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Bon voyage :cheers:

Those dlls (Ariel.dll/Deimos.dll/...) are useless even with x64 Windows builds of Orbiter.

One more Ukrainian space industry enterprise was "liberated": https://www.bbc.com/news/world-europe-62189844

I would recommend this author if you like hard science fiction: https://www.goodreads.com/en/book/show/58922793-cold-eyes

After some googling I've found this equation: link I think, you have to solve a system of equations to find TA (true anomaly) for both satellites at the points of their orbital planes intersection: ν1 = (RAAN2-RAAN1)/2 ± Pi/2 ν2 = (RAAN1-RAAN2)/2 ± Pi/2 tan( ν1 ) = cos( i ) * tan ( TA1+AOP1 )...

It's used in other open-source software like Celestia, PyKep, SpiceyPy. SpiceyPy is under MIT, Celestia and PyKep is GPL. I can't see how it may be tricky.

Why not? It's open source and "No fees or licensing are required": https://naif.jpl.nasa.gov/naif/rules.html

I asked the question here: https://www.orbiter-forum.com/threads/orbiter-is-now-open-source.40023/page-8#post-588372 No answer. But I use SPICE celbody module with Orbiter x64, so it's not a big problem.

BTW, Dmitry Rogozin, head of Roscosmos, is a well-known white nationalist:

Yes, of course :) It's too. For example, engineers design nozzles for atmosphere and I wonder what limitations it adds to propellant ISP. Would it have much better ISP in vacuum with different nozzles (designed for vacuum) with the same propellant? And in general, how big a part plays...

It's about launching from planets with thick atmosphere or from planets/moons with thin atmosphere or without one. Aerodynamic drag it's not the only issue here. I'm just reading Cold Eyes by Peter Cawdron and thinking about all these issues. It's a Sci-Fi novel about a high-G planet with thick...

It's not so simple. You are forgetting about consequences of such ISP reduction. Just go to https://launchercalculator.com/ and play with "1st stage Isp sea level or at the start altitude" changing it to the "1st stage Isp vacuum" value and watch "Gravity Losses" and "Aerodynamic Losses"...

Somehow nobody ever counts wasted m/s due to rocket engine specific impulse losses in atmosphere. ;)

Try to check Modules\D3D9Client\D3D9ClientLog.html It might give some clue.

I just installed DirectX SDK too. And I use Visual Studio 2022 not 2019. But the most important thing is that I changed CMAKE_BUILD_TYPE to Release.

I wouldn't say so. I did some calculations and compared the current rotation model in Orbiter with IAU and ITRF93 models ( https://www.orbiter-forum.com/threads/orbiter-and-earth-rotation.40260/ ) , and for some celestial bodies it doesn't seem as a good enough approximation even for short terms.

Yes, but in he also said that after reaching the final orbit at L2 there may be short flashes up to 5 magnitude.

@Notebook More accurate coordinates for given date and observer position you can get from https://ssd.jpl.nasa.gov/horizons/app.html#/

Webb is here

Although If you need to get into any orbit with specific LAN/inclination/eccentricity/AoP (with any anomaly) it's not Lambert. Maybe, the minimum delta-v here can be derived from laws of conservation energy and momentum. But I'm not sure. I think you will be needed some sort of additional...