diff --git a/commonFunctions/kalman/run_MEA.m b/commonFunctions/kalman/run_MEA.m
index cbf8e45d2b2acc7d9d9659031983ab04b3a434a3..a8a275748b1c5cf5167d347361b65d7ac388be33 100644
--- a/commonFunctions/kalman/run_MEA.m
+++ b/commonFunctions/kalman/run_MEA.m
@@ -50,7 +50,7 @@ for ii = 2:length(t_mea)
     P(:,:,ii) = A*P(:,:,ii-1)*A' + settings.mea.Q;
 
     % barometer correction
-    if sensorTot.comb_chamber.measures(index_chambPress)  > 1
+    if sensorTot.comb_chamber.measures(index_chambPress) > 1
         S = C*P(:,:,ii)*C' + settings.mea.R;
         if ~det(S)<1e-3
             K = P(:,:,ii)*C' / S; % if you want to try with constant gain [0.267161;-0.10199;-0.000205604 ];
@@ -60,7 +60,7 @@ for ii = 2:length(t_mea)
     end
 
     % accelerometer correction (not for 2023)
-    if contains(mission.name, '2024')
+    if contains(mission.name, '2024') || contains(mission.name, '2025')
         K_t = settings.mea.K_t;
         alpha = settings.mea.alpha;
         c = settings.mea.c;
diff --git a/data/2024_Lyra_Portugal_October/config2024_Lyra_Portugal_October.m b/data/2024_Lyra_Portugal_October/config2024_Lyra_Portugal_October.m
index 0f658f06f967baf5b53db722f9a557f6b48563db..478c0498a88e2e4fabb0a9f81ce895606c987f95 100644
--- a/data/2024_Lyra_Portugal_October/config2024_Lyra_Portugal_October.m
+++ b/data/2024_Lyra_Portugal_October/config2024_Lyra_Portugal_October.m
@@ -176,9 +176,12 @@ settings.mea.engine_model_C1     = [1.00196621875211 -0.485916431287183 0];
 settings.mea.K_t = 105.2;
 
 % covariance matrices
-settings.mea.Q                   = eye(3);                      % model noise covariance matrix    
-settings.mea.R                   = 0.36; 
-settings.mea.P0_mat = diag([0 0 0.36^2]);
+% settings.mea.Q                   = eye(3);                                  % model noise covariance matrix       
+% settings.mea.R                   = 0.36; 
+% settings.mea.P0_mat = diag([0 0 0.36^2]);
+settings.mea.Q                   = diag([1 1 5]);                                  % model noise covariance matrix       
+settings.mea.R                   = 3.6; 
+settings.mea.P0_mat = diag([0 0 3.6^2]);
 
 % shut down prediction altitude
 settings.mea.z_shutdown          = 3200;                                    % [m] target apogee prediction for shutdown
@@ -186,11 +189,14 @@ settings.mea.t_lower_shadowmode  = 0;                                       % mi
 settings.mea.t_higher_shadowmode = 10;                                      % maximum burning time
 settings.shutdownValveDelay      = 0.2;                                     % time from the shut down command to the actual valve closure
 settings.mea.cd_correction_factor = 2.69;
+
 % accelerometer correction parameters
-[~,~,settings.mea.P0] = computeAtmosphericData(103);     %[Pa] reference pressure at the SFT location
-settings.mea.acc_threshold = 40;           %[m/s^2] minimum acceleration to perform correction with accelerometer
-settings.mea.vel_threshold = 40;           %[m/s] minimum velocity to perform correction with accelerometer
-Rs = 1.0e+03*[0.4771    1.4391];
+[~,~,settings.mea.P0] = computeAtmosphericData(160);                        % [Pa] reference pressure at the SFT location
+settings.mea.acc_threshold = 40;                                            % [m/s^2] minimum acceleration to perform correction with accelerometer
+settings.mea.vel_threshold = 40;                                            % [m/s] minimum velocity to perform correction with accelerometer
+% Rs = 1.0e+03*[0.4771    1.4391];
+Rs = 3.0e+03*[0.4771    1.4391];
+
 % variable variance coefficients for accelerometer
 settings.mea.alpha = (Rs(2) - Rs(1))/(100^2-30^2);
 settings.mea.c = -settings.mea.alpha*30^2+Rs(1); 
diff --git a/simulator/src/sensor_plots_MEA_test.m b/simulator/src/sensor_plots_MEA_test.m
index 81c8e125a6748ac634ffc5f7e7aa7b1c092a9864..2f046b0a65ca174555c250a8dc17f2f0e77ea60e 100644
--- a/simulator/src/sensor_plots_MEA_test.m
+++ b/simulator/src/sensor_plots_MEA_test.m
@@ -1,27 +1,27 @@
 function sensor_plots_MEA_test(simOutput, environment, rocket, settings)
 
-%% Accelerometer measurements
-figure('Name', "Accelerometer measurements")
-subplot(3,1,1)
-plot(simOutput.sensors.imu.time, simOutput.sensors.imu.accelerometer_measures(:,1)./9.81);
-hold on, grid on
-plot(simOutput.t, simOutput.recall.accelerations_body(:,1)./9.81);
-legend("Accelerometer", "Real");
-title("Acceleration BODY", 'Interpreter','latex');
-ylabel("$a_X$ [g]")
-subplot(3,1,2)
-plot(simOutput.sensors.imu.time, simOutput.sensors.imu.accelerometer_measures(:,2)./9.81);
-hold on, grid on
-plot(simOutput.t, simOutput.recall.accelerations_body(:,2)./9.81);
-legend("Accelerometer", "Real");
-ylabel("$a_Y$ [g]")
-subplot(3,1,3)
-plot(simOutput.sensors.imu.time, simOutput.sensors.imu.accelerometer_measures(:,3)./9.81);
-hold on, grid on
-plot(simOutput.t, simOutput.recall.accelerations_body(:,3)./9.81);
-legend("Accelerometer", "Real");
-xlabel("Time [s]"), ylabel("$a_Z$ [g]")
-drawnow
+% %% Accelerometer measurements
+% figure('Name', "Accelerometer measurements")
+% subplot(3,1,1)
+% plot(simOutput.sensors.imu.time, simOutput.sensors.imu.accelerometer_measures(:,1)./9.81);
+% hold on, grid on
+% plot(simOutput.t, simOutput.recall.accelerations_body(:,1)./9.81);
+% legend("Accelerometer", "Real");
+% title("Acceleration BODY", 'Interpreter','latex');
+% ylabel("$a_X$ [g]")
+% subplot(3,1,2)
+% plot(simOutput.sensors.imu.time, simOutput.sensors.imu.accelerometer_measures(:,2)./9.81);
+% hold on, grid on
+% plot(simOutput.t, simOutput.recall.accelerations_body(:,2)./9.81);
+% legend("Accelerometer", "Real");
+% ylabel("$a_Y$ [g]")
+% subplot(3,1,3)
+% plot(simOutput.sensors.imu.time, simOutput.sensors.imu.accelerometer_measures(:,3)./9.81);
+% hold on, grid on
+% plot(simOutput.t, simOutput.recall.accelerations_body(:,3)./9.81);
+% legend("Accelerometer", "Real");
+% xlabel("Time [s]"), ylabel("$a_Z$ [g]")
+% drawnow
 
 % %% Gyroscope measurements
 % figure('Name', "Gyroscope measurements")
@@ -101,40 +101,40 @@ drawnow
 % xlabel("Time [s]"), ylabel("Up agl [m]");
 % drawnow
 
-%% Velocities
-% ODE velocity rotated in ned frame
-v_ned = zeros(length(simOutput.t), 3);
-drogue_idx = sum(simOutput.t <= simOutput.state_lastTimes(3));
-v_ned(1:drogue_idx,:) = quatrotate(quatconj(simOutput.Y(1:drogue_idx, 10:13)), simOutput.Y(1:drogue_idx, 4:6));
-if simOutput.state_lastTimes(6) == 0
-    v_ned(drogue_idx+1:end,:) = simOutput.Y(drogue_idx+1:end,4:6);
-else
-    prf_idx = sum(simOutput.t <= simOutput.state_lastTimes(4));
-    v_ned(drogue_idx+1:prf_idx,:) = simOutput.Y(drogue_idx+1:prf_idx,4:6);
-    v_ned(prf_idx+1:end,:) = quatrotate(quatconj(simOutput.Y(prf_idx+1:end, 10:13)), simOutput.Y(prf_idx+1:end, 4:6));
-end
-
-figure("Name", "GPS Velocity measurements")
-subplot(3,1,1)
-plot(simOutput.sensors.gps.time, simOutput.sensors.gps.velocity_measures(:,1));
-hold on; grid on;
-plot(simOutput.t, v_ned(:,1));
-legend("GPS", "Real");
-title("Velocities");
-ylabel("$V_N\ [m/s]$");
-subplot(3,1,2)
-plot(simOutput.sensors.gps.time, simOutput.sensors.gps.velocity_measures(:,2));
-hold on; grid on;
-plot(simOutput.t, v_ned(:,2));
-legend("GPS", "Real");
-ylabel("$V_E\ [m/s]$");
-subplot(3,1,3)
-plot(simOutput.sensors.gps.time, simOutput.sensors.gps.velocity_measures(:,3));
-hold on; grid on;
-plot(simOutput.t, v_ned(:,3));
-legend("GPS", "Real");
-xlabel("Time [s]"), ylabel("$V_D\ [m/s]$");
-drawnow
+% %% Velocities
+% % ODE velocity rotated in ned frame
+% v_ned = zeros(length(simOutput.t), 3);
+% drogue_idx = sum(simOutput.t <= simOutput.state_lastTimes(3));
+% v_ned(1:drogue_idx,:) = quatrotate(quatconj(simOutput.Y(1:drogue_idx, 10:13)), simOutput.Y(1:drogue_idx, 4:6));
+% if simOutput.state_lastTimes(6) == 0
+%     v_ned(drogue_idx+1:end,:) = simOutput.Y(drogue_idx+1:end,4:6);
+% else
+%     prf_idx = sum(simOutput.t <= simOutput.state_lastTimes(4));
+%     v_ned(drogue_idx+1:prf_idx,:) = simOutput.Y(drogue_idx+1:prf_idx,4:6);
+%     v_ned(prf_idx+1:end,:) = quatrotate(quatconj(simOutput.Y(prf_idx+1:end, 10:13)), simOutput.Y(prf_idx+1:end, 4:6));
+% end
+% 
+% figure("Name", "GPS Velocity measurements")
+% subplot(3,1,1)
+% plot(simOutput.sensors.gps.time, simOutput.sensors.gps.velocity_measures(:,1));
+% hold on; grid on;
+% plot(simOutput.t, v_ned(:,1));
+% legend("GPS", "Real");
+% title("Velocities");
+% ylabel("$V_N\ [m/s]$");
+% subplot(3,1,2)
+% plot(simOutput.sensors.gps.time, simOutput.sensors.gps.velocity_measures(:,2));
+% hold on; grid on;
+% plot(simOutput.t, v_ned(:,2));
+% legend("GPS", "Real");
+% ylabel("$V_E\ [m/s]$");
+% subplot(3,1,3)
+% plot(simOutput.sensors.gps.time, simOutput.sensors.gps.velocity_measures(:,3));
+% hold on; grid on;
+% plot(simOutput.t, v_ned(:,3));
+% legend("GPS", "Real");
+% xlabel("Time [s]"), ylabel("$V_D\ [m/s]$");
+% drawnow
 
 % %% Barometer measurements
 % [~, ~, P_real] = computeAtmosphericData(-simOutput.Y(:,3)+environment.z0);
diff --git a/simulator/src/std_plots_MEA_test.m b/simulator/src/std_plots_MEA_test.m
index 097dc9e2cc17432413296faa06c9f9288111a415..faecc01d65a7af5e194da76bac773aa046032fd4 100644
--- a/simulator/src/std_plots_MEA_test.m
+++ b/simulator/src/std_plots_MEA_test.m
@@ -45,20 +45,21 @@ if contains(mission.name,'2023') || contains(mission.name,'2024') || contains(mi
         sgtitle('MEA')
         subplot(2,1,1)
 
-        plot(simOutput.t, -simOutput.Y(:, 3),'DisplayName','Altitude');
-        title('Predicted vs Real apogee');
+        plot(simOutput.t, -simOutput.Y(:, 3),'DisplayName','Altitude')
+        title('Predicted vs Real apogee')
         hold on; grid on;
-        plot(simOutput.sensors.mea.time, simOutput.sensors.mea.prediction,'DisplayName','Prediction');
+        plot(simOutput.sensors.mea.time, simOutput.sensors.mea.prediction,'DisplayName','Prediction')
+        xline(simOutput.sensors.mea.t_shutdown,'r--','DisplayName','MEA ShutDown')
         legend
         ylabel('Altitude AGL [m]')
 
         subplot(2,1,2)
-        plot(simOutput.sensors.mea.time, simOutput.sensors.mea.mass   ,'DisplayName','Est mass');
-        title('Estimated vs real mass');
+        plot(simOutput.sensors.mea.time, simOutput.sensors.mea.mass,'DisplayName','Est mass')
+        title('Estimated vs real mass')
         hold on;
-        plot(simOutput.t, simOutput.recall.true_mass   ,'DisplayName','True mass');
+        plot(simOutput.t, simOutput.recall.true_mass,'DisplayName','True mass')
+        xline(simOutput.sensors.mea.t_shutdown,'r--','DisplayName','MEA ShutDown')
         legend
-        xline(simOutput.sensors.mea.t_shutdown,'r--')
         xlabel('Time [s]');
         ylabel('Mass [kg]');
         if settings.flagExportPLOTS == true
@@ -69,17 +70,17 @@ end
 
 drawnow
 
-%% ADA
-figures.ada = figure('Name', 'ADA vs trajectory');
-plot( simOutput.sensors.ada.time,  simOutput.sensors.ada.xv(:,1),'DisplayName','$ADA_{z}$')
-hold on
-plot( simOutput.sensors.ada.time,  simOutput.sensors.ada.xv(:,2),'DisplayName','$ADA_{vz}$')
-plot( simOutput.t, -simOutput.Y(:,3),'DisplayName','True z')
-plot( simOutput.t, -v_ned(:,3),'DisplayName','True Vz')
-legend
-title('ADA vs trajectory')
-xlabel("Time [s]"), ylabel("Altitude AGL \& Velocity [m, m/s]")
-drawnow
+% %% ADA
+% figures.ada = figure('Name', 'ADA vs trajectory');
+% plot( simOutput.sensors.ada.time,  simOutput.sensors.ada.xv(:,1),'DisplayName','$ADA_{z}$')
+% hold on
+% plot( simOutput.sensors.ada.time,  simOutput.sensors.ada.xv(:,2),'DisplayName','$ADA_{vz}$')
+% plot( simOutput.t, -simOutput.Y(:,3),'DisplayName','True z')
+% plot( simOutput.t, -v_ned(:,3),'DisplayName','True Vz')
+% legend
+% title('ADA vs trajectory')
+% xlabel("Time [s]"), ylabel("Altitude AGL \& Velocity [m, m/s]")
+% drawnow
 
 % figures.ADADer = figure('Name', 'ADA Derivatives');
 % hold on
@@ -221,131 +222,131 @@ drawnow
 % end
 % drawnow
 
-%% Velocities BODY w.r.t. time against NAS
-figures.velocities_BODY = figure('Name', 'Velocities BODY','ToolBar','auto');
-%
-subplot(3,1,1)
-plot(simOutput.t, simOutput.Y(:, 4),'DisplayName','$V_x$')
-hold on; grid on;
-plot(simOutput.sensors.nas.time, v_NAS_body(:, 1),'DisplayName','$V_x$ est')
-if not(settings.scenario == "descent")
-    xline(simOutput.ARB.allowanceTime,'k--')
-end
-if settings.parafoil  && (settings.scenario == "descent" || settings.scenario == "full flight")
-    xline(simOutput.t(simOutput.events.mainChuteIndex),'b--','DisplayName','Parafoil opening')
-end
-xline(simOutput.apogee.time,'r--','DisplayName','Apogee')
-if any(~isnan(simOutput.sensors.nas.timestampPitotCorrection))
-    xline(min(simOutput.sensors.nas.timestampPitotCorrection(~isnan(simOutput.sensors.nas.timestampPitotCorrection))),'b--','Start pitot correction')
-    xline(max(simOutput.sensors.nas.timestampPitotCorrection(~isnan(simOutput.sensors.nas.timestampPitotCorrection))),'b--','Stop pitot correction')
-end
-ylabel('$V_x$ [m/s]');
-legend
-%
-subplot(3,1,2)
-plot(simOutput.t, simOutput.Y(:, 5),'DisplayName','$V_y$')
-hold on;
-plot(simOutput.sensors.nas.time, v_NAS_body(:, 2),'DisplayName','$V_y$ est')
-if not(settings.scenario == "descent")
-    xline(simOutput.ARB.allowanceTime,'k--')
-end
-if settings.parafoil  && (settings.scenario == "descent" || settings.scenario == "full flight")
-    xline(simOutput.t(simOutput.events.mainChuteIndex),'b--','DisplayName','Parafoil opening')
-end
-xline(simOutput.apogee.time,'r--','DisplayName','Apogee')
-if any(~isnan(simOutput.sensors.nas.timestampPitotCorrection))
-    xline(min(simOutput.sensors.nas.timestampPitotCorrection(~isnan(simOutput.sensors.nas.timestampPitotCorrection))),'b--','Start pitot correction')
-    xline(max(simOutput.sensors.nas.timestampPitotCorrection(~isnan(simOutput.sensors.nas.timestampPitotCorrection))),'b--','Stop pitot correction')
-end
-ylabel('$V_y$ [m/s]');
-legend
-%
-subplot(3,1,3)
-plot(simOutput.t, simOutput.Y(:, 6),'DisplayName','$V_z$')
-hold on;
-plot(simOutput.sensors.nas.time, v_NAS_body(:, 3),'DisplayName','$V_z$ est')
-if not(settings.scenario == "descent")
-    xline(simOutput.ARB.allowanceTime,'k--','DisplayName','Air brakes opening')
-end
-if settings.parafoil  && (settings.scenario == "descent" || settings.scenario == "full flight")
-    xline(simOutput.t(simOutput.events.mainChuteIndex),'b--','DisplayName','Parafoil opening')
-end
-xline(simOutput.apogee.time,'r--','DisplayName','Apogee')
-if any(~isnan(simOutput.sensors.nas.timestampPitotCorrection))
-    xline(min(simOutput.sensors.nas.timestampPitotCorrection(~isnan(simOutput.sensors.nas.timestampPitotCorrection))),'b--','Start pitot correction')
-    xline(max(simOutput.sensors.nas.timestampPitotCorrection(~isnan(simOutput.sensors.nas.timestampPitotCorrection))),'b--','Stop pitot correction')
-end
-xlabel('Time [s]');
-ylabel('$V_z$ [m/s]');
-sgtitle('Velocities BODY');
-legend
-if settings.flagExportPLOTS == true
-    exportStandardizedFigure(figures.velocities_BODY,"report_images\"+mission.name+"\src_velocities_BODY.pdf",0.9)
-end
-drawnow
-
-%% Velocities NED w.r.t. time against NAS
-figures.velocities_NED = figure('Name', 'Velocities NED','ToolBar','auto');
-%
-subplot(3,1,1)
-plot(simOutput.t, v_ned(:, 1),'DisplayName','$V_n$')
-hold on; grid on;
-plot(simOutput.sensors.nas.time, simOutput.sensors.nas.states(:, 4),'DisplayName','$V_n$ est')
-if not(settings.scenario == "descent")
-    xline(simOutput.ARB.allowanceTime,'k--')
-end
-ylabel('$V_x$ [m/s]');
-legend
-%
-subplot(3,1,2)
-plot(simOutput.t, v_ned(:, 2),'DisplayName','$V_e$')
-hold on;
-plot(simOutput.sensors.nas.time,simOutput.sensors.nas.states(:, 5) ,'DisplayName','$V_e$ est')
-if not(settings.scenario == "descent")
-    xline(simOutput.ARB.allowanceTime,'k--')
-end
-ylabel('$V_y$ [m/s]');
-legend
-%
-subplot(3,1,3)
-plot(simOutput.t, v_ned(:, 3),'DisplayName','$V_d$')
-hold on;
-plot(simOutput.sensors.nas.time, simOutput.sensors.nas.states(:, 6),'DisplayName','$V_d$ est')
-if not(settings.scenario == "descent")
-    xline(simOutput.ARB.allowanceTime,'k--','DisplayName','Air brakes opening')
-end
-xline(simOutput.apogee.time,'r--','DisplayName','Apogee')
-xlabel('Time [s]');
-ylabel('$V_z$ [m/s]');
-sgtitle('Velocities NED');
-legend
-if settings.flagExportPLOTS == true
-    exportStandardizedFigure(figures.velocities_NED,"report_images\"+mission.name+"\src_velocities_NED.pdf",0.9)
-end
-drawnow
-
-%% check consistency of NAS:
-altitude = simOutput.sensors.nas.states(:,3)+environment.z0;
-v_int_NAS = 0;
-v_int_simulation = 0;
-for i = 2:length(simOutput.sensors.nas.states(:,6))
-    v_int_NAS(i) = v_int_NAS(i-1) + sum(simOutput.sensors.nas.states([i-1,i],6))/settings.frequencies.NASFrequency/2;
-end
+% %% Velocities BODY w.r.t. time against NAS
+% figures.velocities_BODY = figure('Name', 'Velocities BODY','ToolBar','auto');
+% %
+% subplot(3,1,1)
+% plot(simOutput.t, simOutput.Y(:, 4),'DisplayName','$V_x$')
+% hold on; grid on;
+% plot(simOutput.sensors.nas.time, v_NAS_body(:, 1),'DisplayName','$V_x$ est')
+% if not(settings.scenario == "descent")
+%     xline(simOutput.ARB.allowanceTime,'k--')
+% end
+% if settings.parafoil  && (settings.scenario == "descent" || settings.scenario == "full flight")
+%     xline(simOutput.t(simOutput.events.mainChuteIndex),'b--','DisplayName','Parafoil opening')
+% end
+% xline(simOutput.apogee.time,'r--','DisplayName','Apogee')
+% if any(~isnan(simOutput.sensors.nas.timestampPitotCorrection))
+%     xline(min(simOutput.sensors.nas.timestampPitotCorrection(~isnan(simOutput.sensors.nas.timestampPitotCorrection))),'b--','Start pitot correction')
+%     xline(max(simOutput.sensors.nas.timestampPitotCorrection(~isnan(simOutput.sensors.nas.timestampPitotCorrection))),'b--','Stop pitot correction')
+% end
+% ylabel('$V_x$ [m/s]');
+% legend
+% %
+% subplot(3,1,2)
+% plot(simOutput.t, simOutput.Y(:, 5),'DisplayName','$V_y$')
+% hold on;
+% plot(simOutput.sensors.nas.time, v_NAS_body(:, 2),'DisplayName','$V_y$ est')
+% if not(settings.scenario == "descent")
+%     xline(simOutput.ARB.allowanceTime,'k--')
+% end
+% if settings.parafoil  && (settings.scenario == "descent" || settings.scenario == "full flight")
+%     xline(simOutput.t(simOutput.events.mainChuteIndex),'b--','DisplayName','Parafoil opening')
+% end
+% xline(simOutput.apogee.time,'r--','DisplayName','Apogee')
+% if any(~isnan(simOutput.sensors.nas.timestampPitotCorrection))
+%     xline(min(simOutput.sensors.nas.timestampPitotCorrection(~isnan(simOutput.sensors.nas.timestampPitotCorrection))),'b--','Start pitot correction')
+%     xline(max(simOutput.sensors.nas.timestampPitotCorrection(~isnan(simOutput.sensors.nas.timestampPitotCorrection))),'b--','Stop pitot correction')
+% end
+% ylabel('$V_y$ [m/s]');
+% legend
+% %
+% subplot(3,1,3)
+% plot(simOutput.t, simOutput.Y(:, 6),'DisplayName','$V_z$')
+% hold on;
+% plot(simOutput.sensors.nas.time, v_NAS_body(:, 3),'DisplayName','$V_z$ est')
+% if not(settings.scenario == "descent")
+%     xline(simOutput.ARB.allowanceTime,'k--','DisplayName','Air brakes opening')
+% end
+% if settings.parafoil  && (settings.scenario == "descent" || settings.scenario == "full flight")
+%     xline(simOutput.t(simOutput.events.mainChuteIndex),'b--','DisplayName','Parafoil opening')
+% end
+% xline(simOutput.apogee.time,'r--','DisplayName','Apogee')
+% if any(~isnan(simOutput.sensors.nas.timestampPitotCorrection))
+%     xline(min(simOutput.sensors.nas.timestampPitotCorrection(~isnan(simOutput.sensors.nas.timestampPitotCorrection))),'b--','Start pitot correction')
+%     xline(max(simOutput.sensors.nas.timestampPitotCorrection(~isnan(simOutput.sensors.nas.timestampPitotCorrection))),'b--','Stop pitot correction')
+% end
+% xlabel('Time [s]');
+% ylabel('$V_z$ [m/s]');
+% sgtitle('Velocities BODY');
+% legend
+% if settings.flagExportPLOTS == true
+%     exportStandardizedFigure(figures.velocities_BODY,"report_images\"+mission.name+"\src_velocities_BODY.pdf",0.9)
+% end
+% drawnow
 
-for i = 2:length(simOutput.Y(:,6))
-    v_int_simulation(i) = v_int_simulation(i-1) + sum(v_ned([i-1,i],3)*0.01)/2;
-end
+% %% Velocities NED w.r.t. time against NAS
+% figures.velocities_NED = figure('Name', 'Velocities NED','ToolBar','auto');
+% %
+% subplot(3,1,1)
+% plot(simOutput.t, v_ned(:, 1),'DisplayName','$V_n$')
+% hold on; grid on;
+% plot(simOutput.sensors.nas.time, simOutput.sensors.nas.states(:, 4),'DisplayName','$V_n$ est')
+% if not(settings.scenario == "descent")
+%     xline(simOutput.ARB.allowanceTime,'k--')
+% end
+% ylabel('$V_x$ [m/s]');
+% legend
+% %
+% subplot(3,1,2)
+% plot(simOutput.t, v_ned(:, 2),'DisplayName','$V_e$')
+% hold on;
+% plot(simOutput.sensors.nas.time,simOutput.sensors.nas.states(:, 5) ,'DisplayName','$V_e$ est')
+% if not(settings.scenario == "descent")
+%     xline(simOutput.ARB.allowanceTime,'k--')
+% end
+% ylabel('$V_y$ [m/s]');
+% legend
+% %
+% subplot(3,1,3)
+% plot(simOutput.t, v_ned(:, 3),'DisplayName','$V_d$')
+% hold on;
+% plot(simOutput.sensors.nas.time, simOutput.sensors.nas.states(:, 6),'DisplayName','$V_d$ est')
+% if not(settings.scenario == "descent")
+%     xline(simOutput.ARB.allowanceTime,'k--','DisplayName','Air brakes opening')
+% end
+% xline(simOutput.apogee.time,'r--','DisplayName','Apogee')
+% xlabel('Time [s]');
+% ylabel('$V_z$ [m/s]');
+% sgtitle('Velocities NED');
+% legend
+% if settings.flagExportPLOTS == true
+%     exportStandardizedFigure(figures.velocities_NED,"report_images\"+mission.name+"\src_velocities_NED.pdf",0.9)
+% end
+% drawnow
 
-figures.AltNAS = figure('Name', 'Altitude NAS');
-plot(simOutput.sensors.nas.time,altitude,'DisplayName','Altitude NAS')
-hold on
-title("Altitude NAS and simulation")
-plot(simOutput.sensors.nas.time,v_int_NAS,'DisplayName','Velocity NAS integrated')
-plot(simOutput.t,simOutput.Y(:,3),'DisplayName','Altitude Simulation')
-plot(simOutput.t,v_int_simulation,'DisplayName','Velocity simulation integrated')
-legend
-xlabel("Time [s]"), ylabel("-Altitude AGL [m]")
-drawnow
+% %% check consistency of NAS:
+% altitude = simOutput.sensors.nas.states(:,3)+environment.z0;
+% v_int_NAS = 0;
+% v_int_simulation = 0;
+% for i = 2:length(simOutput.sensors.nas.states(:,6))
+%     v_int_NAS(i) = v_int_NAS(i-1) + sum(simOutput.sensors.nas.states([i-1,i],6))/settings.frequencies.NASFrequency/2;
+% end
+% 
+% for i = 2:length(simOutput.Y(:,6))
+%     v_int_simulation(i) = v_int_simulation(i-1) + sum(v_ned([i-1,i],3)*0.01)/2;
+% end
+% 
+% figures.AltNAS = figure('Name', 'Altitude NAS');
+% plot(simOutput.sensors.nas.time,altitude,'DisplayName','Altitude NAS')
+% hold on
+% title("Altitude NAS and simulation")
+% plot(simOutput.sensors.nas.time,v_int_NAS,'DisplayName','Velocity NAS integrated')
+% plot(simOutput.t,simOutput.Y(:,3),'DisplayName','Altitude Simulation')
+% plot(simOutput.t,v_int_simulation,'DisplayName','Velocity simulation integrated')
+% legend
+% xlabel("Time [s]"), ylabel("-Altitude AGL [m]")
+% drawnow
 
 % %% euler angles
 % eul_NAS = quat2eul(simOutput.sensors.nas.states(:,[10,7:9]));