Abstract: A golf club head that is capable of preserving the metallic acoustic signature of an entirely metallic golf club head all while utilizing a lightweight composite material is disclosed herein. More specifically, the golf club head in accordance with the present invention creates a frontal acoustic chamber in conjunction with a rear weight saving chamber via a panel member barrier is disclosed. The panel member may even be combined with an optimized thickness relationship at the transition region between the striking face portion and the panel member to further optimize the performance of the golf club head.

Abstract: Methods are provided herein for assembling at least two nucleic acids using a sequence specific nuclease agent (e.g., a gRNA-Cas complex) to create end sequences having complementarity and subsequently assembling the overlapping complementary sequences. The nuclease agent (e.g., a gRNA-Cas complex) can create double strand breaks in dsDNA in order to create overlapping end sequences or can create nicks on each strand to produce complementary overhanging end sequences. Assembly using the method described herein can assemble any nucleic acids having overlapping sequences or can use a joiner oligo to assemble sequences without complementary ends.

Abstract: Capture assemblies and compliant extension assemblies may be utilized for insertion into a nozzle of a liquid engine of a spacecraft. The capture assembly may include an apparatus such as a probe for insertion into the nozzle and an assembly at least partially enclosed in a forward portion of the probe. The assembly may include a plurality of actuated fingers for deploying outwardly from the probe when the probe is inserted into the nozzle. The compliant extension assembly may be at least partially enclosed in a housing connected to the capture assembly for axial movement of the probe. The compliant extension assembly may facilitate axial movement of the probe between a retracted position and an extended position, wherein the probe is extended forwardly, relative to the housing.

Abstract: Capture assemblies and compliant extension assemblies may be utilized for insertion into a nozzle of a liquid engine of a spacecraft. The capture assembly may include an apparatus such as a probe for insertion into the nozzle and an assembly at least partially enclosed in a forward portion of the probe. The assembly may include a plurality of actuated fingers for deploying outwardly from the probe when the probe is inserted into the nozzle. The compliant extension assembly may be at least partially enclosed in a housing connected to the capture assembly for axial movement of the probe. The compliant extension assembly may facilitate axial movement of the probe between a retracted position and an extended position, wherein the probe is extended forwardly, relative to the housing.

Abstract: Mechanisms for deploying a solar array include an elongated deployment member routed along a first panel, along an extension, and at least partially along a second panel. The elongated deployment member is configured to, upon retraction of the elongated deployment member by a deployment motor, move the extension into an extended position and rotate the second panel about a hub located at a distal end of the extension. Solar array assemblies include such a mechanism. Methods of deploying a solar array include retracting an elongated deployment member to rotate an extension into an extended position and further retracting the elongated deployment member to rotate a panel coupled to the extension approximately 360° about a hub of the extension.

Abstract: Mechanisms for deploying a solar array include an elongated deployment member routed along a first panel, along an extension, and at least partially along a second panel. The elongated deployment member is configured to, upon retraction of the elongated deployment member by the deployment motor, move the extension into an extended position and rotate the second panel about a hub located at a distal end of the extension. Solar array assemblies include such a mechanism. Methods of deploying a solar array include retracting an elongated deployment member to rotate an extension into an extended position and further retracting the elongated deployment member to rotate a panel coupled to the extension approximately 360° about a hub of the extension.

Abstract: A deployable truss is formed from a plurality of column members connected at their ends where at least some of the column members are formed from column assemblies, each including a plurality of strut members that are at least connected to each other at a first and second end of the column assembly. For added rigidity, strut members of a column assembly may be connected to each other between the first and second ends using, for example, a rigidizable resin, a fixed spacer, or a deployable spacer. Connecting strut members between the ends of the column assembly provides mutual bracing to the strut members and decreases the free buckling length of the individual strut members. Spacers are preferably configured to radially space the strut members away from the longitudinal centerline of the column assembly to increase its moment of inertia, and hence its buckling strength.

Abstract: A deployable truss is formed from a plurality of column members connected at their ends where at least some of the column members are formed from column assemblies, each including a plurality of strut members that are at least connected to each other at a first and second end of the column assembly. For added rigidity, strut members of a column assembly may be connected to each other between the first and second ends using, for example, a rigidizable resin, a fixed spacer, or a deployable spacer. Connecting strut members between the ends of the column assembly provides mutual bracing to the strut members and decreases the free buckling length of the individual strut members. Spacers are preferably configured to radially space the strut members away from the longitudinal centerline of the column assembly to increase its moment of inertia, and hence its buckling strength.

Abstract: A deployable truss is formed from a plurality of column members connected at their ends where at least some of the column members are formed from column assemblies, each including a plurality of strut members that are at least connected to each other at a first and second end of the column assembly. For added rigidity, strut members of a column assembly may be connected to each other between the first and second ends using, for example, a rigidizable resin, a fixed spacer, or a deployable spacer. Connecting strut members between the ends of the column assembly provides mutual bracing to the strut members and decreases the free buckling length of the individual strut members. Spacers are preferably configured to radially space the strut members away from the longitudinal centerline of the column assembly to increase its moment of inertia, and hence its buckling strength.

Abstract: A solar panel for a spacecraft has a base with a face, and at least one row of solar cells and at least one elongated reflector are mounted on the face of the base. The reflectors and the rows are mounted generally parallel to each other in an alternating fashion. The reflector has first and second reflecting sides when the reflector is in a deployed position. The reflector is mounted so that the first side of the reflector is adjacent to a row of solar cells and reflects radiation incident on the first side onto the adjacent row of solar cells when the reflector is in a deployed position. Preferably, a plurality of rows and a plurality of reflectors are mounted on the face of the base, with at least one of the reflectors being disposed between two adjacent rows of solar cells.

Abstract: A solar panel for a spacecraft has a base with a face, and at least one row of solar cells and at least one elongated reflector are mounted on the face of said base. The reflectors and the rows are mounted generally parallel to each other in an alternating fashion. The reflector has a first and a second reflecting side when the reflector is in a deployed position. The reflector is mounted so that the first side of the reflector is adjacent to a row of solar cells and reflects radiation incident on the first side onto the adjacent row of solar cells when said reflector is in a deployed position. Preferably, a plurality of rows and a plurality of reflectors are mounted on the face of the base, with at least one of the reflectors being disposed between two adjacent rows of solar cells.

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 self-deployable parallelogram-type panel array for solar cells. The array includes two sets of rigid panels, the panels of each set being hinged together, and the sets extending side-by-side along a central axis. The sets are foldable, and are pivoted together at their central points so as to form parallelogram-type structures. A respective yoke is hinged to each set to coordinate the movement of the sets. The yokes are hinged to a base on the opposite side of the axis from their respective set to provide greater structural stability and a higher first node resonant frequency. Deployment force is exerted by self-powered hinges, and are the only source of deployment force. The yokes are joined by gears to coordinate their rotation and thereby the stowing and deploying of the array.