namespace JSBSim {
-/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-COMMENTS, REFERENCES, and NOTES [use "class documentation" below for API docs]
-%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
-
/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
CLASS DOCUMENTATION
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
<li>Variance (in percent, from 0 to 1.0, nominally 0.05)</li>
</ul>
Additionally, the following control inputs, operating characteristics, and
- location are required, as with all other engine types:</font>
+ location are required, as with all other engine types:
<ul>
- <li>Throttle setting (in percent, from 0 to 1.0)</font></li>
+ <li>Throttle setting (in percent, from 0 to 1.0)</li>
<li>Maximum allowable throttle setting</li>
<li>Minimum working throttle setting</li>
<li>Sea level fuel flow at maximum thrust</li>
determined.
@author Jon S. Berndt
- @version $Id$
- @see FGNozzle
- @see FGThruster
- @see FGForce
- @see FGEngine
- @see FGPropulsion
- @see FGTank
- @see <a href="http://cvs.sourceforge.net/cgi-bin/viewcvs.cgi/jsbsim/JSBSim/FGRocket.h?rev=HEAD&content-type=text/vnd.viewcvs-markup">
- Header File </a>
- @see <a href="http://cvs.sourceforge.net/cgi-bin/viewcvs.cgi/jsbsim/JSBSim/FGRocket.cpp?rev=HEAD&content-type=text/vnd.viewcvs-markup">
- Source File </a>
+ $Id$
+ @see FGNozzle,
+ FGThruster,
+ FGForce,
+ FGEngine,
+ FGPropulsion,
+ FGTank
*/
/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
public:
/** Constructor.
@param exec pointer to JSBSim parent object, the FDM Executive.
- @param Eng_cfg pointer to the config file object. */
- FGRocket(FGFDMExec* exec, FGConfigFile* Eng_cfg);
+ @param Eng_cfg pointer to the config file object.
+ @param engine_number engine number */
+ FGRocket(FGFDMExec* exec, FGConfigFile* Eng_cfg, int engine_number);
/** Destructor */
- ~FGRocket();
+ ~FGRocket(void);
/** Determines the thrust coefficient.
- This routine takes the nozzle exit pressure and calculates the thrust
- coefficient times the chamber pressure.
- @param pe nozzle exit pressure
@return thrust coefficient times chamber pressure */
- double Calculate(double pe);
-
+ double Calculate(void);
+
/** Gets the chamber pressure.
@return chamber pressure in psf. */
double GetChamberPressure(void) {return PC;}
+ /** Gets the flame-out status.
+ The engine will "flame out" if the throttle is set below the minimum
+ sustainable setting.
+ @return true if engine has flamed out. */
+ bool GetFlameout(void) {return Flameout;}
+ string GetEngineLabels(string delimeter);
+ string GetEngineValues(string delimeter);
+
private:
double SHR;
double maxPC;
double kFactor;
double Variance;
double PC;
+ bool Flameout;
+
void Debug(int from);
};
}