Equation of the center

Simulated view of an object in an elliptic orbit, as seen from the focus of the orbit. The view rotates with the mean anomaly, so the object appears to oscillate back and forth across this mean position with the equation of the center. The object also appears to become smaller and larger as it moves farther away and nearer because of the eccentricity of the orbit. A marker (red) shows the position of the periapsis.

In two-body, Keplerian orbital mechanics, the equation of the center is the angular difference between the actual position of a body in its elliptical orbit and the position it would occupy if its motion were uniform, in a circular orbit of the same period. It is defined as the difference true anomaly, ν, minus mean anomaly, M, and is typically expressed a function of mean anomaly, M, and orbital eccentricity, e.[1]

## Contents

* 1 Discussion
* 2 Series expansion
* 3 Examples
* 4 See also
* 5 References
* 6 Further reading

## Discussion

Since antiquity, the problem of predicting the motions of the heavenly bodies has been simplified by reducing it to one of a single body in orbit about another. In calculating the position of the body around its orbit, it is often convenient to begin by assuming circular motion. This first approximation is then simply a constant angular rate multiplied by an amount of time. There are various methods of proceeding to correct the approximate circular position to that produced by elliptical motion, many of them complex, and many involving solution of Kepler's equation. In contrast, the equation of the center is one of the easiest methods to apply.

In cases of small eccentricity, the position given by the equation of the center can be nearly as accurate as any other method of solving the problem. Many orbits of interest, such as those of bodies in the Solar System or of artificial Earth satellites, have these nearly-circular orbits. As eccentricity becomes greater, and orbits more elliptical, the equation's accuracy declines, failing completely at the highest values, hence it is not used for such orbits.

The equation in its modern form can be truncated at any arbitrary level of accuracy, and when limited to just the most important terms, it can produce an easily calculated approximation of the true position when full accuracy is not important. Such approximations can be used, for instance, as starting values for iterative solutions of Kepler's equation,[1] or in calculating rise or set times, which due to atmospheric effects cannot be predicted with much precision.

The Ancient Greece , in particular Hipparchus, knew the equation of the center as prostaphaeresis, although their understanding of the geometry of the planets' motion was not the same.[2] The word equation (Latin, aequatio, -onis) in the present sense comes from astronomy. It was specified and used by Kepler, as that variable quantity determined by calculation which must be added or subtracted from the mean motion to obtain the true motion. In astronomy, the term equation of time has a similar meaning.[3] The equation of the center in modern form was developed as part of perturbation analysis, that is, the study of the effects of a third body on two-body motion.[4][5]

## Series expansion

Maximum error of the series expansion of the equation of the center, in radians, as a function of orbital eccentricity (bottom axis) and the power of e at which the series is truncated (right axis). Note that at low eccentricity (left-hand side of the graph), the series does not need to be carried to high order to produce accurate results.

Series-expanded equation of the center as a function of mean anomaly for various eccentricities, with the equation of the center truncated at e7 for all curves. Note that the truncated equation fails at high eccentricity and produces an oscillating curve.

In Keplerian motion, the coordinates of the body retrace the same values with each orbit, which is the definition of a periodic function. Such functions can be expressed as periodic series of any continuously increasing angular variable,[6] and the variable of most interest is the mean anomaly, M. Because it increases uniformly with time, expressing any other variable as a series in mean anomaly is essentially the same as expressing it in terms of time. Because the eccentricity, e, of the orbit is small in value, the coefficients of the series can be developed in terms of powers of e.[5] Note that while these series can be presented in truncated form, they represent a sum of an infinite number of terms.[7]

The series for ν, the true anomaly can be expressed most conveniently in terms of M, e and Bessel functions of the first kind,[8]

[math]\displaystyle{ \nu = M + 2\sum_{s=1}^\infty \frac 1 s \left\\{J_s(se) + \sum_{p=1}^\infty \beta^p\left[J_{s-p}(se) + J_{s+p}(se) \right]\right\\}\sin sM, }[/math]

where

[math]\displaystyle{ J_n(se) }[/math] are the Bessel functions and

[math]\displaystyle{ \beta=\frac{1}{e}\left(1-\sqrt{1-e^2}\right). }[/math][9]

The result is in radians.

The Bessel functions can be expanded in powers of x by,[10]

[math]\displaystyle{ J_n(x) = \frac{1}{n!}\left(\frac{x}{2}\right)^n\sum_{m=0}^\infty(-1)^m\frac{\left(\frac{x}{2}\right)^{2m}}{m!\prod_{k=1}^m (n+k)} }[/math]

and βm by,[11]

[math]\displaystyle{ \beta^m = \left(\frac{e}{2}\right)^m\left[1+m\sum_{n=1}^\infty\frac{(2n+m-1)!}{n!(n+m)!}\left(\frac{e}{2}\right)^{2n}\right]. }[/math]

Substituting and reducing, the equation for ν becomes (truncated at order e7),[8]

[math]\displaystyle{ \begin{align} \nu = M &\+ \left(2e - \frac{1}{4}e^3 + \frac{5}{96}e^5 + \frac{107}{4608}e^7\right) \sin M\\\ &{}+ \left(\frac{5}{4}e^2 - \frac{11}{24}e^4 + \frac{17}{192}e^6\right) \sin 2 M\\\ &{}+ \left(\frac{13}{12}e^3 - \frac{43}{64}e^5 + \frac{95}{512}e^7\right) \sin 3 M\\\ &{}+ \left(\frac{103}{96}e^4 - \frac{451}{480}e^6\right) \sin 4 M\\\ &{}+ \left(\frac{1097}{960}e^5 - \frac{5957}{4608}e^7\right) \sin 5 M\\\ &{}+ \frac{1223}{960}e^6\sin6M + \frac{47273}{32256}e^7\sin7M + \cdots \end{align} }[/math]

and by the definition, moving M to the left-hand side,

[math]\displaystyle{ \nu - M = \left(2e - \frac{1}{4}e^3 + \frac{5}{96}e^5 + \frac{107}{4608}e^7\right) \sin M + \cdots }[/math]

gives the equation of the center.

This equation is sometimes derived in an alternate way and presented in terms of powers of e with coefficients in functions of sin M (truncated at order e6),

[math]\displaystyle{ \begin{align} \nu = M &{}+ 2e \sin M + \frac{5}{4}e^2\sin 2M\\\ &{}+ \frac{e^3}{12}(13\sin 3M - 3\sin M)\\\ &{}+ \frac{e^4}{96}(103\sin 4M - 44\sin 2M)\\\ &{}+ \frac{e^5}{960}(1097\sin 5M - 645\sin 3M + 50\sin M)\\\ &{}+ \frac{e^6}{960}(1223\sin 6M - 902\sin 4M + 85\sin 2M)+ \cdots \end{align} }[/math]

which is identical to the above form.[12][13]

For small e, the series converges rapidly. If e exceeds 0.6627..., it diverges for some values of M, first discovered by Pierre-Simon Laplace.[12][14]

## Examples

| Orbital
eccentricity[15] | Maximum equation of the center (series truncated as shown)

|
|

e7 | e3 | e2
Venus | 0.006777  | 0.7766°  | 0.7766°  | 0.7766°
Earth | 0.01671  | 1.915°  | 1.915°  | 1.915°
Saturn | 0.05386  | 6.174°  | 6.174°  | 6.186°
Mars | 0.09339  | 10.71°  | 10.71°  | 10.77°
Mercury | 0.2056  | 23.68°  | 23.77°  | 23.28°

## See also

* Celestial mechanics
* Gravitational two-body problem
* Kepler orbit
* Kepler problem
* Two-body problem

## References

1. ↑ 1.0 1.1 Vallado, David A. (2001). Fundamentals of Astrodynamics and Applications (second ed.). Microcosm Press, El Segundo, CA. p. 82. ISBN 1-881883-12-4.
2. ↑ Narrien, John (1833). An Historical Account of the Origin and Progress of Astronomy. Baldwin and Cradock, London. pp. 230–231. https://archive.org/details/historicalaccoun00narr.
3. ↑ Capderou, Michel (2005). Satellites Orbits and Missions. Springer-Verlag. p. 23. ISBN 978-2-287-21317-5. https://archive.org/details/satellitesorbits00capd.
4. ↑ Moulton, Forest Ray (1914). An Introduction to Celestial Mechanics (second revised ed.). Macmillan Co., New York. p. 165. https://books.google.com/books?id=5XJAAAAAIAAJ. , at Google books
5. ↑ 5.0 5.1 Smart, W. M. (1953). Celestial Mechanics. Longmans, Green and Co., London. p. 26.
6. ↑ Brouwer, Dirk; Clemence, Gerald M. (1961). Methods of Celestial Mechanics. Academic Press, New York and London. p. 60. https://archive.org/details/methodsofcelesti00brou.
7. ↑ Vallado, David A. (2001). p. 80
8. ↑ 8.0 8.1 Brouwer, Dirk; Clemence, Gerald M. (1961). p. 77.
9. ↑ Brouwer, Dirk; Clemence, Gerald M. (1961). p. 62.
10. ↑ Brouwer, Dirk; Clemence, Gerald M. (1961). p. 68.
11. ↑ Smart, W. M. (1953). p. 32.
12. ↑ 12.0 12.1 Moulton, Forest Ray (1914). pp. 171–172.
13. ↑ Danby, J.M.A. (1988). Fundamentals of Celestial Mechanics. Willmann-Bell, Inc., Richmond, VA. pp. 199–200. ISBN 0-943396-20-4.
14. ↑ Plummer, H. C. (1918). An Introductory Treatise on Dynamical Astronomy. Cambridge University Press. pp. 46–47. https://archive.org/details/introductorytrea00plumiala.
15. ↑ Seidelmann, P. Kenneth; Urban, Sean E., eds (2013). Explanatory Supplement to the Astronomical Almanac (3rd ed.). University Science Books, Mill Valley, CA. p. 338. ISBN 978-1-891389-85-6.

## Further reading

* Marth, A. (1890). On the computation of the equation of the centre in elliptical orbits of moderate eccentricities. Monthly Notices of the Royal Astronomical Society, Vol. 50, p. 502\. Gives the equation of the center to order e10.
* Morrison, J. (1883). On the computation of the eccentric anomaly, equation of the centre and radius vector of a planet, in terms of the mean anomaly and eccentricity. Monthly Notices of the Royal Astronomical Society, Vol. 43, p. 345\. Gives the equation of the center to order e12.
* Morrison, J. (1883). Errata. Monthly Notices of the Royal Astronomical Society, Vol. 43, p. 494.

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