Nozzle extension made from carbon-carbon composite for the 11Д58M engine

Cooperative work is performed by the following institutions:

FSUE "Keldysh Research Center"- scientific supervision of the problem.
R&SC "Energia"- manufacture of the 11Д58M engine and conductance of firing tests.
NPO "Iskra"- delivery of radiation-cooled nozzle extension.
TsNIISM- development and application of antioxidation coating.


Main technical data of 11Д58M engine:
Propellants: oxygen + naphthyl.
Combustion chamber pressure: 75... 80 kg/cm²,
Operation time: up to 1200 s.
Nozzle throat diameter: 84 mm.
Nozzle expansion ratio: 184
Length of radiation-cooled nozzle extension: 700 mm.

Calculation and experimental studies of operability of the nozzle extension made from Grauris carbon-carbon composite as applied to the 11Д58M engine

On June 10, 2003 the Zenit-SL rocket was successfully launched with the 11Д58M engine built up with a radiation-cooled nozzle extension made from the Grauris carbon-carbon composite material.