RD815
Yuzhnoye Design Bureau
The RD815 is a single-chamber dual-thrust staged combustion cryogenic rocket engine developed by Yuzhnoye SDO as the core propulsion element for the advanced Mayak family of heavy and super heavy-lift launch vehicles. Burning liquid oxygen and kerosene, it produces 251.3 tf of sea-level thrust and 274.5 tf of vacuum thrust, with specific impulses of 306.7 […]
Key figurescomparable across the catalogue
- Mass
- 3,200 kg
- Thrust
- 251.3 N
- Specific impulse
- 306.7 s
- TRL
- 4
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
- O2 + kerosene
- Sea Level Thrust
- 251.3 tf
- Vacuum Thrust
- 274.5 tf
- Specific Impulse (sea level)
- 306.7 s
- Specific Impulse (vacuum)
- 335 s
- Propellant Mixture Ratio
- 2.7
- Number of Starts
- 1
- Engine Weight (incl. mounts and gimbal actuators)
- 3,200 kg
- Cycle
- Staged combustion, dual-thrust
- TRL
- 4
About
The RD815 is a single-chamber dual-thrust staged combustion cryogenic rocket engine developed by Yuzhnoye SDO as the core propulsion element for the advanced Mayak family of heavy and super heavy-lift launch vehicles. Burning liquid oxygen and kerosene, it produces 251.3 tf of sea-level thrust and 274.5 tf of vacuum thrust, with specific impulses of 306.7 seconds at sea level and 335 seconds in vacuum. Multiple RD815 engines are clustered across the Mayak variants: 3 engines on Mayak-M-3.9 core, up to 18 booster engines plus 3 core engines on Mayak-SH-7, creating combined sea-level thrusts ranging from ~754 tf to ~5,278 tf. The engine weighs 3,200 kg including mounts and gimbal actuators. Currently at Technology Readiness Level 4, it is under active development.
Documentation
No public datasheet yet — request the datasheet / ICD from the supplier.