This research is concerned with the details of rocket combustion processes and how fundamental physical, chemical and aerodynamic approaches give insight to these details. These fundamental approaches are oriented to give specific basic knowledge about combustion instability in rockets and the important parameters which govern such instabilities; and about chemical kinetic aspects of propellant systems and the relationship of kinetics to the over-all combustion process, instability problem, propellant sensitivity, etc. One aspect is directed towards understanding the gas phase contribution to high-frequency combustion instability. The investigation employs rockets using premixed gaseous propellants and a non-linear shock wave instability analysis. These 'gas rockets' eliminate those phenomena peculiar to condensed phase systems and thus the instabilities can be attributed to gas phase phenomena, mainly chemical kinetics. Another aspect seeks to understand the high temperature homogeneous gas phase reaction kinetics of propellants. (Author)
Combustion Processes in Liquid Propellant Rocket Motors
1969
42 pages
Report
Keine Angabe
Englisch
Combustion & Ignition , Rocket Engines & Motors , Liquid propellant rocket engines , Combustion , Stability , Reaction kinetics , Decomposition , Adiabatic gas flow , Liquid rocket oxidizers , Liquid rocket fuels , Hypergolic rocket propellants , Hydrazine , Nitrogen oxides , Heat of reaction , Oxidation , Gaseous rocket propellants , Chemical reactions , Instability