Night_stalker
Slava Ukraini!
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[X] Plan De Parva Agri Cultura (Space Station Variant)
They both use effectively the same upper stack due to the need to launch discrete stages, and the limits on what can be flung out. Using the expanded capacity of the RLA-5 you don't need anywhere near that launch schedule. You can park a hypergolic stage in orbit and leave it there for a month before the next crewed launch comes by, it's the big advantage of that setup. In the double RLA-3 setup though, if the second rocket fails to launch, the mission just aborts into a normal orbital science mission that then re-enters without issue after a week or so of doing science in the FGB. The crisis is over for the most part via a Supreme Soviet imposed solution mostly due to it coming into election season and no one wanting to give more ammunition to the right-wing or have that as an open issue to be debated about through the entire period.
Considering we're just starting the formalized Moonshot program, I assume right now will be the time to decide.Are we too late to push for a more capable lander than the LK?
You'd conduct a large sample return as an unmanned mission launched in a single RLA-5, focusing entirely on a very heavy return vehicle that is automated and not carrying a bunch of life support and people to the moon and back. For the current moon program, you just really do not have the flight mass to reliably use a heavier lander, maybe the conceived two-crew version of the LK, but nothing any heavier.Well, I am glad we didn't completely destroy ourselves or Kosygin in the crisis then. Minimum standards achieved!
Are we too late to push for a more capable lander than the LK? I really want to send a geologist to the moon and let him pick a few hundred kilos of samples at least once. Preferable from a couple different landing sites...
And if not doing that with a bigger LK, would the expanded Luna program allow us to build a capable sample return bus that we could have a geologist visit with a buggy and load up more samples than just the LK can carry?
Regards,
fasquardon
You'd conduct a large sample return as an unmanned mission launched in a single RLA-5, focusing entirely on a very heavy return vehicle that is automated and not carrying a bunch of life support and people to the moon and back. For the current moon program, you just really do not have the flight mass to reliably use a heavier lander, maybe the conceived two-crew version of the LK, but nothing any heavier.
Now to explain the various moon missions for the scenarios of RLA-3 only vs. both being available or even just RLA-5
Why would you launch into a horribly delta v expensive orbit when you can just wait for the launch window so that you intercept at either the ascending or descending node without much issue?
Why would you launch into a horribly delta v expensive orbit when you can just wait for the launch window so that you intercept at either the ascending or descending node without much issue?
Nobody executes an orbital plane change to get to the moon. They just line up the launch so the plane intersection lines up with the lunar intercept. It'd be something like 2.9 km/s otherwise.Because most things on the internet assume you are launching from Canaveral, as that is the primary launch site in the English speaking world.
And the most the moon is at most 5 degrees above or below the plane of the ecliptic, which means that whatever launch window is taken, there's still a pretty big burn to get to the same orbital plane as the moon, and moreso for launches from the Soviet Union. (Well, by "pretty big" I am coming up with us needing an extra 500-ish m/s of dV compared to a mission launched from Canaveral, but I am pretty sure I'm not doing the math right and I can't remember what the latitude of Yariyev either, and do we need to tilt our launch paths to avoid China like the Soviet Union of OTL? So there's so many things I could be doing wrong here.)
You do not need to remotely match planes of orbit to get a moon intercept, if that was necessary moon missions outside a certain latitude would be impossible as the delta v requirements for inclination changes are massive. Instead you launch with an orbit that allows you to intercept the moon on it's ascending of desending node. This is effectively a normal launch to low earth orbit but when the transfer window comes you effectively burn so as your orbit passes the equatorial plane at the same point the moons does at apoapasis requiring no extra delta V and a launch window that happens every month. From there a normal full efficiency capture can occur. Higher inclination launch sites are a bit less delta v efficient, but that is already compensated for in the math for the boosters and not really relevant to a moon mission.Because most things on the internet assume you are launching from Canaveral, as that is the primary launch site in the English speaking world.
And the most the moon is at most 5 degrees above or below the plane of the ecliptic, which means that whatever launch window is taken, there's still a pretty big burn to get to the same orbital plane as the moon, and moreso for launches from the Soviet Union. (Well, by "pretty big" I am coming up with us needing an extra 500-ish m/s of dV compared to a mission launched from Canaveral, but I am pretty sure I'm not doing the math right and I can't remember what the latitude of Yariyev either, and do we need to tilt our launch paths to avoid China like the Soviet Union of OTL? So there's so many things I could be doing wrong here.)
Regards,
fasquardon
You do not need to remotely match planes of orbit to get a moon intercept, if that was necessary moon missions outside a certain latitude would be impossible as the delta v requirements for inclination changes are massive. Instead you launch with an orbit that allows you to intercept the moon on it's ascending of desending node. This is effectively a normal launch to low earth orbit but when the transfer window comes you effectively burn so as your orbit passes the equatorial plane at the same point the moons does at apoapasis requiring no extra delta V and a launch window that happens every month. From there a normal full efficiency capture can occur. Higher inclination launch sites are a bit less delta v efficient, but that is already compensated for in the math for the boosters and not really relevant to a moon mission.
weather sats are an immediate benefit to the entire country as well to multiple industries not doing it in favor of space stations and moon rockets n shit is probably the biggest self own our space program can do