Eccentric Anomaly

Calculation

$E=\backslash arccos\; \}$

$\backslash tan\{T\; \backslash over\; 2\}\; =\; \backslash sqrt\}\; \backslash tan\{E\; \backslash over\; 2\}.\backslash ,$

$r\; =\; a\; \backslash left\; (\; 1\; -\; e\; \backslash cdot\; \backslash cos\{E\}\; \backslash right\; )\backslash ,\backslash !$

$r\; =\; a\{(1\; -\; e^2)\; \backslash over\; (1\; +\; e\; \backslash cdot\; \backslash cos\{T\})\}.\backslash ,\backslash !$

See also

• Kepler's laws of planetary motion
• Mean anomaly
• True anomaly

Reference

• Murray, C. D. & Dermott, S. F. 1999, Solar System Dynamics, Cambridge University Press, Cambridge.

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