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Path: Orbit/OrbitMechanics
% Compute the sun-synchronous inclination for an orbit. All parameters beyond semi-major axis are optional. See also J2OrbitEffects. -------------------------------------------------------------------------- Form: [iSync,WDot] = SunSyncInclination( a, e, j2, mu, R ) -------------------------------------------------------------------------- ------ Inputs ------ a (1,1) Semi major axis e (1,1) Eccentricity (Default: 0) j2 (1,1) J2 term mu (1,1) Gravitational parameter R (1,1) Planet radius ------- Outputs ------- iSync (1,1) Synchronous inclination (rad) WDot (1,1) Orbit plane precession (rad/s) -------------------------------------------------------------------------- : Wiesel, W. E. (1989.) Spaceflight Dynamics. pp. 86-88. Vallado, 2nd Edition, p. 782-784 --------------------------------------------------------------------------
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