Abstract: An antenna device is disclosed, including an additively manufactured tubular body portion having a wall portion with a plurality of holes. The tubular body portion is configured to transmit electromagnetic radiation in a selected operating frequency range, and to have a mass below a maximum mass threshold. The plurality of holes reduce the mass of the tubular body below the maximum mass threshold without significantly adversely affecting electromagnetic radiation transmission capability of the tubular body in the selected operating frequency range.

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 satellite assembly is disclosed, including a satellite and a shroud. The satellite is stowed in a launch vehicle and the shroud includes a frame supporting a flexible thermal blanket enclosing the satellite.

Abstract: A satellite is disclosed, including a body and a communication device attached to the body. The body has an additively manufactured external wall structure at least partially forming an enclosed compartment, and the communication device is configured to receive and transmit data while in space.

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: A vibration isolation system is disclosed, including a rigid retaining device having an internal space, a first external side, and a second external side. A rigid anchoring device is retained in the internal space of the rigid retaining device. The anchoring device has a linkage member that extends from the internal space to the first external side of the retaining device and is configured for rigid connection to a first apparatus. The second side of the retaining device is configured for attachment to a second apparatus. A damping material is sandwiched between the retaining device and the anchoring device, and is configured to limit transfer of vibration between the retaining device and the anchoring device.

Abstract: A method of additively manufacturing a spacecraft panel includes printing a first skin and a second skin, spaced apart from the first skin. The method further includes printing a first truss structure connecting the first skin to the second skin.

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: Protective blankets comprise a flexible blanket body and a voltage supply. The flexible blanket body comprises a plurality of sheets of material operatively coupled together to define the flexible blanket body. The plurality of sheets comprises one or more sheets composed at least in part of a carbon nanotube material and at least one sheet composed of a different material. The voltage supply is electrically coupled at least to a first sheet of the one or more sheets composed at least in part of the carbon nanotube material, such that the first sheet defines a resistive heater.

Abstract: Methods and apparatus to methods and apparatus for performing propulsion operations using electric propulsion system are disclosed. An example launch vehicle includes a first space vehicle including a first core structure and a first electric propulsion system, and a second space vehicle including a second core structure and a second electric propulsion system, the second core structure releasably attached to the first space vehicle in a stacked configuration.

Abstract: A spacecraft panel includes a first skin, a second skin spaced apart from the first skin, and a first truss structure connecting the first skin to the second skin. The first truss structure includes a plurality of truss members, and each truss member is integral with the first skin and the second skin, such that the first skin, the second skin, and the first truss structure collectively form a single monolithic joint-free structure.

Abstract: An antenna device is disclosed, including a cavity structure having a floor portion and a perimeter wall portion connected to the floor portion. A dipole structure extends upward from a center region of the floor portion inside the cavity structure. At least one of the wall portion and the dipole structure has an opening small enough relative to an expected radio frequency wavelength to avoid affecting antenna performance.

Abstract: A satellite is disclosed, including a body having an additively manufactured wall panel and a communication device connected to the body. The wall panel includes a facesheet and a stiffening structure extending from a first side of the facesheet. The communication device is configured to send and receive data while in space.

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 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 assembly is disclosed, including a satellite and a shroud. The satellite is stowed in a launch vehicle and the shroud includes a frame supporting a flexible thermal blanket enclosing the satellite.

Abstract: A satellite apparatus is disclosed, including a housing having first and second opposing walls, and a support structure inside the housing spanning the first and second walls. The support structure is structurally connected to the housing only at the first and second walls, and an end portion of the support structure is configured for connection to a launch vehicle by a separation system.

Abstract: A satellite dispenser includes a central tubular structure. The satellite dispenser also includes a plurality of satellites arranged around the central tubular structure. The satellite dispenser further includes a plurality of shear connectors coupling the central tubular structure and the plurality of satellites arranged together in shear continuity.

Abstract: An antenna device is disclosed, including an additively manufactured tubular body portion having a wall portion with a plurality of holes. The tubular body portion is configured to transmit electromagnetic radiation in a selected operating frequency range, and to have a mass below a maximum mass threshold. The plurality of holes reduce the mass of the tubular body below the maximum mass threshold without significantly adversely affecting electromagnetic radiation transmission capability of the tubular body in the selected operating frequency range.

Abstract: A space vehicle system, a method of manufacturing a multiple space vehicle system, and a method of disposing space vehicles into Earth orbit are disclosed. The space vehicle system may include a first space vehicle including a first core structure with a first wall thickness. The space vehicle system may include a second space vehicle including a second core structure with a second wall thickness, the second wall thickness different from the first wall thickness, and the second core structure releasably attached to the first space vehicle in a stacked configuration.