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True anomaly

 
WordNet: true anomaly
Note: click on a word meaning below to see its connections and related words.

The noun has one meaning:

Meaning #1: the angular distance of a point in an orbit past the point of periapsis measured in degrees


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Wikipedia: True anomaly
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The true anomaly is the angle z-s-p

In celestial mechanics, the true anomaly is an angular parameter that defines the position of a body moving along a Keplerian orbit. It is the angle between the direction of periapsis and the current position of the body, as seen from the main focus of the ellipse (the point around which the object orbits).

The true anomaly is usually denoted by the Greek letters ν or θ, or the Roman letter f.

The true anomaly is one of three angular parameters ("anomalies") that define a position along an orbit; the other two being the eccentric anomaly and the mean anomaly.

Contents

Formulas

From state vectors

For elliptic orbits true anomaly \nu\,\! can be calculated from orbital state vectors as:

 \nu = \arccos { {\mathbf{e} \cdot \mathbf{r}} \over { \mathbf{\left |e \right |} \mathbf{\left |r \right |} }}   (if \mathbf{r} \cdot \mathbf{v} < 0 then replace \nu\ by 2\pi-\nu\ )

where:

Circular orbit

For circular orbits this can be simplified to:

 \nu = \arccos { {\mathbf{n} \cdot \mathbf{r}} \over { \mathbf{\left |n \right |} \mathbf{\left |r \right |} }}   (if \mathbf{n} \cdot \mathbf{v} >0 then replace \nu\ by 2\pi-\nu\ )

where:

  •  \mathbf{n} is vector pointing towards the ascending node (i.e. the z-component of  \mathbf{n} is zero).

Circular orbit with zero inclination

For circular orbits with the inclination of zero this can be simplified further to:

 \nu = \arccos { r_x  \over { \mathbf{\left |r \right |}}}   (if  v_x > 0\ then replace \nu\ by 2\pi-\nu\ )

where:

From the eccentric anomaly

The relation between the true anomaly ν and the eccentric anomaly E is:

\cos{\nu} = {{\cos{E} - e} \over {1 - e \cdot \cos{E}}}

or equivalently

\tan{\nu \over 2} = \sqrt{{{1+e} \over {1-e}}} \tan{E \over 2}.

Therefore

  \nu   = 2 \, \mathop{\mathrm{arg}}\left(\sqrt{1-e} \, \cos\frac{E}{2} , \sqrt{1+e}\sin\frac{E}{2}\right)

where \operatorname{arg}(x, y) is the polar argument of the vector \left(x, y\right) (available in many programming languages as the library function atan2(y, x)).

Radius from true anomaly

The radius (distance from the focus of attraction and the orbiting body) is related to the true anomaly by the formula

r = a\cdot{1 - e^2 \over 1 + e \cdot \cos\nu}\,\!

where a is the orbit's semi-major axis (segment cz).

See also

References

  • Murray, C. D. & Dermott, S. F. 1999, Solar System Dynamics, Cambridge University Press, Cambridge.
  • Plummer, H.C., 1960, An Introductory treatise on Dynamical Astronomy, Dover Publications, New York. (Reprint of the 1918 Cambridge University Press edition.)

 
 
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