Boa tarde,
Gostaria de minimizar os dois primeiros objetivos e maximizar o terceiro,dentro das restricoes impostas.
E depois plotar uma 3D Pareto front , tudo em matlab.
Atualmente o codigo tem erros entao ,seria possivel alguem me corrigir o codigo por favor 

 

codigo:

 

prob.Objective.one = [(x(2)/x(3)*x(18))/(1+x(1)+x(16))*((x(17)^2)/2)-((x(18)^2)/2),((x(2)/x(3))*x(18))/(x(1)*x(19)*x(20))];

prob.Objective.two =[-((x(1)/(x(2)/x(3))), -(10^13)*(x(4)/(1.4*(10^6)))*exp(-71442/x(5))*(7.56*(x(6)^7.2)-1.6)*(x(7)^0.64)), -(x(9)*(1-(x(11)/x(9))-(x(12)/x(9))))),-(x(9)-x(10)), -(x(9)*(1-(x(11)/x(9))-(x(12)/x(9)))), -x(13)/x(14), -x(15)/(x(24)/x(2))];

prob.Objective.three = 1 - x^2;

prob.ObjectiveSense = "max";

prob.ObjectiveSense.one = "minimize";

prob.Objective.two = "minimize";

prob.Objective.three = "maximize";

fun = @(x)exp(x(1) + 2*x(2));

nonlcon = @ellipseparabola;

x0 = [0 0];

A = []; % No other constraints

b = [];

Aeq = [];

beq = [];

lb = [];

ub = [];

x = fmincon(fun,x0,A,b,Aeq,beq,lb,ub,nonlcon);

function [c,ceq] = ellipseparabola(x)

c(1) = x(1)-1; % f= fuel to air ratio

c(2) = x(2)-1; % Fn= net thurst

c(3) = x(3)-1; % m0= air mass flow rate

c(4) = x(4)-1; % p3=inlet pressure

c(5) = x(5)-1; % Tpz=primary zone temperature

c(6) = x(6)-1; % o=equivalence ratio

c(7) = x(7)-1; % t=residence time

c(8) = x(8)-1; % aa=pressure term

c(9) = x(9)-1; % Wto=take off weight

c(10) = x(10)-1; % Wlanding=landing weight

c(11) = x(11)-1; % Wf=fuel weight

c(12) = x(12)-1; % WE=empty weight

c(13) = x(13)-1; % Wpl=payload weight

c(14) = x(14)-1; % Wc=crew weight

c(15) = x(15)-1; % Fuel load mass

c(16) = x(16)-1; % afterburner fuel-to-air ratio

c(17) = x(17)-1; % exhaust velocity

c(18) = x(18)-1; % cruising speed

c(19) = x(19)-1; % fuel heating value

c(20) = x(20)-1; % burner efficiency

c(21) = x(21)-1; % inlet temperature

c(22) = x(22)-1; % ambient static temperature

c(23) = x(23)-1; % lift

c(24) = x(24)-1; % density

c(25) = x(25)-1; % velocity

c(26) = x(26)-1; % wing area

c(27) = x(27)-1; % wing span

c(28) = x(28)-1; % Trapezoidal wing area in ft

c(29) = x(29)-1; % zero fuel weight

c(30) = x(30)-1; % upper dimension of wing

c(31) = x(31)-1; % right dimension side of wing

c(32) = x(32)-1; % left dimension side of wing

c(33) = x(33)-1; % wing span

c(34) = x(34)-1; % root chord

c(35) = x(35)-1; % lenght

c(36) = x(36)-1; % moment

c(37) = x(37)-1; % gross weight of aicraft

c(38) = x(38)-1; % maximum demonstrated level airpeed

c(39) = x(39)-1; % stalling speed

c(40) = x(40)-1; % stalling speed with flaps retracted

c(41) = x(41)-1; % Gust alleviation factor

c(42) = x(42)-1; % reference gust velocity

c(43) = x(43)-1; % design cruise speed

c(44) = x(44)-1; % pi number

c(45) = x(45)-1; % vertical gust velocity

c(46) = x(46)-1; % distance in ft penetrated into the gust

c(47) = x(47)-1; % Mean geometric chord

c(48) = x(48)-1; % i dont know the name

c(49) = x(49)-1; % Drag

c(50) = x(50)-1; % fuel weight fraction for the cruise segment

c(51) = x(51)-1; % lift coefficient

c(52) = x(52)-1; % drag coefficient

c(53) = x(53)-1; % Area

c(54) = x(54)-1; %3-dimensional lift curve slope

c(55) = x(55)-1; % 56 variable B=log(Y)

ceq = [];

end

[sol,fval,exitflag,output] = solve(prob,...

Solver="gamultiobj",...

Options=options);

sol = solve(prob);

paretoplot(sol)

% Plot Pareto front

pareto(fval(:,1:nobj/2), -fval(:,nobj/2+1:end));

xlabel('Objective 1');

ylabel('Objective 2');

zlabel('Objective 3');