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 # MOLTO-3BP
 Multi-Objective Low-Thrust Optimizer for Three Body Problem
+[![DOI](https://zenodo.org/badge/169291732.svg)](https://zenodo.org/badge/latestdoi/169291732)
+Change the DOI toe the new one generated
+
+MOLTO-3BP is a fully automated Matlab tool for the preliminary design of low-thrust trajectories in the restricted three body problem. The software toool applies only for transfers departing from a Earht's circular orbit to a Moon's circular Orbit.
+
+
+## Installation Guide
+Installation requires simply that you download [MOLTO-3BP](https://github.com/uc3m-aerospace/MOLTO-3BP) and add all the folders and subfolders to your Matlab path.
+
+### Dependencies
+A recent version of Matlab is needed to run the code (R2016a or newer). 
+
+## Quick Usage Guide
+
+In order to optimize a mission, the user needs to call the main function *molto_3bp.m* providing an input structure. The user only need to define the departure and target orbit radiuses. Here you have an example:
+
+```matlab
+% MISSION FROM Geostationary Earth Orbit to a circular Low Moon Orbit.
+%% Initial Data
+R_e  = 6378;                                   % [km] Mean Earth's radius
+R_m  = 1738;                                   % [km] Mean Moon's radius
+h_i  = 35786;                                  % [km] Altitude of departure orbit
+h_f  = 4000-R_m;                               % [km] Altitude of arrival orb
+%
+r0   = h_i+R_e;                                % [km] Distance to Earth's Center
+rf   = h_f+R_m;                                % [km] Distance to Moon's Center
+%
+% Save to input structure
+%
+input.r0  = r0;
+input.rf  = rf;
+%
+% Genetic algorithm parameters
+%
+input.pop = 1000;     % NSGA-II population number
+input.gen = 200;      % NSGA-II generation number
+input.init_file     = []; % Load initial populations file (if available)
+input.output_file   = 'Example1.txt'; % Output file name
+input.useParallel   = 'yes'; % (yes/no) Compute fitness function in paralle
+        
+% RUN MOLTO-IT ALGORITHM
+output = molto_3bp(input)