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Sorry for necroposting. I've been having fun with GMAT for last days learning this tool and trying to solve these old Orbiter challenges. Looks like here we can use Earth gravity to minimize delta-V when we escaping the Moon and then we can use a gravity assist maneuver near the Moon to fly away...

Thanks for the challenge. It was fun. Honestly, I thought is's better to change plane as higher as possible. So, I had started from 3 burns and then step by step GMAT eliminated the first burn and came to the similar 2-burn solution. Unfortunately, I've found that the IMFD's autoburn is...

It looks like the best possible total delta-V here is around 2004 m/s. There are Delta Velocity programs for IMFD in P30 LVLH frame: Burn 1: 51982.1825373219 dVf: -864.817 m/s dVp: 1121.245 m/s Burn 2: 51982.2734755480 dVf: -525.079 m/s dVp: -263.381 m/s Total: 1416 + 588 = 2004 m/s A...

Now it has an opensource optimization plugin (Yukon), and you don't need proprietary tools (VF13ad/Matlab) anymore. Then I'm afraid it will be useless with my Windows 7 :( Yes, they really used GMAT for TESS mission, there is even "Generated by the General Mission Analysis Tool (GMAT)" text...

An interesting video tutorial for GMAT (General Mission Analysis Tool) where the TESS trajectory calculation is described. The trajectory is slightly different (it was 2014) but there is the same idea. And GMAT 2018a already has an optimizator (Yukon) which can be used instead of proprietary...

Have you read Kip Thorne's "The Science of Interstellar" ? I'm afraid, it's not possible to simulate Gargantua in the Orbiter, even roughly. Usefull links: http://interstellarfilm.wikia.com/wiki/Gargantua By calculations of Kip Thorne, Gargantua is about 100 million solar masses, placing it...

BTW, what's happened with 'Keithth G' posts? Forum glitch?

Thanks. Amazing, 75 km after 14 days - excellent result!!! Looking forward to release of the MFD :)

Eq.(10) gives good stability, but not enough: http://orbiter-forum.com/showthread.php?p=127798 Moon L1: So I'm curious about ADSWNJ's results.

I used https://map.gsfc.nasa.gov/ContentMedia/lagrange.pdf equations (10), (11)

Very interesting! Could you compare stability of calculated orbits with my old module? Lagrangian points MFD v0.2

Did someone try to use GMAT (an offline n-body integrator from NASA)? https://gmat.gsfc.nasa.gov/

@SolarLiner tle2[5] =line2.Substring(53, 11); double r = double.Parse(tle2[5]); 53->52

??? ;)

@SolarLiner double a = 0.720e3 * pow(0.5e1, 0.1e1 / 0.3e1) * pow(pow(r, -0.2e1) * gm * pow(pi, -0.2e1), 0.1e1 / 0.3e1); double a = 0.720e3 * Math.Pow(0.5, 0.1 / 0.3) * Math.Pow(Math.Pow(r, -0.2) * gm * Math.Pow(pi, -0.2), 0.1 / 0.3); 0.1e1 = 1 not 0.1 -0.2e1 = -2 not -0.2 ... ;) This...

@Quick_Nick Don't forget about equatorial->ecliptical plane conversion. Orbiter uses ecliptical plane, TLE - equatorial.

Maple (http://www.maplesoft.com/) solution of equations: > restart; with(codegen): > eq1:=cos(ecl_i)=cos(eq_i)*cos(ob_ecl)+sin(eq_i)*cos(eq_RAAN)*sin(ob_ecl): > eq2:=cos(eq_i)=cos(ecl_i)*cos(ob_ecl)-sin(ecl_i)*cos(ecl_RAAN)*sin(ob_ecl): > eq3:=sin(ecl_i)*sin(ecl_RAAN)=sin(eq_i)*sin(eq_RAAN): >...

Source code of eq_to_ecl? #include <math.h> #include <stdio.h> #include <stdlib.h> #include <string.h> double gm = 3.9860044e14; double ob_ecl=.40927970966248346; //23.45 deg; double gr(double x) { x=x*57.295779513082320875; while ((x<0)||(x>=360.0)) { if (x<0) {x+=360; continue;}...

Simple Lambert's problem solver and porkchop plotter tool for interplanetary trajectory optimization. Can be used for calculation of TransX's Eject Plan vector.Acknowledgements: NAIF team for CSPICE library: http://naif.jpl.nasa.gov/naif/ The PaGMO development team for routine witch...

https://www.youtube.com/watch?v=kIp39XN-hZE Start looking from 2:05. It's may be interesting challenge for Orbiter players (especially for TransX experts) ;)