//}
//void Atmosphere::SetContrails (FP contraillevel)
//{
// Sky.ContrailBandCentre = contraillevel;
//}
void Atmosphere::SetMissionWind (SWord month)
{
FP pie;
pie = 3.14159265359;
FP delta;
delta = month - 6;
if (delta < 0)
delta = - delta;
if (delta < 3)
{
//Summer
wind0 = Math_Lib.rnd (6);
dir0 = 135 + Math_Lib.rnd (45);
windalt = 80 + Math_Lib.rnd (45);
diralt = 45 + Math_Lib.rnd (90);
}
else
{
wind0 = Math_Lib.rnd (10);
dir0 = 225 + Math_Lib.rnd (90);
windalt = 100 + Math_Lib.rnd (75);
diralt = 270 + Math_Lib.rnd (45);
}
//calc wind as vector
//wind0 and windalt are in knots, the x,yz vectors are in m/s
FP dir = (180 + dir0) * pie * 2 / 360;
FP cos = FCos(dir);
FP sin = FSin(dir);
Wind0.x = wind0 * sin * 0.514; //RDH 02/05/99
Wind0.y = 0;
Wind0.z = wind0 * cos * 0.514; //RDH 02/05/99
dir = (180 + diralt) * pie * 2 / 360;
cos = FCos(dir);
sin = FSin(dir);
WindAlt.x = windalt * sin * 0.514; //RDH 02/05/99
WindAlt.y = 0;
WindAlt.z = windalt * cos * 0.514; //RDH 02/05/99
WindAltHeight = WIND_DIRECTION_CHANGE; //always as 35,000ft for MA
//##calc as f(date)
delta = TempVar;
if (delta < 0)
delta = -delta;
Frequency = 65535 - 26 * delta; // 0 = always, 65535 = very infrequent
MaxMagnitude = delta;
MinMagnitude = 0; // 1 = 1 m/s
MaxDuration = 500;
MinDuration = 250; // csecs
}
void Atmosphere::SetMissionPress (SWord month)
{
FP delta;
delta = month - 6;
if (delta < 0)
delta = - delta;
if (delta < 3)
{//Summer
Press0 = 1001 + TempVar;
}else
{
Press0 = 999 - TempVar;
}
//DeadCode CSB 10/06/99 ContrailBandCentre = FEET2CM(1000 * (40 - delta + Math_Lib.rnd (2)));
//DeadCode CSB 10/06/99 int band = Math_Lib.rnd (5) + 3;
//DEADCODE RDH 19/05/99 if (Math_Lib.rnd (2))
//DEADCODE RDH 19/05/99 band = -band;
//DeadCode CSB 10/06/99 ContrailBandWidth = FEET2CM(1000 * band);
//DEADCODE RDH 19/05/99 screenshots ContrailBandWidth = FEET2CM(10000 * band);//csb
ContrailBandCentre = FEET2CM(32000); //CSB 10/06/99
ContrailBandWidth = FEET2CM(4000); //CSB 10/06/99
FP ChanceBad = 0.5 + 0.5 * FCos(month * 6.2831853 / 12.0); //CSB 02/07/99
ChanceBad = 819.2 + 8192.0 * ChanceBad; //CSB 02/07/99
if(Math_Lib.rnd() > ChanceBad) //CSB 02/07/99
//DeadCode CSB 02/07/99 if (Press0 > 1000)
{
Conditions = 0;
Visibility = 4000000;
}
else
{
Visibility = 4000000; //##lower vis possible here
if (Temp0 < 273)
Conditions = 2;
else
Conditions = 1;
}
if ( (Press0 < 980)
&& (MMC.currtime < HR09)
)
MistInValley = true;
else
MistInValley = false;
//this will be a function of temp and press
CloudLayer = 457200;
}
//컴컴컴컴컴컴컴컴컴컴컴컴컴컴컴컴컴컴컴컴컴컴컴컴컴컴컴컴컴컴컴컴컴컴컴컴컴컴컴
//Procedure DerivativeBase
//Author Andrew McRae
//Date Tue 17 Jun 1997
//
//Description Used to calibrate model with linearized
// stability derivatives
//
// This model is aerodynamically accurate
// for small disturbances from level flight.
//
//Inputs
//
//Returns
//
//------------------------------------------------------------------------------
void Model::DerivativeBase ()
{
/*
Stability Derivatives
Forces X,Y,Z
Moments L,M,N
Velocity u,v,w
Angular Velocity p,q,r
Roll, Pitch, Yaw inputs a,b,c
Downward Acceleration wd (za)
(r = density)
(everything has 0.5)
Forces Moments
Forward Stbd Down Roll Pitch Yaw
Xu rVS Yu ... Zu rVS Lu ... Mu rVSc Nu ...
Xv ... Yv rVS Zv ... Lv rVSb Mv ... Nv rVSb
Xw rVS Yw ... Zw rVS Lw ... Mw rVSc Nw ...
Xp ... Yp rVSb Zp ... Lp rVSb2 Mp ... Np rVSb2
Xq rVSc Yq ... Zq rVSc Lq ... Mq rVSc2 Nq ...
Xr ... Yr rVSb Zr ... Lr rVSb2 Mr ... Nr rVSb2
Xa ... Ya rV2S Za ... La rV2Sb Ma ... Na rV2Sb
Xb rV2S Yb ... Zb rV2S Lb ... Mb rV2Sc Nb ...
Xc ... Yc rV2S Zc ... Lc rV2Sb Mc ... Nc rV2Sb
Xwd rSc Ywd ... Zwd rSc Lwd ... Mwd rSc2 Nwd ...
*/
typedef struct vel { FP u,v,w; } VEL;
typedef struct rotvel { FP p,q,r; } ROTVEL;
typedef struct ctrl { FP a,b,c; } CTRL;
typedef struct acc { FP ud,vd,wd; } ACC;
typedef struct veldervs { VEL X,Y,Z,L,M,N; } VELDERVS;
typedef struct rotveldervs { ROTVEL X,Y,Z,L,M,N; } ROTVELDERVS;
typedef struct ctrldervs { CTRL X,Y,Z,L,M,N; } CTRLDERVS;
typedef struct accdervs { ACC X,Y,Z,L,M,N; } ACCDERVS;
VELDERVS V;
ROTVELDERVS RV;
CTRLDERVS C;
ACCDERVS A;
//DeadCode AMM 24Nov99 MODEL_DT = 3;
MODEL_LOOPS = 1;
static Bool setup = TRUE;
FP testalpha = -Degs2Rads ((FP)Elevator / 3000);
if (testalpha > DEGS2RADS(10)) testalpha = DEGS2RADS(10);
if (testalpha < DEGS2RADS(-10)) testalpha = DEGS2RADS(-10);
if (setup)
{
// temp
Pos.y = FT_3000;
Vel.x = 0;
Vel.y = 0;
Vel.z = 150;
Ori.x.x = 1;
Ori.x.y = 0;
Ori.x.z = 0;
Ori.y.x = 0;
Ori.y.y = 1;
Ori.y.z = 0;
Ori.z.x = 0;
Ori.z.y = 0;
Ori.z.z = 1;
// RotOriXVec (Ori, testalpha);
// RotOriXVec (Ori, DEGS2RADS(5));
RotOriYVec (Ori, DEGS2RADS(10));
RotVel.x = 0;
RotVel.y = 0;
RotVel.z = 0;
RotVel.y = 0.00105; // 1 rpm
RotVel.z = -0.00105;
// temp end
setup = FALSE;
}
// UpdateAirStruc ();
Sky.Ambient (Pos.y, AmbDensity, AmbTemp, AmbPres);
CalcAirVel ();
GearTouched = FALSE;
// Set Mass and Rot Inertia
Mass = 0;
NullVec (RotInertia);
PMODEL pModel = ControlledAC->fly.pModel;
PMASSPOINT pMass = MassList;
while (pMass != NULL)
{
pMass->Process (pModel);
pMass = pMass->List.NextItem ();
}
// ProcessEngines ();
Mass = 617415;
RotInertia.x = 1.49534e10;
RotInertia.y = 3.59877e10;
RotInertia.z = 4.98958e10;
// WORK IN STANDARD UNITS
// Calc Derivative Mutipliers
FP B = (MainPlaneList->Area / MainPlaneList->Chord) * 0.01;
FP Ch = MainPlaneList->Chord * 0.01;
FP rS = 0.5 * (AmbDensity * 10000) * (MainPlaneList->Area * 0.0001);
FP rVS = rS * AirSpeed;
FP rVSb = rVS * B;
FP rVSc = rVS * Ch;
FP rVSb2 = rVSb * B;
FP rVSc2 = rVSc * Ch;
FP rV2S = rVS * AirSpeed;
FP rV2Sb = rV2S * B;
FP rV2Sc = rV2S * Ch;
FP rSc = rS * Ch;
FP rSc2 = rSc * Ch;
// Get derivative inputs
// Velocities
FP u = -AirVel.z;
FP v = -AirVel.x;
FP w = AirVel.y;
// Rotational velocities
FP p = RotVel.z * 100;
FP q = RotVel.x * 100;
FP r = -RotVel.y * 100;
// Calc Control inputs
FP a = -((FP)Aileron * F2PIE * 20) / (32768 * 360);
FP b = ((FP)Elevator * F2PIE * 20) / (32768 * 360);
FP c = -((FP)Rudder * F2PIE * 20) / (32768 * 360);
// Acceleration
FP ud = 0;
FP vd = 0;
FP wd = 0;
// Calc alpha
FP alpha = CalcAngle (VecLen2D (u,v), w);
if (alpha > DEGS2RADS(180)) alpha -= DEGS2RADS(360);
alpha += DEGS2RADS (3);
// alpha = testalpha;
// if (alpha > DEGS2RADS(10)) alpha = DEGS2RADS(10);
// if (alpha < DEGS2RADS(-10)) alpha = DEGS2RADS(-10);
FP Sin = FSin (alpha);
FP Cos = FCos (alpha);
// Calc Cl, Cd
FP Cl = alpha * 5.27;
FP Cd = alpha * 0.29;
#ifdef PRINT_DERV_DATA
PrintVar (30, 16, "alp %.2f ", Rads2Degs(alpha));
PrintVar (45, 16, "Cl %.2f ", Cl);
PrintVar (60, 16, "Cd %.2f ", Cd);
PrintVar (30, 18, "u %.4f ", u);
PrintVar (45, 18, "v %.4f ", v);
PrintVar (60, 18, "w %.4f ", w);
PrintVar (30, 19, "p %.4f ", p);
PrintVar (45, 19, "q %.4f ", q);
PrintVar (60, 19, "r %.4f ", r);
#endif
// Force Velocity dervs
V.X.u = -Cd * u * rVS; V.Y.u = 0 * u * rVS; V.Z.u = -Cl * u * rVS;
V.X.v = 0 * v * rVS; V.Y.v = -0.546 * v * rVS; V.Z.v = 0 * v * rVS;
V.X.w = Cl * w * rVS; V.Y.w = 0 * w * rVS; V.Z.w = -Cd * w * rVS;
// Moment Velocity dervs
V.L.u = 0 * u * rVSb; V.M.u = 0 * u * rVSc; V.N.u = 0 * u * rVSb;
V.L.v = -0.0654 * v * rVSb; V.M.v = 0 * v * rVSc; V.N.v = 0.118 * v * rVSb;
V.L.w = 0 * w * rVSb; V.M.w = -0.44 * w * rVSc; V.N.w = 0 * w * rVSb;
// *****************
// * V.M.w is iffy *
// *****************
// Force RotVel dervs
RV.X.p = 0; RV.Y.p = 0 * p * rVSb; RV.Z.p = 0;
RV.X.q = 0 * q * rVSc; RV.Y.q = 0; RV.Z.q = 0 * q * rVSc;
RV.X.r = 0; RV.Y.r = 0.1435 * r * rVSb; RV.Z.r = 0;
// Moment RotVel dervs
RV.L.p = -0.195 * p * rVSb2; RV.M.p = 0; RV.N.p = -0.008 * p * rVSb2;
RV.L.q = 0; RV.M.q = -0.032 * q * rVSc2; RV.N.q = 0;
RV.L.r = 0.0575 * r * rVSb2; RV.M.r = 0; RV.N.r = -0.067 * r * rVSb2;
// Check M.q (c/2U ?????)
// Force Control dervs
C.X.a = 0; C.Y.a = 0 * a * rV2S; C.Z.a = 0;
C.X.b = 0.43 * Sin * b * rV2S; C.Y.b = 0; C.Z.b = 0.43 * b * Cos * rV2S;
C.X.c = 0; C.Y.c = 0.149 * c * rV2S; C.Z.c = 0;
// Moment Control dervs
C.L.a = -0.114 * a * rV2Sb; C.M.a = 0; C.N.a = 0.009 * a * rV2Sb;
C.L.b = 0; C.M.b = -0.934 * b * rV2Sc; C.N.b = 0;
C.L.c = 0.0057 * c * rV2Sb; C.M.c = 0; C.N.c = -0.069 * c * rV2Sb;
// Z Acc dervs
// use Cm alpha dot in F94A derv tables
#ifdef PRINT_DERV_DATA
PrintVar (30, 0, "V.X.u %.0f ", V.X.u);
PrintVar (45, 0, "V.Y.u %.0f ", V.Y.u);
PrintVar (60, 0, "V.Z.u %.0f ", V.Z.u);
PrintVar (30, 1, "V.X.v %.0f ", V.X.v);
PrintVar (45, 1, "V.Y.v %.0f ", V.Y.v);
PrintVar (60, 1, "V.Z.v %.0f ", V.Z.v);
PrintVar (30, 2, "V.X.w %.0f ", V.X.w);
PrintVar (45, 2, "V.Y.w %.0f ", V.Y.w);
PrintVar (60, 2, "V.Z.w %.0f ", V.Z.w);
PrintVar (30, 4, "V.L.u %.0f ", V.L.u);
PrintVar (45, 4, "V.M.u %.0f ", V.M.u);
PrintVar (60, 4, "V.N.u %.0f ", V.N.u);
PrintVar (30, 5, "V.L.v %.0f ", V.L.v);
PrintVar (45, 5, "V.M.v %.0f ", V.M.v);
PrintVar (60, 5, "V.N.v %.0f ", V.N.v);
PrintVar (30, 6, "V.L.w %.0f ", V.L.w);
PrintVar (45, 6, "V.M.w %.0f ", V.M.w);
PrintVar (60, 6, "V.N.w %.0f ", V.N.w);
PrintVar (30, 8, "RV.X.p %.0f ", RV.X.p);
PrintVar (45, 8, "RV.Y.p %.0f ", RV.Y.p);
PrintVar (60, 8, "RV.Z.p %.0f ", RV.Z.p);
PrintVar (30, 9, "RV.X.q %.0f ", RV.X.q);
PrintVar (45, 9, "RV.Y.q %.0f ", RV.Y.q);
PrintVar (60, 9, "RV.Z.q %.0f ", RV.Z.q);
PrintVar (30, 10, "RV.X.r %.0f ", RV.X.r);
PrintVar (45, 10, "RV.Y.r %.0f ", RV.Y.r);
PrintVar (60, 10, "RV.Z.r %.0f ", RV.Z.r);
PrintVar (30, 12, "RV.L.p %.0f ", RV.L.p);
PrintVar (45, 12, "RV.M.p %.0f ", RV.M.p);
PrintVar (60, 12, "RV.N.p %.0f ", RV.N.p);
PrintVar (30, 13, "RV.L.q %.0f ", RV.L.q);
PrintVar (45, 13, "RV.M.q %.0f ", RV.M.q);
PrintVar (60, 13, "RV.N.q %.0f ", RV.N.q);
PrintVar (30, 14, "RV.L.r %.0f ", RV.L.r);
PrintVar (45, 14, "RV.M.r %.0f ", RV.M.r);
PrintVar (60, 14, "RV.N.r %.0f ", RV.N.r);
#endif
// calc forces
FCRD force;
force.x = V.X.u + V.X.v + V.X.w + RV.X.p + RV.X.q + RV.X.r + C.X.a + C.X.b + C.X.c;
force.y = V.Y.u + V.Y.v + V.Y.w + RV.Y.p + RV.Y.q + RV.Y.r + C.Y.a + C.Y.b + C.Y.c;
force.z = V.Z.u + V.Z.v + V.Z.w + RV.Z.p + RV.Z.q + RV.Z.r + C.Z.a + C.Z.b + C.Z.c;
NettForce.x = force.y;
NettForce.y = -force.z;
NettForce.z = force.x;
// calc moments
FCRD moment;
moment.x = V.L.u + V.L.v + V.L.w + RV.L.p + RV.L.q + RV.L.r + C.L.a + C.L.b + C.L.c;
moment.y = V.M.u + V.M.v + V.M.w + RV.M.p + RV.M.q + RV.M.r + C.M.a + C.M.b + C.M.c;
moment.z = V.N.u + V.N.v + V.N.w + RV.N.p + RV.N.q + RV.N.r + C.N.a + C.N.b + C.N.c;
NettMoment.x = moment.y * 100;
NettMoment.y = -moment.z * 100;
NettMoment.z = moment.x * 100;
// Engines
PTHRUSTPOINT pThrust = ThrustList;
while (pThrust != NULL)
{
pThrust->Process ();
NettForce.x += pThrust->Force.x;
NettForce.y += pThrust->Force.y;
NettForce.z += pThrust->Force.z;
pThrust = pThrust->List.NextItem ();
}
MODLIMIT (NettForce.x, 600000);
MODLIMIT (NettForce.y, 2500000);
MODLIMIT (NettForce.z, 600000);
MODLIMIT (NettMoment.x, 250000000);
MODLIMIT (NettMoment.y, 250000000);
MODLIMIT (NettMoment.z, 250000000);
CalcAcc ();
//TempCode ARM 15Jul97 {
//TempCode ARM 15Jul97 OldAcc.x = Acc.x;
//TempCode ARM 15Jul97 OldAcc.y = Acc.y;
//TempCode ARM 15Jul97 OldAcc.z = Acc.z;
//TempCode ARM 15Jul97
//TempCode ARM 15Jul97 Acc.x = (NettForce.x / Mass);
//TempCode ARM 15Jul97 Acc.y = (NettForce.y / Mass);
//TempCode ARM 15Jul97 Acc.z = (NettForce.z / Mass);
//TempCode ARM 15Jul97 }
CalcRotAcc ();
//TempCode ARM 15Jul97 {
//TempCode ARM 15Jul97 OldRotAcc.x = RotAcc.x;
//TempCode ARM 15Jul97 OldRotAcc.y = RotAcc.y;
//TempCode ARM 15Jul97 OldRotAcc.z = RotAcc.z;
//TempCode ARM 15Jul97
//TempCode ARM 15Jul97 RotAcc.x = (NettMoment.x / RotInertia.x);
//TempCode ARM 15Jul97 RotAcc.y = (NettMoment.y / RotInertia.y);
//TempCode ARM 15Jul97 RotAcc.z = (NettMoment.z / RotInertia.z);
//TempCode ARM 15Jul97 }
TransInt (ALL);
//TempCode ARM 15Jul97 {
//TempCode ARM 15Jul97 FCRD acc;
//TempCode ARM 15Jul97
//TempCode ARM 15Jul97 acc.x = (OldAcc.x + Acc.x) * 0.5;
//TempCode ARM 15Jul97 acc.y = (OldAcc.y + Acc.y) * 0.5;
//TempCode ARM 15Jul97 acc.z = (OldAcc.z + Acc.z) * 0.5;
//TempCode ARM 15Jul97
//TempCode ARM 15Jul97 TnsPnt (acc, acc, Ori);
//TempCode ARM 15Jul97
//TempCode ARM 15Jul97 OldVel.x = Vel.x;
//TempCode ARM 15Jul97 OldVel.y = Vel.y;
//TempCode ARM 15Jul97 OldVel.z = Vel.z;
//TempCode ARM 15Jul97
//TempCode ARM 15Jul97 Vel.x += acc.x * MODEL_DT;
//TempCode ARM 15Jul97 Vel.y += (acc.y - GRAVITY) * MODEL_DT;
//TempCode ARM 15Jul97 Vel.z += acc.z * MODEL_DT;
//TempCode ARM 15Jul97
//TempCode ARM 15Jul97 OldPos.x = Pos.x;
//TempCode ARM 15Jul97 OldPos.y = Pos.y;
//TempCode ARM 15Jul97 OldPos.z = Pos.z;
//TempCode ARM 15Jul97
//TempCode ARM 15Jul97 Pos.x += ((OldVel.x + Vel.x) * MODEL_DT) * 0.5;
//TempCode ARM 15Jul97 Pos.y += ((OldVel.y + Vel.y) * MODEL_DT) * 0.5;
//TempCode ARM 15Jul97 Pos.z += ((OldVel.z + Vel.z) * MODEL_DT) * 0.5;
//TempCode ARM 15Jul97 }
RotInt (ALL);
//TempCode ARM 15Jul97 {
//TempCode ARM 15Jul97 OldRotVel.x = RotVel.x;
//TempCode ARM 15Jul97 OldRotVel.y = RotVel.y;
//TempCode ARM 15Jul97 OldRotVel.z = RotVel.z;
//TempCode ARM 15Jul97
//TempCode ARM 15Jul97 RotVel.x += ((OldRotAcc.x + RotAcc.x) * MODEL_DT) * 0.5;
//TempCode ARM 15Jul97 RotVel.y += ((OldRotAcc.y + RotAcc.y) * MODEL_DT) * 0.5;
//TempCode ARM 15Jul97 RotVel.z += ((OldRotAcc.z + RotAcc.z) * MODEL_DT) * 0.5;
//TempCode ARM 15Jul97
//TempCode ARM 15Jul97 RotVelInt ();
//TempCode ARM 15Jul97 }
// UpdateAirStruc ();
// Ground ();
// Instruments (ControlledAC);
}
