Abstract: Composite heat pipes, methods of assembling composite heat pipes, sandwich panels having one or more composite heat pipes, methods of assembling sandwich panels, radiator panels, methods of assembling radiator panels, spacecraft, and methods of assembling spacecraft are disclosed. Composite heat pipes include an elongate conductive casing and one or more fiber reinforced composite layers operatively coupled to one or more lateral sides of the elongate conductive casing. Sandwich panels include two spaced-apart face-sheets, a core positioned between the two spaced-apart face-sheets, and one or more composite heat pipes. Spacecraft include a body and two radiator panels operatively coupled to the body opposite each other.

Abstract: A space vehicle system, a method of manufacturing the space vehicle system, and a method of launching the space vehicle system are disclosed. The method of manufacturing the space vehicle system may include disposing a first space vehicle with an upper core structure upon a second space vehicle with a lower core structure such that loads of the first space vehicle are transmitted to the lower core structure of the second space vehicle.

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: A battery assembly is provided. The assembly includes a battery containment apparatus including a chassis base and divider sheets coupled to the chassis base, wherein the divider sheets are spaced from each other such that a battery cell slot is defined between adjacent sheets. The apparatus further includes a compression plate assembly including first compression and second compression plates coupled to a divider sheet at opposing ends of the apparatus, and a tensioning member coupled between the first and second compression plates. A battery cell is positioned within each battery cell slot defining a plurality of battery cells, and the first and second compression plates compressively hold the battery cells between the divider sheets. At least one of the chassis base and the compression plate assembly are formed from a thermoplastic material.

Abstract: Radiator panels include two spaced-apart face-sheets including an inside face-sheet and an outside face-sheet that are constructed of a fiber reinforced composite material, a honeycomb core positioned between the two spaced-apart face-sheets, and one or more heat pipes extending through the honeycomb core. Spacecraft include a body and two radiator panels operatively coupled to the body opposite each other.

Abstract: Composite heat pipes, methods of assembling composite heat pipes, sandwich panels having one or more composite heat pipes, methods of assembling sandwich panels, radiator panels, methods of assembling radiator panels, spacecraft, and methods of assembling spacecraft are disclosed. Composite heat pipes include an elongate conductive casing and one or more fiber reinforced composite layers operatively coupled to one or more lateral sides of the elongate conductive casing. Sandwich panels include two spaced-apart face-sheets, a core positioned between the two spaced-apart face-sheets, and one or more composite heat pipes. Spacecraft include a body and two radiator panels operatively coupled to the body opposite each other.

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: 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: 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: Methods and apparatus to methods and apparatus for performing propulsion operations using electric propulsion system are disclosed. An example method includes deploying a space vehicle including an electric propulsion system; and using the electric propulsion system for attitude control and orbit control, no other propulsion system provided to enable the attitude control and the orbit control.

Abstract: A battery assembly is provided. The assembly includes a battery containment apparatus including a chassis base and divider sheets coupled to the chassis base, wherein the divider sheets are spaced from each other such that a battery cell slot is defined between adjacent sheets. The apparatus further includes a compression plate assembly including first compression and second compression plates coupled to a divider sheet at opposing ends of the apparatus, and a tensioning member coupled between the first and second compression plates. A battery cell is positioned within each battery cell slot defining a plurality of battery cells, and the first and second compression plates compressively hold the battery cells between the divider sheets. At least one of the chassis base and the compression plate assembly are formed from a thermoplastic material.

Abstract: An apparatus comprises a first plurality of walls, a second plurality of walls, and a plurality of channels formed by the first plurality of walls and the second plurality of walls. The second plurality of walls meets the first plurality of walls at substantially right angles and forms a housing with a first side and a second side. The plurality of channels extends through the housing from the first side to the second side. The plurality of channels has a first plurality of openings on the first side. The plurality of channels has a second plurality of openings on the second side. The plurality of channels has substantially a same shape and is configured to receive a plurality of battery cells.

Abstract: A multiple space vehicle launch system that may be adapted to be disposed within a payload region of a launch vehicle fairing is disclosed. The vehicle launch system may include a first space vehicle including a first core structure and a second space vehicle including a second core structure. The second core structure may be oriented relative to the first space vehicle such that when placed within a fairing, a launch load is transmitted from the first core structure of the first space vehicle and is borne by the second core structure of the second space vehicle. The first space vehicle and the second space vehicle each include respective propulsion units.

Abstract: Radiator panels include two spaced-apart face-sheets including an inside face-sheet and an outside face-sheet that are constructed of a fiber reinforced composite material, a honeycomb core positioned between the two spaced-apart face-sheets, and one or more heat pipes extending through the honeycomb core. Spacecraft include a body and two radiator panels operatively coupled to the body opposite each other.

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 spacecraft may include a module structure having a plurality of module sides. The spacecraft may include a central cylinder extending through a center of the spacecraft. The central cylinder may be the only closed cross-section extending along a longitudinal axis of the spacecraft.

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: Methods and apparatus to methods and apparatus for performing propulsion operations using electric propulsion system are disclosed. An example method includes deploying a space vehicle including an electric propulsion system; and using the electric propulsion system for attitude control and orbit control, no other propulsion system provided to enable the attitude control and the orbit control.

Abstract: A space vehicle system, a method of manufacturing the space vehicle system, and a method of launching the space vehicle system are disclosed. The method of manufacturing the space vehicle system may include disposing a first space vehicle with an upper core structure upon a second space vehicle with a lower core structure such that loads of the first space vehicle are transmitted to the lower core structure of the second space vehicle.

Abstract: A cone-shaped composite article may include an inner sublaminate containing at least four unidirectional plies having an inner stacking sequence with fiber angles of 0, 90, ?45, and +45 degrees such that the inner laminate has a quasi-isotropic layup pattern at any location on the inner laminate. The cone-shaped composite article may also include an outer sublaminate containing at least four unidirectional plies having an outer stacking sequence that is a mirror image of the inner stacking sequence. Each one of the unidirectional plies may be continuous along a ply arclength wrapping 360 degrees around the cone-shaped composite article and may have opposing ply ends terminating at a ply seam.