PDF document and a MATLAB script called pprop_e2m that can be used to numerically integrate the geocentric and heliocentric orbital equations of motion of an Earth to Mars interplanetary trajectory. This scientific simulation begins at a user-defined epoch and state vector somewhere within the Earth’s sphere-of-influence (SOI) and ends at (1) closest approach to Mars, (2) a user-defined Mars-centered (areocentric) distance, or (3) at a user-defined final epoch.
What do these errors mean?
Attempted to access coef(753); index out of bounds because numel(coef)=214.
Error in jplephem>interp (line 595)
cbody(m) = coef(n);
Error in jplephem>state (line 432)
tmpv = interp(ibuf, t, ncf, 3, na, 2);
Error in jplephem (line 204)
[pv, rrd] = state(et2, list);
Error in p2000 (line 23)
result = jplephem (jdate, ntarg, ncent);
Error in pcfunc (line 25)
[rf, vf] = p2000(11, ip2, jdate2);
Error in porkchop (line 181)
[dv1, dv2] = pcfunc (JDi, JDf);
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