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revert accidental checkin

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andy 2007-09-05 02:03:15 +00:00
parent f52165731a
commit 7f546e94d3
1 changed files with 6 additions and 16 deletions
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22
src/FDM/YASim/Airplane.cpp
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@ -28,8 +28,6 @@ const float STHRESH = 1;
// oscillate.
const float SOLVE_TWEAK = 0.3226;
const float GRAV = 9.8f;
Airplane::Airplane()
{
_emptyWeight = 0;
@ -125,7 +123,7 @@ void Airplane::getPilotAccel(float* out)
// Gravity
Glue::geodUp(s->pos, out);
Math::mul3(GRAV, out, out);
Math::mul3(-9.8f, out, out);
// The regular acceleration
float tmp[3];
@ -595,7 +593,7 @@ void Airplane::compileContactPoints()
// Give it a spring constant such that at full compression it will
// hold up 10 times the planes mass. That's about right. Yeah.
float mass = _model.getBody()->getTotalMass();
float spring = (1/DIST) * GRAV * 10.0f * mass;
float spring = (1/DIST) * 9.8f * 10.0f * mass;
float damp = 2 * Math::sqrt(spring * mass);
int i;
@ -787,7 +785,6 @@ void Airplane::setupWeights(bool isApproach)
void Airplane::runCruise()
{
__builtin_printf("runCruise()\n");
setupState(_cruiseAoA, _cruiseSpeed,_approachGlideAngle, &_cruiseState);
_model.setState(&_cruiseState);
_model.setAir(_cruiseP, _cruiseT,
@ -831,7 +828,6 @@ void Airplane::runCruise()
void Airplane::runApproach()
{
__builtin_printf("runApproach()\n");
setupState(_approachAoA, _approachSpeed,_approachGlideAngle, &_approachState);
_model.setState(&_approachState);
_model.setAir(_approachP, _approachT,
@ -940,7 +936,7 @@ void Airplane::solve()
runCruise();
_model.getThrust(tmp);
float thrust = tmp[0] + GRAV * _cruiseWeight * Math::sin(_cruiseGlideAngle);
float thrust = tmp[0] + _cruiseWeight * Math::sin(_cruiseGlideAngle) * 9.81;
_model.getBody()->getAccel(tmp);
Math::tmul33(_cruiseState.orient, tmp, tmp);
@ -981,7 +977,7 @@ void Airplane::solve()
float pitch1 = tmp[1];
// Now calculate:
float awgt = GRAV * _approachWeight;
float awgt = 9.8f * _approachWeight;
float dragFactor = thrust / (thrust-xforce);
float liftFactor = awgt / (awgt+alift);
@ -989,10 +985,8 @@ void Airplane::solve()
float tailDelta = -pitch0 * (ARCMIN/(pitch1-pitch0));
// Sanity:
if(dragFactor <= 0 || liftFactor <= 0) {
__builtin_printf("NEGATIVE drag %f lift %f\n", dragFactor, liftFactor);
if(dragFactor <= 0 || liftFactor <= 0)
break;
}
// And the elevator control in the approach. This works just
// like the tail incidence computation (it's solving for the
@ -1011,7 +1005,7 @@ void Airplane::solve()
// Now apply the values we just computed. Note that the
// "minor" variables are deferred until we get the lift/drag
// numbers in the right ballpark.
__builtin_printf("Apply drag %f lift %f\n", dragFactor, liftFactor);
applyDragFactor(dragFactor);
applyLiftRatio(liftFactor);
@ -1022,8 +1016,6 @@ void Airplane::solve()
continue;
}
__builtin_printf("Apply aoa %f tail %f\n", SOLVE_TWEAK*aoaDelta, SOLVE_TWEAK*tailDelta);
// OK, now we can adjust the minor variables:
_cruiseAoA += SOLVE_TWEAK*aoaDelta;
_tailIncidence += SOLVE_TWEAK*tailDelta;
@ -1040,8 +1032,6 @@ void Airplane::solve()
if(abs(elevDelta) < STHRESH*0.0001)
break;
__builtin_printf("Apply elev %f\n", SOLVE_TWEAK*elevDelta);
// Otherwise, adjust and do the next iteration
_approachElevator.val += SOLVE_TWEAK * elevDelta;
if(abs(_approachElevator.val) > 1) {