固体推进剂吸气式涡轮火箭发动机的建模及特征研究

Study on modeling and features of solid propellant air-turbo-rocket

建立了固体推进剂吸气式涡轮火箭发动机的设计状态数学模型,提出了燃烧室燃气与空气配比的关系,分析了压气机增压比、涡轮进口燃气总温和涡轮落压比对燃烧室油气比的影响,以及固体推进剂吸气式涡轮火箭发动机的设计特点。基于涡轮压气机功率平衡条件、静压相等的掺混条件和尾喷管流量匹配条件,建立了固体推进剂吸气式涡轮火箭发动机的非设计状态数学模型。

A mathematical model for performance calculation of solid propellant air-turbo-rocket in design state was derived, and a relationship of fuel-air ratio in the chamber was put forward. The effects of compressor pressure ratio, turbine inlet fuel total temperature and turbine expansion ratio on the fuel-air ratio together with the design features of solid propellant air-turbo-rocket were analyzed. Based on the power balance condition of compressor and turbine, the mixing condition of eqivalent static pressure and the flow matching condition of the blast tube, a mathematical model for performance calculation of solid propellant air-turbo-rocket in off-design state was deduced.