Abstract

The attitude of a satellite placed on a non-heliosynchronous earth orbit in a plane that is inclined relative to the equatorial plane of the earth is controlled for efficient use of solar panels and radiators. The satellite has a structure, solar panels apt to be rotated with respect to the structure rotation and two opposed radiators each fixed on one of two opposed faces of the satellite structure which are orthogonal to the rotation axis. One of the radiators has greater emissivity than the other. A yaw axis bound to the structure satellite and orthogonal to rotation axis is aimed towards the earth. The solar panels of the satellite are maintained in an optimum orientation relative to the sun by rotating them. At least during periods of each year when an angle ଲ between a sun-earth direction and the plane of the satellite orbit lies between two predetermined values, the satellite structure is rotated about the yaw axis to maintain the radiators in a plane parallel to a direction toward the sun so long as the satellite is remote from an orthogonal projection of the sun direction onto the satellite orbit plane. The orientation of the satellite structure is reversed when necessary to ensure that the radiator of higher emissivity is in shadow.

Other References

• Proceedings of the 28th Eintersociety Energy Conversion Engineering Conference, vol. 1, Aug. 8, 1993-Aug. 13, 1993, Atlanta, U.S.A. pp. 1428-1444, XP 000428328 Seaworth et al. "Implications of A Solar Electric Orbital Transfer Vehicle Design on Power System Requirements" p.1430, right column, line 1--p. 1432, left column, line 18--p. 1438, left column, line 1--p. 1441, right column, line17; Figs. 14-2