Publication Date:
2019-06-27
Description:
The combustion characteristics of hypergolic propellants are described. A research project was conducted to determine if the reaction control system engine propellants on Apollo spacecraft undergo explosive reaction when subjected to conditions present in the engine at the time of ignition. Combustion characteristics pertinent to the hard-start phenomenon are considered. The thermal stability of frozen mixtures of hydrazine-based fuels with nitrogen tetroxide was analyzed. Results of the tests are presented in the form of tables and graphs.
Keywords:
PROPULSION SYSTEMS
Type:
NASA-CR-134314
,
BM-IR-1646-VOL-2
Format:
application/pdf