Fix stall widths for the "auxilliary" (reverse flow) stalls so they

[flightgear.git] / src / FDM / JSBSim / FGRocket.h

diff --git a/src/FDM/JSBSim/FGRocket.h b/src/FDM/JSBSim/FGRocket.h
index c99446c55e35864c3c20a33e1eb2b356405b6c98..00befb0d415c4f981e658273d8fab86a55170868 100644 (file)
--- a/src/FDM/JSBSim/FGRocket.h
+++ b/src/FDM/JSBSim/FGRocket.h
@@ -51,9 +51,7 @@ DEFINITIONS
 FORWARD DECLARATIONS
 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
 
-/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-COMMENTS, REFERENCES, and NOTES [use "class documentation" below for API docs]
-%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
+namespace JSBSim {
 
 /*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 CLASS DOCUMENTATION
@@ -68,9 +66,9 @@ 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>
@@ -87,13 +85,13 @@ CLASS DOCUMENTATION
     determined.
 
     @author Jon S. Berndt
-    @version $Id$
-    @see FGNozzle
-    @see FGThruster
-    @see FGForce
-    @see FGEngine
-    @see FGPropulsion
-    @see FGTank
+    $Id$
+    @see FGNozzle,
+    FGThruster,
+    FGForce,
+    FGEngine,
+    FGPropulsion,
+    FGTank
 */
 
 /*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
@@ -105,28 +103,41 @@ class FGRocket : public FGEngine
 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 */
-  float Calculate(float 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:
-  float SHR;
-  float maxPC;
-  float propEff;
-  float kFactor;
-  float Variance;
-  void Debug(void);
+  double SHR;
+  double maxPC;
+  double propEff;
+  double kFactor;
+  double Variance;
+  double PC;
+  bool Flameout;
+
+  void Debug(int from);
 };
-
+}
 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 #endif