Modular spacecraft system

Claim 2

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.

Claim 3

The spacecraft module of claim 1, further comprising a gravity gradient stabilization means which is extendible and retractable relative to one end of the spacecraft body.

Claim 4

The spacecraft module of claim 1 wherein the spacecraft body further comprises an inner chamber having a generally cylindrical shape which is located within the spacecraft body in a position such that the longitudinal axis of the inner chamber is parallel to and displaced from the longitudinal axis of the spacecraft body.

Claim 5

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.

Claim 6

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.

Claim 7

The modular spacecraft system of claim 4 wherein the solar array comprises articulation means to permit the solar array to rotate about an axis parallel to the second orthogonal axis of the spacecraft body.

Claim 8

The modular spacecraft system of claim 5 wherein the spacecraft body has a generally cylindrical shape and the articulation means permits rotation about an axis parallel to the longitudinal axis of the spacecraft body.