Question
A spacecraft of mass m orbits Earth at a radius R and speed $v_0$ as shown below. An aerospace engineer decides it should orbit at a radius of $\frac{2R}{3}$ instead. The mass of Earth is M.
What is the new speed, $v_n$, of the spacecraft in terms of $v_0$?
- My answer
We can begin by saying $v_0 = ωR$ where ω is angular velocity.
Every single point on the radius of this circle has the same angular velocity. I understand that different points on this radius will have different linear velocities. Now if we were to travel 2/3 of the radius up from the centre of the circle, then at that point the linear velocity would be
$v_n$ = ω$\frac{2R}{3}$ = $\frac{2}{3}ωR$ = $\frac{2}{3}v_0$
The actual correct answer:
This mass, $m$, has a centripetal acceleration, $a_c$, which is caused by a centripetal force which in this case is the force of gravity the Earth applies to $m$. So by Netwon's second law we can say
$F_g$ = m$a_c$.
$\frac{GMm}{R^2}$ = $\frac{mv_0^2}{R}$
$v_0$ = $\sqrt\frac{GM}{R}$
$v_n$ = $\sqrt\frac{GM}{\frac{2R}{3}}$
$v_n$ = $\sqrt\frac{3}{2}$ $\sqrt\frac{GM}{R}$ = $\sqrt\frac{3}{2}v_0$
I understand the correct answer which is good but I don't understand why what I wrote was wrong. Why can't the relationship $v = ωR$ be used to find out the what the new velocity is.

The spacecraft is moving in a circular path because It's in equilibrium: The gravitational force equals to the centrifugal force. At $\frac{2}{3}R$, the gravitational force will be stronger, so we would need stronger centrifugal force as well; and it can't happen with the same angular velocity.