System and method for enhanced solar array pointing in sun-nadir steering

A satellite (30) for use in a non-geostationary orbit, comprising:

• a satellite body (35);
• an onboard attitude control system (32) programmed for sun-nadir steering;
• a solar wing (36) mounted to the satellite body (35), the solar wing being adapted to be rotatable about a first axis (A), the solar wing further being adapted to be rotatable about a second axis (B) perpendicular to the first axis, the solar wing including at least one solar array (39);
• a first motor (42) in operative engagement with the solar wing (36) for selectively rotating the solar wing about the first axis (A);
• a second motor (46) in operative engagement with the solar wing (36) for selectively rotating the solar wing about a second axis (B);
• and
• a control circuit (40) in operative communication with the first and second motors for selectively causing the first motor to rotate the solar wing about the first axis and for selectively causing the second motor to rotate the solar wing about the second axis.

A method for decreasing the power requirements of a satellite (30) in a low earth orbit, the satellite including solar wing (36) having a power generating solar array (39), the method comprising the steps of:

• programming an onboard attitude control system (32) for sun-nadir steering;
• rotating the solar wing (36) about a first axis (A);
• and
• pivoting the solar wing (36) about a second axis (B) to maintain the solar array (39) normal to a sunline (33).