src/FDM/JSBSim/FGRocket.h

   1 /*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
   2
   3  Header:       FGRocket.h
   4  Author:       Jon S. Berndt
   5  Date started: 09/12/2000
   6
   7  ------------- Copyright (C) 2000  Jon S. Berndt (jsb@hal-pc.org) --------------
   8
   9  This program is free software; you can redistribute it and/or modify it under
  10  the terms of the GNU General Public License as published by the Free Software
  11  Foundation; either version 2 of the License, or (at your option) any later
  12  version.
  13
  14  This program is distributed in the hope that it will be useful, but WITHOUT
  15  ANY WARRANTY; without even the implied warranty of MERCHANTABILITY or FITNESS
  16  FOR A PARTICULAR PURPOSE.  See the GNU General Public License for more
  17  details.
  18
  19  You should have received a copy of the GNU General Public License along with
  20  this program; if not, write to the Free Software Foundation, Inc., 59 Temple
  21  Place - Suite 330, Boston, MA  02111-1307, USA.
  22
  23  Further information about the GNU General Public License can also be found on
  24  the world wide web at http://www.gnu.org.
  25
  26 HISTORY
  27 --------------------------------------------------------------------------------
  28 09/12/2000  JSB  Created
  29
  30 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
  31 SENTRY
  32 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
  33
  34 #ifndef FGROCKET_H
  35 #define FGROCKET_H
  36
  37 /*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
  38 INCLUDES
  39 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
  40
  41 #include "FGEngine.h"
  42 #include "FGConfigFile.h"
  43
  44 /*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
  45 DEFINITIONS
  46 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
  47
  48 #define ID_ROCKET "$Id$"
  49
  50 /*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
  51 FORWARD DECLARATIONS
  52 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
  53
  54 /*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
  55 COMMENTS, REFERENCES, and NOTES [use "class documentation" below for API docs]
  56 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
  57
  58 /*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
  59 CLASS DOCUMENTATION
  60 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
  61
  62 /** Models a generic rocket engine.
  63     The rocket engine is modeled given the following parameters:
  64     <ul>
  65         <li>Chamber pressure (in psf)</li>
  66         <li>Specific heat ratio (usually about 1.2 for hydrocarbon fuel and LOX)</li>
  67         <li>Propulsive efficiency (in percent, from 0 to 1.0)</li>
  68         <li>Variance (in percent, from 0 to 1.0, nominally 0.05)</li>
  69     </ul>
  70     Additionally, the following control inputs, operating characteristics, and
  71     location are required, as with all other engine types:</font>
  72     <ul>
  73         <li>Throttle setting (in percent, from 0 to 1.0)</font></li>
  74         <li>Maximum allowable throttle setting</li>
  75         <li>Minimum working throttle setting</li>
  76         <li>Sea level fuel flow at maximum thrust</li>
  77         <li>Sea level oxidizer flow at maximum thrust</li>
  78         <li>X, Y, Z location in structural coordinate frame</li>
  79         <li>Pitch and Yaw</li>
  80     </ul>
  81     The nozzle exit pressure (p2) is returned via a
  82     call to FGNozzle::GetPowerRequired(). This exit pressure is used,
  83     along with chamber pressure and specific heat ratio, to get the
  84     thrust coefficient for the throttle setting. This thrust
  85     coefficient is multiplied by the chamber pressure and then passed
  86     to the nozzle Calculate() routine, where the thrust force is
  87     determined.
  88
  89     @author Jon S. Berndt
  90     @version $Id$
  91     @see FGNozzle
  92     @see FGThruster
  93     @see FGForce
  94     @see FGEngine
  95     @see FGPropulsion
  96     @see FGTank
  97     @see <a href="http://cvs.sourceforge.net/cgi-bin/viewcvs.cgi/jsbsim/JSBSim/FGRocket.h?rev=HEAD&content-type=text/vnd.viewcvs-markup">
  98          Header File </a>
  99     @see <a href="http://cvs.sourceforge.net/cgi-bin/viewcvs.cgi/jsbsim/JSBSim/FGRocket.cpp?rev=HEAD&content-type=text/vnd.viewcvs-markup">
 100          Source File </a>
 101 */
 102
 103 /*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 104 CLASS DECLARATION
 105 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
 106
 107 class FGRocket : public FGEngine
 108 {
 109 public:
 110   /** Constructor.
 111       @param exec pointer to JSBSim parent object, the FDM Executive.
 112       @param Eng_cfg pointer to the config file object. */
 113   FGRocket(FGFDMExec* exec, FGConfigFile* Eng_cfg);
 114
 115   /** Destructor */
 116   ~FGRocket();
 117
 118   /** Determines the thrust coefficient.
 119       This routine takes the nozzle exit pressure and calculates the thrust
 120       coefficient times the chamber pressure.
 121       @param pe nozzle exit pressure
 122       @return thrust coefficient times chamber pressure */
 123   double Calculate(double pe);
 124
 125   /** Gets the chamber pressure.
 126       @return chamber pressure in psf. */
 127   double GetChamberPressure(void) {return PC;}
 128
 129 private:
 130   double SHR;
 131   double maxPC;
 132   double propEff;
 133   double kFactor;
 134   double Variance;
 135   double PC;
 136   void Debug(int from);
 137 };
 138
 139 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 140 #endif
 141