非对称方形尾喷管内流场数值分析与推力特性研究  

Numerical Analysis on Inner Flow Field and Thrust Speciality Research of the Asymmetry Quadrate Nozzle

作　　者：冯喜平[1] 秦延涵[1] 李进贤[1] 赵胜海[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《弹箭与制导学报》2009年第6期149-151,154,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：文中建立了非对称方形尾喷管及传统轴对称尾喷管的物理数学模型,基于N-S方程和RNGk-ε湍流模型,对两种尾喷管三维内流场进行了数值分析,研究了非对称方形尾喷管内部流动参数的变化趋势及其推力特性。结果表明:在相同收敛段、喷管长度和扩张比的条件下,两种喷管内的流动参数变化趋势一致与轴对称喷管相比,非对称方形尾喷管推力略低,但能够保证喷管的推力性能水平。physical and numerical models were establishedased on N-S control equations and RNG κ-ε turbulence model, the interior flow fields of the nozzles were analyzed through numerical method, both the flow parameters change trend and thrust speciality of the asymmetry quadrate nozzle were researched. The results show that, with the same constrin- gency segment, nozzle length and expansion ratio, the change trend of flow parameters is consistent both the nozzles, and the asymmetry quadrate nozzle has the lower thrust compared with the axial-symmetry nozzlebut the level of its thrust performance can be ensured.

关 键 词：固体火箭发动机 非对称方形尾喷管 数值模拟 推力特性 

分 类 号：V435.23[航空宇航科学与技术—航空宇航推进理论与工程]