RD860L
Yuzhnoye Design Bureau
The RD860L is a restartable dual-assembly main engine with a pneumatic pump feed system developed by Yuzhnoye SDO for lunar upper stage and lander propulsion requiring both main thrust and integrated thrust vector control. It comprises a stationary engine assembly DB-1 and a gimballed assembly DB-2 for directional control. The system applies tried-and-tested technologies from […]
Key figurescomparable across the catalogue
- Mass
- 106 kg
- Thrust
- 1 N
- Specific impulse
- 316 s
- TRL
- 6
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 (main mode)
- 1 tf
- Vacuum Thrust (throttled mode)
- 0.25 tf
- Specific Impulse main/throttled (vacuum)
- 322.5 / 316 s
- Propellant Mixture Ratio
- 2.25
- Configuration
- Two assemblies: DB-1 (stationary) + DB-2 (gimballed)
- Number of Starts
- 10 (depends on onboard gas capacity)
- Engine Weight (excl. gimbal actuators)
- 106 kg
- Feed System
- Pneumatic pump
- TRL
- 6
About
The RD860L is a restartable dual-assembly main engine with a pneumatic pump feed system developed by Yuzhnoye SDO for lunar upper stage and lander propulsion requiring both main thrust and integrated thrust vector control. It comprises a stationary engine assembly DB-1 and a gimballed assembly DB-2 for directional control. The system applies tried-and-tested technologies from earlier propulsion systems and burns nitrogen tetroxide and UDMH propellants. It produces 1 tf of vacuum thrust at the main operating mode and 0.25 tf in throttled mode, with specific impulses of 322.5 and 316 seconds respectively. Up to 10 restarts are supported. The engine weighs 106 kg excluding gimbal actuators. Technology Readiness Level is 6, confirming demonstration in a relevant environment.
Documentation
No public datasheet yet — request the datasheet / ICD from the supplier.