Abstract: A modular spacecraft is provided. The modular spacecraft includes a bus module and a payload module. The bus module provides additional thermal radiative capacity for the payload module by including a bus-panel payload thermal zone that couples operational components of the payload module to a radiator panel in the bus module. The bus module also includes its own operational components that are thermally coupled to the radiator panel but that are thermally isolated from the payload module and the bus-panel payload thermal zone.

Abstract: A side-by-side dual-launch spacecraft arrangement is provided. The arrangement may include a dual-launch adaptor, a first spacecraft, and a second spacecraft. The first spacecraft and the second spacecraft may be mounted on the dual-launch adaptor and may be arranged side by side on the dual-launch adaptor. An aspect ratio of each of the first and second spacecraft may be within a range of 0.55 and 0.8.

Abstract: A side-by-side dual-launch spacecraft arrangement is provided. The arrangement may include a first and second spacecraft mounted within a fairing. The first and second spacecraft may be mounted side by side on the dual-launch adaptor. A ratio of a first lateral dimension of the GEO spacecraft to a second lateral dimension of the GEO spacecraft may be within a range from 0.55 to 0.8, with the first lateral dimension and the second lateral dimension being perpendicular to each other and smaller than a height of the GEO spacecraft.

Abstract: A side-by-side dual-launch spacecraft arrangement is provided. The arrangement may include a dual-launch adaptor, a first spacecraft, and a second spacecraft. The first spacecraft and the second spacecraft may be mounted on the dual-launch adaptor and may be arranged side by side on the dual-launch adaptor. An aspect ratio of each of the first and second spacecraft may be within a range of 0.55 and 0.8.

Abstract: Methods are described for launching multiple space vehicles. A first space vehicle and a second space vehicle can be detachably attached to a launch vehicle. The first space vehicle is for an orbit of a first desired altitude in a first desired orbital plane. The second vehicle is for an orbit of a second desired altitude in a second desired orbital plane. The launch vehicle with the first and second space vehicles may be launched into a first orbit in or near the first desired orbital plane. The second space vehicle may be released in the first orbit. When the orbital plane of the second space vehicle coincides with the second desired orbital plane, the second space vehicle may be transferred to a transfer orbit. The second space vehicle may be transferred to the orbit of the second desired altitude in the second desired orbital plane.