Modular spacecraft system
AssigneeSpace Industries, Inc.
InventorsMaxime A. Faget, Caldwell C. Johnson, David J. Bergeron, III
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Abstract
A modular spacecraft system adapted for orbital flight is capable of expansion by the connection of at least two substantially identical spacecraft modules, each of which is capable of independent operation. Each spacecraft module comprises a spacecraft body, at least one solar array extendible outwardly from the spacecraft body, and at least one structural interface means for connecting one spacecraft module to another spacecraft module. Methods for deployment of a spacecraft module and for assembly of a modular spacecraft system utilizing a reusable space vehicle are also disclosed.
Claims6
A spacecraft module adapted for orbital flight and connectable to a substantially identical spacecraft module, said spacecraft module comprising:
- a spacecraft body having a generally cylindrical shape comprising circumferential side walls, opposed end walls, and a longitudinal axis;
- at least one solar array extendible outwardly from a first side wall area of the spacecraft body, wherein said solar array comprises an articulation means to permit the solar array to rotate about an axis parallel to the longitudinal axis of the spacecraft body;
- and
- at least one structural interface means located on a second side wall area of the spacecraft body spaced circumferentially from said first side wall area for connecting one spacecraft module to another spacecraft module in a side-by-side configuration, so that the longitudinal axes of their respective spacecraft bodies are parallel.
A modular spacecraft system adapted for orbital flight, and capable of expansion by the connection of substantially identical spacecraft modules, each of which is capable of independent operation when not connected to other modules, wherein said modular spacecraft systems comprises at least two spacecraft modules, each of said spacecraft modules comprising:
- a spacecraft body adapted to carry a payload;
- at least one solar array for generating electrical power;
- means for controlling the attitude of the spacecraft module;
- and
- at least one structural interface means for connecting one spacecraft module to another spacecraft module;
- wherein the attitude control means of at least one spacecraft module comprises a gravity gradient stabilization means which is extendible and retractable relative to the spacecraft body;
- and
- wherein each spacecraft body has three orthogonal axes, the solar array is extendible outwardly from a point on the spacecraft body which is generally along an axis parallel to one of the orthogonal axes, the gravity gradient stabilization means is extendible and retractable relative to the spacecraft body generally along an axis parallel to a second of the orthogonal axes, and the structural interface means is located on a side of the spacecraft in a plane normal to the third of the orthogonal axes.
Dependencies are inferred from the claim text.