Abstract: Stray light in a metering structure is controlled by surrounding with a rigid shield an elongated length of a strut and supporting on the rigid shield a surface finish which is highly absorptive of light. The strut is thermally decoupled from the rigid shield using a plurality of insulating web layers comprising a multi-layer insulation (MLI) system disposed between the strut and the rigid shield. The MLI in such scenarios (1) thermally isolates the strut from the shield (2) serves as a support structure to support the rigid shield on the strut, and (3) absorbs thermally induced mechanical stresses as between the rigid shield and the strut.

Abstract: Metering structure includes a rigid strut configured to support an optical element. A rigid shield mounted on the strut has a shield length which is substantially coextensive with the elongated length of the rigid strut such that rigid shield substantially encloses the strut along the entire shield length. The rigid shield has a surface finish which is highly absorptive of electromagnetic radiation in the optical spectrum. One or more thermal insulating material layers comprise a multi-layer insulation (MLI) system disposed between the rigid strut and the rigid shield. Rigid and flexure brackets secure the rigid shield to the strut.

Abstract: Technology is disclosed herein for orbit raising of multiple spacecraft launched with a single launch vehicle. Two or more spacecraft are configured in a stacked launch configuration in which a lower spacecraft is mechanically coupled with a payload adapter of a launch vehicle with one or more upper spacecraft above the lower spacecraft. Propellant that is stored in the lower spacecraft during launch is transferred to an upper spacecraft in the stack after launch. The propellent may be used by the upper spacecraft for an orbit raising maneuver that raises the orbit of at least the upper spacecraft from a first orbit to a second orbit. Storing the propellant in the lower spacecraft lowers the center of mass of the stack during launch. Lowering the center of mass reduces the structural bending moment of the stack during launch, which allows a greater total launch mass.

Abstract: Technology is disclosed herein for using an antenna reflector to regulate a spacecraft temperature during orbit raising. When in a launch configuration, the antenna reflector may be stowed in a fairing of a launch vehicle. After the spacecraft is deployed from the launch vehicle and prior to orbit raising, the antenna reflector is moved from the launch configuration to an orbit raising configuration in which the antenna reflector is used to regulate the spacecraft temperature. The antenna reflector may be proximate a thermal radiator panel of the spacecraft when in the launch configuration. The antenna reflector may be positioned such that sunlight will reflect off the antenna reflector onto the thermal radiator panel, thereby warming the spacecraft. After orbit raising, the antenna reflector is moved from the orbit raising configuration to an operational configuration in which a boresight of the antenna reflector may be directed toward nadir.