RD835 / RD835T
Yuzhnoye Design Bureau
The RD835 and RD835T are dual-thrust staged combustion cryogenic rocket engines developed by Yuzhnoye SDO with a high thrust-to-weight ratio, designed for advanced Mayak family launch vehicles. Both variants utilize proven Zenit launch vehicle technology and burn liquid oxygen and kerosene propellants, each producing 50 tf of vacuum thrust with a high specific impulse of […]
Key figurescomparable across the catalogue
- Mass
- 830 kg
- Thrust
- 50 N
- Specific impulse
- 355 s
- TRL
- 3
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
- Vacuum Thrust
- 50 tf
- Specific Impulse (vacuum)
- 355 s
- Propellant Mixture Ratio
- 2.6
- Number of Starts (RD835)
- 2
- Number of Starts (RD835T)
- 1
- Engine Weight RD835 (excl. gimbal drives)
- 830 kg
- Engine Weight RD835T (excl. gimbal drives)
- 808 kg
- Cycle
- Staged combustion
- TRL
- 3
About
The RD835 and RD835T are dual-thrust staged combustion cryogenic rocket engines developed by Yuzhnoye SDO with a high thrust-to-weight ratio, designed for advanced Mayak family launch vehicles. Both variants utilize proven Zenit launch vehicle technology and burn liquid oxygen and kerosene propellants, each producing 50 tf of vacuum thrust with a high specific impulse of 355 seconds. The RD835 supports 2 restarts for recoverable first stage applications while the RD835T is single-start for expendable use. The RD835 weighs 830 kg and the RD835T weighs 808 kg (both excluding gimbal drives). These engines are planned to form clustered assemblies capable of producing 500 to 1000 tf of combined thrust for heavy and super-heavy Mayak first stage propulsion. Currently at Technology Readiness Level 3.
Documentation
No public datasheet yet — request the datasheet / ICD from the supplier.