Ploting satellite's orbit

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endrius ndreks
endrius ndreks on 31 May 2021
Commented: Star Strider on 1 Jun 2021
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
clear
close all
clc
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)

Accepted Answer

Star Strider
Star Strider on 31 May 2021
It is not possible to run the code because several constants and at least one function are missing.
Try either:
plot3(x,y,z,'.b')
or:
scatter3(x,y,z,'b','filled')
and see if the plot now appears.
  2 Comments
endrius ndreks
endrius ndreks on 1 Jun 2021
It worked, thanks.
I had been trying for a week
Star Strider
Star Strider on 1 Jun 2021
As always, my pleasure!

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