RD-0169

Last updated

RD-0169 - is a Russian oxygen-methane fueled rocket engine being developed by KBKhA. Liquefied natural gas (methane) is used as fuel, while liquid oxygen is used as an oxidizer. Designed for use in reusable launch vehicles (like Soyuz-7).

Contents

The advantages of the configuraton are: ease of use, environmental friendliness, and the possibility of reusable use. It was planned to achieve a thrust of 200 tons. In the standard version, the pressure in the combustion chamber is planned at 175 kgf/cm2. [1] It is being developed on the basis of RD-0162 with an intermediate and smaller version in the form of RD-0177; two modifications are known: RD-0169A (the engine of the first stage of the Soyuz-7) and RD-0169V (a four-chamber engine of the second stage of the Soyuz-7). The chief designer is Viktor Gorokhov.

Development

In 1994, the Russian government Chemical Automatics Design Bureau (KBKhA) began conducting research on converting the RD-0120, RD-0124, RD-0234, RD-0242, RD-0256 engine series of designs to methane-oxygen propellants. In 1996-1999 design calculations, materials science and technological studies were carried out on a number of liquid-propellant rocket engines with a thrust of 5-240 tf. (RD-0139, RD-0140, RD-0134, RD-0141, RD-0142, RD-0143A, RD-0143K, RD-0144, RD-0149) using oxygen-methane fuel. The demonstration engines RD-0110MD, based on the RD-0110, and RD-0146M, were hot fire tested in ground facilities. [2]

The RD-0162 rocket engine was developed at the Voronezh KBKhA after 2006, initially with an engine version aimed at 2,000 kN (200 tf) thrust, and later, after 2012, a smaller version with a thrust of 416 kN (42.4 tf) in the RD-0162SD version. Engine development funding was included in the Russian Federal Space Program for 2016–2025.[ citation needed ]

In 2012, according to the technical specifications from the Khrunichev Space Center, KBKhA developed a preliminary design of a liquid oxygen-methane engine RD-0162.[ citation needed ]

In December 2016, successful tests of the demonstrator engine RD-0162D2A took place. [3]

At the end of October 2017, a series of fire tests of the RD-0162D2A engine, with a thrust of 40 tons took place; a preliminary design for an oxygen-methane engine with a thrust of 85 tons was subsequently[ when? ] developed. [4] The next stage involves the specification of design documentation for an engine with a thrust of 85 tons, as well as continued preparation of production and the manufacture of power plants for testing individual engine systems. [5]

On September 26, 2019, a contract was posted on the government procurement website for the creation of a methane engine by the Voronezh KBKhA with a targeted completion date of November 15, 2021. According to the technical specifications, the engine was named RD-0177, the thrust should be 85 tf, the sea level specific impulse should be 312 s, and the mass should not exceed 2200 kg.[ citation needed ]

On August 27, 2020, Igor Arbuzov, General Director of NPO Energomash, told the media that individual elements of the units of the future methane engine had now been tested - a gas generator, a mixing head. Now the company is moving on to work directly on the production of the RD-0177 demonstrator engine, which they aim to manufacture in 2022. [6] [ needs update ]

On December 24, 2021, at the testing complex of the Voronezh Rocket Engine Center, hot fire tests of the standard autonomous ignition system of the reusable oxygen-methane rocket engine RD-0177 were successfully carried out. According to the chief designer of the KBHA, Viktor Gorokhov, the planned test program was exceeded: within one test day, rather than five starts, eight were carried out, during which they confirmed the operability and plausibility of reusable use of the engine ignition system for future use as part of the return stages of launch vehicles. [7]

See also

Related Research Articles

<span class="mw-page-title-main">RD-170</span> Soviet (now Russian) rocket engine, the most powerful in the world

The RD-170 is the world's most powerful and heaviest liquid-fuel rocket engine. It was designed and produced in the Soviet Union by NPO Energomash for use with the Energia launch vehicle. The engine burns kerosene fuel and LOX oxidizer in four combustion chambers, all supplied by one single-shaft, single-turbine turbopump rated at 170 MW (230,000 hp) in a staged combustion cycle.

<span class="mw-page-title-main">NK-33</span> Soviet rocket engine

The NK-33 and NK-43 are rocket engines designed and built in the late 1960s and early 1970s by the Kuznetsov Design Bureau. The NK designation is derived from the initials of chief designer Nikolay Kuznetsov. The NK-33 was among the most powerful LOX/RP-1 rocket engines when it was built, with a high specific impulse and low structural mass. They were intended for the ill-fated Soviet N1F Moon rocket, which was an upgraded version of the N1. The NK-33A rocket engine is now used on the first stage of the Soyuz-2-1v launch vehicle. When the supply of the NK-33 engines are exhausted, Russia will supply the new RD-193 rocket engine. It used to be the first stage engines of the Antares 100 rocket series, although those engines are rebranded the AJ-26 and the newer Antares 200 and Antares 200+ rocket series uses the RD-181 for the first stage engines, which is a modified RD-191, but shares some properties like a single combustion chamber unlike the two combustion chambers used in the RD-180 of the Atlas V and the four combustion chambers used in the RD-170 of the Energia and Zenit rocket families, and the RD-107, RD-108, RD-117, and RD-118 rocket engines used on all of the variants of the Soyuz rocket.

<span class="mw-page-title-main">NPO Energomash</span> Russian rocket engine manufacturer

NPO Energomash "V. P. Glushko" is a major Russian rocket engine manufacturer. The company primarily develops and produces liquid propellant rocket engines. Energomash originates from the Soviet design bureau OKB-456, which was founded in 1946. NPO Energomash acquired its current name on May 15, 1991, in honor of its former chief designer Valentin Glushko.

<span class="mw-page-title-main">RD-107</span> Russian rocket engine

The RD-107 and its sibling, the RD-108, are a type of rocket engine initially used to launch R-7 Semyorka missiles. RD-107 engines were later used on space launch vehicles based on the R-7. As of 2021, very similar RD-107A and RD-108A engines are used to launch the Soyuz-2.1a, and Soyuz-2.1b, which are in active service.

<span class="mw-page-title-main">Chemical Automatics Design Bureau</span> Russian rocket engine manufacturer

Chemical Automatics Design Bureau (CADB), also KB Khimavtomatika, is a Russian design bureau founded by the NKAP in 1941 and led by Semyon Kosberg until his death in 1965. Its origin dates back to a 1940 Moscow carburetor factory, evacuated to Berdsk in 1941, and then relocated to Voronezh city in 1945, where it now operates. Originally designated OKB-296 and tasked to develop fuel equipment for aviation engines, it was redesignated OKB-154 in 1946.

<span class="mw-page-title-main">RD-191</span> Russian rocket engine

The RD-191 is a high-performance single-combustion chamber rocket engine, developed in Russia and sold by Roscosmos. It is derived from the RD-180 dual-combustion chamber engine, which itself was derived in turn from the four-chamber RD-170 originally used in the Energia launcher.

RD-0410 was a Soviet nuclear thermal rocket engine developed by the Chemical Automatics Design Bureau in Voronezh from 1965 through the 1980s using liquid hydrogen propellant. The engine was ground-tested at the Semipalatinsk Test Site, and its use was incorporated in the Kurchatov Mars 1994 crewed mission proposal.

<span class="mw-page-title-main">RD-0124</span> Russian rocket engine

The RD-0124 is a rocket engine burning liquid oxygen and kerosene in an oxygen-rich staged combustion cycle, developed by the Chemical Automatics Design Bureau in Voronezh. RD-0124 engines are used on the Soyuz-2.1b and Soyuz-2-1v. A variant of the engine, the RD-0124A, is used on the Angara rocket family's URM-2 upper stage.

The RD-701 is a liquid-fuel rocket engine developed by Energomash, Russia. It was briefly proposed to propel the reusable MAKS space plane, but the project was cancelled shortly before the end of USSR. The RD-701 is a tripropellant engine that uses a staged combustion cycle with afterburning of oxidizer-rich hot turbine gas. The RD-701 has two modes. Mode 1 uses three components: LOX as an oxidizer and a fuel mixture of RP-1 / LH2 which is used in the lower atmosphere. Mode 2 also uses LOX, with LH2 as fuel in vacuum where atmospheric influence is negligible.

<span class="mw-page-title-main">RD-0146</span> Russian rocket engine

The RD-0146 (РД-0146) is a liquid-fuel cryogenic rocket engine developed by KBKhA Kosberg in Voronezh, Russia.

The RD-120 is a liquid upper stage rocket engine burning RG-1 and LOX in an oxidizer rich staged combustion cycle with an O/F ratio of 2.6. It is used in the second stage of the Zenit family of launch vehicles. It has a single, fixed combustion chamber and thus on the Zenit it is paired with the RD-8 vernier engine. The engine was developed from 1976 to 1985 by NPO Energomash with V.P. Radovsky leading the development. It is manufactured by, among others, Yuzhmash in Ukraine.

This page is an incomplete list of orbital rocket engine data and specifications.

<span class="mw-page-title-main">RD-0110</span> Soviet (later Russian) rocket engine

The RD-0110 is a rocket engine burning liquid oxygen and kerosene in a gas generator combustion cycle. It has four fixed nozzles and the output of the gas generator is directed to four secondary vernier nozzles to supply vector control of the stage. It has an extensive flight history with its initial versions having flown more than 57 years ago.

<span class="mw-page-title-main">RD-0110R</span>

The RD-0110R is a rocket engine burning kerosene in liquid oxygen in a gas generator combustion cycle. It has four nozzles that can gimbal up to 45 degrees in a single axis and is used as the vernier thruster on the Soyuz-2-1v first stage. It also has heat exchangers that heat oxygen and helium to pressurize the LOX and RG-1 tanks of the Soyuz-2.1v first stage, respectively. The oxygen is supplied from the same LOX tank in liquid form, while the helium is supplied from separate high pressure bottles.

Voronezh Mechanical Plant is a Russian engine and heavy machinery manufacturing plant. It is located in the city of Voronezh, in the Voronezh Oblast.

<span class="mw-page-title-main">Soyuz-7 (rocket family)</span> Proposed reusable Russian rocket design

The Soyuz-7 or Amur is a partially-reusable, methane–fueled, orbital launch vehicle currently in the design concept stage of development by the Roscosmos State Corporation in Russia. The preliminary design process began in October 2020, with operational flights planned for no earlier than 2028. Amur is intended to substitute for the existing Soyuz-2, at a much lower per launch cost.

<span class="mw-page-title-main">SpaceX Raptor</span> SpaceX family of liquid-fuel rocket engines

Raptor is a family of rocket engines developed and manufactured by SpaceX. The engine is a full-flow staged combustion cycle (FFSC) engine powered by cryogenic liquid methane and liquid oxygen ("methalox").

<span class="mw-page-title-main">M10 (rocket engine)</span>

M10 is a liquid-fuel upper-stage rocket engine in development by Avio on behalf of European Space Agency for use on Vega E. The engine, initially known as LM10-MIRA, was a derivation of the existing Russian RD-0146 engine and result of a past collaboration between Avio and Chemical Automatics Design Bureau (KBKhA) ended in 2014 after the escalation of the Russo-Ukrainian conflict and consequent economic sanctions. On May 6, 2022 engine testing campaign started at Salto di Quirra, Sardinia, with consequent maiden flight on a Vega-E launcher expected by 2026 from Guiana Space Centre.

Archimedes is a liquid-fuel rocket engine burning liquid oxygen and liquid methane in an oxidizer-rich staged combustion cycle. It is designed by aerospace company Rocket Lab for its Neutron rocket.

The RD-0126 "Yastreb" was a liquid-fuel cryogenic rocket engine burning liquid hydrogen and liquid oxygen, developed by KBKhA Kosberg in Voronezh, Russia. The RD-0126 variant had a conventional de Laval nozzle, while the RD-0126E (РД-0126Э) was designed and constructed with an expansion-deflection nozzle. Both variants were designed to produce 39.2 kN (8,812.5 lbf) of thrust.

References

  1. ↑ "ДВИГАТЕЛЬ РД-0162". Archived from the original on 5 September 2019.
  2. ↑ РАБОЧИЕ ПРОЦЕССЫ В РАКЕТНОМ ДВИГАТЕЛЕ МАЛОЙ ТЯГИ НА ГАЗООБРАЗНЫХ КОМПОНЕНТАХ ТОПЛИВА КИСЛОРОД И МЕТАН, mai.ru
  3. ↑ "Новейший кислородно-метановый двигатель прошёл испытания". pp. 3DNews. Archived from the original on 19 February 2017.
  4. ↑ ""Энергомаш": создание нового двигателя в США стимулирует нас к развитию". RIA Novosti. Archived from the original on 21 October 2017.
  5. ↑ "КБХА. ЗАВЕРШЕНА РАЗРАБОТКА ЭКСКИЗНОГО ПРОЕКТА НОВОГО КИСЛОРОДНО-МЕТАНОВОГО ДВИГАТЕЛЯ ТЯГОЙ 85 ТОНН". Archived from the original on 1 September 2018.
  6. ↑ "Глава НПО "Энергомаш": постепенно возвращаемся к переговорам с зарубежными партнерами". TASS. Archived from the original on 28 August 2020.
  7. ↑ "В ВЦРД испытана штатная система зажигания кислородно-метанового двигателя". 24 December 2021. Archived from the original on 24 December 2021.
This page is based on this Wikipedia article
Text is available under the CC BY-SA 4.0 license; additional terms may apply.
Images, videos and audio are available under their respective licenses.