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.

One aspect of the present invention is a puncture healing polymer blend comprising a self-healing first polymer material having sufficient melt elasticity to snap back and close a hole formed by a projectile passing through the material at a velocity sufficient to produce a local melt state in the first polymer material. The puncture healing polymer blend further includes a non-self-healing second material that is blended with the first polymer material. The blend of self-healing first polymer material and second material is capable of self-healing, and may have improved material properties relative to known self-healing polymers.

Textiles intercalated with shear thickening fluids (STF) are disclosed. The STF-intercalated textiles are light weight and include high tenacity textiles that exhibit enhanced resistance to puncture, cutting, abrasion, dust penetration, and projectile penetration. Also disclosed are multi-layer articles, such as safety suits and extra-vehicular mobility units, which include STF-intercalated textiles. Methods for manufacturing STF-intercalated textiles are also disclosed.

A temperature control system may include a heat exchanger configured to cool air within a pressurized enclosed crew cabin when the air is circulated across the heat exchanger and coolant is circulated through the heat exchanger. The system may further include a sublimator configured to cool the coolant. The system may also include a primary coolant line configured to transport the coolant from the sublimator through the heat exchanger.

A temperature control system may include a heat exchanger configured to cool air within a pressurized enclosed crew cabin when the air is circulated across the heat exchanger and coolant is circulated through the heat exchanger. The system may further include a sublimator configured to cool the coolant. The system may also include a primary coolant line configured to transport the coolant from the sublimator through the heat exchanger.

A method of additively manufacturing a spacecraft panel includes printing a first skin and a second skin, spaced apart from the first skin. The method further includes printing a first truss structure connecting the first skin to the second skin.

A composite material comprising a first shielding layer (210); at least one metal containing layer (208) over the first shielding layer; and a second shielding layer (206) over said at least one metal containing layer opposite of the first shielding layer; wherein the first shielding layer (210) and the second shielding layer (206) each and/or in combination with other layers of the composite material provide the composite material with radiation shielding characteristics.

A collision-avoidance propulsion system and method for orbiting satellites and other spacecraft takes advantage of ambient cosmic rays in space to catalyze micro-fusion events via particle-target fusion and muon-catalyzed fusion processes, using the reaction products to produce thrust upon orbiting satellites and other spacecraft. A supply of deuterium-containing particle fuel material is propelled in a specified direction of the spacecraft in response to indication of a potential collision with another space object (e.g. orbiting debris). In one embodiment, this may be performed by propellant gas expelling the fuel material through conduits to specified ports on the exterior of the spacecraft. The propelled material interacts with the ambient cosmic rays and muon generated from those cosmic rays to induce micro-fusion. A portion of the energetic reaction products (e.g. alpha particles) are received upon the spacecraft to alter its trajectory in a manner that avoids the potential collision.

A collision-avoidance propulsion system and method for orbiting satellites and other spacecraft takes advantage of ambient cosmic rays in space to catalyze micro-fusion events via particle-target fusion and muon-catalyzed fusion processes, using the reaction products to produce thrust upon orbiting satellites and other spacecraft. A supply of deuterium-containing particle fuel material is propelled in a specified direction of the spacecraft in response to indication of a potential collision with another space object (e.g. orbiting debris). In one embodiment, this may be performed by propellant gas expelling the fuel material through conduits to specified ports on the exterior of the spacecraft. The propelled material interacts with the ambient cosmic rays and muon generated from those cosmic rays to induce micro-fusion. A portion of the energetic reaction products (e.g. alpha particles) are received upon the spacecraft to alter its trajectory in a manner that avoids the potential collision.

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.