# Search results

1. ### Orbiter as a visualization tool of external data

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

DXVK knows:
3. ### Problem - SOLVED - Problem with latest Orbiter build on Linux

@johnnymanly Did you try https://github.com/doitsujin/dxvk ?
4. ### GMAT Mars transfer orbit model

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...
5. ### GMAT Mars transfer orbit model

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']...
6. ### GMAT Mars transfer orbit model

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
7. ### GMAT Mars transfer orbit model

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...
8. ### GMAT Mars transfer orbit model

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
9. ### News Roscosmos News

And the recording is a deepfake? :cool:
10. ### News Roscosmos News

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
11. ### News Roscosmos News

@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. 🤬
12. ### Challenge LOP-G to Brighton Beach and Back Again

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.
13. ### Challenge LOP-G to Brighton Beach and Back Again

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...
14. ### Challenge LOP-G to Brighton Beach and Back Again

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...
15. ### Challenge LOP-G to Brighton Beach and Back Again

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...
16. ### Challenge LOP-G to Brighton Beach and Back Again

@firefox00 Don't look at RadApo. It's a keplerian apoapsis, not real. You can trust RadPer here (because it's the starting point) but not RadApo. So, change RadPer to your periapsis (3000km), reduce numbers of orbits to 3 (For I = 1:1:3;), run, apply correction, run again, apply, increase to 4...
17. ### Challenge LOP-G to Brighton Beach and Back Again

@firefox00 It was calculated by a GMAT script that looked like the script in the attachment.
18. ### General Question Rendering issues with D3D7 and D3D9 clients (Open Orbiter)

D3D7Client in Orbiter.exe and D3D7Client in Orbiter_ng.exe work differently. Сheck also 'Delta-glider\Brighton Beach.scn' for example.
19. ### Better Ephemerides, Rotation Models, and a Solution to X64 Builds

It's ~34Mb. But now it won't work very well outside of this 5 years. I've been testing this today, the elliptical orbits calculated on the edges of the kernel interval are very inaccurate. Pre-calculated mean orbits would be more accurate, but it will be impossible to connect them seamlessly...
20. ### Better Ephemerides, Rotation Models, and a Solution to X64 Builds

It depends on the number of celestial bodies and the time period it covers. I currently use the orbiter.bsp file, which is approximately 600MB in size, as described here: https://orbiter-forum.com/threads/better-ephemerides-rotation-models-and-a-solution-to-x64-builds.41231/post-609141 If there...