Satellite orbit equation

  • Thread starter Chip90
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Homework Statement



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?


Homework Equations



conservation of E and angular momentum

The Attempt at a Solution



For 2, I am very lost.

For 1:
I did

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
 
Last edited:

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