A multilayer particle shield for a spacecraft includes an inboard exterior layer configured to be disposed proximal to the spacecraft, an outboard exterior layer configured to be disposed distal from the spacecraft and at least one interior layer disposed between the inboard exterior layer and the outboard exterior layer, wherein the interior layer includes a semi-rigid, porous, compressible spacer.

Systems for insulating a space vehicle or space borne container from an external environment as well as cryogens from heat sources. Such systems also protect the vehicle from the high dynamic pressures, the high heat loads encountered in atmospheric flight, and provide storage capability that strongly limits, or effectively eliminates, cryogenic boil-off losses once in space. Such systems include an expandable structure having a plurality of contiguously adjacent expandable layers. The layers are connected by a plurality of tension connectors between successive layers. For launch and flight the layers can be restrained in a collapsed position. Whereupon exiting a free stream environment, the layers are expanded where they can lock into place or otherwise remain in an expanded state. The expansion creates separation between the layers with minimal conduction paths providing near theoretically perfect multi-layer insulation and extremely effective debris protection.

Systems for insulating a space vehicle or space borne container from an external environment as well as cryogens from heat sources. Such systems also protect the vehicle from the high dynamic pressures, the high heat loads encountered in atmospheric flight, and provide storage capability that strongly limits, or effectively eliminates, cryogenic boil-off losses once in space. Such systems include an expandable structure having a plurality of contiguously adjacent expandable layers. The layers are connected by a plurality of tension connectors between successive layers. For launch and flight the layers can be restrained in a collapsed position. Whereupon exiting a free stream environment, the layers are expanded where they can lock into place or otherwise remain in an expanded state. The expansion creates separation between the layers with minimal conduction paths providing near theoretically perfect multi-layer insulation and extremely effective debris protection.

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 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.

Systems, methods and apparatus related to a self-preservation/self-protection system (SPS). The SPS system includes a local area situation awareness sensor suite (LASASS), multiple central pattern generator (mCPG) decision circuitries and related actuators. The SPS system utilizes the LASASS, mCPG circuitries and actuators to perform the desired processing and effectuate changes in the position of an object to be detected or avoided.

Systems, methods and apparatus related to a self-preservation/self-protection system (SPS). The SPS system includes a local area situation awareness sensor suite (LASASS), multiple central pattern generator (mCPG) decision circuitries and related actuators. The SPS system utilizes the LASASS, mCPG circuitries and actuators to perform the desired processing and effectuate changes in the position of an object to be detected or avoided.

A part of a spacecraft, for instance an upper stage, is configured to re-enter into the atmosphere and to be reused for several missions. The part is equipped with a reusable kit comprising non-ablative heat shields, for example constructed with an outer surface formed of Ceramic Matrix Composites, such as Ultra High Temperature Ceramic Matrix Composites, and optionally at least one decelerator and/or at least one parachute and/or parafoil system.