Hello everyone i am new to these forums(adsbygoogle = window.adsbygoogle || []).push({});

As a part of my master thesis i am trying to construct transfer orbits based on pathces of the restricted 3 body problem.

However i keep meeting several walls

One is how to calculate the optimal orbit from the earth orbit to the sun earth L1 point

The next is propagating this untill it falls back towards the earth then patch it to the earth moon restricted problem and fall trough earth moon L2 into a low lunar orbit

All help is welcome

I have the book from belbruno covering much of the math involved but i am having problems constructing a program from it.

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# Restricted circular 3 body problem RC3BP

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