diff --git a/RoccarasoFlight/postprocessing/AFD/configSimPostp.m b/RoccarasoFlight/postprocessing/AFD/configSimPostp.m
new file mode 100644
index 0000000000000000000000000000000000000000..9fe20883058a0db8d6d726e301fb609225137b35
--- /dev/null
+++ b/RoccarasoFlight/postprocessing/AFD/configSimPostp.m
@@ -0,0 +1,192 @@
+%{
+
+CONFIG - This script sets up all the parameters for the simulation
+All the parameters are stored in the "settings" structure.
+
+REVISIONS:
+- #0 16/04/2016, Release, Francesco Colombi
+
+Copyright © 2021, Skyward Experimental Rocketry, AFD department
+All rights reserved
+
+SPDX-License-Identifier: GPL-3.0-or-later
+
+%}
+
+%% MISSION FILE
+% Choose the mision you want to simulate from rocketsData folder
+
+
+%% LOAD DATA
+run("..\..\..\..\msa-toolkit\data\Gemini_Roccaraso_September_2023\simulationsData.m");
+
+%% LAUNCH SETUP
+% launchpad directions
+% for a single run the maximum and the minimum value of the following angles must be the same.
+settings.OMEGAmin = 79*pi/180; % [rad] Minimum Elevation Angle, user input in degrees (ex. 80)
+settings.OMEGAmax = 79*pi/180; % [rad] Maximum Elevation Angle, user input in degrees (ex. 80)
+settings.PHImin = 178*pi/180; % [rad] Minimum Azimuth Angle from North Direction, user input in degrees (ex. 90)
+settings.PHImax = 178*pi/180; % [rad] Maximum Azimuth Angle from North Direction, user input in degrees (ex. 90)
+
+% !! ATTENTION !! The following 2 work just for the stochastichs simulations with constant wind model only
+settings.upwind = false; % If true, phi is selected opposite to the wind direction
+settings.PHIsigma = 0*pi/180; % [deg] If upwind is true, you can select a variance for the direction
+
+%% ROCCARASO TERRAIN
+% !! ATTENTION !! the following works only at Roccaraso
+settings.terrain = false;
+
+if settings.terrain
+ settings.lat0 = 41.8084579; % Launchpad latitude
+ settings.lon0 = 14.0546408; % Launchpad longitude
+ settings.funZ = funZGen('zData.mat', settings.lat0, settings.lon0);
+end
+
+%% ENGINE SETTINGS
+% Following set the instant of time at which the engine is cut off. Set Inf
+% if you want to have a complete burn.
+
+if settings.HREmot
+ settings.timeEngineCut = (inf) * settings.tb; % [s] Moment in time in wich the engine will be cut off
+ settings = settingsEngineCut(settings); % updatind settings parameters
+end
+
+%% AEROBRAKES SETTINGS
+% Multiple air-brakes and smooth opening simulation
+settings.multipleAB = true; % If true, multiple and smooth airbrakes opening will be simulated
+
+% If FALSE:
+% - settings.control: only the first value will be computed;
+% - settings.dtControl: is not read.
+% If TRUE:
+% - settings.control: define the sequence of air-brakes opening
+% configuration. Closed air-brakes are simulated
+% untill the conditions settings.tControl and
+% settings.machControl are both verified, check
+% simulationsData.m;
+% - settings.dtControl: define the usage time of the i-th
+% configuration. Its length must be -1 the
+% length of settings.control
+
+settings.control = [1 3]; % aerobrakes, 1-2-3 for 0%, 50% or 100% opened
+settings.dtControl = res.time(indexOpeningARB) - res.time(indexCO); % aerobrakes, configurations usage time
+
+%% PARAFOIL SIMULATION
+settings.parafoilSim = false; % [-] True if parafoil the parafoli open loop descentn needs to be performed
+
+%% DESCENT PHASE MODEL
+settings.descent6DOF = false; % set to true in order to start a 6DOF parachute descent phase
+
+%% WIND DETAILS
+% select which model you want to use:
+
+%%%%% Matlab Wind Model
+settings.wind.model = false;
+% matlab hswm model, wind model on altitude based on historical data
+
+% input Day and Hour as arrays to run stochastic simulations
+settings.wind.DayMin = 105; % [d] Minimum Day of the launch
+settings.wind.DayMax = 105; % [d] Maximum Day of the launch
+settings.wind.HourMin = 4; % [h] Minimum Hour of the day
+settings.wind.HourMax = 4; % [h] Maximum Hour of the day
+settings.wind.ww = 0; % [m/s] Vertical wind speed
+
+%%%%% Input wind
+
+%%% Roccaraso 2022 wind
+% settings.wind.inputMagnitude = [3 * ones(1, 18), 7* ones(1, 15), 15* ones(1, 10), 19 * ones(1, 20), 21 * ones(1, 37)];
+% settings.wind.inputAzimut = [300 * ones(1, 10) , 250 * ones(1, 90)]; % wind azimut angle at each altitude (toward wind incoming direction) [deg]
+%---------------------------------------------------
+
+settings.wind.input = true;
+% Wind is generated for every altitude interpolating with the coefficient defined below
+
+settings.wind.inputGround = 3; % wind magnitude at the ground [m/s]
+settings.wind.inputAlt = linspace(0, 2000, 100); % altitude vector [m]
+
+settings.wind.inputMagnitude = [3 * ones(1,15), 6 * ones(1, 5), 7 * ones(1, 10), 9 * ones(1, 15), 12 * ones(1, 20), 14 * ones(1, 35)];
+settings.wind.inputAzimut = [300 * ones(1, 15), 270 * ones(1, 85)]; % wind azimut angle at each altitude (toward wind incoming direction) [deg]
+
+settings.wind.inputMult = (settings.wind.inputMagnitude./settings.wind.inputGround - 1) * 100;
+
+%settings.wind.inputAzimut = [300 * ones(1, 10) , 250 * ones(1, 90)]; % wind azimut angle at each altitude (toward wind incoming direction) [deg]
+%settings.wind.inputMult = [0 66 133 183 200 250]; % percentage of increasing magnitude at each altitude
+%settings.wind.inputAzimut = randi([170 280], 1, 100); % wind azimut angle at each altitude (toward wind incoming direction) [deg]
+
+settings.wind.inputUncertainty = [0, 0];
+% settings.wind.inputUncertainty = [a,b]; wind uncertanties:
+% - a, wind magnitude percentage uncertanty: magn = magn *(1 +- a)
+% - b, wind direction band uncertanty: dir = dir 1 +- b
+
+
+%%%%% Variable wind model
+settings.wind.variable = false;
+if settings.wind.variable
+ % Generate a gaussian distribution at ground level and
+ % a uniform distribution in altitude, linear interpolation between
+ % The azimuth in the high layer is +-deltaAz wrt the Azimut at ground
+ settings.wind.var.magMeanG = 4.7;
+ settings.wind.var.magSigmaG = 1.2840;
+ settings.wind.var.azMinG = 0*pi/180;
+ settings.wind.var.azMaxG = 359*pi/180;
+ settings.wind.var.hG = 100;
+ settings.wind.var.magMinH = 4;
+ settings.wind.var.magMaxH = 30;
+ settings.wind.var.deltaAzH = 5*pi/180;
+ settings.wind.var.hH = 1000;
+ % NOTE: wind azimuth angle indications (wind directed towards):
+ % 0 deg (use 360 instead of 0) -> North
+ % 90 deg -> East
+ % 180 deg -> South
+ % 270 deg -> West
+end
+
+%%%%% Random wind model
+% if all the model above are false
+
+% Wind is generated randomly from the minimum to the maximum parameters which defines the wind.
+% Setting the same values for min and max will fix the parameters of the wind.
+
+settings.wind.MagMin = 5; % [m/s] Minimum Magnitude
+settings.wind.MagMax = 5; % [m/s] Maximum Magnitude
+settings.wind.ElMin = 0*pi/180; % [rad] Minimum Elevation, user input in degrees (ex. 0)
+settings.wind.ElMax = 0*pi/180; % [rad] Maximum Elevation, user input in degrees (ex. 0) (Max == 90 Deg)
+settings.wind.AzMin = wrapTo360(180)*pi/180; % [rad] Minimum Azimuth, user input in degrees (ex. 90)
+settings.wind.AzMax = wrapTo360(180)*pi/180; % [rad] Maximum Azimuth, user input in degrees (ex. 90)
+
+% NOTE: wind azimuth angle indications (wind directed towards):
+% 0 deg (use 360 instead of 0) -> North
+% 90 deg -> East
+% 180 deg -> South
+% 270 deg -> West
+
+%% BALLISTIC SIMULATION
+% Set to True to run a ballistic (without parachutes) simulation
+settings.ballistic = false;
+
+%% PLOT DETAILS
+settings.plots = true;
+
+%% LANDING POINTS
+% satellite maps of the landing zone
+settings.landingMap = true; % 2D map
+settings.satellite3D = false; % 3D map
+
+%% OPEN ROCKET
+settings.openRocketSM = false;
+
+if settings.openRocketSM
+ openRocketSkywardPath = '../../OpenRocketSkyward/';
+ addpath(genpath(openRocketSkywardPath))
+ settings.mHaackFlag = isequal(settings.OgType, 'MHAACK');
+
+ vars.Mach = linspace(0.1, 0.9, 6);
+ vars.Alpha = sort([linspace(-20, 20, 17), -1, 1]);
+ vars.Beta = linspace(-20, 20, 20);
+ vars.Alt = linspace(0, 4000, 5);
+ vars.xcg = settings.xcg;
+ vars.hprot = settings.hprot;
+
+ settings.input = createDissileInput(settings, vars);
+end
+settings.stoch.N = 1;
diff --git a/RoccarasoFlight/postprocessing/AFD/estimationCA.m b/RoccarasoFlight/postprocessing/AFD/estimationCA.m
index a7e55b8a10119d8282516f527331ee3b77cabb04..d7f08131d7d65be148bd90a8ed5d58513e4c6e31 100644
--- a/RoccarasoFlight/postprocessing/AFD/estimationCA.m
+++ b/RoccarasoFlight/postprocessing/AFD/estimationCA.m
@@ -1,117 +1,149 @@
+function results = estimationCA(main, alt0)
+
+ %% DECLARE CONSTANTS
+ NPOINTS = 1000;
+ MSTRUCT = 25.2885; % [kg] Gemini structural mass
+ AREF = 0.15^2 * pi * 0.25;
+ PROP_FINAL_MASS = 0.7799 + 0.4445; % [kg] initial propellant mass
+ tIGN = 0.97500; % Ignition time in the thrust curve
+ tCO = 5.32702; % Cutoff time in the thrsut curve
+ mDot = 0.9660; % [kg/s] Averaged propellant mass flow rate
+ DELTA_TIME = 0.4988;
+ load("CA_alpha0.mat");
+
+ % acceleration raw
+ indexApoIMU = find(main.IMU(:, 1)> main.tApogee, 1, 'first');
+ accXB_raw = main.IMU(1:indexApoIMU ,2);
+ tAcc = main.IMU(1:indexApoIMU, 1);
+ accXB = movmean(accXB_raw, 30);
+
+ % Motor data
+ load("../RPS/cleanData/ROC2/engineFlightData.mat");
+ timeThrust = flightData.timeThrust;
+ indexTimeThrust = and(timeThrust > tIGN, timeThrust < tCO);
+ timeThrust = timeThrust(indexTimeThrust);
+ timeThrust = timeThrust - timeThrust(1) - DELTA_TIME;
+
+ Thrust = flightData.Thrust(indexTimeThrust);
+
+ tNodal = [timeThrust(1), -0.2248, 3.33322, timeThrust(end)];
+ indexTransIGN = and(timeThrust>=tNodal(1), timeThrust<tNodal(2));
+ indexTransCO = and(timeThrust>tNodal(3), timeThrust<=tNodal(4));
+
+ thrustTransIGN = Thrust(indexTransIGN);
+ thrustTransCO = Thrust(indexTransCO);
+
+ offsetIGN = thrustTransIGN(1);
+ offsetCO = thrustTransCO(end);
+
+ thrustTransIGN = thrustTransIGN - offsetIGN;
+ thrustTransCO = thrustTransCO - offsetCO;
+
+ thrustTransIGN = thrustTransIGN * (1 + offsetIGN/thrustTransIGN(end));
+ thrustTransCO = thrustTransCO * (1 + offsetCO/thrustTransCO(1));
+
+ Thrust = [thrustTransIGN; Thrust(and(timeThrust>=tNodal(2), timeThrust<=tNodal(3))); thrustTransCO];
+ mMotor = linspace(PROP_FINAL_MASS + mDot*(tCO - tIGN), PROP_FINAL_MASS, sum(indexTimeThrust));
+ timeThrust = timeThrust - timeThrust(1);
+
+ % Velocity
+ tNas = main.NASData(1:main.NASApogeeIndex, 1);
+ altNas = -main.NASData(1:main.NASApogeeIndex, 4);
+ velNas = vecnorm(main.NASData(1:main.NASApogeeIndex, 5:7), 2, 2);
+
+ load sensorPitot.mat
+ indNasPit = sensorTot_WithPitot.nas.time < main.tApogee;
+
+ tNasPit = sensorTot_WithPitot.nas.time(indNasPit);
+ velNasPit = vecnorm(sensorTot_WithPitot.nas.states(indNasPit, 4:6), 2,2);
+ altNasPit = -sensorTot_WithPitot.nas.states(indNasPit, 3);
+
+
+ % Normalize data
+ timeRef = linspace(max([tNas(1), tAcc(1), tNasPit(1)]), min([tNas(end), tAcc(end), tNasPit(end)]) , NPOINTS);
+ indexEndThrust = find(timeRef > timeThrust(end), 1, 'first') - 1;
+
+ accXBRef = interp1(tAcc, accXB, timeRef);
+
+ ThrustRef = zeros(1, NPOINTS);
+ ThrustRef(1:indexEndThrust) = interp1(timeThrust, Thrust, timeRef(1:indexEndThrust));
+
+ mRocket = (mMotor(end) + MSTRUCT) * ones(1, NPOINTS);
+ mRocket(1:indexEndThrust) = interp1(timeThrust, mMotor, timeRef(1:indexEndThrust)) + MSTRUCT;
+
+ velRef = interp1(tNas, movmean(velNas, 10), timeRef);
+
+ velNasPitRef = interp1(tNasPit, velNasPit, timeRef);
+
+ altRef = interp1(tNasPit, altNasPit, timeRef);
+
+ % Air density and sonic velocity
+ [~, vSonRef, ~, rhoRef] = atmosisa(altRef + alt0);
+ machRef = velRef./vSonRef;
+ machPitRef = velNasPitRef./vSonRef;
+
+ % index opening
+ indexOpeningARB = find(timeRef > 5.12, 1, 'first');
+
+ % Compute CA
+ CA = (ThrustRef - mRocket.*accXBRef) ./ (0.5 .* rhoRef .* velRef.^2 * AREF);
+
+ CA_NasPitot = (ThrustRef - mRocket.*accXBRef) ./ (0.5 .* rhoRef .* velNasPitRef.^2 * AREF);
+
+ tCO = tCO -1.8519;
+ indexCO = find(ThrustRef == 0, 1, 'first');
+
+ mRocketNoPwr = mRocket(indexCO:end);
+ CANoPwr = CA(indexCO:end);
+ CA_100ARB = zeros(1, length(timeRef));
+ CA_0ARB = zeros(1, length(timeRef));
+
+ for i = 1:length(timeRef)
+ [~, indexMach] = nearestValSorted(MachRef, machPitRef(i));
+ [~, indexAlt] = nearestValSorted(AltRef, altRef(i));
+ CA_100ARB(i) = CA_MD(indexMach, indexAlt, 3);
+ CA_0ARB(i) = CA_MD(indexMach, indexAlt, 1);
+ end
+
+ ThrustComp = 0.5 .* rhoRef(1:indexCO) .* velRef(1:indexCO).^2 .* AREF .* CA_0ARB(1:indexCO) + mRocket(1:indexCO).*accXBRef(1:indexCO);
+
+ figure
+ plot(timeRef(indexCO:end),CANoPwr);
+ hold on
+ plot(timeRef(indexCO:end), CA_NasPitot(indexCO:end));
+ plot(timeRef(indexCO:end), [CA_0ARB(indexCO:indexOpeningARB) CA_100ARB(indexOpeningARB+1:end)]);
+ xlabel('Time [s]');
+ ylabel('CA [-]');
+ title('CA from telemetry');
+ grid on
+ legend('NAS', 'NAS with PITOT', 'MD', 'Location','southoutside', 'Orientation', 'horizontal');
+
+ %% SAVE RESULTS
+
+ results.time = timeRef;
+ results.Thrust = ThrustRef;
+ results.ThrustComputed = ThrustComp;
+
+ results.velocity.vel_pitot = velNasPitRef;
+ results.velocity.val_noPitot = velRef;
+
+ results.alt = altRef;
+
+ results.CA.CA100 = CA_100ARB;
+ results.CA.CA0 = CA_0ARB;
+ results.CA.CA_pitot = CA_NasPitot;
+ results.CA.CA_noPitot = CA;
+
+ results.mass.propMass = mMotor;
+ results.mass.rocketMass = mRocket;
+
+ results.accXBody = accXBRef;
+
+ results.events.shutdonw = indexCO;
+ results.events.ARB_opening = indexOpeningARB;
-%% CA estimation
-NPOINTS = 1000;
-MSTRUCT = 25.2885; % [kg] Gemini structural mass
-AREF = 0.15^2 * pi * 0.25;
-PROP_FINAL_MASS = 0.7799 + 0.4445; % [kg] initial propellant mass
-tIGN = 0.97500; % Ignition time in the thrust curve
-tCO = 5.32702; % Cutoff time in the thrsut curve
-mDot = 0.9660; % [kg/s] Averaged propellant mass flow rate
-DELTA_TIME = 0.4988;
-load("CA_alpha0.mat");
-
-% acceleration raw
-indexApoIMU = find(main.IMU(:, 1)> main.tApogee, 1, 'first');
-accXB_raw = main.IMU(1:indexApoIMU ,2);
-tAcc = main.IMU(1:indexApoIMU, 1);
-accXB = movmean(accXB_raw, 30);
-
-% Motor data
-load("../RPS/cleanData/ROC-02/engineFlightData.mat");
-timeThrust = flightData.timeThrust;
-indexTimeThrust = and(timeThrust > tIGN, timeThrust < tCO);
-timeThrust = timeThrust(indexTimeThrust);
-timeThrust = timeThrust - timeThrust(1) - DELTA_TIME;
-
-Thrust = flightData.Thrust(indexTimeThrust);
-
-tNodal = [timeThrust(1), -0.2248, 3.33322, timeThrust(end)];
-indexTransIGN = and(timeThrust>=tNodal(1), timeThrust<tNodal(2));
-indexTransCO = and(timeThrust>tNodal(3), timeThrust<=tNodal(4));
-
-thrustTransIGN = Thrust(indexTransIGN);
-thrustTransCO = Thrust(indexTransCO);
-
-offsetIGN = thrustTransIGN(1);
-offsetCO = thrustTransCO(end);
-
-thrustTransIGN = thrustTransIGN - offsetIGN;
-thrustTransCO = thrustTransCO - offsetCO;
-
-thrustTransIGN = thrustTransIGN * (1 + offsetIGN/thrustTransIGN(end));
-thrustTransCO = thrustTransCO * (1 + offsetCO/thrustTransCO(1));
-
-Thrust = [thrustTransIGN; Thrust(and(timeThrust>=tNodal(2), timeThrust<=tNodal(3))); thrustTransCO];
-mMotor = linspace(PROP_FINAL_MASS + mDot*(tCO - tIGN), PROP_FINAL_MASS, sum(indexTimeThrust));
-timeThrust = timeThrust - timeThrust(1);
-
-% Velocity
-tNas = main.NASData(1:main.NASApogeeIndex, 1);
-altNas = -main.NASData(1:main.NASApogeeIndex, 4);
-velNas = vecnorm(main.NASData(1:main.NASApogeeIndex, 5:7), 2, 2);
-
-tPitot = main.PITOT(:, 1);
-vPitot = main.PITOT(:, 3);
-
-% Air density
-[~, vSon, ~, rho] = atmosisa(altNas + alt0);
-
-% Mach number
-mach = velNas./vSon;
-
-% Normalize data
-timeRef = linspace(max([tNas(1), tAcc(1), tPitot(1)]), min([tNas(end), tAcc(end), tPitot(end)]) , NPOINTS);
-indexEndThrust = find(timeRef > timeThrust(end), 1, 'first');
-
-accXBRef = interp1(tAcc, accXB, timeRef);
-
-ThrustRef = zeros(1, NPOINTS);
-ThrustRef(1:indexEndThrust) = interp1(timeThrust, Thrust, timeRef(1:indexEndThrust));
-
-mRocket = (mMotor(end) + MSTRUCT) * ones(1, NPOINTS);
-mRocket(1:indexEndThrust) = interp1(timeThrust, mMotor, timeRef(1:indexEndThrust)) + MSTRUCT;
-
-rhoRef = interp1(tNas, rho, timeRef);
-
-velRef = interp1(tNas, movmean(velNas, 10), timeRef);
-
-velPitRef = interp1(tPitot, vPitot, timeRef);
-
-altRef = interp1(tNas, altNas, timeRef);
-
-% Compute CA
-CA = (ThrustRef - mRocket.*accXBRef) ./ (0.5 .* rhoRef .* velRef.^2 * AREF);
-
-CA_pitot = (ThrustRef - mRocket.*accXBRef) ./ (0.5 .* rhoRef .* velPitRef.^2 * AREF);
-
-tCO = tCO -1.8519;
-indexCO = find(ThrustRef == 0, 1, 'first');
-
-mRocketNoPwr = mRocket(indexCO:end);
-CANoPwr = CA(indexCO:end);
-CA_100ARB = zeros(1, length(CANoPwr));
-CA_0ARB = zeros(1, length(CANoPwr));
-
-for i = 1:length(CANoPwr)
- [~, indexMach] = nearestValSorted(MachRef, mach(i));
- [~, indexAlt] = nearestValSorted(AltRef, altRef(i));
- CA_100ARB(i) = CA_MD(indexMach, indexAlt, 3);
- CA_0ARB(i) = CA_MD(indexMach, indexAlt, 1);
end
-figure
-plot(timeRef(indexCO:end),CANoPwr);
-hold on
-plot(timeRef(indexCO:end), CA_pitot(indexCO:end));
-plot(timeRef(indexCO:end), CA_100ARB);
-plot(timeRef(indexCO:end), CA_0ARB);
-xlabel('Time [s]');
-ylabel('CA [-]');
-title('CA from telemetry');
-grid on
-legend('NAS', 'PITOT', '100% ARB', '0% ARB', 'Location','southoutside', 'Orientation', 'horizontal');
-
-
diff --git a/RoccarasoFlight/postprocessing/AFD/mainPostprocess.m b/RoccarasoFlight/postprocessing/AFD/mainPostprocess.m
index 8ce83195d867c22c18b6c0ed67be45b58b09dd0f..3616d5a4580deab3333a7d604fcc6a5dae1556b5 100644
--- a/RoccarasoFlight/postprocessing/AFD/mainPostprocess.m
+++ b/RoccarasoFlight/postprocessing/AFD/mainPostprocess.m
@@ -9,7 +9,7 @@ alt0 = 1414;
%% adding path and recall data
addpath("..\commonFunctions\");
-addpath("..\..\..\..\msa-toolkit\commonFunctions\miscellaneous\");
+addpath(genpath("..\..\..\..\msa-toolkit\commonFunctions\"));
main = importData('main');
%% Trajectory
@@ -21,8 +21,47 @@ end
%% CA Estimation
if opt.flagCA
- estimationCA;
+ res = estimationCA(main,alt0);
+
end
+%% TEST Simulation
+
+if opt.flagCA
+
+ indexCO = res.events.shutdonw;
+ indexOpeningARB = res.events.ARB_opening;
+
+ configSimPostp;
+
+ % CONTINUE
+ Thrust = res.Thrust(1:indexCO);
+ Thrust(end) = 0;
+ timeThrust = res.time(2:indexCO);
+ timeThrust = [0, timeThrust];
+
+ settings.motor.expM = res.mass.propMass(1:indexCO);
+ settings.motor.Pe = reshapeVector(timeThrust, settings.motor.expTime, settings.motor.Pe);
+ settings.mTotalTime = res.mass.rocketMass(1:indexCO);
+ settings.ms = res.mass.rocketMass(end);
+ settings.xcg = reshapeVector(timeThrust, settings.motor.expTime, settings.xcg);
+ settings.Ixx = reshapeVector(timeThrust, settings.motor.expTime, settings.Ixx);
+ settings.Iyy = reshapeVector(timeThrust, settings.motor.expTime, settings.Iyy);
+ settings.Izz = reshapeVector(timeThrust, settings.motor.expTime, settings.Izz);
+ settings.I = [settings.Ixx; settings.Iyy; settings.Izz];
+
+ %%% Inertias derivatives (avoiding calculations in ascent.m)
+ settings.Idot = diff(settings.I')'./diff(timeThrust);
+ settings.Idot(:, end+1) = settings.Idot(:, end);
+
+ settings.State.xcgTime = settings.State.xcgTime * timeThrust(end)/settings.State.xcgTime(end);
+
+ settings.motor.expTime = timeThrust;
+ settings.motor.expThrust = Thrust;
+ settings.tb = settings.motor.expTime(end);
+ settings.tControl = settings.tb;
+
+ [Tf, Yf, Ta, Ya, bound_value] = stdRun(settings);
+end
diff --git a/RoccarasoFlight/postprocessing/AFD/sensorPitot.mat b/RoccarasoFlight/postprocessing/AFD/sensorPitot.mat
new file mode 100644
index 0000000000000000000000000000000000000000..3519293201d763415582910d6409c41a8273a728
Binary files /dev/null and b/RoccarasoFlight/postprocessing/AFD/sensorPitot.mat differ