RD-0110

Last updated
RD-0110
RD-0110 rocket engine.jpg
Country of origin USSR
First flight1965-10-05
Designer KBKhA
Manufacturer Voronezh Mechanical Plant [1]
ApplicationUpper Stage
Associated LV Molniya-M and Soyuz
Predecessor RD-0108
StatusIn Production
Liquid-fuel engine
Propellant LOX / RG-1
Mixture ratio2.2 [2]
Cycle Gas Generator
Configuration
Chamber4
Performance
Thrust, vacuum298 kilonewtons (67,000 lbf)
Thrust-to-weight ratio 74.36 [3]
Chamber pressure 6.8 megapascals (990 psi)
Specific impulse, vacuum326 seconds
Burn time250 s
Dimensions
Length1,575 millimetres (62.0 in)
Diameter2,240 millimetres (88 in)
Dry weight408.5 kilograms (901 lb)
Used in
Molniya-M Block-I and on most Soyuz Block-I
References
References [4]

The RD-0110 (or RO-8 , RD-0108 , RD-461 ) 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 (as of February 2018). [5] [6] [7]

Contents

History

OKB-154 of S.A. Kosberg was tasked with developing an engine for the unmanned Molniya Block-I stage. Thus, the RD-0107 was developed in the 1960 to 1961 period, based on the RD-0106 (GRAU Index: 8D715) engine that powered the SS-8 Sasin ICBM, also designed by OKB-154. It also leveraged the experience in the field from the Vostok Block-E RD-0105/RD-0109 development. [4] [7] [8] [9] The engine had its debut flight on October 10, 1960, and the last Molniya flight was on October 22, 1967. [4] [10]

For the crewed carrying Voskhod Block-I, a version of the engine that complied with the human rating 3K Regulations was needed. During 1963 OKB-154 developed this new version of the engine. Known with by the GRAU index 8D715P, the RD-0108 kept the same characteristics and performance of the RD-0107 while fully complying with the crew rating regulations. [11] This engine had its first flight on November 16, 1963, and last flew on June 29, 1976. [4] [12]

For the Molniya-M Block-I, OKB-154 did an improvement program that put special emphasis on the reliability of the engine. This project gave birth to the RD-0110. A particular problem observed during acceptance testing were high frequency instabilities, particularly during the start sequence. But it was solved by installing of longitudinal felt ribs on the combustion chamber. [3] The development of the RD-0110 was performed in 9 months during 1963, with its inaugural flight happening in 1964. [5] It is also used on the Soyuz third stage in all models until the RD-0124 debut on the 2.1b. It has flown over 1350 times, and accumulated more than 336,500 s of burn time and is still flown many times per year. [5]

Design

The RD-0110 was created in a period when KBKhA had just started to design rocket engines. After many studies, simplicity and reliability were the main drivers of the design. For this reason a single shaft integrating the LOX pump, the RG-1 pump and the turbine was chosen. To provide acceptable suction performance, the RD-0110 turbopump has a dual inlet design with back to back centrifugal impellers. This allows it to work at relatively low inlet pressures without requiring additional booster pumps. The turbine is driven by a fuel rich gas generator. [5] The ignition system for both the gas generator and the combustion chamber is done by pyrotechnic devices. The engine control is handled by a regulator, a throttle and a set of valves. It can throttle between 100% and 90.5%, with the option of 107% for a short time in emergencies. [3]

During development, combustion instability issues were observed. The problem was found to be intimately related to the injection system design. It was finally solved by developing an optimized bi-propellant centrifugal atomizer design. During certification testing, high frequency combustion instabilities at start up were still observed. Even though the start instabilities were relatively rare at 1 in 60 to 80, and only on acceptance bench, great effort was made to eliminate the issue. Thanks to acoustic studies and modelling, a solution was found. Six combustible longitudinal felt ribs were placed at the inner surface of the combustion chamber and this solved the issue permanently. [3]

The RD-0110 uses fuel as coolant for the regenerative cooling system. As most other Soviet designs, it uses a corrugated metal construction for the cooling jackets. The thrust chamber and upper nozzle sections has the corrugated metal sandwiched between an inner and outer metal layers. The lower section of the nozzle has no external lining, exposing the corrugated jacket to save weight. All these sections use steel for construction. Given the extreme temperatures at the throat section, this part is made of copper alloy with milled channels and an external lining. A separate film cooling system is implemented though a different manifold and is injected though a circular slot upstream of the throat. [13]

Production

The RD-0107/0108/0110 engines are produced in the Voronezh Mechanical Plant. [1] [7]

Versions

Modifications to the RD-0107 design have led to production of three distinct versions of the engine:

See also

Related Research Articles

The Voskhod rocket was a derivative of the Soviet R-7 ICBM designed for the human spaceflight programme but later used for launching Zenit reconnaissance satellites. It consisted of the Molniya 8K78M third stage minus the Blok L. In 1966, all R-7 variants were equipped with the uprated core stage and strap-ons of the Soyuz 11A511. The Blok I stage in the Voskhod booster used the RD-0107 engine rather than the crew-rated and more powerful RD-0110 used on the Soyuz. The sole exceptions to this were the two crewed Voskhod launches, which had RD-0108 engines, a crew-rated RD-0107 but with the same performance.

<span class="mw-page-title-main">Gas-generator cycle</span> Rocket engine operation method

The Gas Generator Cycle, also called open cycle, is one of the most commonly used power cycles in bipropellant liquid rocket engines. Part of the unburned propellant is burned in a gas generator and the resulting hot gas is used to power the propellant pumps before being exhausted overboard, and lost. Because of this loss, this type of engine is termed open cycle.

<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-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.

<span class="mw-page-title-main">Soyuz (rocket)</span> First version of the Soyuz launch vehicle

The Soyuz was a Soviet expendable carrier rocket designed in the 1960s by OKB-1 and manufactured by State Aviation Plant No. 1 in Kuybyshev, Soviet Union. It was commissioned to launch Soyuz spacecraft as part of the Soviet human spaceflight program, first with 8 uncrewed test flights, followed by the first 19 crewed launches. The original Soyuz also propelled four test flights of the improved Soyuz 7K-T capsule between 1972 and 1974. In total it flew 30 successful missions over 10 years and suffered two failures.

<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.

<span class="mw-page-title-main">S1.5400</span> First staged combustion rocket engine ever developed, for the Soviet space program

The S1.5400 was a Soviet single-nozzle liquid-propellant rocket engine burning liquid oxygen and kerosene in an oxidizer-rich staged combustion cycle, being the first rocket engine to use this cycle in the world. It was designed by V. M. Melnikov, an alumnus of Isaev, within Korolev's Bureau, for the Molniya fourth stage, the Block-L. It was also the first Soviet engine designed for start and restart in vacuum and had the highest Isp at the time of its deployment.

<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.

<span class="mw-page-title-main">RD-0109</span> Rocket engine

The RD-0109 is a rocket engine burning liquid oxygen and kerosene in a gas generator combustion cycle. It has single nozzle and is an evolution of the RD-0105. It was the engine used on the Vostok Block-E that launched Yuri Gagarin to orbit.

The RD-0214 (GRAU Index: 8D811) is a rocket vernier engine burning N2O4 and UDMH in a gas generator cycle. It has four nozzles that can each gimbal 45 in plane to provide TVC to the RD-0212 propulsion module of Proton third stage. It is a revised version of the RD-0207.

<span class="mw-page-title-main">RD-0210</span>

The RD-0210 (GRAU Index: 8D411K) is also known as the RD-465. It and its twin, the RD-0211, are rocket engines burning N2O4 and UDMH in an oxidizer rich staged combustion cycle. They have single nozzle, possess TVC and are the latest evolution in the RD-0203/4 lineage. They are the engines used on the Proton second stage. The RD-0213 is a fixed nozzle variation that is used on the RD-0212 module of the Proton third stage.

<span class="mw-page-title-main">RD-119</span>

The RD-119 was a liquid rocket engine, burning liquid oxygen and UDMH in the gas-generator cycle. It has a huge expansion ratio on the nozzle and uses a unique propellant combination to achieve an extremely high isp of 352 s for a semi-cryogenic gas-generator engine. It also has a unique steering mechanism. The engine main nozzle is fixed, and the output of the gas generator is fed into four nozzles on the side of the engine. Instead of using gimbaled verniers to supply vector control, the combustion gases are distributed by an electrically driven system that can control the thrust among the nozzles.

<span class="mw-page-title-main">RD-214</span> Rocket engine

The RD-214 (GRAU Index 8D59) was a liquid rocket engine, burning AK-27I (a mixture of 73% nitric acid and 27% N2O4 + iodine passivant and TM-185 (a kerosene and gasoline mix) in the gas generator cycle. As was the case with many V-2 influenced engines, the single turbine was driven by steam generated by catalytic decomposition of H2O2. It also had four combustion chambers and vector control was achieved by refractory vanes protruding into the nozzle's exhaust.

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">A.M. Isayev Chemical Engineering Design Bureau</span>

The A.M. Isayev Chemical Engineering Design Bureau, also known as KB KhimMash or just KBKhM, is a Russian rocket engine design and manufacturing company. It is located in the city of Korolyov. It started as the OKB-2 division of the NII-88 research institute, where A.Isaev directed the development of liquid rocket engines for ballistic missile submarines.

The RD-861 is a Soviet liquid propellant rocket engine burning UDMH and nitrogen tetroxide in a gas generator combustion cycle. It has a main combustion chamber, with four vernier nozzles fed by the gas generator output. It can be reignited a single time.

The RD-855 (GRAU Index 8D68M]), also known as the RD-68M, is a liquid-fueled rocket engine with four nozzles. As a vernier engine, it provides fine steering adjustments for rockets. It is powered by a combination of N2O4, an oxidizer, and UDMH, a propellant. This combination is hypergolic, meaning the two substances ignite on contact, eliminating the need for an external ignition source.

The RD-0255 is a propulsion module composed of an RD-0256 main engine and a RD-0257 vernier engine. Both are liquid rocket engine, burning UDMH in N2O4. The RD-0256 main engine operates in the oxidizer rich staged combustion cycle, while the vernier RD-0257 uses the simpler gas generator cycle. It was used on the R-36MUTTKh (GRAU:15A18) and R-36M2 (GRAU:15A18M). Subsequently, it has been in the Dnepr second stage and as of 2016 it is still in active service.

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. 1 2 "Liquid Rocket Engine". Voronezh Mechanical Plant. Archived from the original on 30 May 2015.
  2. 1 2 3 4 "RD-0107". Encyclopedia Astronautica. Archived from the original on March 21, 2002. Retrieved 2015-05-29.
  3. 1 2 3 4 Rubinsky, Vitaly R. (1995). "Chapter 4: Combustion Instability in the RD-0110 Engine". In Anderson, William E.; Yang, Vigor (eds.). Progress in Astronautics and Aeronautics Volume 169: Liquid Rocket Engine Combustion Instability. AIAA. pp. 89–112. doi:10.2514/4.866371. ISBN   978-1-56347-183-4 . Retrieved 2015-05-30.
  4. 1 2 3 4 "RD0107, RD0108, RD0110. Molniya (8K78), Voskhod (8K78M), Soyuz (11A511У) launch vehicles". KBKhA. Archived from the original on 14 October 2011.
  5. 1 2 3 4 "Turbopumps for Gas Generator and Staged Combustion Cycle Rocket Engines" (PDF). AIAA. July 2005. Retrieved 2015-05-29.
  6. ↑ "R-7/Soyuz Data Sheet". Space Launch Report. Archived from the original on 6 August 2010.
  7. 1 2 3 Zak, Anatoly. "RD-0110". russianspaceweb.com. Retrieved 2015-05-29.
  8. ↑ "RD-0106". Encyclopedia Astronautica. Archived from the original on March 20, 2002. Retrieved 2015-05-30.
  9. ↑ "RD0105. Luna (8K72) launch vehicle. RD0109. Vostok (8K72K) launch vehicle". KBKhA. Archived from the original on 23 November 2011. Retrieved 2015-05-29.
  10. ↑ Pillet, Nicolas. "Liste des lancements Molnia" (in French). Kosmonavtika.com. Retrieved 2015-05-30.
  11. ↑ "Part 9: Launchers for an Early Circumlunar Programme". Cosmopark.ru. Archived from the original on 25 September 2011.
  12. ↑ Pillet, Nicolas. "Liste des lancements Voskhod" (in French). Kosmonavtika.com. Retrieved 2015-05-30.
  13. ↑ Sutton, George Paul (November 2005). History of Liquid Propellant Rocket Engines. AIAA. pp. 637–638. ISBN   978-1563476495.
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.