Editing Eccentric anomaly

{{Short description|Angle defining a position in an orbit}}
In [[orbital mechanics]], the '''eccentric anomaly''' is an [[keplerian element|angular parameter]] that defines the position of a body that is moving along an [[ellipse|elliptic]] [[Kepler orbit]], the angle measured at the center of the ellipse between the orbit's periapsis and the current position. The eccentric anomaly is one of three angular parameters ("anomalies") that can be used to define a position along an orbit, the other two being the [[true anomaly]] and the [[mean anomaly]].

==Graphical representation==
[[File:EccentricAnomaly.svg|thumb|324x324px|The eccentric anomaly of point ''P'' is the angle ''E''. The center of the ellipse is point O, and the focus is point ''F''.]]
Consider the ellipse with equation given by:
:<math>\frac{x^2}{a^2} + \frac{y^2}{b^2} = 1, </math>

where ''a'' is the ''semi-major'' axis and ''b'' is the ''semi-minor'' axis.

For a point on the ellipse, ''P''&nbsp;=&nbsp;''P''(''x'',&nbsp;''y''), representing the position of an orbiting body in an elliptical orbit, the eccentric anomaly is the angle ''E'' in the figure. The eccentric anomaly ''E'' is one of the angles of a right triangle with one vertex at the center of the ellipse, its adjacent side lying on the ''major'' axis, having hypotenuse ''a'' (equal to the ''semi-major'' axis of the ellipse), and opposite side (perpendicular to the ''major'' axis and touching the point ''P′'' on the auxiliary circle of radius ''a'') that passes through the point ''P''. The eccentric anomaly is measured in the same direction as the true anomaly, shown in the figure as <math>\theta</math>. The eccentric anomaly ''E'' in terms of these coordinates is given by:<ref name=Wentworth>
{{cite book |title=Elements of analytic geometry |author=George Albert Wentworth |authorlink=George A. Wentworth |page=[https://archive.org/details/elementsanalyti02wentgoog/page/n159 141] |url=https://archive.org/details/elementsanalyti02wentgoog |chapter=The ellipse §126 |edition=2nd |publisher=Ginn & Co. |year=1914}}</ref>
:<math>\cos E = \frac{x}{a} ,</math>

and
:<math>\sin E = \frac{y}{b}</math>

The second equation is established using the relationship
:<math>\left(\frac{y}{b}\right)^2 = 1 - \cos^2 E = \sin^2 E</math>,

which implies that {{nowrap|1=sin ''E'' = ±{{sfrac|''y''|''b''}}}}. The equation {{nowrap|1=sin ''E'' = −{{sfrac|''y''|''b''}}}} is immediately able to be ruled out since it traverses the ellipse in the wrong direction. It can also be noted that the second equation can be viewed as coming from a similar triangle with its opposite side having the same length ''y'' as the distance from ''P'' to the ''major'' axis, and its hypotenuse ''b'' equal to the ''semi-minor'' axis of the ellipse.

==Formulas==

===Radius and eccentric anomaly===
The [[eccentricity (mathematics)|eccentricity]] ''e'' is defined as:

:<math>e=\sqrt{1 - \left(\frac{b}{a}\right)^2 } \ . </math>

From [[Pythagoras's theorem]] applied to the triangle with ''r'' (a distance ''FP'') as hypotenuse:
:<math>\begin{align}
  r^2 &= b^2 \sin^2E + (ae - a\cos E)^2 \\
      &= a^2\left(1 - e^2\right)\left(1 - \cos^2 E\right) + a^2 \left(e^2 - 2e\cos E + \cos^2 E\right) \\
      &= a^2 - 2a^2 e\cos E + a^2 e^2 \cos^2 E \\
      &= a^2 \left(1 - e\cos E\right)^2 \\
\end{align} </math>

Thus, the radius (distance from the focus to point ''P'') is related to the eccentric anomaly by the formula
:<math>r = a \left(1 - e \cos{E}\right) \ .</math>

With this result the eccentric anomaly can be determined from the true anomaly as shown next.

===From the true anomaly===
The ''[[true anomaly]]'' is the angle labeled <math>\theta</math> in the figure, located at the focus of the ellipse. It is sometimes represented by {{mvar|f}} or {{mvar|v}}. The true anomaly and the eccentric anomaly are related as follows.<ref name=Tsui>{{cite book |first=James Bao-yen |last=Tsui |year=2000 |title=Fundamentals of Global Positioning System receivers: A software approach |edition=3rd |page=48 |publisher=[[John Wiley & Sons]] |isbn=0-471-38154-3 |url=https://books.google.com/books?id=jPRCxNDZqDQC&pg=PA48}}</ref>

Using the formula for {{mvar|r}} above, the sine and cosine of {{mvar|E}} are found in terms of {{mvar|f}}&nbsp;:
:<math>\begin{align}
              \cos E &= \frac{\,x\,}{a} = \frac{\, a e + r \cos f \,}{a} = e + (1 - e \cos E) \cos f \\
  \Rightarrow \cos E &= \frac{\, e + \cos f \,}{1 + e \cos f} \\
              \sin E &= \sqrt{\, 1 - \cos^2 E \;} = \frac{\, \sqrt{\, 1 - e^2 \;} \, \sin f \,}{ 1 + e\cos f } ~.
\end{align}</math>

Hence,
:<math>\tan E = \frac{\, \sin E \,}{\cos E} = \frac{\, \sqrt{\, 1 - e^2 \;} \, \sin f \,}{e + \cos f} ~.</math>

where the correct quadrant for {{mvar|E}} is given by the signs of numerator and denominator, so that {{mvar|E}} can be most easily found using an [[atan2]] function.

Angle {{mvar|E}} is therefore the adjacent angle of a right triangle with hypotenuse <math>\; 1 + e \cos f \;,</math> adjacent side <math>\; e + \cos f \;,</math> and opposite side <math>\;\sqrt{ \, 1 - e^2 \; } \, \sin f \;.</math>

Also,
:<math>\tan\frac{\, f \,}{2} = \sqrt{\frac{\, 1 + e \,}{1 - e}\,}  \,\tan\frac{\, E \,}{2}</math>

Substituting {{math|cos}}&nbsp;{{mvar|E}} as found above into the expression for {{mvar|r}}, the radial distance from the focal point to the point {{math|P}}, can be found in terms of the true anomaly as well:<ref name=Tsui/>
:<math>r = \frac{a \left(\, 1 - e^2 \,\right)}{\,  1 + e \cos f \, } =  \frac{p}{\,  1 + e \cos f \, }\,</math>
where
:<math>\, p \equiv a \left(\, 1 - e^2 \,\right) </math>
is called ''"the semi-latus rectum"'' in classical geometry.

===From the mean anomaly===

The eccentric anomaly ''E'' is related to the [[mean anomaly]] ''M'' by [[Kepler's equation]]:<ref name=Capderou>{{cite book |title=Satellites: orbits and missions |author=Michel Capderou |chapter=Definition of the mean anomaly, Eq. 1.68 |page=21 |chapter-url=https://books.google.com/books?id=BAihdjtLZXcC&pg=PA21 |isbn=2-287-21317-1 |year=2005 |publisher=Springer}}</ref>
:<math>M = E - e \sin E</math>

This equation does not have a [[closed-form solution]] for ''E'' given ''M''. It is usually solved by [[numerical methods]], e.g. the [[Newton's method|Newton–Raphson method]]. It may be expressed in a [[Fourier series]] as
:<math>E = M + 2\sum_{n=1}^{\infty } \frac{J_{n}(ne)}{n}\sin(n M)</math>
where <math>J_{n}(x)</math> is the [[Bessel function]] of the first kind.

==See also==
*[[Eccentricity vector]]
*[[Orbital eccentricity]]

==Notes and references==
<references/>

==Sources==
* Murray, Carl D.; & Dermott, Stanley F. (1999); ''Solar System Dynamics'', Cambridge University Press, Cambridge, GB
* Plummer, Henry C. K. (1960); ''An Introductory Treatise on Dynamical Astronomy'', Dover Publications, New York, NY (Reprint of the 1918 Cambridge University Press edition)
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[[Category:Orbits]]

[[de:Exzentrische Anomalie]]