-
Notifications
You must be signed in to change notification settings - Fork 7
Commit
This commit does not belong to any branch on this repository, and may belong to a fork outside of the repository.
- Loading branch information
Showing
1 changed file
with
42 additions
and
0 deletions.
There are no files selected for viewing
This file contains bidirectional Unicode text that may be interpreted or compiled differently than what appears below. To review, open the file in an editor that reveals hidden Unicode characters.
Learn more about bidirectional Unicode characters
Original file line number | Diff line number | Diff line change |
---|---|---|
@@ -1,2 +1,44 @@ | ||
# 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) |