An yearly manned mission around Sun - proposal by Vladimir Bugrov

[asmi]

At some point I was interested in what kind of research has been done in psychological and behavioral aspects of the spaceflight, and many papers I came across note that many space flyers dating back as far as Salyut missions mentioned psychological importance of being able to look at the Earth. And many theorize that this might become a big problem for long duration deep space missions, where crew won't be able to see the home planet. This proposed mission will be able confirm or deny that thesis without risking a mission too much as the station will still be relatively close, and the crew can be brought back rather quickly.

[Lar]

"occupied by commies" is not helpful phrasing. Please leave politics out, and stay on the topic of the thread.

I've not deleted anything. Yet.

[fregate]

A few questions:

1. Why is the TMK stack launched from Earth in a retrograde orbit? Doesn't that have a massive payload penalty?
2. Is the sun shield designed to focus the Sun's already-intense light on the TMK core? It looks like a giant reflector dish, and some of the pictures show it facing the sun, but others show it facing away.
3. If the TMK is shielded from the sun, then the crew return Soyuz is directly and continuously exposed to the Sun.
4. The picture seems to indicate that assembly takes place at SEL1, not at EML2.

This is all very confusing to me. I should go back a re-read the CONOPS, because so far it is making no sense. And even if it did make sense, I am having trouble seeing the benefit to be gained from such a mission. Couldn't they do the exact same mission, one year autonomous flight, in LEO, or even EML1/2?

Thanks!

@Mark S - my answers for your questions:
1. Uninhibited fantasy of illustrator - should be standard orbit (not retrograde one). Well spotted!

2, 3 I agree - shield suppose to protect all parts of mission stack (aka MTK), creators of "Sunshine" did much better job in 2007 but their spaceship was much closer to the Sun For this mission heliocentric orbit is closer by 0.01 au comparing with Earth orbit around Sun (1 au). Therefore MTK does not require a giant shield.

4. Regarding location of MTK construction site this is just variation of the theme - IMHO EML-2 is more accessible by Assemblers and Testers crews (means CHEAPER to build) if you have an OPSEK asset deployed there. Really depends how long it takes to assemble and test full stack. Considering the pace of ISS progress it could take years before TMK would be ready.

CONOPS was written by me based on my best judgement of three articles and two books - it's not an official mission profile.

Such mission would be a definitely a stepping stone to Human Deep space exploration, unlocking a REAL opportunity to either of the following manned missions:
- Venus flyby
- Mars flyby
- Venus orbital mission
- Martian orbital mission
- Martial moons mission (Phobos and/or Deimos)

It would provide a proof that both hardware and crew could endure interplanetary missions with duration up to one year, and validate EDL system for velocities bigger than required for return leg of journey from cis-lunar space, while maintaining " a safety net" of a relatively close distance from Earth for the whole mission duration.

Would you like to calculate a TOF from SEL-1 to 200 km LEO or to EML-2 to "share with a class" what would be a duration for a return journey to Earth in case of mission abort scenario?

[Vultur]

If this were really to happen/be funded, who would make the decision, and when would it likely be made/announced?

[fregate]

If this were really to happen/be funded, who would make the decision, and when would it likely be made/announced?

@Vultur - obviously such mission must be included in Federal Space Program (and before that it MUST pass a feasibility study by TsNIIMash), and should be endorsed by both Roskosmos's Strategic Planning and Human Spaceflight Program directorates. It could be announced even today (subject of funding),but IMHO such mission would not happened before 2025.
It might also provide a good objective for qualifying flights for New Generation Manned Transportation Vehicle PTK NP (personally I do not believe in Deep Space version of Soyuz) , SHLV rocket  (decision to be made in Jan 2015) and cryogenic space tug for such mission (KVSTK - a HydroLOX space tug of super heavy class). We'll see - just watch this space!
Ironically in 1988 USSR was closer to fulfil such mission (when Energia LV flew first time)

[asmi]

I've done some back-of-the-envelope calculations - assumed Keplerian orbit with apogee at the SEL2 (1.496*10^9 m) and perigee of 200 km, and I got about 37.5 days from SEL2 to LEO (half of the period). If my understanding of Newton laws in regards to Lagrange points is correct, in reality this trip will take somewhat less time, but it's still about a month.

[fregate]

I've done some back-of-the-envelope calculations - assumed Keplerian orbit with apogee at the SEL2 (1.496*10^9 m) and perigee of 200 km, and I got about 37.5 days from SEL2 to LEO (half of the period). If my understanding of Newton laws in regards to Lagrange points is correct, in reality this trip will take somewhat less time, but it's still about a month.

Good, but we need either SEL-1 to 200 km circular LEO or SEL-1 to EML-2. Please refer to Brauning Orbital Mechanic web site (it has a good example of Hohman transfer http://www.braeunig.us/space/problem.htm Problem 4.20) 
I am sorry but I would be busy translating other slides.   

[asmi]

Good, but we need either SEL-1 to 200 km circular LEO or SEL-1 to EML-2. Please refer to Brauning Orbital Mechnic web (it has a good example of Hohman transfer http://www.braeunig.us/space/problem.htm Problem 4.20) 
I am sorry but I would be busy translating other slides.   

It's too much for me at midnight - will take a look tomorrow But since SEL1 is approximately the same distance from the Earth as SEL2 is, the number above would serve as a good rough estimate.

[fregate]

Good, but we need either SEL-1 to 200 km circular LEO or SEL-1 to EML-2. Please refer to Brauning Orbital Mechnic web (it has a good example of Hohman transfer http://www.braeunig.us/space/problem.htm Problem 4.20) 
I am sorry but I would be busy translating other slides.   

It's too much for me at midnight - will take a look tomorrow But since SEL1 is approximately the same distance from the Earth as SEL2 is, the number above would serve as a good rough estimate.

Plus/Minus - in this case rather Plus, but "Close enough"

[fregate]

V.Bugrov presentation slides on annual Korolev Readings in Bauman Technical University in Jan 2015 - compliments of Alexander Ilin (Luna-7 Team Manager)