x_1 and y_1 convert from orbital plane coordinates to observed coordinates.
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M(t) gives mean anomaly in terms of time
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E(m) is a second-order Newton's method approx. of E in terms of M. Good for e<0.9ish
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atan2() function
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T(E_0) gives true anomaly in terms of eccentric anomaly
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R^2 calculation
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R^2 value:
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