Implement atmosphere and dynamics data

code/T3dxdt.m

@@ -1,23 +1,24 @@
 function TxDot =  T3dxdt(t,x)
 %% Threat is a 240 mm Rocket
 % Compute Rocket xDot = [velocity; acceleration]'
-g = 9.8066; % acceleration due to gravity
-gravity = [0; 0; -g]; % gravity vector
-diameter = 0.24; % missile diameter in m.
-S = XX; % reference area in m^2
-[acousticSpeed,rho] = getRho(x);
-mach = norm(x(4:6))/acousticSpeed;
-
-timeCurve = [XX]';  %seconds
-thrustCurve = [XX]'; % Newtons
-
-massCurve = [XX]'; % kg
-
-machCurve = [XX];
-dragCurve = [XX];
-
-machCurveB = [XX];
-dragCurveB = [XX];
+g = 9.8066; % acceleration due to gravity
+gravity = [0; 0; -g]; % gravity vector
+diameter = 0.24; % missile diameter in m.
+S = pi*(diameter/2)^2; % reference area in m^2
+[acousticSpeed,rho] = getRho(x);
+mach = norm(x(4:6))/acousticSpeed;
+
+% Transcribed from the provided target-data plots.
+timeCurve = [0 7.5 7.5001 45]';  %seconds
+thrustCurve = [77000 77000 0 0]'; % Newtons
+
+massCurve = [410 210 210 210]'; % kg
+
+machCurve = [0 0.5 0.7 0.9 1.0 1.1 1.2 1.3 1.5 2.0 2.5 3.0 3.5 4.0];
+dragCurve = [0.40 0.40 0.43 0.60 0.75 0.87 0.86 0.80 0.74 0.60 0.50 0.44 0.40 0.39];
+
+machCurveB = [0 0.5 0.7 0.9 1.0 1.1 1.2 1.3 1.5 2.0 2.5 3.0 3.5 4.0];
+dragCurveB = [0.31 0.31 0.34 0.47 0.62 0.78 0.77 0.72 0.64 0.50 0.40 0.34 0.30 0.27];
 
 if(t<=timeCurve(end-1))
     Cd = interp1(machCurveB,dragCurveB,mach,'linear','extrap');