First steps in a weather reorganization. Note especially that

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

diff --git a/src/FDM/JSBSim/FGAircraft.h b/src/FDM/JSBSim/FGAircraft.h
index 3346de06d445dc42c38fd6c796cc6c164a561bd3..b9624792d1995756abc0d29cd9cc389224d9b0b0 100644 (file)
--- a/src/FDM/JSBSim/FGAircraft.h
+++ b/src/FDM/JSBSim/FGAircraft.h
@@ -74,45 +74,6 @@ FORWARD DECLARATIONS
 COMMENTS, REFERENCES, and NOTES [use "class documentation" below for API docs]
 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 
-Longitudinal
-  CL0 - Reference lift at zero alpha
-  CD0 - Reference drag at zero alpha
-  CDM - Drag due to Mach
-  CLa - Lift curve slope (w.r.t. alpha)
-  CDa - Drag curve slope (w.r.t. alpha)
-  CLq - Lift due to pitch rate
-  CLM - Lift due to Mach
-  CLadt - Lift due to alpha rate
- 
-  Cmadt - Pitching Moment due to alpha rate
-  Cm0 - Reference Pitching moment at zero alpha
-  Cma - Pitching moment slope (w.r.t. alpha)
-  Cmq - Pitch damping (pitch moment due to pitch rate)
-  CmM - Pitch Moment due to Mach
- 
-Lateral
-  Cyb - Side force due to sideslip
-  Cyr - Side force due to yaw rate
- 
-  Clb - Dihedral effect (roll moment due to sideslip)
-  Clp - Roll damping (roll moment due to roll rate)
-  Clr - Roll moment due to yaw rate
-  Cnb - Weathercocking stability (yaw moment due to sideslip)
-  Cnp - Rudder adverse yaw (yaw moment due to roll rate)
-  Cnr - Yaw damping (yaw moment due to yaw rate)
- 
-Control
-  CLDe - Lift due to elevator
-  CDDe - Drag due to elevator
-  CyDr - Side force due to rudder
-  CyDa - Side force due to aileron
- 
-  CmDe - Pitch moment due to elevator
-  ClDa - Roll moment due to aileron
-  ClDr - Roll moment due to rudder
-  CnDr - Yaw moment due to rudder
-  CnDa - Yaw moment due to aileron
-
 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 CLASS DOCUMENTATION
 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
@@ -123,10 +84,7 @@ CLASS DOCUMENTATION
     landing gear, etc. These constituent parts may actually run as separate
     JSBSim models themselves, but the responsibility for initializing them and
     for retrieving their force and moment contributions falls to FGAircraft.<br>
-    When an aircraft model is loaded the config file is parsed and for each of the
-    sections of the config file (propulsion, flight control, etc.) the
-    corresponding "ReadXXX()" method is called. From within this method the 
-    "Load()" method of that system is called (e.g. LoadFCS).
+    
     @author Jon S. Berndt
     @version $Id$
     @see
@@ -187,7 +145,9 @@ public:
   inline double Getvbarh(void) { return vbarh; } // H. Tail Volume
   inline double Getvbarv(void) { return vbarv; } // V. Tail Volume
   inline FGColumnVector3& GetMoments(void) { return vMoments; }
+  inline double GetMoments(int idx) { return vMoments(idx); }
   inline FGColumnVector3& GetForces(void) { return vForces; }
+  inline double GetForces(int idx) { return vForces(idx); }
   inline FGColumnVector3& GetBodyAccel(void) { return vBodyAccel; }
   inline FGColumnVector3& GetNcg   (void)    { return vNcg; }
   inline FGColumnVector3& GetXYZrp(void) { return vXYZrp; }
@@ -199,6 +159,7 @@ public:
 
   inline void SetAlphaCLMax(double tt) { alphaclmax=tt; }
   inline void SetAlphaCLMin(double tt) { alphaclmin=tt; }
+  inline void SetAircraftName(string name) {AircraftName = name;}
   
   inline double GetStallWarn(void) { return impending_stall; }
   
@@ -222,16 +183,8 @@ private:
   double lbarh,lbarv,vbarh,vbarv;
   double alphaclmax,alphaclmin;
   double impending_stall;
-  string CFGVersion;
   string AircraftName;
 
-  bool ReadMetrics(FGConfigFile*);
-  bool ReadPropulsion(FGConfigFile*);
-  bool ReadFlightControls(FGConfigFile*);
-  bool ReadAerodynamics(FGConfigFile*);
-  bool ReadUndercarriage(FGConfigFile*);
-  bool ReadPrologue(FGConfigFile*);
-  bool ReadOutput(FGConfigFile*);
   void Debug(int from);
 };