固体火箭发动机流体喉部推力矢量特性

针对采用水作为二次流工质的流体喉部进行了冷流实验及数值模拟研究.研究了该种固体火箭发动机流体喉部的一般规律，包括不同二次流射流方式，不同二次流流量下流体喉部的扼流性能，推力偏角及推力效率，数值模拟及实验结果吻合较好.结果表明:扼流性能与二次流的注射位置、注射角度及流量比有关，且随二次流/主流流量比的增大而增大.喉部二次流喷射能有效的调节有效喉部面积进而调节推力大小，当流量比为0.4时，最大有效喉部面积比为0.8；扩张段二次流喷射能有效调节推力方向，当流量比为0.4时，最大推力偏角为20°；喉部二次流与扩张段二次流入射位置存在相位差可有效降低喉部与扩张段二次流干扰. 

Thrust vectoring features about fluidic throat for solid rocket motor

A cold-flow experiment and numerical simulation research were performed on the fluidic throat using water as working fluid. The general rules of the fluidic throat for solid rocket motor were studied, including the injection styles choke performance, the thrust angle and the thrust performance of the fluidic throat under different conditions of secondary flow injection styles and secondary flow ratio. Numerical simulations were in good agreement with experimental results. Results show that, the choke performance is related to the point, angle and flow ratio of secondary injection. Meanwhile, the choke performance will be better with the increase of the flow ratio of the secondary flow and main flow. Secondary injection of the nozzle throat can effectively regulate the effective throat area which contributes to the thrust magnitude. When the flow ratio is 0.4, the maximum effective throat area ratio is 0.8. Secondary injection at the divergent section can regulate the thrust direction effectively. When the flow ratio is 0.4, the maximum thrust angle is 20°. The phase difference of the throat injection and divergent section injection is used for reducing the interference from throat and divergent segment.