Path: Orbit/OrbitMechanics
% Compute J2 effects on the orbital elements - analytic model. Computes the advance of the perigee, orbit plane precession, critical inclination and the synchronous inclination as a function of the J2 term and other orbital parameters. -------------------------------------------------------------------------- Form: [wDot, WDot, thDot] = J2OrbitEffects( a, e, i, j2, mu, rP ) -------------------------------------------------------------------------- ------ Inputs ------ a (1,1) Semi major axis e (1,1) Eccentricity i (1,1) Orbit inclination j2 (1,1) J2 term (unnormalized) mu (1,1) Gravitational parameter rP (1,1) Planet radius ------- Outputs ------- wDot (1,1) Perigee advance (rad/s) WDot (1,1) Orbit plane precession (rad/s) thDot Latitude drift rate [rad/s] -------------------------------------------------------------------------- Reference: Wiesel, W. E. (1989.) Spaceflight Dynamics. pp. 86-87. -------------------------------------------------------------------------- See also SunSyncInclination --------------------------------------------------------------------------
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