Vladimir Bodrov
RD-276
RD-276
The most powerful single-chamber LRE, running on high-boiling fuel components.
RD-191
RD-191
Liquid rocket engine with afterburning of oxidizing gas
Liquid rocket engine with afterburning of oxidizing gas
Fuel: Oxygen + kerosene
Modifications of the RD-191 engine
Development period 1999-2011
Purpose of the Angara PH
Number and period of launches 2 launches in 2014
The main stages of the RD-191 program
Conclusion of a contract with GKNPC im. Khrunicheva – 31.12.1998.
The development of design documentation was completed in 1999.
A mock-up was made for the Angara launch vehicle - March 1999.
The first fire test of RD-191 – July 27, 2001
RD-191 certification was completed in May 2011.
MVSK83
MVSK83
Corrective-braking engine
Technical specifications
Corrective-braking engine (GTD)
Fuel: NDMG/ATIN
Function
Creation of a multiple force pulse in the process of orientation and stabilization of the spacecraft by commands received from the quality management system.
Application
Reactive control system of automatic spacecraft.
Design features
A four-chamber engine based on four LRE DMT 11D428A-24, integrated into a common fuel component supply system and rigidly mounted on a bracket.
The level of development
The letter "O". Flight operation
MVSK83
Russian space rocket adjustment and braking engine to provide center of mass velocity variation during spacecraftorbit correction and spacecraft deceleration
RDMT17D58E
RDMT17D58E
Low-thrust rocket engine
Technical specifications
Two-component low-thrust rocket engine
Fuel: NDMG/ATIN
Function
Creation of a multiple force pulse in the process of orientation and stabilization of the spacecraft by commands received from the quality management system.
Application
By the beginning of 2015, 1,385 engines of this type were operated as part of the Almaz orbital station, the Briz upper stage, the retrofitting modules of the Mir orbital station – Kvant-2, Kristall, Spectrum, Nature, the first Russian Zarya module of the International Space Station and the upper stage of the Strela launch vehicle.
The level of development
The letter "O". Flight operation
RDMT17D58E
Low-thrust rocket engine
RDMT11D458
RDMT11D458
Low-thrust engines
Technical specifications
Two-component low-thrust rocket engine
Fuel: NDMG/ATIN
Function
Creation of a multiple force pulse in the process of orientation and stabilization of the spacecraft by commands received from the quality management system.
Application
The Almaz and Mir orbital stations (Kvant, Kristall, Spectrum, and Nature modules), the Zarya module of the International Space Station, and the Briz upper stage.
The level of development
The letter "O". Flight operation
RDMT11D458
Low-thrust Russian spacecraft engines
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Bankera
RDMT-11D428A-16
RDMT-11D428A-16
Low-thrust rocket engine
Technical specifications
Two-component low-thrust rocket engine
Fuel: NDMG/ATIN
Function
Creation of a multiple force pulse during the orientation and stabilization of the spacecraft by commands received from the quality management system.
Application
By the beginning of 2015, 2,643 engines of this type provided successful flights of Soyuz-TM and Progress-M transport ships. The engine is used in the Zvezda service module of the International Space Station.
Design features
Nozzle made of heat-resistant niobium alloy with heat-resistant silicide coating
The level of development
The letter "O1". Flight operation
RDMT-11D428A-16
Low-thrust rocket engine
RD-0120
RD-0120
Rocket engine
liquidLiquid propellant rocket engine powered by liquid hydrogen and liquid oxygen.
The engine with the highest specific characteristics among the engines of its class. Certified for 6 inclusions. Demonstrated the ability to work on throttled up to 25% of the nominal mode. The achieved high technical performance of the feed units made it possible to ensure the operability of the system at relatively low temperatures of the generator gas. For the first time in the manufacture of engine elements, the granule technology for obtaining blanks of parts was used.
2022
The launch of the RN Energia with the Buran orbital aircraft was carried
1987
The first launch of the RN Energia with a payload layout was carried
1986
The first fire test of RD-0120 took place
1978
The first engine entered the test stand in the fall
1976
The development of the RD-0120 KBHA began.
RD-0146/0146D
RD-0146/0146D
Rocket engine.
liquidLiquid propellant rocket engine without gas generator.
The first engine in Russia, made according to a non-generator scheme. The world's first LRE, made according to an independent two-shaft fuel component supply scheme with sequential gas supply to turbines. This circumstance made it possible to demonstrate the efficiency of the feed system with optimal characteristics of the units. The engine consists of low-speed pre-pumps that ensure the engine's performance at low tank pressures of the components.
RD-0146/RD-0146D Engine Modernization Program.
In 1997, according to the technical task of the Khrunichev State Research and Development Center, the RD-0146 with a high-altitude nozzle was started for promising variants of the Proton and Angara rocket launchers.
A mock-up of the RD-0146 engine was demonstrated at the Aerospace 2000 exhibition.
In 2001, one of the copies of RD-0146 was sent to Pratt-Whitney by agreement.
Since 2008, KBHA has been developing the RD-0146D oxygen-hydrogen main engine for use in the upper stage of the heavy class of the Angara-A5 PH. RD-0146D has the ability to switch on multiple times during the flight. The engine includes an uncooled nozzle consisting of stationary and moving parts.
RD-0124/0124A
RD-0124/0124A
Rocket engine.
Four-chamber liquid-propellant rocket engine powered by kerosene and liquid oxygen.
The record holder among all oxygen-kerosene rocket engines in the world in terms of specific thrust impulse (efficiency), providing the maximum possible energy characteristics of the PH stage on these fuel components. It is distinguished by highly efficient systems of mixing in the combustion chamber, cooling of the combustion chamber, stability of start-up parameters.
Engines for the upper stages of the Soyuz-2 launch vehicle, the Angara launch vehicle.
THE MAIN PARAMETERS OF THE RD-0124A ENGINE FAMILY
four-chamber liquid-propellantLiquid rocket engine poweredwith byafterburning keroseneof andoxidizing liquidgenerator oxygengas.
Fuel: Oxygen + naphthyl
RD-0124 / RD-0124A Engine Modernization Program
In 1993, according to the Terms of Reference of the GNPRCC "TSSKB-Progress" (now RCC "Progress") and a contract with the Russian Space Agency, work began on the creation of the RD-0124 main engine of the third stage of the upgraded Soyuz-2 launch vehicle.
The peculiarity of this engine is to start without pre-cooling the structure and cavities of the cryogenic component - liquid oxygen, which is especially important for engines with reusable activation.
In 2006, the first flight tests took place as part of the Soyuz-2.1B launch vehicle.
By the end of 2015, 28 flights of the Soyuz-2.1b, Soyuz-STB and Soyuz-2.1v rocket engines with RD-0124 were carried out.
In 1998, the technical design of the RD-0124A engine for the Angara launch vehicle was developed by KBHA according to the TK of the Salyut Design Bureau.
RD-0124A is developed on the basis of the RD-0124 engine, but it has a number of technical features, for example, in terms of fuel selection to control the deviation of the CS, ensuring the pressurization of tanks, and also differs in increased operating time in flight.
2014
RD-107/108liquidLiquid propellant rocket engine designed for the world's first intercontinental ballistic missile R-7.
The development of engines for the first intercontinental ballistic missile R-7 and the family of space launch vehicles "Vostok", "Voskhod", "Lightning", "Soyuz" began in 1954. The creation of such four-chamber oxygen-kerosene engines with steering chambers for controlling the flight of the rocket required solving a number of complex scientific and technical problems.
The engines provided the successful flight of the first intercontinental ballistic missile in August 1957, the launch of the first artificial Earth satellite in October 1957, and the flight of the first man into space in April 1961.
With the help of engines of the RD-107 and RD-108 family developed by NPO Energomash, the implementation of the domestic manned flight program has been reliably ensured to date.
To date, work has been carried out to modernize the basic RD-107 engines for the first stage and RD-108 engines for the second stage - 18 modifications for various programs.
Serial production of engines is carried out in Samara under the supervision of the Volga branch of NPO Energomash.
113 launches of Soyuz-FG and Soyuz-2 rocket launchers with RD-107A and RD-108A engines were carried out, including 42 manned (as of June 30, 2016)
October 30, 2002
The first manned launch
March 21, 2001
The first launch of a rocket launcher with RD-107A and RD-108A rocket engines with the withdrawal of the Progress spacecraft
RD-107/108
Rocket engine
NPO Energomash named after Academician V. P. Glushko was edited by
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