Abstract: A fuel cell system includes a plurality of fuel cell plates. A first plate of the fuel cell plates is connected to a plurality of plate supports located on a periphery of the first plate. Each support of the plurality of plate supports is electrically insulating and bounds an opening for receiving an aligning member therein.

Abstract: A fuel cell system includes a plurality of fuel cell plates. A first plate of the fuel cell plates is connected to a plurality of plate supports located on a periphery of the first plate. Each support of the plurality of plate supports is electrically insulating and bounds an opening for receiving an aligning member therein.

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 structural spacecraft component comprising internal microstructure; wherein said microstructure comprises a plurality of parallel layers and a plurality of spacers that connect adjacent parallel layers; wherein said structural spacecraft component is a product of an additive manufacturing process.

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: An additive manufacturing filament production apparatus, having a processing chamber; and a continuous molding module wherein said processing chamber comprises a sealable air-tight housing, a heating element, an actuator-controlled piston, and a vacuum supply.

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: 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 structural spacecraft component comprising internal microstructure; wherein said microstructure comprises a plurality of parallel layers and a plurality of spacers that connect adjacent parallel layers; wherein said structural spacecraft component is a product of an additive manufacturing process.

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 device for removing a closure from a container includes a hollow needle, a piston for driving the needle into the closure and a compressed gas cartridge for driving the piston. Once the needle has been driven into the closure so that an end of the needle is inside the container, the piston can reciprocate to force air through the needle and pressurize the container in order to eject the closure. The piston can also reciprocate to evacuate air from the container through a stopper with a check valve when leftover contents of the container are to be preserved.

Abstract: A surgical fastening system for implantable devices is disclosed. The implantable device may contain a plurality of fasteners in pre-deployment position, may have a housing fitted over or around fit which contains a plurality of fasteners in pre-deployment position, or may be a part of a two-part system into which it its. Accordingly, the present invention also encompasses a deployment system or tool that optionally positions the implantable device, and which causes the fasteners to move into post-deployment position. The fasteners may be staples, metal loops, coils, springs or hooks formed of biocompatible materials, including shape memory alloys such as NiTi.

Abstract: An air impeller with both sound attenuation and vibration isolation means in a compact assembly. Three muffler chambers are provided preceding the inlet to the impeller each with sound absorbing foam material and vibration isolators are provided at both inlet and discharge sides of the impeller.

Abstract: A zero clearance bearing assembly comprising a housing defining a generally cylindrical bearing chamber with a pair of ball bearing units disposed therein. One unit is adjacent an axial thrust reaction surface of frusto-conical configuration and a shoulder on an associated shaft urges the unit into engagement with the surface. The other unit is press fit on the shaft and also has a shaft shoulder urging it toward the thrust surface. An air impeller on the shaft urges the same toward the other bearing unit and the thrust unit reacts to both the impeller load and an axial preload spring engaging the other bearing unit. One or both of the bearing units is provided with an improved radial preload device comprising a spring and a pair of circumaxially spaced reaction surfaces opposing the same.

Abstract: A method for plastic injection molding a centrifugal air impeller having a series of radially elongated air moving blades of varying width from root to tip and an inlet cover and back plate each of which takes a generally circular disc-like configuration with the former defining an air inlet opening and serving as a first housing element and the latter serving as a second axially spaced opposing substantially flat housing element. The inlet cover and air moving blades are molded integrally with the blades projecting axially from the cover and with the cover contoured as required to accommodate substantially all of the width variation in the blades in progression from root to tip. Thus, the longitudinal blade edges opposite the inlet cover reside substantially in a common plane facilitating the attachment of the integral inlet cover and blade assembly to the substantially flat back plate in face-to-face axial alignment.

Abstract: A low part count blower-motor assembly in a two-part housing which defines fluid inlet and discharge openings for the blower but which is otherwise sealed when assembled. An integrated tubular stator subassembly is fixedly attached to one of the housing parts and projects axially toward the fluid inlet opening. An integrated motor rotor subassembly is also disposed within the housing for rotation about the stator subassembly in coaxial relationship therewith, a part of the rotor subassembly being disposed axially between the stator and the inlet opening in spaced relationship with the opening. A shaft is journaled in the central opening of the tubular stator subassembly and projects axially there from toward the inlet opening and a fluid impeller mounted on the projecting end portion of the shaft receives fluid from the inlet opening. The impeller is also fixedly attached to the part of the rotor which resides between the stator and inlet opening.