摘要
针对固体火箭发动机气体二次喷射推力矢量控制方案,基于N-S方程和RNGk-ε湍流模型,通过对不同二次喷射工况下的流场进行数值模拟与分析,探索了气体二次喷射位置、喷射流量、喷射角度对推力矢量控制的影响规律。结果表明:喷管二次喷射位置靠近其扩散段中部时,推力矢量控制性能最优,就计算模型而言,侧向力和轴向力之比约达4%;推力矢量控制性能随气体二次喷射流量的增大而提高,但存在临界参数;二次喷射角度对推力矢量控制性能也存在一定影响,但影响效果较弱。的研究结果可为气体二次喷射推力矢量控制系统的研究与设计提供参考。
According to solid rocket motor thrust vector control system with the second gas injection, based on the N - S equation and RNG k- ε turbulence mode, the effect on thrust vector control with the location, the mass rate and angle of the second gas jet flow injection has been explored through numerical simulation and analysis about the different sec- ondary injection conditions. The results show that：the performance of thrust vector control is optimal, when the position of the second injection close to the central of the nozzle dilation section, in this calculational model, the ratio of the lateral thrust and the axial is about 4% ;the performance of thrust vector control improves with the second injection mass rate increasing, but with a critical parameter; the thrust vector control. The results ection thrust vector control system. the angle of the second gas injection can have some influences to the performance in this paper can provide a reference for the research and design on the second gas. injection thrust vector control system.
出处
《航空计算技术》
2009年第4期22-26,共5页
Aeronautical Computing Technique
基金
武器装备预研基金资助项目(9140C5201120801)
关键词
固体火箭发动机
气体二次喷射
推力矢量控制
数值模拟
solid rocket motor
the second gas injection
thrust vector control
numerical simulation
