Abstract: A system for fabricating an object includes an additive manufacturing apparatus configured to build a three dimensional (3D) tool by additively depositing two or more layers of material. The system includes a deposition apparatus configured to deposit at least one metal on the 3D tool to form the object on the 3D tool. The system includes a burnout apparatus configured to heat the 3D tool to remove the 3D tool from the object.

Abstract: Methods and apparatus to methods and apparatus for performing propulsion operations using electric propulsion system are disclosed. An example apparatus includes means to use an electric propulsion system coupled to a frame of a spacecraft, the electric propulsion system including at least a first thruster and a second thruster, the first thruster adjacent a first side of the frame, the second thruster adjacent a second side of the frame, and means to allow at least one of the first thruster or the second thruster to control the spacecraft without using a chemical propulsion system.

Abstract: An isolation coupler for coupling a functional element to a support structure includes a first bracket. The first bracket includes a number of first-bracket sides. The number of first-bracket sides forms a closed polygonal shape, in plan view. The isolation coupler further includes a number of isolators coupled to each one of the first-bracket sides. The isolation coupler also includes a second bracket. The second bracket includes a number of second-bracket sides. The second bracket sides are coupled to the isolators. The number of second-bracket sides is equal to the number of first-bracket sides and forms the closed polygonal shape, in plan view. The isolators separate each one of the first-bracket sides from a corresponding one of the second-bracket sides to attenuate a load transferred from the first bracket to the second bracket.

Abstract: A drive train linkage includes a drive arm having a drive arm pivot axis, a driven arm having a driven arm pivot axis, at least one first coupling member extending between and being rotatably coupled to each of the drive arm and driven arm, and at least one second coupling member extending between and being rotatably coupled to each of the drive arm and driven arm so that the at least one second coupling member opposes the at least one first coupling member, where the at least one first coupling member and the at least one second coupling member are coupled to both the drive arm and the driven arm so to form a substantially zero mechanical deadband coupling between the drive arm and the driven arm.

Abstract: A method of manufacturing a vehicle control surface includes generating, using an electronic controller, a three-dimensional plan for the vehicle control surface. The three-dimensional plan includes, at least, non-vehicular support structure dimensions, for a non-vehicular support structure, and skin dimensions for a skin. The method further includes configuring the dimensions of the non-vehicular support structure based on build environment characteristics associated with an additive manufacturing process of the control surface. The additive manufacturing process is based on the three-dimensional plan. The method further includes fabricating the vehicle control surface, using the additive manufacturing process, based on the three-dimensional plan.

Abstract: Methods and apparatus to methods and apparatus for performing propulsion operations using electric propulsion system are disclosed. An apparatus includes a space vehicle including means for performing propulsion operations without using a chemical propulsion system.

Abstract: An additively manufactured heat transfer device is disclosed, including an enclosure portion with outer walls. The outer walls contain an inner channel configured to direct a flow of coolant fluid. The heat transfer device further includes a fluid intake port and a fluid outtake port, each connected to the first inner channel. The fluid intake port is configured to direct a flow of coolant fluid through an outer wall of the enclosure portion into the inner channel, and the fluid outtake port is configured to direct a flow of coolant fluid through an outer wall of the enclosure portion out of the inner channel. The inner channel is defined by internal walls, and the enclosure portion and the internal walls form a single additively manufactured unit.

Abstract: A washer and retained nut assembly has a washer with a retaining flange and a positioning cavity and a nut received in the washer. The nut has a shoulder received in the positioning cavity with a top surface of the shoulder engaging a lower surface of the retaining flange in a loose condition of the washer and nut. The nut further has an engagement surface contacting a receiving surface in the washer in an engaged position of the washer and nut. The nut further has a peripheral surface engaging a blocking surface in the washer with the nut and washer in a maximum offset angle orientation between the washer and nut in the engaged position.

Abstract: A satellite is disclosed comprising an anti-nadir panel having a first side and a second side. In one or more embodiments, the first side of the anti-nadir panel is mounted to an anti-nadir side of the main body of the satellite. The satellite further comprises at least one battery pack mounted to the second side of the anti-nadir panel, where at least one battery pack comprises at least one battery cell.

Abstract: A mounting device is disclosed, including a first torsion bar structure having an elongated axis and opposing end portions connected by a middle portion. The mounting device further includes a second torsion bar structure having an elongated axis and opposing end portions connected by a middle portion. The middle portions of the first and second torsion bar structures are connected. The end portions of the first torsion bar structure are configured for attachment to a vehicle, and the end portions of the second torsion bar structure are configured for attachment to an accessory. The first and second torsion bar structures are configured to decrease transmission of vibration frequencies between the vehicle and the accessory.

Abstract: An additively manufactured antenna device is disclosed, including a base portion and a body portion. The body portion is attached to the base portion and includes a lattice stiffening structure configured to eliminate secondary printing support.

Abstract: Systems and methods for dampening dynamic loading between two bodies are described. An example dampening system includes a non-ferrous metal body attached to a second body and a stack of magnets attached to a third body. The stack of magnets is movably disposed within or around the non-ferrous metal body, and adjacent magnets are arranged in an opposed polar relationship, whereby relative movement of said second and third bodies is damped. An example method of dampening dynamic loading includes arranging a plurality of magnets along an axis to form at least one pair of magnets having an opposed polar relationship along the axis. The method further includes axially moving the at least one pair of magnets relative to a non-ferrous metal body, so as to dampen dynamic loading of a payload attached to a vehicle.

Abstract: Systems and methods for dampening dynamic loading between two bodies are described. An example dampening system includes a non-ferrous metal body attached to a second body and a stack of magnets attached to a third body. The stack of magnets is movably disposed within or around the non-ferrous metal body, and adjacent magnets are arranged in an opposed polar relationship, whereby relative movement of said second and third bodies is damped. An example method of dampening dynamic loading includes arranging a plurality of magnets along an axis to form at least one pair of magnets having an opposed polar relationship along the axis. The method further includes axially moving the at least one pair of magnets relative to a non-ferrous metal body, so as to dampen dynamic loading of a payload attached to a vehicle.

Abstract: Protective blankets include a plurality of sheets of material operatively coupled together to define the protective blanket. The plurality of sheets includes at least one sheet composed of carbon nanotube reinforced composite material and at least one sheet composed of a different material. Methods of assembling protective blankets include layering the plurality of sheets and operatively coupling together the plurality of sheets. Spacecraft include a body and a protective blanket operatively coupled to the body. Methods of assembling spacecraft include coupling a protective blanket to the body of a spacecraft.

Abstract: A carbon nanotube enhanced polymer includes a polymer and a plurality of carbon nanotube sheetlets mixed with the polymer. The carbon nanotube sheetlets each include a network of intertwined carbon nanotubes.

Abstract: A method of manufacturing a vehicle control surface includes generating, using an electronic controller, a three-dimensional plan for the vehicle control surface. The three-dimensional plan includes, at least, non-vehicular support structure dimensions, for a non-vehicular support structure, and skin dimensions for a skin. The method further includes configuring the dimensions of the non-vehicular support structure based on build environment characteristics associated with an additive manufacturing process of the control surface. The additive manufacturing process is based on the three-dimensional plan. The method further includes fabricating the vehicle control surface, using the additive manufacturing process, based on the three-dimensional plan.

Abstract: Methods and apparatus to methods and apparatus for performing propulsion operations using electric propulsion system are disclosed. An example apparatus includes means to use an electric propulsion system coupled to a frame of a spacecraft, the electric propulsion system including at least a first thruster and a second thruster, the first thruster adjacent a first side of the frame, the second thruster adjacent a second side of the frame, and means to allow at least one of the first thruster or the second thruster to control the spacecraft without using a chemical propulsion system.

Abstract: A sealant containment assembly for enclosing fasteners disposed within a confined space. The sealant containment assembly includes a first containment member and a second containment member that extend between two surfaces. The first and second containment members each include structure-engaging ends for engaging a structural member and the first and second containment members each include enclosure ends that connect the first and second containment members together to enclose the fasteners within a confined space defined by the first and second containment members, the first and second surfaces, the structural member and the connected enclosure ends. The assembly also includes at least one injection port disposed outside of the confined space but is in communication with at least one distribution port disposed inside the confined space for filling the confined space with sealant, thereby embedding the fasteners in sealant.

Abstract: A method of manufacturing a cone-shaped composite article may include providing unidirectional plies in a continuous arcuate shape in a flat pattern configured to wrap 360 degrees around a cone-shaped mandrel such that opposing ply ends of each unidirectional ply terminate at a ply seam. The method may further include laying up at least one inner sublaminate on the cone-shaped mandrel, the inner sublaminate containing at least four of the unidirectional plies having an inner stacking sequence with fiber angles of ?45, 90, 0, +45 degrees such that the inner sublaminate has a quasi-isotropic layup at any location of the inner sublaminate. The method may additionally include laying up at least one outer sublaminate in an outer stacking sequence being a mirror image of the at least one inner stacking sequence.

Abstract: A space vehicle system, a method of manufacturing a multiple space vehicle launch system, and a method to transmit a launch load between space vehicles during a launch are disclosed. The space vehicle system may include a first space vehicle including a first core structure, a second space vehicle including a second core structure releasably attached to the first space vehicle in a stacked configuration, a first solar array supported by the first core structure, the first core structure extending beyond a lower edge of the first solar array, and a second solar array supported by the second core structure, the second core structure extending beyond an upper edge of the second solar array.