S5.51
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
The complex plumbing fed numerous smaller attitude control thrusters at the base of the LOK.
Credit: © Mark Wade
Isayev N2O4/UDMH rocket engine. Hardware 1969. Complex engine used to maneuver the LOK to a rendezvous with the LK lander in lunar orbit, then propel the LOK out of lunar orbit. Verniers included for midcourse corrections.
Burn time main/vernier engines 700 + 300 sec. Oxidizer to fuel ratio 1,85 / 1,76.
Chambers: 2 + 1. Throttled thrust(vac): 4.089 kN (919 lbf). Engine: 480 kg (1,050 lb). Thrust to Weight Ratio: 7.05. Oxidizer to Fuel Ratio: 1.85.
Related
- Family
- Storable liquid
- Country
- Russia
- Propellants
- N2O4/UDMH
- Agency
- Isayev bureau
Photo Gallery
S5.51 LOK engine
Side view of the twin-chamber Isayev S5.51 engine used in the Soyuz 7K-LOK lunar orbiter. The two smaller chambers of the S5.52 supplemental engine protude beyond the main engine bells to either side.
Credit: © Mark Wade
