РБ Centaur - История и перспективы

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Integrated Cryogenic Evolved Stage ICES  (ICES) Program (Lockheed Martin).






Long Duration In-Space Stage with cryogenic operation for the long-duration (COLD) system.

To satisfy NASA's exploration needs for a cross cutting, extensible LO2/LH2 stage, Lockheed Martin is
developing the Integrated Common Evolved Stage (ICES). The ICES is designed to provide an efficient,
common platform that is extensible to all transportation aspects of the exploration mission. The ICES is specifically
designed to cross cut to nonexploration applications, and to provide improved support for existing NASA, DoD, and
commercial launch requirements.

The ICES concept will enable NASA to meet the strategic technical challenges that support a sustainable
exploration program. Cross-program commonality is the key to enable a robust, reliable, and sustainable exploration
program. Commonality spreads the nonrecurring and infrastructure costs between multiple users to reduce the cost
for everyone.

The ICES development is planned as the first phase of any future Atlas evolution and is composed of a larger
volume Centaur. This is achieved through significantly increasing stage diameter while maintaining successful
Centaur heritage design concepts. The ICES is intended to become the foundation for a modular system of stages to
satisfy a wide variety of uses for space exploration from upper stages to in-space stages to propellant depots. The
ICES places the tremendous efficiencies of cryogenic propellants into the hands of the Moon and Mars mission
architects. This allows a significant reduction in launch mass relative to Saturn, which primarily relied on the much
lower efficiency of storable propellants.

The ICES is based on a simple modular design as shown in fig. 13. Common domes are joined to barrel panels
through the friction-stir welding process. The barrel panels come in multiple segments that allow stages of variable
propellant capacity. The common-thrust structure accommodates either 1, 2, 4, or 6 RL-10 engines. The longer ICES
versions with four or six engines are suitable for upper stage and Earth-departure stage (EDS) applications that carry
very heavy payloads. Shorter ICES versions with one or two engines would be used for traditional Geosynchronous
Transfer Orbit (GTO) missions, interplanetary missions, or in-space stages such as lunar orbit insertion (LOI), transearth
injection (TEI), or lunar descent stage.

ICES will take advantage of the existing Centaur subsystems such as avionics, pneumatic, and propulsion
elements. The majority of these subsystems are directly applicable with little or no changes required.

Ref: Atlas Centaur Extensibility to Long-Duration In-Space Applications
AIAA 2005-6738
Bernard F. Kutter, Frank Zegler, Sam Lucas, Larry Hines, Dr. Mohamed Ragab, Iran Spradley and Josh Hopkins.
Lockheed Martin Space Systems Company

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Сравниваем ТТХ Centaur, Delta IV Upper Stages, 12KRB в качестве РБ (EDS Earth Departure Stage)
для трассы Земля-Луна:

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Centaur and Saturn IV

In April 1960, NASA contracted Douglas Aircraft Company to build the S-IV stage.  

Several months later, von Braun decided that the stage would be powered by six
67 kN thrust RL-10 engines (Pratt & Whitney), saving the time and
cost of upgrading the engine to 89 kN of thrust.
 
Rocketdyne was contracted to build the J-2 engine.

S-IV stage for SA-9 at Santa Monica, November 1964.

The S-IV stage's six RL10-A-3 engines were arranged in a hexagonal
pattern. A truncated cone-shaped thrust structure transferred engine
force to the propellant tank walls. Just above the engines was an elliptical
LOX tank and above that was a cylindrical LH2 tank. A common bulkhead
separated the two tanks. Six LH2 feed lines, one for each engine,
wrapped around the outside of the LOX tank.



RL10-A-3 engine specifications

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Centaur and Ares V

Although the Ares V offers the greatest potential value to science, the launch vehicle must be
made capable of accommodating science payloads. Science missions are more likely to take advantage of
the Ares V if these capabilities are designed into the vehicle rather than their needing to be added later.
A potentially serious issue for using Ares V for planetary missions concerns the need for a
dedicated upper stage to provide high excess escape velocities for spacecraft (velocity squared per second
squared, known as C3). Neither the current most likely upper stage, the Atlas V Centaur III Dual Engine
Configuration, nor the previous Titan IV Centaur, would make efficient use of the Ares V payload shroud
volume and may present other design problems such as load (weight)-bearing capability (see Figure S.1).
Planetary missions could better use an upper stage that is shorter and takes advantage of the full width of
the Ares V; however, the development of such a stage could be expensive. In order for Ares V to be
attractive for future science missions, vehicle designers will have to consider the requirements of potential
science missions.

Recommendation: If NASA wishes to use the Constellation System for science missions, then it
should preserve the capability for Orion to carry small scientific payloads and should ensure that
the Ares V development team considers the needs of scientific payloads in system design.

The Constellation System offers great potential for space science missions, but the costs of the
types of missions evaluated in this report may be unaffordable. Many of these missions have such large
costs that they might require that funds be taken from numerous other, smaller science missions. which
could create imbalances in the science programs in the individual disciplines. These missions will have to
be evaluated carefully within the NRC's decadal survey process. NASA will have to proceed with
caution as it develops these new capabilities.

Because virtually all planetary missions require some sort of upper stage, and because NASA
recently increased the overall length of Ares V, the Solar System Science Workshop participants were
particularly concerned about the amount of usable volume inside the shroud. According to one rough
estimate, adding a Centaur upper stage to Ares V would leave only 4 meters from the top of the Centaur
to the top of the shroud—significantly less than the length of a flagship-class spacecraft such as Cassini.



FIGURE S.1 2 possible configurations of the Ares V shroud - the current baseline shroud and a proposed
extended shroud. Shown inside the shrouds are two possible Centaur upper-stage configurations: the Titan IV
Centaur (left) and the Atlas V Centaur III Dual Engine Configuration (right). Any spacecraft carried atop an upper
stage would have severely restricted volume constraints. Neither shroud option takes advantage of the width of the
Ares V shroud. SOURCE: Adapted; courtesy of NASA.

General Cost Category in Which This Mission Concept Is Likely to Fall
Conventional propulsion (using the Ares V with an additional Centaur upper stage) and the radioisotope electrical propulsion (REP)
place this missions into the $1 billion to $5 billion category.

Source: Launching Science: Science Opportunities Provided by NASA's Constellation System

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Centaur/CEV/Service Node mission to Earth Moon Lagrange points

Ultimately, a servicing node at Earth-Moon L1 or L2 would make it possible to construct large
astronomical observatories that surpass even Ares V single-launch capabilities, as shown in Figure 4.7. It
could also be used to facilitate lunar exploration goals, and in the far-term, an Earth-Moon L2 point
servicing mission could provide a stepping stone between lunar missions and Mars missions. It could be
used as a test site for issues such as duration in space, distance from Earth, communication delays, and
supply issues. However, these missions might prove to be expensive, and it would be reasonable to
expect both NASA's Science Mission Directorate and the Exploration Systems Mission Directorate to
share these costs.

FIGURE 4.6 Concept for in-space servicing throughout the Earth-Moon system. This figure shows the stack after
Earth orbit rendezvous of the Orion with the Centaur and servicing node. The Centaur is ejected before rendezvous
with the observatory. SOURCE: Courtesy of NASA.

FIGURE 4.7 A chart illustrating the concept of operations for a servicing node at Earth-Moon L1. The facility to be
serviced, in this case an astronomical observatory, travels via low-energy (i.e., velocity) transfer to the Earth-Moon
L1 (or L2) location, where it is met by the Orion/CEV and servicing node module, which features an airlock. This
system can remain on-site for 2-3 weeks and, perhaps, carry out other tasks. Upon completion of the servicing
mission, the Orion crew module returns to Earth and the servicing node may remain at one of the libration points for
further duties. SOURCE: Courtesy of NASA.

Service Node как две капли воды (если забыть про солнечные батареи) похож на орбитальный отсек "Шеньжоу"  

[Salo]

На Шэньчжоу-7 их уже не было. :wink:

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Centaur Earth Departure Stage and EADS Lunar Lander:


Increased lunar cargo capabilities through international industrial cooperation
Robert Ford, Lockheed Martin Space Systems
and Chris Gilbert, Astrium Space Transportation
Space Exploration Architecture Workshop 7- 8 July 2008, Noordwijk

Lockheed Martin and Astrium have been cooperating on space exploration since 2004
• Agency space exploration strategies are ambitious but likely will be unable to cover all
necessary elements of a sustainable exploration program
• ESA and other space agencies are considering complementary exploration programs
• Lockheed Martin and Astrium have begun to identify areas in which core exploration goals can
be usefully and economically enhanced and extended through international industrial
cooperation.
• Commercial space transportation services offer a potential means of reducing transportation
costs.
• Lockheed Martin and Astrium have assets which could be combined to provide timely,
innovative and cost-effective solutions to Agency customers with coherent exploration goals
• As an example in the context of the Space Transportation Architecture Study we have
examined the feasibility of exploiting Ariane 5 and Atlas V to deliver increased cargo mass to
the lunar surface.


In-orbit assembly is a viable strategy in support of space exploration missions. Звучит один к одному
как высказывание Леонида Ильича "Долговременные орбитальные станции — магистральный путь развития советской космонавтики" (C)  

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Lockheed Martin лунный лэндер на базе РБ Centaur (2006):

Centaur Application to Robotic and Crewed Lunar Lander Evolution
AIP Conf. Proc. -- January 30, 2007 -- Volume 880, pp. 779-786
SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2007: 11th Conf Thermophys.Applic.in Micrograv.;
24th Symp Space Nucl.Pwr.Propulsion; 5th Conf Hum/Robotic Techn &Vision Space Explor.; 5th Symp Space Coloniz.;
4th Symp New Frontrs &Future Con; DOI:10.1063/1.2437517


FIGURE 2. Atlas HLV with Robotic Lunar Lander as Payload.

FIGURE 3. Conceptual Horizontal-Landing Centaur-Based Robotic Lunar Lander with Required Modifications.

TABLE 1. Robotic Lander Nominal Weights.

FIGURE 4.Conceptual Centaur-Based Lunar Lander.

TABLE 2. Crewed Lander Mass History (Weights).

FIGURE 5. Descent, Landing and Abort Concept.

FIGURE 6. Aft View Showing Descender Cargo.

FIGURE 7. Solar Power and Waste Heat Radiation System Deployment



Преложенный ЛМ лунный лэндер на основе РБ Центавр (с горизонтальной компоновкой по схеме "Харриера")
не получил поддежки в НАСА - для лунного лэндера LSAM "Altair" была выбрана "классическая"
вертикальная схема (Аполло Lunar Module) с раздельными посадочной и взлётной ступенями ("ИЗБА-НА-КУР-НОЖ" ).

[zyxman]

Lockheed Martin лунный лэндер на базе РБ Centaur (2006):

Спасибо, забавные картинки

[pkl]

Эт что? Лунный пикап? :lol:

[Lev]

Это очередные Мурзилки. Просто в Роскосмосе еще не набрались наглости выдавать подобные мурзилки за реальное железо.
Пиар, однако. Роскосмосу надо учиться и учиться выдавать фантазии за реальность и под самые глючные фантазии выскребать бабло..

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2 Lev
LM лоббирует готовые опробованные разработки (Centaur достался им по наследству) - по английски это называется re-use.  
Для компании это намного выгоднее чем начинать разработку нового изделия с НУЛЯ при довольно сжатых сроках и высокой степени риска.
IMHO концепт лэндера с горизонтальной компоновкой более предпочтителен для ручной посадки (оптимальный дизайн с точки зрения эргономики),
хотя усложнет управление лэндером при посадке.

Не мытьём так катанием ЛМ добилась своего - РБ Центавр будет устанавливаться и на Арес I (не-пилотируемая миссия), и на Арес V для запуска АМС.


Ares I Notional Configuration Options for Science Missions

[pkl]

А что? Хороший разгонник. Нам о таком только мечтать.

[zyxman]

Роскосмосу надо учиться и учиться выдавать фантазии за реальность и под самые глючные фантазии выскребать бабло..

Роскосмосу это пока не надо.
Это у них там, на диком западе, налогоплательщик (и пайщик), не просто может а периодически требует отчетов, плюс кто-то может и в суд подать если будет сомнение в объективности, поэтому и частные фирмы и госструктуры вынуждены постоянно рисовать "веселые картинки", частично как отчеты понятные обывателю, частично как промоушен (и продажи и создание положительного имиджа).

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Ares I Notional Configuration Options for Science Missions

ATK Plans Commercial Ares I, Aviation Week Apr 9, 2008

ATK, which is building the first stage of NASA's Ares I crew launch vehicle by recycling the solid-fuel booster it builds
for the space shuttle, wants to make the same capability available to other users for missions without crews.

Ron Dittemore, president of ATK Launch Systems presented  at the 24th National Space Symposium in COLORADO
SPRINGS, Colo a possible concepts that include an Ares I with a payload shroud for launching big geosynchronous
communications satellites, and a version with a Centaur stage mounted atop the NASA-designed, Boeing-built Ares I
cryogenic upper stage for planetary missions.

As configured to launch NASA's Orion crew exploration vehicle, the Ares I is being designed to lift 56,500 pounds to low
Earth orbit. But ATK also is studying upgrades that could add another 9,910 pounds to that capability. Those include
higher operating pressure in the motor, an increased throat diameter, a shift to HTBP propellant from the PBAN used on
the NASA systems, and a graphite composite case.

Ares I грузоподьёмность:
- пилотируемая версия (CEV) - 25628 kg;
- коммерческая версия (модифицированная РН) - 30123 kg  

NASA says Ares I could send payload to the Moon , Flight International 21/10/08

NASA has concluded that a single Ares I crew launch vehicle could send a 454kg (998lb) payload to the
Moon using a 1,750kg robotic lander.

The US space agency has been examining unmanned missions for the Ares rocket, the primary mission for which
is to launch the Orion crew exploration vehicle. An unmanned mission considered by NASA is delivering a
communications satellite into lunar orbit and placing a sample return vehicle with its ascent craft on to the surface.

"Utilising two Ares launches, with one launch delivering a liquid hydrogen, liquid oxygen trans-lunar injection stage,
can deliver a much larger payload of 4,121kg [to the Moon's surface]," says the NASA Marshall Space
Flight Center study's paper, submitted for the 59th International Astronautical Congress.

NASA has also analysed the use of Ares I for interplanetary probes and decided that a departure-stage solid rocket
motor, larger than the Alliant Techsystem's Star 63F motor, would allow a probe to be sent to the inner planets and
the main asteroid belt.

Meanwhile, a dual Ares I launch that used the Lockheed Martin Centaur as a departure stage could send a robotic
spacecraft to the outer planets.

[Чебурашка]

С коммерческого Ares I вряд ли что получиться, а вот пересадить все тяжёлые АМС NASA (типа New Horizons, MSL и JUNO) и другие прикладные аппараты вполне.

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Re: КВРБ «Двина-КВТК»

днища совмещенные но всё же двойные! это на атласе. про дельтовский Центавр такой информации не встречал надо будет мануал перечитать.
Fregate вы нигде на встречали информацию о сухой массе Центавра выводящего КА на ГСО, то есть с дополнительным набором оборудования для длительных миссий?

У Дельты баки кислорода и водорода разделены.
В документе "Lockheed Atlas V Mission Planners Guide" есть секция про Centaur Extended Mission Kit, к сожалению в Сети выложено только содержание документа - попробую порыться дома.

Может быть и здесь:
Taming Liquid Hydrogen: The Centaur Upper Stage Rocket, 1958-2002. By Virginia P. Dawson and Mark D. Bowles. Washington, D.C.: NASA History Office [NASA SP-2004-4230], 2004. Tables. Index. List of Interviews. Pp xiii, 289.

А вообще в форуме есть отдельная тема по Центавру :idea:

http://rapidshare.com/files/255213826/ATLAS_HISTORY__VEHICLE_DESIGN__AND_PRODUCTION.pdf.html

вот ссылка))

мне вообще то интересно почему наши не могут такой легкий РБ сделать

[mescalito]

собственно обозначу тему для обсуждения

почему сухая масса КВРБ больше чем у Центавра при почти одинаковой массе заправляемого топлива?

моя версия:

тяжелая бортовая система управления (ЭВМ и ее СОТР и др.)

тяжелые баки (по сравнению с Центавром)

масса КВРБ указывается для полетов на ГСО а масса Центавра указывается для полетов на ГПО то есть без дополнительного набора оборудования обеспечивающий долговременный полет (гелий, аккумулятор, гидразин, теплозащита и др.)

различный подход к посчету сухой массы (то есть мы включаем то что не включают они и наоборот)

прошу высказываться))

[Старый]

Очевидно все факторы вместе взятые.

[Старый]

Для более правильнеого сравнения лучше брать не атласовский а титановский Центавр.