| RD-0210 (РД-0210) | |
| Country Of Origin: | USSR/Russia |
| First Date: | 1967-03-10 |
| Designer: | OKB-154, Yankel I. Guerchkovitch |
| Manufacturer: | Voronezh Mechanical Plant |
| Purpose: | Upper Stage |
| Associated: | Proton |
| Predecessor: | RD-0208 |
| Status: | In Production |
| Type: | liquid |
| Oxidiser: | N2O4 |
| Fuel: | UDMH |
| Mixture Ratio: | 2.6 |
| Cycle: | Oxidizer Rich Staged combustion |
| Combustion Chamber: | 1 |
| Thrust(Vac): | 582kN |
| Chamber Pressure: | 14.7MPa |
| Specific Impulse Vacuum: | 326.5s |
| Burn Time: | 220s |
| Length: | 2327mm |
| Diameter: | 1470mm |
| Dry Weight: | 566kg (1,248lb) |
| Used In: | UR-200 and UR-500 and Proton second stage |
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.
When Chelomey's OKB-52 started their UR-200 ICBM 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 engine, a then extremely aggressive feat. Only M. V. Melnikov of OKB-1 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 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, 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.
The RD-0203/4 was the second staged combustion 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 on a free return trajectory, that sent the first alive organisms around the moon and back to Earth.
On 19 April 1971 a Proton orbited Salyut 1 the first space station to orbit the Earth.
On 19 May 1971 a Proton launched the Mars 2 probe to Mars. The orbiter was identical to the Venera 9 bus, and the lander was the first man made object to reach the surface of Mars.
On 8 June 1975 a Proton launched the Venera 9 to Venus. It consisted of an orbiter based on the Mars 2 design, and a lander which was sent the first pictured from the surface of Venus.
On 20 November 1998 a Proton launched Zarya 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 Russian portion of the station - the Russian Orbital Segment.
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:
Some of these engines were bundled into modules of multiple engines. The relevant modules and auxiliary engines are:
| Engine | RD-0203 | RD-0204 | RD-0206 | RD-0208 | RD-0209 | RD-0210 | RD-0211 | RD-0213 |
|---|---|---|---|---|---|---|---|---|
| AKA | 8D44 | 8D44 | 8D47 | 8D411 | 8D412 | 8D411K | 8D412K | 8D48 |
| Propulsion Module | RD-0202 | RD-0205 (with RD-0207) | RD-0212 (with RD-0214) | |||||
| Development | 1961-1964 | 1961-1964 | 1961-1964 | 1962-1966 | 1962-1966 | 1962-1967 | 1962-1967 | 1962-1967 |
| Engine Type | Liquid oxidizer rich staged combustion using N2O4/UDMH propellant with an O/F ratio of 2.6 | |||||||
| Combustion Chamber Pressure | 14.7MPa | |||||||
| Nozzle | Single nozzle (Fixed) | Single nozzle | Single nozzle (Fixed) | Single nozzle (Fixed) | ||||
| Thrust (Vacuum) | 559kN | 559kN | 575.5kN | 570kN | 570kN | 582kN | 582kN | 582kN |
| Thrust (Sea Level) | 500kN | 500kN | ||||||
| Isp (Vacuum) | 311s | 311s | 326s | 326s | 326s | 326.5s | 326.5s | 326.5s |
| Isp(Sea Level) | 278s | 278s | ||||||
| Burn Time | 136s | 136s | 150s | 150s | 150s | 220s | 220s | 250s |
| Length | 1.8m (05.9feet) | 1.8m (05.9feet) | 2327mm | 2327mm | 2327mm | 2327mm | 3008mm | |
| Width | 890mm | 890mm | 1470mm | 1470mm | 1470mm | 1470mm | 1470mm | 1470mm |
| Dry Weight | 381kg (840lb) | 381kg (840lb) | 540kg (1,190lb) | 540kg (1,190lb) | 566kg (1,248lb) | 566kg (1,248lb) | 550kg (1,210lb) | |
| Use | UR-200 First Stage | UR-200 First Stage | UR-200 Second Stage | UR-500 Second Stage | UR-500 Second Stage | Proton Second Stage | Proton Second Stage | Proton Third Stage |
| First Launch | 1963-11-06 | 1963-11-06 | 1963-11-06 | 1965-07-16 | 1965-07-16 | 1967-03-10 | 1967-03-10 | 1967-03-10 |
| Last Launch | 1964-10-20 | 1964-10-20 | 1964-10-20 | 1966-07-06 | 1966-07-06 | |||
| Status | Retired | Retired | Retired | Retired | Retired | In Production | In Production | In Production |
| References | ||||||||