Abstract: A spacecraft includes a structural interface adapter for mating to a launch vehicle, an aft surface disposed proximate thereto, and a forward surface disposed opposite thereto, a main body structure, including a plurality of sidewalls, disposed between the aft surface and the forward surface and a plurality of unfurlable antenna reflectors. At least one unfurlable antenna reflector is configured to be illuminated, in an on-orbit configuration, by a respective feed array. The spacecraft is reconfigurable from a launch configuration to the on-orbit configuration. In the launch configuration, the at least one unfurlable antenna reflector is disposed, undeployed, forward of the respective feed array, proximate to and outboard of one of the plurality of sidewalls. In the on-orbit configuration, the forward surface is substantially earth-facing and the at least one unfurlable antenna reflector is disposed, deployed, so as to be earth-facing from a position aft of the respective feed array.

Abstract: A modularized feed array arrangement includes a plurality of radio frequency (RF) radiating elements, a plurality of waveguides positioned inboard of the plurality of RF radiating elements, each RF radiating element being electrically coupled with an outboard portion of one or more of the waveguides; and a plurality of modules, each module including a plurality of RF switches, a plurality of amplifiers, and a manifold panel that includes a plurality of RF choke joints. An inboard portion of each RF switch is electrically coupled with a respective amplifier. Each RF choke joint includes a proximal portion electrically coupled with an outboard portion of a respective one of the RF switches and a distal portion electrically coupled with an inboard portion of a respective one of the waveguides.

Abstract: A spacecraft includes a structural interface adapter for mating to a launch vehicle, an aft surface disposed proximate thereto, and a forward surface disposed opposite thereto, a main body structure, including a plurality of sidewalls, disposed between the aft surface and the forward surface and a plurality of unfurlable antenna reflectors. At least one unfurlable antenna reflector is configured to be illuminated, in an on-orbit configuration, by a respective feed array. The spacecraft is reconfigurable from a launch configuration to the on-orbit configuration. In the launch configuration, the at least one unfurlable antenna reflector is disposed, undeployed, forward of the respective feed array, proximate to and outboard of one of the plurality of sidewalls. In the on-orbit configuration, the forward surface is substantially earth-facing and the at least one unfurlable antenna reflector is disposed, deployed, so as to be earth-facing from a position aft of the respective feed array.

Abstract: A modularized feed array arrangement includes a plurality of radio frequency (RF) radiating elements, a plurality of waveguides positioned inboard of the plurality of RF radiating elements, each RF radiating element being electrically coupled with an outboard portion of one or more of the waveguides; and a plurality of modules, each module including a plurality of RF switches, a plurality of amplifiers, and a manifold panel that includes a plurality of RF choke joints. An inboard portion of each RF switch is electrically coupled with a respective amplifier. Each RF choke joint includes a proximal portion electrically coupled with an outboard portion of a respective one of the RF switches and a distal portion electrically coupled with an inboard portion of a respective one of the waveguides.