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#60
by
PeterAlt
on 12 Apr, 2013 17:45
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Will that enable the russians to have four crews staying?
NEM will join the ISS in 2015-2016. Currently, 2020 is the end of the nominal existence of ISS. After 2020, no one can specify how many Russian crew members have. While the partners have not agreed to extend until 2028, RSOS will created as part of the future Russian station.
The size of the Russian part of the crew determined capacity of the Soyuz - 3 cosmonauts
We need to consider both as possibilities. That there could be an independent Russian station after 2020, or they'll recertify ISS to go on until at least 2028. As the station advances in its age, we may learn that it just isn't worth it to keep it going beyond 2020, or we may learn that its condition is better than expected. In the later scenario, it makes sense to keep it going as long as it remains healthy enough where the cost to keep it that way isn't prohibitedly expensive.
Will the other power and science module also have a cabin? If so, in total, between the Russian modules, how many cabins in total are there? Plus, there's four US cabins, correct? Will this make up for what was lost when the US Habitation Module was cancelled?
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#61
by
PeterAlt
on 12 Apr, 2013 17:50
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Will that enable the russians to have four crews staying?
No, it will enable them to keep three up there, once one of them gets booted out of the USOS CQs after the fourth USOS crewmember starts flying via commercial crew.
Or temporary quarters for short duration Soyuz visits or Soyuz Expedition hand off visits?
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#62
by
Prober
on 12 Apr, 2013 18:23
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Will that enable the russians to have four crews staying?
No, it will enable them to keep three up there, once one of them gets booted out of the USOS CQs after the fourth USOS crewmember starts flying via commercial crew.
Or temporary quarters for short duration Soyuz visits or Soyuz Expedition hand off visits?
like paying passengers?
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#63
by
baldusi
on 12 Apr, 2013 20:36
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Will that enable the russians to have four crews staying?
No, it will enable them to keep three up there, once one of them gets booted out of the USOS CQs after the fourth USOS crewmember starts flying via commercial crew.
Or temporary quarters for short duration Soyuz visits or Soyuz Expedition hand off visits?
like paying passengers?
Or direct handover of the US crew?
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#64
by
360-180
on 07 Jun, 2013 05:14
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#65
by
Stan Black
on 30 Jun, 2013 14:23
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Just looking through the documentation noticed that NEM is to be used to store propellant?
3.2.3.3 Гидравлический интерфейс должен обеспечивать:
− герметичное соединение топливных магистралей НЭМ и УМ и передачу топлива из ОДУ НЭМ в ТМДТ УМ и обратно;
− разъединение топливных магистралей НЭМ и УМ при отделении НЭМ от УМ по завершении полета НЭМ.
2) для динамических операций по управлению движением МКС (изменение углов крена) на этапах полета в составе РС МКС;
− хранение запаса топлива;
− перекачку топлива из кораблей и модулей РС МКС посредством ТМДТ УМ в топливные баки ОДУ НЭМ и обратно;
− проверку на герметичность состыкованных магистралей дозаправки ОДУ НЭМ и УМ;
− дренаж компонентов топлива при продувке магистралей дозаправки топливом перед отделением кораблей от УМ.
http://www.zakupki.gov.ru/pgz/public/action/orders/info/common_info/show?notificationId=4577238
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#66
by
Danderman
on 30 Jun, 2013 23:25
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Given the NEMs are designed as part of the separate OPSEK station, prop tanks would/should be part of the design.
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#67
by
360-180
on 01 Jul, 2013 08:14
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#68
by
Fuji
on 03 Feb, 2014 04:33
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By order of RSC Energia aerodynamic research of the Ascent Unit for the ISS Science-Power Module is conducted at TsAGIhttp://www.energia.ru/en/news/news-2014/news_01-30.htmlPhase I of aerodynamic research of a new Ascent Unit (AU) intended for delivery to the International Space Station (ISS) of Science-Power Module (SPM) to be developed by RSC Energia in cooperation with industry enterprises has been competed.
For reference:
The Science-Power Module delivery to the ISS is scheduled to be provided in 2017 or 2018 using Proton-M launch vehicle (LV). The new Ascent Unit development is caused by the fact that SPM dimensions exceed standard dimensions of this LV.
Ascent Unit ? What's differences payload shroud?
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#69
by
360-180
on 03 Feb, 2014 11:19
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Ascent Unit ? What's differences payload shroud?
Fairings+Payload
Ascent Unit (КГЧ - космическая головная часть) is a complicated structure. It comprises a lower fairing (ОПО - "support-transition compartment"), payload (НЭМ) and an upper fairing (ГО).
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#70
by
baldusi
on 03 Feb, 2014 11:51
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Will they do like with FGB and cover some parts with fairing and some let exposed, or are they going to use the 5m fairing?
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#71
by
russianhalo117
on 03 Feb, 2014 19:15
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Will they do like with FGB and cover some parts with fairing and some let exposed, or are they going to use the 5m fairing?
Looks more like the latter, but kind of looks wider than that in the picture from the wind tunnel test. Two ascent units appear to be ordered for launch 2017, 2018 to launch SPM modules to ISS.
January 30, 2014
By order of RSC Energia aerodynamic research of the Ascent Unit for the ISS Science-Power Module is conducted at TsAGIPhase I of aerodynamic research of a new Ascent Unit (AU) intended for delivery to the International Space Station (ISS) of Science-Power Module (SPM) to be developed by RSC Energia in cooperation with industry enterprises has been competed.
TsAGI task in this project is to investigate the AU aerodynamics in a wide speed range. Preliminary studies were conducted in 2012 on a small model (a scale of 1:80) in the wind tunnels of machine-building TsNII. The tests at TsAGI are carried out on the model at a 1:20 scale.
The first part of the research program was implemented at TsAGI using wind tunnel Т-109, beginning with December 2013. Currently the model aerodynamic tests are conduced in transonic wind tunnel Т-128.
Hereinafter scientists and specialists are to process and analyze the obtained results.
For reference:
The Science-Power Module delivery to the ISS is scheduled to be provided in 2017 or 2018 using Proton-M launch vehicle (LV). The new Ascent Unit development is caused by the fact that SPM dimensions exceed standard dimensions of this LV.
Information on research conducted at TsAGI is available at the Institute site:
http://www.tsagi.ru/pressroom/news/1045/
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#72
by
InfraNut2
on 04 Feb, 2014 10:01
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Will they do like with FGB and cover some parts with fairing and some let exposed, or are they going to use the 5m fairing?
The wide part will be left exposed. A top fairing covers the docking end and a lower fairing covers the small diameter part. Unless they have changed their minds lately. The RSC Energia video linked by Nicolas PILLET
upthread shows this most clearly.
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#73
by
360-180
on 04 Feb, 2014 12:16
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Will they do like with FGB and cover some parts with fairing and some let exposed, or are they going to use the 5m fairing?
More likely to be as a module Zvezda. The module will be protected lower fairing(ОПО), module's side is opened, the top will be upper fairing(ГО) like Dragon.
This design will not alter the existing launch pad
see
http://forum.nasaspaceflight.com/index.php?topic=29307.msg928378#msg928378
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#74
by
Danderman
on 06 Feb, 2014 14:39
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Time for some perspective here.
RSC Energia normally does not create the hulls used for large pressurized space platforms. The FGB class hulls (2.9 meter diameter) and the Salyut class hulls (4.1 meter) are made at Khrunichev, and Energia's role is final assembly, a system that has been in place for over 40 years.
However, Energia is demonstrating that it can produce 3.3 meter diameter hulls (Node module), and with the the Science Energy Modules, is planning to build 4.3 meter diameter hulls, thus bypassing Khrunichev's traditional role.
What is significant, as well, is that the 4.3 meter hull is too large for existing payload shrouds, which begs the question as to why Energia is baselining a design that cannot easily be flown with existing launchers. Moreover, why a 3.3 meter diameter for the Node module? This all points to tooling for these systems being "imported" from somewhere else, or else Energia is planning a new launcher that can accommodate 4.3 meter diameter hulls.
For some background on this issue, tooling for large diameters is a big, big issue in aerospace. It is trivial to lengthen tanks, but to make them wider costs large money. SpaceX chose to make Falcon 9 1.1 longer than 1.0 precisely for this reason.
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#75
by
baldusi
on 06 Feb, 2014 18:11
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For starters, it could signal a move to 5m fairings. At 4.3 it might fit in an An-124.
And once you decide on a new tooling (because you decided you can take that business of a competitor that jas been messing everything it touched for the las 15 years), you might as well go and order at whatever diameter you see fit.
The 3.3m point to a possible Progress new pressurized compartment.
But I can't stop thinking that 4.3m sounds to a possible export product.
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#76
by
Danderman
on 06 Feb, 2014 18:33
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For starters, it could signal a move to 5m fairings. At 4.3 it might fit in an An-124.
Please remind us why RSC Energia would care about a 5 meter payload fairing.
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#77
by
Ronsmytheiii
on 06 Feb, 2014 21:58
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What is significant, as well, is that the 4.3 meter hull is too large for existing payload shrouds, which begs the question as to why Energia is baselining a design that cannot easily be flown with existing launchers.
While true of existing designs, the future Angara-3 Will use a 4.3 meter fairing according to Russian web:
http://www.russianspaceweb.com/angara3.htmlIf they are trying to make a continuing series of modules rather than a one off, would be entirely logical to use the new diameter as a baseline rather than the old one.
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#78
by
Danderman
on 06 Feb, 2014 22:10
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What is significant, as well, is that the 4.3 meter hull is too large for existing payload shrouds, which begs the question as to why Energia is baselining a design that cannot easily be flown with existing launchers.
While true of existing designs, the future Angara-3 Will use a 4.3 meter fairing according to Russian web:
http://www.russianspaceweb.com/angara3.html
If they are trying to make a continuing series of modules rather than a one off, would be entirely logical to use the new diameter as a baseline rather than the old one.
and the same page says: "The standard version of the Angara-3 would borrow the payload fairing from the Proton rocket" which implies that the outer diameter of the Proton fairing is 4350 mm.
Or else it's an error.
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#79
by
Stan Black
on 06 Feb, 2014 22:14
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How will they deliver it to the launch site?