RVToMEq:
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Transforms elements r and v to modified equinoctial.
The modified equinoctial elements are
p = a(1 + e^2)
f = ecos(w + W);
g = esin(w + W);
h = tan(i/2)cosW
k = tan(i/2)sinW
L = W + w + nu
W is right ascension of the ascending node
w is argument of perigee
Since version 7.
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Form:
x = RVToMEq( r, v, mu )
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Inputs
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r (3,1) Position vector
v (3,1) Velocity vector
mu (1,1) Gravitational parameter
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Outputs
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x (6,1) Elements
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Children:
SC: BasicOrbit/RV2El
Sail: Coordinates/ElToMEq
