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24-399: The RD-0146 is the first Russian rocket engine to burn liquid oxygen and liquid hydrogen in the expander cycle, in which turbopumps are driven by waste heat absorbed in the nozzle and combustion chamber. The RD-0146 featured the fastest-spinning turbopump of any serially produced rocket engine: the fuel turbopump spun at over 120,000 rpm. The RD-0146M variant uses liquified natural gas as

48-479: A Vega-E launcher expected by 2026 from Guiana Space Centre . The M10 engine is the first operational European methane rocket engine, conceived for use on upper stages of future Vega-E and Vega-E Light launchers, in which will replace both the solid-fueled Zefiro 3rd stage and hydrazine-fueled AVUM 4th upper stage. An industrial team directed by Avio with companies of Austria , Belgium , France , Czech Republic , Romania and Switzerland will manufacture

72-435: A preburner . It is also the first to have a nozzle extension without an active cooling system, as well as the first engine by KBKhA to feature separate fuel and oxidiser turbopumps. The engine is capable of five firings and thrust control in two planes. According to the developer, the lack of a gas generator system ensures higher reliability of the engine for multiple firings, by removing the potential of an ignition failure in

96-564: A 7.5t thrust LM10-MIRA demonstrator engine. The engine was successfully tested in June 2014 in Voronezh , Russia . After the end of the collaboration with KBKhA, Avio continued the development of M10 under the Vega-Evolution program returning to the original target thrust of 10t. Objectives were finalizing development of main subsystems such as turbopumps , valves , igniter , thrust vectoring and

120-400: A boiling point of 90.19 K (−182.96 °C; −297.33 °F) at 1 bar (15 psi). Liquid oxygen has an expansion ratio of 1:861 and because of this, it is used in some commercial and military aircraft as a transportable source of breathing oxygen. Because of its cryogenic nature, liquid oxygen can cause the materials it touches to become extremely brittle. Liquid oxygen is also

144-616: A contract to KBKhA to develop a new engine, the RD-0146U, for use on its Proton and Angara launch vehicles. The engine was to be of around 10 tf (98 kN) thrust class. Soon after, on 7 April 2000, the American company Pratt & Whitney Rocketdyne entered an agreement with KBKhA, financing the development of the RD-0146. Pratt & Whitney would gain exclusive international marketing rights to this variant. In 2002, RSC Energia awarded KBKhA with

168-705: A contract to develop the RD-0146E variant for use on its Onega launch vehicle, a Soyuz-2 variant with a fully cryogenic upper stage. In 2008, KBKhA began development of the RD-0146D variant for use on the KVTK upper stage for Angara A5. In 2009, TsSKB Progress selected the RD-0146 for use on the new Rus-M launch vehicle's second stage. The first RD-0146 engine was planned to be delivered to Pratt & Whitney in May 2001. Delays attributed to subcontractor production troubles postponed this, and

192-414: A fuel instead of hydrogen, while the RD-0146D variant is projected to produce specific impulse ( I sp ) as high as 470 seconds (4.6 km/s) in a vacuum. The engine has been proposed for use on multiple carrier rockets throughout its history. RD-0146 variants were, at various times, selected to power new upper stages for Proton , Angara , Onega (a development of Soyuz-2 ), and Rus-M . As of 2022,

216-604: A new ALM 3D printed Thrust Chamber Assembly (TCA). A subscale model of the TCA was tested successfully on 13 November 2018 in Colleferro , Italy. In February 2020 a full scale engine prototype with a 3D printed TCA was successfully tested at NASA Marshall Space Flight Center , firing 19 times for a total of 450 seconds. On May 6 2022, the engine test and qualification campaign started in Avio's new Space Propulsion Test Facility (SPTF) at

240-417: A very powerful oxidizing agent: organic materials will burn rapidly and energetically in liquid oxygen. Further, if soaked in liquid oxygen , some materials such as coal briquettes, carbon black , etc., can detonate unpredictably from sources of ignition such as flames, sparks or impact from light blows. Petrochemicals , including asphalt , often exhibit this behavior. The tetraoxygen molecule (O 4 )

264-611: 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

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288-432: Is classified as an industrial gas and is widely used for industrial and medical purposes. Liquid oxygen is obtained from the oxygen found naturally in air by fractional distillation in a cryogenic air separation plant . Air forces have long recognized the strategic importance of liquid oxygen, both as an oxidizer and as a supply of gaseous oxygen for breathing in hospitals and high-altitude aircraft flights. In 1985,

312-563: The RD-0146D is in development for use on the KVTK upper stage. In 1988, RSC Energia directed KBKhA to begin work on a new preburner-less LO x /LH 2 rocket engine for use on upper stages, the RO-95. Though this 10 tf (98 kN) engine never left the design phase, its development confirmed the reliability and performance of the expander cycle to KBKhA. In 1999, a new expander-cycle engine project began. In that year, GKNPTs Khrunichev awarded

336-470: The USAF started a program of building its own oxygen-generation facilities at all major consumption bases. Liquid oxygen is the most common cryogenic liquid oxidizer propellant for spacecraft rocket applications, usually in combination with liquid hydrogen , kerosene or methane . Liquid oxygen was used in the first liquid fueled rocket . The World War II V-2 missile also used liquid oxygen under

360-495: The collaboration with KHBhA, Avio continued the development of the M10 engine for the Vega-E program with a target thrust of 10 tonnes-force. As of March 2021, the engine ground qualification is foreseen for 2024. Liquid oxygen Liquid oxygen , sometimes abbreviated as LOX or LOXygen , is a clear cyan liquid form of dioxygen O 2 . It was used as the oxidizer in

384-499: The engine power cycle. LM10-MIRA is a liquid oxygen - liquid methane demonstrator engine developed by Avio and KBKhA on the basis of the RD-0146. Development began under the terms of an agreement signed between the Italian and Russian governments in Moscow on November 28, 2000. The 7.5 tonnes-force engine was successfully tested in June 2014 in Voronezh , Russia . After the end of

408-412: The engine. The M10 minimum thrust requirements are a thrust of 98 kN (22,000 lbf) with a propellant mixture ratio of 3.4 and a minimum specific impulse of 362s. A feasibility study on improving Vega began in 2004, when the rocket was still in development, with the aim of increase performance, reduce costs and move away from toxic hydrazine fuels. The study proposed a new three-stage version of

432-466: The first liquid-fueled rocket invented in 1926 by Robert H. Goddard , an application which has continued to the present. Liquid oxygen has a clear cyan color and is strongly paramagnetic : it can be suspended between the poles of a powerful horseshoe magnet . Liquid oxygen has a density of 1.141 kg/L (1.141 g/ml), slightly denser than liquid water, and is cryogenic with a freezing point of 54.36 K (−218.79 °C; −361.82 °F) and

456-547: The first live firing of a production engine took place on 9 October, 2001. A second engine was built and fired in December 2002, and was subsequently delivered to Pratt & Whitney in March 2003. The RD-0146 used a different testing methodology than previous Soviet and Russian engine trial programs. Individual components and subsystems would be tested separately, while earlier testing would use an all-up method, in which an entire engine

480-690: The name A-Stoff and Sauerstoff . In the 1950s, during the Cold War both the United States' Redstone and Atlas rockets, and the Soviet R-7 Semyorka used liquid oxygen. Later, in the 1960s and 1970s, the ascent stages of the Apollo Saturn rockets , and the Space Shuttle main engines used liquid oxygen. As of 2024, many active rockets use liquid oxygen: M10 (rocket engine) M10

504-440: The nitrogen has evaporated from such a vessel, there is a risk that liquid oxygen remaining can react violently with organic material. Conversely, liquid nitrogen or liquid air can be oxygen-enriched by letting it stand in open air; atmospheric oxygen dissolves in it, while nitrogen evaporates preferentially. The surface tension of liquid oxygen at its normal pressure boiling point is 13.2 dyn/cm. In commerce, liquid oxygen

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528-471: The rocket named Lyra with a liquid oxygen-methane upper stage. In 2007 Avio and KBKhA started the collaboration for the development of such an engine under an agreement signed between Italian and Russian governments in Moscow on November 28, 2000. The first phase of the collaboration, ended in 2008, aimed at designing a concept for a 10t thrust LOx - LNG engine . The second phase of the collaboration focused instead on designing, manufacturing and testing

552-463: Was assembled and tested. This meant that a single component failure would make it necessary to disassemble the system to detect flaws. In order to facilitate test firings of the RD-0146, a new liquid hydrogen production plant was constructed, with a capacity of 100 kg (220 lb) per day. This became the second such facility in Russia. The RD-0146 is the first Russian rocket engine not to feature

576-528: Was first predicted in 1924 by Gilbert N. Lewis , who proposed it to explain why liquid oxygen defied Curie's law . Modern computer simulations indicate that, although there are no stable O 4 molecules in liquid oxygen, O 2 molecules do tend to associate in pairs with antiparallel spins , forming transient O 4 units. Liquid nitrogen has a lower boiling point at −196 °C (77 K) than oxygen's −183 °C (90 K), and vessels containing liquid nitrogen can condense oxygen from air: when most of

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