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