mga.hpp

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// ------------------------------------------------------------------------ //
// This source file is part of the 'ESA Advanced Concepts Team's            //
// Space Mechanics Toolbox' software.                                       //
//                                                                          //
// The source files are for research use only,                              //
// and are distributed WITHOUT ANY WARRANTY. Use them on your own risk.     //
//                                                                          //
// Copyright (c) 2004-2007 European Space Agency                            //
// ------------------------------------------------------------------------ //

#pragma once

#include <vector>
#include "pl_eph_an.hpp"

using namespace std;

// problem types
const int orbit_insertion = 0;          // Tandem
const int total_DV_orbit_insertion = 1; // Cassini 1
const int rndv = 2;                     // Rosetta
const int total_DV_rndv = 3;            // Cassini 2 and Messenger
const int asteroid_impact = 4;          // gtoc1
const int time2AUs = 5;                 // SAGAS

struct customobject
{
  double keplerian[6];
  double epoch;
  double mu;
};

struct mgaproblem
{
  int type;              //problem type
  vector<int> sequence;  //fly-by sequence (ex: 3,2,3,3,5,is Earth-Venus-Earth-Earth-Jupiter)
  vector<int> rev_flag;  //vector of flags for clockwise legs
  double e;              //insertion e (only in case total_DV_orbit_insertion)
  double rp;             //insertion rp in km (only in case total_DV_orbit_insertion)
  customobject asteroid; //asteroid data (in case fly-by sequence has a final number = 10)
  double Isp;
  double mass;
  double DVlaunch;
};

int MGA(
    //INPUTS
    vector<double>,
    mgaproblem,

    //OUTPUTS
    vector<double> &, vector<double> &, double &);