Author Topic: Russia to Develop Rocket for New-Generation Manned Spacecraft (Read 256061 times)

James Lowe1 · « **on:** 05/12/2006 02:30 pm »

http://mosnews.com/news/2006/05/12/rocketnew.shtml

mr.columbus · « **Reply #1 on:** 05/12/2006 03:18 pm »

Well, this is in line with former press statements that Soyuz 2-3 is the rocket of choice. The question however remains, whether they are still talking of an enhanced Soyuz 2 (as the name suggests), or whether they will construct a totally new rocket (Onega; Soyuz 3). Judging from the lift of 11 tons, could it be that this Soyuz 2-3 really is just an enhancement in the line of Soyuz 2-1a and 2-1b?

Strangely enough, the old presentation by Alan Thirkettle (The one that I posted yesterday) has a slide of the Soyuz 2-3 giving the exact same lifting mass (11tons) and as first enhancement 12.5 and 12.7tons AND states that it is well possible to launch such a Soyuz from the new launch pad in Kourou.

Anybody know how they would enhance launch capabilities from 8 to 11 tons and then to 13 tons without changing the basic structure of the rocket?

Bricktop · « **Reply #2 on:** 05/13/2006 12:24 pm »

Quote

According to TsSKB-Progress press statements earlier this year the difference between Soyuz-2 and Soyuz-2-3 is the NK-33-1 (NK-33 with extendible nozzle) engine on the core stage.

Isn't there also a wide body core stage on a Soyuz-2-3 like it was earlier planned for Yamal launcher?

publiusr · « **Reply #3 on:** 05/18/2006 09:42 pm »

I think so. The Aurora/Christmas Island R-7 was to use NK-33 (on the core stage at least) instead of the single, four-nozzle engine currently used. With a hydrogen upper stage--and other improvements--this may be the 16 ton payload configuration the article spoke of. This pushes it beyond Long March and closer to Ariane 5 and Proton.

Try http://www.russianspaceweb.com
http://www.russianspaceweb.com/soyuz3_lv.html

InfraNut · « **Reply #4 on:** 05/31/2006 06:40 pm »

There is a separate page for Soyuz-2-3 on RussianSpaceWeb: http://www.russianspaceweb.com/soyuz2_3_lv.html

In addition to the very efficient (high ISP) NK-33-1 and the increased fuel capacity on the core stage that is the main part of the first development stage, there is also improved booster engines: 4 x RD-0155

They (RD-0155) seems to be the major part the second step of the Soyuz-2-3 development.

Actually I am not shure whether the core stage shape change is in step 1 or 2. NK-33's will initially be taken from the existing stockpile with only nozzle extensions added as far as i know, so they must be in the first step.

The preceeding Soyuz-2 development is mostly done but the new 3rd stage engines have not been flown yet (Soyuz-2-1B; maybe in september?).

The hydrogen upper stage is part of the Soyuz-3 development, and that remains in doubt, since it not needed for the latest kliper/parom/cargocontainer architecture, and is much more costly than Soyuz-2-3 development.

InfraNut · « **Reply #5 on:** 05/31/2006 07:17 pm »

I wonder why they do not skip RD-0155 booster engine development and go directly to the RD-120.10F that was intended for the Soyuz-3.

Does RD-120 have too high trust to be useful for Soyuz-2-3?

Or, is it much more expensive to develop?

Or, is RD-0155 much further along in development?

Or, has RD-120 development for Soyuz-3 been dropped or is in doubt?

Or, is there another reason?

It might even a possibility that they are already planning to use the RD-120 for Soyuz-2-3, since the latest press coverage I have seen has nothing specific on the booster engine upgrade other than it is implicated that there is one.

Anyone who knows or feel qualified to guess?

publiusr · « **Reply #6 on:** 06/09/2006 10:37 pm »

Not me. They could use Zenit and not have to do any more LV development--but that needs a thaw in Russian Ukraine relations.

fregate · « **Reply #7 on:** 06/24/2009 11:44 am »

Let's re-open topic (even it's already a history: Kliper had been replaced by MTV NG capsular spacecraft):

Possible design of cryogenic hydrogen/LOX propulsion 3rd stage:

Images are from Novosti Kosmonavtiki Magazine Russian space forum.

fregate · « **Reply #8 on:** 08/19/2009 07:27 am »

The first official scale model of LV for a New Generation Manned Transportation Vehicle (RSC Energia - MAKS2009 Airshow):

fregate · « **Reply #9 on:** 08/19/2009 07:29 am »

Spacecraft Scale Model:

johnxx9 · « **Reply #10 on:** 08/19/2009 10:24 am »

Anatoly Zak was spot-on on his info about both PPTS and Rus-M.

The crew Launch vehicle has capability of 23.8 tons to 200 km LEO.
Boosters - 2 X RD-180 (Semi-Cryo)
Core Stage - 1 X RD -180 (Semi-Cryo)
Upper Stage - 4 X RD-0146 (Cryo)

http://www.russianspaceweb.com/ppts_lv.html

EE Scott · « **Reply #11 on:** 08/19/2009 11:14 am »

Great looking LV. Maybe they'll build the Atlas V heavy before ULA. If only they would follow-through and actually do it.

Dmitry_V_home · « **Reply #12 on:** 08/19/2009 01:38 pm »

Quote from: johnxx9 on 08/19/2009 10:24 am

Anatoly Zak was spot-on on his info about both PPTS and Rus-M.

The crew Launch vehicle has capability of 23.8 tons to 200 km LEO.
Boosters - 2 X RD-180 (Semi-Cryo)
Core Stage - 1 X RD -180 (Semi-Cryo)
Upper Stage - 4 X RD-0146 (Cryo)

http://www.russianspaceweb.com/ppts_lv.html

No. First stage=3*RD -180 . Second stage=4 X RD-0146

johnxx9 · « **Reply #13 on:** 08/19/2009 04:32 pm »

Quote from: Dmitry_V_home on 08/19/2009 01:38 pm

Quote from: johnxx9 on 08/19/2009 10:24 am
Anatoly Zak was spot-on on his info about both PPTS and Rus-M.

The crew Launch vehicle has capability of 23.8 tons to 200 km LEO.
Boosters - 2 X RD-180 (Semi-Cryo)
Core Stage - 1 X RD -180 (Semi-Cryo)
Upper Stage - 4 X RD-0146 (Cryo)

http://www.russianspaceweb.com/ppts_lv.html

No. First stage=3*RD -180 . Second stage=4 X RD-0146

It's the same! Eg. with Delta-IVH and Falcon-9H.

Dmitry_V_home · « **Reply #14 on:** 08/19/2009 06:32 pm »

Quote from: johnxx9 on 08/19/2009 04:32 pm

It's the same! Eg. with Delta-IVH and Falcon-9H.

No. Three boosters separates as a uniform fragment.

fregate · « **Reply #15 on:** 08/20/2009 02:42 am »

LV specifications from MAKS-2009:

GLOW (metric tonnes) - 673
Number of stages - 2
Lenght (m) - 61.1
Oxydizer - LOX
1st stage fuel - petrleum-based (naphtil)
2nd stage fuel - hydrogen
LEO Payload (kg) more than 20,000
GTO Payload (kg) at least 7,000
GEO Payload (kg) at least 4,000

LV is a joint project of Samara Space Center (TsSKB-Progress), RSC Energia (Korolev) and State Rocket Center Makeev Design Bureau.

fregate · « **Reply #16 on:** 08/22/2009 02:06 am »

More close up photos from MAKS-2009 Airshow (Credit of Russian NK forum - thank you, Lev):

sdsds · « **Reply #17 on:** 08/22/2009 02:35 am »

Quote from: Dmitry_V_home on 08/19/2009 06:32 pm

Three boosters separates as a uniform fragment.

Thus no need to throttle back the center engine or cross-feed propellants, eh? Also, does the open framework below the second stage imply "fire in the hole" style staging?

fregate · « **Reply #18 on:** 08/22/2009 02:53 am »

Russia Reveals Vision for Manned Spaceflight. IEEE Spectrum article here:
http://www.spectrum.ieee.org/aerospace/space-flight/russia-reveals-vision-for-manned/1

Dmitry_V_home · « **Reply #19 on:** 08/22/2009 12:33 pm »

Quote from: sdsds on 08/22/2009 02:35 am

Thus no need to throttle back the center engine or cross-feed propellants, eh? Also, does the open framework below the second stage imply "fire in the hole" style staging?

According to some information throttle the central engine it is provided on updating of a rocket with load-carrying capacity of 55 tons.