Bartholomew said:
If a rocket gives a constant thrust of 1 Newton in outer space then from a "starting" frame of reference the distance it goes every second will always increase. That should mean the work it does per second (the "rate of work") always increases though the force remains constant, right? If you exert a force of 2 Newtons over 2 meters to do 4 joules of work, more of that work will be done over the last second (when the speed is high) than over the first second (when the object is barely moving).
Thet's exactly right
But how does that make SENSE? For conservation of energy it should require the rocket to use more energy to exert the same force force at high speeds than at low speeds, shouldn't it? But IS it? Like, a chemical rocket has a fixed amount of propellant--chemical energy--which it could use at about a constant rate for a constant thrust force. If that energy, used at a constant rate, does work (energy) at a constantly _increasing_ rate--what resolves this apparent dilemma?
You need to consider the energy in the exhaust to maintain the system energy. The detailed calculations are rather messy, but if you add up the total energy (in your fixed reference frame) of the rocket and its exhaust, you'll find that the books balance.
For a more intuitive answer, rockets are not as energy efficient as having something to push against. For low velocities, they really suck. For high velocities, they also suck. When the final velocity of the rocket is near the exhaust velocity, they actually aren't too bad.
The answer to your dilema at high velocities for the increasing power output of the rocket is that the rocket is burning fuel that is already moving, fuel that was accelerated by the fuel that was burned earlier. So the energy to accelerate the rocket isn't coming from nowhere, it was spent earlier, getting the rocket and it's fuel up to velocity.
Note that the amount of fuel required to reach a given velocity grows expeonentially with the velocity target, by the well-known rocket equation
v_rocket = v_exhaust * ln(fuelled_mass / unfuelled_mass)
This exponential relationship is why it's very hard to reach more than a couple of times the exhaust velocity of a rocket. For very large ratios of final velocity to exhaust velocity, multistage rockets are the only way to get the mass ratios high enough.