【摘要】 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。更多还原

【Abstract】 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.更多还原