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28-608: It should not be confused with the RD-0120 , which is a discontinued LOX/hydrogen rocket engine that was used in the Soviet Energia launch system. During the Buran programme initial development of the 11D77 —the launch vehicle later known as Zenit —, KBKhA had been assigned the development of the second stage engine, as they had done for the Proton and Soyuz vehicles. But given

56-653: A 5% extra margin, extended the design life to 4260 seconds, the number of ignitions to 19 and allows to consider it as a base for a reusable rocket, the engine is still not capable of restarting inflight. After a program that used 4 test engines and performed 28 hot fire tests with an accumulated running time of 8,135 seconds, the engine was qualified for flight. Testing started in March 2004 and it had its debut flight on February 15, 2006 where it successfully orbited EchoStar X . This engine has had two operative versions and some proposed variations: Not considering straight variations of

84-475: A complicated debut, with the second stage failing on its first (April 13, 1985), second (June 21, 1985) and fourth (December 28, 1985) flights. While only the first failure could be attributed to the RD-120 —the propellant flow regulator had a leak and the stage ran out of propellant before being orbital—, the program initial performance was quite troubling. Eventually it proved its worth, and by December 1987

112-486: A resolution for the development of Zenit, the RD-171 and RD-120. By April 1976, Yuzhnoye supplied NPO Energomash with the final requirements for the 11D77 first and second stage propulsion. One of the desirable effects of consolidating the first and second stage propulsion on the same designer, was that they could learn their lessons on staged combustion engines on the smaller and simpler upper stage engine, and then apply them to

140-563: Is a Chinese liquid rocket engine burning LOX and kerosene in an oxidizer-rich staged combustion cycle . Development of the engine began in the 2000s, along with its sibling, the smaller YF-115 , which would power the upper stages of the Long March 6 and Long March 7 rockets. Testing was directed by the China National Space Administration (CNSA) commencing in 2005. Development works are mainly carried out by

168-527: Is a single-shaft design, with a single-stage oxygen pump and a dual-stage kerosene pump driven by the same turbine. It also has two low-pressure pumps that prevent cavitation . This arrangement is very similar to the RD-170 design. The engine has a heat exchanger to heat oxygen gas for LOX tank pressurization, and also supplies high-pressure kerosene as hydraulic fluid for the thrust vector control actuators. The development required ten years of research, requiring

196-568: The 747 air-launched first stage. The RD-120 offered the best price and performance, and was the preferred choice of Orbital Sciences . In fact, on October 11, 1995, the RD-120 was fired on the U.S. and thus became the first Russian rocket engine actively in production to be fired in American soil. This version of the engine, would mainly differ from the Zenit in the addition of a gimbal mount that would enable it to offer TVC . This version would be known as

224-514: The Long March 5 , the Long March 6 and the Long March 7 . The engine's maiden flight, on the Long March 6, took place on September 20, 2015. The YF-100 is a pump-fed oxidizer rich staged combustion rocket engine. It has adjustable thrust and variable mixture ratio . Its preburner burns all the LOX mass flow with a bit of kerosene to generate hot gas that powers the single turbine. The turbopump

252-619: The RD-120M . The second private partner in the X-34 program, Rockwell International , wanted to use their own engine, the RS-27 . And given the constrained schedule and budget of the program, the engine selection was not able to be resolved and the program cancelled and reimplemented as the pure NASA research program that the X-34 was later known for. Also during the 1990s, the Chinese acquired two or three models of

280-652: The RD-855 or RD-861 , they were considered too toxic for modern ecological standards. While they still offer to develop hypergolic propulsion, like in the case of the RD-843 for the Vega 's AVUM stage or the Tsyklon-4 project, for the Mayak launch vehicle family a more environmentally friendly LOX and kerosene propellant was decided. Not only had Yuzhnoye mastered the most complex cycle for

308-498: The Energia core rather than the orbiter, so were not recoverable after a flight, but created a more modular design (the Energia core could be used for a variety of missions besides launching the shuttle). The RD-0120 and the SSME have both similarities and differences. The RD-0120 achieved a slightly higher specific impulse and combustion chamber pressure with reduced complexity and cost (but it

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336-475: The Peaceful Uses of Outer Space , which would enter in force on February 15, 2006. According to official press release on March 26, 2013 by Ukrainian Ministry of Economic Development and Trade, development of a rocket engine for Indian launch vehicles initiated in 2006 under a joint Indian-Ukrainian project named "Jasmine". The engine blue prints supposedly transferred by Ukraine to India, have been identified as

364-625: The RD-120 (and the Zenit) were considered commissioned. But in the years of the Soviet dissolution, the second stage failed twice in a row on August 30, 1991 and February 5, 1992. Zenit had other second stage failures, but only the first one has ever been attributed directly to the RD-120 itself. During 1990, the NPO Energomash Head of the Propulsion Department, and leading designer, V.K.Chvanov,

392-528: The RD-120 was used as the first practical application of the oxidizer rich staged combustion with kerosene propellant at NPO Energomash , before tackling the RD-170 . So, while this later family of engines have more aggressive performance parameters and the original project (the RD-123) predates the RD-120, it was indeed the first actual design of the series development. While Yuzhnoye propulsion experience had been mostly on hypergolic propellants engines, like

420-582: The RD-120, and possibly some documentation. This enabled them to bootstrap their indigenous kerosene staged combustion engine program, the YF-100 and YF-115 . The RD-120 had significant margins built in, which allowed between 2001 and 2003 to develop a modernized 'Uprated' or 'Forced' version of the engine for Sea Launch which increased thrust 10% to 912 kN (205,000 lbf). It also incorporated many improvements, which allowed it to increase chamber pressure and thrust without additional weight gain. It still has

448-580: The RD-120, this very influential engine has been the foundations of many engines spanning derivatives in four countries. The Ukrainian RD-801 and RD-810 , the Chinese YF-100 and YF-115 , as well as the Indian SCE-200 can be traced directly back to the RD-120. The Soviet/Russian RD-170 family of engines base developed on the lessons learned from the RD-120 project. As stated in the History section,

476-539: The RD-120. During the 1990s, the Chinese acquired two or three models of the RD-120, and possibly some documentation. This enabled them to bootstrap their indigenous kerosene staged combustion engine program, the YF-100 and YF-115 . As was the same case with the Indians and the RD-810, the transfer of the physical engines and blue prints only help in the development. But the development required ten years of research, requiring

504-719: The RD-8, but the RD-801 and the RD-810 members of the family can be considered true descendants of the RD-120. One characteristic of this family is the limitation of keeping the preburner output temperature below 500 °C (932 °F). On June 2, 2005, India and Ukraine signed the Framework Agreement between the Government of Ukraine and the Government of the Republic of India on Cooperation in

532-480: The RD-810. Since the transfer specifically excluded engineering analysis methods and software, the Indians did, in fact, had to develop most technologies and engineering models to manufacture and certify the engine. Given the practically identical specifications to the RD-810, and the fact that even the Indians used the Yuzhnoye renders of the engine in their presentations, it can be considered at least heavily influenced by

560-538: The USSR. It is the first Chinese rocket engine to adopt the staged-combustion cycle and the most powerful to date. During July 2012 the engine fired for 200 seconds generating 120 t (260,000 lb) of thrust. On May 28, 2012, the National Defense Science and Industry Bureau certified the engine. The engine is designed for use on the first stage of the Chinese government's new generation of launch vehicles,

588-554: The Xi'an Aerospace Propulsion Institute. The engine had its first 300 seconds test fire in November 2007. A high efficiency/high thrust environmentally-friendly rocket engine was always an objective within Programme 863 in the 1980s; however, Chinese industry was not mature enough at that time to produce such a rocket until they obtained RD-120s in early 1990 from Russia following the collapse of

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616-466: The bigger and more innovative first stage RD-170. NPO Energomash, had already worked on a prototype kerosene / oxygen staged combustion engine in that range, based on the RD-268 hypergolic engine, which was already under serial production with Yuzhmash . In February, 1977, the preliminary design of the RD-120 was finished. And on January 31, 1979 the first fire test of the RD-120 was performed. The RD-120 had

644-514: The difficult development of the cryogenic propellant engine, Energomash assumed the responsibility of developing the second stage engine of the 11D77, which would eventually be known as the RD-120 . The fact that the RD-120 and the RD-0120 had this intertwined conception, within the same program, and with a swap of designer bureaus, does not help to avoid the confusion. On March 16, 1976 the Government passed

672-590: The difficulties for NPO Energomash in developing the RD-123 (which would later be known as the RD-170 ), they ceded the hydrogen / oxygen sustainer engine development to KBKhA. This project, the analog of the SSME , was project RD-130 within NPO Energomash. But when KBKhA tackled the development, named it RD- 0 120 , a name that is always a source of confusion with the engine of the current article. In exchange for them tackling

700-529: The mastering of 70 key technologies, the development of 50 new materials and the construction of 61 sets of engines with a combined total of more than 40,000 seconds of ignition time by 2013. RD-0120 The Soviet RD-0120 (also designated 11D122 ) was the Energia core rocket engine, fueled by LH 2 / LOX , roughly equivalent to the Space Shuttle Main Engine (SSME). These were attached to

728-569: The propellant ( oxidizer rich staged combustion cycle ) with the RD-8 , but they had worked closely with NPO Energomash during the RD-120 program. The manufacturing is done at its sister company of Yuzhmash in Ukraine , and the RD-120 thrust augmentation project of 2001 to 2003 had been a mixed project between the three companies. On the base of this experience, a family of derivatives engines were proposed. The RD-805 and RD-809 are mostly modifications of

756-556: Was awarded the State Prize for the creation of RD-120. In October 1992, Pratt & Whitney signed an agreement with NPO Energomash to sale and represent their line of engine in the United States. During the initial version of the X-34 program, the one trying to develop a reusable launch vehicle for small payloads through a public/private association, the RD-120 was seriously considered for

784-490: Was single-use), as compared to the SSME. It uses a fuel-rich staged combustion cycle and a single shaft to drive both the fuel and oxidizer turbopumps. Some of the Russian design features, such as the simpler and cheaper channel wall nozzles, were evaluated by Rocketdyne for possible upgrades to the SSME. It achieved combustion stability without the acoustic resonance chambers that the SSME required. YF-100 The YF-100

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