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 ********************************************************************************
40 [1] Cooke, Zyda, Pratt, and McGhee, "NPSNET: Flight Simulation Dynamic Modeling
41 Using Quaternions", Presence, Vol. 1, No. 4, pp. 404-420 Naval Postgraduate
43 [2] D. M. Henderson, "Euler Angles, Quaternions, and Transformation Matrices",
45 [3] Richard E. McFarland, "A Standard Kinematic Model for Flight Simulation at
46 NASA-Ames", NASA CR-2497, January 1975
47 [4] Barnes W. McCormick, "Aerodynamics, Aeronautics, and Flight Mechanics",
48 Wiley & Sons, 1979 ISBN 0-471-03032-5
49 [5] Bernard Etkin, "Dynamics of Flight, Stability and Control", Wiley & Sons,
50 1982 ISBN 0-471-08936-2
52 The aerodynamic coefficients used in this model are:
55 CL0 - Reference lift at zero alpha
56 CD0 - Reference drag at zero alpha
57 CDM - Drag due to Mach
58 CLa - Lift curve slope (w.r.t. alpha)
59 CDa - Drag curve slope (w.r.t. alpha)
60 CLq - Lift due to pitch rate
61 CLM - Lift due to Mach
62 CLadt - Lift due to alpha rate
64 Cmadt - Moment due to alpha rate
65 Cm0 - Reference moment at zero alpha
66 Cma - Pitching moment slope (w.r.t. alpha)
67 Cmq - Pitch damping (pitch moment due to pitch rate)
68 CmM - Moment due to Mach
71 Cyb - Side force due to sideslip
72 Cyr - Side force due to yaw rate
74 Clb - Dihedral effect (roll moment due to sideslip)
75 Clp - Roll damping (roll moment due to roll rate)
76 Clr - Roll moment due to yaw rate
77 Cnb - Weathercocking stability (yaw moment due to sideslip)
78 Cnp - Rudder adverse yaw (yaw moment due to roll rate)
79 Cnr - Yaw damping (yaw moment due to yaw rate)
82 ClDe - Lift due to elevator
83 CdDe - Drag due to elevator
84 CyDr - Side force due to rudder
85 CyDa - Side force due to aileron
87 CmDe - Pitch moment due to elevator
88 ClDa - Roll moment due to aileron
89 ClDr - Roll moment due to rudder
90 CnDr - Yaw moment due to rudder
91 CnDa - Yaw moment due to aileron
93 ********************************************************************************
95 *******************************************************************************/
101 #include "FGCoefficient.h"
102 #include "FGEngine.h"
105 /*******************************************************************************
107 *******************************************************************************/
109 /*******************************************************************************
111 *******************************************************************************/
114 class FGAircraft : public FGModel
117 FGAircraft(FGFDMExec*);
122 bool LoadAircraft(char*);
124 inline char* GetAircraftName(void) {return AircraftName;}
126 inline void SetGearUp(bool tt) {GearUp = tt;}
127 inline bool GetGearUp(void) {return GearUp;}
128 inline float GetWingArea(void) {return WingArea;}
129 inline float GetWingSpan(void) {return WingSpan;}
130 inline float Getcbar(void) {return cbar;}
131 inline FGEngine* GetEngine(int tt) {return Engine[tt];}
132 inline FGTank* GetTank(int tt) {return Tank[tt];}
133 inline float GetWeight(void) {return Weight;}
134 inline float GetMass(void) {return Mass;}
136 inline float GetL(void) {return Moments[0];}
137 inline float GetM(void) {return Moments[1];}
138 inline float GetN(void) {return Moments[2];}
140 inline float GetFx(void) {return Forces[0];}
141 inline float GetFy(void) {return Forces[1];}
142 inline float GetFz(void) {return Forces[2];}
144 inline float GetIxx(void) {return Ixx;}
145 inline float GetIyy(void) {return Iyy;}
146 inline float GetIzz(void) {return Izz;}
147 inline float GetIxz(void) {return Ixz;}
163 void MassChange(void);
168 char AircraftName[50];
169 float Ixx, Iyy, Izz, Ixz, EmptyMass, Mass;
174 float WingArea, WingSpan, cbar;
176 float Weight, EmptyWeight;
181 int numSelectedOxiTanks;
182 int numSelectedFuelTanks;
183 FGTank* Tank[MAX_TANKS];
184 FGEngine *Engine[MAX_ENGINES];
186 FGCoefficient *Coeff[6][10];
191 enum Param {LiftCoeff,
205 /******************************************************************************/