Patent ID: 6198990
Filing Date: 2001-03-06
Classification: B64G

Abstract:
A method of accurately inserting a satellite into a common orbit and associated common orbit plane wherein a Q vector corresponds to dimensions of said orbit and repetitively traces a Q vector path with a period of .about.18.6 years and said Q vector represents orbit perturbations effected by the earth, the sun and the moon and wherein said common orbit plane has an orbit normal that is tilted from said Q vector by a constant angle and said orbit normal regresses about said Q vector with a regression rate that varies as the product of the cosine of its constant angle and the magnitude of said Q vector and wherein, on an initial date D.sub.i, said common orbit plane had an initial instantaneous inclination I.sub.i and an initial RAAN .OMEGA..sub.i,the method comprising the steps of:selecting a subsequent orbit insertion date D.sub.s that is delayed from said initial date D.sub.i by an elapsed time T.sub.c;updating said initial RAAN .OMEGA..sub.i with said Q vector path, said constant angle, said regression rate and said elapsed time T.sub.e to realize a subsequent RAAN .OMEGA..sub.s of said common orbit plane;from said Q vector path, said constant angle and said subsequent RAAN .OMEGA..sub.s, deriving a subsequent instantaneous inclination I.sub.s of said common orbit plane; andinserting said satellite on said subsequent orbit insertion date D.sub.S into an orbit having said subsequent instantaneous inclination I.sub.S and said subsequent RAAN .OMEGA..sub.S;deviation, at any selected time, of said common orbit plane and said satellite from a common RAAN and a common instananeous inclination is thereby reduced.