SLS - space launch system (3-я попытка)

[Salo]

Дмитрий В. пишет:

Apollo13 пишет:

Salo пишет:
Речь о LE-5B (MB-60).

Но зачем? Чем он лучше RL-10?

Может, дешевле?

У MB-60 тяга около 27 тонн при очень высоком УИ:
http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20110015783_2011016690.pdf

[Mark]

NASA, Industry Test "3D Printed" Rocket Engine Injector, July 11, 2013,
тоже и СЛС двигатели.

"NASA recognizes that on Earth and potentially in space, additive manufacturing can be game-changing for new mission opportunities, significantly reducing production time and cost by 'printing' tools, engine parts or even entire spacecraft," said Michael Gazarik, NASA's associate administrator for space technology in Washington. "3-D manufacturing offers opportunities to optimize the fit, form and delivery systems of materials that will enable our space missions while directly benefiting American businesses here on Earth."
 

 
Этот тип форсунки, изготовленных с традиционными процессами будет принимать более чем на год, чтобы сделать, но с этих новых процессов она может быть произведено в менее чем четыре месяца, с 70 процентов снижение стоимости.

http://www.nasa.gov/content/nasa-industry-test-3d-printed-rocket-engine-injector/

[Петр Зайцев]

Apollo13 пишет:
Но зачем? Чем он лучше RL-10?

УИ 447 против 410 у RL-10 вероятно играет роль.

[Дмитрий В.]

Петр Зайцев пишет:

Apollo13 пишет:
Но зачем? Чем он лучше RL-10?

УИ 447 против 410 у RL-10 вероятно играет роль.

У RL-10B2 - почти 465 единиц.

[Salo]

У MB-60 467 с и тяга в два с половиной раза больше.

[N.A.]

Salo пишет:
http://www.itar-tass.com/c19/807810.html

Национальное управление США по аэронавтике и исследованию космического пространства /NASA/ начало переговоры с японским аэрокосмическим агентством ДЖАКСА о совместной разработке двигателя для новой ракеты, способной доставить экспедицию на Марс.
...
За счет поставок двигателей в США ДЖАКСА рассчитывает снизить стоимость новой ракеты и таким образом повысить ее конкурентоспособность на рынке коммерческих запусков спутников.

Речь о LE-5B (MB-60).

©

http://www.youtube.com/watch?feature=player_detailpage&v=YKwGExwkMuw#t=51s
MB-XX ... represents engine family with applications of wide thrust range targeting for future launch vehicles [Atlas V, H-IIA, D IV].

The MB-60 Cryogenic Upper Stage Engine - A World Class Propulsion System
By William Sack1), Kenji Kishimoto1), Akira Ogawara2), Kimito Yoshikawa2), and Masahiro Atsumi2)
1) Pratt and Whitney Rocketdyne, Canoga Park, California, USA
2) Mitsubishi Heavy Industries, Nagoya Guidance and Propulsion Systems Works, Japan
Mitsubishi Heavy Industries (MHI) and Pratt & Whitney Rocketdyne (PWR) have been co-developing the MB-60 cryogenic upper stage engine since 1999. This engine is sized to provide 267 kN (60 Klbf) of vacuum thrust using liquid hydrogen and liquid oxygen propellants. Key features of this engine include: robust/reliable design, high specific impulse, low weight, and multi-restart capability all combined in an affordable package. On the MB-60 engine, these design objectives are satisfied by combining components that draw on key technologies integrated into a system that is powered using the expander-bleed (or open expander) cycle. At the start of this joint international engine development effort, PWR and MHI focused on demonstrating those technologies that enabled attainment of the engine design goals and mitigated certain development risks. Key technologies that were demonstrated as part of this development effort included: a high performance injector, main combustion chamber (MCC) heat load and resistance characteristics, film cooled nozzle operation, and high performance fuel turbomachinery. In addition to these technology demonstration tests, a demonstrator engine combining all of these technologies was later assembled and tested successfully. This engine served to demonstrate the integrated performance of all the key components (with the exception of the nozzle). It also provided an opportunity to develop and demonstrate other integrated features of the engine. These integrated features included: high chamber pressure operation, the engine start and shutdown sequences, engine specific impulse, and the ability of the MHI/PWR team to co-develop an engine within the constraints imposed by government export regulations. The purpose of this paper will be to discuss each of the various technologies and features listed above in more detail as well as the results of the demonstrator engine test. This paper serves to document the world class capability of the MB-60 engine and establish its readiness for continued development.

1. Introduction
Mitsubishi Heavy Industries (MHI) and Pratt and Whitney Rocketdyne (PWR) began work on the MB-60 engine in 1998. This work was facilitated by a technology assistance agreement (TAA) that enabled co-development of a 267 kN (60 Klbf) cryogenic upper stage engine. Work was divided 50/50 between PWR and MHI. PWR was responsible for the turbomachinery and the nozzle. MHI was responsible for the thrust chamber assembly (TCA), valves, controls, and ducts. System level tasks were performed jointly and it was agreed that engine assembly would be performed in the country in which it was to be delivered.
...

НАСА привычно скрывает правду©: она похоже просто решила нагнуть PWR Aerojet с ценой на J-2X (RL10?), намекнув, что может влегкую обойтись без их услуг, заключив сепаратную сделку с японцами о "совместной разработке" результата совместной разработки.  

[Apollo13]

В общем из презентации достаточно очевидны преимущества MB-60. Однако в ней речь идет о CPS а не о 3-й ступени SLS Block II как я думал.

[Apollo13]

Статья с попыткой оценки реальной стоимости SLS:

http://www.thespacereview.com/article/2330/1

Orion capsule with service module and escape system	$1 billion
SLS first stage, second stage and upper stage	$1 billion
Annual operating and launch facility maintenance costs	$2 billion
1/30 share of development cost	$1 billion
TOTAL	$5 billion cost per launch

[Mark]

Пока немного, если подумаю что стоимость пуска одного Шаттла был более чем 1,5 миллиард $.

[Apollo13]

ИМХО статья написана предвзято, и цифры не внушают большого довения но это мне кажется абсолютно верно:

The current large SLS/Orion development budget of about $3 billion a year precludes any development of any other payloads for the SLS. In an article in 2012, Chris Kraft and Tom Moser point out that development of "the crewed lunar lander, a multi-mission space exploration vehicle (MMSEV), a deep space habitat, a lunar surface rover and other lunar infrastructure" are being crowded out by the SLS development effort, so that by the time the SLS would be ready to use, there would be little or no hardware for it to launch. The same would be true for any specialized hardware needed for asteroid or Mars exploration. In addition, they point out that the "the extra $4 billion to $5 billion per year needed to make an SLS-based exploration strategy work" will be unaffordable given the worsening fiscal situation. The dilemma posed by this situation is that NASA can afford to slowly develop a giant rocket, or develop payloads to launch on the rocket, but not both at the same time.

[Mark]

В покере бюджете НАСА, американски Сенат теперь конкретизировал его идеи бюджета. Он даже является немного о просьбе президента. Не оспаривается между сторонами в этом контексте, что должность требует SLS/Орион больший бюджет.

Последные видео- 70t Space Launch System Takes Flight. Ещо несколо лет...

[pkl]

Mark пишет:
 Пока немного, если подумаю что стоимость пуска одного Шаттла был более чем 1,5 миллиард $.

Имеется в виду стоимость одного рядового пуска шаттла или речь о первом запуске Колумбии 12.04.1981?

[Mark]

pkl пишет:

Mark пишет:
Пока немного, если подумаю что стоимость пуска одного Шаттла был более чем 1,5 миллиард $.

Имеется в виду стоимость одного рядового пуска шаттла или речь о первом запуске Колумбии 12.04.1981?

Я имел виду стоимость пуска Шаттла, эквивалентно в долларах 2010 года. Ето правилно, 2,2 миллиард $ .

[che wi]

First Liquid Hydrogen Tank Barrel Segment for the SLS Core Stage Completed at Michoud
http://www.nasa.gov/exploration/systems/sls/sls-barrel-at-michoud.html

The first liquid hydrogen tank barrel segment for the core stage of NASA's new heavy-lift launch vehicle, the Space Launch System (SLS), recently was completed at the agency's Michoud Assembly Facility in New Orleans.
 
The segment is considered a "confidence" barrel segment because it validates the vertical weld center is working the way it should. The vertical weld center is a friction-stir-weld tool for wet and dry structures on the SLS core stage.
Friction stir welding uses frictional heating, combined with forging pressure, to produce high-strength bonds virtually free of defects. The welding process transforms metals from a solid state into a "plastic-like" state and uses a rotating pin tool to soften, stir and forge a bond between two metal plates to form a uniform welded joint -- a vital requirement of next-generation space hardware.

The vertical weld center, completed in June, is welding barrel panels together to produce whole barrels for the core stage's two pressurized tanks, the forward skirt and the aft engine section. The vertical weld center stands about three stories tall and weighs 150 tons.

The finished barrel segment stands at 22 feet tall, weighs 9,100 pounds and is made of Al 2219, an aerospace aluminum alloy. The segment will be used in structural tests to ensure the integrity of the piece. "This barrel section was welded as part of a plan to demonstrate new weld tool manufacturing capabilities and will be used for futher production tool confidence welding activities," said Steve Holmes, manufacturing lead in the Stages Office at NASA's Marshall Space Flight Center in Huntsville, Ala. "The first fully welded barrel segments are extremely important to test tools and manufacturing processes prior to start of qualification hardware and first-flight articles."

Five similar barrels and two end domes will be constructed to make up the SLS core stage liquid hydrogen tank. The core stage will be more than 200 feet tall with a diameter of 27.6 feet, and it will store cryogenic liquid hydrogen and liquid oxygen that will feed the vehicle's RS-25 engines.

NASA and The Boeing Company engineers have been conducting friction-stir-welding tests at Michoud to ensure quality and safety of flight hardware. Boeing is the prime contractor for the SLS core stage, including its avionics. Marshall manages the SLS Program for the agency.

[che wi]

NASA's Space Launch System Completes Preliminary Design Review

http://www.nasa.gov/press/2013/august/nasas-space-launch-system-completes-preliminary-design-review/

[Mark]

che wi пишет:
NASA's Space Launch System Completes Preliminary Design Review

http://www.nasa.gov/press/2013/august/nasas-space-launch-system-completes-preliminary-design-review/

Завершение предварительного проектирования PDR, ето важны етап для СЛС. После етого будет Key Decision Point-C  который  дает зеленый свет для дальнейшего развития SLS. Патом будет в 2015г. Critical Design Review.

[frigate]

Heavy Lifter by Guy Norris
Aviation Week & Space Technology (N. 26) 26 July 2013

[Salo]

Chris Bergin: SLS completes PDR – Monster Rocket looking for science missions
http://www.nasaspaceflight.com/2013/08/sls-completes-pdr-rocket-science-missions/

[Mark]

Для НАСА работает тоже и художник. Про заказе НАСА, один арт художник сделал картинки СЛС носителя.

http://www.nasa.gov/sites/default/files/styles/946xvariable_height/public/223028_10151541886978091_1563720599_n.jpg?itok=JuhrEUBE

http://www.nasa.gov/sites/default/files/styles/946xvariable_height/public/sls-inflight_afterburn_300dpi.jpg?itok=NDGxXmZI

http://www.nasa.gov/sites/default/files/sls_wireframe_1.jpg

Да, реклама тоже нужна.

[Большой]

Марк, а картинка с размерами СЛС есть?