Combustion Characteristics Experimental Study of Solid Hydrocarbon Propellant for Air-Turbo Rocket

摘要

The combustion characteristics of propellants heavily affect the performance of solid-propellant air-turbo rockets(SP-ATRs). In this study,an SP-ATR experimental combustion system was developed,and experimental studies wereconducted on the primary and secondary combustion characteristics of two solid hydrocarbon fuel propellants.The results show that the solid hydrocarbon fuel-rich propellant,which is an ideal propellant for SP-ATRs,can playthe dual role of driving the turbines and executing secondary combustion. The studies on the two candidatepropellants show that CHOI has higher energy characteristics,and CH02 exhibits better performance in terms of theinterior ballistic stability and ejection efliciency. For cold inflow conditions,when the fuel gas flow rate is at theoptimum equivalence ratio,there are difficulties in secondary combustion. A combustion experiment with a variablegas flow rate was designed,and the upper limit of the excess air coefficient was obtained under the condition of coldinflow.