LONG-RUN TESTING OF MODEL NOZZLE EXTENSIONS MADE OF A CARBON-CARBON COMPOSITE MATERIAL IN A LIQUID-PROPELLANT ROCKET ENGINE OPERATING ON HYDROGEN AND OXYGEN

摘要

Results of a series of firing tests of two model nozzle extensions made of a carbon-carbon composite material are reported. This material can be used to fabricate nozzle extensions for a large-scale liquid-propellant rocket engine. The tests are performed in an experimental setup operating on oxygen and hydrogen. It is shown that the thermochemical loads on the nozzle material in model tests are greater than those under real conditions. The temperature of the outer surface of the nozzle extension is measured in each experiment by thermocouples and an infrared imager. The level of wall material ablation during the entire test period is determined. It is demonstrated that the results of firing tests can be used for estimating the operation performance of a large-scale engine. A simple analytical dependence is derived for recalculating the results of model tests on material ablation to full-scale conditions.