Editing Elliptic orbit (section)

== Orbital period ==
Under standard assumptions the orbital period (<math>T\,\!</math>) of a body travelling along an elliptic orbit can be computed as:<ref>{{cite book |first1=Roger R. |last1=Bate |first2=Donald D. |last2=Mueller |first3=Jerry E. |last3=White |url=https://books.google.com/books?id=UtJK8cetqGkC&pg=PA33 |title=Fundamentals Of Astrodynamics |date=1971 |publisher=Dover |location=New York |isbn=0-486-60061-0 |page=33 |edition=First}}</ref> 
:<math>T=2\pi\sqrt{a^3\over{\mu}}</math>
where:
*<math>\mu</math> is the [[standard gravitational parameter]].
*<math>a\,\!</math> is the length of the [[semi-major axis]].
Conclusions:
*The orbital period is equal to that for a [[circular orbit]] with the orbital radius equal to the semi-major axis (<math>a\,\!</math>),
*For a given semi-major axis the orbital period does not depend on the eccentricity (See also: [[Kepler's laws of planetary motion#Third law|Kepler's third law]]).