I want to calculate the time of flight (TOF) between two true anomalies on an orbit with known orbital elements. Based on this wikipedia article and the post Time of flight between two anomalies in a known orbital trajectory , I ended up using the following formula.
Knowing the true anomalies $\nu_1$ and $\nu_2$ (with $\nu_2 > \nu_1$) at some (unknown) times $t_1$ and $t_2$ ($t_2 > t_1$), I express the TOF $t_2 - t_1$ from $\nu_1$ to $\nu_2$ by: $$ t_2-t_1 = \sqrt{\frac{a^3}{\mu}}(E_2-E_1 + e(\sin E_1 - \sin E_2)) $$ Where $E_1$ and $E_2$ are the corresponding eccentric anomalies calculated using the equation: $$ E = 2 \arctan \left( \sqrt{\frac{1-e}{1+e}} \tan \frac{\nu}{2} \right) $$

However this expression in practice gives me a wrong negative TOF.

This can be verified with a simple numerical example. Since $\sqrt{a^3/\mu}$ is always positive, we can focus only on the sign of the part involving the eccentric anomalies. Considering :

$e = 0.11$ (slightly elliptic orbit)
$\nu_1 = 2.43 \ \text{rad}$
$\nu_2 = 3.78 \ \text{rad}$

We calculate $E_1$ and $E_2$:

$E_1 \approx 2.35 \ \text{rad} $
$E_2 \approx -2.43 \ \text{rad} $

Which then gives:

$$ \begin{align} (E_2-E_1 + e(\sin E_1 - \sin E_2)) & = (-2.43-2.35+0.11\times(\sin(2.35)-\sin(-2.43))) \\ & \approx -4.63 < 0 \end{align} $$

This problem will arise whenever a true anomaly is greater than $\pi$ because of the $\pi$-periodicity of $\tan$. Is there a way to counter this ? Is there a formula for TOF that works well for all cases ? If possible one that would also work with a hyperbolic orbit (through sign changes and the usage of the hyperbolic anomaly).

Thanks in advance.

  • $\begingroup$ @Uwe I don't understand your comment. I never mentioned two or more bodies. I'm focusing on a single perfect elliptic orbit (I'm working on a simulation). A spacecraft is moving on that orbit. I want to calculate the time of flight of that spacecraft going from a point A on that orbit specified by its true anomaly $\nu_1$, and a point B of true anomaly $\nu_2$. $\endgroup$
    – Krafpy
    Aug 4, 2021 at 14:47
  • 1
    $\begingroup$ Since you're working with an elliptical orbit, continue working through the calculation. If the resulting time of flight is negative, add the orbital period. $\endgroup$
    – notovny
    Aug 4, 2021 at 15:17
  • $\begingroup$ @Uwe Quoting entry #5 from the dictionary.com definition of anomaly, Astronomy. a quantity measured in degrees, defining the position of an orbiting body with respect to the point at which it is nearest to or farthest from its primary. $\endgroup$ Aug 4, 2021 at 15:17
  • 3
    $\begingroup$ @novotny Alternatively add $2\pi$ to the ending eccentric anomaly ($E_2$) when $E_2<E_1$. $\endgroup$ Aug 4, 2021 at 15:30
  • $\begingroup$ I am sorry, I confused anomalies and mascons. $\endgroup$
    – Uwe
    Aug 4, 2021 at 15:45

1 Answer 1


When true anomaly is between 0 and $\pi$ the formula for E is fine, but above $\pi$ you have to adjust the Arctan value to get E in the right quadrant. It looks like just add 2$\pi$ to a negative value E.

Yes, there is a system to not use E, called universal variables. See Fundamentals of Astrodynamics by Bate et al., and Fundamentals of Astrodynamics and Applications by Vallado, both in Chapter 4.

  • $\begingroup$ Use asterisks for titles of books and articles. Using dollar signs is for math, and while math mode is wonderful for math, it's lousy for italicizing words. I'll fix this one for you. $\endgroup$ Aug 4, 2021 at 18:17

Your Answer

By clicking “Post Your Answer”, you agree to our terms of service, privacy policy and cookie policy

Not the answer you're looking for? Browse other questions tagged or ask your own question.