Abstract: A deployable and tracked solar array mechanism for restraining and releasing deployable solar panel arrays on a spacecraft is provided. The mechanism comprises a solar array drive mountable to the top side surface of the spacecraft. A solar panel array is pivotally attached to the solar array drive and positionable against the spacecraft. At least one notch is formed in at least one of the side edges of the solar panel array. A frame is slidably mounted to the spacecraft around the solar panel array. At least one tab extends from the frame over the solar panel array and releasably restrains the solar panel array. A spring mechanism urges the frame in a direction generally away from the solar array drive assembly.

Abstract: The present invention relates to a metal or alloy substrate having a modified surface, and more particularly a stainless steel substrate, produced by the use of an electrochemical process. The invention also relates generally to a method for producing a stable and covalent association between self-assembled layers and a surface of a metal substrate, and more particularly a stainless steel substrate. The metal or alloy substrate, and more particularly the stainless steel substrate, is modified by the covalent attachment of self-assembled monolayers on the surface by using an electrochemical process. These functionalized self-assembled monolayers provide a link to irreversibly attach or immobilize an active or nonactive agent.

Abstract: An apparatus (10) for helping to protect a vehicle occupant includes an inflatable vehicle occupant protection device (12). An inflator (14) provides inflation fluid for inflating the protection device (12). The inflation fluid flow from the inflator (14) is transverse to a central axis (16) of the inflator. A shield (70) includes a piece of material (72) folded about the inflator (14) and having a wall portion (102) that is interposed between at least a portion of the inflator and the protection device (12) and against which inflation fluid initially exiting from the inflator at least partially impinges. The wall portion (102) has a plurality of tear seams (76) that rupture due to inflation fluid pressure acting on the shield (70) to enable the wall portion to form a plurality of flaps (80) within the protection device (12).

Abstract: An outer space deployable boom system is formed of a plurality of interconnected longeron members that are linked by diagonal members and batten frames. The diagonal members are arranged in a unique K-type configuration that provides a predictable and orderly folding dynamic as the boom system transitions from a stowed state to a deployed state.

Abstract: A system for tax planning with legislation conformance options comprises one more processors coupled to a memory. The memory stores instructions executable by the processors to implement a tax planner configured to receive data exported from a tax return preparation tool. After receiving the data, the tax planner receives input indicating whether a tax projection to be prepared using the data is to include an impact of specified tax legislation. If the input indicates that the tax projection is to include the impact of the specified legislation, the tax planner is configured to include the impact in the tax projection without requiring data to be re-exported from the tax return preparation tool. If the input indicates that the tax projection is to exclude the impact of the specified legislation, the tax planner is configured to prepare the tax projection without including the impact of the specified legislation.

Abstract: A boom structure is deployable from a collapsed, stowable configuration to an elongated truss configuration. The boom structure contains a plurality of truss-forming multi-sided bays. A bay contains a pair of battens joined together at corner regions by foldable longerons. A side of a bay has a plurality of diagonal cord members crossing one another and connected to diagonally opposed corner regions of the side. When the longerons are in their folded positions, the battens are nested together against one another in a stacked arrangement and the diagonal cord members flex into a compact stowed configuration between adjacent battens. The stowed battens are compressed to each other at their corners to form a stowed structure capable of reacting loads.

Abstract: A rotatable steering shaft (12) has a surface (93) that defines a tapered locking opening (92). A mounting member (14) receivable on the shaft (12) has a first locking pin passage (70). A locking pin (16) for securing the mounting member (14) to the shaft (12) has a first portion (100) receivable in the first locking pin passage (70) in the mounting member (14). The locking pin (16) also has a tapered end portion (104) receivable in the tapered locking opening (92) in the shaft to secure the mounting member to the shaft for rotation with the shaft.

Abstract: A stowable and deployable concentrator for solar cells. A substrate mounts a row of solar cells. A row of Fresnel lens elements is mounted to the substrate so as to be deflectable toward the substrate in a stowed configuration and biased away from it in the deployed configuration. The Fresnel lens is linear and flexibly mounted in a shaper which shapes it to a proper curvature in the deployed configuration. A pair of these concentrators can be hinged together to form a conveniently stowed and readily deployed combination.

Abstract: A stowable and deployable concentrator for solar cells, A flexible, springily resilient Fresnel lens is held in a frame whose relaxed condition holds the Fresnel lens as the linear fragment of a cylinder. When in this deployed shape, the Fresnel lens concentrates energy onto a strip of solar cells, The frame is springily mounted by support means, biased toward the deployed condition, and when the Fresnel lens and frame are pressed toward the cells, they tend to flatten toward a stowed condition.

Abstract: An assembly of an array of solar cells and a substrate blanket to which they are mounted. The blanket is woven from glass fibers and coated with a silicone. The blanket, because of its composition, is resistant to attack by atomic oxygen, flexible, a good electrical insulator, and a good thermal conductor.

Abstract: A solar cell array deployable from a folded flat triangular structure to a substantially circular deployed shape. A root spar supports a hub. The hub has an axis of rotation normal to the axis of the root spar. The hub drives a lead spar, and a plurality of intermediate spars rotate freely around the hub. A foldable gore is fitted between each pair of adjacent spars except between the root spar and the lead spar. Rotation of the hub in one direction folds the gores into a stack. Rotation in the opposite direction opens the gores to form tensioned membranes between the spars. A reversible power source drives the hub.

Abstract: A powered hinge powered by a hot wax linear actuator, which can provide for bi-directional rotation of the hinge as the consequence of sequential and intermittent energizing and deenergizing sequence of the actuator.

Abstract: A mast forming and deployment system comprising a storage reel for storing a strip of sheet metal wound on the reel, and a tube forming a deployment apparatus. The strip is fed to ploy guides that form the sheet metal into a tube with overlapping edges. A drive system feeds the strip of sheet metal to and through the tube forming apparatus and drives staples which hold together the overlapping edges.