Patent ID: 9669948
Date: 2017-06-06
CPC Classifications: B64G

Claim:
1. A Geo-synchronous Earth-Orbit (GEO) side-by-side dual-launch spacecraft arrangement, comprising: a fairing having a diameter between 4 and 6 meters (m); a dual-launch adaptor comprising a first interface and a second interface, the first interface being larger than the second interface, the second interface configured to interface to a launch vehicle; a first GEO spacecraft mounted at the first interface of the dual-launch adaptor by a first core cylinder structure substantially traversing a vertical core of a bus structure of the first GEO spacecraft, wherein the first GEO spacecraft comprises: a first payload component mounted on a first side of the first GEO spacecraft; and a second payload component mounted on a second side of the first GEO spacecraft, wherein the second side of the first GEO spacecraft is opposite the first side of the first GEO spacecraft; and a second GEO spacecraft mounted at the first interface of the dual-launch adaptor by a second core cylinder structure substantially traversing a vertical core of a bus structure of the second GEO spacecraft, wherein the second GEO spacecraft comprises a third payload component mounted on a first side of the second GEO spacecraft, wherein each of the first and second GEO spacecraft has an aspect ratio within a range from 0.55 to 0.8, the aspect ratio being a ratio of a size of a corresponding spacecraft along a first lateral dimension and a size of the corresponding spacecraft along a second lateral dimension, wherein the first and second lateral dimensions are perpendicular to each other and each of the first and second lateral dimensions is perpendicular to, and smaller than, a height of the corresponding spacecraft, wherein the first GEO spacecraft and the second GEO spacecraft are arranged side by side on the dual-launch adapter and within the fairing, and wherein a maximum number of spacecraft contained within the fairing is two.