Based on the original Rocket Workbench on SourceForge in CVS at:
https://sourceforge.net/projects/rocketworkbench
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174 lines
4.5 KiB
174 lines
4.5 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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#if !defined (rocket_h)
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#define rocket_h 1
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#include <iostream>
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#include "c++rocket.h"
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// enumeration for data
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typedef enum
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{
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pression_sol, // ground pressure in Pa
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masse_molaire, // molar mass of the atmosphere
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temperature, // temperature of the atmosphere
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ATM_DATA_LAST
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} AtmData;
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typedef enum
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{
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masse, // mass of the plenet in Kg
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rayon, // radius of the planet in m
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PLANETE_DATA_LAST
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} PlaneteData;
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typedef enum
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{
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Kdrag, // drag coefficient
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Kdd, // Kd variation with delta
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Klift, // lift coefficient
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Kspin, // cross-spin coefficient
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Kmoment, // moment coefficient
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Kdamping, // damping coefficient
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dmoment, // restoring moment asymetry
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dlift, // lift asymetry
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Diameter, // diameter of the rocket in m
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Mass, // rocket mass in kg (without booster)
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rcm_throat, // distance between mass center and throat throat
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rcm_exit, // distance between mass center and 'exit area'
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k, // radius of geryration about a transverse axis in meter
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// this field should become a function of time
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dt, // angle of the thrust about the rocket axis
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PARA_ROCKET_LAST
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} ParaRocket;
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// Classes ********************************************
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class propulseur {
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char name[32];
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double diameter;
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double length;
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double masse_poudre;
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double masse_totale;
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double **thrust; // table of thrust in function of time
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int check(void); // function to verify if there is data loaded
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public:
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double burntime;
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int ndata; // number of point in **thrust
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int load_data(char*); // char* is the file name
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int print_data(void);
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//#ifdef WITH_GTK
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//int plot_data(void); //plot a graph of the thrust as a fonction of time
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//#endif
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propulseur(void) { ndata = 0; }
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~propulseur(void);
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double T(double time); // thrust in function of time
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double M(double time); // mass in function of time
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// to be verify
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double impulse(void); // total impulse of the motor
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double favg(void); // mean thrust of the motor
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double vg(void); // gaz speed at the exit
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double isp(void); // specific impulse
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double propellant_mass_fraction(void);
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double impulse_to_weight(void);
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};
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class rocket
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{
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int nprop; // nomber of stage
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public:
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char name[32]; // name of the rocket
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double r_data[PARA_ROCKET_LAST];
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class propulseur prop[MAXPROP];
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// set a stage of the rocket (file is the path name of the data file)
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int set_propulseurs(int stage, char file[128]);
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int n_prop(void) { return nprop; }
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rocket(void);
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rocket(double *);
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~rocket() { cout << "Destroying rocket\n"; }
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};
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class atmosphere
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{
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public:
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double a_data[ATM_DATA_LAST];
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atmosphere(void);
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atmosphere(double *);
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~atmosphere() { cout << "Destroying atmosphere\n";}
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};
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class planete : public atmosphere
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{
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public:
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double p_data[PLANETE_DATA_LAST];
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double densiteatm(double); // g/cm^3
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planete(void);
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planete(double *);
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planete(double *planete_data, double *atm_data);
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~planete() { cout << "Destroying planete\n"; }
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};
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class flight_program
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{
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public:
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double ta[MAXPROP]; //temps de l'allumage (depuis le largage du précédent)
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double tl[MAXPROP]; //temps du largage (après la fin de la combustion)
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int set_prog(int stage, double allumage, double largage);
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flight_program(void);
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~flight_program(void) { }
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};
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#endif
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