Dashboard and trajectory simulation

gtm_design/OscillatorySpin.asv

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+%% --------------------- Oscillatory Trajectory Simulation --------------------------
+%
+% This MATLAB script models a targeted oscillatory spin condition for a GTM_T2 aircraft, 
+% simulates the trajectory from that condition, and plots various flight 
+% parameters over time.
+%
+% Simulation Details:
+% - The script begins by initializing the simulation with nominal design conditions for 
+%   a GTM_T2 aircraft.
+% - It then proceeds to set up conditions for an oscillatory spin as specified in
+%   init_spin_design function.
+% - The trajectory is simulated for a duration of 100 seconds.
+% - The resulting trajectory is plotted, showing the behavior of key flight parameters 
+%   such as alpha, beta, flight path angle, airspeed, angular rates, and Euler angles 
+%   over time.
+% - The trajectory is also visualized in a 3D plot with an orientated aircraft shape.
+%
+%
+%% About
+%
+% Author:     Omar Mourad
+% Email:      <mailto: st181901@stud.uni-stuttgart.de>
+% Created:    20.03.2024 
+
+
+%% Conditions
+
+% Start with some altitude,otherwise nominal init
+MWS = init_design('GTM_T2');
+loadmws(MWS,'gtm_design');
+printStates(MWS);
+
+% Proceed with the oscillatory spin conditions
+MWS = init_spin_design('GTM_T2');
+printStates(MWS);
+loadmws(MWS,'gtm_design');
+
+%% Simulate
+%Determine the Simulation time (in Secs)
+time_of_simulation = 10; 
+[t,x,y]=sim('gtm_design',[0 time_of_simulation]); 
+
+%% Convert from lat/lon to ft 
+Xeom=y(:,7:18);
+dist_lat=(Xeom(:,7)-Xeom(1,7)) * 180/pi*364100.79;
+dist_lon=(Xeom(:,8)-Xeom(1,8)) * 180/pi*291925.24;
+alt=Xeom(:,9);
+tplot=[0:.1:max(t)];
+
+%% Save the data to file
+save('simulationData.mat', 't', 'y', 'Xeom', 'dist_lat', 'dist_lon', 'alt');
+
+%% Define simple airplane shape
+scale=1;
+x1=scale*([0.0,-.5, -2.0, -3.0,-4.0, -3.25, -5.5, -6.0, -6.0]+3.0);
+y1=scale*[0.0, 0.5,  0.5, 4.25, 4.5,  0.5,   0.5,  1.5,  0.0];
+Vehicletop=[ [x1,fliplr(x1)]; [y1,fliplr(-y1)]; -.01*ones(1,2*length(x1))];
+Vehiclebot=[ [x1,fliplr(x1)]; [y1,fliplr(-y1)];  .01*ones(1,2*length(x1))];
+
+
+%%NEW PLOTS
+% Interpolate data to match the tplot timeline
+X_ani = interp1(t, Xeom, tplot);
+Y_ani = interp1(t, y(:,1:5), tplot);
+lat_ani = interp1(t, dist_lat, tplot);
+lon_ani = interp1(t, dist_lon, tplot);
+alt_ani = interp1(t, alt, tplot);
+
+%% Setup Dynamic Plots
+h = figure(1);
+set(h, 'Position', [20, 20, 1200, 800]);
+clf;
+
+% Alpha/Beta Plot Initialization
+%hAlphaBeta = subplot(4, 2, 1);
+axes('position',[.1 .75 .23 .13])
+pAlpha = plot(tplot(1), X_ani(1, 3), 'r', 'LineWidth', 1.5); % Alpha
+hold on;
+pBeta = plot(hAlphaBeta, tplot(1), X_ani(1, 4), 'b', 'LineWidth', 1.5); % Beta
+grid on;
+legend({'\alpha', '\beta'}, 'Location', 'SouthEast');
+xlabel('Time (sec)');
+ylabel('\alpha (deg), \beta (deg)');
+title('Alpha/Beta');
+ylim([-50 50]);
+
+% Flight Path and Airspeed Initialization
+%hFlightPath = subplot(4, 2, 2);
+axes('position',[.1 .55 .23 .13])
+hGamma = plot(tplot(1), Y_ani(1, 5), 'r', 'LineWidth', 1.5); % Gamma
+hold on;
+hEAS = plot(hFlightPath, tplot(1), Y_ani(1, 1), 'b', 'LineWidth', 1.5); % Air-Speed
+grid on;
+legend({'\gamma', 'EAS'}, 'Location', 'SouthEast');
+xlabel('Time (sec)');
+ylabel('\gamma (deg), Equivalent Airspeed (knots)');
+title('Flight Path Angle and Airspeed');
+
+% Angular Rates Plot Initialization
+hAngularRates = subplot(4, 2, 3);
+axes('position',[.1 .35 .23 .13])
+pP = plot(hAngularRates, tplot(1), X_ani(1, 4) * 180 / pi, 'r', 'LineWidth', 1.5); % p
+hold on;
+pQ = plot(hAngularRates, tplot(1), X_ani(1, 5) * 180 / pi, 'g', 'LineWidth', 1.5); % q
+pR = plot(hAngularRates, tplot(1), X_ani(1, 6) * 180 / pi, 'b', 'LineWidth', 1.5); % r
+legend({'p', 'q', 'r'}, 'Location', 'SouthEast');
+xlabel('Time (sec)');
+ylabel('Angular Rates (deg/sec)');
+title('Angular Rates');
+grid on;
+
+% Euler Angles Plot Initialization
+hEulerAngles = subplot(4, 2, 4);
+pRoll = plot(hEulerAngles, tplot(1), X_ani(1, 10) * 180 / pi, 'r', 'LineWidth', 1.5); % Roll (phi)
+hold on;
+pPitch = plot(hEulerAngles, tplot(1), X_ani(1, 11) * 180 / pi, 'g', 'LineWidth', 1.5); % Pitch (theta)
+pYaw = plot(hEulerAngles, tplot(1), X_ani(1, 12) * 180 / pi, 'b', 'LineWidth', 1.5); % Yaw (psi)
+legend({'Roll', 'Pitch', 'Yaw'}, 'Location', 'NorthEast');
+xlabel('Time (sec)');
+ylabel('\phi (deg), \theta (deg), \psi (deg)');
+title('Euler Angles');
+grid on;
+
+% 3D Trajectory Plot Initialization
+hTrajectory = subplot(4, 2, [6 7]);
+plot3(hTrajectory, dist_lat, dist_lon, alt, 'k', 'LineWidth', 1.5); % Entire Trajectory
+hold on;
+h3DAircraft = plot3(hTrajectory, lat_ani(1), lon_ani(1), alt_ani(1), 'ro', 'MarkerSize', 8, 'MarkerFaceColor', 'r');
+grid on;
+xlabel('Lat. Crossrange (ft)');
+ylabel('Long. Crossrange (ft)');
+zlabel('Altitude (ft)');
+title('3D Oscillatory Spin Trajectory');
+view([25, 10]);
+
+%% Start Dynamic Plot Updates
+for i = 1:length(tplot)
+    % Update Alpha/Beta plot
+    set(pAlpha, 'XData', tplot(1:i), 'YData', X_ani(1:i, 3));
+    set(pBeta, 'XData', tplot(1:i), 'YData', X_ani(1:i, 4));
+
+    % Update Flight Path and Airspeed plot
+    set(hGamma, 'XData', tplot(1:i), 'YData', Y_ani(1:i, 5));
+    set(hEAS, 'XData', tplot(1:i), 'YData', Y_ani(1:i, 1));
+
+    % Update Angular Rates plot
+    set(pP, 'XData', tplot(1:i), 'YData', X_ani(1:i, 4) * 180 / pi);
+    set(pQ, 'XData', tplot(1:i), 'YData', X_ani(1:i, 5) * 180 / pi);
+    set(pR, 'XData', tplot(1:i), 'YData', X_ani(1:i, 6) * 180 / pi);
+
+    % Update Euler Angles plot
+    set(pRoll, 'XData', tplot(1:i), 'YData', X_ani(1:i, 10) * 180 / pi);
+    set(pPitch, 'XData', tplot(1:i), 'YData', X_ani(1:i, 11) * 180 / pi);
+    set(pYaw, 'XData', tplot(1:i), 'YData', X_ani(1:i, 12) * 180 / pi);
+
+    % Update 3D Trajectory plot
+    set(h3DAircraft, 'XData', lat_ani(i), 'YData', lon_ani(i), 'ZData', alt_ani(i));
+
+    % Plot Aircraft Shape at Current Position
+    % Top View
+    fill3(Vehicletop(1,:) + lat_ani(i), Vehicletop(2,:) + lon_ani(i), Vehicletop(3,:) + alt_ani(i), 'r', 'FaceAlpha', 0.5);
+    % Bottom View
+    fill3(Vehiclebot(1,:) + lat_ani(i), Vehiclebot(2,:) + lon_ani(i), Vehiclebot(3,:) + alt_ani(i), 'b', 'FaceAlpha', 0.5);
+
+    % Pause for animation effect
+    pause(0.1);
+end
+
+
+
+% %% ------------------------Plots---------------------------
+% h=figure(1);,set(h,'Position',[20,20,1200,800]);clf
+% 
+% % Alpha/Beta
+% axes('position',[.1 .75 .23 .13])
+% plot(t,[y(:,3),y(:,4)]); % y(:,3) ----> Alphas // y(:,4) ----> Betas
+% legend({'\alpha','\beta'},'Location','SouthEast');,grid on
+% xlabel('time (sec)'),
+% ylabel('\alpha (deg), \beta (deg)');
+% title('Alpha/Beta');
+% 
+% % Flight Path Angle and Airspeed
+% axes('position',[.1 .55 .23 .13])
+% [ax,h1,h2]=plotyy(t,y(:,5),t,y(:,1));grid on % y(:,5) ----> Gammas //
+% xlabel('time (sec)'),                        % %y(:,1) ----> Airspeeds
+% ylabel(ax(1),'Flight Path,  \gamma (deg)');
+% ylabel(ax(2),'Equivalent Airspeed (konts)')
+% legend([h1;h2],{'\gamma','eas'},'Location','SouthEast');
+% title('Flight Path Angle and Airspeed');
+% 
+% % Angular Rates
+% axes('position',[.1 .35 .23 .13])
+% plot(t,Xeom(:,4:6)*180/pi);grid on
+% legend({ 'p','q','r'},'Location','SouthEast');
+% xlabel('time (sec)'),ylabel('angular rates (deg/sec)')
+% title('Angular Rates');
+% 
+% % Euler Angles
+% axes('position',[.1 .15 .23 .13]);
+% plot(t,[y(:,16)*180/pi, y(:,17)*180/pi, y(:,18)*180/pi]);
+% % y(:,16) ---> Phi  // y(:,17) ---> Theta // y(:,18) ---> Psi
+% legend({'roll','pitch','yaw'},'Location','NorthEast');,grid on
+% xlabel('time (sec)');
+% ylabel('\phi (deg), \theta (deg), \psi (deg)');
+% title('Euler Angles');
+% 
+% % Trajectory: 3D plot with orientated vehicle
+% axes('position',[.45,.15,.5,.7])
+% plot3(dist_lat,dist_lon,alt);grid on, axset=axis; % Just get axis limits
+% %cnt=0;
+% % resample at equally spaced points for animation plot
+% tplot=[0:.1:max(t)];
+% X_ani=interp1(t,Xeom,tplot);
+% lat_ani=interp1(t,dist_lat,tplot);
+% lon_ani=interp1(t,dist_lon,tplot);
+% alt_ani=interp1(t,alt,tplot);
+% tic
+% for i=[1:length(tplot)]
+%   plot3(dist_lat,dist_lon,alt);grid on
+%   Offset=repmat([lat_ani(i);lon_ani(i);alt_ani(i)],1,size(Vehicletop,2));
+%   Ptmp=diag([1,1,-1])*transpose(euler321(X_ani(i,10:12)))*Vehicletop + Offset;
+%   patch(Ptmp(1,:),Ptmp(2,:),Ptmp(3,:),'g');
+%   Ptmp=diag([1,1,-1])*transpose(euler321(X_ani(i,10:12)))*Vehiclebot + Offset;
+%   patch(Ptmp(1,:),Ptmp(2,:),Ptmp(3,:),'c');
+%   view(25,10),axis(axset),hold off
+%   xlabel('Lat. Crossrange(ft)');
+%   ylabel('Long. Crossrange(ft)');
+%   zlabel('Altitude(ft)');
+%   title('Simulation of Oscillatory Spin Trajectory');
+%   pause(.1);
+% end
+% toc
+% if(exist('AutoRun','var'))
+%     pause(.2);
+%     orient portrait; print -dpng OscillatorySpin;
+% end
+% 

gtm_design/OscillatorySpin.m

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+%% --------------------- Oscillatory Trajectory Simulation --------------------------
+%
+% This MATLAB script models a targeted oscillatory spin condition for a GTM_T2 aircraft, 
+% simulates the trajectory from that condition, and plots various flight 
+% parameters over time.
+%
+% Simulation Details:
+% - The script begins by initializing the simulation with nominal design conditions for 
+%   a GTM_T2 aircraft.
+% - It then proceeds to set up conditions for an oscillatory spin as specified in
+%   init_spin_design function.
+% - The trajectory is simulated for a duration of 100 seconds.
+% - The resulting trajectory is plotted, showing the behavior of key flight parameters 
+%   such as alpha, beta, flight path angle, airspeed, angular rates, and Euler angles 
+%   over time.
+% - The trajectory is also visualized in a 3D plot with an orientated aircraft shape.
+%
+%
+%% About
+%
+% Author:     Omar Mourad
+% Email:      <mailto: st181901@stud.uni-stuttgart.de>
+% Created:    20.03.2024 
+
+
+%% Conditions
+
+% Start with some altitude,otherwise nominal init
+MWS = init_design('GTM_T2');
+loadmws(MWS,'gtm_design');
+printStates(MWS);
+
+% Proceed with the oscillatory spin conditions
+MWS = init_spin_design('GTM_T2');
+printStates(MWS);
+loadmws(MWS,'gtm_design');
+
+%% Simulate
+%Determine the Simulation time (in Secs)
+time_of_simulation = 100; 
+[t,x,y]=sim('gtm_design',[0 time_of_simulation]); 
+
+%% Convert from lat/lon to ft 
+Xeom=y(:,7:18);
+dist_lat=(Xeom(:,7)-Xeom(1,7)) * 180/pi*364100.79;
+dist_lon=(Xeom(:,8)-Xeom(1,8)) * 180/pi*291925.24;
+alt=Xeom(:,9);
+tplot=0:.1:max(t);
+
+%% Save the data to file
+save('OscillatorySpinData.mat','t', 'tplot' , 'y', 'Xeom', 'dist_lat', 'dist_lon', 'alt');

gtm_design/SteepSpiral.m

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+%% --------------------- Steep Spiral Trajectory Simulation --------------------------
+%
+% This MATLAB script models a targeted steep spiral condition for a GTM_T2 aircraft, 
+% simulates the trajectory from that condition, and plots various flight 
+% parameters over time.
+%
+% Simulation Details:
+% - The script begins by initializing the simulation with nominal design conditions for 
+%   a GTM_T2 aircraft.
+% - It then proceeds to set up conditions for a steep spiral as specified in
+%   init_spiral_design function.
+% - The trajectory is simulated for a duration of 100 seconds.
+% - The resulting trajectory is plotted, showing the behavior of key flight parameters 
+%   such as alpha, beta, flight path angle, airspeed, angular rates, and Euler angles 
+%   over time.
+% - The trajectory is also visualized in a 3D plot with an orientated aircraft shape.
+%
+%
+%% About
+%
+% Author:     Omar Mourad
+% Email:      <mailto: st181901@stud.uni-stuttgart.de>
+% Created:    15.03.2024 
+
+
+%% Conditions
+
+% Start with some altitude,otherwise nominal init
+MWS = init_design('GTM_T2');
+loadmws(MWS,'gtm_design');
+printStates(MWS);
+
+% Proceed with the steep spiral conditions
+MWS = init_spiral_design('GTM_T2');
+printStates(MWS);
+loadmws(MWS,'gtm_design');
+
+%% Simulate
+%Determine the Simulation time (in Secs)
+time_of_simulation = 100;    
+[t,x,y]=sim('gtm_design',[0 time_of_simulation]); 
+intermediate = y;
+%% Convert from lat/lon to ft 
+Xeom=y(:,7:18);
+dist_lat=(Xeom(:,7)-Xeom(1,7)) * 180/pi*364100.79;
+dist_lon=(Xeom(:,8)-Xeom(1,8)) * 180/pi*291925.24;
+alt=Xeom(:,9);
+tplot=0:.1:max(t);
+
+%% Save the data to file
+save('SteepSpiralData.mat','t', 'tplot' , 'y', 'Xeom', 'dist_lat', 'dist_lon', 'alt');