*ARCHIVED* development moved to aircraft-studio.
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close all;
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force = 8000; % lbs
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stringer_A = 0.5; % in^2
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thickness = 0.04; % in
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top_stringers_y = 6; % in
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middle_stringers_y = 2; % in
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I = 2*stringer_A*top_stringers_y^2 + 2*stringer_A*middle_stringers_y^2;
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% solve for shear stress distribution. this calc ignores the thickness of
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% the web between teh stringers(stringers)
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% V / (*) * int(*)
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shear_top_web = force / (*) * top_stringers_y * stringer_A;
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shear_middle_web = shear_top_web + (/(*)**);
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figure; grid on; hold on;set(,'color',[111]);
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plot([shear_top_web],[top_stringers_y],'linewidth',2);
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plot([shear_middle_web],[-middle_stringers_y],'linewidth',2);
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plot([shear_top_web],[--],'linewidth',2);
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plot([0shear_top_web],[top_stringers_y],'linewidth',2);
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plot([0shear_top_web],[--],'linewidth',2);
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plot([shear_top_web],[middle_stringers_y],'linewidth',2);
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plot([shear_top_web],[--],'linewidth',2);
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xlabel('shear stress (lb/in^2)','fontsize',16,'fontweight','bold');ylabel('Distance from Center (in)','fontsize',16,'fontweight','bold')
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set(,'FontSize',16,'fontweight','bold');
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%Alternate approach.. compute change in bending stress at each stringer to
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%find the change in shear load
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%at top stringer
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d_sigma = force * top_stringers_y / I; %(/in^2)
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d_force_top = d_sigma * stringer_A;
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%at middle stringer..
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d_sigma = force * middle_stringers_y / I; %(/in^2)
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d_force_middle = d_force_top + d_sigma*stringer_A;
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%check if load balances
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check_load = 2*d_force_top*4 + d_force_middle*4;
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