The RD-0210 (

GRAU The Main Missile and Artillery Directorate of the Ministry of Defense of the Russian Federation (), commonly referred to by its transliterated Russian acronym GRAU (), is a department of the Russian Ministry of Defense. It is subordinate to the ...

Index: 8D411K) is also known as the RD-465. It and its twin, the RD-0211, are

rocket engine A rocket engine uses stored rocket propellants as the reaction mass for forming a high-speed propulsive jet of fluid, usually high-temperature gas. Rocket engines are reaction engines, producing thrust by ejecting mass rearward, in accorda ...

s burning N₂O₄ and

UDMH Unsymmetrical dimethylhydrazine (UDMH; 1,1-dimethylhydrazine, НДМГ or codenamed Geptil) is a chemical compound with the formula H2NN(CH3)2 that is used as a rocket propellant. It is a colorless liquid, with a sharp, fishy, ammonia-like smell ...

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 A proton is a stable subatomic particle, symbol , H+, or 1H+ with a positive electric charge of +1 ''e'' elementary charge. Its mass is slightly less than that of a neutron and 1,836 times the mass of an electron (the proton–electron mass ...

second stage. The RD-0213 is a fixed nozzle variation that is used on the RD-0212 module of the

third stage.

Development

When Chelomey's

OKB-52 NPO Mashinostroyeniya (russian: НПО машиностроения, lit=RDA of machine manufacturing) is a rocket design bureau based in Reutov, Russia. During the Cold War it was responsible for several major weapons systems, including the UR-1 ...

started their

UR-200 The UR-200 was an intercontinental ballistic missile (ICBM) developed by Vladimir Chelomey's OKB-52 in the Soviet Union. It was known during the Cold War by the NATO reporting name SS-10 '' Scrag'' and internally by the GRAU index 8K81. The d ...

ICBM An intercontinental ballistic missile (ICBM) is a ballistic missile with a range greater than , primarily designed for nuclear weapons delivery (delivering one or more thermonuclear warheads). Conventional, chemical, and biological weapons ...

project, they requested S. A. Kosberg's OKB-154 to develop the propulsion. They decided to use the same basic block for both the first and second stage. But to achieve the required performance, Kosberg had to develop a

staged combustion Staged combustion is a method used to reduce the emission of nitrogen oxides ( NOx) during combustion. There are two methods for staged combustion: air staged supply and fuel staged supply. Applications of staged combustion include boilers and ro ...

engine, a then extremely aggressive feat. Only M. V. Melnikov of

OKB-1 PAO S. P. Korolev Rocket and Space Corporation Energia (russian: Ракетно-космическая корпорация «Энергия» им. С. П. Королёва, Raketno-kosmicheskaya korporatsiya "Energiya" im. S. P. Korolyov ...

had designed a staged combustion engine before, the S1.5400, and it used a different propellant mix with significantly less thrust. To simplify design and manufacture, the engine would be used both on the first and the second stages. The first stage would use a module - the RD-0202 - that comprised three RD-0203 and one RD-0204, while the upper stage would use a RD-0205 module comprising a RD-0206 main engine plus an auxiliary vernier engine, the RD-0207. The RD-0204 only difference to the RD-0203 was that it included a heat exchanger to heat the pressurant gases for the first stage tank. The RD-0206 was very similar to the RD-0204, but its nozzle was vacuum optimized and had a fixed nozzle. The

thrust vector control Thrust vectoring, also known as thrust vector control (TVC), is the ability of an aircraft, rocket, or other vehicle to manipulate the direction of the thrust from its engine(s) or motor(s) to control the attitude or angular velocity of the ve ...

task was delegated to the four nozzle RD-0207 vernier engine. While the UR-200 project was in direct competition to the R-36 and was cancelled in favor of the latter, it did have a few test launches and thus was a proven design. When Chelomey started his super heavy ICBM UR-500 (8K82) project, he originally intended to use multiple UR-200 modules as a first stage. When this concept proved not viable, and the multi-body that was finally used was settled on, they had to search for new propulsion on the first stage. For the second stage, they adapted the UR-200 first stage's. It needed new tanks to match the first stage, but most of the rest could be adapted. The engines had to be started in the air and had to get longer nozzles, optimized for vacuum operation. Both of this features were demonstrated on the RD-0206, and were readily adapted. They also received a thrust vector gimbaling system, to have better control during launch. Thus, the RD-0208/RD-0209 were born. In a parallel case with the RD-0203/4, the RD-0209 was a version of the RD-0208 that included a heat exchanger. When the UR-500 proved to be too big as an ICBM, the application of the vehicle as a weapon was cancelled. But it could be adapted as a heavy launch vehicle that could perform important missions for the

Soviet moonshot The Soviet crewed lunar programs were a series of programs pursued by the Soviet Union to land humans on the Moon, in competition with the United States Apollo program. The Soviet government publicly denied participating in such a competitio ...

, and so the Proton-K (8K82) was born. This allowed Chelomey to pitch it as a competitor, along the UR-700 project, of Korolev's N-1. For this new missions, it would not need to comply with ICBM specification standards, but would need at least a third stage. The second stage was enlarged, and the RD-0208/9 were revised as the RD-0210 and RD-0211 by uprating them slightly and significantly increasing the burning time. For the third stage, the UR-200 second stage was adapted -again, with the same 4.1m tanking as the first and second stages- and the RD-0205 module with an RD-0206 and an RD-0207 vernier engine was given an overhaul. The new module, - known as RD-0212 - consisted of an RD-0213 and an RD-0214 vernier engine. The RD-0213 was a RD-0206 brought to RD-0211/12 standards, and the RD-0214 was a revised RD-0207.

History

The RD-0203/4 was the second

engine in the world, only after the S1.5400, and was also the first staged combustion engine with storable propellants. On 15 September 1968 the RD-0210, RD-0211 and the RD-0212 module launched the Zond 5 around the

Moon The Moon is Earth's only natural satellite. It is the fifth largest satellite in the Solar System and the largest and most massive relative to its parent planet, with a diameter about one-quarter that of Earth (comparable to the width of ...

on a

free return trajectory In orbital mechanics, a free-return trajectory is a trajectory of a spacecraft traveling away from a primary body (for example, the Earth) where gravity due to a secondary body (for example, the Moon) causes the spacecraft to return to the primar ...

, that sent the first alive organisms around the moon and back to Earth. On 19 April 1971 a Proton orbited

Salyut 1 Salyut 1 (DOS-1) (russian: Салют-1) was the world's first space station launched into low Earth orbit by the Soviet Union on April 19, 1971. The Salyut program followed this with five more successful launches of seven more stations. The f ...

the first space station to orbit the Earth. On 19 May 1971 a Proton launched the

Mars 2 The Mars 2 was an uncrewed space probe of the Mars program, a series of uncrewed Mars landers and orbiters launched by the Soviet Union beginning 19 May 1971. The Mars 2 and Mars 3 missions consisted of identical spacecraft, each with an orbi ...

probe to

Mars Mars is the fourth planet from the Sun and the second-smallest planet in the Solar System, only being larger than Mercury. In the English language, Mars is named for the Roman god of war. Mars is a terrestrial planet with a thin at ...

. The orbiter was identical to the

Venera 9 Venera 9 (russian: Венера-9, lit=Venus-9), manufacturer's designation: 4V-1 No. 660, was a Soviet uncrewed space mission to Venus. It consisted of an orbiter and a lander. It was launched on June 8, 1975, at 02:38:00 UTC and had a m ...

bus, and the lander was the first man made object to reach the surface of Mars. On 8 June 1975 a Proton launched the

Venus Venus is the second planet from the Sun. It is sometimes called Earth's "sister" or "twin" planet as it is almost as large and has a similar composition. As an interior planet to Earth, Venus (like Mercury) appears in Earth's sky never f ...

. It consisted of an orbiter based on the

design, and a lander which was sent the first pictured from the surface of Venus. On 20 November 1998 a Proton launched

Zarya Zarya may refer to: *Zorya, personification of dawn in Slavic mythology * Zarya (antenna), a type of medium-wave broadcasting antenna used in former Soviet Union *Zarya (ISS module) is a module of the International Space Station. * ''Zarya'' (magazi ...

the first module of the ISS. On 12 July 2000 a Proton launched Zvezda, the third module launched of the ISS and the center of the

Russia Russia (, , ), or the Russian Federation, is a transcontinental country spanning Eastern Europe and Northern Asia. It is the largest country in the world, with its internationally recognised territory covering , and encompassing one-ei ...

n portion of the station - the

Russian Orbital Segment The Russian Orbital Segment (ROS) is the name given to the components of the International Space Station (ISS) constructed in Russia and operated by the Russian Roscosmos. The ROS handles Guidance, Navigation, and Control for the entire Station ...

Versions

The basic engine has been used for the UR-200 first and second stages, the UR-500 second stage and the Proton second and third stages. Each variation is as follows: * RD-0203 (

Index: 8D44): The second staged combustion rocket in the world, and the first hypergolic. It used an oxidizer rich preburner and had a thrust of . Propulsion of the UR-200 first stage. * RD-0204: Slight variation of the RD-0203 that included a heat exchanger for heating the tank pressurizant gases. Propulsion of the UR-200 first stage. * RD-0206 (

Index: 8D47): Variation of the RD-0203/4, optimized for vacuum expansion and no TVC. Used on the UR-200 second stage. * RD-0208 (

Index: 8D411): Evolution of the RD-0203, with vacuum optimized nozzle and air start capability. Used on the second stage of the UR-500. * RD-0209 (

Index: 8D412): Same as RD-0208, but with a heat exchanger. Used on the second stage of the UR-500. * RD-0210 (

Index: 8D411K): Also known as the RD-465, it is an evolution of the RD-0208. Used on the second stage of the Proton-K and Proton-M rockets. * RD-0211 (

Index: 8D412K): Also known as the RD-468, it is the same as RD-0210, but with a heat exchanger like the RD-0209. Used on the second stage of the Proton-K and Proton-M rockets. * RD-0213 (

Index: 8D48): Variation of the RD-0210/11, optimized for vacuum expansion and no TVC. Used on the RD-0212 propulsion module of the Proton third stage.

Modules

Some of these engines were bundled into modules of multiple engines. The relevant modules and auxiliary engines are: * RD-0202 (

Index: 8D45): A module comprising three RD-0203 and a single RD-0204. Propulsion module of the UR-200 first stage. * RD-0205 (

Index: 8D46): A module comprising an RD-0206 and an RD-0207 vernier engine. Propulsion of the UR-200 second stage. * RD-0212 (

Index: 8D49): Also known as the RD-473, it is a propulsion module comprising one RD-0213 and an RD-0214 vernier engine. Propulsion module of the third stage of the Proton-K and Proton-M rockets.

References

External links