Multiple application paraboloid spacecraft structure

Abstract

A combined application paraboloid spacecraft structure that is adapted to serve as a structural element for space transportation vehicles, and in additional applications, as a separated spacecraft. The primary structure of the combined application paraboloid spacecraft structure is shaped as the shell of a paraboloid of revolution which has focusing properties for use in such functions as a solar power concentrator, a surveillance or an astronomical telescope, or a communications antenna when deployed in space. The primary structure of this combined application paraboloid can nest and can also be used to support other single or multiple host spacecraft during launch and orbit to orbit transportation. The convex side of the combined application paraboloid primary structure is designed to receive and support auxiliary equipment for combined application paraboloid spacecraft and space transportation vehicles, such as command and control equipment, communications equipment, thrusters, power supplies, and solar power collector panels. The multiple application spacecraft may be employed with a single host spacecraft or a plurality of host spacecraft, or a plurality of such multiple application paraboloid spacecraft may be nested together in a self supporting/protecting stack for launch. The primary structure may also be employed itself as a protective fairing or other aerothermodynamic shield, or in a support function for equipment carried on space transportation vehicles.