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: An apparatus for damping a first member relative to a second member. The apparatus includes a receiving member that includes a flange, an axial elastomeric member, and a radial elastomeric member. The axial elastomeric member is positionable between a surface of the first member and the flange of the receiving member, and the radial elastomeric member is positionable between the first member and the receiving member.

Abstract: An apparatus for damping a first member relative to a second member. The apparatus includes a receiving member that includes a flange, an axial elastomeric member, and a radial elastomeric member. The axial elastomeric member is positionable between a surface of the first member and the flange of the receiving member, and the radial elastomeric member is positionable between the first member and the receiving member.

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: Systems and methods for interconnecting dual manifested spacecraft for launch by a launch vehicle are disclosed. Different motive forces are utilized to couple a first spacecraft to a second spacecraft and to restrict demating of the second spacecraft from the first spacecraft. Some systems and methods utilize pneumatic pressure to permit mating of a first spacecraft to a second spacecraft and utilize spring force to restrict demating of the second spacecraft from the first spacecraft.

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 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: 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: This disclosure provides a cap assembly for encapsulating a fastener or portion of a fastener that protrudes from a surface and into a confined space. The cap assembly includes a plurality of nested sections that telescope a collapsed configuration to an extended configuration. The plurality of nested sections includes a base section that includes a base rim that engages the surface in the extended configuration. The plurality of nested sections also includes an end section that has an end wall. The end wall and the base rim define a length of the cap assembly in the extended configuration that is sufficient to encapsulate the fastener within the cap assembly with the base rim engaging the surface and the end wall spaced apart from a distal end of the fastener.

Abstract: Systems and methods for interconnecting dual manifested spacecraft for launch by a launch vehicle are disclosed. Different motive forces are utilized to couple a first spacecraft to a second spacecraft and to restrict demating of the second spacecraft from the first spacecraft. Some systems and methods utilize pneumatic pressure to permit mating of a first spacecraft to a second spacecraft and utilize spring force to restrict demating of the second spacecraft from the first spacecraft.

Abstract: Systems and methods for interconnecting dual manifested spacecraft for launch by a launch vehicle are disclosed. Different motive forces are utilized to couple a first spacecraft to a second spacecraft and to restrict demating of the second spacecraft from the first spacecraft. Some systems and methods utilize pneumatic pressure to permit mating of a first spacecraft to a second spacecraft and utilize spring force to restrict demating of the second spacecraft from the first spacecraft.

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: This disclosure provides a cap assembly for encapsulating a fastener or portion of a fastener that protrudes from a surface and into a confined space. The cap assembly includes a plurality of nested sections that telescope a collapsed configuration to an extended configuration. The plurality of nested sections includes a base section that includes a base rim that engages the surface in the extended configuration. The plurality of nested sections also includes an end section that has an end wall. The end wall and the base rim define a length of the cap assembly in the extended configuration that is sufficient to encapsulate the fastener within the cap assembly with the base rim engaging the surface and the end wall spaced apart from a distal end of the fastener.

Abstract: Spacecraft, radiator panels for spacecraft, kits for radiator panels, inserts associated with radiator panels, heat pipes associated with radiator panels, external structural reinforcement members associated with radiator panels, and methods of assembling radiator panels are disclosed herein. Some radiator panels include at least one insert that is positioned adjacent to a heat pipe between two spaced-apart face-sheets, with the insert being configured to secure a package to the inside face-sheet opposite of the heat pipe. Some radiator panels include at least one external structural reinforcement member that extends across an external side of the radiator panel.

Abstract: A spacecraft may include an upper core structure or a lower core structure. The upper core structure may include an upper cylinder for supporting an upper spacecraft of a dual-manifest launch configuration. The lower core structure may include a lower cylinder for supporting a lower spacecraft with the upper cylinder mounted on top of the lower cylinder. The upper cylinder may have an upper cylinder inner diameter that may be substantially similar to the lower cylinder inner diameter.

Abstract: Systems and methods for interconnecting dual manifested spacecraft for launch by a launch vehicle are disclosed. Different motive forces are utilized to couple a first spacecraft to a second spacecraft and to restrict demating of the second spacecraft from the first spacecraft. Some systems and methods utilize pneumatic pressure to permit mating of a first spacecraft to a second spacecraft and utilize spring force to restrict demating of the second spacecraft from the first spacecraft.

Abstract: Systems and methods for interconnecting dual manifested spacecraft for launch by a launch vehicle are disclosed. Different motive forces are utilized to couple a first spacecraft to a second spacecraft and to restrict demating of the second spacecraft from the first spacecraft. Some systems and methods utilize pneumatic pressure to permit mating of a first spacecraft to a second spacecraft and utilize spring force to restrict demating of the second spacecraft from the first spacecraft.

Abstract: Systems and methods for interconnecting dual manifested spacecraft for launch by a launch vehicle are disclosed. Different motive forces are utilized to couple a first spacecraft to a second spacecraft and to restrict demating of the second spacecraft from the first spacecraft. Some systems and methods utilize pneumatic pressure to permit mating of a first spacecraft to a second spacecraft and utilize spring force to restrict demating of the second spacecraft from the first spacecraft.

Abstract: Spacecraft, radiator panels for spacecraft, kits for radiator panels, inserts associated with radiator panels, heat pipes associated with radiator panels, external structural reinforcement members associated with radiator panels, and methods of assembling radiator panels are disclosed herein. Some radiator panels include at least one insert that is positioned adjacent to a heat pipe between two spaced-apart face-sheets, with the insert being configured to secure a package to the inside face-sheet opposite of the heat pipe. Some radiator panels include at least one external structural reinforcement member that extends across an external side of the radiator panel.