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Keano16
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Homework Statement
It is required to put a satellite into an orbit with apogee of 5R/2, where R is the radius of the planet. The satellite is to be launched from the surface with a speed Vo at 30degrees to the local vertical. If M is the mass of the planet, show that (Vo)^2 = 5GM/4R. Assume zero rotation.
Homework Equations
The Attempt at a Solution
I tried to use conservation of energy first i.e., 1/2*m*Vo^2 - GMm/R = 2GmM/3R
3R/2 - distance between planet's surface and apogee).
Needless to say, that doesn't yield the right answer, I was wondering perhaps elliptical orbits have some other requirements -- perhaps the inclusion of angular momentum?
Thanks, I appreciate any nudge towards the right direction.