function [deltaV,lambda]=nma_rocket_solveRocketEquationOneStage_form2(epsilon,mL,mp,Isp)
%Solves rocket equation for delta V, mass of properellent and mass of structure and payload
%function [deltaV,lambda]=nma_rocket_solveRocketEquationOneStage_form2(epsilon,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 and epsilon for a
% one stage rocket.
%
% Input:
% epsilon: The structral mass ratio ( defined as ms/(mp+ms) ).
% mL: the mass of the payload to carry. in kg.
% mp: mass of properllent 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)
%
% Author: Nasser Abbasi
% May 30, 2003
%
g = 9.8066; % conversion factor
ms = (epsilon*mp)/(1-epsilon);
m0 = ms+mp+mL;
mf = ms+mL;
deltaV = g*Isp*log(m0/mf);
lambda = mL/(mp+ms);