- #1
Lucy Yeats
- 117
- 0
Homework Statement
An efficient way to reach the Moon is to first put the spacecraft in a low circular Earth
orbit (radius r0, speed v0). The speed is then boosted to vp giving an elliptical orbit with
apogee at the Moon’s orbit, ra, and perigee at r0. Show that:
(vp/v0)^2=2ra/(r0+ra)
Homework Equations
http://en.wikipedia.org/wiki/Vis-viva_equation
The Attempt at a Solution
Using the Vis Viva equations, I found:
vp^2=GM((2/r0)-(1/ra))
v0^2=GM((2/r0)-(1/r0))=GM(1/r0)
so (vp/v0)^2=((2/r0)-(1/ra))/(1/r0)
Which simplifies to (2ra-r0)/ra, which isn't right.
Where did I go wrong?