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Oops. Stray checkin. Revert.

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andy 2002-05-29 07:09:41 +00:00
parent f324ea9bad
commit adeeed1a0e
1 changed files with 14 additions and 31 deletions
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45
src/FDM/YASim/Airplane.cpp
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@ -8,7 +8,6 @@
#include "Thruster.hpp"
#include "Airplane.hpp"
namespace yasim {
// gadgets
@ -795,16 +794,6 @@ void Airplane::solve()
_solutionIterations = 0;
_failureMsg = 0;
while(1) {
#if 0
printf("%d %f %f %f %f %f\n", //DEBUG
_solutionIterations,
1000*_dragFactor,
_liftRatio,
_cruiseAoA,
_tailIncidence,
_approachElevator.val);
#endif
if(_solutionIterations++ > 10000) {
_failureMsg = "Solution failed to converge after 10000 iterations";
return;
@ -827,7 +816,7 @@ void Airplane::solve()
runApproach();
_model.getBody()->getAngularAccel(tmp);
double apitch0 = tmp[1];
float apitch0 = tmp[1];
_model.getBody()->getAccel(tmp);
float alift = _approachWeight * tmp[2];
@ -869,13 +858,13 @@ void Airplane::solve()
// like the tail incidence computation (it's solving for the
// same thing -- pitching moment -- by diddling a different
// variable).
const float ELEVDIDDLE = 0.001f;
const float ELEVDIDDLE = 0.0001f;
_approachElevator.val += ELEVDIDDLE;
runApproach();
_approachElevator.val -= ELEVDIDDLE;
_model.getBody()->getAngularAccel(tmp);
double apitch1 = tmp[1];
float apitch1 = tmp[1];
float elevDelta = -apitch0 * (ELEVDIDDLE/(apitch1-apitch0));
// Now apply the values we just computed. Note that the
@ -886,8 +875,8 @@ void Airplane::solve()
applyLiftRatio(liftFactor);
// DON'T do the following until the above are sane
if(normFactor(dragFactor) > 1.0001
|| normFactor(liftFactor) > 1.0001)
if(normFactor(dragFactor) > 1.1
|| normFactor(liftFactor) > 1.1)
{
continue;
}
@ -895,25 +884,19 @@ void Airplane::solve()
// OK, now we can adjust the minor variables:
_cruiseAoA += 0.5f*aoaDelta;
_tailIncidence += 0.5f*tailDelta;
_approachElevator.val += 0.5f*elevDelta;
_cruiseAoA = clamp(_cruiseAoA, -0.175f, 0.175f);
_tailIncidence = clamp(_tailIncidence, -0.175f, 0.175f);
_cruiseAoA = clamp(_cruiseAoA, -0.174f, 0.174f);
_tailIncidence = clamp(_tailIncidence, -0.174f, 0.174f);
_approachElevator.val = clamp(_approachElevator.val, -1.f, 1.f);
if(norm(dragFactor) < 1.00001 &&
norm(liftFactor) < 1.00001 &&
abs(aoaDelta) < .000017 &&
abs(tailDelta) < .000017)
abs(tailDelta) < .000017 &&
abs(elevDelta) < 0.00001)
{
// If this finaly value is OK, then we're all done
if(abs(elevDelta) < 0.0001)
break;
// Otherwise, adjust and do the next iteration
_approachElevator.val += 0.8 * elevDelta;
if(abs(_approachElevator.val) > 1) {
_failureMsg = "Insufficient elevator to trim for approach";
break;
}
break;
}
}
@ -923,10 +906,10 @@ void Airplane::solve()
} else if(_liftRatio < 1e-04 || _liftRatio > 1e4) {
_failureMsg = "Lift ratio beyond reasonable bounds.";
return;
} else if(Math::abs(_cruiseAoA) >= .17453293) {
} else if(Math::abs(_cruiseAoA) >= .174) {
_failureMsg = "Cruise AoA > 10 degrees";
return;
} else if(Math::abs(_tailIncidence) >= .17453293) {
} else if(Math::abs(_tailIncidence) >= .174) {
_failureMsg = "Tail incidence > 10 degrees";
return;
}