摘要
针对战术导弹用冲压发动机,提出了一种推力矢量设计方案,即在进气道整流罩底部附设楔形体,利用它的摆动运动,使尾喷气流偏转,产生推力矢量。基于CFD数值模拟,分析了该方案的喷管流动特征,以及飞行马赫数和楔形体偏转角度对推力矢量的影响。计算结果表明,该设计方案可行,且还能适度减小进气道整流罩底阻。
A kind of thrust vector design scheme was put forward for the ramjet of a tactical missile. An additional wedge was set on the bottom of inlet fairing. Swing motion of the wedge can deflect jet flow to provide thrust vector. Based on CFD numerical simulation, flow characteristics of the nozzle in the scheme were analyzed, as well as the effects of flight Mach number and wedged body deflective angle on thrust vector. The results show that the design scheme is feasible, moreover it can moderately reduce base drag of inlet fairing.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2008年第3期228-231,共4页
Journal of Solid Rocket Technology
