Data transmission systems and methods for low and very low earth orbit satellite communications

A satellite for incorporation in a constellation of multiple said satellites to be used in a radio communication system for transmitting data via a radio route comprising at least one said satellite as a node of radio route, said satellite comprising:

• a casing having a longitudinal axis defining the y-axis of a right-handed x, y, z coordinate system and containing (i) a plurality of antennas for receiving and transmitting radio signals, (ii) at least one rechargeable battery, (iii) at least one solar panel for recharging said battery, (iv) an attitude controlling mechanism, and (v) control circuitry for selectively energizing said attitude controlling mechanism, wherein:
• said control circuitry selectively connects said at least one battery to said attitude controlling mechanism for controlling the angle of the x-y plane of the casing relative to the earth's surface with the z-axis pointing generally away from the earth to define an outward facing casing surface including said at least one solar panel and a downward facing casing surface including said antenna array;
• and
• said outer casing is streamlined to minimize aerodynamic drag on the satellite.

A satellite for incorporation in a constellation of multiple said satellites to be used in a radio communication system for transmitting data via a radio route comprising at least one said satellite as a node of radio route, said satellite comprising:

• a casing having a longitudinal axis defining the y-axis of a right-handed x, y, z coordinate system and containing (i) a plurality of antennas for receiving and transmitting radio signals, (ii) at least one rechargeable battery, (iii) at least one solar panel for recharging said battery, (iv) an attitude stabilizing mechanism, (v) an attitude controlling mechanism, and (vi) control circuitry for selectively energizing said attitude stabilizing mechanism and said attitude controlling mechanism, wherein:
• said control circuitry selectively connects said at least one battery to said attitude stabilizing mechanism for urging said satellite into an operational attitude with the y-axis of the casing traveling in an orbital path generally along a longitude of the earth;
• said control circuitry selectively connects said at least one battery to said attitude controlling mechanism for controlling the angle of the x-y plane of the casing relative to the earth's surface with the z-axis pointing generally away from the earth to define an outward facing casing surface including said at least one solar panel and a downward facing casing surface including said antenna array;
• and
• said outer casing is streamlined to minimize aerodynamic drag on the satellite.