RD860
Yuzhnoye Design Bureau
The RD860 is a single-chamber, restartable main engine with a pneumatic pump feed system developed by Yuzhnoye SDO for thrust production and flight control of upper stages, space tugs, and lunar landing modules. It burns nitrogen tetroxide and UDMH propellants with two throttle levels: a main mode at 0.5 tf vacuum thrust and a throttled […]
Key figurescomparable across the catalogue
- Mass
- 34 kg
- Thrust
- 0.5 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)
- 0.5 tf
- Vacuum Thrust (throttled mode)
- 0.25 tf
- Specific Impulse main/throttled (vacuum)
- 322.5 / 316 s
- Propellant Mixture Ratio
- 2.25
- Number of Starts
- 10 (depends on onboard gas capacity)
- Engine Weight (excl. gimbal actuators)
- 34 kg
- Feed System
- Pneumatic pump
- TRL
- 6
About
The RD860 is a single-chamber, restartable main engine with a pneumatic pump feed system developed by Yuzhnoye SDO for thrust production and flight control of upper stages, space tugs, and lunar landing modules. It burns nitrogen tetroxide and UDMH propellants with two throttle levels: a main mode at 0.5 tf vacuum thrust and a throttled mode at 0.25 tf, achieving specific impulses of 322.5 and 316 seconds respectively. The engine supports up to 10 restarts (dependent on onboard gas supply), making it well-suited for multi-burn lunar orbital insertion, descent initiation, and landing maneuvers. Technology Readiness Level of 6 confirms demonstration in a relevant environment. Engine weight is 34 kg excluding gimbal actuators, making it a compact and capable lunar propulsion solution.
Documentation
No public datasheet yet — request the datasheet / ICD from the supplier.