变控制流供应角度涡流阀固体变推力火箭发动机调节方案  

Variable control flow supply angle regulation scheme of vortex valve solid rocket motor thrust modulation

作　　者：魏祥庚[1] 李江[1] 陈剑[1] 侯廉 

机构地区：[1]西北工业大学燃烧热结构与内流场重点实验室,西安710072

出　　处：《航空动力学报》2017年第11期2737-2742,共6页Journal of Aerospace Power

摘　　要：针对涡流阀变推力发动机变控制流供应角度方案,开展了发动机工作特性的数值模拟及实验研究。数值研究结果表明:采用变控制流供应角度可以很好地实现涡流阀变推力发动机的推力调节;涡流阀最大推力调节比超出加质发动机调节比26%;调节比随着控制流供应角度的减小而增大。实验结果表明:变控制流供应角度方案可行,验证了"气-气"调节的优越性。变控制流供应角度涡流阀固体变推力发动机为实现固体发动机推力调节提供了一种技术途径。Numerical calculation and experimental study on the performance of the variable control flow supply angle regulation scheme of vortex valve solid rocket motor were carried out.Numerical results showed that the variable control flow supply angle regulation scheme can be used to achieve a very good performance,the maximum thrust regulation ratio of the vortex valve solid rocket motor exceeded that of the straight mass augmentation motor by 26%,and the pressure ratio increased with the decrease of the control flow supply angle.Experimental results showed that the variable control flow supply angle regulation scheme was feasible and the superiority of＂gas-gas＂regulation was verified.The variable control flow supply angle regulation scheme provided a technical approach for the realization of thrust regulation of solid rocket motor.

关 键 词：固体火箭发动机 推力调节 涡流阀 控制流 角度调节 

分 类 号：V435.23[航空宇航科学与技术—航空宇航推进理论与工程]