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elliptical orbit question plz help
see attachment
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
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
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
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