An Earth (mass M) satellite of mass m is in a circular orhit of radius r1. It is moved to an orbit with a larger radius r2, by way of an intermediate elliptical orbit, This is achieved by firing rockets for a short period when it is in the inner orbit and then firing the rockets again when it has reached the maximum distance M. Determine the total mechanical energy for each of the three orbits and the energy increase for each transfer.
I don't want the answers to this question, but I would like some help in firguring out how to work this problem. Formulas etc. There will be conservation of angular momentum and there is a relationship between r1 and v1 - but I'm not sure exactly how to work it out. Any help would be grand. Ta!
I don't want the answers to this question, but I would like some help in firguring out how to work this problem. Formulas etc. There will be conservation of angular momentum and there is a relationship between r1 and v1 - but I'm not sure exactly how to work it out. Any help would be grand. Ta!