Initialize Hayden project repository

code/M3dxdt.m

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+function MxDot =  M3dxdt(Mt,missileState,targetState)
+%% Missile is a 120 mm Rocket with an IR Seeker
+% Compute Missile xDot = [velocity; acceleration]'
+g = 9.8066; % acceleration due to gravity
+gravity = [0; 0; -g]; % gravity vector
+diameter = 0.120; % missile diameter in m.
+S = XX; % reference area in m^2
+[acousticSpeed,rho] = getRho(missileState);
+Mspeed = norm(missileState(4:6));
+mach = Mspeed/acousticSpeed;
+timeCurve = [XX]';  %seconds
+thrustCurve = [XX]'; % Newtons
+massCurve = [XX]'; % kg
+
+machCurve = [XX];
+dragCurve = [XX];
+
+machCurveB = [XX];
+dragCurveB = [XX];
+
+if(Mt<=timeCurve(end-1))
+    Cd = interp1(machCurveB,dragCurveB,mach,'linear','extrap');
+else
+    Cd = interp1(machCurve,dragCurve,mach,'linear','extrap');
+end
+mass = interp1(timeCurve,massCurve,Mt,'linear','extrap');
+thrust = interp1(timeCurve,thrustCurve,Mt,'linear','extrap');
+%Compute acceleration --------------------------------------------
+if Mspeed<=20
+    step = 0;
+else
+    step = 1;
+end
+dragAccel = -0.5*rho*Cd*S*missileState(4:6)*norm(missileState(4:6))/mass;% drag acceleration in m/sec^2
+thrustAccel = thrust*missileState(4:6)/(mass*(norm(missileState(4:6))));
+guideAccel = getGuidance(Mt,missileState,targetState);
+accel = dragAccel + thrustAccel + gravity*step + guideAccel; % total acceleration
+MxDot = [missileState(4:6);accel];
+end