RD840
Yuzhnoye Design Bureau
The RD840 is a liquid-propellant low-thrust engine developed by Yuzhnoye SDO, intended for use in space launch vehicle apogee stages and spacecraft orbital maneuvering systems. It operates on nitrogen tetroxide and unsymmetrical dimethylhydrazine (UDMH) propellants with a pressurized feed system, and is capable of up to 100 restarts over a total operational time of 2,750 […]
Key figurescomparable across the catalogue
- Mass
- 4.3 kg
- Thrust
- 40.7 N
- Specific impulse
- 315 s
Normalised to common units so this product can be compared with others in its category. The supplier's own wording is below.
As published by the supplier
- Propellants
- NT + UDMH
- Vacuum Thrust
- 40.7 kgf
- Specific Impulse (vacuum)
- 315 s
- Propellant Mixture Ratio
- 2.05
- Chamber Pressure
- 10 kgf/cm2
- Number of Ignitions
- 100
- Total Operation Time
- 2,750 s
- Engine Mass
- 4.3 kg
- Feed System
- Pressurized
About
The RD840 is a liquid-propellant low-thrust engine developed by Yuzhnoye SDO, intended for use in space launch vehicle apogee stages and spacecraft orbital maneuvering systems. It operates on nitrogen tetroxide and unsymmetrical dimethylhydrazine (UDMH) propellants with a pressurized feed system, and is capable of up to 100 restarts over a total operational time of 2,750 seconds, making it ideal for multi-burn mission profiles such as apogee kick maneuvers, orbit raising, and station-keeping. The engine produces 40.7 kgf of vacuum thrust with a specific impulse of 315 seconds. Its lightweight design at 4.3 kg makes it suitable for small spacecraft and upper stage applications. It is used as the lunar lander propulsion engine in Yuzhnoye’s light-class and flying lunar lander concepts.
Documentation
No public datasheet yet — request the datasheet / ICD from the supplier.