function [mp,ms,lambda]=nma_rocket_solveRocketEquationOneStage(epsilon,mL,Isp,deltaV) %Solves for Mp (mass of properellent) and Ms (mass of structure) for a given one stage rocket. %function [mp,ms,lambda]=nma_rocket_findMpFromRocketEquation(epsilon,mL,Isp,deltaV) % % Solves for Mp (mass of properellent) and Ms (mass of structure) % for a given one stage rocket. % % Input: % epsilon: The structral mass ratio ( defined as ms/(mp+ms) ). % mL: the mass of the payload to carry. in kg. % Isp: the specific impulse. in seconds. % deltaV: the speed gain in meters/seconds. % % Output: % mp: mass of properllent in kg % ms: mass of structure in kg % lambda: the payload ratio= mL/(ms+mp) % % Author: Nasser Abbasi % May 30, 2003 % g = 9.8066; % conversion factor LHS = exp(deltaV/(g*Isp)); m = mL*(1-LHS) / (epsilon*LHS - 1); ms = epsilon*m; mp = m-ms; lambda = mL/(mp+ms);