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RD-0212 engine

Developed at the KB Khimavtomatiki, KBKhA, design bureau in the city of Voronezh, the RD-0212 engine propels the third stage of the Proton rocket.

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silo

General design of the RD-0212 engine.

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RD-0212 design

RD-0212 (also known as 8D49) is a multi-engine propulsion system, which includes the main engine, designated RD-0213, and a four-chamber steering thruster known as RD-0214. Both burn a highly toxic mix of unsymmetrical hydrazine fuel and nitrogen tetroxide oxidizer. The main advantage of this propellant is the possibility to store it in liquid form at normal temperatures, without any need for cryogenic equipment.

The main RD-0213 engine closely resembles the RD-0210 and RD-0211 engines on Proton's second stage. All three propulsion systems are powered by a turbopump and belong to the so-called closed-cycle engines. It means that after driving the turbopump, which forces fuel into the combustion chamber, the hot oxidizer gas is also directed back into the combustion chamber to increase the engine's thrust.

Designed for a single 250-second burn during the mission, the RD-0213 has the capability to vary its thrust with the help of a special controller installed in the fuel gas generator. A special throttle on the fuel line ensures equal expenditure of fuel and oxidizer from the rocket's tanks. Pyrotechnic devices are used to start the engine in flight.

production

production

RD-0212 engines (background) and RD-0214 steering engines during production at Voronezh Mechanical Plant in 2016.

RD-0214 steering engine

Unlike, the RD-0213, the RD-0214 engine features an open-cycle design. It has a single turbopump, a pair of gas generators, a control system and a pyrotechnic activation system.

Each chamber on RD-0214 can rotate up to 45 degrees with the help of an electric motor under commands of the flight control system to steer the rocket in flight. The steering engine also carries pressurization hardware for the propellant tanks of the third stage.

The RD-0214 steering engine is based on the similar RD-0207 engine, which steered the second stage of the UR-200 missile in flight. To move the RD-0207 from the second stage of UR-200 to the larger third stage of Proton, engineers had to extend the feed lines for all four thrusters. They also adjusted the pressurization system and installed improved ignition valves, which became available by that time. Otherwise, the design of the engine remained mostly unchanged.

At the ignition time, the dual turbopump of the engine gets its initial spin from a solid-propellant ignition system. As soon as propellant starts flowing, the turbopump switches to a pressurized gas coming from the gas generator. (264)

Where they came from?

Developed at KBKhA design bureau under leadership of Yankel Gershkovich, the propulsion system for the third stage of the Proton rocket was based on the heritage of the ill-fated UR-200 rocket. It was based on the RD-0205 engine, which propelled the second stage of the UR-200. Thus, the most serious technical challenges of the design were resolved in the course of the RD-0205 development, which started in March 1961. It would be only the second operational Soviet closed-cycle engine, coming in the footsteps of a kerosene-burning propulsion system developed at Sergei Korolev's OKB-1 bureau.

When the development of engines for the Proton rocket started in 1962, the RD-0205 from UR-200 became the basis for three engines on Proton: RD-0210 and RD-0211 on the second stage and RD-0212 on the third stage.

Engines received a number of upgrades comparing to their predecessor -- the RD-0205:

  • The fuel line received a membrane valve with a bypass line and a cutoff valve. It was designed to optimize the ignition of the engines in most conditions, while avoiding a dangerous increase in the turbopump rotor speed and guarantee that the gas generator would always start firing slightly ahead of the burning process in the combustion chamber;
  • More effective injectors were installed at entrances into the propellant lines to improve the performance of the turbopumps;
  • Ignition valves moved toward the entrances into the pumps in order to reduce hydraulic shock in propellant lines and in low-pressure areas of the engine.

Ground testing of the RD-0212 engine was conducted at KBKhA's vertical bench stand, which was built in 1963.

The so-called experimental and final tune-up tests, or ZDI, of the engines were completed by the end of 1966 and in October and November of the same year, the engines fired as part of the bench tests of a fully assembled third stage. In March 1967, they first flew on the Proton rocket.

Practically immediately, from December 1966 to August 1967, as Proton was undergoing flight testing, the bureau conducted the first effort to improve the reliability of the engine, which became known as Variant P. Changes included:

  • The introduction of thermal protection made of zirconium dioxide, ZrO2, on the internal surface of the combustion chamber;
  • The strengthening of several components, including the turbine housing;
  • The introduction of a gas generator with lower pressure fluctuation on oxidizer injectors in order to reduce the influence of high-frequency vibrations;
  • Improvements to the oxidizer pump aimed to reduce cavitation effects;
  • The introduction of destructive tests on a number of components during sampling tests in the engine batches.
  • Testing of the engine for leaks with a mixture of air and helium.

In addition, tougher testing procedures now included live firing of one RD-0212 engine out of each batch of three engines, instead of one of five previously.

The final tune-up test, ZDIs, for the Variant P engines started in April 1967 and inter-agency certification tests, MVI, were completed in August of the same year. The serial production of the engines was initiated at the Voronezh Mechanical Plant, VMZ, where it continues until this day. A team of engineers led by Yu. D. Gorokhov took the job of supervising the serial production of the engine, as well as continuous bench tests and actual flight use of the engines.

The RD-0212 was formally declared operational only in 1978. By 1990s, KBKhA had conducted more than 600 live firings of the engine. As of July 1997, its reliability was estimated at 0.99469.

However improvement to RD-0212 continued, often in the wake of problems experienced by its close cousins on Proton's second stage, which was a source of several failures, including two botched launches in 1999.

Turbopump rotor issue

At least one technical issue was associated primarily with RD-0212. On March 27, 1969, after two failures of the second-stage engines in flight, the RD-0212 engine also malfunctioned as it was firing at full thrust at T+438.66 seconds in flight, resulting in the loss of the first Mars-69 spacecraft. Investigators concluded that due to imbalance of the rotor in the oxidizer pump, its main ball bearing failed. As a result, tougher requirements were introduced for the balancing of the pump rotor. In addition, ball bearings had to be improved along with other upgrades aimed to reduce the pressure on the ball bearings. However, despite continuing launches, the bearings issue was declared fully resolved only in 1982, when the pump was equipped with a special mechanism designed to reduce loads on its rotor. (747)

However, three more failures of the third stage propulsion system took place: on January 18, 1988, on May 16, 2014, and, exactly a year later, on May 16, 2015. Only the latter accident enabled to finally establish that the route cause of all three failures was the imbalance of the rotor shaft in the turbopump of the RD-0214 engine, according to Roskosmos officials. A new round of upgrades was prescribed as a solution.

Specifications of the RD-0212 engine:

-
RD-0213 (main engine)
RD-0214 (steering engine)
Thrust in vacuum
582-593.6 kH (59.36 tons)
30.9-31.5 kH (3.15 tons)
Specific impulse
326.5 seconds
293 seconds
Combustion chamber pressure
14.7 MPa (150 kilograms per square centimeter)
5.49 MPa (54 kilograms per square centimeter)
Absolute pressure at oxidizer injection
0.372-0.686 MPa
-
Absolute pressure at fuel injection
0.152-0.49 MPa
-
Propellant ratio
2.54
2.54
Thrust range
4 percent
-
Burn time
250 seconds
270 seconds
Dry mass
550 kilograms
90 kilograms
Engine length
2,327 millimeters
524 millimeters
Engine diameter
1,470 millimeters
3,780 millimeters
Prototype engine
RD-0206 from UR-200 ICBM
RD-0207 from UR-200 ICBM

 

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The article, graphics and photography by Anatoly Zak; Last update: June 24, 2016

Page editor: Alain Chabot: Last edit: June 7, 2015

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IMAGE ARCHIVE

Gershkovich

A veteran of the KBKhA design bureau since 1945, Yankel Gershkovich led the team of engineers in charge of the RD-0212 engine development. Credit: Roskosmos


UR-200

The propulsion system of the second stage of the UR-200 missile, which became a basis for RD-0212. Click to enlarge. Copyright © 2000 Anatoly Zak


rd0212

RD-0212 engine. Credit: KBKhA


side

RD-0212

A 1-to-5 scale models of the RD-0210/0211 engine (left) for the second stage and RD-0212 for the third stage of the Proton rocket (top and bottom right. Click to enlarge. Copyright © 2011 Anatoly Zak


operational

An operational RD-0212 engine. Credit: GKNPTs Khrunichev


Stage 2

The third stage of the Proton rocket during its assembly in Moscow. Credit: GKNPTs Khrunichev