Hello friends (I hope ),(adsbygoogle = window.adsbygoogle || []).push({});

For a maths project I am working on, I need to be able to prove the equation for an elliptical orbit, related to Kepler's first law:

and p = a(1-e^{2}) (or should be as p can be replaced by that value)

Where:

r = distance from sun to any point on the orbit

p = semi latus rectrum

a = semi-major axis

e = eccentricity

θ = true anomaly (angle between a and r anticlockwise I think)

Can someone please help me to understand where these equations come from and also confirm that I have got my current facts straight?

Regards,

Memocyl

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# B Mathematical Proof of Kepler's First Law of Orbits

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