Doubling speed in circular orbit to attain elliptical orbit

[ln(]

Homework Statement

A satellite is in a circular orbit (radius R) around a planet of mass M. To change the satellite's orbit the engines fire and its speed is suddenly doubled. The engines fire for a very short time. Determine the length of the semi-major axis of the new orbit.

Homework Equations

$v = \sqrt{GM(2/r - 1/a)}$
$\frac{-GMm}{2a} = \frac{1}{2}mv^2 - \frac{GMm}{r}$

The Attempt at a Solution

The velocity of the satellite prior to any propulsion is $v = \sqrt{GM(2/r - 1/a)} = \sqrt{GM/R}$ because $a = r$ for circular orbits.
Right after propulsion, we have $2v = \sqrt{GM(2/r - 1/a)} = \sqrt{GM(2/R - 1/a)}$. If I square this, I get $4v^2 = GM(2/R - 1/a) = 4GM/R$ after substitution. Then, $2/R - 1/a = 4/R$ and $a = -R/2$, but that isn't possible because $a > 0$ for elliptical orbits.

If I use energy, I end up with the same thing. Where have I gone wrong?

 

[gneill]

Perhaps you haven't done anything wrong...

Consider that escape speed is just $\sqrt{2}$ times the circular orbit speed at a given radius. Here you're doubling the speed. So what type of orbit should you end up with?

 

[ln(]

Perhaps you haven't done anything wrong...

Consider that escape speed is just $\sqrt{2}$ times the circular orbit speed at a given radius. Here you're doubling the speed. So what type of orbit should you end up with?

An unbounded one?

EDIT: more specifically a hyperbolic one, where a < 0 is perfectly fine. That's interesting since this question actually is multiple choice in my notes, with answers choices a) R b) 1.5R c) 2R d) 2.5R or e) 4R. The key must be wrong then.

 

[gneill]

An unbounded one?

Yes indeed!

EDIT: more specifically a hyperbolic one, where a < 0 is perfectly fine. That's interesting since this question actually is multiple choice in my notes, with answers choices a) R b) 1.5R c) 2R d) 2.5R or e) 4R. The key must be wrong then.

Yup. The probably changed the question and forgot to update the answers.