Editing Orbital elements

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<math>a = \sqrt[3]{(T\div2\pi)^2 \mu}</math>
 
<math>a = \sqrt[3]{(T\div2\pi)^2 \mu}</math>
  
<br>(The equation for <math>a</math> is based on ''T'' because ''T'' can be easily derived from the <br>number of seconds in a day divided by a TLE's 'Revolutions per Day' element.)
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<math>\mu</math> is the standard gravitational parameter. (398600441.8 <math>m^3s^{-2}</math> on Earth)
<br><br><math>a</math> is the semi-major axis in meters.
 
<br><math>\mu</math> is the standard gravitational parameter. (398,600,441,800,000 <math>m^3s^{-2}</math> on Earth)
 
 
<br>''T'' is the orbital period in seconds.
 
<br>''T'' is the orbital period in seconds.
 
<!-- 'Orbiter Elements' section added by Quick_Nick of the Orbiter Forum -->
 
<!-- 'Orbiter Elements' section added by Quick_Nick of the Orbiter Forum -->
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* [http://celestrak.com/columns/v04n03/ Celestrak Two-Line Elements FAQ]
 
* [http://celestrak.com/columns/v04n03/ Celestrak Two-Line Elements FAQ]
  
[[Category: Articles]]
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[[Category:Glossary]]
 
[[Category:Glossary]]

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