bfgs_f_celu2.asv

Control optimisation. It is example of use BFGS algorithm to control satellite form Earth atmosphere

% funkcja celu
function q = bfgs_f_celu2(tau,x0,h0,u2)


global RzRm bm az am c;
global kq;

% przygotowanie:
tau=tau';
dtau = diff( [0 tau]);
n = ceil(dtau/h0);
nk = sum(n);
cn = cumsum([1 n]);
[x_rk4] = rk4(x0,tau,h0,u2);
t = wylicz_t(nk+1,h0);
t_dlugosc = length(t);
%ostatni_rk4 = x_rk4(length(x_rk4),1:5)

%     h = 1e-3;
%     e = zeros(length(tau),1)';
%     e(1) = 1;
%     taueh = tau+e*h;
%     for j=1:100
%         taueh = tau+e*h*j;
%         [x_rk4] = rk4(x0,taueh,h0,u2);
%         probka(j)=x_rk4(1)
%     end
%     %figure(5)
%     plot((1:100)*h,probka);



wektor_u1 = wylicz_u1(tau,t);
wektor_u2 = wylicz_u2(tau,t,u2,h0);
xT = x_rk4(t_dlugosc,1:5);     %polozenieT
% rownania ruchu Marsa:

xmT = RzRm*cos((am*t(t_dlugosc))+bm);
ymT = RzRm*sin((am*t(t_dlugosc))+bm);
dxmT = -RzRm*am*sin((am*t(t_dlugosc))+bm);
dymT =  RzRm*am*cos((am*t(t_dlugosc))+bm);

q1 = kq(1)*( (xmT-xT(1))^2 );
q2 = kq(2)*( (dxmT-xT(2))^2 );
q3 = kq(3)*( (ymT-xT(3))^2 );
q4 = kq(4)*( (dymT-xT(4))^2 );
q5 = kq(5)*xT(5);

q = 0.5*(q1 + q2 + q3 + q4) - q5;
%q = daj_q(t(t_dlugosc),xmT,ymT,dxmT,dymT,polozenieT);
q=;
end % koniec funkcji