Design and performance of ion-engine systems for control of earth satellites

Abstract

Nomenclature A = earth's oblateness coefficient Ad = satellite drag area Ac = satellite area exposed to solar radiation c = speed of light in a vacuum Cd = satellite coefficient of atmospheric drag iQ = initial inclination of the satellite orbit K2 = earth's gravitational constant Ki2 = moon's gravitational constant Ksz = sun's gravitational constant ms = satellite mass r = initial orbital radius R = moon's distance from the center of the earth Rs = sun's distance from the center of the earth T = earth triaxiality coefficient V = satellite orbital velocity /8 = angular position of the moon as measured in the satellite plane from the line of nodes 7 = angular position of the sun as measured in the satellite plane from the line of nodes e = coordinate axis normal to the initial satellite plane v = angular position of the satellite as measured in the satellite plane from the line of nodes £ = coordinate axis through the satellite line of nodes and assumed to coincide with the vernal equinox direction p = density of atmospheric particles r = moon's latitude with respect to the satellite plane v = coordinate axis in the initial satellite plane which is normal at the £ axis 4> = radiant flux from the sun at the earth's distance ^ = sun's latitude with respect to the satellite plane cos = nominal angular velocity of the satellite 12 = angular position of equator's minor axis measured from vernal equinox direction