I have the velocity vectors of the spacecraft in the ICRF frame(obtained it from the solver) centered about the barycentre of the Solar system. I am having difficulty obtaining the position vector of the spacecraft near Venus in the ICRF frame. Is there any way to obtain the position vectors of the spacecraft using ICRF frame? The MATLAB code is:
r1vec=[-1.477068281616569E+08,2.279790503327744E+07,4.898292942424305E+03]; Earth position vector in ICRF frame r2vec=[5.041133888931480E+07,-9.500729420957273E+07,-4.262957928339511E+06]; Venus position vector in ICRF frame tf=112; m=0; muC=1.32711E+11; [V1, V2, extremal_distances]=lambert(r1vec, r2vec, tf, m, muC)
The output is:
V(near earth) = -4.3381 -26.2828 -1.3166 V(near Venus) = 30.1512 22.1471 1.3083 extremal_distances = 1.0e+08 1.0764 1.4949
The extremal distances are the periapsis and apoapsis distances of the transfer ellipse.