초록 ▼

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

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).

대표청구항 ▼

A spacecraft apparatus capable of being placed in a low Earth orbit using a launch vehicle (L) and also being capable of operating as one of a constellation of communications satellites in a low Earth orbit for providing communications among said constellation of communications satellites and among

A spacecraft apparatus capable of being placed in a low Earth orbit using a launch vehicle (L) and also being capable of operating as one of a constellation of communications satellites in a low Earth orbit for providing communications among said constellation of communications satellites and among a plurality of portable, mobile, and fixed terminals comprising: an antenna array (12); said antenna array (12) including a plurality of substantially hexagonal, planar antenna panels (14) and having an interior (11) which is substantially enclosed by said plurality of substantially hexagonal, planar antenna panels (14); said plurality of substantially hexagonal, planar antenna panels (14) being maintained in an orbital orientation which aims said plurality of substantially hexagonal, planar antenna panels (14) generally toward the Earth\s surface; a plurality of spherical connector elements (22) and tubular connector elements (24); said plurality of spherical and tubular connector elements (22 & 24) being used to mechanically couple said plurality of substantially hexagonal, planar antenna panels (14) in a generally contiguous pattern which approximates the contour of a partially oblate hemisphere; and said antenna array (12) being capable of being stowed in a coaxially nested arrangement with other antenna arrays (12) for transportation in said launch vehicle (L); a space-facing array (16); said space-facing array (16) including a plurality of substantially polygonal, planar segments (18); each of said plurality of substantially polygonal, planar segments (18) being maintained in an orbital orientation which aims said plurality of substantially polygonal, planar segments (18) generally away from the Earth\s surface; having a hinged boundary (18a); said hinged boundary (18a) residing generally adjacent to said antenna array (12); and further having a plurality of movable boundaries (18b); each of said plurality of movable boundaries being capable of moving in a circular path toward said antenna array (12) to provide access to said interior (11) of said antenna array (12); said space-facing array (16) also partially enclosing said interior (11) of said antenna array (12); and a solar panel (20) for supplying power to said antenna array (12); said solar panel (20) being capable of being stowed substantially within said interior (11) of said antenna array (12); said solar panel (20) being capable of being deployed outside said antenna array (12) and unfurled to a fully extended position (20b) after said space-facing array (16) is opened by moving said plurality of substantially polygonal, planar segments (18); said solar panel (20) including a layer of amorphous silicon solar cells; said solar panel (20) being mechanically connected to said antenna array (12); and said solar panel (20) being capable of being rotated about its longitudinal axis (A) to optimize the collection of solar radiation.