Liquid-propellant
Liquid-propellant
BURNING HYPERGOLIC PROPELLANTS
ROCKET ENGINES BURNING HYPERGOLIC PROPELLANTS
RD840
RD840
Liquid-propellant
ROCKET ENGINE BURNING HYPERGOLIC PROPELLANTS
DESCRIPTION
The RD840 main rocket engine is intended to be used in space launch vehicle and spacecraft apogee stages.
The engine is one-stage, one-mode, of multiple ignition, with pressurized propellant feed.
FEATURES
| Propellants | NT + UDMH |
| Thrust in vacuum, kgf | 40,7 |
| Specific impulse in vacuum, s | 315 |
| Propellant mixture ratio | 2,05 |
| Combustion chamber pressure, kgf/cm2 | 10 |
| Pressure at nozzle exit section, kgf/cm2 | 0,001 |
| Number of ignitions | 100 |
| Engine operation time, s | 2750 |
| Engine mass, kg | 4,3 |
RD843
RD843
Liquid-propellant
ROCKET ENGINE BURNING HYPERGOLIC PROPELLANTS
DESCRIPTION
The RD843 is a single-chamber, fixed-thrust, restartable, hypergolic-propellant main engine with a pressurized propellant feed system.
The engine is designed to produce thrust and control the pitch and yaw of the LV upper stage in powered flight.
FEATURES
| Propellants | NT + UDMH |
| Thrust in vacuum, tf | 0,25 |
| Specific impulse in vacuum, s | 315,5 |
| Propellant mixture ratio | 2,0 |
| Starts | 8 (number of starts can be increased) |
| Engine weight, kg | 16,5* |
| TRL | 9 |
* not including the weight of gimbal actuators and the frame
RD861K
RD861К
Liquid-propellant
ROCKET ENGINE BURNING HYPERGOLIC PROPELLANTS
DESCRIPTION
The RD861K is a single-chamber restartable main engine with a turbopump feed system. The engine is designed for five starts and uses a gas generator cycle with injecting the exhaust generator gas into the supersonic nozzle section.
The engine is designed to produce thrust and control the pitch and yaw of the Cyclone-4 third stage and the Cyclone-4М second stage in powered flight.
The RD-861K engine is designed as a modification of RD861, a highly reliable, serially produced engine operated in the Cyclone-3 third stage.
FEATURES
| Propellants | NT + UDMH |
| Thrust in vacuum, tf | 7,916 |
| Specific impulse in vacuum, s | 330 |
| Propellant mixture ratio | 2,4 |
| Starts | 5* |
| Engine weight, kg | 214 |
| TRL | 8 |
* the number of starts can be increased by enlarging the LV onboard helium capacity
DU802
DU802
Liquid-propellant
PROPULSION SYSTEM BURNING HYPERGOLIC PROPELLANTS
DESCRIPTION
The DU802 propulsion system with a pneumatic pump feed system was intended for the Krechet autonomous space tug designed for nudging payloads to their desired orbits or trajectories to the Moon.
The propulsion system has a high thrust-to-weight ratio and is capable of operating with multiple starts for 10 days or longer in flight.
FEATURES
| Propellants | NT + UDMH |
| Thrust in vacuum, tf | 0,45 |
| Specific impulse in vacuum, s | 322,5 |
| Propellant mixture ratio | 2,25 |
| Starts | 10* |
| Mass, kg | 165,4 |
| TRL | 7 |
* depends on the onboard gas capacity of the LV stage
BURNING CRYOGENIC PROPELLANTS
RD846V
RD846V
Liquid-propellant
LIQUID ENGINE BURNING CRYOGENIC PROPELLANTS
DESCRIPTION
The RD846V is a single-chamber, fixed-thrust, single-start main engine with an electric pump feed system.
The engine is designed to produce thrust and control the pitch and yaw of the LV upper stage in powered flight.
FEATURES
| Propellants | O2+kerosene |
| Thrust in vacuum, tf | 2,420 |
| Specific impulse in vacuum, s | 341,6 |
| Propellant mixture ratio | 2,5 |
| Starts | 1* |
| Engine weight, kg | 56** |
| TRL | 3 |
* the number of starts can be increased
** including the weight of engine mounts and electrical actuators of pumps, not including the weight of gimbal actuators
RD805
RD805
Liquid-propellant
LIQUID ENGINE BURNING CRYOGENIC PROPELLANTS
DESCRIPTION
The RD805 is a single-chamber, fixed-thrust, single-start, staged combustion main engine with an oxidizer-rich preburner and a turbopump feed system.
The engine is designed to produce thrust and control the pitch and yaw of the LV upper stage in powered flight.
The engine uses the tried-and-tested components of the highly reliable, serially produced steering engine RD-8 operated in the Zenit launch vehicle.
FEATURES
| Propellants | О2+ kerosene |
| Thrust in vacuum, tf | 2,15 |
| Specific impulse in vacuum, s | 345 |
| Propellant mixture ratio | 2,5 |
| Starts | 1 |
| Engine weight, kg | 80* |
| TRL | 4 |
* the weight of gimbal drives is not included
RD809M
RD809M
Liquid-propellant
LIQUID ENGINE BURNING CRYOGENIC PROPELLANTS
DESCRIPTION
The RD809M is a four-chamber, fixed-thrust, single-start, staged combustion main engine with a turbopump feed system.
The engine is designed to produce thrust and control the LV upper stage pitch, yaw, and roll in powered flight by gimballing each engine chamber in one plane.
The engine uses the tried-and-tested components of the highly reliable, serially produced steering engine RD-8 operated in the Zenit launch vehicle.
FEATURES
| Propellants | О2+ kerosene |
| Thrust in vacuum, tf | 9 |
| Specific impulse in vacuum, s | 345 |
| Propellant mixture ratio | 2,5 |
| Starts | 1 |
| Engine weight, kg | 325* |
| TRL | 6 |
* the weight of gimbal drives is not included
RD809K
RD809K
Liquid-propellant
LIQUID ENGINE BURNING CRYOGENIC PROPELLANTS
DESCRIPTION
The RD809K is a restartable, single-chamber, fixed-thrust, staged-combustion main engine with a turbopump feed system.
The engine is designed to produce thrust and control the pitch and yaw of the LV upper stage in powered flight.
The engine uses the tried-and-tested components of the highly reliable, serially produced steering engine RD-8 operated in the Zenit launch vehicle.
FEATURES
| Propellants | О2+ kerosene |
| Thrust in vacuum, tf | 10 |
| Specific impulse in vacuum, s | 352 |
| Propellant mixture ratio | 2,62 |
| Starts | до 4 |
| Engine weight, kg | 330* |
| TRL | 6 |
* the weight of gimbal drives is not included
RD835, RD835T
RD835,
RD835T
Liquid-propellant
LIQUID ENGINE BURNING CRYOGENIC PROPELLANTS
DESCRIPTION
The RD835 and RD835Т are single-chamber, dual-thrust, staged combustion main engines with a turbopump feed system. The engines have a high thrust-to-weight ratio.
The engines are designed to produce thrust and control the pitch and yaw of the advanced launch vehicles such as Mayak developed by Yuzhnoye SDO.
The engines employ the tried-and-tested technologies of the Zenit launch vehicle. The engines can be used for developing the RD836 engine that can be operated in the launch vehicle first stage.
FEATURES
| RD835 | RD835Т | ||
| Propellants | О2+ kerosene | ||
| Thrust in vacuum, tf | 50 | ||
| Specific impulse in vacuum, s | 355 | ||
| Propellant mixture ratio | 2,6 | ||
| Starts | 2 | 1 | |
| Engine weight, kg | 830* | 808* | |
| TRL | 3 |
* the weight of gimbal drives is not included
RD870
RD870
Liquid-propellant
LIQUID ENGINE BURNING CRYOGENIC PROPELLANTS
DESCRIPTION
The RD870 is a single-chamber, dual-thrust, single-start, staged combustion main engine with a turbopump feed system.
The engine is designed to produce thrust and control the pitch and yaw of the Cyclone-4М first stage in powered flight.
The engine employs the tried-and-tested technologies of the Zenit launch vehicle.
FEATURES
| Propellants | О2+ kerosene |
| Thrust at sea level, tf | 79,3 |
| Thrust in vacuum, tf | 89,4 |
| Specific impulse at sea level, s | 301,5 |
| Specific impulse in vacuum, s | 340 |
| Propellant mixture ratio | 2,68 |
| Starts | 1 |
| Engine weight, kg | 1420* |
| TRL | 6 |
* the weight of gimbal drives is not included
RD872
RD872
Liquid-propellant
LIQUID ENGINE BURNING CRYOGENIC PROPELLANTS
DESCRIPTION
The RD872 is a single-chamber, dual-thrust, single-start, staged combustion main engine with a turbopump feed system.
The engine is designed to produce thrust and control the pitch and yaw of the LV upper stage in powered flight.
The engine employs the tried-and-tested technologies of the Zenit launch vehicle.
FEATURES
| Propellants | О2+ kerosene |
| Thrust in vacuum, tf | 93 |
| Specific impulse in vacuum, s | 350,5 |
| Propellant mixture ratio | 2,6 |
| Starts | 1 |
| Engine weight, kg | 1530* |
| TRL | 6 |
* including the weight of engine mounts and gimbal actuators
RD874
RD874
Liquid-propellant
LIQUID ENGINE BURNING CRYOGENIC PROPELLANTS
DESCRIPTION
The RD874 main propulsion system comprises four engines RD870 mounted on the common frame. The RD870 engine is a single-chamber, oxidizer-rich staged combustion engine with a turbopump propellant feed system.
The RD874 main propulsion system is designed for producing thrust and control the roll, pitch, and yaw of the LV first stage during its powered flight.
The RD874 main propulsion system employs the tried-and-tested technologies of the Zenit launch vehicle.
FEATURES
| Propellants: | |
| – oxidizer | Liquid oxygen |
| – fuel | kerosene |
| Nominal thrust, tf | |
| – at sea level | 319,2 |
| – in vacuum | 356,4 |
| Nominal specific impulse, s | |
| – at sea level | 303,2 |
| – in vacuum | 338,7 |
| Nominal propellant mixture ratio | 2,68 |
| Starts | 1 |
| Dry weight, kg | 6070 |
| TRL | 6 |
RD815
RD815
Liquid-propellant
LIQUID ENGINE BURNING CRYOGENIC PROPELLANTS
DESCRIPTION
The RD815 is a single-chamber, dual-thrust, single-start, staged combustion main engine with a turbopump feed system.
The engine is designed to produce thrust and control the pitch and yaw of advanced launch vehicles such as Mayak developed by Yuzhnoye SDO. The engine can be used for developing a family of cluster engines capable of producing 500 to 1000 tf of thrust.
The engine employs the tried-and-tested technologies of the Zenit launch vehicle.
The engine features a high thrust-to-weight ratio.
FEATURES
| Propellants | О2+ kerosene |
| Thrust at sea level, tf | 251,3 |
| Thrust in vacuum, tf | 274,5 |
| Specific impulse at sea level, s | 306,7 |
| Specific impulse in vacuum, s | 335 |
| Propellant mixture ratio | 2,7 |
| Starts | 1 |
| Engine weight, kg | 3200* |
| TRL | 4 |
* including the weight of engine mounts and gimbal actuators
RD880.3
RD880.3
Liquid-propellant
LIQUID ENGINE BURNING CRYOGENIC PROPELLANTS
DESCRIPTION
The RD880.3 is a cluster, single-start, oxidizer-rich staged combustion main engine with a turbopump feed system.
The engine is designed to produce thrust and control the pitch and yaw of the LV first stage in powered flight.
The engine employs the tried-and-tested technologies of the Zenit launch vehicle.
FEATURES
| Propellants | О2+kerosene |
| Thrust at sea level, tf | 502.6 |
| Thrust in vacuum, tf | 549 |
| Specific impulse at sea level, s | 306.7 |
| Specific impulse in vacuum, s | 335 |
| Propellant mixture ratio | 2.7 |
| Starts | 1 |
| Engine weight, kg | 6700* |
| TRL | 4 |
* including the weight of gimbal actuators and the frame
RD882
RD882
Liquid-propellant
LIQUID ENGINE BURNING CRYOGENIC PROPELLANTS
DESCRIPTION
The RD882 is a cluster, single-start, oxidizer-rich staged combustion main engine with a turbopump feed system.
The engine is designed to produce thrust and control the pitch and yaw of the LV first stage in powered flight.
The engine employs the tried-and-tested technologies of the Zenit launch vehicle.
FEATURES
| Propellants | О2+kerosene |
| Thrust at sea level, tf | 1005.2 |
| Thrust in vacuum, tf | 1098 |
| Specific impulse at sea level, s | 306.7 |
| Specific impulse in vacuum, s | 335 |
| Propellant mixture ratio | 2.7 |
| Starts | 1 |
| Engine weight, kg | 12360* |
| TRL | 4 |
* including the weight of gimbal actuators and the frame
RD840
RD840 Liquid-propellant
ROCKET ENGINE BURNING HYPERGOLIC PROPELLANTS
DESCRIPTION
The RD840 main rocket engine is intended to be used in space launch vehicle and spacecraft apogee stages.
The engine is one-stage, one-mode, of multiple ignition, with pressurized propellant feed.
FEATURES
| Propellants | NT + UDMH |
| Vacuum thrust, kgf | 40,7 |
| Specific impulse in vacuum, s | 315 |
| Propellant mixture ratio | 2,05 |
| Combustion chamber pressure, kgf/cm2 | 10 |
| Pressure at nozzle exit section, kgf/cm2 | 0,001 |
| Number of ignitions | 100 |
| Engine operation time, s | 2750 |
| Engine mass, kg | 4,3 |
* not including the weight of gimbal actuators and the frame
RD843
RD843 Liquid-propellant
ROCKET ENGINE BURNING HYPERGOLIC PROPELLANTS
DESCRIPTION
The RD843 is a single-chamber, fixed-thrust, restartable, hypergolic-propellant main engine with a pressurized propellant feed system.
The engine is designed to produce thrust and control the pitch and yaw of the LV upper stage in powered flight.
FEATURES
| Propellants | NT + UDMH |
| Thrust in vacuum, tf | 0,25 |
| Specific impulse in vacuum, s | 315,5 |
| Propellant mixture ratio | 2,0 |
| Starts | 8 (number of starts can be increased) |
| Engine weight, kg | 16,5* |
| TRL | 9 |
* not including the weight of gimbal actuators and the frame
RD861К
RD861К Liquid-propellant
ROCKET ENGINE BURNING HYPERGOLIC PROPELLANTS
DESCRIPTION
The RD861K is a single-chamber restartable main engine with a turbopump feed system. The engine is designed for five starts and uses a gas generator cycle with injecting the exhaust generator gas into the supersonic nozzle section.
The engine is designed to produce thrust and control the pitch and yaw of the Cyclone-4 third stage and the Cyclone-4М second stage in powered flight.
The RD-861K engine is designed as a modification of RD861, a highly reliable, serially produced engine operated in the Cyclone-3 third stage.
FEATURES
| Propellants | NT + UDMH |
| Thrust in vacuum, tf | 7,916 |
| Specific impulse in vacuum, s | 330 |
| Propellant mixture ratio | 2,4 |
| Starts | 5* |
| Engine weight, kg | 214 |
| TRL | 8 |
* the number of starts can be increased by enlarging the LV onboard helium capacity
DU802
DU802 Liquid-propellant
PROPULSION SYSTEM BURNING HYPERGOLIC PROPELLANTS
DESCRIPTION
The DU802 propulsion system with a pneumatic pump feed system was intended for the Krechet autonomous space tug designed for nudging payloads to their desired orbits or trajectories to the Moon.
The propulsion system has a high thrust-to-weight ratio and is capable of operating with multiple starts for 10 days or longer in flight.
FEATURES
| Propellants | NT + UDMH |
| Thrust in vacuum, tf | 0,45 |
| Specific impulse in vacuum, s | 322,5 |
| Propellant mixture ratio | 2,25 |
| Starts | 10* |
| Mass, kg | 165,4 |
| TRL | 7 |
* depends on the onboard gas capacity of the LV stage
LIQUID ENGINES BURNING CRYOGENIC PROPELLANTS
RD846V
RD846V Liquid-propellant
LIQUID ENGINE BURNING CRYOGENIC PROPELLANTS
DESCRIPTION
The RD846V is a single-chamber, fixed-thrust, single-start main engine with an electric pump feed system.
The engine is designed to produce thrust and control the pitch and yaw of the LV upper stage in powered flight.
FEATURES
| Propellants | O2+ kerosene |
| Thrust in vacuum, tf | 2,420 |
| Specific impulse in vacuum, s | 341,6 |
| Propellant mixture ratio | 2,5 |
| Starts | 1* |
| Engine weight, kg | 56** |
| TRL | 3 |
* the number of starts can be increased
** including the weight of engine mounts and electrical actuators of pumps, not including the weight of gimbal actuators
RD805
RD805 Liquid-propellant
LIQUID ENGINE BURNING CRYOGENIC PROPELLANTS
DESCRIPTION
The RD805 is a single-chamber, fixed-thrust, single-start, staged combustion main engine with an oxidizer-rich preburner and a turbopump feed system.
The engine is designed to produce thrust and control the pitch and yaw of the LV upper stage in powered flight.
The engine uses the tried-and-tested components of the highly reliable, serially produced steering engine RD-8 operated in the Zenit launch vehicle.
FEATURES
| Propellants | О2+ kerosene |
| Thrust in vacuum, tf | 2,15 |
| Specific impulse in vacuum, s | 345 |
| Propellant mixture ratio | 2,5 |
| Starts | 1 |
| Engine weight, kg | 80* |
| TRL | 4 |
* the weight of gimbal drives is not included
РД809M
РД809М Рідинний двигун
LIQUID ENGINE BURNING CRYOGENIC PROPELLANTS
DESCRIPTION
The RD809M is a four-chamber, fixed-thrust, single-start, staged combustion main engine with a turbopump feed system.
The engine is designed to produce thrust and control the LV upper stage pitch, yaw, and roll in powered flight by gimballing each engine chamber in one plane.
The engine uses the tried-and-tested components of the highly reliable, serially produced steering engine RD-8 operated in the Zenit launch vehicle.
FEATURES
| Propellants | О2+ kerosene |
| Thrust in vacuum, tf | 9 |
| Specific impulse in vacuum, s | 345 |
| Propellant mixture ratio | 2,5 |
| Starts | 1 |
| Engine weight, kg | 325* |
| TRL | 6 |
* the weight of gimbal drives is not included
RD809K
RD809K Liquid-propellant
LIQUID ENGINE BURNING CRYOGENIC PROPELLANTS
DESCRIPTION
The RD809K is a restartable, single-chamber, fixed-thrust, staged-combustion main engine with a turbopump feed system.
The engine is designed to produce thrust and control the pitch and yaw of the LV upper stage in powered flight.
The engine uses the tried-and-tested components of the highly reliable, serially produced steering engine RD-8 operated in the Zenit launch vehicle.
FEATURES
| Propellants | О2+ kerosene |
| Thrust in vacuum, tf | 10 |
| Specific impulse in vacuum, s | 352 |
| Propellant mixture ratio | 2,62 |
| Starts | до 4 |
| Engine weight, kg | 330* |
| TRL | 6 |
* the weight of gimbal drives is not included
RD835, RD835T
RD835, RD835T
Liquid-propellant
LIQUID ENGINE BURNING CRYOGENIC PROPELLANTS
DESCRIPTION
The RD835 and RD835Т are single-chamber, dual-thrust, staged combustion main engines with a turbopump feed system. The engines have a high thrust-to-weight ratio.
The engines are designed to produce thrust and control the pitch and yaw of the advanced launch vehicles such as Mayak developed by Yuzhnoye SDO.
The engines employ the tried-and-tested technologies of the Zenit launch vehicle. The engines can be used for developing the RD836 engine that can be operated in the launch vehicle first stage.
FEATURES
| RD835 | RD835Т | ||
| Propellants | О2+ kerosene | ||
| Thrust in vacuum, tf | 50 | ||
| Specific impulse in vacuum, s | 355 | ||
| Propellant mixture ratio | 2,6 | ||
| Starts | 2 | 1 | |
| Engine weight, kg | 830* | 808* | |
| TRL | 3 |
* the weight of gimbal drives is not included
RD870
RD870 Liquid-propellant
LIQUID ENGINE BURNING CRYOGENIC PROPELLANTS
DESCRIPTION
The RD870 is a single-chamber, dual-thrust, single-start, staged combustion main engine with a turbopump feed system.
The engine is designed to produce thrust and control the pitch and yaw of the Cyclone-4М first stage in powered flight.
The engine employs the tried-and-tested technologies of the Zenit launch vehicle.
FEATURES
| Propellants | О2+ kerosene |
| Thrust at sea level, tf | 79,3 |
| Thrust in vacuum, tf | 89,4 |
| Specific impulse at sea level, s | 301,5 |
| Specific impulse in vacuum, s | 340 |
| Propellant mixture ratio | 2,68 |
| Starts | 1 |
| Engine weight, kg | 1420* |
| TRL | 6 |
* the weight of gimbal drives is not included
RD872
RD872 Liquid-propellant
LIQUID ENGINE BURNING CRYOGENIC PROPELLANTS
DESCRIPTION
The RD872 is a single-chamber, dual-thrust, single-start, staged combustion main engine with a turbopump feed system.
The engine is designed to produce thrust and control the pitch and yaw of the LV upper stage in powered flight.
The engine employs the tried-and-tested technologies of the Zenit launch vehicle.
FEATURES
| Propellants | О2+ kerosene |
| Thrust in vacuum, tf | 93 |
| Specific impulse in vacuum, s | 350,5 |
| Propellant mixture ratio | 2,6 |
| Starts | 1 |
| Engine weight, kg | 1530* |
| TRL | 6 |
RD874
RD874 Liquid-propellant
LIQUID ENGINE BURNING CRYOGENIC PROPELLANTS
DESCRIPTION
The RD874 main propulsion system comprises four engines RD870 mounted on the common frame. The RD870 engine is a single-chamber, oxidizer-rich staged combustion engine with a turbopump propellant feed system.
The RD874 main propulsion system is designed for producing thrust and control the roll, pitch, and yaw of the LV first stage during its powered flight.
The RD874 main propulsion system employs the tried-and-tested technologies of the Zenit launch vehicle.
FEATURES
| Propellants: | |
| – oxidizer | Liquid oxygen |
| – fuel | kerosene |
| Nominal thrust, tf | |
| – at sea level | 319,2 |
| – in vacuum | 356,4 |
| Nominal specific impulse, s | |
| – at sea level | 303,2 |
| – in vacuum | 338,7 |
| Nominal propellant mixture ratio | 2,68 |
| Starts | 1 |
| Dry weight, kg | 6070 |
| TRL | 6 |
RD815
RD815 Liquid-propellant
LIQUID ENGINE BURNING CRYOGENIC PROPELLANTS
DESCRIPTION
The RD815 is a single-chamber, dual-thrust, single-start, staged combustion main engine with a turbopump feed system.
The engine is designed to produce thrust and control the pitch and yaw of advanced launch vehicles such as Mayak developed by Yuzhnoye SDO. The engine can be used for developing a family of cluster engines capable of producing 500 to 1000 tf of thrust.
The engine employs the tried-and-tested technologies of the Zenit launch vehicle.
The engine features a high thrust-to-weight ratio.
FEATURES
| Propellants | О2+ kerosene |
| Thrust at sea level, tf | 251,3 |
| Thrust in vacuum, tf | 274,5 |
| Specific impulse at sea level, s | 306,7 |
| Specific impulse in vacuum, s | 335 |
| Propellant mixture ratio | 2,7 |
| Starts | 1 |
| Engine weight, kg | 3200* |
| TRL | 4 |
* including the weight of engine mounts and gimbal actuators
RD880.3
RD880.3 Liquid-propellant
LIQUID ENGINES BURNING CRYOGENIC PROPELLANTS
DESCRIPTION
The RD880.3 is a cluster, single-start, oxidizer-rich staged combustion main engine with a turbopump feed system.
The engine is designed to produce thrust and control the pitch and yaw of the LV first stage in powered flight.
The engine employs the tried-and-tested technologies of the Zenit launch vehicle.
FEATURES
| Propellants | О2+kerosene |
| Thrust at sea level, tf | 502.6 |
| Thrust in vacuum, tf | 549 |
| Specific impulse at sea level, s | 306.7 |
| Specific impulse in vacuum, s | 335 |
| Propellant mixture ratio | 2.7 |
| Starts | 1 |
| Engine weight, kg | 6700* |
| TRL | 4 |
* including the weight of gimbal actuators and the frame
RD882
RD882 Liquid-propellant
LIQUID ENGINES BURNING CRYOGENIC PROPELLANTS
DESCRIPTION
The RD882 is a cluster, single-start, oxidizer-rich staged combustion main engine with a turbopump feed system.
The engine is designed to produce thrust and control the pitch and yaw of the LV first stage in powered flight.
The engine employs the tried-and-tested technologies of the Zenit launch vehicle.
FEATURES
| Propellants | О2+kerosene |
| Thrust at sea level, tf | 1005.2 |
| Thrust in vacuum, tf | 1098 |
| Specific impulse at sea level, s | 306.7 |
| Specific impulse in vacuum, s | 335 |
| Propellant mixture ratio | 2.7 |
| Starts | 1 |
| Engine weight, kg | 12360* |
| TRL | 4 |
* including the weight of gimbal actuators and the frame