Erick
146 lines
4.5 KiB
Matlab
146 lines
4.5 KiB
Matlab
clear all;
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%% Initializing VI files
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addpath_vicrt_20;
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cfg = createCfg('vicrt_cdb.cfg');
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systemFile = 'file://C:/Users/ashwi/Desktop/VIgrade/MMRtestVehicle.xml';
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modelDirFiles='crtWork';
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systemStruct = generateSystemStruct(systemFile,cfg,modelDirFiles);
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baseFingerprint='fingerprintSLT.xml';
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%% Inputs
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aeroBalF = .2:0.01:.32;
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aeroBalR = ones(size(aeroBalF)) - aeroBalF;
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df = 495.4;
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aeroFile = 'C:\Program Files\VI-grade\VI-CarRealTime 20\acarrt\MMR_2019.cdb\aero_forces.tbl\MMR_2019_aero.aer';
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%% Output arrays
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laptime = NaN(size(aeroBalF));
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pitchAng = NaN(size(aeroBalF));
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u = cell(size(aeroBalF));
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Faf = cell(size(aeroBalF));
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Far = cell(size(aeroBalF));
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gear = cell(size(aeroBalF));
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%% Batch Simulations
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for i = 1:length(aeroBalF)
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fdf = df .* aeroBalF(i);
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rdf = df .* aeroBalR(i);
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Parse_aero(aeroFile,fdf, rdf);
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[successFlag, outputNameList]=runViCrt(baseFingerprint,systemStruct,'work',modelDirFiles);
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split = regexp(outputNameList{1, 1} , '\', 'split');
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ResFile = strcat(split{1,2},'.csv');
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OUT{i} = readtable(ResFile);
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laptime(i) = OUT{i}.xTime(end);
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pitchAng(i) = mean(OUT{i}.Chassis_Pospitch);
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u{i} = OUT{i}.Speed;
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Faf{i} = OUT{i}.Aero_DownForceF;
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Far{i} = OUT{i}.Aero_DownForceR;
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gear{i} = OUT{i}.Driver_Gear;
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X{i} = OUT{i}.X;
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Y{i} = OUT{i}.Y;
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s(i) = OUT{i}.S(end);
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end
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%% Plots
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% Laptime
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figure(1)
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clf
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b = bar(aeroBalF,laptime,'BarWidth',0.7 );
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text(b.XEndPoints,b.YEndPoints,string(b.YEndPoints),'HorizontalAlignment','center',...
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'VerticalAlignment','bottom');
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ylim([min(laptime)-1 max(laptime)+1]);
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title('Laptime')
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xlabel('Aero balance- Front [*100%]')
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ylabel('Laptime [s]')
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grid on;
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% Speed map
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figure(2)
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clf
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for i = 1:length(aeroBalF)
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ax(i) = subplot(round(length(aeroBalF)/2),2,i);
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h = surf([X{i} X{i}],[Y{i} Y{i}],zeros(size([Y{i} Y{i}])),[u{i} u{i}],'EdgeColor','interp');
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title(strjoin({'Velocity maps | Front aero distribution=', sprintf('%d',aeroBalF(i)*100),'%'}));
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hold on
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plot(X{i}(1),Y{i}(1),'+')
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hold on
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idx = find(abs(diff(OUT{i}.Driver_Gear))) + 1; % gear change index
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plot(X{i}(idx),Y{i}(idx),'d')
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gearNum = cellstr(num2str(OUT{i}.Driver_Gear(idx)));
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text(X{i}(idx)+0.1,Y{i}(idx)+3, gearNum,'FontSize',8);
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[maxu(i),idxu] = max(u{i});
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maxuc = cellstr(num2str(maxu(i)));
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%text(X{i}(idxu),Y{i}(idxu), maxuc,'FontSize',14,'Color','r');
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h.LineWidth = 2;
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%h.DisplayName = 'Front aero dist: %.3f %',aeroBalF(i)*100;
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colormap('turbo')
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colorbar;
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view(2)
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end
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linkaxes(ax,'xy')
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% Brake maps
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figure(3)
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clf
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for i = 1:length(aeroBalF)
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ax(i) = subplot(round(length(aeroBalF)/2),2,i);
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h = surf([X{i} X{i}],[Y{i} Y{i}],zeros(size([Y{i} Y{i}])),[OUT{i}.Driver_Brake OUT{i}.Driver_Brake],'EdgeColor','interp');
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title(strjoin({'Brake % | Front aero distribution=', sprintf('%d',aeroBalF(i)*100),'%'}));
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view(2)
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h.LineWidth = 2;
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colorbar;
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colormap('turbo')
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end
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linkaxes(ax,'xy')
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% Throtle maps
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figure(4)
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clf
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for i = 1:length(aeroBalF)
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ax(i) = subplot(round(length(aeroBalF)/2),2,i);
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h = surf([X{i} X{i}],[Y{i} Y{i}],zeros(size([Y{i} Y{i}])),[OUT{i}.Driver_Brake OUT{i}.Driver_Throttle],'EdgeColor','interp');
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title(strjoin({'Throttle % | Front aero distribution=', sprintf('%d',aeroBalF(i)*100),'%'}));
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view(2)
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h.LineWidth = 2;
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colorbar;
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colormap('turbo')
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end
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linkaxes(ax,'xy')
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%% Functions
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function Parse_aero(aeroFile,fdf, rdf)
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A = fileread(aeroFile);
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C = regexp(A, '\n', 'split');
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C{1, 39} = sprintf('0 %.3f %.3f %.3f %.3f %.3f %.3f', fdf, fdf ,fdf ,fdf ,fdf, fdf);
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C{1, 40} = sprintf('25 %.3f %.3f %.3f %.3f %.3f %.3f', fdf, fdf ,fdf ,fdf ,fdf, fdf);
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C{1, 41} = sprintf('50 %.3f %.3f %.3f %.3f %.3f %.3f', fdf, fdf ,fdf ,fdf ,fdf, fdf);
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C{1, 42} = sprintf('75 %.3f %.3f %.3f %.3f %.3f %.3f', fdf, fdf ,fdf ,fdf ,fdf, fdf);
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C{1, 43} = sprintf('100 %.3f %.3f %.3f %.3f %.3f %.3f', fdf, fdf ,fdf ,fdf ,fdf, fdf);
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C{1, 55} = sprintf('0 %.3f %.3f %.3f %.3f %.3f %.3f', rdf, rdf ,rdf ,rdf ,rdf, rdf);
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C{1, 56} = sprintf('25 %.3f %.3f %.3f %.3f %.3f %.3f', rdf, rdf ,rdf ,rdf ,rdf, rdf);
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C{1, 57} = sprintf('50 %.3f %.3f %.3f %.3f %.3f %.3f', rdf, rdf ,rdf ,rdf ,rdf, rdf);
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C{1, 58} = sprintf('75 %.3f %.3f %.3f %.3f %.3f %.3f', rdf, rdf ,rdf ,rdf ,rdf, rdf);
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C{1, 59} = sprintf('100 %.3f %.3f %.3f %.3f %.3f %.3f', rdf, rdf ,rdf ,rdf ,rdf, rdf);
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combinedStr = strjoin(C,'\n');
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fprintf(1,'fdf = %.3f\trdf = %.3f\n',fdf,rdf)
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% Save file
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fid = fopen(aeroFile, 'w+');
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fprintf(fid, combinedStr);
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fclose(fid);
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end |