Abstract: An A-frame shaped truss foundation system for a single-axis tracker with moderately sloped legs that translate lateral loads into tension and compression without substantially increasing the magnitude of the lateral load force while optimizing material usage. Several such truss foundation systems are installed in a row to support a torque tube of a single-axis solar tracker. An adapter joins ends of adjacent upper legs and separates the truss legs by an angle more than 35-degrees up to 70-degrees. In some cases, the adapter may have an integrated bearing.

Abstract: The present invention relates to an advanced spaceborne Synthetic Aperture Radar (SAR) system and method that can provide high resolution measurements of the Earth or planetary surface, overcoming limitations in conventional SAR systems, and reduce development costs. The present invention utilizes advanced and innovative techniques, such as software defined waveforms, digital beamforming (DBF) and reconfigurable hardware, to provide radar capabilities not possible with conventional radar instruments, while reducing the radar development cost. The SAR system architecture employs a modular, low power, lightweight design approach to meet stringent spaceborne radar instrument requirements.

Abstract: A method for installing an interior structure for a mobile platform is provided. The method may involve carrying a lightweight collapsible frame through a man-door of a mobile platform while the collapsible frame is in a collapsed state. The collapsed frame may then be expanded to provide at least a portion of a load bearing frame for a mobile platform interior structure. A plurality of interchangeable panels may be attached to the collapsible frame to form interior surfaces of the mobile platform interior structure.

Abstract: A system for concentrating solar radiation onto a space debris object to vaporize includes a focusing system, an object tracking system and a positioning system. The focusing system has a total focal length fT, and includes a first focusing device and a second focusing device. The first focusing devices change from a compact state to a deployed state, and the compact surface area is less than the deployed surface area. The object tracking system determines the location of the object. The positioning system orients the focusing system such that solar radiation focuses on the space debris object.

Abstract: The present invention consists of an active tie-rod device making it possible to hold and smoothly release space appendages. The active tie-rod device includes a fixed base, an active tie-rod screwed into the said fixed base, a retractable release mechanism for the active tie-rod making it possible, in the stowed position, to hold the said active tie-rod in place, and a nut for tensioning the assembly. The active tie-rod includes an internal heater, and consisting at least partially of a material with a high coefficient of thermal expansion, so that, under the action of the internal heater, the active tie-rod can expand, retracting the retractable release mechanism for the active tie-rod, and consequently allowing the smooth release of the said space appendages.

Abstract: A polygonal support structure is disclosed herein. The polygonal support structure has a plurality of rigid segments configured to be joined at longitudinal ends by a joint affixed to at least one end of each rigid segment. Each joint is configured to rigidly, rotatingly or hingedly join each rigid segment to an adjacent rigid segment to form the polygonal support structure. A plurality of flexible members are configured and disposed to provide tension between each joint and joints spaced two segments therefrom, in each direction, about the polygonal support structure. One or more joints may be configured to join and un-join two adjacent rigid segments and each rigid segment and each joint may be configured to enable stacking of rigid segment into a compact configuration for transport. In at least one aspect, a polygonal support structure may be configured to support assemblies in a substantially weightless environment.

Abstract: Structures and methods are disclosed regarding deployable structures with expandable longerons adjustably coupled with supporting structures such that an angle between the supporting structures can be adjusted. Such structures can include and/or be used for solar arrays, bridges, support structures, and more. These structures can be easily transported to a new location and deployed from the stowed configuration into a larger functional structure. In some embodiments these structures can use one or more longerons that can have two resting states: deployed and rolled.

Abstract: A deployable structure that may include a slit-tube longeron and a flat panel coupled with the slit-tube longeron. The slit-tube longeron may include a tubular member having a slit that runs along the longitudinal length of the slit-tube longeron. The deployable structure may be configured to couple with a satellite. And the deployable structure may be configured to transform between a stowed state and a deployed state where the tubular member is substantially straight when the deployable structure is in the deployed state, and the tubular member is wrapped around the satellite when the deployable structure is in the stowed state.

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: Flexible and resilient masts are connected by flexible and resilient inner and outer spars, and flexible cords radially connect the spars. A flexible material is attached to the cords. The assembly is wrapped around a rotatable cylindrical drum in the structure's stored configuration. Each mast is flexible only about an axis lying parallel to the axis of rotation of the drum, and is otherwise rigid. Each mast is linear when extended and has a bending stress when deformed into a non-linear configuration, such as when wrapped around the drum. When the structure is in its stored configuration, a restraining device opposes the bending stress and another prevents the drum from rotating. Upon disengagement of the restraining devices, the stored bending strain energy forces the drum to rotate and the masts to extend into the deployed configuration and thereby unfurl the flexible material.

Abstract: Structures and methods are disclosed regarding deployable structures with expandable longerons adjustably coupled with supporting structures such that an angle between the supporting structures can be adjusted. Such structures can include and/or be used for solar arrays, bridges, support structures, and more. These structures can be easily transported to a new location and deployed from the stowed configuration into a larger functional structure. In some embodiments these structures can use one or more longerons that can have two resting states: deployed and rolled.

Abstract: Deployable structures are disclosed having collapsible structural members that include a stowed configuration with a volume smaller than the expanded configuration. Such structures can include and/or be used for litters, bridges, support structures, solar arrays, and more. These structures can be easily transported to a new location and deployed from the stowed configuration into a larger functional structure. In some embodiments these structures can use one or more slit-tube longerons that can have two resting states: deployed and rolled.

Abstract: A deployable structure is disclosed. The deployable structure may include one or more slit-tube longerons; and one or more flat sheets coupled with the one or more slit-tube longerons. The one or more slit-tube longerons and the one or more flat sheets may be stowed by rolling the one or more slit-tube longerons and the one or more flat sheets together into a roll. In one embodiment, at least a portion of the one or more slit-tube longerons may be exposed when stowed. In another embodiment, the one or more slit-tube longerons may be manufactured from a shape memory material. These slit-tube longerons unroll into to a straight configuration when exposed to heat.

Abstract: A method for installing an interior structure for a mobile platform is provided. The method includes carrying a lightweight collapsible frame through a man-door of a mobile platform while the collapsible frame is in a collapsed state. The collapsed frame is then expanded to provide at least a portion of a load bearing frame for a mobile platform interior structure. A plurality of interchangeable panels are removable attached to the collapsible frame to form interior surfaces of the mobile platform interior structure.

Abstract: The present invention consists of an active tie-rod device making it possible to hold and smoothly release space appendages. The active tie-rod device includes a fixed base, an active tie-rod screwed into the said fixed base, a retractable release mechanism for the active tie-rod making it possible, in the stowed position, to hold the said active tie-rod in place, and a nut for tensioning the assembly. The active tie-rod includes an internal heater, and consisting at least partially of a material with a high coefficient of thermal expansion, so that, under the action of the internal heater, the active tie-rod can expand, retracting the retractable release mechanism for the active tie-rod, and consequently allowing the smooth release of the said space appendages.

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: In one aspect, a space vehicle includes a structure configured to expand from a first configuration to a second configuration and at least two equipment compartments attached to the periphery of the structure. The structure includes at least one of an antenna mesh, a light-shielding mesh, an optical reflector mesh and a net. In another aspect, a space vehicle includes an antenna structure configured to expand from a first configuration to a second configuration and at least two equipment compartments attached to the periphery of the antenna structure. At least one of the at least two equipment components include a solar panel, a propulsion system and an antenna feed. In a further aspect, a space vehicle includes a payload element and at least two spacecraft-support structures attached to the periphery of the payload element. At least one of the at least two spacecraft-support structures includes a propulsion system and a tracking, telemetry and control system.

Abstract: For an inflatable structure having a flexible outer shell or wall structure having a flexible restraint layer comprising interwoven, load-bearing straps, apparatus for integrating one or more substantially rigid members into the flexible shell. For each rigid member, a corresponding opening is formed through the flexible shell for receiving the rigid member. A plurality of connection devices are mounted on the rigid member for receiving respective ones of the load-bearing straps.

Abstract: A folding, retractable dome for protecting a feature, such as a docking mechanism, a hatch or other equipment at an exterior surface of a space vehicle, includes a plurality of arcuate ribs, each having opposite ends respectively pinioned at opposite sides of the feature at the surface of the vehicle for rotational movement about an axis of rotation extending through the opposite ends and through an arcuate path of revolution extending over the feature, and a flexible cover attached to each of the ribs such that, in a deployed configuration of the dome, in which adjacent ribs are rotated apart from each other at a maximum relative angle therebetween, the cover is stretched generally tangentially between the adjacent ribs to form a generally arcuate shield over the feature, and in a retracted position of the dome, in which adjacent ribs are rotated together at a minimum relative angle therebetween, the cover is collapsed to define folded pleats between the adjacent ribs.

Abstract: The invention relates to devices for releasing the stacking tie-rods that are used for holding deployable structures, in particular solar panels of artificial satellites. The device of the invention is self-releasing in order to enable such deployable structures to be released via the top portion of the stacking column. The invention consists in holding together the members (101) that are to be deployed by means of a tie-rod (102) having a nut (111) screwed onto its free end. The force for holding the stack together is transmitted by modules (106, 107) which are themselves held together by said force. When the stacking tension is reduced, resilient means, such as two flat spring blades (112, 113), cause the modules to move away from the tie-rod, thus enabling the members of the deployable structure to be released.

Abstract: A truss structure for supporting a membrane that is to be deployed in space, where the truss structure maintains the membrane sufficiently flat with uniform tension. The truss structure includes a circular perimeter truss and a transitional truss. The transitional truss includes a series of ties that are coupled to the perimeter truss and the membrane. When the truss structure is deployed, telescopic parts of the perimeter truss that are stowed in expansion cause the transitional truss to expand and pull the membrane into the flat configuration.

Abstract: An interior structure for a mobile platform is provided. The interior structure is constructed of a lightweight collapsible frame that can be reconfigured from a compact, substantially flat collapsed state to a non-compact, substantially sprawling expanded state. In the expanded state, the collapsible frame provides at least a portion of a structural load bearing frame for the interior structure. The interior structure additionally includes a plurality of interchangeable panels that attach to the collapsible frame to form interior surfaces of the structure. The panels form such things as the interior wall, ceiling and floor surfaces and can also include amenities such as shelves, lights, beds, closets, electrical outlets, Internet connections and entertainment equipment. The interior structure can be carried though the typical man-door of a mobile platform.