Based on the original Rocket Workbench on SourceForge in CVS at:
https://sourceforge.net/projects/rocketworkbench
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314 lines
6.6 KiB
314 lines
6.6 KiB
/* cpropep.c - Calculation of Complex Chemical Equilibrium */
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/* Copyright (C) 2000 */
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/* Antoine Lefebvre <antoine.lefebvre@polymtl.ca> */
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/* This program is free software; you can redistribute it and/or modify*/
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/* it under the terms of the GNU General Public License as published by*/
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/* the Free Software Foundation; either version 2 of the License, or */
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/* (at your option) any later version. */
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/* This program is distributed in the hope that it will be useful, */
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/* but WITHOUT ANY WARRANTY; without even the implied warranty of */
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/* MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the */
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/* GNU General Public License for more details. */
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/* You should have received a copy of the GNU General Public License */
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/* along with this program; if not, write to the Free Software */
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/* Foundation, Inc., 675 Mass Ave, Cambridge, MA 02139, USA. */
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#include <iostream>
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#include <stdio.h>
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#include <cmath>
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#include "c++rocket.h"
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#include "rocket.h"
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extern FILE* yyin; // file pointer for the file parser
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// function generate by the flex lexer generator (motor.l)
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extern int motorscan(char *name, double *diameter,
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double *length, double *masse_totale,
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double *masse_poudre, double **thrust,
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int *ndata);
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simulation *simptr; // this is the pointer to the active simulation
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const double G = 6.67259e-11; // universal gaz constant
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const double R = 8.3145; // perfect gaz constant
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const double g = 9.80665; // Earth gravitational constant
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// default value for the initialisation
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static double rocket_default[PARA_ROCKET_LAST] = { 0.204,
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2,
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2.33,
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20.4,
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6.32,
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31.6,
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0,
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0,
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0.1143,
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16,
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1,
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1.1,
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0.229,
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0 };
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static double planete_default[PLANETE_DATA_LAST] = { 5.98e24,
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6370000 };
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static double atmosphere_default[ATM_DATA_LAST] = { 1.013e5,
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0.0289644,
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273.15 };
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propulseur::~propulseur()
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{
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cout << "Destroying propulseur\n";
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if (!(ndata == 0))
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{
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delete [] thrust[0];
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delete [] thrust[1];
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delete [] thrust;
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}
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}
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int propulseur::print_data(void)
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{
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if (!(check()))
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return -1;
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cout << "Motor:\t\t\t" << name << endl;
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cout << "Diameter:\t\t" << diameter << " m" << endl;
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cout << "Length:\t\t" << length << " m" << endl;
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cout << "Mass de propergol:\t" << masse_poudre << " Kg" << endl;
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cout << "Total mass:\t\t" << masse_totale << " Kg" << endl;
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//cout << ndata << endl;
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cout << endl;
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cout << "Time (s)\t" << "Thrust (N)" << endl;
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for (int k = 0; k < ndata; k++)
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cout << thrust[0][k] << "\t\t" << thrust[1][k] << endl;
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return 0;
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}
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int propulseur::load_data(char file[32])
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{
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FILE *file_in = NULL;
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if ((file_in = fopen(file, "r")) == NULL)
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{
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cout << "No such file or directory " << file << endl;
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return -1;
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}
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yyin = file_in;
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thrust = new double*[2];
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motorscan(name, &diameter, &length, &masse_totale,
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&masse_poudre, thrust, &ndata);
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fclose(file_in);
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burntime = thrust[0][ndata-1];
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return 0;
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}
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//#ifdef WITH_GTK
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//int propulseur::plot_data(void) {
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// cout << "I plot the data...\n";
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// return 0;
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//}
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//#endif
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int propulseur::check(void)
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{
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if (ndata == 0)
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{
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cout << "No data loaded\n";
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return -1;
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}
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return 1;
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}
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double propulseur::T(double time)
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{
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if (!(check()))
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return 0; // no thrust
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double pousse;
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// there is file with no data at time 0
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if (time < thrust[0][0])
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return (thrust[1][0]/thrust[0][0])*time;
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// after the last data, the thrust is 0
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if (time > thrust[0][ndata-1])
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return 0;
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// linear interpolation ( should be interesting
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// to add quadratic interpolation
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for (int i = 1; i < ndata; i++)
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if ((thrust[0][i] > time) && (thrust[0][i-1] <= time))
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{
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pousse = (thrust[1][i]-thrust[1][i-1])/
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(thrust[0][i]-thrust[0][i-1])*(time-thrust[0][i-1]) +
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thrust[1][i-1];
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}
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return pousse;
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}
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double propulseur::M(double time)
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{
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if (!(check()))
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return 0;
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if (time > burntime)
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return (masse_totale - masse_poudre);
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else
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return (masse_totale - time*(masse_totale-masse_poudre)/burntime);
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return 0;
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}
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double propulseur::impulse(void)
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{
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if (!(check()))
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return -1;
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double I = 0;
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for (int i = 0; i < (ndata - 1); i++)
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I += (thrust[1][i]+thrust[1][i+1])*(thrust[0][i+1]-thrust[0][i])/2;
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return I;
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}
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double propulseur::favg(void)
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{
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if (check())
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return (impulse()/burntime);
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return -1;
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}
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double propulseur::vg(void)
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{
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if (check())
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return impulse()/masse_poudre;
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return -1;
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}
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double propulseur::isp(void)
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{
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if (check())
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return vg()/g;
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return -1;
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}
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double propulseur::propellant_mass_fraction(void)
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{
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if (check())
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return masse_poudre/masse_totale;
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return -1;
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}
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double propulseur::impulse_to_weight(void)
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{
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if (check())
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return impulse()/(masse_totale*g);
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return -1;
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}
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rocket::rocket(void)
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{
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nprop = 0;
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r_data = rocket_default;
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}
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rocket::rocket(double *r)
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{
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nprop = 0;
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for (int i = 0; i < PARA_ROCKET_LAST; i++)
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r_data[i] = r[i];
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}
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int rocket::set_propulseurs(int stage, char file[128])
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{
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if (stage > MAXPROP)
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return -1;
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if (!(stage == 1))
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if (prop[stage-2].ndata == 0) {
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cout << "Stage " << stage-1 << " not loaded.\n";
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return -1;
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}
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prop[stage-1].load_data(file);
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nprop = stage;
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return 0;
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}
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planete::planete(void)
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{
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p_data = planete_default;
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}
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planete::planete(double *p)
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{
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for (int i = 0; i < PLANETE_DATA_LAST; i++)
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p_data[i] = p[i];
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}
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planete::planete(double *p, double *a) : atmosphere(a)
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{
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for (int i = 0; i < PLANETE_DATA_LAST; i++)
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p_data[i] = p[i];
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}
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double planete::densiteatm(double altitude)
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{
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double d = (((a_data[pression_sol] * a_data[masse_molaire]) / (R*a_data[temperature]))* exp(( (a_data[masse_molaire]*G*p_data[masse])/(R*a_data[temperature]) ) * ( (1/(p_data[rayon] + altitude)) - (1/p_data[rayon]) ) ));
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return d;
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}
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atmosphere::atmosphere(void)
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{
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a_data = atmosphere_default;
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}
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atmosphere::atmosphere(double* a)
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{
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for (int i = 0; i < ATM_DATA_LAST; i++)
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a_data[i] = a[i];
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}
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flight_program::flight_program(void)
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{
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for (int i = 0; i < MAXPROP; i++)
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{
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ta[i] = 0;
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tl[i] = 0;
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}
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}
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int flight_program::set_prog(int stage, double allumage, double largage)
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{
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if ( (stage < 1) || (stage > MAXPROP) )
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return -1;
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ta[stage - 1] = allumage;
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tl[stage - 1] = largage;
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return 0;
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}
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