function [deltaV,lambda,epsilon]=nma_rocket_solveRocketEquationOneStage_form3(mL,mp,ms,Isp) %Solves rocket equation for delta V, mass of properellent and mass of structure and payload %function [deltaV,lambda,epsilon]=nma_rocket_solveRocketEquationOneStage_form3(mL,mp,ms,Isp) % Solves the rocket equation for delta V given Mp (mass of properellent) % and Ms (mass of structure) and mL (payload) and Isp % % Input: % mL: the mass of the payload to carry. in kg. % mp: mass of properllent in kg % ms: mass of structure in kg % Isp: the specific impulse. in seconds. % % Output: % deltaV: the speed gain in meters/seconds possible with this rocket. % lambda: the payload ratio= mL/(ms+mp) % epsilon: The structral mass ratio ( defined as ms/(mp+ms) ). % % Author: Nasser Abbasi % May 30, 2003 g = 9.8066; % conversion factor m0 = ms+mp+mL; mf = ms+mL; deltaV = g*Isp*log(m0/mf); lambda = mL/(mp+ms); epsilon = ms/(ms+mp);