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

作　　者：屠秋野[1] 陈玉春[1] 苏三买[1] 蔡元虎[1] 蹇泽群[2] 

机构地区：[1]西北工业大学动力与能源学院,西安710072 [2]中国航天科技集团公司四院,西安710025

出　　处：《固体火箭技术》2006年第5期317-319,345,共4页Journal of Solid Rocket Technology

基　　金：西北工业大学"英才培养计划"基金项目(04XD0103)

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。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.

关 键 词：固体推进剂吸气式涡轮火箭发动机 设计状态 非设计状态 数学模型 

分 类 号：V438[航空宇航科学与技术—航空宇航推进理论与工程]