Path: Orbit/OrbitMechanics
% Computes the mean anomaly from change in time
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Form:
M = MeanAnom( dt, a, p, mu )
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Inputs
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dt Change in time
a Semi-major axis (+ for ellipse, inf for parabola
and - for hyperbola)
p Parameter (used for parabolas)
mu Gravitational parameter
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Outputs
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M Mean anomaly
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References: Wiesel, W. E., Spaceflight Dynamics, McGraw-Hill, 1988,
pp. 56-57.
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Common: Graphics/Plot2D
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