Suppose we wish to calculate the position of a body that is in a hyperbolic orbit \((e>1)\), as is the case with some comets in orbit around the Sun. where \(M\) is the mean anomaly (in radians), and ...Suppose we wish to calculate the position of a body that is in a hyperbolic orbit \((e>1)\), as is the case with some comets in orbit around the Sun. where \(M\) is the mean anomaly (in radians), and \(F\) is a variable that takes the place of the eccentric anomaly. As with the elliptical Kepler's equation, the hyperbolic version cannot be solved for \(F\) in closed form; instead we must rely on some numerical method like Newton's method to solve for \(F\).
