diff --git a/sw/in_progress/airspeed/ultrasimplesim.m b/sw/in_progress/airspeed/ultrasimplesim.m
new file mode 100644
index 0000000000..30e77504d6
--- /dev/null
+++ b/sw/in_progress/airspeed/ultrasimplesim.m
@@ -0,0 +1,244 @@
+clear
+clc
+close all
+
+
+
+dt = 1/60;
+simsteps = 16000;
+
+timespan=0:1/60:100;
+
+t = 0;
+airspeed = 14;
+acceleration = 0;
+vclimb = 0;
+altitude = 100;
+pitch = 0;
+alpha = 0;
+pitch_sp = 0.2;
+throttle = 0.5;
+power = 0.25;
+elevator = 0;
+
+
+% Airspeed command
+airspeed_sp  = ones(1,simsteps).* 11;
+airspeed_sp(1,6000:12000) = 16;
+airspeed_sp(1,13000:14000) = 7;
+
+% Altitude command
+altitude_sp  = ones(1,simsteps).* 100;
+altitude_sp(1,2000:4000) = 125;
+altitude_sp(1,8000:10000) = 125;
+
+battery_good = ones(1,simsteps);
+battery_good(1,15000:16000) = 0;
+
+% Save state
+X = zeros(simsteps,13);
+
+% Very sofisticated Aircraft Model
+Vmax    = 26;   % Level flight full power
+Vmin    = 8;    % Stall
+Mass    = 1.0;
+
+% Controller States
+pitch_cumsum = 0;
+airspeed_cumsum = 0;
+
+controller = 1;
+
+for i=1:simsteps
+    
+    %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+    % Simplified A/C long dynamics with stall and energy
+    %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+    % Pitch loop without integrators
+    elevator = (pitch_sp - pitch) * 15;
+    if (elevator > 0.4)
+        elevator = 0.4;
+    elseif (elevator < -0.2)
+        elevator = -0.2;
+    end
+    % Follow elevator but also align with the flow
+    pitch = pitch + elevator * dt - alpha * dt; 
+    % Angle of attack from 0 deg at vmax to 17 deg stall at vmin
+    if airspeed > Vmax
+        alpha = 0;
+        LoverD = 6;
+    elseif airspeed < Vmin
+        % from Vmin downto 3/4Vmin ... increase alpha from 17 to 45 deg 
+        lin = (Vmin-airspeed) / (Vmin/4);
+        if (lin > 2)
+            lin = 2;
+        end
+        alpha = (17 + (45-17) * lin) / 57; % complete stall
+        LoverD = 8 + (4.1-8) * lin;
+    else
+        alpha = (Vmax - airspeed) / (Vmax-Vmin) * 17.0 / 57;
+        LoverD = 8;
+    end
+    % Path angle
+    gamma = pitch - alpha;
+    vclimb = sin(gamma) * airspeed;
+    altitude = altitude + vclimb * dt;
+    % Using the pitch angle...
+    P_climb = vclimb * Mass;
+    % Lift over Drag
+    P_drag = airspeed / LoverD * Mass;
+    % Motor Energy
+    if battery_good(i) == 0
+        throttle = 0;
+    end
+    power_sp = throttle ^ 2;
+    power = power + (power_sp - power) * 0.1;
+    % Full throttle = same energy as vmax glide
+    P_motor = (Vmax / LoverD) * sqrt(power) * Mass;
+    % Total energy
+    P_tot = P_motor - P_drag - P_climb;
+
+    acceleration = P_tot / Mass;
+    airspeed = airspeed + (acceleration * dt);
+    
+    if (airspeed < Vmin/2)
+        airspeed = Vmin/2;
+    end
+    if (altitude < 0)
+        altitude = 0;
+    end
+    
+    %%%%%%%%%%%%%%%%%%%%%%%%%
+    % Run Control 1
+    
+    if controller == 1
+        Throttle_min = 0.2;
+        Throttle_max = 0.9;
+        
+        Pitch_min = -20/57;
+        Pitch_max = 30/57;
+
+        
+
+        % Traditional with integrators:
+
+        vclimb_sp = (altitude_sp(i) - altitude);
+        if (vclimb_sp > 3)
+            vclimb_sp = 3;
+        elseif (vclimb_sp < -3)
+            vclimb_sp = -3;
+        end
+        throttle = vclimb_sp * 0.33;
+        if (throttle > Throttle_max)
+            throttle = Throttle_max;
+        elseif (throttle < Throttle_min)
+            throttle = Throttle_min;
+        end
+        % P-gain
+        pitch_sp = 0.1 +  vclimb_sp * 0.05;
+        if (pitch_sp > Pitch_max)
+            pitch_sp = Pitch_max;
+        elseif (pitch_sp < Pitch_min)
+            pitch_sp = Pitch_min;
+        end 
+
+    %%%%%%%%%%%%%%%%%%%%%%%%%
+    % Run Control 2
+    
+    elseif controller == 2
+        Throttle_min = 0.15;
+        Throttle_max = 1;
+        
+        Pitch_min = 6/57;
+        Pitch_max = 18/57;
+
+        
+
+        % Traditional with integrators:
+
+        vclimb_sp = (altitude_sp(i) - altitude);
+        if (vclimb_sp > 3)
+            vclimb_sp = 3;
+        elseif (vclimb_sp < -3)
+            vclimb_sp = -3;
+        end
+        % I-gain
+        pitch_cumsum = pitch_cumsum + vclimb_sp * 0.001;
+        if (pitch_cumsum > Pitch_max)
+            pitch_cumsum = Pitch_max;
+        elseif (pitch_cumsum < Pitch_min)
+            pitch_cumsum = Pitch_min;
+        end 
+        % P-gain
+        pitch_sp = pitch_cumsum +  vclimb_sp * 0.05;
+
+        err_airspeed = airspeed_sp(i) - airspeed;
+        airspeed_cumsum = airspeed_cumsum + err_airspeed * 0.0002;
+        if (airspeed_cumsum > Throttle_max)
+            airspeed_cumsum = Throttle_max;
+        elseif (airspeed_cumsum < Throttle_min)
+            airspeed_cumsum = Throttle_min;
+        end
+        throttle = airspeed_cumsum + err_airspeed * 0.08;
+        if (throttle > Throttle_max)
+            throttle = Throttle_max;
+        elseif (throttle < Throttle_min)
+            throttle = Throttle_min;
+        end
+    
+    end    
+    
+    % Save For plotting
+    X(i,:) = [  airspeed_sp(i) airspeed altitude_sp(i) altitude  throttle power pitch_sp pitch alpha gamma elevator vclimb_sp vclimb]; 
+    
+end
+
+
+
+figure
+subplot(6,1,1)
+hold on
+plot(airspeed_sp,'r');
+plot(X(:,2),'b');
+plot(ones(simsteps,1)*Vmin,'k');
+plot(ones(simsteps,1)*Vmax,'k');
+title('Airspeed')
+grid
+
+subplot(6,1,2)
+hold on
+plot(X(:,7)*57,'r');
+plot(X(:,8)*57,'b');
+title('Pitch')
+grid
+
+subplot(6,1,3)
+hold on
+plot(X(:,5),'r');
+title('Throttle')
+grid
+
+
+subplot(6,1,4)
+hold on
+plot(X(:,9)*57,'g');
+plot(ones(simsteps,1)*17,'r');
+plot(X(:,10)*57,'k');
+title('Alpha Gamma (degrees)')
+%legend('1','2')
+grid
+
+subplot(6,1,5)
+hold on
+plot(X(:,12),'r');
+plot(X(:,13),'b');
+title('VClimb')
+grid
+
+subplot(6,1,6)
+hold on
+plot(altitude_sp,'r');
+plot(X(:,4),'b');
+title('Altitude')
+grid
+