Abstract: A spacecraft capable of generating an artificial gravity environment comprises frame with a circular track with at least two modules traveling on the track. The two modules are configured to engage the first track opposite the first module to minimize mass imbalance, and a balancing system for the first and second modules configured to mass balance the first and second modules relative to each other. The frame itself does not rotate, and may have other mission supporting structures attached, including storage and supply modules, and observational modules, and spacecraft hangars and spacecraft docking modules. A method of operating a spacecraft to generate artificial gravity in a habitation module comprises operating a frame in space, propelling first and second habitation modules about the frame to generate artificial gravity environments in the modules, and mass balancing the first module relative to the second module to maintain balance of the spacecraft.

Abstract: The present invention relates to an innovative thermal design concept of tailoring the absorptance and emittance of a coating—namely silicon oxide (SiOx) coated aluminized Kapton—as a radiator coating for small, nano-satellite (i.e., CubeSat) thermal management. The present invention improves on the thermal design of existing satellites, by: a) thermally coupling all components to the baseplate to eliminate the need for heater power for the battery; b) using all six sides of the CubeSat as radiators by changing the wall material from fiberglass to aluminum; c) using a different ratio of absorptance to emittance for each side by tailoring the SiOx thickness; d) having a high emittance for the wall interior and components; and e) eliminating the need for MLIs. The elimination of the MLIs reduces the volume and increases the clearance to minimize the risk for solar array deployment and cost of the thermal control subsystem.

Abstract: 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.

Abstract: A moon/planet complex, an orbiting docking spaceport, and transportation vehicles therebetween that includes i) moon/planet base station having a landing platform with a plurality of charged plates; ii) a moon/planet orbiting craft, docking spacecraft having landing platform with a plurality of charged plates; iii) a personnel transport spacecraft to shuttle personnel between an orbiting craft and planetary/moon base station having rotating electromagnetic rings 320 and/or rotating electromagnetic plates to interact with charged plates; iv) a large personnel/cargo transport spacecraft to shuttle personnel between an orbiting craft and planetary base station having rotating electromagnetic plates to interact with charged plates.

Abstract: In a method for packing a spacecraft membrane (1) which in a plane of extension comprises a longitudinal axis between opposite longitudinal corners (4) and a transverse axis running transverse to the longitudinal axis and through transverse corners into a spacecraft membrane package, two packing steps are executed: In a first packing step, the spacecraft membrane (1) is packed into a transverse package (9) along the transverse axis. In a second packing step, the transverse package (9) is packed into a longitudinal package along a longitudinal axis. The packing of the spacecraft membrane (1) in the first packing step comprises a packing of material of the spacecraft membrane (1) from or on both sides of the longitudinal axis. In the first packing step, the spacecraft membrane (1) is packed in such a way that in the created transverse package (9) the transverse corners are freely accessible.

Abstract: A gateway segment assembly line that allows for the construction of space stations while in orbit by fabricating individual segments in space. An assembly housing provides an open ended structure through which materials are processed in order to construct a segment for a space station. The materials are loaded into a plurality of workstations positioned along the assembly housing through the use of a plurality of external manipulators adjacently connected to the assembly housing. Each of the plurality of workstations provides the equipment for sequentially loading materials into the assembly housing. An assembly line conveyor, positioned throughout the plurality of workstations, guides materials through the assembly housing as the materials are mated to form the segment. Upon completion of the segment, a plurality of segment transport units transports the segment to an orbital construction site, wherein the segment is mated with subsequent segments to form the space station.

Abstract: Modeling and control software that integrates the complexities of solar array models, a space environment, and an electric propulsion system into a rigid body vehicle simulation and control model is provided. A rigid body vehicle simulation of a solar electric propulsion (SEP) vehicle may be created using at least one solar array model, at least one model of a space environment, and at least one model of a SEP propulsion system. Power availability and thrust profiles may be determined based on the rigid body vehicle simulation as the SEP vehicle transitions from a low Earth orbit (LEO) to a higher orbit or trajectory. The power availability and thrust profiles may be displayed such that a user can use the displayed power availability and thrust profiles to determine design parameters for an SEP vehicle mission.

Abstract: System and method for inducing rapid reentry of orbital debris including determining a spatial extent of the orbital debris, and deploying dust to the orbital debris to enhance the drag on the orbital debris. Small objects with perigee above about 900 km where the debris lifetime can be centuries can be targeted for de-orbiting.

Abstract: System and method for inducing rapid reentry of orbital debris including determining a spatial extent of the orbital debris, and deploying dust to the orbital debris to enhance the drag on the orbital debris.

Abstract: A detachable inflation system for use with an air vehicle having at least one inflatable structure. The detachable inflation system comprises a pallet structure. The detachable inflation system further comprises an initial inflation system, attached to the pallet structure, that provides one or more compressed fluids. The initial inflation system is connected to an inflation distribution system in the air vehicle for distributing the one or more compressed fluids into the inflatable structure to inflate the inflatable structure. The detachable inflation system further comprises a detachable parachute.

Abstract: An air barrier having a scuff coating is used in connection with the core of a spacecraft to form an inflatable, or expandable, human habitat module. The air barrier is comprised of a number of segments joined together to form a enclosure that has at least one opening. The joined segments are generally gas impermeable, flexible, and have a scuff coating on both sides of the segments.

Abstract: Methods and systems may provide for a structure having a plurality of interconnected panels, wherein each panel has a plurality of detection layers separated from one another by one or more non-detection layers. The plurality of detection layers may form a grid of conductive traces. Additionally, a monitor may be coupled to each grid of conductive traces, wherein the monitor is configured to detect damage to the plurality of interconnected panels in response to an electrical property change with respect to one or more of the conductive traces. In one example, the structure is part of an inflatable space platform such as a spacecraft or habitat.

Abstract: A processing and delivery system is in space around a celestial body having a magnetic field. The system includes at least one facility having supplies and configured for in-space recycling and manufacturing to produce processed objects utilizing space debris objects and the supplies. The system includes at least one space vehicle configured to deliver the space debris objects from their orbits to the at least one facility using electrodynamic propulsion. The system includes at least one space vehicle configured to deliver new supplies to the at least one facility from other orbits using electrodynamic propulsion. The system includes at least one space vehicle configured to deliver the processed objects from the at least one facility to their destination orbits using electrodynamic propulsion.

Abstract: An inflatable dummy target fittable into a carrier missile capable of being released from the carrier missile during exo-atmospheric flight; upon release, the dummy target or portion thereof is capable of being inflated and manifest characteristics that resemble GTG missile characteristics, wherein the GTG missile characteristics include IR signature, RF signature and GTG missile

Abstract: A method of assembling an inflatable shell of a structure comprises folding a plurality of shell sections about a set of fold lines and integrating the plurality of shell sections together with one another to form the shell. In another embodiment, an inflatable shell comprises a plurality of shell sections, each shell section having two pairs of fold lines for folding into stowage comprising a first gore section having a plurality of first gore panels layered and collectively folded about at a first set of fold lines. Each layer of the first gore panels and second gore panels are configured such that, once the first gore panel and second gore panel are attached to one another at the respective side edges of each panel, the lines of attachment forming a second set of fold lines for the shell section. A system and method for fabricating gore panels is also disclosed.

Abstract: A flexible vessel includes a restraint structure and a barrier structure. The restraint structure further includes a first portion, and a second substantially rounded end cap portion that is attached to the first portion. The restraint structure also includes an array of tendons. The barrier structure is positioned within the restraint structure. When the barrier contains a fluid, a portion of the load is carried by the restraint structure and another portion of the load is carried by the barrier structure. The flexible vessel is collapsible to occupy a first volume and distended to occupy a second volume. The flexible vessel is part of a system when used in various applications with respect to a craft.

Abstract: A method of assembling an inflatable shell of a structure comprises folding a plurality of shell sections about a set of fold lines and integrating the plurality of shell sections together with one another to form the shell. In another embodiment, an inflatable shell comprises a plurality of shell sections, each shell section having two pairs of fold lines for folding into stowage comprising a first gore section having a plurality of first gore panels layered and collectively folded about at a first set of fold lines. Each layer of the first gore panels and second gore panels are configured such that, once the first gore panel and second gore panel are attached to one another at the respective side edges of each panel, the lines of attachment forming a second set of fold lines for the shell section. A system and method for fabricating gore panels is also disclosed.

Abstract: An inflatable structure comprises at least two generally toroidal, inflatable modules. When in a deployed mode, the first, inner module has a major diameter less than that of a second, outer module and is positioned within the inner circumference of the outer module such that the first module is nested circumferentially alongside the second module. The inflatable structure, in a non-deployed, non-inflated mode, is of compact configuration and adapted to be transported to a site of deployment. When deployed, the inflatable structure is of substantially increased interior volume. In one embodiment, access between the interior of the first module and the second module is provided by at least one port or structural pass-through. In another embodiment, the inflatable structure includes at least one additional generally toroidal module external of and circumferentially surrounding the second module.

Abstract: An inflatable structure comprises at least two generally toroidal, inflatable modules. When in a deployed mode, the first, inner module has a major diameter less than that of a second, outer module and is positioned within the inner circumference of the outer module such that the first module is nested circumferentially alongside the second module. The inflatable structure, in a non-deployed, non-inflated mode, is of compact configuration and adapted to be transported to a site of deployment. When deployed, the inflatable structure is of substantially increased interior volume. In one embodiment, access between the interior of the first module and the second module is provided by at least one port or structural pass-through. In another embodiment, the inflatable structure includes at least one additional generally toroidal module external of and circumferentially surrounding the second module.

Abstract: A method for determining a design of an inflatable module including a rigid member disposed in a restraint layer, wherein the restraint layer includes orthogonal straps, includes modeling a strap adjacent to the rigid member and a strap connected to the rigid member. The adjacent strap and the member strap extend in a first direction. The method further includes selecting a first length of the member strap such that the adjacent strap carries load before the member strap during pressurization of the inflatable module, modeling tensions in the member strap with the first length and the adjacent strap during pressurization of the inflatable model, and outputting the modeled tensions in the member strap with the first length and the adjacent strap. An inflatable module includes a member strap having a length such that an adjacent strap carries load before the member strap during pressurization of the inflatable module.

Abstract: The invention relates to a device for controlling the deployment of an inflatable structure including, in the non-deployed state, a flexible tube (12) which is folded in zigzags and fixed to one end of a plug (13) provided with a buoyant gas admission (15), the other end of the tube being closed; means (25 to 29) for controlling the change of state of the tube from the folded state (12a) to the deployed state (30), the means being arranged inside the tube (12) and consisting of a set of interconnected flexible blades (25) which are radially arranged around the strut (16) in the form of petals, in such a way that the set can be displayed along the strut; and means (28, 29) for bringing the set of petals (25) towards the plug (13) in such a way as to press the folded part (12a) of the tube, each petal (25) being applied to a series of superimposed folds (21 to 24) of the folded part of the tube.

Abstract: A flexible inflatable hinge includes curable resin for rigidly positioning panels of solar cells about the hinge in which wrap around contacts and flex circuits are disposed for routing power from the solar cells to the power bus further used for grounding the hinge. An indium tin oxide and magnesium fluoride coating is used to prevent static discharge while being transparent to ultraviolet light that cures the embedded resin after deployment for rigidizing the inflatable hinge.

Abstract: A method for transporting people and cargo from the surface of the Earth to orbit around the Earth is disclosed. The present invention uses a series of lighter-than-air vehicles to allow for a far safer and less strenuous trip to orbit than using current rocket-based technology. The high altitude atmospheric airship is flown from the ground to the upper atmosphere, where it docks with the buoyant transfer station, and from there, the people and cargo transfer to an orbital airship for the remainder of the trip to orbit. The orbital airship returns to the station for another transfer back to the atmospheric airship for the return back to the surface of Earth.

Abstract: The invention relates to a device for controlling the deployment of an inflatable structure including, in the non-deployed state, a flexible tube (12) which is folded in zigzags and fixed to one end of a plug (13) provided with a buoyant gas admission (15), the other end of the tube being closed; means (25 to 29) for controlling the change of state of the tube from the folded state (12a) to the deployed state (30), the means being arranged inside the tube (12) and consisting of a set of interconnected flexible blades (25) which are radially arranged around the strut (16) in the form of petals, in such a way that the set can be displayed along the strut; and means (28, 29) for bringing the set of petals (25) towards the plug (13) in such a way as to press the folded part (12a) of the tube, each petal (25) being applied to a series of superimposed folds (21 to 24) of the folded part of the tube.

Abstract: The invention is an aircraft having an inflatable wing connected to a base unit, with the inflatable wing inflated with a lifting gas such as helium. The inflatable wing has a series of cell structures, and may be configured with ballonets to selectively introduce and expel outside air within the inflatable wing to vary the buoyancy and/or airfoil properties of the inflatable wing. The aircraft is particularly useful at low speeds and in thin atmospheres (such as at high Earth altitudes and on Mars), and can be used for interplanetary missions to explore planetary bodies, such as moons and planets, having atmospheres.

Abstract: This document discloses, among other things, an inflatable apparatus having a plurality of attachment points. The apparatus can be collapsed, and when distended, the attachment points are dimensionally stable with varying applied pressure.

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 shear-thickening fluid is used in conjunction with fabrics utilized in an expandable spacecraft. The combination of the fluid and the fabric allows the fabric to resist penetration by hypervelocity particles in space.

Abstract: An air barrier having a scuff coating is used in connection with the core of a spacecraft to form an inflatable, or expandable, human habitat module. The air barrier is comprised of a number of segments joined together to form a enclosure that has at least one opening. The joined segments are generally gas impermeable, flexible, and have a scuff coating on both sides of the segments.

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: A flexible vessel includes a restraint structure and a barrier structure. The restraint structure further includes a first portion, and a second substantially rounded end cap portion that is attached to the first portion. The restraint structure also includes an array of tendons. The barrier structure is positioned within the restraint structure. When the barrier contains a fluid, a portion of the load is carried by the restraint structure and another portion of the load is carried by the barrier structure. The flexible vessel is collapsible to occupy a first volume and distended to occupy a second volume. The flexible vessel is part of a system when used in various applications with respect to a craft.

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: A computer-implemented method is provided for designing a restraint layer of an inflatable vessel. The restraint layer is inflatable from an initial uninflated configuration to an inflated configuration and is constructed from a plurality of interfacing longitudinal straps and hoop straps. The method involves providing computer processing means (e.g., to receive user inputs, perform calculations, and output results) and utilizing this computer processing means to implement a plurality of subsequent design steps. The computer processing means is utilized to input the load requirements of the inflated restraint layer and to specify an inflated configuration of the restraint layer. This includes specifying a desired design gap between pairs of adjacent longitudinal or hoop straps, whereby the adjacent straps interface with a plurality of transversely extending hoop or longitudinal straps at a plurality of intersections.

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: According to invention, said elements (1.1 to 1.n) are secured to the same side (3) of a flexible inflatable mattress (4) and, when said elements are in the folded state, said mattress (4) is in the deflated state and is folded so that said elements are situated in pairs on either side of a fold (5.1 to 5.n?1) of said mattress.

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.