Abstract: A regolith container for use with regolith on an extraterrestrial mass is disclosed. The filled container covers a portion of a spacecraft to provide the spacecraft with a measure of protection against space debris and radiation. The container can be compartmentalized to reduce the loss of regolith should from the container if a single compartment is penetrated.

Abstract: A method for assembling and landing a habitable module on an extraterrestrial mass is claimed. At least one inflatable module and a second module are placed into orbit about an extraterrestrial mass. Connecting nodes, propulsion busses, and landing pads are also placed into orbit. A habitable structure is constructed from the modules, busses, pads, and nodes. The structure can be robotically constructed. The habitable structure is then landed onto the surface of the extraterrestrial mass. The landing can be remotely controlled and the modules can be non-occupied.

Abstract: A modular human habitat simulator for providing an environment on Earth that approximates, in a controlled test situation, a number of conditions expected to exist when an inflatable modular habitat is deployed into Earth orbit. The simulator has a housing with a rigid wall defining an internal volume, a longitudinal axis, a first and second opposing openings along the longitudinal axis, the rigid wall having an exterior surface, and an interior surface where the interior surface is generally the shape of an interior surface of a deployed inflatable shell of a modular human habitat, and the internal volume is substantially that of a deployed inflatable modular human habitat volume.

Abstract: An orbital debris shield for protecting the hull of a spacecraft. The shield is comprised of a number of flexible and releasably attached gores that substantially cover the hull. Interleafed between layers of the gores are layers of a spacing material. As debris collides with the gores, the material is shocked and breaks up to some degree. As the shocked debris disperses through a layer of the gore, the spacing material interacts with the debris. After dispersing through a number of layers of the gores and the spacing material, the debris transfers a significant portion of kinetic energy and the probability of the remaining particles piercing the hull is significantly decreased.

Abstract: An orbital debris shield for protecting the hull of a spacecraft is claimed. The shield is comprised of a number of flexible and releasably attached gores that substantially cover the hull. Interleafed between layers of the gores are layers of a spacing material. As debris collides with the gores, the material is shocked and breaks up to some degree. As the shocked debris disperses through a layer of the gore, the spacing material interacts with the debris. After dispersing through a number of layers of the gores and the spacing material, the debris transfers a significant portion of kinetic energy and the probability of the remaining particles piercing the hull is significantly decreased.

Abstract: A flexible structural restraint layer for use with an inflatable modular structure, having a fore and aft assembly separated by a longeron and an inflatable bladder. The restraint layer is comprised of two circumferential strap assemblies, each attachedly fastened at opposing ends of a radial strap assembly. There are a plurality of axial straps that are secured in place to the circumferential strap assemblies and the radial strap assembly. The restraint layer surrounds the bladder and the ends of the axial straps are secured in place at the fore and aft end of the modular structure. When the bladder is inflated, the structural restraint layer distributes the load created by the inflated bladder.

Abstract: The present invention provides a sealing and restraint apparatus to establish a pressure boundary for inflatable or expandable spacecraft. The apparatus is capable of connecting the flexible pressure boundary of an inflatable spacecraft to the rigid structure of the spacecraft. The flexible pressure boundary of the present invention comprises a gas membrane and a restraint layer. The gas membrane minimizes air leakage. The restraint layer carries the forces created by the internal pressurization of the spacecraft. This apparatus provides a hermetic seal and the structural integrity necessary to resist internal pressurization forces.

Abstract: An inflatable satellite bus is claimed for use with a mission payload. The inflatable satellite bus is comprised of a core adapted to receive a mission payload. There is an expandable shell attached to the core and substantially enclosing the core. The core has an attitude control device and a power system attached to the core and operated by a controller.

Abstract: A spacecraft window assembly for providing external viewing from inside an inflatable module is claimed. The inflatable shell has a plurality of layers and each layer has a window opening. The spacecraft window assembly comprises a body, a window assembly window opening, and at least one pressure pane disposed within, and forming a substantially airtight seal with, the window assembly. The body of the window assembly is adapted for securedly receiving each one of the plurality of layers of the inflatable shell to the body of the window assembly such that the window opening in each layer of the inflatable shell is substantially aligned with the pressure pane. Further, the body of the window assembly is adapted to form a substantially air tight seal with at least one layer of the inflatable shell.

Abstract: A method for making an opening in the bladder of an inflatable modular structure. The structure has a core comprised of a fore and aft assembly separated by a longeron. There is an inflatable bladder and a restraint layer that are secured to the core. The restraint layer is comprised of two circumferential strap assemblies; each attachedly fastened at opposing ends of a radial strap assembly, and has an opening for a window. The restraint layer fits over the bladder. The bladder is inflated and the restraint layer is used along with a window template to locate the position of the window on the bladder. The bladder is deflated, the template is removed, and the identified portion of the bladder is cut away. The method may then be repeated.

Abstract: An apparatus is disclosed for disposing of biomass material. The apparatus may include a receiving chamber for receiving a biomass, a maceration chamber for macerating the biomass received from the receiving chamber and producing macerated biomass, and an incinerating chamber incinerating the macerated biomass into a incinerated biomass. The apparatus is particularly suited to operate in remote or zero-gravity environments.

Abstract: The present invention provides a thermal, and if desired, a radiation barrier to protect the exterior surface of a spacecraft. In particular, the present invention protects the polymeric materials of construction utilized in inflatable and expandable spacecraft from the deleterious effects of both thermal and radiation aging. The protective barrier is formed from a tube or tubes through which a fluid circulates. The tube segment substantially enclose the spacecraft, and in particular, the critical layers that are desired to be protected. This protective barrier provides a thermal heat sink, temperature equalization, and a waste heat rejection system, that can moderate the temperature extremes encountered by spacecraft. In addition, dependent on the fluid selected, substantial radiation shielding can be provided that can protect the entire spacecraft.