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block Wind6DOFBlock
import Modelica.Math.Matrices.*;
import SI=Modelica.SIunits;
import Modelica.Blocks.Interfaces.*;
parameter Real rho = 1.225;
parameter Real g = 9.81;
parameter Real m = 1043.26;//1.56 for zagi
parameter Real S_ref = 16.1651;//reference area
parameter Real C_bar = 1.493 ;//average chord
parameter Real b = 10.911 ;//span
//parameter Real b= 1.4224, cbar = 0.3302,s = 0.2589;
parameter Real CD0 = 0.036;//= 0.01631;for Zagi
parameter Real K_drag = 0.0830304;//for cessna
parameter Real CD_beta = 0.17;//for cessna
parameter Real CD_alpha= 0.2108;
parameter Real CD_q = 0;
parameter Real CD_delta_e= 0.3045;
//side force
parameter Real Cy_beta = -0.31;//for cessna
parameter Real Cy_p = -0.037;//for cessna
parameter Real Cy_r = 0.21;//for cessna
parameter Real Cy_delta_r = 0.187; //for cessna
parameter Real Cy_delta_a= 0; //for cessna
// lift
parameter Real CL0 = 0.25; //for cessna
parameter Real CL_alpha = 4.47;//for cessna
parameter Real CL_q = 3.9;//for cessna
parameter Real CL_delta_e = 0.3476;//for cessna
// rolling moment
parameter Real Cl_beta = -0.089;//for cessna
parameter Real Cl_p = -0.47;//for cessna
parameter Real Cl_r = 0.096;//for cessna
parameter Real Cl_delta_a= -0.09;//for cessna
parameter Real Cl_delta_r = 0.0147;//for cessna
// pitching moment
parameter Real Cm0 = -0.02;//for cessna
parameter Real Cm_alpha = -1.8;//for cessna
parameter Real Cm_q = -12.4;//for cessna
parameter Real Cm_delta_e = -1.28;//for cessna
// yawing moment
parameter Real Cn_beta = 0.065;//for cessna
parameter Real Cn_p = -0.03;//for cessna
parameter Real Cn_r = -0.99;//for cessna
parameter Real Cn_delta_a = -0.0053;//for cessna
parameter Real Cn_delta_r = -0.0657;//for cessna
//Initial conditions. (deltaE, thrust[1] and the others are straightforward)
parameter Real[3,3] J = {{1285.31, 0.0, 0.0}, {0.0, 1824.93, 0.0}, {0.0, 0.0, 2666.893}};
Real CL;
Real CD;
Real CY;
Real Cl;
Real Cm;
Real Cn;
Real CX;
Real CZ;
//Params
RealInput deltaE (start = -0.15625) annotation(start = 0.1,Placement(visible = true, transformation(origin = {-110, -33}, extent = {{-20, -20}, {20, 20}}, rotation = 0), iconTransformation(origin = {-110, -33}, extent = {{-20, -20}, {20, 20}}, rotation = 0)));
//Change inelevator angle
parameter Real deltaR = 0;
parameter Real deltaA= 0;
RealInput thrust (start = 1112.82) annotation(Placement(visible = true, transformation(origin = {-110, 33}, extent = {{-20, -20}, {20, 20}}, rotation = 0), iconTransformation(origin = {-110, 33}, extent = {{-20, -20}, {20, 20}}, rotation = 0)));//Thrust force = 1112.82;
//12 states
Real p (start = 0);
Modelica.Blocks.Interfaces.RealOutput q (start = 0) annotation(Placement(visible = true, transformation(origin = {110, 33}, extent = {{-10, -10}, {10, 10}}, rotation = 0), iconTransformation(origin = {110, 33}, extent = {{-10, -10}, {10, 10}}, rotation = 0))); //Angular velocity
Real r (start = 0);
Real OMEGA[3,3] = skew({p,q,r});//Skew symmetric matrix form of the angular velocity term
Real V (start =39.8858);
Modelica.Blocks.Interfaces.RealOutput alpha (start = 0.1) annotation( Placement(visible = true, transformation(origin = {110, -33}, extent = {{-10, -10}, {10, 10}}, rotation = 0), iconTransformation(origin = {110, -33}, extent = {{-10, -10}, {10, 10}}, rotation = 0))); //Angle of attack
Real beta (start = 0);
Real x (start = 0);
Real y (start = 0);
Real z (start = 100);
Real gamma (start = 0);
Real chi (start = 0);
Real mu (start = 0);
Real qbar = 0.5*rho*V^2;
Real [3] Moment;
Real Vdot;
Real alphadot;
Real betadot;
Real[3] omegadot;
Real mudot;
Real gammadot;
Real chidot;
Real xdot;
Real ydot;
Real zdot;
equation
CL = CL0+CL_alpha*alpha+((CL_q*q*C_bar)/(2*V))+CL_delta_e*deltaE;
//CD = CD0+CD_alpha*alpha+((CD_q*q*C_bar)/(2*V))+CD_delta_e*abs(deltaE) ;
CD = CD0 + K_drag*CL^2;
CY = Cy_beta * beta + Cy_p * (p*b)/(2*V) + Cy_r *(r*b)/(2*V) + Cy_delta_a * deltaA + Cy_delta_r*deltaR;//Sideslip coeff
Cl = Cl_beta * beta + Cl_p*(p*b)/(2*V) + Cl_r *(r*b)/(2*V) + Cl_delta_a * deltaA + Cl_delta_r * deltaR;//Rolling coeff
Cm = Cm0+Cm_alpha*alpha+((Cm_q*q*C_bar)/(2*V))+Cm_delta_e*deltaE;//pitching coeff
Cn = Cn_beta * beta + Cn_p * (p*b)/(2*V) + Cn_r *(r*b) /(2*V) + Cn_delta_a * deltaA + Cn_delta_r * deltaR;//Yawing coeff
CX = -CD*cos(alpha) + CL*sin(alpha);
CZ = -CD*sin(alpha) - CL*cos(alpha);
Moment[2] = Cm*qbar*S_ref*C_bar;
Moment[1] = Cl*qbar*S_ref*b;
Moment[3] = Cn*qbar*S_ref*b;
Vdot = der(V);
alphadot = der(alpha);
betadot = der(beta);
omegadot[1] = der(p);
omegadot[2] = der(q);
omegadot[3] = der(r);
xdot = der(x);
ydot = der(y);
zdot = der(z);
mudot = der(mu);
gammadot = der(gamma);
chidot = der(chi);
Vdot = 1/m*(thrust*cos(alpha)*cos(beta)-0.5*rho*V^2*S_ref*(CD*cos(beta)-CY*sin(beta))-m*g*sin(gamma));
alphadot = q-1/cos(beta)*((p*cos(alpha)+r*sin(alpha))*sin(beta)-g/V*cos(gamma)*cos(mu)+0.5*rho*V^2*S_ref*CL/(m*V)+thrust*sin(alpha)/(m*V));
betadot = (p*sin(alpha)-r*cos(alpha))+1/(m*V)*(-thrust*cos(alpha)*sin(beta)+0.5*rho*V^2*S_ref*(CY*cos(beta)+CD*sin(beta))+m*g*cos(gamma)*sin(mu));
omegadot = inv(J) * (Moment- OMEGA* J*{p,q,r});
xdot=V*cos(gamma)*cos(chi);
ydot=V*cos(gamma)*sin(chi);
zdot=-V*sin(gamma);
mudot = p+tan(gamma)*sin(mu)*q+tan(gamma)*cos(mu)*r;
gammadot = cos(mu)*q-sin(mu)*r;
chidot=(1/cos(gamma))*sin(mu)*q+(1/cos(gamma))*cos(mu)*r;
annotation(experiment(StartTime = 0, StopTime = 500, Interval = 0.002),
uses(Modelica(version = "3.2.2")));
end Wind6DOFBlock;
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