附壁射流式姿控发动机推力切换动态响应特性  

Study on Dynamic Switching Characteristics of Wall-attachment Solid Attitude Control Thruster

作　　者：张强 田凌寒 ZHANG Qiang;TIAN Linghan(National Key Laboratory of Combustion,Thermo-structure and Flow,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固体火箭发动机燃烧、热结构与内流场国防科技重点实验室,西安710025

出　　处：《弹箭与制导学报》2020年第5期114-117,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：附壁射流式姿控发动机内流场动态响应过程极其复杂,且难以通过试验获得。利用数值仿真的方法对某附壁射流式姿控发动机推力切换过程中整个内流场的动态特性进行了研究,获得了推力切换动态响应特性。结果表明:推力切换时,阀内附壁侧和分离侧流量比例为6∶1;元件原分离侧形成附壁并发展稳定历时0.15 ms,换向拨片作动时间为0.18 ms;发动机推力切换响应时间为0.3 ms。A computational fluid dynamics(CFD) investigation into the dynamic switching process of a solid attitude control thruster(ACT) with wall attachment theory is conducted. The flow characteristics and the motion of the switching disk are studied. The devolvement process and whole details of the flow are obtained and discussed. The results show that the jet is subsonic in the region below the control arms, and it takes 0.15 ms for the jet to switch from one sidewall to another. Accordingly, the disk motion time is 0.18 ms, thus the entire thrust switching process takes 0.3 ms.

关 键 词：附壁射流 姿控发动机 推力切换 动态响应 

分 类 号：V43[航空宇航科学与技术—航空宇航推进理论与工程]