摘要
为了获得涡流阀参数对发动机推力调节性能的影响规律,针对涡流阀的加注方式以及几何结构,利用建立的基于涡流阀方案的固体火箭发动机推力可调实验系统开展了实验研究。通过实验结果的分析,得到了加注环孔径、涡流室高度和直径以及中心进气面积的不同对涡流阀调节性能的影响规律。结果表明:适当降低涡流室的高度、较大的中心进气面积、较大的涡流室直径有利于提高涡流阀的调节性能。因此,可以通过对涡流阀结构的优化设计来提高发动机的推力调节性能。
A series of researches were experimentally investigated to study the influences of vortex valve geometry parameters on thrust modulation. The experimental system of thrust modulation SRM based on vortex valve is established. The influences of diameter of the injection ring, height and diameter of the vortex chamber as well as area of the gas passage on thrust modulation performance are obtained. The experimental results show that the modulation performance of vortex valve can be improved by reducing the height of vortex chamber appropriately and by using larger area of the gas passage as well as by using greater diameter of the vortex chamber. Thus, thrust modulation performance of SRM can be improved through optimizing vortex valve geometry parameters.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2007年第4期352-355,共4页
Journal of Propulsion Technology
