Importance

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Abstract

A series of spacecraft designs (10, 26 & 34) for a Satellite Communication System is disclosed. One of the preferred embodiments of the invention called 'Domesat' (10) includes a hemispherical, high-gain, electronically-steered antenna array (12) that is always pointed toward the Earth (E). Hexagonal antenna panels (14) are held together by tubular and spherical connectors (22 & 24). The upper portion of the satellite (10) incorporates a space-facing array (16) of panels (18) which are always pointed toward the zenith (Z). The interior of the dome-shaped antenna array (12) is used to store solar cell panels (20) which unfurl through an opening (11) in the space-facing array (16) when the spacecraft (10) reaches its final orbit. An alternative embodiment of the invention called 'Gearsat' (26) comprises a hollow torus which inflates when it reaches orbit. When viewed from the side along its circumference, 'Gearsat' (26) looks like two flattened pyramids sharing a common base. Phased array antenna panels ( 29) are deployed across the top of the pyramid along an exterior cylindrical surface (28), while twin arrays of solar cells (30) cover the slanted surfaces. The satellite (26) rotates about its center, and individual antenna panels (29) are spatially synchronized to transmit and receive signals from particular regions on the ground. A third alternative embodiment called 'Batsat' (34), includes a central cylindrical body (B) and a plurality of substantially circular linked antenna and solar/thermal panels (A1-A9 and S1 & S2) which carry individual antennas (X) and solar/thermal surfaces (Y). All of the embodiments (10, 26 & 34) are capable of being nested or stacked in a compact arrangement that fit within the payload bay of a launch vehicle (L).

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First Claim