[coeff-transport] mainAutoMatProtub now exports Coefficient class directly

autoMatricesProtub/mainAutoMatProtub.m

-function [coeffsTot, coeffsTotHighAOA] = mainAutoMatProtub(rocket, environment, settings, options)
+function [coeffsOut, coeffsOutHighAOA] = mainAutoMatProtub(rocket, environment, settings, options)
 arguments
     rocket = []; % Empty by default
     environment Environment = Environment.empty
@@ -98,12 +98,13 @@ input = createDissileInput(rocket, autoMatSettings.vars);
 [coeffsTot, finsCN] = dissileMatcom(input);
 
 %% SAVE DATA
-if options.saveVars
-    saveVars(autoMatSettings.varsHighAOA, rocket, mission, coeffsTotHighAOA, finsCNHighAOA, ...
-        chosenXcg, autoMatSettings.saveFinsCN, 'aeroCoefficientsHighAOA.mat');
-    saveVars(autoMatSettings.vars, rocket, mission, coeffsTot, finsCN, ...
-        chosenXcg, autoMatSettings.saveFinsCN, 'aeroCoefficients.mat');
-end
+
+coeffsOut = exportVars( ...
+    autoMatSettings.varsHighAOA, rocket, mission, coeffsTotHighAOA, finsCNHighAOA, chosenXcg, ...
+    autoMatSettings.saveFinsCN, options.saveVars, 'aeroCoefficientsHighAOA.mat');
+coeffsOutHighAOA = exportVars( ...
+    autoMatSettings.vars, rocket, mission, coeffsTot, finsCN, chosenXcg, ...
+    autoMatSettings.saveFinsCN, options.saveVars, 'aeroCoefficients.mat');
 
 AMtime = toc;
 fprintf('Aerodynamics Prediction completed \n')

autoMatricesProtub/src/saveVars.m → autoMatricesProtub/src/exportVars.m

-function saveVars(vars, rocket, mission, total, finsCN, chosenXcg, saveFinsCN, outputName)
+function coeffs = exportVars(vars, rocket, mission, total, finsCN, chosenXcg, ...
+    saveFinsCN, saveToFile, outputName)
 
 arguments
     vars 
@@ -8,6 +9,7 @@ arguments
     finsCN 
     chosenXcg 
     saveFinsCN 
+    saveToFile
     outputName 
 end
 
@@ -40,14 +42,34 @@ if strcmp(rocket.parafoil.noseType,'MHAACK')
         geometry.cMod = rocket.parafoil.noseCMod;
         geometry.pMod = rocket.parafoil.nosePMod;
     else
-        error('parafoil.pMod and/or parafoil.cMod are not defined; check simulationsData')
+        error('parafoil.pMod and/or parafoil.cMod are not defined; check rocketConfig')
     end
 end
 
 geometry.xcg = chosenXcg;
 
+
 %% CREATING OUTPUT
 outputPath = fullfile(mission.dataPath, outputName);
+
+if rocket.dynamicDerivatives, fieldName = rocket.motor.name;
+    else, fieldName = 'generic';
+end
+
+if saveFinsCN
+    finsCN = squeeze(finsCN(1, :, :, :, :, :)); % Consider only the first xcg bc fins CN is xcg-independent
+else
+    finsCN = [];
+end
+
+coeffs = Coefficient();
+coeffs.state = state;
+coeffs.total = total;
+coeffs.geometry = geometry;
+coeffs.finsCN = finsCN;
+
+if saveToFile
+    % Save files as struct to allow exporting
     output = struct();
 
     if ~isfile(outputPath)
@@ -56,20 +78,12 @@ else
         save(outputPath, '-struct', 'output', '-append')
     end
 
-if rocket.dynamicDerivatives, fieldName = rocket.motor.name;
-    else, fieldName = 'generic';
-end
-
     output.(fieldName) = struct();
     output.(fieldName).state = state;
     output.(fieldName).total = total;
     output.(fieldName).geometry = geometry;
-output.(fieldName).finsCN = [];
-
-if saveFinsCN
-    finsCN = squeeze(finsCN(1, :, :, :, :, :)); % Consider only the first xcg bc fins CN is xcg-independent
     output.(fieldName).finsCN = finsCN;
-end
 
-save(outputPath, '-struct', 'output', '-append')
+    save(outputPath, '-struct', 'output', '-append'); 
+end
 end
\ No newline at end of file