(adsbygoogle = window.adsbygoogle || []).push({}); 1. The problem statement, all variables and given/known data

The given data is the perigee altitude [itex]r_p[/itex], the apogee altitude [itex]r_a[/itex] and the period T. Mission: find the altitude 30 min after perigee passage.

2. Relevant equations

Semi-major axis a is calculated.

Kepler's equation gives a relation for the eccentric anomaly E:

[tex]E - \epsilon \sin{E} = \frac{2 \pi}{T} \left( t - t_p \right)[/tex]

The radius of the orbit is given by

[tex]r = a \left( 1 - \epsilon \cos{E} \right)[/tex]

3. The attempt at a solution

How do I solve for the eccentric anomaly E so I can use the formula for the radius? Or should I use another approach?

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# Homework Help: Orbit calculations

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