Abstract: A hinge system for deploying panels or other structures from a satellite or spacecraft has at least two configurations. The panels are held in a substantially stacked disposition in the stowed configuration by the hinge system which connects to each panel and includes an intermediate arm sized to span any necessary space between the two panels in the stowed configuration. A deployment cable is attached to one of the panels and threaded over a series of pulleys disposed on the hinge system and onto a spool in the other panel. When the spool is driven to wind the deployment cable onto it, the tension in the cable pulls on the pulleys, causing the hinge to unfold and then slide into a housing located on one of the panels. This deployed configuration allows the panels to be held aligned and directly adjacent to one another by the tension of the deployment cable.

Abstract: A boom assembly for a rocket-launched spacecraft, the boom assembly comprising a plurality of rigid sections and a plurality of elastic sections that pivotally connect each of the rigid sections together so as to enable the boom assembly to be folded into a storage configuration and so as to enable the boom assembly to be automatically unfolded into a deployed configuration that provides the spacecraft with a large rigid extending platform. At least one of the rigid sections is mounted to the spacecraft so as to secure the boom assembly to the spacecraft. In one embodiment, a plurality of extendable components, such as solar panels and radar antennae, are mounted to the rigid sections so as to allow for storing and deploying the extendable components. In another embodiment, there may be no components mounted other than a length of wire or a length of metal tape which will allow the boom to act as an antenna.

Abstract: A spacecraft, such as a satellite, includes a panel array comprised of a plurality of panels that are stacked together and secured to the side of the satellite during launch. At least one shear tie device is configured to couple the panels together in shear to increase the resistance to deformation of the stack of panels. The shear tie device preferably comprises a male member that mates with a female member. A plurality of fingers secure the male member within the female member during launch. Upon reaching orbit, a bladder is inflated which deforms the fingers and releases the male member from engagement with the female member.

Abstract: A reflector assembly for use in antennas or solar collectors in which light weight and high reflector surface shape accuracy are essential for maintaining desired RF or light reflection requirements. The assembly is provided with a rigid, deployable outer support rim and at least one curved frame net supported by the outer rim. The frame net may be formed of a network of intersecting bands extending across the surface. A reflective material is placed against the frame net. A load is applied to the frame net to form a concave surface. The assembly is collapsible for convenient delivery into space prior to deployment.

Abstract: A low concentration solar array for spacecraft and other uses which has a series of solar panels which can be deployed from a folded stowed configuration to a planar configuration. When the solar panels are stowed, the padding of reflector panels cushions and protects the solar panels from the stresses and vibrations of launch and space flight. Once the solar panels are extended into a deployed planar configuration, the reflector panels are raised to concentrate sunlight upon the solar panels. These reflector panels are constructed from rigid honeycomb substrates and therefore are the active structural members of the solar array, providing the structural rigidity for the solar array.

Abstract: A release mechanism for attaching and releasing appendages from a main body such that shock and frictional effects are minimized. The release mechanism comprises a housing, a main cylindrical body, a collet, a toroidal spring and actuators, where the main cylindrical body includes radial projections. A wrap spring couples the collet and the toroidal spring.

Abstract: A deployable and retractable, telescoping style mast assembly and method employs a plurality of tubular sections of differing diameters. The tubular sections are nested one-in-another and are slidable with respect to each other, in a telescoping manner, to provide a deployable/retractable telescoping mast assembly. Retractable pins are provided to retractably extend from a collar coupled to at least one of the tube sections. In their extended state, the retractable pins are adapted to extend through apertures provided in an adjacent tube section. The retractable pins are provided with a head at one end thereof. The head of each pin is adapted to be engaged by a guide coupled to a third tube section upon the third tube section being in a collapsed state. Upon engagement with the pin head, the guide operates to pull the pin into a retracted state so as to retract the pin out of the pin receiving aperture.

Abstract: A truss structure, which is movable between a collapsed position and a deployed position, has at least one frame section. The frame section has a number of frame units, wherein each frame unit includes three elongated members forming a triangle independent of the triangle formed by the other frame units. A first elongated member of each frame unit is coupled to a first elongated member of another frame unit such that these coupled first elongated members form a polygon. The remaining elongated members of each frame unit are pivotally connected to the first elongated member of their respective frame unit so as to be pivoted with respect to the first elongated member during movement of the truss structure between the collapsed and deployed positions. A number of foldable batten members are connected at their ends to the frame units to form a second polygon. The foldable batten members fold, approximately at their midpoints, during movement of the truss structure between the collapsed and deployed positions.

Abstract: In a deployable mast composed of: a plurality of resiliently flexible longeron elements; a plurality of resiliently flexible lateral elements arranged in groups of lateral elements constituting batten frames spaced apart along the longeron elements and delimiting respective bays of the mast, with each group of lateral elements being connected to all of the longerons; and a plurality of flexible diagonal elements each connected between two longeron elements and extending between two groups of lateral elements, the longeron, lateral and diagonal elements being constructed and connected to constitute a structure movable between a deployed state defining a column of predetermined length and a stowed state defining a structure having a length less than the predetermined length, there are provided five such longeron elements and each group of lateral elements is connected to all of the longeron elements.

Abstract: A deployable truss structure desirable for space applications is disclosed. The structure is triangular in cross section, with each longitudinal face of the structure being comprised of parallel longeron members interconnected by parallel batten members, the battens located at the mid-section of each face being non-rigid members, the structure including hinged diagonal members.

Abstract: An erectable structure truss attachment joint includes a first truss having a casing containing a piston between a flange on the end of the casing and a wedge threadably mounted on an adjustment screw inside the casing. A tension rod passing through the wedge and the piston has a knob extending out of the casing on one end and an end bolt holding a leaf spring against the wedge on the other. A helical spring inside the casing creates pressure between the piston and the tension rod. A second truss has a notched retention wall at one end forming a chamber. The knob of the tension rod is inserted into the chamber to attach the two trusses. When the adjustment screw is tightened, the wedge acts against angled faces of the leaf spring on one side and the piston on the other side to create pressure against the piston and the leaf spring. The leaf spring exerts pressure against the end bolt to pull the tension rod into the interior of the casing.