固体运载火箭变轨发动机喷管气流分离研究  

Research for Flow Separating of Solid Launch Vehicle Orbit Maneuver Motor Nozzle

作　　者：周文清 崔建伟 韩小波 朱力 

机构地区：[1]中国航天科工集团第六研究院41所,呼和浩特010010

出　　处：《深空探测学报》2016年第2期181-186,共6页Journal Of Deep Space Exploration

摘　　要：固体运载火箭变轨发动机喷管在工作过程中可能产生气流分离问题,为研究气流分离对喷管性能的影响,开展了理论计算与数值模拟分析。通过分析获得了气流分离点位置、推力系数、喷管壁面的压强、对流换热系数、温度分布。结果表明:地面推力系数是真空推力系数的73.3%,喷管气流分离影响了发动机能量转换;气流分离后喷管壁面压强、对流换热系数、温度存在跃变现象,从而会对喷管扩张段产生不利影响。该分析为进一步研究固体火箭发动机高空喷管通过地面试验性能预示高空性能及喷管扩张段热防护设计提供参考。A researching method for flow separating of solid launch vehicle orbit maneuver motor nozzle is proposed in this paper. The theoretical calculation is carried out for studying the influence of flow separating on the nozzle performance. The numerical simulation analysis is done to obtain the flow separating location,thrust coefficient,wall-surface static pressure,coefficient of convective heat transfer and distribution of temperature field. Results indicate that the ground thrust coefficient is73.3% of the vacuum thrust coefficient for the engine energy conversion efficiency reduced. Parameter jumping caused by flow separation is harmful to nozzle working. Flow separating research based on using the ground test indicating altitude performance of nozzle gives some suggestion of nozzle thermal protection design for reference.

关 键 词：固体运载 火箭发动机 喷管 气流分离 

分 类 号：V19[航空宇航科学与技术—人机与环境工程]