Recent content by Ajaja

It would be nice. I use OpenOrbiter x64 and haven't built the spice module for O2016.

DXVK knows:

@johnnymanly Did you try https://github.com/doitsujin/dxvk ?

It's windows in days where to search for an optimal trajectory. With 0 it just calculates for selected dates. If True - ignore minimal dV needed for the final maneuver (orbital insertion) and optimize only for departure dV (and dV at flybys for multybody trajectories). Days or dates. With...

Just select flyby parameters. It was initially designed by Keithth G to find and optimize trajectories with multiple gravity assist maneuvers. But nothing prevents to use it with simple trajectories. For example: import sys import pygmo as pg from flyby import flyby p = flyby(['earth', 'mars']...

Just use some porkchop plotter application. I even made one many years ago ( https://www.orbiter-forum.com/resources/lambertsolver.3050/ ) But now it's easier to use online porkchop plotters, e.g.: http://sdg.aero.upm.es/index.php/online-apps/porkchop-plot

BTW, for Earth-Mars transfer the departure at 2040-May-07 and arrival at 2041-Sep-12 are far from optimal dates: Date of earth departue : 2040-May-07 00:00:00 Date of mars arrival : 2041-Sep-12 00:00:00 Transfer time from earth to mars: 493.0 days Total mission duration...

The easiest way to use the lamber solution with GMAT is to convert v-infinity at departure to GMAT's OutgoingAsymptote (OutgoingC3/OutgoingRHA/OutgoingDHA) and then optimize it in GMAT. Take a look at https://orbiter-forum.com/threads/pykep-to-transx-conversion.33685/#post-514495

And the recording is a deepfake? :cool:

They published the story here (in German): https://www.bild.de/bild-plus/politik/ausland/politik-ausland/bild-hat-geheime-telefon-mitschnitte-russen-planen-mega-angriff-auf-kiew-85847600.bild.html

@BILD obtained secret voice recordings between former Roscosmos chief Dmitry Rogozin and current (sate-owned) Progress CEO Dmitry Baranov in which they prepare and finalize a plan to crash a “civilian” #Soyuz carrier rocket into #Kyiv or another Ukrainian city. 🤬

It may be easier to find a way to get back from NRHO to Earth using Backward Propagation. But with 2 maneuvers from the scheme it will still be a challenging task.

The coordinate systen is nothing to do with this. The inclination is not exactly 90 degrees, so it's not a polar orbit strictly speaking, but it's close enough to the one. I think, at the periapsis you don't need to get into the NRHO at once, you just have to make a correction to reach the NRHO...

The spacecraft never gets there. It's NRHO, but RadApo is calculated for an elliptical orbit. Just a guess. It varies RadApo and Inclination to find a solution, but the Inclination is a parameter for an elliptical orbit too. RadApo/RadPer/Inclination are just the simpliest way to set initial...

Not exactly 7 days. It stops propagating when SC crosses YZ-plane (SC.LunaEarth.X = 0) in the Earth-Moon rotating frame. It's at the apoapsis and the periapsis. And it tries to minimize differences in position/velocity at the periapsis compared to the initial values. The script above gives...