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**elliptical orbit question please help**

## Homework Statement

see attachment

## Homework Equations

2a (average distance of satellite from central body) = A (aphelium) + P (perihelium)

ME = KE + PE

ME = -GMm/24

KE = .5mv^2

PE = -GMm/r

ME orignall = ME final

## The Attempt at a Solution

I tried to put ME = KE + PE = constant.

I solved for theoretical A, and P, if the velocity was only transverse.

Then, I subtracted the theoretical P by the distance caused by the KE. I sitll did not get the answer htough

#### Attachments

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