影响超音速分离线喷管流动特性因素的数值研究  

Numerical Investigation on Factors Affecting Flow Structure Characteristics of Supersonic Split Line Nozzle

作　　者：李元 李鑫 李耿 陈林泉 LI Yuan;LI Xin;LI Geng;CHEN Linquan(Xi'an Aerospace Propulsion Technology Institute,Xi'an 710025,China)

机构地区：[1]西安航天动力技术研究所,西安710025

出　　处：《弹箭与制导学报》2022年第2期94-99,共6页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：超音速分离线(SSSL)喷管技术是一种有着良好应用前景的推力矢量技术。由于其结构设计的特点,SSSL喷管在减轻喷管消极质量、结构布局、放大偏转矢量角等方面有着较为明显的优势,并且SSSL喷管内流场的流动特性与传统喷管有显著差异。为研究其流动特性、分析不同因素对内流场流动的影响,文中采用数值仿真的方法,对超音速分离线喷管在不同设计参数下不同摆角的内流场进行计算研究。结果表明:在合理的设计参数范围内,超音速分离线喷管具有偏转放大效应;摆角在0°至5°范围内时,轴向推力系数和侧向推力系数随着摆角的增大而减小;喷管扩张段扩张半角越大,偏转放大效应越好;分离线处扩张比越大,偏转放大效应越好。The supersonic split line(SSSL) nozzle technique is one kind of thrust-vectoring techniques with promising application prospects. Due to the characteristics of its structural design, SSSL nozzle has obvious advantages in reducing the initial mass, compact structure and amplifying the deflection vector angle. In addition, due to its structural characteristics, the flow structure and performance characteristics in SSSL nozzle are significantly different from those in traditional nozzle. In order to study its flow characteristics and analyze the influence of different factors on the internal flow field, the internal flow field of supersonic split line nozzle with different swing angles under different design parameters was calculated and studied by using the method of numerical simulation. Results indicate that the deflection amplification effect of supersonic split line nozzle is true within the reasonable design parameters. The axial thrust coefficient and radial thrust coefficient decrease with the increase of swing angle. The larger the expansion half angle of the nozzle expansion section, the better the deflection amplification effect. The larger the expansion ratio at the split line, the better the deflection amplification effect.

关 键 词：超音速分离线喷管 摆动喷管 推力矢量技术 偏转放大效应 数值仿真 摆动角度 扩张半角 扩张比 

分 类 号：TJ763[兵器科学与技术—武器系统与运用工程] V435[航空宇航科学与技术—航空宇航推进理论与工程]