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matlabHelpers/polyFitTest.asv

@@ -0,0 +1,82 @@
+clear all; clc;
+%% Create Thrust Curve using Piecewise Function
+dt = 0.001;
+
+t1 = 0.148 : dt : 0.419;
+t2 = 0.420 : dt : 3.382;
+t3 = 3.383 : dt : 3.45;
+
+y1 = 65.165.*t1 - 2.3921;
+y2 = 0.8932*t2.^6 - 11.609*t2.^5 + 60.739*t2.^4 - 162.99*t2.^3 ...
+    + 235.6*t2.^2 - 174.43*t2 + 67.17;
+y3 = -195.78*t3 + 675.11;
+
+m = 1.2;
+
+a = [y1, y2, y3] ./ m;
+t = 0.148 : dt : 3.45;
+thrustCurve = [t', (a*m)'];
+
+%% Integrate
+v = 0;
+h = 0;
+g = -9.81;
+a = a + g;
+
+for i = 1 : length(a)
+    v = ((a(i)) * dt) + v;
+    h = v * dt + h;
+end
+
+h = h + ((v^2) / (2*-g))
+vb = v
+
+thrustFiring = 0;
+dt = 0.001;
+v = 0;
+j = 1;
+k = 1;
+t = 0;
+
+while 1
+    if abs(v + vb) < 0.01
+        thrustFiring = 1;
+        tb = 0;
+    end
+    
+    if thrustFiring == 0
+        v = g*dt + v;
+        h = v*dt + h;
+        a = g;
+    elseif thrustFiring == 1
+        if ((tb >= 0.148) && (tb <= 3.45))
+            v = v + a(j)*dt;
+            h = h + v*dt;
+            
+            disp(tb)
+            j = j + 1;
+        else
+            v = g*dt + v;
+            h = v*dt + h;
+        end
+        
+        tb = tb + dt;
+    end
+    accel(k) = a;
+    vz(k) = v;
+    z(k) = h;
+    time(k) = t;
+
+    t = t + dt;
+    k = k + 1;
+    if h < 0
+        break
+    end
+end
+
+figure(1)
+plot(time, z)
+figure(2)
+plot(time, vz)
+figure(3)
+plot(time, accel)

matlabHelpers/polyFitTest.m

@@ -0,0 +1,88 @@
+clear all; clc;
+%% Create Thrust Curve using Piecewise Function
+dt = 0.001;
+
+t1 = 0.148 : dt : 0.419;
+t2 = 0.420 : dt : 3.382;
+t3 = 3.383 : dt : 3.45;
+
+y1 = 65.165.*t1 - 2.3921;
+y2 = 0.8932*t2.^6 - 11.609*t2.^5 + 60.739*t2.^4 - 162.99*t2.^3 ...
+    + 235.6*t2.^2 - 174.43*t2 + 67.17;
+y3 = -195.78*t3 + 675.11;
+
+m = 1.2;
+
+a = [y1, y2, y3] ./ m;
+t = 0.148 : dt : 3.45;
+thrustCurve = [t', (a*m)'];
+
+%% Integrate
+v = 0;
+h = 0;
+g = -9.81;
+a = a + g;
+
+for i = 1 : length(a)
+    v = ((a(i)) * dt) + v;
+    h = v * dt + h;
+end
+
+h = h + ((v^2) / (2*-g))
+vb = v
+
+thrustFiring = 0;
+dt = 0.001;
+v = 0;
+j = 1;
+k = 1;
+t = 0;
+
+while 1
+    if (abs(v + vb) < 0.005) && (thrustFiring == 0)
+        thrustFiring = 1;
+        tb = 0;
+    end
+    
+    if thrustFiring == 0
+        v = g*dt + v;
+        h = v*dt + h;
+        az = g;
+    elseif thrustFiring == 1
+        if ((tb >= 0.148) && (tb <= 3.45))
+            v = v + a(j)*dt;
+            h = h + v*dt;
+            az = a(j);
+
+            j = j + 1;
+        else
+            if tb > 3.45
+                thrustFiring = 0;
+            end
+            
+            v = g*dt + v;
+            h = v*dt + h;
+            az = g;
+        end
+        
+        tb = tb + dt;
+    end
+    
+    accel(k) = az;
+    vz(k) = v;
+    z(k) = h;
+    time(k) = t;
+
+    t = t + dt;
+    k = k + 1;
+    if ((h < 0) && (thrustFiring == 0))
+        break
+    end
+end
+
+figure(1)
+plot(time, z)
+figure(2)
+plot(time, vz)
+figure(3)
+plot(time, accel)

matlabHelpers/test.m

@@ -0,0 +1,46 @@
+clear all; close all; clc;
+
+g = -9.81;
+mass = 1.2;
+mdot = 0.0182;
+dt = 0.001;
+
+vprev = 0;
+hprev = 0;
+i = 1;
+
+for t = 0 : dt : 3.45
+    m = mass - mdot*t;
+    if t < 0.148
+        thrust = 0;
+    elseif (t > 0.147) && (t < 0.419)
+        thrust = 65.165.*t - 2.3921;
+    elseif (t > 0.420) && (t < 3.382)
+        thrust = 0.8932*t^6 - 11.609*t^5 + 60.739*t^4 - 162.99*t^3 ...
+            + 235.6*t^2 - 174.43*t + 67.17;
+    elseif (t > 3.381) && (t < 3.451)
+        thrust = -195.78*t + 675.11;
+    elseif t > 3.45
+        thrust = 0;
+    end
+   
+    acceleration(i) = (thrust / mass) + g;
+    velocity(i) = acceleration(i) * dt + vprev;
+    height(i) = velocity(i) * dt + hprev;
+    
+    vprev = velocity(i);
+    hprev = height(i);
+    i = i + 1;
+end
+figure(1)
+hold on
+t = 0 : dt : 3.45;
+plot(t + 0.7712, velocity - max(velocity))
+
+t1 = 0 : 0.001 : 0.7712;
+v = -9.81*t1;
+plot(t1, v)
+
+figure(2)
+h = 0.5*-9.81*t1.^2
+plot(t1, h)