1 /*******************************************************************************
7 ------------- Copyright (C) 1999 Jon S. Berndt (jsb@hal-pc.org) -------------
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
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
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.
23 Further information about the GNU General Public License can also be found on
24 the world wide web at http://www.gnu.org.
27 --------------------------------------------------------------------------------
30 ********************************************************************************
32 *******************************************************************************/
37 /*******************************************************************************
38 COMMENTS, REFERENCES, and NOTES
39 *******************************************************************************/
41 The aerodynamic coefficients used in this model typically are:
44 CL0 - Reference lift at zero alpha
45 CD0 - Reference drag at zero alpha
46 CDM - Drag due to Mach
47 CLa - Lift curve slope (w.r.t. alpha)
48 CDa - Drag curve slope (w.r.t. alpha)
49 CLq - Lift due to pitch rate
50 CLM - Lift due to Mach
51 CLadt - Lift due to alpha rate
53 Cmadt - Pitching Moment due to alpha rate
54 Cm0 - Reference Pitching moment at zero alpha
55 Cma - Pitching moment slope (w.r.t. alpha)
56 Cmq - Pitch damping (pitch moment due to pitch rate)
57 CmM - Pitch Moment due to Mach
60 Cyb - Side force due to sideslip
61 Cyr - Side force due to yaw rate
63 Clb - Dihedral effect (roll moment due to sideslip)
64 Clp - Roll damping (roll moment due to roll rate)
65 Clr - Roll moment due to yaw rate
66 Cnb - Weathercocking stability (yaw moment due to sideslip)
67 Cnp - Rudder adverse yaw (yaw moment due to roll rate)
68 Cnr - Yaw damping (yaw moment due to yaw rate)
71 CLDe - Lift due to elevator
72 CDDe - Drag due to elevator
73 CyDr - Side force due to rudder
74 CyDa - Side force due to aileron
76 CmDe - Pitch moment due to elevator
77 ClDa - Roll moment due to aileron
78 ClDr - Roll moment due to rudder
79 CnDr - Yaw moment due to rudder
80 CnDa - Yaw moment due to aileron
82 [1] Cooke, Zyda, Pratt, and McGhee, "NPSNET: Flight Simulation Dynamic Modeling
83 Using Quaternions", Presence, Vol. 1, No. 4, pp. 404-420 Naval Postgraduate
85 [2] D. M. Henderson, "Euler Angles, Quaternions, and Transformation Matrices",
87 [3] Richard E. McFarland, "A Standard Kinematic Model for Flight Simulation at
88 NASA-Ames", NASA CR-2497, January 1975
89 [4] Barnes W. McCormick, "Aerodynamics, Aeronautics, and Flight Mechanics",
90 Wiley & Sons, 1979 ISBN 0-471-03032-5
91 [5] Bernard Etkin, "Dynamics of Flight, Stability and Control", Wiley & Sons,
92 1982 ISBN 0-471-08936-2
95 /*******************************************************************************
97 *******************************************************************************/
100 # include <Include/compiler.h>
101 # ifdef FG_HAVE_STD_INCLUDES
105 # include <fstream.h>
114 #include "FGCoefficient.h"
115 #include "FGEngine.h"
118 #include "FGConfigFile.h"
120 /*******************************************************************************
122 *******************************************************************************/
126 /*******************************************************************************
128 *******************************************************************************/
130 class FGAircraft : public FGModel
133 FGAircraft(FGFDMExec*);
137 bool LoadAircraft(string, string, string);
138 bool LoadAircraftEx(string, string, string);
139 inline string GetAircraftName(void) {return AircraftName;}
140 inline void SetGearUp(bool tt) {GearUp = tt;}
141 inline bool GetGearUp(void) {return GearUp;}
142 inline float GetWingArea(void) {return WingArea;}
143 inline float GetWingSpan(void) {return WingSpan;}
144 inline float Getcbar(void) {return cbar;}
145 inline FGEngine* GetEngine(int tt) {return Engine[tt];}
146 inline FGTank* GetTank(int tt) {return Tank[tt];}
147 inline float GetWeight(void) {return Weight;}
148 inline float GetMass(void) {return Mass;}
149 inline float GetL(void) {return Moments[0];}
150 inline float GetM(void) {return Moments[1];}
151 inline float GetN(void) {return Moments[2];}
152 inline float GetFx(void) {return Forces[0];}
153 inline float GetFy(void) {return Forces[1];}
154 inline float GetFz(void) {return Forces[2];}
155 inline float GetIxx(void) {return Ixx;}
156 inline float GetIyy(void) {return Iyy;}
157 inline float GetIzz(void) {return Izz;}
158 inline float GetIxz(void) {return Ixz;}
159 inline float GetXcg(void) {return Xcg;}
160 inline int GetNumEngines(void) {return numEngines;}
169 void MassChange(void);
173 float baseIxx, baseIyy, baseIzz, baseIxz, EmptyMass, Mass;
174 float Ixx, Iyy, Izz, Ixz;
176 float baseXcg, baseYcg, baseZcg;
181 float WingArea, WingSpan, cbar;
183 float Weight, EmptyWeight;
189 int numSelectedOxiTanks;
190 int numSelectedFuelTanks;
191 FGTank* Tank[MAX_TANKS];
192 FGEngine *Engine[MAX_ENGINES];
194 FGCoefficient *Coeff[6][10];
199 enum Param {LiftCoeff,
208 vector <FGLGear*> lGear;
214 /******************************************************************************/