Abstract: Apparatus for Manufacture and In-Space Assembly of Antennas comprising: a prefabricated primary reflector center section; a trusselator truss assembler; a phased feed array; wherein said prefabricated reflector center section, trusselator, and phased feed array are fixedly connected to one another; a self-positioning and orienting tool; a truss extending from said trusselator; a secondary reflector attached to said truss; robotic arms; a nibbler end effector mounted on one of said robotic arms; a grapple end effector mounted on one of said robotic arms; a mold for casting a piece of a primary reflector; a power cube; a solar array providing power to said power cube; refabricator plus; and an ESPA ring.

Abstract: A truss-formation apparatus comprising two truss makers and a lateral stage, wherein the truss makers create trusses and each truss maker comprises thermal dies, heaters with temperature sensors, and mandrels; wherein the truss makers form trusses that comprise parallel truss elements and battens; wherein a pultrusion actuator pulls parallel truss elements down along a mandrel; wherein a batten actuator causes a thermal die to rotate around a mandrel forming battens that connect parallel truss elements to one another; and wherein the lateral stage comprises a thermal die and traverses the gap between the parallel trusses forming cross members that connect the trusses.

Abstract: Apparatus for Manufacture and In-Space Assembly of Antennas comprising: a prefabricated primary reflector center section; a trusselator truss assembler; a phased feed array; wherein said prefabricated reflector center section, trusselator, and phased feed array are fixedly connected to one another; a self-positioning and orienting tool; a truss extending from said trusselator; a secondary reflector attached to said truss; robotic arms; a nibbler end effector mounted on one of said robotic arms; a grapple end effector mounted on one of said robotic arms; a mold for casting a piece of a primary reflector; a power cube; a solar array providing power to said power cube; refabricator plus; and an ESPA ring

Abstract: A launchable land anchor having a tether, an anchor head housing a self-righting control module, a ground penetration device, a plurality of stability panels extending from a bottom portion having an interior surface and an exterior surface, and a plurality of sensors disposed on said exterior surface of said stability panels. Embodiments according to the present invention allow for self-righting functionality and continuous monitoring of stability to ensure security of the anchoring and removing the need of an on-site operator to setup and monitor the land anchor.

Abstract: Orbital winch having: lower and upper frames; spool having upper and lower flanges with lower flange attached to lower frame; axial tether guide mounted to upper frame; secondary slewing ring coaxial with spool and rotatably mounted to upper frame, wherein secondary slewing ring's outer surface has gearing; upper tether guide mounted to inner surface of secondary slewing ring; linear translation means having upper end mounted to upper frame and lower end mounted on lower frame; primary slewing ring rotatably mounted within linear translation means allowing translation axially between flanges, wherein primary slewing ring's outer surface has gearing; lower tether guide mounted on primary slewing ring's inner surface; pinion rod having upper end mounted to upper frame and lower end mounted to lower frame, wherein pinion rod's teeth engage primary and secondary slewing rings' outer surface teeth; and tether passing through axial, upper, and lower tether guides and winding around spool.

Abstract: A deorbit device comprising a passive electrodynamic conductive tape connected at one end to a spacecraft.

Abstract: A deorbit device comprising a passive electrodynamic conductive tape connected at one end to a spacecraft.

Abstract: The present invention comprises an electrodynamic tether structure and a method of use. The structure of the tether taught by the present invention is a short, wide, interconnected multiwire (compared to the long, narrow single wires of the prior art) conductive tether whose area maximizes electrodynamic drag while simultaneously minimizing the Area-Time-Product swept by the tether during its operating life. The preferred tether length is two kilometers to five kilometers. The preferred tether mass is one percent to five percent of the spacecraft mass. The method of operation comprises orienting the tether structure at an angle to the local vertical to maximize electrodynamic drag on the host spacecraft and minimize tether instability. The angle of 35.26 degrees is preferred.