РД на метане

[Bell]

А подскажите кто-нибудь, какое соотношение компонентов в сладком ГГ на метане? Очень надо

Даже иначе вопрос поставлю - при каком минимальном содержании метана в кислороде (избыток последнего) возможно горение?

[Salo]

Роман, ты что-то попутал. Горение метана при избытке кислорода возможно вплоть до исчезающих долей процента. Вот с избытком метана другая картина.
Соотношение компонентов в С5.86:
 

[fagot]

В принципе, в двухзонном ГГ соотношение может быть любым, другое дело, что при большом избытке метана наверняка полезет сажа.

[Плейшнер]

Bell пишет:
при каком минимальном содержании метана в кислороде (избыток последнего) возможно горение?

В воздухе минимальное содержание метана  5%
В кислороде - хз, но например у водорода  4% что в воздухе что в кислороде
( хотя для метана в кислороде как будто попадалось, что нижняя граница  снижается до 4, но это не точно)

[Salo]

5% это для взрыва.

[Плейшнер]

Salo пишет:
5% это для взрыва.

Ниже 5 - не загорается, выше 15 - горит без взрыа

[Salo]

https://twitter.com/blueorigin/status/659884423425318912

Blue Origin ‏@blueorigin  
BE-4 team: Nice job on today's Critical Design Review. Making progress on America's ride to space! #VulcanRocket  
 

[NK]

РД-0164 изящней

[NK]

я так понимаю если все пойдет хорошо, БЕ осталось лет пять готового изделия

[Apollo13]

KR пишет:
я так понимаю если все пойдет хорошо, БЕ осталось лет пять готового изделия

2

[Seerndv]

Salo пишет:
https://twitter.com/blueorigin/status/659884423425318912

Blue Origin ‏@ blueorigin
BE-4 team: Nice job on today's Critical Design Review. Making progress on America's ride to space! # VulcanRocket
 

Это те же яйца, но вид сбоку?
Или ещё раз пересмотрели ранее размещавшееся:

[Bell]

Salo пишет:
Роман, ты что-то попутал. Горение метана при избытке кислорода возможно вплоть до исчезающих долей процента. Вот с избытком метана другая картина.
Соотношение компонентов в С5.86:

Действительно перепутал, наоборот речь была о сладком газе с избытком метана.
Ну ты наверно понял, почему спрашиваю Тема на Абазе про газ и Украину.

[Salo]

http://www.balancer.ru/g/p3989068

Bell пишет:

Во!! То что надо!
 
источник:
 

[Salo]

https://www.nasa.gov/centers/marshall/news/releases/2015/nasa-tests-methane-powered-engine-components-for-next-generation-landers.html

Oct. 28, 2015
NASA Tests Methane-Powered Engine Components for Next Generation Landers


A thruster — the combination of an injector and chamber — roared to life in a series of tests recently at Marshall's Test Stand 115. The distinct blue flame is produced by the thruster's fuel, methane. Methane is a promising fuel for the journey to Mars, as it is more stable than liquid hydrogen, can be stored at more manageable temperatures and could be produced on Mars from local resources, using in-situ resource utilization. Data gathered from testing will be used to develop an optimized thruster assembly that could support engine designs for a Mars lander and many other in-space applications.
Credits: NASA/MSFC  
 
NASA tested components for an engine that could be used for Mars landers powered with methane, a fuel that has never before propelled a NASA spacecraft.
A spectacular blue flame erupted as a rocket engine thruster roared to life in a series of tests recently at NASA's Marshall Space Flight Center in Huntsville, Alabama. The blue flame, not typical of most engine tests, was the signature of the thruster's fuel -- methane.
"With the current configuration, these methane thrusters could propel a small lander," said Steve Hanna, lead for NASA's Advanced Exploration Systems at Marshall. "With the data gained from these tests, the technology is scalable for even larger applications for in-space engines and larger landers."
Methane is a promising fuel for the journey to Mars. Methane -- more stable than liquid hydrogen, today's most common rocket fuel -- can also be stored at more manageable temperatures. Methane may be recovered or created from local resources, using in-situ resource utilization (ISRU).
With a storage temperature similar to that of liquid oxygen -- the oxidizer for methane-powered engines -- methane's storage tanks will require less insulation, leading to more affordable tanks. Methane is also denser than liquid hydrogen, which allows for smaller tanks.
With the Mars 2020 mission, NASA plans to will demonstrate ISRU technologies that could enable propellant and consumable oxygen production from the Martian atmosphere. If successful, astronauts could create both the fuel and oxidizer needed to propel an ascent vehicle to Martian orbit.
The current thruster being tested, which is part of a pressure-fed design, produces 4,000 pounds of thrust. To achieve the 25,000 pounds of thrust needed for larger descent/ascent landers on Mars, and enable engines to be throttled as needed, Marshall engineers are also developing a pump-fed engine design. In the design, a turbopump will use a turbine capable of up to 95,000 revolutions per minute to deliver methane to the thruster, allowing for higher thrust levels.
Marshall engineers recently successfully conducted preliminary testing and facility checkout of a turbopump for a methane engine. Engineers plan to perform a series of tests later this year to verify the turbopump, previously tested with liquid hydrogen, can be used with either fuel, and is capable of delivering enough fuel to power a large methane engine.
Thrusters -- the combination of an injector and chamber, known as thruster assemblies in larger engines -- fueled by methane with a liquid oxygen oxidizer, have been under development at Marshall for the last decade. Both the thruster and the turbopump were manufactured with additive manufacturing, or 3-D printing.
Not only does 3-D printing allow for quicker production times and a reduction in the machining and brazing required with traditional fabrication processes, it also allows for the addition of thermocouple ports along the length of the chamber. These ports communicate with the chamber's coolant channels, providing discrete temperature data never before available.
"This data will help critical thermal modeling," said Sandra Greene, an engineer in Marshall's Propulsion Systems Department. "That's why the thermocouple ports are so exciting -- we not only get the inlet and exit temperature of the methane, but we also get data to help us verify what is happening inside the chamber's coolant system."
This unique thermal data will be used to anchor thermal models to optimize the design of the thruster for a full regenerative engine system that uses methane as fuel.
A regenerative engine system cycles fuel through channels within the chamber to cool the chamber before and during ignition. In previous methane thruster development efforts at Marshall, chamber designs were primarily uncooled -- using ablative or high-temperature refractory materials to prevent the chamber from overheating.
"To maximize performance, a regeneratively cooled chamber is desired," said Greene. "This chamber is Marshall's first attempt at such a design in a methane-powered system."
With NASA closer to sending astronauts to Mars than ever before, these tests and the technology they inspire could enable the first steps on the Martian surface to come from astronauts exiting a lander driven by a spectacular blue methane flame.
To view video of the methane-powered thruster test, click .

Kim Newton
 Marshall Space Flight Center, Huntsville, Ala.
 256-544-0371
kimberly.d.newton@nasa.gov
 
Last Updated: Oct. 28, 2015
Editor: Lee Mohon


The distinct blue flame in recent tests is produced by the thruster's fuel, methane. Data gathered from testing will be used to develop optimized components that could support engine designs for NASA's next generation of exploration landers.
Credits: NASA/MSFC/David Olive
 

Marshall engineers recently performed preliminary "chill" tests on a 3-D printed turbopump to be used with a methane-powered engine. The tests, a precursor to full-scale testing, verified hardware and test instrumentation for the temperatures required during the firing of a methane engine.
Credits: NASA/MSFC
 

The 3-D printed, methane-powered thruster consists of an injector, left, and chamber, right. The 3-D printing techniques allow Marshall engineers to incorporate thermocouple ports into the chamber's design, which collect discrete data during testing.
Credits: NASA/MSFC

[silentpom]

это с морфеем никак не связано?

[Salo]

http://www.federalspace.ru/21849/

РОСКОСМОС: ПЕРСПЕКТИВЫ СОТРУДНИЧЕСТВА С РЕСПУБЛИКОЙ КОРЕЯ
23.11.2015 16:44
 

   23 ноября 2015 года состоялась встреча генерального директора Госкорпорации «РОСКОСМОС» Игоря КОМАРОВА и Чрезвычайного и Полномочного Посла Республики Корея в России Пак Ро Бёка.

   В рамках углубления межгосударственного взаимодействия в области освоения космоса, обсуждались вопросы сотрудничества в области метановых двигателей, электронной компонентной базы космического назначения и пускового комплекса для будущих ракет-носителей.

[Seerndv]

Мож чего пропустил в октябре, в связи с потрясениями на работе, но вот это было?

СПГ для ЖРД
 
 Топливо из кухонной конфорки весьма эффективно для ракетных двигателей

Алексей Яковлев
 
Ракетно-космический мир на перепутье: глобальные тенденции требуют снизить стоимость и увеличить экологическую безопасность космических услуг. Конструкторам приходится изобретать новые жидкостные ракетные двигатели (ЖРД) на экологически чистых видах топлива, заменяя дорогой, крайне энергоемкий жидкий водород дешевым сжиженным природным газом (СПГ) с содержанием метана 90–98 процентов. Это горючее в паре с жидким кислородом позволяет создавать новые высокоэффективные и недорогие двигатели с максимальным использованием уже существующих элементов конструкторского, материального, технологического и производственного задела. 
...

Подробнее: http://www.vko.ru/oboronka/spg-dlya-zhrd

[Salo]

АниКей выкладывал 2 страницами ранее  http://novosti-kosmonavtiki.ru/forum/messages/forum13/topic581/message1425684/#message1425684

[Salo]

http://horizonsas.com/products/

Black Arrow 2 is Horizon's first project, named after the first British rocket to launch a satellite in 1971.
Standing nearly 25m tall, it is a two stage orbital space launch vehicle designed to reliably deploy small satellites in support of missions for the UK Space Agency (UKSA), European Space Agency (ESA) and commercial satellite companies from all around the world.
The first stage produces 360,000 Newtons of thrust (approx. 81,000 lbf) and the upper stage produces 45,000 Newtons (approx. 10,000 lbf).
Both stages are fueled with clean-burning Liquid Oxygen (LOX) and Liquefied Natural Gas (LNG) propellants.

[silentpom]

жаль, что не на перекиси