- #1

SteveR001

Say we have a rocket of mass M that has a constant power W available for propulsive use (from solar panels perhaps) and it ejects a mass of propellant (m) at a rate (r) per second at a speed (u) relative to the rocket (zero to an outside observer) such that power (W) used remains constant. We could also restrict u to be a maximum of say 3000 m/s and cut off the engine at or before this point; because that is the only situation I’m interested in. The rocket will be given an initial speed u, otherwise it would never accelerate. The mass/s of exhaust ejected will diminish with speed (V) and would be calculated.

As far as I can tell from numerical simulation, the power, acceleration and rocket momentum remain constant, while the overall the performance and flight characteristics appear related to initial speed (u), plus of course the initial mass and power available. Has this model been analysed anywhere? What is its equation of motion and how does it compare to the Tsiolkovsky rocket equation? Is this rocket energy and mass efficient?