The Effect of Propellant Energy and Mass Distribution on Rocket Propulsion Efficiency

摘要

The effect of varying the exhaust gas velocity of a rocket so that the exhaust gases possess little or no kinetic energy in an earth observer's frame of reference is examined. Under certain boundary conditions an improvement in terminal velocity of 10 to 20% is obtained relative to a rocket with fixed exhaust velocity. Given a fixed budget of energy per unit payload mass, the optimum mass of working fluid into which to distribute this energy (for maximum burnout speed) is calculated as a function of gravitational field strength. (Author)