public int ExportSweep(CelestialBody body, double pitch, int flapSetting, bool spoilers)
{
if (!IsReady())
{
return(0);
}
FARAeroUtil.UpdateCurrentActiveBody(body);
FARAeroUtil.ResetEditorParts();
StaticAnalysisExportFile exportdata = new StaticAnalysisExportFile();
InstantConditionSimInput input = new InstantConditionSimInput(0, 0, 0, 0, 0, 0, FlightEnv.NewDefaultVal(body), pitch, flapSetting, spoilers);
InstantConditionSimOutput output;
Vector3d centerofmass = _instantCondition.GetCoM();
// Loop through each combination (two dimensions).
foreach (float mach in exportdata.MachNumberList)
{
input.fltenv.MachNumber = mach;
input.alpha = 0; // zero is used as a neutral value for the reset
_instantCondition.ResetClCdCmSteady(centerofmass, input); // reset old results (particularly cossweep) that may not reflect the current mach number
foreach (float aoadeg in exportdata.AoADegreeList)
{
input.alpha = aoadeg;
_instantCondition.GetClCdCmSteady(input, out output, true, true);
exportdata.AddDatapoint(mach, aoadeg, output.Cl, output.Cd, output.Cm);
}
}
exportdata.Export();
return(exportdata.DataCount);
}
public StabilityDerivExportOutput CalculateStabilityDerivs(CelestialBody body, double alt, double machNumber, int flapSetting, bool spoilers, double beta, double phi)
{
double pressure = body.GetPressure(alt);
double temperature = body.GetTemperature(alt);
double density = body.GetDensity(pressure, temperature);
double sspeed = body.GetSpeedOfSound(pressure, density);
double u0 = sspeed * machNumber;
double q = u0 * u0 * density * 0.5f;
Vector3d CoM;
double mass, area, MAC, b;
_instantCondition.GetCoMAndSize(out CoM, out mass, out area, out MAC, out b);
double effectiveG = _instantCondition.CalculateEffectiveGravity(body, alt, u0);
double neededCl = effectiveG * mass / (q * area);
InstantConditionSimVars iterationSimVars =
new InstantConditionSimVars(_instantCondition, body, alt, machNumber, neededCl, beta, phi, flapSetting, spoilers);
InstantConditionSimInput nominalInput;
InstantConditionSimOutput nominalOutput;
InstantConditionSimIterationResult stableCondition =
iterationSimVars.IterateForAlphaAndPitch(out nominalInput, out nominalOutput);
InstantConditionSimInput input = nominalInput.Clone();
InstantConditionSimOutput pertOutput;
double[] derivatives = new double[27];
// update size (in practice MAC and b) to match stableCondition
_instantCondition.GetCoMAndSize(out CoM, out mass, out area, out MAC, out b);
double Ix, Iy, Iz;
double Ixy, Iyz, Ixz;
_instantCondition.GetInertia(CoM, out Ix, out Iy, out Iz, out Ixy, out Iyz, out Ixz);
input.alpha = stableCondition.stableAoA + 2;
iterationSimVars.ResetAndGetClCdCmSteady(input, out pertOutput);
// Rodhern: A change is made to the Xw formula. Theoretically doing " -= nominalOutput.Cl" is the most 'correct',
// it does however in some way mix the Cd value measured at 'stableAoA + 2' with a Cl value measured at 'StableAoA'.
// Because Cl and Cd are very AoA-dependent, the asymmetrical measurement (AoA+=[0;2]) is quite affected.
double pertOutCl = pertOutput.Cl;
pertOutput.Cl = (pertOutput.Cl - nominalOutput.Cl) / (2 * FARMathUtil.deg2rad); //vert vel derivs
pertOutput.Cd = (pertOutput.Cd - nominalOutput.Cd) / (2 * FARMathUtil.deg2rad);
pertOutput.Cm = (pertOutput.Cm - nominalOutput.Cm) / (2 * FARMathUtil.deg2rad);
pertOutput.Cl += nominalOutput.Cd;
pertOutput.Cd -= pertOutCl; // Rodhern: Convergence is worse, but possibly the numerical value is more useful this way.
pertOutput.Cl *= -q * area / (mass * u0);
pertOutput.Cd *= -q * area / (mass * u0);
pertOutput.Cm *= q * area * MAC / (Iy * u0);
derivatives[3] = pertOutput.Cl; //Zw
derivatives[4] = pertOutput.Cd; //Xw
derivatives[5] = pertOutput.Cm; //Mw
input.alpha = stableCondition.stableAoA;
input.fltenv.MachNumber = machNumber + 0.05;
iterationSimVars.ResetAndGetClCdCmSteady(input, out pertOutput);
pertOutput.Cl = (pertOutput.Cl - nominalOutput.Cl) / 0.05 * machNumber; //fwd vel derivs
pertOutput.Cd = (pertOutput.Cd - nominalOutput.Cd) / 0.05 * machNumber;
pertOutput.Cm = (pertOutput.Cm - nominalOutput.Cm) / 0.05 * machNumber;
pertOutput.Cl += 2 * nominalOutput.Cl;
pertOutput.Cd += 2 * nominalOutput.Cd;
pertOutput.Cm += 2 * nominalOutput.Cm;
pertOutput.Cl *= -q * area / (mass * u0);
pertOutput.Cd *= -q * area / (mass * u0);
pertOutput.Cm *= q * area * MAC / (Iy * u0);
derivatives[6] = pertOutput.Cl; //Zu
derivatives[7] = pertOutput.Cd; //Xu
derivatives[8] = pertOutput.Cm; //Mu
input.fltenv.MachNumber = machNumber;
input.alphaDot = -3;
iterationSimVars.ResetAndGetClCdCmSteady(input, out pertOutput);
pertOutput.Cl = (pertOutput.Cl - nominalOutput.Cl) / (3 * FARMathUtil.deg2rad); //pitch rate derivs
pertOutput.Cd = (pertOutput.Cd - nominalOutput.Cd) / (3 * FARMathUtil.deg2rad);
pertOutput.Cm = (pertOutput.Cm - nominalOutput.Cm) / (3 * FARMathUtil.deg2rad);
pertOutput.Cl *= -q * area / mass;
pertOutput.Cd *= -q * area / mass;
pertOutput.Cm *= q * area * MAC / Iy;
derivatives[9] = pertOutput.Cl; //Zq
derivatives[10] = pertOutput.Cd; //Xq
derivatives[11] = pertOutput.Cm; //Mq
input.alphaDot = 0;
double pitchDelta = (stableCondition.stablePitchValue > 0) ? -0.1 : 0.1;
input.pitchValue = stableCondition.stablePitchValue + pitchDelta;
iterationSimVars.ResetAndGetClCdCmSteady(input, out pertOutput);
pertOutput.Cl = (pertOutput.Cl - nominalOutput.Cl) / pitchDelta; //elevator derivs
pertOutput.Cd = (pertOutput.Cd - nominalOutput.Cd) / pitchDelta;
pertOutput.Cm = (pertOutput.Cm - nominalOutput.Cm) / pitchDelta;
pertOutput.Cl *= -q * area / mass; // Rodhern: Replaced 'q' by '-q', so that formulas
pertOutput.Cd *= -q * area / mass; // for Ze and Xe match those for Zu and Xu.
pertOutput.Cm *= q * area * MAC / Iy;
derivatives[12] = pertOutput.Cl; //Ze
derivatives[13] = pertOutput.Cd; //Xe
derivatives[14] = pertOutput.Cm; //Me
input.pitchValue = stableCondition.stablePitchValue;
input.beta = (beta + 2);
iterationSimVars.ResetAndGetClCdCmSteady(input, out pertOutput);
pertOutput.Cy = (pertOutput.Cy - nominalOutput.Cy) / (2 * FARMathUtil.deg2rad); //sideslip angle derivs
pertOutput.Cn = (pertOutput.Cn - nominalOutput.Cn) / (2 * FARMathUtil.deg2rad);
pertOutput.C_roll = (pertOutput.C_roll - nominalOutput.C_roll) / (2 * FARMathUtil.deg2rad);
pertOutput.Cy *= q * area / mass;
pertOutput.Cn *= q * area * b / Iz;
pertOutput.C_roll *= q * area * b / Ix;
derivatives[15] = pertOutput.Cy; //Yb
derivatives[17] = pertOutput.Cn; //Nb
derivatives[16] = pertOutput.C_roll; //Lb
input.beta = beta;
input.phiDot = -3;
iterationSimVars.ResetAndGetClCdCmSteady(input, out pertOutput);
pertOutput.Cy = (pertOutput.Cy - nominalOutput.Cy) / (3 * FARMathUtil.deg2rad); //roll rate derivs
pertOutput.Cn = (pertOutput.Cn - nominalOutput.Cn) / (3 * FARMathUtil.deg2rad);
pertOutput.C_roll = (pertOutput.C_roll - nominalOutput.C_roll) / (3 * FARMathUtil.deg2rad);
pertOutput.Cy *= q * area / mass;
pertOutput.Cn *= q * area * b / Iz;
pertOutput.C_roll *= q * area * b / Ix;
derivatives[18] = pertOutput.Cy; //Yp
derivatives[20] = pertOutput.Cn; //Np
derivatives[19] = pertOutput.C_roll; //Lp
input.phiDot = 0;
input.betaDot = -3;
iterationSimVars.ResetAndGetClCdCmSteady(input, out pertOutput);
pertOutput.Cy = (pertOutput.Cy - nominalOutput.Cy) / (3 * FARMathUtil.deg2rad); //yaw rate derivs
pertOutput.Cn = (pertOutput.Cn - nominalOutput.Cn) / (3 * FARMathUtil.deg2rad);
pertOutput.C_roll = (pertOutput.C_roll - nominalOutput.C_roll) / (3 * FARMathUtil.deg2rad);
pertOutput.Cy *= q * area / mass;
pertOutput.Cn *= q * area * b / Iz;
pertOutput.C_roll *= q * area * b / Ix;
derivatives[21] = pertOutput.Cy; //Yr
derivatives[23] = pertOutput.Cn; //Nr
derivatives[22] = pertOutput.C_roll; //Lr
input = new InstantConditionSimInput(body); // Reset to (an artificial) default condition
_instantCondition.ResetClCdCmSteady(CoM, input);
// Assign values to output variables
StabilityDerivOutput stabDerivOutput = new StabilityDerivOutput(stableCondition, derivatives);
stabDerivOutput.nominalVelocity = u0;
stabDerivOutput.altitude = alt;
stabDerivOutput.body = body;
stabDerivOutput.b = b;
stabDerivOutput.MAC = MAC;
stabDerivOutput.area = area;
stabDerivOutput.stabDerivs[0] = Ix;
stabDerivOutput.stabDerivs[1] = Iy;
stabDerivOutput.stabDerivs[2] = Iz;
stabDerivOutput.stabDerivs[24] = Ixy;
stabDerivOutput.stabDerivs[25] = Iyz;
stabDerivOutput.stabDerivs[26] = Ixz;
// Assign values to export variables
StabilityDerivExportVariables stabDerivExport = new StabilityDerivExportVariables();
stabDerivExport.craftmass = mass;
stabDerivExport.envpressure = pressure;
stabDerivExport.envtemperature = temperature;
stabDerivExport.envdensity = density;
stabDerivExport.envsoundspeed = sspeed;
stabDerivExport.envg = _instantCondition.CalculateAccelerationDueToGravity(body, alt);
stabDerivExport.sitmach = machNumber;
stabDerivExport.sitdynpres = q;
stabDerivExport.siteffg = _instantCondition.CalculateEffectiveGravity(body, alt, u0);
return(new StabilityDerivExportOutput(stabDerivOutput, stabDerivExport));
}
public void ResetAndGetClCdCmSteady(InstantConditionSimInput input, out InstantConditionSimOutput output)
{
parent.ResetClCdCmSteady(CoM, input);
parent.GetClCdCmSteady(input, out output, true, false);
}
