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Get the AISim FDM in a semi-flyable state

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This commit is contained in:
Erik Hofman 2020-09-03 14:39:38 +02:00
parent bdc66d5535
commit ce1e85f656
2 changed files with 3 additions and 19 deletions
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20
src/FDM/SP/AISim.cpp
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@ -121,7 +121,7 @@ FGAISim::FGAISim(double dt) :
// the aircraft on it's wheels.
for (int i=0; i<no_gears; ++i) {
// convert from structural frame to body frame
gear_pos[i] = simd4_t<float,3>( cg[X] - gear_pos[i][X],
gear_pos[i] = simd4_t<float,3>(-cg[X] - gear_pos[i][X],
-cg[Y] + gear_pos[i][Y],
cg[Z] - gear_pos[i][Z])*INCHES_TO_FEET;
if (gear_pos[i][Z] < agl) agl = gear_pos[i][Z];
@ -508,7 +508,7 @@ FGAISim::update_velocity(float v)
float Sqbarcbar = Sqbar*cbar;
/* Drag, Side, Lift */
Coef2Force = simd4_t<float,3>(-Sqbar, Sqbar, -Sqbar, Sqbar);
Coef2Force = simd4_t<float,3>(Sqbar);
/* Roll, Pitch, Yaw */
Coef2Moment = simd4_t<float,3>(Sbqbar, Sqbarcbar, Sbqbar, Sbqbar);
@ -658,19 +658,11 @@ FGAISim::load(std::string path)
CYr = 0.262f;
CYdr_n = 0.091f*dr_max;
#if 0
Clb = -0.057f;
Clp = -0.613f;
Clr = 0.079f;
Clda_n = 0.170f*da_max;
Cldr_n = 0.01f*dr_max;
#else
Clb = 0.0;
Clp = 0.0;
Clr = 0.0f;
Clda_n = 0.0f*da_max;
Cldr_n = 0.0f*dr_max;
#endif
Cma = -1.0f;
Cmadot = -4.42f;
@ -678,19 +670,11 @@ FGAISim::load(std::string path)
Cmde_n = -1.05f*de_max;
Cmdf_n = -0.059f*df_max;
#if 0
Cnb = 0.0630f;
Cnp = -0.0028f;
Cnr = -0.0681f;
Cnda_n = -0.0100f*da_max;
Cndr_n = -0.0398f*dr_max;
#else
Cnb = 0.0f;
Cnp = 0.0f;
Cnr = 0.0f;
Cnda_n = 0.0f*da_max;
Cndr_n = 0.0f*dr_max;
#endif
return true;
}

2
src/FDM/SP/AISim.hpp
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@ -106,7 +106,7 @@ public:
xClmnT.ptr()[AILERON][YAW] = Cnda_n*f;
}
inline void set_flaps_norm(float f) {
xCDYLT.ptr()[FLAPS][LIFT] = CLdf_n*f;
xCDYLT.ptr()[FLAPS][LIFT] = -CLdf_n*f;
xCDYLT.ptr()[FLAPS][DRAG] = CDdf_n*std::abs(f);
xClmnT.ptr()[FLAPS][PITCH] = Cmdf_n*f;
}