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A MATLAB Script for Propagating Trajectories from the Earth to the Moon

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A MATLAB Script for Propagating Trajectories from the Earth to the Moon

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14 Aug 2013 (Updated )

Integrate n-body trajectories from the Earth to the Moon. Includes non-spherical Earth gravity.

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Description

PDF document and a MATLAB script called pprop_lunar that can be used to numerically integrate the geocentric orbital equations of motion of a trajectory from the Earth to the Moon. This scientific simulation begins at a user-defined epoch and geocentric state vector (position and velocity vectors) representing the point of trans-lunar injection (TLI) and ends at (1) closest approach to the Moon, (2) a user-defined Moon-centered (selenocentric) distance, or (3) at a user-defined final epoch.

MATLAB release MATLAB 7.14 (R2012a)
Other requirements Requires JPL binary ephemeris file. Available from Orbital Mechanics with MATLAB area of the Orbital and Celestial Mechanics Website located at www.cdeagle.com.
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Comments and Ratings (2)
14 May 2014 Vincenzo Capuano

I soleved the problem; it didn't work because I didm't dwonload the JPL binary ephemeris file.

Anyway, I have another question; have you any idea about the accuracy in position and velocity of this propagator?

Thank you very much,
Vincenzo

14 May 2014 Vincenzo Capuano

Hello,

I tried to run your script, but it doesn't work:

Error using fread
Invalid file identifier. Use fopen to generate a valid file identifier.

Error in jplephem (line 71)
ttl = fread(fid, 252);

Error in pprop_eqm (line 44)
svsun = jplephem(jdate, 11, 3);

Error in odearguments (line 88)
f0 = feval(ode,t0,y0,args{:}); % ODE15I sets args{1} to yp0.

Error in ode45 (line 114)
[neq, tspan, ntspan, next, t0, tfinal, tdir, y0, f0, odeArgs, odeFcn, ...

Error in findca (line 33)
[t, ysol, tevent, yevent, ie] = ode45(@pprop_eqm, [0 tend], [ri vi], options);

Error in pprop_lunar (line 101)
[jdtdb_ca, re2sc, ve2sc, rm2sc, vm2sc] = findca(jdtdb_tli, ri, vi);

Can you help me please?

Updates
28 May 2014

Includes new option to model the effect of the Moon on the trajectory using non-spherical lunar gravity.

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