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Hi Good Afternoon. Can someone help me with my genetic algorithm in matlab , unfortunately it is not working but the structure is right I think . I need it to work in order to see the pareto front 3D and the performance of the constraints please. I would be very grateful if you could. The constraints are these and the objective functions are also written correctly. Note this is a personal project not an assignment! King regards MATLAB CODE: % Define decision variables, objectives, and constraints nvars = 56; % number of decision variables nobj = 8; % number of objectives ncon = 56; % number of constraints % Set up genetic algorithm options options = optimoptions('ga', ...   'PopulationSize', 100, ...   'MaxGenerations', 100, ...   'MutationFcn', {@mutationuniform, 0.05}, ...   'CrossoverFcn', @crossoverarithmetic); % Define the objective functions to maximize and minimize f = @(x) [=((Fn/m0)*V0)/(1+f+Fab)*((V9^2)/2)-((V0^2)/2), ((Fn/m0)*V0)/(f*QR*NB), -1-(1/(T1/T0)), m0*V0]; g = @(x) [-((f/(Fn/m0)), -(10^13)*(p3/(1.4*(10^6)))*exp(-71442/Tpz)*(7.56*(o^7.2)-1.6)*(t^0.64)), -(WT0*(1-(WF/WTO)-(WE/WTO))),-(WTO-WLanding), -(WT0*(1-(WF/WTO)-(WE/WTO))), -WPL/WC, -M/(TSFC/Fn)]; % Define your own constraint functions myCon1 = @(x) f=>1;      % f= fuel to air ratio myCon2 = @(x) Fn=>1;     % Fn= net thurst myCon3 = @(x) m0=>1;     % m0= air mass flow rate  myCon4 = @(x) p3=>1;     % p3=inlet pressure myCon5 = @(x) Tpz=>1;    % Tpz=primary zone temperature myCon6 = @(x) o=>1;     % o=equivalence ratio myCon7 = @(x t=>1;      % t=residence time myCon8 = @(x) aa=>1;     % aa=pressure term myCon9 = @(x) WTO=>1;    % Wto=take off weight myCon10 = @(x) WLanding=>1;    ; % Wlanding=landing weight myCon11 = @(x)  WF=>1;    % Wf=fuel weight myCon12 = @(x) WE=>1;    % WE=empty weight myCon13 = @(x) WPL=>1;    ;    % Wpl=payload weight myCon14 = @(x) WC==>1;         % Wc=crew weight myCon15 = @(x)  M==>1;          % Fuel load mass myCon16 = @(x) Fab=>1;    % afterburner fuel-to-air ratio myCon17 = @(x) V9=>1;    % exhaust velocity myCon18 = @(x) V0=>1;    % cruising speed myCon19 = @(x) QR=>1;    % fuel heating value myCon20 = @(x) NB=>1;    % burner efficiency myCon21 = @(x) T1=>1;    % inlet temperature myCon22 = @(x) T0=>1;    % ambient static temperature  myCon23 = @(x) L=>1;    % lift myCon24= @(x) p=>1;    % density myCon25= @(x) V=>1;    % velocity myCon26 = @(x)  A=>1;    % wing area myCon27 = @(x) bw=>1;    % wing span myCon28 = @(x) sw=>1;    % Trapezoidal wing area in ft myCon29 = @(x) WZF=>1;    ;    % zero fuel weight myCon30 = @(x) b=>1;    ;     % upper dimension of wing myCon31 = @(x) cr=>1;    ;    % right dimension side of wing  myCon32 = @(x) ct=>1;    ;    % left dimension side of wing  myCon33 = @(x) WS==>1;    ;    % wing span myCon34 = @(x) RC=>1;     % root chord myCon35 = @(x) l=>1;    % lenght  myCon36 = @(x) m=>1;    ;     % moment                                                                myCon37 = @(x) W0=>1;    % gross weight of aicraft myCon38 = @(x) VH=>1;    % maximum demonstrated level airpeed myCon39 = @(x) VS=>1;    % stalling speed myCon40 = @(x) VS1=>1;    % stalling speed with flaps retracted myCon41 = @(x) KG=>1;         % Gust alleviation factor myCon42 = @(x) UREF=>1;    ;   % reference gust velocity  myCon43 = @(x) VC=>1;    % design cruise speed myCon44 = @(x) pi=>1;    ;   % pi number myCon45 = @(x) Ude=>1;    % vertical gust velocity myCon46 = @(x) x=>1;          % distance in ft penetrated into the gust myCon47 = @(x) CMGC=>1;    ;   % Mean geometric chord myCon48 = @(x) UG=>1;    % i dont know the name myCon49 = @(x) D=>1;    % Drag myCon50 = @(x) Y=>1;    % fuel weight fraction for the cruise segment myCon51 = @(x) CL=>1;    % lift coefficient  myCon52 = @(x) CD=>1;    % drag coefficient myCon53 = @(x) A=>1;    % Area myCon54 = @(x) Cla=>1;    ;   %3-dimensional lift curve slope myCon55 = @(x) B=log(Y);% 56 variable confun = @(x) deal(myCon1(x), myCon2(x), myCon3(x), myCon4(x), myCon5(x), myCon6(x), myCon7(x), myCon8(x), myCon9(x), myCon10(x), myCon11(x), myCon12(x), myCon13(x), myCon14(x), myCon15(x), myCon16(x), myCon17(x), myCon18(x), myCon19(x), myCon20(x), myCon21(x), myCon22(x), myCon23(x), myCon24(x), myCon25(x), myCon26(x), myCon27(x), myCon28(x), myCon29(x), myCon30(x), myCon31(x), myCon32(x), myCon33(x), myCon34(x), myCon35(x), myCon36(x), myCon37(x), myCon38(x), myCon39(x), myCon40(x), myCon41(x), myCon42(x), myCon43(x), myCon44(x), myCon45(x), myCon46(x), myCon47(x), myCon48(x), myCon49(x), myCon50(x), myCon51(x), myCon52(x), myCon53(x), myCon54(x), myCon55(x)); % Run genetic algorithm [x, fval, exitflag, output, population, scores] = ga(objfun, nvars, [], [], [], [], [], [], confun, options); % Plot Pareto front pareto(fval(:,1:nobj/2), -fval(:,nobj/2+1:end)); xlabel('Objective 1'); ylabel('Objective 2'); zlabel('Objective 3');

Hi Good Afternoon. Can someone help me with my genetic algorithm in matlab , unfortunately it is not working but the structure is right I think . I need it to work in order to see the pareto front 3D and the performance of the constraints please. I would be very grateful if you could. The constraints are these and the objective functions are also written correctly. Note this is a personal project not an assignment! King regards MATLAB CODE: % Define decision variables, objectives, and constraints nvars = 56; % number of decision variables nobj = 8; % number of objectives ncon = 56; % number of constraints % Set up genetic algorithm options options = optimoptions('ga', ...   'PopulationSize', 100, ...   'MaxGenerations', 100, ...   'MutationFcn', {@mutationuniform, 0.05}, ...   'CrossoverFcn', @crossoverarithmetic); % Define the objective functions to maximize and minimize f = @(x) [=((Fn/m0)*V0)/(1+f+Fab)*((V9^2)/2)-((V0^2)/2), ((Fn/m0)*V0)/(f*QR*NB), -1-(1/(T1/T0)), m0*V0]; g = @(x) [-((f/(Fn/m0)), -(10^13)*(p3/(1.4*(10^6)))*exp(-71442/Tpz)*(7.56*(o^7.2)-1.6)*(t^0.64)), -(WT0*(1-(WF/WTO)-(WE/WTO))),-(WTO-WLanding), -(WT0*(1-(WF/WTO)-(WE/WTO))), -WPL/WC, -M/(TSFC/Fn)]; % Define your own constraint functions myCon1 = @(x) f=>1;      % f= fuel to air ratio myCon2 = @(x) Fn=>1;     % Fn= net thurst myCon3 = @(x) m0=>1;     % m0= air mass flow rate  myCon4 = @(x) p3=>1;     % p3=inlet pressure myCon5 = @(x) Tpz=>1;    % Tpz=primary zone temperature myCon6 = @(x) o=>1;     % o=equivalence ratio myCon7 = @(x t=>1;      % t=residence time myCon8 = @(x) aa=>1;     % aa=pressure term myCon9 = @(x) WTO=>1;    % Wto=take off weight myCon10 = @(x) WLanding=>1;    ; % Wlanding=landing weight myCon11 = @(x)  WF=>1;    % Wf=fuel weight myCon12 = @(x) WE=>1;    % WE=empty weight myCon13 = @(x) WPL=>1;    ;    % Wpl=payload weight myCon14 = @(x) WC==>1;         % Wc=crew weight myCon15 = @(x)  M==>1;          % Fuel load mass myCon16 = @(x) Fab=>1;    % afterburner fuel-to-air ratio myCon17 = @(x) V9=>1;    % exhaust velocity myCon18 = @(x) V0=>1;    % cruising speed myCon19 = @(x) QR=>1;    % fuel heating value myCon20 = @(x) NB=>1;    % burner efficiency myCon21 = @(x) T1=>1;    % inlet temperature myCon22 = @(x) T0=>1;    % ambient static temperature  myCon23 = @(x) L=>1;    % lift myCon24= @(x) p=>1;    % density myCon25= @(x) V=>1;    % velocity myCon26 = @(x)  A=>1;    % wing area myCon27 = @(x) bw=>1;    % wing span myCon28 = @(x) sw=>1;    % Trapezoidal wing area in ft myCon29 = @(x) WZF=>1;    ;    % zero fuel weight myCon30 = @(x) b=>1;    ;     % upper dimension of wing myCon31 = @(x) cr=>1;    ;    % right dimension side of wing  myCon32 = @(x) ct=>1;    ;    % left dimension side of wing  myCon33 = @(x) WS==>1;    ;    % wing span myCon34 = @(x) RC=>1;     % root chord myCon35 = @(x) l=>1;    % lenght  myCon36 = @(x) m=>1;    ;     % moment                                                                myCon37 = @(x) W0=>1;    % gross weight of aicraft myCon38 = @(x) VH=>1;    % maximum demonstrated level airpeed myCon39 = @(x) VS=>1;    % stalling speed myCon40 = @(x) VS1=>1;    % stalling speed with flaps retracted myCon41 = @(x) KG=>1;         % Gust alleviation factor myCon42 = @(x) UREF=>1;    ;   % reference gust velocity  myCon43 = @(x) VC=>1;    % design cruise speed myCon44 = @(x) pi=>1;    ;   % pi number myCon45 = @(x) Ude=>1;    % vertical gust velocity myCon46 = @(x) x=>1;          % distance in ft penetrated into the gust myCon47 = @(x) CMGC=>1;    ;   % Mean geometric chord myCon48 = @(x) UG=>1;    % i dont know the name myCon49 = @(x) D=>1;    % Drag myCon50 = @(x) Y=>1;    % fuel weight fraction for the cruise segment myCon51 = @(x) CL=>1;    % lift coefficient  myCon52 = @(x) CD=>1;    % drag coefficient myCon53 = @(x) A=>1;    % Area myCon54 = @(x) Cla=>1;    ;   %3-dimensional lift curve slope myCon55 = @(x) B=log(Y);% 56 variable confun = @(x) deal(myCon1(x), myCon2(x), myCon3(x), myCon4(x), myCon5(x), myCon6(x), myCon7(x), myCon8(x), myCon9(x), myCon10(x), myCon11(x), myCon12(x), myCon13(x), myCon14(x), myCon15(x), myCon16(x), myCon17(x), myCon18(x), myCon19(x), myCon20(x), myCon21(x), myCon22(x), myCon23(x), myCon24(x), myCon25(x), myCon26(x), myCon27(x), myCon28(x), myCon29(x), myCon30(x), myCon31(x), myCon32(x), myCon33(x), myCon34(x), myCon35(x), myCon36(x), myCon37(x), myCon38(x), myCon39(x), myCon40(x), myCon41(x), myCon42(x), myCon43(x), myCon44(x), myCon45(x), myCon46(x), myCon47(x), myCon48(x), myCon49(x), myCon50(x), myCon51(x), myCon52(x), myCon53(x), myCon54(x), myCon55(x)); % Run genetic algorithm [x, fval, exitflag, output, population, scores] = ga(objfun, nvars, [], [], [], [], [], [], confun, options); % Plot Pareto front pareto(fval(:,1:nobj/2), -fval(:,nobj/2+1:end)); xlabel('Objective 1'); ylabel('Objective 2'); zlabel('Objective 3');

Computer Networking: A Top-Down Approach (7th Edition)
Computer Networking: A Top-Down Approach (7th Edition)
7th Edition
ISBN:9780133594140
Author:James Kurose, Keith Ross
Publisher:James Kurose, Keith Ross
Chapter1: Computer Networks And The Internet
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Hi Good Afternoon.
Can someone help me with my genetic algorithm in matlab , unfortunately it is not working but the structure is right I think .
I need it to work in order to see the pareto front 3D and the performance of the constraints please.

I would be very grateful if you could.
The constraints are these and the objective functions are also written correctly.

Note this is a personal project not an assignment!

King regards

MATLAB CODE:

% Define decision variables, objectives, and constraints
nvars = 56; % number of decision variables
nobj = 8; % number of objectives
ncon = 56; % number of constraints

% Set up genetic algorithm options
options = optimoptions('ga', ...
  'PopulationSize', 100, ...
  'MaxGenerations', 100, ...
  'MutationFcn', {@mutationuniform, 0.05}, ...
  'CrossoverFcn', @crossoverarithmetic);

% Define the objective functions to maximize and minimize
f = @(x) [=((Fn/m0)*V0)/(1+f+Fab)*((V9^2)/2)-((V0^2)/2), ((Fn/m0)*V0)/(f*QR*NB), -1-(1/(T1/T0)), m0*V0];

g = @(x) [-((f/(Fn/m0)), -(10^13)*(p3/(1.4*(10^6)))*exp(-71442/Tpz)*(7.56*(o^7.2)-1.6)*(t^0.64)), -(WT0*(1-(WF/WTO)-(WE/WTO))),-(WTO-WLanding), -(WT0*(1-(WF/WTO)-(WE/WTO))), -WPL/WC, -M/(TSFC/Fn)];

% Define your own constraint functions
myCon1 = @(x) f=>1;      % f= fuel to air ratio

myCon2 = @(x) Fn=>1;     % Fn= net thurst

myCon3 = @(x) m0=>1;     % m0= air mass flow rate 

myCon4 = @(x) p3=>1;     % p3=inlet pressure

myCon5 = @(x) Tpz=>1;    % Tpz=primary zone temperature

myCon6 = @(x) o=>1;     % o=equivalence ratio

myCon7 = @(x t=>1;      % t=residence time

myCon8 = @(x) aa=>1;     % aa=pressure term

myCon9 = @(x) WTO=>1;    % Wto=take off weight

myCon10 = @(x) WLanding=>1;    ; % Wlanding=landing weight

myCon11 = @(x)  WF=>1;    % Wf=fuel weight

myCon12 = @(x) WE=>1;    % WE=empty weight

myCon13 = @(x) WPL=>1;    ;    % Wpl=payload weight

myCon14 = @(x) WC==>1;         % Wc=crew weight

myCon15 = @(x)  M==>1;          % Fuel load mass

myCon16 = @(x) Fab=>1;    % afterburner fuel-to-air ratio

myCon17 = @(x) V9=>1;    % exhaust velocity

myCon18 = @(x) V0=>1;    % cruising speed
myCon19 = @(x) QR=>1;    % fuel heating value

myCon20 = @(x) NB=>1;    % burner efficiency

myCon21 = @(x) T1=>1;    % inlet temperature

myCon22 = @(x) T0=>1;    % ambient static temperature 

myCon23 = @(x) L=>1;    % lift

myCon24= @(x) p=>1;    % density

myCon25= @(x) V=>1;    % velocity

myCon26 = @(x)  A=>1;    % wing area

myCon27 = @(x) bw=>1;    % wing span

myCon28 = @(x) sw=>1;    % Trapezoidal wing area in ft

myCon29 = @(x) WZF=>1;    ;    % zero fuel weight

myCon30 = @(x) b=>1;    ;     % upper dimension of wing

myCon31 = @(x) cr=>1;    ;    % right dimension side of wing 

myCon32 = @(x) ct=>1;    ;    % left dimension side of wing 

myCon33 = @(x) WS==>1;    ;    % wing span

myCon34 = @(x) RC=>1;     % root chord

myCon35 = @(x) l=>1;    % lenght 

myCon36 = @(x) m=>1;    ;     % moment                                                               

myCon37 = @(x) W0=>1;    % gross weight of aicraft

myCon38 = @(x) VH=>1;    % maximum demonstrated level airpeed

myCon39 = @(x) VS=>1;    % stalling speed

myCon40 = @(x) VS1=>1;    % stalling speed with flaps retracted

myCon41 = @(x) KG=>1;         % Gust alleviation factor

myCon42 = @(x) UREF=>1;    ;   % reference gust velocity 

myCon43 = @(x) VC=>1;    % design cruise speed

myCon44 = @(x) pi=>1;    ;   % pi number

myCon45 = @(x) Ude=>1;    % vertical gust velocity

myCon46 = @(x) x=>1;          % distance in ft penetrated into the gust

myCon47 = @(x) CMGC=>1;    ;   % Mean geometric chord

myCon48 = @(x) UG=>1;    % i dont know the name

myCon49 = @(x) D=>1;    % Drag

myCon50 = @(x) Y=>1;    % fuel weight fraction for the cruise segment

myCon51 = @(x) CL=>1;    % lift coefficient 

myCon52 = @(x) CD=>1;    % drag coefficient

myCon53 = @(x) A=>1;    % Area

myCon54 = @(x) Cla=>1;    ;   %3-dimensional lift curve slope

myCon55 = @(x) B=log(Y);% 56 variable

confun = @(x) deal(myCon1(x), myCon2(x), myCon3(x), myCon4(x), myCon5(x), myCon6(x), myCon7(x), myCon8(x), myCon9(x), myCon10(x), myCon11(x), myCon12(x), myCon13(x), myCon14(x), myCon15(x), myCon16(x), myCon17(x), myCon18(x), myCon19(x), myCon20(x), myCon21(x), myCon22(x), myCon23(x), myCon24(x), myCon25(x), myCon26(x), myCon27(x), myCon28(x), myCon29(x), myCon30(x), myCon31(x), myCon32(x), myCon33(x), myCon34(x), myCon35(x), myCon36(x), myCon37(x), myCon38(x), myCon39(x), myCon40(x), myCon41(x), myCon42(x), myCon43(x), myCon44(x), myCon45(x), myCon46(x), myCon47(x), myCon48(x), myCon49(x), myCon50(x), myCon51(x), myCon52(x), myCon53(x), myCon54(x), myCon55(x));

% Run genetic algorithm
[x, fval, exitflag, output, population, scores] = ga(objfun, nvars, [], [], [], [], [], [], confun, options);

% Plot Pareto front
pareto(fval(:,1:nobj/2), -fval(:,nobj/2+1:end));
xlabel('Objective 1');
ylabel('Objective 2');
zlabel('Objective 3');

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