Patent ID: 7823836

Claim:
A method of maneuvering a satellite in an orbit, the satellite having a payload disposed longitudinally along a first (x) axis and rotatable solar panels disposed longitudinally along a second (y) axis perpendicular to the first axis (x), the satellite having a moment of inertia about the first axis I XX and about the second axis I YY and a moment of inertia I ZZ about a third (z) axis perpendicular to the first axis (x) and the second (y) axis such that I XX <I YY and I XX <I ZZ the method comprising the steps of: when the satellite is not in a payload data collection mode, performing steps comprising the steps of: orienting the satellite to align the first (x) axis normal to the plane of the orbit; rotating the satellite about the first (x) axis such that the second (y) axis is perpendicular to a Sun line of sight; rotating the solar panels about the second (y) axis at a first angle (θ) from the satellite orbital plane to orient the solar panels towards the Sun; and maintaining the alignment of the first (x) axis normal to the satellite orbital plane during the non-payload data collection mode; when the satellite is in a payload data collection mode, performing steps comprising the steps of: rotating the satellite about only the first (x) axis to direct the payload at a terrestrial target; and collecting payload data.