%Función que propaga la posición de un planeta(TIERRA o JUPITER) a un instante t desde la
%época dados los elementos orbitales en la época
function EOt=pplanetaCP(t,EO)
global mus
%EOt=zeros(1,12);
T=2*pi*sqrt(EO(2)^3/(mus));
n=2*pi/T;
DeltaT=t;
%T0=t/36525;
%EO(1:6)=EO(1:6)+EO(7:12)*T0;
% EOt(1:12)=EO(1:12);
% M=EOt(6)-EOt(5);
% EOt(5)=EOt(5)-EOt(4);
%
% myfun = @(E,M) M-E+EO(1)*sin(E);
% X = fzero(@(E) myfun(E,M),0.1);
% TAepoch=2*atan(sqrt((1+EO(1))/(1-EO(1)))*tan(X/2));
%
% EOt(6)=TAepoch;
if floor(DeltaT/T)==0 %Hay q porpagar un tiempo menor al del periodo del planeta
E=atan(tan(EO(6)/2)*sqrt((1-EO(1))/(1+EO(1))))*2;
M=E-EO(1)*sin(E);
TPOS=M/n;
if (TPOS+DeltaT)>T
incT=(TPOS+DeltaT)-T;
M=n*incT;
M=2*pi*(M/2/pi-floor(M/2/pi));
myfun = @(E,M) M-E+EO(1)*sin(E);
X = fzero(@(E) myfun(E,M),0.1);
TAepoch=2*atan(sqrt((1+EO(1))/(1-EO(1)))*tan(X/2));
else
incT=(TPOS+DeltaT);
M=n*incT;
M=2*pi*(M/2/pi-floor(M/2/pi));
myfun = @(E,M) M-E+EO(1)*sin(E);
X = fzero(@(E) myfun(E,M),0.1);
TAepoch=2*atan(sqrt((1+EO(1))/(1-EO(1)))*tan(X/2));
end
else %Hay que propagar mas de una órbita
fractT=DeltaT/T-floor(DeltaT/T);
DeltaT=fractT*T;
E=atan(tan(EO(6)/2)*sqrt((1-EO(1))/(1+EO(1))))*2;
M=E-EO(1)*sin(E);
TPOS=M/n;
if (TPOS+DeltaT)>T
incT=(TPOS+DeltaT)-T;
M=n*incT;
M=2*pi*(M/2/pi-floor(M/2/pi));
myfun = @(E,M) M-E+EO(1)*sin(E);
X = fzero(@(E) myfun(E,M),0.05);
TAepoch=2*atan(sqrt((1+EO(1))/(1-EO(1)))*tan(X/2));
else
incT=(TPOS+DeltaT);
M=n*incT;
M=2*pi*(M/2/pi-floor(M/2/pi));
myfun = @(E,M) M-E+EO(1)*sin(E);
X = fzero(@(E) myfun(E,M),0.05);
TAepoch=2*atan(sqrt((1+EO(1))/(1-EO(1)))*tan(X/2));
end
end
EOt=EO;
EOt(6)=TAepoch;
end
e-REdING. Biblioteca de la Escuela Superior de Ingenieros de Sevilla.
