The problem is that a satellite is ejected from a planet radius R and mass M, that has no atmosphere, 30 degrees from vertial with velocity vo.
This is a multi part problem dealing with center of mass/inertia, the part I need help with is the following:
1. When the satellite is at point B, what is the velocity in terms of point A?
Point A is R away from the center of the planet (so it is on the surface of the planet) and Point B is 3R from the center of the planet.
2. What is equation to relate vo to R?
conservation of E and angular momentum
The Attempt at a Solution
For 2, I am very lost.
KEi + PEi = KEf +PEf
(1/2)*m(satellite)*vo^2 - G*m(earth)*m(satellite)/R= (1/2)*m(satellite)*vb^2 - G*m(earth)*m(satellite)/3R
this simplifies to Vb^2=Vo^2 - 16/9 * G*m*(earth)/R