Side-by-side dual-launch arrangement with improved payload compatibility

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.

What is claimed is: 
     
         1 . A Geo-synchronous Earth-Orbit (GEO) spacecraft arrangement, comprising:
 a fairing configured to hold a maximum of two GEO spacecraft; and   a first GEO spacecraft and a second GEO spacecraft mounted side-by-side to a launch structure within the fairing,   wherein, for each of the GEO spacecraft, a ratio of a first lateral dimension of the GEO spacecraft to a second lateral dimension of the GEO spacecraft is within a range from 0.55 to 0.8, and wherein the first lateral dimension and the second lateral dimension are perpendicular to each other and smaller than a height of the GEO spacecraft.   
     
     
         2 . The spacecraft arrangement of  claim 1 , wherein the launch structure comprises a first interface comprising a dual-launch adaptor configured to interface with each of the first GEO spacecraft and the second GEO spacecraft, and a second interface configured to interface with a launch vehicle. 
     
     
         3 . The spacecraft arrangement of  claim 2 , wherein the dual-launch adaptor does not occupy a space along a height of and between the first GEO spacecraft and the second GEO spacecraft. 
     
     
         4 . The spacecraft arrangement of  claim 3 , wherein each GEO spacecraft is mounted to the dual-launch adaptor by a core cylinder structure substantially traversing a vertical core of the GEO spacecraft. 
     
     
         5 . The spacecraft arrangement of  claim 4 , wherein the core cylinder structure has a core diameter within a range from about 1.17 meters (m) to about 1.27 m, and the first lateral dimension and the second lateral dimension are at least 1.2 m and larger than the core diameter. 
     
     
         6 . The spacecraft arrangement of  claim 5 , wherein the dual-launch adaptor is configured to tilt at least one of the first GEO spacecraft and the second GEO spacecraft prior to deployment, and jettison at least one of the GEO spacecraft at an angle relative to a plane defined by the dual-launch adaptor. 
     
     
         7 . The spacecraft arrangement of  claim 5 , wherein the dual-launch adaptor is configured to adjust a lateral position of at least one of the first GEO spacecraft and the second GEO spacecraft to adjust a center-of-mass of the spacecraft arrangement. 
     
     
         8 . The spacecraft arrangement of  claim 1 , wherein the fairing has a diameter between 4 and 6 m. 
     
     
         9 . The spacecraft arrangement of  claim 8 , wherein the first lateral dimension is about 1.30 m, and the second lateral dimension is about 2.10 m. 
     
     
         10 . The spacecraft arrangement of  claim 8 , wherein a height of at least one of the first GEO spacecraft and the second GEO spacecraft is within a range from about 3 m to about 6 m. 
     
     
         11 . The spacecraft arrangement of  claim 10 , wherein each GEO spacecraft comprises a first payload component mounted on a first side of the GEO spacecraft and a second payload component mounted on a second side of the GEO spacecraft, the second side being opposite the first side, the first payload component comprising a reflector with a diameter within a range from about 1.3 m to about 5 m. 
     
     
         12 . The spacecraft arrangement of  claim 11 , wherein a dry mass of at least one of the first GEO spacecraft and the second GEO spacecraft is within a range from about 1,000 kilograms (kg) to about 3,500 kg. 
     
     
         13 . A Geo-synchronous Earth-Orbit (GEO) spacecraft arrangement, comprising:
 a fairing configured to hold two GEO spacecraft, the fairing having a diameter between about 4 and 6 meters (m); and   a first GEO spacecraft and a second GEO spacecraft mounted side-by-side to a launch structure within the fairing, each GEO spacecraft being mounted by a core cylinder structure substantially traversing a vertical core of the GEO spacecraft and having a core cylinder diameter within a range from about 1.17 m to about 1.27 m,   wherein, for each of the GEO spacecraft, a height of the GEO spacecraft is within a range from 3 m to 6 m, a first lateral dimension of the GEO spacecraft is about 1.30 m, and a second lateral dimension of the GEO spacecraft is about 2.10 m, and wherein the first lateral dimension and the second lateral dimension are perpendicular to each other.   
     
     
         14 . The spacecraft arrangement of  claim 13 , wherein the launch structure comprises a first interface comprising a dual-launch adaptor configured to interface with each of the first GEO spacecraft and the second GEO spacecraft, and a second interface configured to interface with a launch vehicle, wherein the dual-launch adaptor does not occupy a space along a height of and between the first GEO spacecraft and the second GEO spacecraft. 
     
     
         15 . The spacecraft arrangement of  claim 14 , wherein the dual-launch adaptor is configured to tilt at least one of the first GEO spacecraft and the second GEO spacecraft prior to deployment, and jettison at least one of the GEO spacecraft at an angle relative to a plane defined by the dual-launch adaptor. 
     
     
         16 . The spacecraft arrangement of  claim 14 , wherein the dual-launch adaptor is configured to adjust a lateral position of at least one of the first GEO spacecraft and the second GEO spacecraft to adjust a center-of-mass of the spacecraft arrangement. 
     
     
         17 . The spacecraft arrangement of  claim 13 , wherein each GEO spacecraft comprises a first payload component mounted on a first side of the GEO spacecraft and a second payload component mounted on a second side of the GEO spacecraft, the second side being opposite the first side. 
     
     
         18 . The spacecraft arrangement of  claim 17 , wherein the first payload component comprising a reflector with a diameter within a range from about 1.3 m to about 1.9 m. 
     
     
         19 . The spacecraft arrangement of  claim 17 , wherein the first payload component comprising a reflector with a diameter within a range from about 2.0 m to about 5 m. 
     
     
         20 . The spacecraft arrangement of  claim 13 , wherein a dry mass of at least one of the first GEO spacecraft and the second GEO spacecraft is within a range from about 1,000 kilograms (kg) to about 3,500 kg.