Ploting satellite's orbit

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I'm currently doing an exercise about orbit propagator. From initials distance from earth and velocity (r0 and v0) i should plot orbit considering a single day and sampling every 5 minute.

When i plot i can see that calculated elements are right, because of extreme values in graphic, but i can't see any line on it, just blank. Can someone find where's the problem? I also tried with a cycle "for t=0:300:86400" and ploting inside the cycle and got the same blank page

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t0=0;  
[a, e, i, OmegaG, omegap, Nu] = rv2COE(r0,v0);   
COE = [a, e, i, OmegaG, omegap, Nu];                   
E0=2*(atan(tan(Nu/2)/(sqrt((1+e)/(1-e)))));             
M0=E0 - e*sin(E0);                                   
                                                      
 t=0:300:86400
     
    Mf = ((t-t0)/sqrt(a^3/Mu))+M0;                       %using newton to find true anomaly Nut in every time frame 
    Efiniziale = Mf;                                     %
    Ef = Iterazione(Efiniziale,e,Mf);                    %
    Nut=2*atan(tan(Ef/2)*sqrt((1+e)/(1-e)));             %
    
    r1 = ((a*(1-e^2))/(1+e*cos(Nut)));                
 
 
    ROmegaG=[cos(OmegaG) -sin(OmegaG) 0; sin(OmegaG) cos(OmegaG) 0; 0 0 1];      
    Ri=[1 0 0; 0 cos(i) -sin(i); 0 sin(i) cos(i)];                               
    Romegap=[cos(omegap) -sin(omegap) 0; sin(omegap) cos(omegap) 0; 0 0 1];     
    Rtot=ROmegaG*Ri*Romegap;                                                    % global rotation matrix
    r1vector=Rtot*[r1*cos(Nut), r1*sin(Nut), 0]';                   
    v1vector=Rtot*[-(Mu*sin(Nut))/H, (Mu*(e+cos(Nut)))/H, 0]';      
    
    x=r1vector(1);
    y=r1vector(2);
    z=r1vector(3);
    
    figure(1)
    hold on
    plot3(x,y,z,'b')
    view(135,45)
            