on the truss. The thermally transparent bumper shields the radiator face-sheet from micrometeoroids and debris and enables thermal transfer from the radiator face-sheet through the thermally transparent bumper.

Disclosed is a micrometeoroid and debris protection system (MDPS) for a thermal control system on a spacecraft. The MDPS comprises a radiator face-sheet, a truss attached to the radiator face-sheet, and a thermally transparent bumper disposed on the truss. The thermally transparent bumper shields the radiator face-sheet from micrometeoroids and debris and enables thermal transfer from the radiator face-sheet through the thermally transparent bumper.

A protective assembly comprises a first region formulated and configured to provide protection from alpha, beta, and electromagnetic radiation and comprising a composite of particles and polymer; a second region formulated and configured to provide protection from ballistic impact and comprising a composite of fibers and polymer; and a third region formulated and configured to provide protection from thermal radiation and comprising a composite of particles, fiber, and polymer. The protective assembly may be provided on an aerospace structure. The protective assembly may be formed on the aerospace structure body using a co-curing process.

A protective assembly comprises a first region formulated and configured to provide protection from alpha, beta, and electromagnetic radiation and comprising a composite of particles and polymer; a second region formulated and configured to provide protection from ballistic impact and comprising a composite of fibers and polymer; and a third region formulated and configured to provide protection from thermal radiation and comprising a composite of particles, fiber, and polymer. The protective assembly may be provided on an aerospace structure. The protective assembly may be formed on the aerospace structure body using a co-curing process.

Segmented shields are disclosed comprising material combinations and rolled configurations to impede and mitigate through-and-through penetration damage of a structure incorporating the segmented shields from the damage resulting from the impact of high-velocity micro-meteoroids and orbital debris particulate.

Segmented shields are disclosed comprising material combinations and rolled configurations to impede and mitigate through-and-through penetration damage of a structure incorporating the segmented shields from the damage resulting from the impact of high-velocity micro-meteoroids and orbital debris particulate.

Segmented shields are disclosed comprising material combinations and rolled configurations to impede and mitigate through-and-through penetration damage of a structure incorporating the segmented shields from the damage resulting from the impact of high-velocity micro-meteoroids and orbital debris particulate.

Segmented shields are disclosed comprising material combinations and rolled configurations to impede and mitigate through-and-through penetration damage of a structure incorporating the segmented shields from the damage resulting from the impact of high-velocity micro-meteoroids and orbital debris particulate.

The present disclosure relates to deployable structures and methods of use thereof. In particular, deployable structures with non-cylindrical or irregular shapes and methods of use thereof are disclosed. Non-cylindrical combustion elements can be used to rigidize such non-cylindrical or irregular shapes. The use of gaseous oxidizers along with deployable structures is also disclosed.

A self-healing shield panel for protecting a spacecraft against High Velocity Particles (HVPs). The self-healing shield includes an exterior layer and an interior layer connected to define a cavity which contains a dilatant fluid with a plurality of spheroids. The kinetic energy from HVP impact is dispersed by the plurality of spheroids and absorbed by the dilatant fluid. The plurality of spheroids within the cavity move to block a puncture hole in the shield.