RD860M
Yuzhnoye Design Bureau
The RD860M is a restartable three-assembly cluster main engine with a pneumatic pump feed system developed by Yuzhnoye SDO for lunar lander propulsion applications. It forms a cluster configuration comprising two stationary engine assemblies DB-1 and DB-3, plus a gimballed assembly DB-2 for combined main thrust and directional control. Burning nitrogen tetroxide and UDMH propellants, […]
Typed specifications7 values
Discloses 5 of 10 fields engineers filter by in this category (category median 3).
- Mass
- 112 kg product page
- Thrust
- 4 903 325 mN product page 2 451 662.5 mN
- Specific impulse
- 322.5 s product page
- Propellant
- NTO (N2O4 or MON) product page UDMH
- TRL
- 6 product page
Each value is typed with its unit and measurement condition and cites the datasheet page it was taken from. Nothing is guessed: a field that is absent here has not been published by the manufacturer. machine-extracted ✓ checked by NewSpace Market ✓ manufacturer confirmed by the manufacturer.
As published by the supplier10 lines, in the manufacturer's own wording
- Propellants
- NT + UDMH
- Vacuum thrust (main mode)
- 0.5 tf
- Vacuum thrust (throttled mode)
- 0.25 tf
- Specific impulse main/throttled (vacuum)
- 322.5 / 316 s
- Propellant mixture ratio
- 2.25
- Configuration
- 3 assemblies: DB-1 (stationary) + DB-2 (gimballed) + DB-3 (stationary)
- Number of starts
- 10 (depends on onboard gas capacity)
- Propulsion system mass (excl. gimbal actuators)
- 112 kg
- Feed system
- Pneumatic pump
- TRL
- 6
About
The RD860M is a restartable three-assembly cluster main engine with a pneumatic pump feed system developed by Yuzhnoye SDO for lunar lander propulsion applications. It forms a cluster configuration comprising two stationary engine assemblies DB-1 and DB-3, plus a gimballed assembly DB-2 for combined main thrust and directional control. Burning nitrogen tetroxide and UDMH propellants, it produces 0.5 tf in main mode and 0.25 tf in throttled mode, with specific impulses of 322.5 and 316 seconds respectively. The system supports up to 10 restarts and is the baseline engine for the medium-class lunar lander concept. Propulsion system mass is 112 kg excluding gimbal actuators. Used on both expendable and reusable lunar lander variants. Technology Readiness Level is 6.
Documentation
No public datasheet yet — request the datasheet / ICD from the supplier.