[ca-analysis] Added CaAnalisys

autoMatricesProtub/mainAutoMatProtub.m

@@ -87,9 +87,9 @@ input = createDissileInput(rocket, autoMatSettings.vars);
 
 %% SAVE DATA
 saveVars(autoMatSettings.varsHighAOA, rocket, mission, coeffsTotHighAOA, finsCNHighAOA, ...
-    chosenXcg, xcgTime, autoMatSettings.saveFinsCN, 'aeroCoefficientsHighAOA.mat');
+    chosenXcg, xcgTime, autoMatSettings.saveFinsCN, 'aeroCoefficientsHighAOA');
 saveVars(autoMatSettings.vars, rocket, mission, coeffsTot, finsCN, ...
-    chosenXcg, xcgTime, autoMatSettings.saveFinsCN, 'aeroCoefficients.mat');
+    chosenXcg, xcgTime, autoMatSettings.saveFinsCN, 'aeroCoefficients');
 AMtime = toc;
 
 fprintf('Aerodynamics Prediction completed \n')

sensitivityAnalysis/mainSensitivity.m

-function [postpAsc, postpDescPara, postpDescBall, postpStab, postpLaunchMode, parameters] = ...
+function [postpAsc, postpDescPara, postpDescBall, postpStab, postpLaunchMode] = ...
     mainSensitivity(postpAsc, postpDescPara, postpDescBall, postpStab, postpLaunchMode, rocket, wind, environment)
 arguments
     postpAsc        = struct.empty();

sensitivityAnalysis/src/postprocess/postprocessAscent.m

@@ -163,7 +163,6 @@ for i = 1:N
     % checking where the missile is undocked from the hook of the launch pad
     iApogee = sim.state.iEvent;
     iExit = find(-sim.state.Y(3, :) > rampAltitude, 1, "first");
-    iSMExit = find(~isnan(sim.coeff.XCPtot), 1, "first");
     %iExit = iExit(end)+1;
 
     % apogee point
@@ -192,7 +191,7 @@ for i = 1:N
     % is not obtained trough extrapolation from aerodynamic matrices
     [SM_min, iMin] = min(sim.coeff.XCPtot);
     [SM_max, iMax] = max(sim.coeff.XCPtot);
-    SM_exit = sim.coeff.XCPtot(iSMExit);
+    SM_exit = sim.coeff.XCPtot(iExit);
 
     cMin = ( (sim.interp.alpha(iMin) > state.alphas(1)*pi/180*tollAngle) && (sim.interp.alpha(iMin) < state.alphas(end)*pi/180*tollAngle) ) &&...
         ( (sim.interp.beta(iMin) > state.betas(1)*pi/180*tollAngle) && (sim.interp.beta(iMin) < state.betas(end)*pi/180*tollAngle) );
@@ -203,9 +202,12 @@ for i = 1:N
     cExt = ( (sim.interp.alpha(iExit) > state.alphas(1)*pi/180*tollAngle) && (sim.interp.alpha(iExit) < state.alphas(end)*pi/180*tollAngle) ) &&...
         ( (sim.interp.beta(iExit) > state.betas(1)*pi/180*tollAngle) && (sim.interp.beta(iExit) < state.betas(end)*pi/180*tollAngle) );
 
-    % if not(cMin), SM_min = nan; end
-    % if not(cMax), SM_max = nan; end
-    % if not(cExt), SM_exit = nan; end
+    if not(cMin) || not(cMax) || not(cExt)
+        warning('The flight envelope is not fully included in the flight conditions in autoMatrices')
+    end
+    if not(cMin), SM_min = nan; end
+    if not(cMax), SM_max = nan; end
+    if not(cExt), SM_exit = nan; end
 
     SM(:, i) = [SM_min; SM_max; SM_exit];